ARM_A318_A319_A320_A321_20090701

@AIRBUS A318/A319/A320/A321

AIRCRAFT RECOVERY MANUAL

ARM

The content of this document is the property of Airbus. It is supplied in confidence and commercial security on its contents must be maintained. It must not be used for any purpose other than that for which it is supplied, nor may information contained in it be disclosed to unauthorized persons. It must not be reproduced in whole or in part without permission in writing from the owners of the copyright. Requests for reproduction of any data in this document and the media authorized for it must be addressed to Airbus. © AIRBUS S.A.S. 2005. All rights reserved.

AIRBUS S.A.S. Customer Services Technical Data Support and Services 31707 Blagnac Cedex FRANCE

Issue: Jun 01/08

Rev: Jul 01/09

@A318/A319/A320/A321 AIRCRAFT RECOVERY MANUAL

HIGHLIGHTS Revision No. 2 - Jul 01/09 LOCATIONS

CHG CODE

DESCRIPTIONS OF CHANGE

CHAPTER 01 Subject 01-20-01 DESC 01-20-01-002-A01

R


R

UPDATED DEFINITION OF SECONDARY DAMAGE

TASK 02-30-01-200-801-A01

R

CROSS REFERENCED DOCUMENTARY UNIT ADDED/REVISED/DELETED

TASK 02-30-01-481-801-A01

R

TOOL P/N AND/OR DESIGNATION ADDED/REVISED/DELETED

TASK 02-30-01-867-802-A01

R

TOOL P/N AND/OR DESIGNATION ADDED/REVISED/DELETED

Subject 02-30-01

CHAPTER 03 Subject 03-00-00 TASK 03-00-00-558-801-A01 FIGURE 03-00-00-991-002-D01 Subject 03-20-02

R R

TASK 03-20-02-970-801-A01

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UPDATED AMM TASK CROSS REFERENCED MANUAL(S) ADDED/REVISED/DELETED

TASK 03-50-01-558-809-A01 TASK 03-50-01-558-811-A01

R R

TASK 03-50-01-558-811-B01

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ADDED CAPACITY DATA IN THE TABLE ADDED NOTE AND CORRECTIVE CLERICAL ERROR NOTE AMENDED ADDED NOTE AND CORRECTIVE CLERICAL ERROR NOTE AMENDED

Subject 03-50-01

HIGHLIGHTS Page 1 Jul 01/09


LOCATIONS TASK 03-50-01-558-811-C01

CHG CODE R

DESCRIPTIONS OF CHANGE ADDED NOTE AND CORRECTIVE CLERICAL ERROR NOTE AMENDED

Subject 03-60-01 DESC 03-60-01-001-A01

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CHAPTER 04 Subject 04-20-00 TASK 04-20-00-588-801-A01 Subtask 04-20-00-588-001-A01 FIGURE 04-20-00-991-001-A01 FIGURE 04-20-00-991-001-B01 FIGURE 04-20-00-991-001-C01 FIGURE 04-20-00-991-001-D01

R R N N N N

ILLUSTRATION ILLUSTRATION ILLUSTRATION ILLUSTRATION

ADDED ADDED ADDED ADDED

CHAPTER 05 Subject 05-40-02 TASK 05-40-02-650-801-A01

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WARNING CAUTION ADDED/REVISED/DELETED

CHAPTER 06 Subject 06-00-00 DESC 06-00-00-002-A01 FIGURE 06-00-00-991-001-A01 FIGURE 06-00-00-991-001-B01 FIGURE 06-00-00-991-001-C01 Subject 06-10-00

N N N N

TASK 06-10-00-970-801-A01 TASK 06-10-00-970-803-A01 Subject 06-30-00

R R

ILLUSTRATION ADDED ILLUSTRATION ADDED ILLUSTRATION ADDED

DESC 06-30-00-001-A01

R

ADDED PERMISSIBLE WIND SPEED WARNING CAUTION ADDED/REVISED/DELETED

FIGURE 06-30-00-991-010-A01

N

ILLUSTRATION ADDED



LOCATIONS DESC 06-30-00-001-B01

CHG CODE R

DESCRIPTIONS OF CHANGE ADDED PERMISSIBLE WIND SPEED WARNING CAUTION ADDED/REVISED/DELETED

FIGURE 06-30-00-991-011-A01 DESC 06-30-00-001-C01

N R

ILLUSTRATION ADDED ADDED PERMISSIBLE WIND SPEED WARNING CAUTION ADDED/REVISED/DELETED

FIGURE 06-30-00-991-012-A01 DESC 06-30-00-001-D01

N R

ILLUSTRATION ADDED ADDED PERMISSIBLE WIND SPEED WARNING CAUTION ADDED/REVISED/DELETED

FIGURE 06-30-00-991-013-A01 TASK 06-30-00-581-802-A01

N R

ILLUSTRATION ADDED TOOL P/N AND/OR DESIGNATION ADDED/REVISED/DELETED WARNING CAUTION ADDED/REVISED/DELETED

Subtask 06-30-00-581-003-A01

R

CAUTION DELETED AS NOT APPLICABLE WARNING CAUTION ADDED/REVISED/DELETED

TASK 06-30-00-581-801-A01

R

Subtask 06-30-00-581-002-A01

R

UPDATED REFERENCE TO AIRCRAFT STABILITY ON JACKS CROSS REFERENCED DOCUMENTARY UNIT ADDED/REVISED/DELETED WARNING CAUTION ADDED/REVISED/DELETED NOTE AMENDED CROSS REFERENCED DOCUMENTARY UNIT ADDED/REVISED/DELETED

Subject 06-40-00



LOCATIONS DESC 06-40-00-002-A01

CHG CODE R

DESC 06-40-00-001-A01 DESC 06-40-00-003-A01 FIGURE 06-40-00-991-001-A01 FIGURE 06-40-00-991-003-A01 TASK 06-40-00-581-801-A01

N N N N R

Subtask 06-40-00-581-001-A01

R

DESCRIPTIONS OF CHANGE DELETED INFORMATION RELATED TO FUSELAGE LIFTING WITH PNEUMATIC LIFTING BAGS ADDED REFERENCE TO LEVELING AND LIFTING PROCEDURES ON WING AND FUSELAGE CROSS REFERENCED DOCUMENTARY UNIT ADDED/REVISED/DELETED

ILLUSTRATION ADDED ILLUSTRATION ADDED CROSS REFERENCED DOCUMENTARY UNIT ADDED/REVISED/DELETED WARNING CAUTION ADDED/REVISED/DELETED NOTE AMENDED UPDATED PROCEDURE TITLE LAYOUT AND TECHNICAL CONTENT CROSS REFERENCED DOCUMENTARY UNIT ADDED/REVISED/DELETED

Subject 06-50-00 TASK 06-50-00-581-803-A01 TASK 06-50-00-581-802-A01 TASK 06-50-00-581-801-A01

R R R

Subtask 06-50-00-581-001-A01

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CHAPTER 07 Subject 07-00-00

TOOL P/N AND/OR DESIGNATION ADDED/REVISED/DELETED CROSS REFERENCED DOCUMENTARY UNIT ADDED/REVISED/DELETED WARNING CAUTION ADDED/REVISED/DELETED NOTE AMENDED CROSS REFERENCED DOCUMENTARY UNIT ADDED/REVISED/DELETED

R



LOCATIONS DESC 07-00-00-002-A01

CHG CODE R

Section 07-20 Subject 07-20-00

N N

DESC 07-20-00-001-A01 FIGURE 07-20-00-991-001-A01 Section 07-40 Subject 07-40-00

N N R R

DESC 07-40-00-001-A01

R

DESCRIPTIONS OF CHANGE CROSS REFERENCED DOCUMENTARY UNIT ADDED/REVISED/DELETED

ILLUSTRATION ADDED

Added of debogging definition

Subject 07-40-01 TASK 07-40-01-584-801-A01 Subject 07-40-02

R

TASK 07-40-02-584-801-A01

R

CROSS REFERENCED DOCUMENTARY UNIT ADDED/REVISED/DELETED TOOL P/N AND/OR DESIGNATION ADDED/REVISED/DELETED

TASK 07-40-02-584-802-A01

R

CROSS REFERENCED DOCUMENTARY UNIT ADDED/REVISED/DELETED CONSUMABLE MATERIAL DATA UPDATED TOOL P/N AND/OR DESIGNATION ADDED/REVISED/DELETED

R


Subject 07-60-02 DESC 07-60-02-001-A01

CHAPTER 09 Subject 09-20-01 DESC 09-20-01-002-A01 FIGURE 09-20-01-991-006-A01 FIGURE 09-20-01-991-008-A01 FIGURE 09-20-01-991-010-A01 FIGURE 09-20-01-991-012-A01 FIGURE 09-20-01-991-015-A01 FIGURE 09-20-01-991-016-A01

R R R R R R D

ILLUSTRATION DELETED HIGHLIGHTS Page 5 Jul 01/09


LOCATIONS

CHG CODE

DESCRIPTIONS OF CHANGE

Subject 09-50-01 FIGURE 09-50-01-991-007-A01

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LIST OF EFFECTIVE CONTENT Revision No. 2 - Jul 01/09 CONTENT

CHG CODE

LAST REVISION DATE


Jun 01/08

DESC 01-00-00-002-A01

Jun 01/08

Subject 01-00-02 DESC 01-00-02-001-A01

Nov 01/08

FIGURE 01-00-02-991-001-A01

Jun 01/08

FIGURE 01-00-02-991-002-A01

Jun 01/08

DESC 01-00-02-002-A01

Jun 01/08

DESC 01-00-02-003-A01

Jun 01/08

DESC 01-00-02-004-A01

Jun 01/08

Subject 01-00-03 DESC 01-00-03-001-A01

Jun 01/08

Subject 01-10-01 DESC 01-10-01-002-A01

Jun 01/08

DESC 01-10-01-001-A01

Jun 01/08

Subject 01-20-01 DESC 01-20-01-001-A01 DESC 01-20-01-002-A01

Jun 01/08 R

Jul 01/09

DESC 01-20-01-002-B01

Jun 01/08

DESC 01-20-01-002-C01

Jun 01/08

DESC 01-20-01-002-D01

Jun 01/08

CHAPTER 02 Subject 02-00-00 DESC 02-00-00-001-A01 FIGURE 02-00-00-991-001-A01

R

Jul 01/09 Jun 01/08

L.E.C. Page 1 Jul 01/09


CONTENT

CHG CODE

LAST REVISION DATE

Subject 02-10-01 DESC 02-10-01-001-A01

Jun 01/08

DESC 02-10-01-002-A01

Jun 01/08

Subject 02-20-01 TASK 02-20-01-285-801-A01

Jun 01/08

Subtask 02-20-01-284-001-A01

Jun 01/08

Subtask 02-20-01-680-001-A01

Jun 01/08

Subtask 02-20-01-862-001-A01

Jun 01/08

Subtask 02-20-01-869-001-A01

Jun 01/08

Subject 02-20-02 TASK 02-20-02-285-801-A01

Jun 01/08

Subtask 02-20-02-285-001-A01

Jun 01/08

Subtask 02-20-02-285-002-A01

Jun 01/08

Subtask 02-20-02-500-001-A01

Jun 01/08

Subtask 02-20-02-869-001-A01

Jun 01/08

Subject 02-30-01 TASK 02-30-01-200-801-A01

R

Jul 01/09

Subtask 02-30-01-867-001-A01

Nov 01/08

Subtask 02-30-01-867-003-A01

Nov 01/08

Subtask 02-30-01-867-004-A01

Nov 01/08

FIGURE 02-30-01-991-001-A01

Jun 01/08

FIGURE 02-30-01-991-002-A01

Jun 01/08

TASK 02-30-01-481-801-A01

R

Jul 01/09

Subtask 02-30-01-481-003-A01

Jun 01/08

Subtask 02-30-01-481-004-A01

Jun 01/08

FIGURE 02-30-01-991-020-A01

Jun 01/08

FIGURE 02-30-01-991-021-A01

Jun 01/08

TASK 02-30-01-867-802-A01 Subtask 02-30-01-869-001-A01

R

Jul 01/09 Jun 01/08 L.E.C. Page 2 Jul 01/09


CONTENT

CHG CODE

Subtask 02-30-01-581-001-A01

LAST REVISION DATE Nov 01/08

Subtask 02-30-01-581-002-A01

Nov 01/08

Subtask 02-30-01-581-003-A01

Nov 01/08

FIGURE 02-30-01-991-019-A01

Jun 01/08

FIGURE 02-30-01-991-022-A01

Jun 01/08

FIGURE 02-30-01-991-023-A01

Jun 01/08

Subject 02-40-01 DESC 02-40-01-001-A01

Jun 01/08

CHAPTER 03 Subject 03-00-00 TASK 03-00-00-558-801-A01

R

Jul 01/09

Subtask 03-00-00-558-001-A01

Nov 01/08

Subtask 03-00-00-558-001-B01

Nov 01/08

Subtask 03-00-00-558-001-C01

Nov 01/08

Subtask 03-00-00-558-001-D01

Nov 01/08

Subtask 03-00-00-970-001-A01

Jun 01/08

FIGURE 03-00-00-991-002-A01

Jun 01/08

FIGURE 03-00-00-991-002-B01

Jun 01/08

FIGURE 03-00-00-991-002-C01

Jun 01/08

FIGURE 03-00-00-991-002-D01

R

Jul 01/09

Subject 03-20-01 DESC 03-20-01-001-A01

Nov 01/08

FIGURE 03-20-01-991-001-A01

Nov 01/08

DESC 03-20-01-002-A01

Nov 01/08

Subject 03-20-02 TASK 03-20-02-970-801-A01

R

Jul 01/09

Subtask 03-20-02-869-001-A01

Nov 01/08

Subtask 03-20-02-970-001-A01

Jun 01/08

FIGURE 03-20-02-991-001-A01

Jun 01/08 L.E.C. Page 3 Jul 01/09


CONTENT

CHG CODE

FIGURE 03-20-02-991-001-B01

LAST REVISION DATE Jun 01/08

FIGURE 03-20-02-991-002-A01

Jun 01/08

Subject 03-50-01 DESC 03-50-01-001-A01

Jun 01/08

TASK 03-50-01-558-801-A01

Nov 01/08

Subtask 03-50-01-558-001-A01

Nov 01/08

TASK 03-50-01-558-801-B01

Nov 01/08

Subtask 03-50-01-558-018-A01

Nov 01/08

FIGURE 03-50-01-991-003-A01

Jun 01/08

FIGURE 03-50-01-991-004-A01

Jun 01/08

TASK 03-50-01-558-801-C01

Nov 01/08

Subtask 03-50-01-558-019-A01

Nov 01/08

FIGURE 03-50-01-991-005-A01

Jun 01/08

FIGURE 03-50-01-991-006-A01

Jun 01/08

TASK 03-50-01-558-801-D01

Nov 01/08

Subtask 03-50-01-558-020-A01

Nov 01/08

FIGURE 03-50-01-991-007-A01

Jun 01/08

FIGURE 03-50-01-991-008-A01

Jun 01/08

TASK 03-50-01-558-802-A01

Nov 01/08

Subtask 03-50-01-558-002-A01

Jun 01/08

TASK 03-50-01-558-803-A01

Nov 01/08

Subtask 03-50-01-558-003-A01

Jun 01/08

TASK 03-50-01-558-804-A01

Nov 01/08

Subtask 03-50-01-558-004-A01

Nov 01/08

TASK 03-50-01-558-805-A01

Nov 01/08

Subtask 03-50-01-558-005-A01

Jun 01/08

TASK 03-50-01-558-806-A01

Nov 01/08

Subtask 03-50-01-558-006-A01

Nov 01/08

TASK 03-50-01-558-807-A01

Nov 01/08 L.E.C. Page 4 Jul 01/09


CONTENT

CHG CODE

Subtask 03-50-01-558-007-A01


TASK 03-50-01-558-808-A01

Nov 01/08

Subtask 03-50-01-558-008-A01

Jun 01/08

TASK 03-50-01-558-809-A01

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Jul 01/09

Subtask 03-50-01-558-009-A01

Nov 01/08

TASK 03-50-01-558-810-A01

Nov 01/08

Subtask 03-50-01-558-010-A01

Nov 01/08

TASK 03-50-01-558-810-B01

Nov 01/08

Subtask 03-50-01-558-012-A01

Nov 01/08

TASK 03-50-01-558-810-C01

Nov 01/08

Subtask 03-50-01-558-013-A01

Nov 01/08

TASK 03-50-01-558-810-D01

Nov 01/08

Subtask 03-50-01-558-014-A01

Nov 01/08

TASK 03-50-01-558-811-A01

R

Subtask 03-50-01-558-011-A01 TASK 03-50-01-558-811-B01

Nov 01/08 R

Subtask 03-50-01-558-015-A01 TASK 03-50-01-558-811-C01

Jul 01/09 Jul 01/09 Nov 01/08

R

Subtask 03-50-01-558-016-A01

Jul 01/09 Nov 01/08

Subject 03-60-01 DESC 03-60-01-001-A01

R

Jul 01/09


Jun 01/08

Subject 04-20-00 TASK 04-20-00-588-801-A01

R

Jul 01/09

Subtask 04-20-00-588-001-A01

R

Jul 01/09

FIGURE 04-20-00-991-001-A01

N

Jul 01/09



CONTENT FIGURE 04-20-00-991-001-B01

CHG CODE N

LAST REVISION DATE Jul 01/09

FIGURE 04-20-00-991-001-C01

N

Jul 01/09

FIGURE 04-20-00-991-001-D01

N

Jul 01/09

Subject 04-30-00 DESC 04-30-00-001-A01

Nov 01/08

FIGURE 04-30-00-991-001-A01

Jun 01/08

FIGURE 04-30-00-991-002-A01

Jun 01/08

FIGURE 04-30-00-991-002-B01

Jun 01/08

FIGURE 04-30-00-991-002-C01

Jun 01/08

FIGURE 04-30-00-991-002-D01

Jun 01/08

FIGURE 04-30-00-991-003-A01

Jun 01/08

TASK 04-30-00-556-801-A01

Nov 01/08

Subtask 04-30-00-556-001-A01

Nov 01/08

Subtask 04-30-00-556-002-A01

Jun 01/08

FIGURE 04-30-00-991-004-A01

Jun 01/08

FIGURE 04-30-00-991-005-A01

Jun 01/08

FIGURE 04-30-00-991-006-A01

Jun 01/08

FIGURE 04-30-00-991-007-A01

Jun 01/08

Subject 04-40-00 DESC 04-40-00-001-A01

Jun 01/08

Subject 04-50-00 DESC 04-50-00-001-A01

Jun 01/08


Nov 01/08

Subject 05-10-00 DESC 05-10-00-001-A01

Nov 01/08

FIGURE 05-10-00-991-004-A01

Nov 01/08

Subject 05-20-00 L.E.C. Page 6 Jul 01/09


CONTENT

CHG CODE

DESC 05-20-00-001-A01


DESC 05-20-00-002-A01

Nov 01/08

FIGURE 05-20-00-991-013-A01

Nov 01/08

FIGURE 05-20-00-991-013-B01

Nov 01/08

FIGURE 05-20-00-991-001-A01

Nov 01/08

FIGURE 05-20-00-991-001-B01

Nov 01/08

FIGURE 05-20-00-991-002-A01

Nov 01/08

FIGURE 05-20-00-991-002-B01

Nov 01/08

DESC 05-20-00-004-A01

Nov 01/08

FIGURE 05-20-00-991-014-A01

Nov 01/08

FIGURE 05-20-00-991-015-A01

Nov 01/08

Subject 05-30-00 TASK 05-30-00-650-801-A01

Nov 01/08

Subtask 05-30-00-869-001-A01

Nov 01/08

Subtask 05-30-00-650-003-A01

Nov 01/08

Subject 05-40-00 DESC 05-40-00-001-A01

Nov 01/08

Subject 05-40-01 TASK 05-40-01-650-801-A01

Nov 01/08

Subtask 05-40-01-869-001-A01

Nov 01/08

Subtask 05-40-01-650-003-A01

Nov 01/08

Subject 05-40-02 TASK 05-40-02-650-801-A01

R

Jul 01/09

Subtask 05-40-02-869-001-A01

Nov 01/08

Subtask 05-40-02-650-002-A01

Nov 01/08

FIGURE 05-40-02-991-004-A01

Nov 01/08

Subject 05-40-03 TASK 05-40-03-650-802-A01

Nov 01/08

Subtask 05-40-03-869-001-A01

Nov 01/08 L.E.C. Page 7 Jul 01/09


CONTENT

CHG CODE

Subtask 05-40-03-010-001-A01


Subtask 05-40-03-010-001-B01

Nov 01/08

Subtask 05-40-03-650-002-A01

Nov 01/08

FIGURE 05-40-03-991-001-A01

Nov 01/08

Subject 05-50-00 DESC 05-50-00-005-A01

Nov 01/08

Subject 05-50-01 DESC 05-50-01-005-A01

Nov 01/08

Subject 05-60-00 DESC 05-60-00-001-A01

Nov 01/08


Jun 01/08

DESC 06-00-00-002-A01

N

Jul 01/09

FIGURE 06-00-00-991-001-A01

N

Jul 01/09

FIGURE 06-00-00-991-001-B01

N

Jul 01/09

FIGURE 06-00-00-991-001-C01

N

Jul 01/09

R

Jul 01/09

Subject 06-10-00 TASK 06-10-00-970-801-A01 Subtask 06-10-00-970-001-A01

Nov 01/08

Subtask 06-10-00-869-001-A01

Jun 01/08

FIGURE 06-10-00-991-001-A01

Nov 01/08

FIGURE 06-10-00-991-002-A01

Jun 01/08

TASK 06-10-00-970-802-A01

Nov 01/08

Subtask 06-10-00-970-002-A01

Jun 01/08

TASK 06-10-00-970-803-A01

R

Jul 01/09

Subtask 06-10-00-970-003-A01

Nov 01/08

Subtask 06-10-00-970-004-A01

Nov 01/08

FIGURE 06-10-00-991-003-A01

Jun 01/08 L.E.C. Page 8 Jul 01/09


CONTENT

CHG CODE


R

Jul 01/09

FIGURE 06-10-00-991-004-A01 Subject 06-30-00 DESC 06-30-00-001-A01 FIGURE 06-30-00-991-006-A01

Jun 01/08

FIGURE 06-30-00-991-010-A01

N

Jul 01/09

DESC 06-30-00-001-B01

R

Jul 01/09

FIGURE 06-30-00-991-007-A01

Jun 01/08

FIGURE 06-30-00-991-011-A01

N

Jul 01/09

DESC 06-30-00-001-C01

R

Jul 01/09

FIGURE 06-30-00-991-008-A01

Jun 01/08

FIGURE 06-30-00-991-012-A01

N

Jul 01/09

DESC 06-30-00-001-D01

R

Jul 01/09

FIGURE 06-30-00-991-009-A01 FIGURE 06-30-00-991-013-A01

Jun 01/08 N

DESC 06-30-00-002-A01

Jul 01/09 Jun 01/08

TASK 06-30-00-581-802-A01

R

Jul 01/09

Subtask 06-30-00-581-003-A01

R

Jul 01/09

FIGURE 06-30-00-991-004-A01

Jun 01/08

TASK 06-30-00-581-801-A01

R

Jul 01/09

Subtask 06-30-00-581-002-A01

R

Jul 01/09

DESC 06-40-00-002-A01

R

Jul 01/09

DESC 06-40-00-001-A01

N

Jul 01/09

DESC 06-40-00-003-A01

N

Jul 01/09

FIGURE 06-40-00-991-001-A01

N

Jul 01/09

FIGURE 06-40-00-991-003-A01

N

Jul 01/09

TASK 06-40-00-581-801-A01

R

Jul 01/09

Subtask 06-40-00-581-001-A01

R

Jul 01/09

Subject 06-40-00



CONTENT

CHG CODE

DESC 06-50-00-001-A01 FIGURE 06-50-00-991-020-A01 TASK 06-50-00-581-803-A01

LAST REVISION DATE Nov 01/08 Nov 01/08

R

Jul 01/09

Subtask 06-50-00-581-002-A01

Nov 01/08

Subtask 06-50-00-581-003-A01

Nov 01/08

FIGURE 06-50-00-991-014-A01

Nov 01/08

FIGURE 06-50-00-991-015-A01

Jun 01/08

FIGURE 06-50-00-991-021-A01

Nov 01/08

TASK 06-50-00-581-802-A01

R

Jul 01/09

Subtask 06-50-00-010-001-A01

Nov 01/08

Subtask 06-50-00-581-004-A01

Nov 01/08

Subtask 06-50-00-581-005-A01

Nov 01/08

FIGURE 06-50-00-991-013-A01

Jun 01/08

FIGURE 06-50-00-991-016-A01

Jun 01/08

FIGURE 06-50-00-991-017-A01

Nov 01/08

FIGURE 06-50-00-991-018-A01

Nov 01/08

TASK 06-50-00-581-801-A01

R

Jul 01/09

Subtask 06-50-00-581-001-A01

R

Jul 01/09

R

Jul 01/09

DESC 07-20-00-001-A01

N

Jul 01/09

FIGURE 07-20-00-991-001-A01

N

Jul 01/09

R

Jul 01/09

R

Jul 01/09

CHAPTER 07 Subject 07-00-00 DESC 07-00-00-002-A01 Subject 07-20-00

Subject 07-40-00 DESC 07-40-00-001-A01 Subject 07-40-01 TASK 07-40-01-584-801-A01 Subtask 07-40-01-500-001-A01

Nov 01/08 L.E.C. Page 10 Jul 01/09


CONTENT

CHG CODE

Subtask 07-40-01-500-002-A01


Subtask 07-40-01-869-001-A01

Jun 01/08

Subtask 07-40-01-584-001-A01

Jun 01/08

Subtask 07-40-01-869-002-A01

Jun 01/08

FIGURE 07-40-01-991-001-A01

Jun 01/08

FIGURE 07-40-01-991-002-A01

Jun 01/08

TASK 07-40-01-584-802-A01

Nov 01/08

Subtask 07-40-01-500-003-A01

Jun 01/08

Subtask 07-40-01-500-004-A01

Jun 01/08

Subtask 07-40-01-869-003-A01

Jun 01/08

Subtask 07-40-01-584-002-A01

Jun 01/08

Subtask 07-40-01-869-004-A01

Jun 01/08

Subject 07-40-02 TASK 07-40-02-584-801-A01

R

Jul 01/09

Subtask 07-40-02-500-001-A01

Jun 01/08

Subtask 07-40-02-500-002-A01

Nov 01/08

Subtask 07-40-02-500-003-A01

Nov 01/08

Subtask 07-40-02-584-001-A01

Jun 01/08

Subtask 07-40-02-869-001-A01

Jun 01/08

FIGURE 07-40-02-991-001-A01

Jun 01/08

FIGURE 07-40-02-991-002-A01

Jun 01/08

FIGURE 07-40-02-991-003-A01

Jun 01/08

TASK 07-40-02-584-802-A01

R

Jul 01/09

Subtask 07-40-02-500-004-A01

Jun 01/08

Subtask 07-40-02-020-001-A01

Nov 01/08

Subtask 07-40-02-500-006-A01

Nov 01/08

Subtask 07-40-02-584-002-A01

Jun 01/08

Subtask 07-40-02-869-002-A01

Jun 01/08

Subtask 07-40-02-500-007-A01

Nov 01/08 L.E.C. Page 11 Jul 01/09


CONTENT

CHG CODE

FIGURE 07-40-02-991-004-A01


FIGURE 07-40-02-991-005-A01

Jun 01/08

FIGURE 07-40-02-991-006-A01

Jun 01/08

FIGURE 07-40-02-991-007-A01

Jun 01/08

Subject 07-40-03 TASK 07-40-03-584-801-A01

Nov 01/08

Subtask 07-40-03-584-001-A01

Jun 01/08

Subtask 07-40-03-584-002-A01

Jun 01/08

Subject 07-40-04 DESC 07-40-04-001-A01

Nov 01/08

FIGURE 07-40-04-991-001-A01

Jun 01/08

FIGURE 07-40-04-991-002-A01

Jun 01/08

FIGURE 07-40-04-991-003-A01

Jun 01/08

Subject 07-60-00 DESC 07-60-00-001-A01

Nov 01/08

Subject 07-60-01 DESC 07-60-01-001-A01

Nov 01/08

FIGURE 07-60-01-991-002-A01

Nov 01/08

FIGURE 07-60-01-991-003-A01

Nov 01/08

Subject 07-60-02 DESC 07-60-02-001-A01

R

Jul 01/09

Subject 07-60-03 DESC 07-60-03-001-A01

Nov 01/08


Jun 01/08


Jun 01/08 L.E.C. Page 12 Jul 01/09


CONTENT

CHG CODE

LAST REVISION DATE

Subject 09-10-01 DESC 09-10-01-002-A01

Jun 01/08

DESC 09-10-01-001-A01

Jun 01/08

Subject 09-10-02 DESC 09-10-02-001-A01

Jun 01/08

DESC 09-10-02-003-A01

Jun 01/08

DESC 09-10-02-002-A01

Nov 01/08

FIGURE 09-10-02-991-001-A01

Jun 01/08

Subject 09-10-03 DESC 09-10-03-001-A01

Nov 01/08

FIGURE 09-10-03-991-001-A01

Jun 01/08

FIGURE 09-10-03-991-002-A01

Jun 01/08

DESC 09-10-03-001-B01

Nov 01/08

FIGURE 09-10-03-991-003-A01

Jun 01/08

FIGURE 09-10-03-991-004-A01

Jun 01/08

DESC 09-10-03-001-C01

Nov 01/08

FIGURE 09-10-03-991-005-A01

Jun 01/08

FIGURE 09-10-03-991-005-B01

Jun 01/08

FIGURE 09-10-03-991-006-A01

Jun 01/08

DESC 09-10-03-001-D01

Nov 01/08

FIGURE 09-10-03-991-007-A01

Jun 01/08

FIGURE 09-10-03-991-008-A01

Jun 01/08

Subject 09-10-04 DESC 09-10-04-001-A01

Nov 01/08

FIGURE 09-10-04-991-001-A01

Jun 01/08

FIGURE 09-10-04-991-001-B01

Jun 01/08

FIGURE 09-10-04-991-001-C01

Jun 01/08

FIGURE 09-10-04-991-001-D01

Jun 01/08



CONTENT DESC 09-10-05-001-A01

CHG CODE


FIGURE 09-10-05-991-001-A01

Jun 01/08

FIGURE 09-10-05-991-001-B01

Jun 01/08

FIGURE 09-10-05-991-001-C01

Jun 01/08

FIGURE 09-10-05-991-001-D01

Jun 01/08

Subject 09-10-06 DESC 09-10-06-001-A01

Jun 01/08

FIGURE 09-10-06-991-001-A01

Jun 01/08

FIGURE 09-10-06-991-001-B01

Jun 01/08

FIGURE 09-10-06-991-001-C01

Jun 01/08

FIGURE 09-10-06-991-001-D01

Jun 01/08

Subject 09-10-08 DESC 09-10-08-001-A01

Nov 01/08

FIGURE 09-10-08-991-001-A01

Jun 01/08

FIGURE 09-10-08-991-001-B01

Jun 01/08

Subject 09-10-09 DESC 09-10-09-001-A01

Nov 01/08

FIGURE 09-10-09-991-001-A01

Jun 01/08

Subject 09-10-10 DESC 09-10-10-001-A01

Jun 01/08

DESC 09-10-10-002-A01

Nov 01/08

FIGURE 09-10-10-991-001-A01

Jun 01/08

FIGURE 09-10-10-991-001-B01

Jun 01/08

FIGURE 09-10-10-991-001-C01

Jun 01/08

FIGURE 09-10-10-991-001-D01

Jun 01/08

FIGURE 09-10-10-991-002-A01

Jun 01/08

FIGURE 09-10-10-991-003-A01

Jun 01/08

FIGURE 09-10-10-991-003-B01

Jun 01/08

FIGURE 09-10-10-991-003-C01

Jun 01/08 L.E.C. Page 14 Jul 01/09


CONTENT

CHG CODE

FIGURE 09-10-10-991-003-D01


FIGURE 09-10-10-991-004-A01

Jun 01/08

DESC 09-10-10-003-A01

Nov 01/08

FIGURE 09-10-10-991-006-A01

Jun 01/08

FIGURE 09-10-10-991-006-B01

Jun 01/08

FIGURE 09-10-10-991-006-C01

Jun 01/08

FIGURE 09-10-10-991-006-D01

Jun 01/08

DESC 09-10-10-004-A01

Nov 01/08

FIGURE 09-10-10-991-010-A01

Jun 01/08

DESC 09-10-10-005-A01

Nov 01/08

FIGURE 09-10-10-991-011-A01

Jun 01/08

FIGURE 09-10-10-991-011-B01

Jun 01/08

FIGURE 09-10-10-991-011-C01

Nov 01/08

FIGURE 09-10-10-991-011-D01

Jun 01/08

DESC 09-10-10-006-A01

Nov 01/08

FIGURE 09-10-10-991-014-A01

Jun 01/08

Subject 09-10-11 DESC 09-10-11-001-A01

Nov 01/08

FIGURE 09-10-11-991-001-A01

Jun 01/08

FIGURE 09-10-11-991-002-A01

Jun 01/08

FIGURE 09-10-11-991-003-A01

Jun 01/08

FIGURE 09-10-11-991-004-A01

Jun 01/08

FIGURE 09-10-11-991-005-A01

Jun 01/08

FIGURE 09-10-11-991-006-A01

Jun 01/08

FIGURE 09-10-11-991-007-A01

Jun 01/08

DESC 09-10-11-001-B01

Nov 01/08

FIGURE 09-10-11-991-014-A01

Jun 01/08

FIGURE 09-10-11-991-015-A01

Jun 01/08

FIGURE 09-10-11-991-016-A01

Jun 01/08 L.E.C. Page 15 Jul 01/09


CONTENT

CHG CODE

FIGURE 09-10-11-991-017-A01


FIGURE 09-10-11-991-018-A01

Jun 01/08

FIGURE 09-10-11-991-019-A01

Jun 01/08

FIGURE 09-10-11-991-020-A01

Jun 01/08

DESC 09-10-11-001-C01

Nov 01/08

FIGURE 09-10-11-991-021-A01

Jun 01/08

FIGURE 09-10-11-991-022-A01

Jun 01/08

FIGURE 09-10-11-991-023-A01

Jun 01/08

FIGURE 09-10-11-991-024-A01

Jun 01/08

FIGURE 09-10-11-991-025-A01

Jun 01/08

FIGURE 09-10-11-991-026-A01

Jun 01/08

FIGURE 09-10-11-991-027-A01

Jun 01/08

DESC 09-10-11-001-D01

Nov 01/08

FIGURE 09-10-11-991-028-A01

Jun 01/08

FIGURE 09-10-11-991-029-A01

Jun 01/08

FIGURE 09-10-11-991-030-A01

Jun 01/08

FIGURE 09-10-11-991-031-A01

Jun 01/08

FIGURE 09-10-11-991-032-A01

Jun 01/08

FIGURE 09-10-11-991-033-A01

Jun 01/08

FIGURE 09-10-11-991-034-A01

Jun 01/08

Subject 09-10-12 DESC 09-10-12-001-A01

Nov 01/08

FIGURE 09-10-12-991-001-A01

Jun 01/08

FIGURE 09-10-12-991-001-B01

Jun 01/08

FIGURE 09-10-12-991-001-C01

Jun 01/08

FIGURE 09-10-12-991-001-D01

Jun 01/08

DESC 09-10-12-002-A01

Jun 01/08

FIGURE 09-10-12-991-002-A01

Jun 01/08

FIGURE 09-10-12-991-003-A01

Jun 01/08 L.E.C. Page 16 Jul 01/09


CONTENT FIGURE 09-10-12-991-014-A01

CHG CODE


DESC 09-10-12-003-A01

Jun 01/08

FIGURE 09-10-12-991-004-A01

Jun 01/08

DESC 09-10-12-004-A01

Jun 01/08

FIGURE 09-10-12-991-008-A01

Nov 01/08

FIGURE 09-10-12-991-009-A01

Jun 01/08

FIGURE 09-10-12-991-015-A01

Jun 01/08

DESC 09-10-12-005-A01

Jun 01/08

FIGURE 09-10-12-991-010-A01

Jun 01/08

DESC 09-10-12-006-A01

Jun 01/08

FIGURE 09-10-12-991-013-A01

Jun 01/08

FIGURE 09-10-12-991-013-B01

Jun 01/08

Subject 09-10-13 DESC 09-10-13-001-A01

Jun 01/08

FIGURE 09-10-13-991-001-A01

Jun 01/08

Subject 09-10-14 DESC 09-10-14-001-A01

Nov 01/08

FIGURE 09-10-14-991-007-A01

Nov 01/08

FIGURE 09-10-14-991-008-A01

Nov 01/08

FIGURE 09-10-14-991-009-A01

Nov 01/08

DESC 09-10-14-001-B01

Nov 01/08

FIGURE 09-10-14-991-010-A01

Nov 01/08

FIGURE 09-10-14-991-011-A01

Nov 01/08

DESC 09-10-14-001-C01

Nov 01/08

FIGURE 09-10-14-991-013-A01

Nov 01/08

FIGURE 09-10-14-991-014-A01

Nov 01/08

FIGURE 09-10-14-991-015-A01

Nov 01/08

DESC 09-10-14-001-D01

Nov 01/08

FIGURE 09-10-14-991-016-A01

Nov 01/08 L.E.C. Page 17 Jul 01/09


CONTENT

CHG CODE

FIGURE 09-10-14-991-017-A01


FIGURE 09-10-14-991-018-A01

Nov 01/08

Subject 09-10-15 DESC 09-10-15-001-A01

Nov 01/08

FIGURE 09-10-15-991-001-A01

Jun 01/08

FIGURE 09-10-15-991-001-B01

Jun 01/08

FIGURE 09-10-15-991-001-C01

Jun 01/08

FIGURE 09-10-15-991-001-D01

Jun 01/08

Subject 09-10-16 DESC 09-10-16-001-A01

Nov 01/08

FIGURE 09-10-16-991-001-A01

Jun 01/08

FIGURE 09-10-16-991-001-B01

Jun 01/08

FIGURE 09-10-16-991-001-C01

Jun 01/08

FIGURE 09-10-16-991-001-D01

Jun 01/08

FIGURE 09-10-16-991-002-A01

Jun 01/08

FIGURE 09-10-16-991-003-A01

Jun 01/08

FIGURE 09-10-16-991-004-A01

Jun 01/08

Subject 09-20-01 DESC 09-20-01-001-A01 DESC 09-20-01-002-A01

Jun 01/08 R

Jul 01/09

FIGURE 09-20-01-991-001-A01

Jun 01/08

FIGURE 09-20-01-991-002-A01

Jun 01/08

FIGURE 09-20-01-991-003-A01

Jun 01/08

FIGURE 09-20-01-991-004-A01

Jun 01/08

FIGURE 09-20-01-991-005-A01

Jun 01/08

FIGURE 09-20-01-991-006-A01

R

FIGURE 09-20-01-991-007-A01 FIGURE 09-20-01-991-008-A01 FIGURE 09-20-01-991-009-A01

Jul 01/09 Jun 01/08

R

Jul 01/09 Jun 01/08 L.E.C. Page 18 Jul 01/09



CHG CODE R

FIGURE 09-20-01-991-011-A01 FIGURE 09-20-01-991-012-A01

LAST REVISION DATE Jul 01/09 Jun 01/08

R

Jul 01/09

FIGURE 09-20-01-991-013-A01

Jun 01/08

FIGURE 09-20-01-991-014-A01

Jun 01/08

FIGURE 09-20-01-991-015-A01

R

Jul 01/09

FIGURE 09-20-01-991-016-A01

D

Jul 01/09

DESC 09-20-01-004-A01

Jun 01/08

DESC 09-20-01-005-A01

Jun 01/08

FIGURE 09-20-01-991-020-A01

Jun 01/08

TASK 09-20-01-869-801-A01

Jun 01/08

Subtask 09-20-01-869-001-A01

Jun 01/08

Subtask 09-20-01-869-002-A01

Jun 01/08

Subject 09-20-02 DESC 09-20-02-001-A01

Jun 01/08

Subject 09-30-01 DESC 09-30-01-001-A01

Jun 01/08

DESC 09-30-01-002-A01

Nov 01/08

Subject 09-30-02 DESC 09-30-02-001-A01

Nov 01/08

Subject 09-30-03 DESC 09-30-03-001-A01

Nov 01/08

DESC 09-30-03-002-A01

Nov 01/08

Subject 09-50-01 DESC 09-50-01-001-A01

Nov 01/08

FIGURE 09-50-01-991-001-A01

Jun 01/08

FIGURE 09-50-01-991-002-A01

Jun 01/08

FIGURE 09-50-01-991-003-A01

Jun 01/08

FIGURE 09-50-01-991-004-A01

Jun 01/08 L.E.C. Page 19 Jul 01/09




FIGURE 09-50-01-991-006-A01

Jun 01/08

FIGURE 09-50-01-991-007-A01

CHG CODE

R

Jul 01/09

FIGURE 09-50-01-991-008-A01

Jun 01/08

FIGURE 09-50-01-991-009-A01

Jun 01/08

FIGURE 09-50-01-991-010-A01

Jun 01/08

FIGURE 09-50-01-991-011-A01

Jun 01/08

FIGURE 09-50-01-991-012-A01

Jun 01/08

FIGURE 09-50-01-991-013-A01

Jun 01/08

FIGURE 09-50-01-991-014-A01

Jun 01/08



TABLE OF CONTENTS

01

INTRODUCTION

01-00-00 01-00-00-001-A01 01-00-00-002-A01

INTRODUCTION General Important Notice to Users of this Document

01-00-02 01-00-02-001-A01 01-00-02-002-A01 01-00-02-003-A01 01-00-02-004-A01

SEQUENCE OF THE DOCUMENT General Task Oriented ARM Content Effectivity Management

01-00-03 01-00-03-001-A01

DEFINITIONS General

01-10-01 01-10-01-002-A01 01-10-01-001-A01

RELATED DATA Airbus Data Other Data

01-20-01 01-20-01-001-A01 01-20-01-002-A01 01-20-01-002-B01 01-20-01-002-C01 01-20-01-002-D01

GENERAL AIRCRAFT CHARACTERISTICS General Aircraft Description General Aircraft Data General Aircraft Data General Aircraft Data General Aircraft Data

02

SURVEY

02-00-00 02-00-00-001-A01

SURVEY General

02-10-01 02-10-01-001-A01 02-10-01-002-A01

CHARTS AND GUIDES Aircraft Recovery Process Aircraft Recovery Logic Chart

02-20-01 02-20-01-285-801-A01

INITIAL AIRCRAFT SURVEY Initial Aircraft Survey

T.O.C. Page 1 Jul 01/09


02-20-02 02-20-02-285-801-A01

INITIAL SITE SURVEY Initial Site Survey

02-30-01 02-30-01-200-801-A01 02-30-01-481-801-A01 02-30-01-867-802-A01

LANDING GEAR Landing Gear Survey Installation of the Safety Device on Landing Gears Jacking for Wheel Change

02-40-01 02-40-01-001-A01

HEALTH AND SAFETY ISSUES General

03

WEIGHT AND CG MANAGEMENT

03-00-00 03-00-00-558-801-A01

WEIGHT AND CG MANAGEMENT General

03-20-01 03-20-01-001-A01 03-20-01-002-A01

FUEL LOAD AND CG CONTROL General Tables

03-20-02 03-20-02-970-801-A01

MANUAL FUEL QUANTITY INDICATION Use of Magnetic Level Indicators (MLI)

03-50-01 03-50-01-001-A01 03-50-01-558-801-A01 03-50-01-558-801-B01 03-50-01-558-801-C01 03-50-01-558-801-D01 03-50-01-558-802-A01 03-50-01-558-803-A01 03-50-01-558-804-A01 03-50-01-558-805-A01 03-50-01-558-806-A01 03-50-01-558-807-A01 03-50-01-558-808-A01 03-50-01-558-809-A01 03-50-01-558-810-A01 03-50-01-558-810-B01

MANAGING AIRCRAFT WEIGHT AND CG Introduction Cargo and Baggage Remaining Effect Cargo and Baggage Remaining Effect Cargo and Baggage Remaining Effect Cargo and Baggage Remaining Effect Total Traffic Load Remaining Effect Ballast Added Effect Waste Water Remaining Effect Non OEW Catering Equipment Added Effect Potable Water Removed Effect Cockpit and Cabin Crew Removed Effect Catering Equipment Removed Effect Hydraulic Fluid Removed Effect Large Components Removed / Missing Large Components Removed / Missing T.O.C. Page 2 Jul 01/09


03-50-01-558-810-C01 03-50-01-558-810-D01 03-50-01-558-811-A01 03-50-01-558-811-B01 03-50-01-558-811-C01 03-60-01 03-60-01-001-A01 04

Large Large Large Large Large

Components Components Components Components Components

Removed / Missing Removed / Missing Movement Effect Movement Effect Movement Effect

REFERENCE FOR CALCULATION Information Required and Source Data PREPARATION

04-00-00 04-00-00-001-A01

PREPARATION General

04-20-00 04-20-00-588-801-A01

STABILIZING THE AIRCRAFT Stabilizing the Aircraft

04-30-00 04-30-00-001-A01 04-30-00-556-801-A01

TETHERING THE AIRCRAFT General Mooring

04-40-00 04-40-00-001-A01

GROUND ANCHORS General

04-50-00 04-50-00-001-A01

SOIL STABILITY General

05

WEIGHT REDUCTION

05-00-00 05-00-00-001-A01

WEIGHT REDUCTION General

05-10-00 05-10-00-001-A01

DEFUELING General

05-20-00 05-20-00-001-A01 05-20-00-002-A01 05-20-00-004-A01

FUEL SYSTEM DESCRIPTION Fuel System Basic Description Tanks Fuel Quantity Indicating System



05-30-00 05-30-00-650-801-A01

MOVING FUEL FOR CG CONTROL Fuel Transfer

05-40-00 05-40-00-001-A01

DEFUEL SCENARIOS Defuel Scenarios

05-40-01 05-40-01-650-801-A01

DEFUEL SCENARIO 1 NORMAL PRESSURE DEFUEL WITH ALL AIRCRAFT SYSTEMS SERVICEABLE Normal Pressure Defuel With All Aircraft Systems Serviceable

05-40-02 05-40-02-650-801-A01

DEFUEL SCENARIO 2 DRAIN REMAINING FUEL Drain Remaining Fuel

05-40-03 05-40-03-650-802-A01

DEFUEL SCENARIO 3 DEFUEL USING AN EXTERNAL WIRING HARNESS Defuel Using an External Wiring Harness

05-50-00 05-50-00-005-A01

CARGO COMPARTMENTS General

05-50-01 05-50-01-005-A01

CARGO REMOVAL Cargo Removal

05-60-00 05-60-00-001-A01

REMOVAL OF LARGE COMPONENTS General

06

LEVELING AND LIFTING

06-00-00 06-00-00-001-A01 06-00-00-002-A01

LEVELING AND LIFTING General Leveling/Lifting Obstructions

06-10-00 06-10-00-970-801-A01 06-10-00-970-802-A01 06-10-00-970-803-A01

LOAD DETERMINATION Vertical Loads Determination Side loads on Jack Fittings Arc Movement Calculation

06-30-00 06-30-00-001-A01 06-30-00-001-B01 06-30-00-001-C01

USE OF JACKS General General General T.O.C. Page 4 Jul 01/09


06-30-00-001-D01 06-30-00-002-A01 06-30-00-581-802-A01 06-30-00-581-801-A01

General Type of Jacks Jacking General Preparation and Instructions for Leveling and Lifting the Aircraft with Jacks

06-40-00 06-40-00-002-A01 06-40-00-001-A01 06-40-00-003-A01 06-40-00-581-801-A01

USE OF PNEUMATIC LIFTING BAGS General Pneumatic Lifting Bags on Fuselage Pneumatic Lifting Bags on Wings General Preparation and Instructions for Leveling and Lifting the Aircraft with Pneumatic Lifting Bags

06-50-00 06-50-00-001-A01 06-50-00-581-803-A01 06-50-00-581-802-A01 06-50-00-581-801-A01

USE OF CRANES General Forward Fuselage Crane Lifting Wing Rib Attachment Tool General Preparation and Instructions for Leveling and Lifting the Aircraft with Cranes

07

MOVING THE AIRCRAFT

07-00-00 07-00-00-002-A01

MOVING THE AIRCRAFT General Preparation

07-20-00 07-20-00-001-A01

PREPARING A ROADWAY General

07-40-00 07-40-00-001-A01

TOWING AND DEBOGGING General

07-40-01 07-40-01-584-801-A01 07-40-01-584-802-A01

TOWING FROM THE NOSE LANDING GEAR Towing on the NLG with a Towbar Towing on the NLG with a Towbarless Tractor

07-40-02 07-40-02-584-801-A01 07-40-02-584-802-A01

TOWING FROM THE MAIN LANDING GEAR Towing with the Main Gear from the Front Towing with the Main Gear from the Rear

07-40-03

TOWING WITH DEFLATED TIRES T.O.C. Page 5 Jul 01/09


07-40-03-584-801-A01

Towing with Deflated Tires

07-40-04 07-40-04-001-A01

TOWING LOAD LIMITS Load and Angle Limits

07-60-00 07-60-00-001-A01

MOVING DAMAGED AIRCRAFT General

07-60-01 07-60-01-001-A01

MOVING DAMAGED AIRCRAFT ON TRAILERS Moving Damaged Aircraft on Trailers

07-60-02 07-60-02-001-A01

MOVING DAMAGED AIRCRAFT WITH CRANES Moving Damaged Aircraft with Cranes

07-60-03 07-60-03-001-A01

MOVING DAMAGED AIRCRAFT WITH SPECIALIZED EQUIPMENT Moving Damaged Aircraft with Specialized Vehicles

08 08-00-00 08-00-00-001-A01 09

POST RECOVERY CORRECTIVE ACTIONS POST RECOVERY CORRECTIVE ACTIONS General APPENDIX

09-00-00 09-00-00-001-A01

APPENDIX Introduction

09-10-01 09-10-01-002-A01 09-10-01-001-A01

UNITS AND CONVERSIONS Units of Measurements Conversion Tables

09-10-02 09-10-02-001-A01 09-10-02-003-A01 09-10-02-002-A01

GLOSSARY OF TERMS Definition of Terms Abbreviations Aircraft Reference Axes

09-10-03 09-10-03-001-A01 09-10-03-001-B01 09-10-03-001-C01 09-10-03-001-D01

AIRCRAFT DIMENSIONS General General General General T.O.C. Page 6 Jul 01/09


09-10-04 09-10-04-001-A01

AIRCRAFT STRUCTURAL SECTIONS General

09-10-05 09-10-05-001-A01

COMPOSITE MATERIALS General

09-10-06 09-10-06-001-A01

FUSELAGE FRAMES AND H-ARM TABLE General

09-10-08 09-10-08-001-A01

WING RIBS AND STATIONS Wing Ribs and Stations

09-10-09 09-10-09-001-A01

HORIZONTAL STABILIZERS RIBS AND STATIONS General

09-10-10 09-10-10-001-A01 09-10-10-002-A01 09-10-10-003-A01 09-10-10-004-A01 09-10-10-005-A01 09-10-10-006-A01

DOOR SIZES AND LOCATIONS General Passenger/Crew Doors and Emergency Exit Doors Cargo Compartment Doors Nose Landing Gear Doors Main Landing-Gear Doors APU Doors

09-10-11 09-10-11-001-A01 09-10-11-001-B01 09-10-11-001-C01 09-10-11-001-D01

AIRCRAFT GROUND CLEARANCES General General General General

09-10-12 09-10-12-001-A01 09-10-12-002-A01 09-10-12-003-A01 09-10-12-004-A01 09-10-12-005-A01 09-10-12-006-A01

AIRCRAFT GROUND SERVICE CONNECTIONS General Hydraulic System Electrical System Fuel System Potable Water System Waste Water Disposal-System

09-10-13 09-10-13-001-A01

AIRCRAFT GROUNDING POINTS General T.O.C. Page 7 Jul 01/09


09-10-14 09-10-14-001-A01 09-10-14-001-B01 09-10-14-001-C01 09-10-14-001-D01

CARGO COMPARTMENTS General General General General

09-10-15 09-10-15-001-A01

LOCATION OF HAZARDOUS MATERIALS General

09-10-16 09-10-16-001-A01

LANDING GEARS General

09-20-01 09-20-01-001-A01 09-20-01-002-A01 09-20-01-004-A01 09-20-01-005-A01 09-20-01-869-801-A01

QUICK REFERENCE DATA General Aircraft Recovery Logic Chart Airline Aircraft Recovery Process Document Off Runway Incident Reporting Proforma IATA Aircraft Recovery Quick Reference Check List

09-20-02 09-20-02-001-A01

RECOVERY TEAM Composition of the Recovery Team

09-30-01 09-30-01-001-A01 09-30-01-002-A01

AIRCRAFT RECOVERY EQUIPMENT TOOLING AND MATERIALS General Airbus Specific Recovery Tools

09-30-02 09-30-02-001-A01

AIRCRAFT RECOVERY TOOLING General

09-30-03 09-30-03-001-A01 09-30-03-002-A01

IATP AIRCRAFT RECOVERY KITS General Example of IATP Recovery Kit

09-50-01 09-50-01-001-A01

WEIGHT AND CG CALCULATION WORKSHEETS Worksheets



INTRODUCTION 01-00-00

INTRODUCTION

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 01-00-00-001-A01 General 1.

This document is intended to provide, for areas which are under Airbus responsibility, aircraft comprehensive details relative to the procedures, planning, equipment and tooling to effectively recover the A318, A319, A320 or A321 aircraft. The airlines and airport authorities can use this information as a planning tool for aircraft recovery preparations. Aircraft recovery is an operation that is the result of an unplanned incident and as such, advance preparations should be made. These preparations should include the establishment of an Aircraft Recovery Team, aircraft recovery training, listings of aircraft recovery equipment availability and the development of an internal Aircraft Recovery Process Document. These are general procedures and will vary according to the individual incident and the equipment available. In most cases the recovery will be carried out under abnormal conditions of both weather and aircraft attitude. Country and state rules and regulations have to be followed, even though they may impede the recovery operation. Make sure that the relevant authorities have formally released the aircraft, before starting the aircraft recovery process. For further information on aircraft accident and incident investigation see ICAO Annex 13. Personal safety and prevention of secondary damage are emphasized in this document. The data provided in this document is based on a serviceable aircraft in a normal attitude (except where specified). If the aircraft is in a different condition, the data will have to be adjusted accordingly. Procedures for aircraft recovery from water are not covered by this document. It is recommended that the individual airlines share their aircraft recovery experiences with the aircraft manufacturer and groups such as the International Airline Transport Association (IATA), Aircraft Recovery Task Force (ARTF) and the International Airline Technical Pool (IATP). The International Airline Technical Pool as well as some airports and airlines could provide Aircraft Recovery Kits, at strategic locations around the world. Information about these groups is available at the following web sites: - http://www.iata.org - http://www.iatp.com NOTE : IATP website and recovery kits are available for IATP members only. NOTE : This chapter gives references to web sites for information only. Airbus shall not be held liable for web site or document content and for update or change of addresses.

01-00-00

Page 1 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 01-00-00-002-A01 Important Notice to Users of this Document 1.

General The technical data contained in this Aircraft Recovery Manual (ARM) is intended only for general planning, preparations and establishing procedures for the recovery of a disabled A318, A319, A320 or A321 aircraft with consideration given for return to service. Airbus recommends that A318, A319, A320 or A321 operators and airport authorities use the data in this manual to develop recovery schemes based on various scenarios, using the equipment available, typical situations and the recommendations included in the ATA specification. Airbus strongly recommends that all data and actions related to the recovery are recorded to ensure that all necessary corrective actions are taken prior to release to service of the aircraft. The data given in this document is accurate at the date of publication. In case of any conflict, the Aircraft Technical Specification shall take precedence. This manual does not include data with regards to any optional modifications. These additions may have an impact on the weight and CG position calculations, defueling and cargo loading procedures. Contact Airbus for further information.

2.

Disclaimer THE USER HEREBY WAIVES, RELEASES AND RENOUNCES ALL WARRANTIES, OBLIGATIONS AND LIABILITIES OF AIRBUS AND RIGHTS, CLAIMS AND REMEDIES OF THE USER AGAINST AIRBUS, EXPRESS OR IMPLIED, ARISING BY LAW OR OTHERWISE, WITH RESPECT TO ANY NON-CONFORMITY OR DEFECT IN THIS DOCUMENT, INCLUDING BUT NOT LIMITED TO: - ANY WARRANTY AGAINST HIDDEN DEFECTS; - ANY IMPLIED WARRANTY OF MERCHANTABILITY OR FITNESS; - ANY IMPLIED WARRANTY ARISING FROM COURSE OF PERFORMANCE, COURSE OF DEALING OR USAGE OF TRADE; - ANY OBLIGATION, LIABILITY, RIGHT, CLAIM OR REMEDY, WHETHER CONTRACTUAL OR DELICTUAL AND WHETHER OR NOT ARISING FROM AIRBUS’S NEGLIGENCE, ACTUAL OR IMPUTED, AND - ANY OBLIGATION, LIABILITY, RIGHT, CLAIM OR REMEDY FOR LOSS OR DAMAGE TO PROPERTY. AIRBUS SHALL HAVE NO OBLIGATION OR LIABILITY, HOWSOEVER ARISING, FOR LOSS OF USE, REVENUE OR PROFIT OR FOR ANY OTHER DIRECT, INCIDENTAL OR CONSEQUENTIAL DAMAGES WITH RESPECT TO ANY NON-CONFORMITY OR DEFECT IN THIS DOCUMENT. AIRBUS SHALL HAVE NO OBLIGATION OR LIABILITY WITH RESPECT TO THE BEHAVIOR OF TOOLING USED FOR THE RECOVERY OF THE AIRCRAFT.

01-00-00

Page 2 Jul 01/09


01-00-02

SEQUENCE OF THE DOCUMENT


This manual obeys the ATA iSpec 2200 specification format.

2.

This document uses a three-part identification reference (XX-XX-XX), in which each pair of digit means : CHAPTER, SECTION and SUBJECT.

3.

The ARM contains two categories of data. A.

Description This part gives the general description of the aircraft or systems, data related to aircraft recovery (recovery team, recovery charts, landing gear, fuel ...) and worksheets. For details about the numbering of the description topics, see FIGURE 01-00-02-991-001-A.

B.

Task For details on the task oriented ARM, see DESC 01-00-02-002-A01. For details about the numbering of the tasks, see FIGURE 01-00-02-991-002-A.

4.

Warnings, Cautions and Notes. - WARNING: Calls attention to use of materials, processes, methods, procedures or limits that must be carefully obeyed to prevent injury or death. - CAUTION: Calls attention to methods and procedures that must be obeyed to prevent damage to equipment. - NOTE: Calls attention to methods that make the work easier or gives explanations.

5.

Abbreviations All the abbreviations used in this manual are detailed in 09-10-02.

6.

Revision bars. The revision bars show that the content is either new or revised.

7.

This manual recommends that the recovery team makes and issues records to help aircraft return to service and carefully monitors the implementation of corrective actions. See 08-00-00.

01-00-02

Page 1 Jul 01/09

5

THREE−DIGIT NUMBER THAT IDENTIFIES THE DESCRIPTIONS. THREE−DIGIT ALPHANUMERICAL IDENTIFIER THAT IDENTIFIES THE CONFIGURATION.

4

5

THAT IDENTIFIES THE CHAPTER−SECTION−SUBJECT.

ATA SIX−DIGIT NUMBER FROM THE ATA ISPEC 2200 BREAKDOWN DOCUMENT

4

1 THRU 3

3

FUNCTION

2

PART

1

N_AR_010002_1_0010101_01_00


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

Numbering System Description FIGURE-01-00-02-991-001-A01

01-00-02

Page 2 Jul 01/09

5

01-00-02

6

5

4

6

THREE−DIGIT ALPHANUMERICAL IDENTIFIER THAT IDENTIFIES THE CONFIGURATION.

IN SEQUENCE TO 800 (MAXIMUM) WITHIN THE PROCEDURE.

N_AR_010002_1_0020101_01_00

801 AND INCREASE, IN SEQUENCE, TO 999 (MAXIMUM). THE SUBTASK NUMBERS BEGIN AT 001 AND INCREASE

TO SEPARATE THE TASKS AND SUBTASKS, THE TASK NUMBERS BEGIN AT

THREE−DIGIT NUMBER ALLOCATED TO EACH TASK AND SUBTASK.

( SEE 01−00−02−002 ) THAT INDICATES THE SPECIFIC PROCEDURE RELATED TO TASKS AND SUBTASKS.

THREE−DIGIT FUNCTION CODE THAT YOU CAN FIND IN THE FUNCTION CODE LIST

THAT IDENTIFIES THE CHAPTER−SECTION−SUBJECT.

ATA SIX−DIGIT NUMBER FROM THE ATA ISPEC 2200 BREAKDOWN DOCUMENT

4

1 THRU 3

3

FUNCTION

2

PART

1


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

Numbering System Task FIGURE-01-00-02-991-002-A01

Page 3 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 01-00-02-002-A01 Task Oriented ARM 1.

General In the ARM, the procedures are contained in tasks. The task is a logical sequence of the procedure steps and is broken down into subtasks. The subtask gives all the details of the significant steps of the procedure. For task numbering, see DESC 01-00-02-001-A01.

2.

Function Codes Each task and subtask has a function code related to its subject. Function Code 000 010 020 040 081 200 284 285 481 500 556 558 581 582 583 584 585 586 587 588 650 680 862

Task/Subtask

Definition Removal Remove/Open For Access Remove Unit/Component/Disconnect/Loosen/Remove Item Deactivation Remove Safety Locks Inspection/Check Inspection of damage Survey Damage and Terrain Install Safety Locks Material and Aircraft Handling Mooring

Task Task/Subtask Task/Subtask Task/Subtask Task/Subtask Task Subtask Task/Subtask Task/Subtask Task/Subtask Task/Subtask Task/Subtask Task/Subtask Task/Subtask Task/Subtask Task/Subtask Task/Subtask Task/Subtask Task/Subtask Task/Subtask Task/Subtask Task/Subtask Task/Subtask

Weight and CG Management Leveling/Lifting Moving the Aircraft Shoring Towing Taxiing Lowering Debogging Stabilizing Fueling/Defueling Drain Fluid De-energize Electrical Network

01-00-02

Page 4 Jul 01/09


Function Code 866 867 869 970 972 980

Task/Subtask

Definition Flight Control Surfaces Movement Landing Gear Movement

Task/Subtask Task/Subtask Task/Subtask Task/Subtask

Miscellaneous Data Recording/Calculating Damage Recording Manual Operation or Positioning

Subtask Subtask

Task/Subtask Function Codes Definition TABLE 1 3.

Task Structure Each recovery task is broken down into the paragraphs that follow: A.

Task Supporting Data (1) General This paragraph gives general information and a short description of the procedure. (2) Inspection This paragraph gives instructions to do a preliminary inspection if necessary. (3) Job Set Up Data This paragraph collects all the generic data which are not in the Job Set Up Information and are necessary to do the actions described in the procedure. (4) Job Set Up Information This paragraph collects all materials, tools and referenced information necessary to do the actions described in the procedure.

B.

Procedure This paragraph is broken down into subtasks. (1) Subtasks The Subtasks contain actions/instructions to do the procedure.

C.

Figures This part contains all illustrations related to the procedure.

01-00-02

Page 5 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 01-00-02-003-A01 Content 1.

2.

3.

4.

MANUAL FRONT MATTER This part of the manual contains the preliminary pages. Items in this part are: A.

The manual front page.

B.

The highlights which give the description of changes at subtask and figure level.

C.

The list of effective content which gives for each task, subtask and figure the last revision date with a change code (which is also used in the highlights): - blank: no changes - R: revised content - N: new content - D: deleted content.

D.

The table of contents which is the list of chapters, subjects, tasks and descriptions contained in the manual.

Chapter 01 - INTRODUCTION This chapter gives general data and information on the A318, A319, A320 or A321 aircraft. Items in this chapter are: A.

A list of related documents in which it is possible to find more information.

B.

A general aircraft description.

Chapter 02 - SURVEY This chapter gives the information that follow for areas which are under Airbus responsibility: A.

An aircraft recovery logic chart, which has been developed for the Aircraft Recovery Manager and his team, to help obey the necessary steps of the recovery process. It is used with a specific CHAPTER/SECTION/SUBJECT of the ARM.

B.

Details on initial inspection, site survey, soil stability, weather conditions and equipment.

C.

Health and safety issues related to aircraft recovery.

Chapter 03 - WEIGHT AND CG MANAGEMENT This chapter contains the items that follow: A.

Weight, H-arm, Y-arm and Z-arm management, with general and specific information for operations such as calculation of the NRW, associated H-arm, Y-arm and Z-arm locations and CG.

B.

The names of documents where it is possible to find aircraft weight and balance data.

C.

The effect of different elements on the CG, such as large aircraft components, fuel, payload…

01-00-02

Page 6 Jul 01/09


5.

6.

7.

Chapter 04 - PREPARATION This chapter contains the details that follow: A.

The tasks which are necessary before leveling/lifting the aircraft (manual operation of flight control surfaces, tethering, ground anchoring, check of weight, H-arm and Y-arm, etc.).

B.

The tethering procedure.

C.

General information and instructions for the manual operation of different units or equipments such as landing gears, flaps, flight controls, cargo doors…

Chapter 05 - WEIGHT REDUCTION This chapter gives: A.

Detailed information on the aircraft fuel system.

B.

The way to manually find the fuel quantity.

C.

Various defueling scenarios.

D.

Detailed information on payload removal.

E.

The removal procedure of the major components.

Chapter 06 - LEVELING AND LIFTING This chapter gives details on: A.

The basic means of leveling/lifting the aircraft. (1) Jacks, (2) Pneumatic Lifting Bags, (3) Cranes.

8.

9.

B.

The method to calculate expected load, travel range and arc movement based on aircraft attitude, NRW and CG calculated in Chapter 03.

C.

Detailed leveling/lifting scenarios.

Chapter 07 - MOVING THE AIRCRAFT This chapter gives: A.

Debogging or towing methods and aircraft limits.

B.

Procedures to be implemented to return a damaged aircraft to the hard surface.

Chapter 08 - POST RECOVERY CORRECTIVE ACTIONS This chapter gives: A.

A link to the post recovery AMM inspection.

B.

An explanation about the need of recording and monitoring corrective actions during the recovery operation.

10. Chapter 09 - APPENDIX The appendices give general information on: A.

Units and Measurements.

01-00-02

Page 7 Jul 01/09


B.

Glossary of terms and list of abbreviations.

C.

General aircraft description.

D.

Recovery preparation.

E.

Tooling and equipment.

F.

Calculation worksheets.

01-00-02

Page 8 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 01-00-02-004-A01 Effectivity Management 1.

The Aircraft Recovery Manual is issued to give the necessary data for A318, A319, A320 or A321 aircraft which are necessary to accomplish a recovery. The configuration is managed at the aircraft level: - A318-100 - A319-100 - A320-100 - A320-200 - A321-100 - A321-200

01-00-02

Page 9 Jul 01/09


01-00-03

DEFINITIONS


Terms Definitions Chapter DESC 09-10-02-001-A01 gives the definition of terms related to aircraft recovery.

2.

Abbreviations Definitions Chapter DESC 09-10-02-003-A01 gives the definitions of abbreviations related to aircraft recovery.

01-00-03

Page 1 Jul 01/09


01-10-01

RELATED DATA

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 01-10-01-002-A01 Airbus Data 1.

General If necessary, you can find additional information/data in the documents that follow: - A318, A319, A320 or A321 Aircraft Characteristics (AC) - A318, A319, A320 or A321 Aircraft Maintenance Manual (AMM) - A318/A319/A320/A321 Illustrated Parts Catalog (IPC) - A318, A319, A320 or A321 Structural Repair Manual (SRM) - A318, A319, A320 or A321 Maintenance Facility Planning Manual (MFP) - A318, A319, A320 or A321 Weight and Balance Manual (WBM) - A318/A319/A320/A321 Illustrated Tool and Equipment Manual (TEM) - A319/A320/A321 Cargo Loading System Manual (CLS) - List of Radioactive and Hazardous Elements Manual (LRE) - CFM56 Engine Manual - IAE V2500 Engine Manual (A319, A320 or A321 only) - PW 6000 Engine Manual (A318 only) - Airn@v, AirbusWorld, …

01-10-01

Page 1 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 01-10-01-001-A01 Other Data 1.

Web Sites This topic gives references to web sites for information only. This list is not exhaustive and is made from the data available to Airbus at issue of the ARM. - http://www.iata.org - http://www.iatp.com NOTE : IATP website and recovery kits are available for IATP members only. NOTE : This chapter gives references to web sites for information only. Airbus shall not be held liable for web site or document content and for update or change of addresses.

2.

Publications - Manuals - Documents This topic gives references to non-Airbus manuals or documents for information only. This list is not exhaustive and is made from the data available to Airbus at issue of the ARM. Airbus shall not be held liable for document content. - Country Regulation - ICAO Annex 14 - ICAO Annex 13 - ICAO 9137 Part 5 - FAA AC 150/5200-31A - FAR 139.325 Airport Emergency Plan - JAR/FAR 145

3.

Airline Documents This topic gives references to airline documents for information only. This list is not exhaustive. - Airline Aircraft Recovery Process Documents (see DESC 09-20-01-004-A01) - Airline Load and Trim Sheet Document - Airline Weight and Balance Manual - Airline Aircraft Modification Record

01-10-01

Page 2 Jul 01/09


01-20-01

GENERAL AIRCRAFT CHARACTERISTICS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 01-20-01-001-A01 General Aircraft Description 1.

The A320 Family of aircraft are subsonic single-aisle aircraft. These aircraft are suitable for passengers and cargo commercial transport. They have two turbofan engines under the wings: - CFM 56-5 engine, - IAE V2500 engine (A319, A320 or A321) - PW 6000 engine (A318 only). The A320 Family aircraft have: - A standard configuration of 3 main fuel tanks (1 tank per wing and a center tank in the center wing box). One or more Additional Center Tanks (ACT) can be installed in the cargo compartments, depending on the airline configuration. - 1 standard 2.5 in refuel/defuel coupling under the wing and 1 gravity refuel cap on each wing (related to the aircraft configuration), - 2 twin-wheel main landing gears (standard configuration) or 2 four-wheel bogies MLG (optional, on A320 only), - 1 nose landing gear with two wheels, - 1 potable water tank in the pressurized section of the fuselage, - A waste water tank, - A lower deck forward cargo compartment, - A lower deck aft cargo compartment, - A lower deck bulk cargo compartment (related to the aircraft configuration).

2.

The appendix gives detailed aircraft description. See 09-00-00.

01-20-01

Page 1 Jul 01/09


**ON A/C A318-100 DESC 01-20-01-002-A01 General Aircraft Data 1.

This section gives general data (weight, payload, fuel capacity, ...) related to the A318-100 aircraft. Refer to the operator’s documentation for accurate values related to the specific aircraft. Weight Variant Maximum Ramp Weight (MRW) Maximum Taxi Weight (MTW) Maximum Takeoff Weight (MTOW) Maximum Land Weight (MLW) Maximum Zero Fuel Weight (MZFW) Operating Empty Weight (OEW) Typical Maximum Payload with CFM Engines Maximum Payload with PW Engines Accommodation Usable Fuel Capacity (Density = 0.785 kg/l) Volume of Cargo Compartments

WV000

WV001

WV002

WV003

WV004

59400 kg (130955 lb)

61900 kg (136466 lb)

63400 kg (139773 lb)

64900 kg (143080 lb)

66400 kg (146387 lb)

59000 kg (130073 lb) 56000 kg (123459 lb)

61500 kg (135584 lb) 56000 kg (123459 lb)

63000 kg (138891 lb) 57500 kg (126766 lb)

64500 kg (142198 lb) 57500 kg (126766 lb)

66000 kg (145505 lb) 57500 kg (126766 lb)

53000 kg (116845 lb)

53000 kg (116845 lb)

54500 kg (120152 lb)

54500 kg (120152 lb)

54500 kg (120152 lb)

With CFM Engines : 38818 kg (85579 lb) With PW Engines : 38661 kg (85233 lb) 14182 kg (31266 lb) 14339 kg (31612 lb) Typical Single Class Layout : 136 Seats 23859 l (6303 US gal)

15682 kg (34573 lb) 15839 kg (34919 lb)

18729 kg (41290 lb) 22.84 m3 (806.59 ft3) Aircraft Data TABLE 1

01-20-01

Page 2 Jul 01/09


Weight Variant Maximum Ramp Weight (MRW) Maximum Taxi Weight (MTW) Maximum Takeoff Weight (MTOW) Maximum Land Weight (MLW) Maximum Zero Fuel Weight (MZFW) Operating Empty Weight (OEW) Typical Maximum Payload with CFM Engines Maximum Payload with PW Engines Accommodation Usable Fuel Capacity (Density = 0.785 kg/l) Volume of Cargo Compartments

WV005

WV006

WV007

WV008

68400 kg (150796 lb)

56400 kg (124341 lb)

61400 kg (135364 lb)

64400 kg (141978 lb)

68000 kg (149914 lb) 57500 kg (126766 lb)

56000 kg (123459 lb) 56000 kg (123459 lb)

61000 kg (134482 lb) 56000 kg (123459 lb)

64000 kg (141096 lb) 56000 kg (123459 lb)

54500 kg (120152 lb)

53000 kg (116845 lb)

53000 kg (116845 lb)

53000 kg (116845 lb)

With CFM Engines : 38818 kg (85579 lb) With PW Engines : 38661 kg (85233 lb) 15682 kg 14182 kg (34573 lb) (31266 lb) 15839 kg 14339 kg (34919 lb) (31612 lb) Typical Single Class Layout : 136 Seats 23859 l (6303 US gal) 18729 kg (41290 lb) 22.84 m3 (806.59 ft3) Aircraft Data TABLE 2

01-20-01

Page 3 Jul 01/09


**ON A/C A319-100 DESC 01-20-01-002-B01 General Aircraft Data 1.

This section gives general data (weight, payload, fuel capacity, ...) related to the A319-100 aircraft. Refer to the operator’s documentation for accurate values related to the specific aircraft. Weight Variant Maximum Ramp Weight (MRW) Maximum Taxi Weight (MTW) Maximum Takeoff Weight (MTOW) Maximum Land Weight (MLW) Maximum Zero Fuel Weight (MZFW) Operating Empty Weight (OEW) Typical Maximum Payload with CFM Engines Maximum Payload with IAE Engines Accommodation Usable Fuel Capacity (Density = 0.785 kg/l) Volume of Cargo Compartments

WV000

WV001

WV002

WV003

64400 kg (141978 lb)

70400 kg (155205 lb)

75900 kg (167331 lb)

68400 kg (150796 lb)

64000 kg (141096 lb)

70000 kg (154324 lb)

75500 kg (166449 lb)

68000 kg (149914 lb)

61000 kg (134482 lb)

61000 kg (134482 lb)

62500 kg (137789 lb)

61000 kg (134482 lb)

57000 kg (125663 lb)

57000 kg (125663 lb)

58500 kg (128970 lb)

57000 kg (125663 lb)

18775 kg (41392 lb) 18674 kg (41169 lb)

17275 kg (38085 lb) 17174 kg (37862 lb)

With CFM Engines : 39725 kg (87579 lb) With IAE Engines : 39826 kg (87801 lb) 17275 kg (38085 lb) 17174 kg (37862 lb) Typical Single Class Layout : 145 Seats 23859 l (6303 US gal) 18729 kg (41290 lb) 27.66 m3 (976.80 ft3) Aircraft Data TABLE 1

01-20-01

Page 4 Jul 01/09


Weight Variant Maximum Ramp Weight (MRW) Maximum Taxi Weight (MTW) Maximum Takeoff Weight (MTOW) Maximum Land Weight (MLW) Maximum Zero Fuel Weight (MZFW) Operating Empty Weight (OEW) Typical Maximum Payload with CFM Engines Maximum Payload with IAE Engines

WV004

WV005

WV006

WV007

68400 kg (150796 lb)

70400 kg (155205 lb)

73900 kg (162922 lb)

75900 (167331 lb)

68000 kg (149914 lb)

70000 kg (154324 lb)

73500 kg (162040 lb)

75500 kg (166449 lb)

62500 kg (137789 lb)

62500 kg (137789 lb)

62500 kg (137789 lb)

61000 kg (134482 lb)

58500 kg (128970 lb)

58500 kg (128970 lb)

58500 kg (128970 lb)

57000 kg (125663 lb)

With CFM Engines : 39725 kg (87579 lb) With IAE Engines : 39826 kg (87801 lb) 18775 kg (41392 lb) 18674 kg (41169 lb) Typical Single Class Layout : 145 Seats 23859 l (6303 US gal) 18729 kg (41290 lb)

Accommodation Usable Fuel Capacity (Density = 0.785 kg/l) Volume of Cargo Compartments

17275 kg (38085 lb) 17174 kg (37862 lb)

27.66 m3 (976.80 ft3) Aircraft Data TABLE 2

Weight Variant Maximum Ramp Weight (MRW) Maximum Taxi Weight (MTW) Maximum Takeoff Weight (MTOW)

WV008

WV009

WV011

WV012

64400 (141978 lb)

66400 (141978 lb)

66400 (141978 lb)

62400 (137568 lb).

64000 kg (141096 lb)

66000 kg (145505 lb)

66000 kg (145505 lb)

62000 kg (136687 lb)

01-20-01

Page 5 Jul 01/09


Weight Variant Maximum Land Weight (MLW) Maximum Zero Fuel Weight (MZFW) Operating Empty Weight (OEW) Typical Maximum Payload with CFM Engines Maximum Payload with IAE Engines Accommodation Usable Fuel Capacity (Density = 0.785 kg/l)

WV008

WV009

WV011

WV012

62500 kg (137789 lb)

62500 kg (137789 lb)

61000 kg (134482 lb)

61000 kg (134482 lb)

58500 kg (128970 lb)

58500 kg (128970 lb)

57000 kg (125663 lb)

57000 kg (125663 lb)

With CFM Engines : 39725 kg (87579 lb) With IAE Engines : 39826 kg (87801 lb) 18775 kg (41392 lb) 18674 kg (41169 lb) Typical Single Class Layout : 145 23859 l (6303 US gal) 18729 kg (41290 lb)

Volume of Cargo Compartments

17275 kg (38085 lb) 17174 kg (37862 lb) Seats


01-20-01

Page 6 Jul 01/09


**ON A/C A320-100 A320-200 DESC 01-20-01-002-C01 General Aircraft Data **ON A/C A320-100 1.

This section gives general data (weight, payload, fuel capacity, ...) related to the A320-100 aircraft. Refer to the operator’s documentation for accurate values related to the specific aircraft. Weight Variant Maximum Ramp Weight (MRW) Maximum Taxi Weight (MTW) Maximum Takeoff Weight (MTOW) Maximum Land Weight (MLW) Maximum Zero Fuel Weight (MZFW) Operating Empty Weight (OEW) - Typical Maximum Payload with CFM Engines Accommodation Usable Fuel Capacity (Density = 0.785 kg/l) Volume of Cargo Compartments

WV000

WV001

WV002

68400 kg (150796 lb)

66400 kg (146387 lb)

68400 kg (150796 lb)

68000 kg (149914 lb)

66000 kg (145505 lb)

68000 kg (149914 lb)

63000 kg (138891 lb) 59000 kg (130073 lb) With CFM Engines : 41244 kg (90927 lb) 17756 kg (39145 lb) Typical Single Class Layout : 180 Seats 23667 l (6252 US gal) 18578 kg (40957 lb)

18556 kg (40909 lb)


**ON A/C A320-200 2.

This section gives general data (weight, payload, fuel capacity, ...) related to the A320-200 aircraft. Refer to the operator’s documentation for accurate values related to the specific aircraft.

01-20-01

Page 7 Jul 01/09


Weight Variant Maximum Ramp Weight (MRW) Maximum Taxi Weight (MTW) Maximum Takeoff Weight (MTOW) Maximum Land Weight (MLW) Maximum Zero Fuel Weight (MZFW) Operating Empty Weight (OEW) Typical Maximum Payload with CFM Engines Maximum Payload with IAE Engines Accommodation Usable Fuel Capacity (Density = 0.785 kg/l) Volume of Cargo Compartments

WV000

WV001

WV002

WV003

73900 kg (162922 lb)

68400 kg (150796 lb)

70400 kg (155205 lb)

75900 kg (167331 lb)

73500 kg (162040 lb)

68000 kg (149914 lb)

70000 kg (154324 lb)

75500 kg (166449 lb)

64500 kg (142198 lb) 60500 kg (133380 lb) With CFM Engines : 42144 kg (92912 lb) With IAE Engines : 41345 kg (91150 lb) 19256 kg (42452 lb) 19155 kg (42230 lb) Typical Single Class Layout : 180 Seats 23859 l (6303 US gal) 26759 l (7069 US gal) with 1 ACT - 29659 l (7835 US gal) with 2 ACT 18729 kg (41290 lb) 21005 kg (46308 lb) with 1 ACT - 23282 kg (51328 lb) with 2 ACT 37.42 m3 (1321.47 ft3) Aircraft Data TABLE 2

Weight Variant Maximum Ramp Weight (MRW) Maximum Taxi Weight (MTW) Maximum Takeoff Weight (MTOW) Maximum Land Weight (MLW)

WV004

WV005

WV006

WV007

71900 kg (158512 lb)

67400 kg (148592 lb)

66400 kg (146387 lb)

77400 kg (170638 lb)

71500 kg (157630 lb)

67000 kg (147710 lb)

66000 kg (145505 lb)

77000 kg (169756 lb)

64500 kg (142198 lb)

01-20-01

Page 8 Jul 01/09


Weight Variant Maximum Zero Fuel Weight (MZFW) Operating Empty Weight (OEW) Typical Maximum Payload with CFM Engines Maximum Payload with IAE Engines Accommodation Usable Fuel Capacity (Density = 0.785 kg/l) Volume of Cargo Compartments

WV004

WV005

WV006

WV007

60500 kg (133380 lb) With CFM Engines : 42144 kg (92912 lb) With IAE Engines : 41345 kg (91150 lb) 19256 kg 19256 kg (42452 lb) (42452 lb) 19155 kg 19155 kg (42230 lb) (42230 lb) Typical Single Class Layout : 180 Seats 23859 l (6303 US gal) 26759 l (7069 US gal) with 1 ACT - 29659 l (7835 US gal) with 2 ACT 18729 kg (41290 lb) 21005 kg (46308 lb) with 1 ACT - 23282 kg (51328 lb) with 2 ACT 37.42 m3 (1321.47 ft3) Aircraft Data TABLE 3

Weight Variant Maximum Ramp Weight (MRW) Maximum Taxi Weight (MTW) Maximum Takeoff Weight (MTOW) Maximum Land Weight (MLW) Maximum Zero Fuel Weight (MZFW) Operating Empty Weight (OEW) Typical Maximum Payload with CFM Engines

WV008

WV009

WV010

WV011

73900 kg (162922 lb)

75900 kg (167331 lb)

77400 kg (170638 lb)

75900 kg (167331 lb)

73500 kg (162040 lb) 64500 kg (142198 lb)

75500 kg (166449 lb)

77000 kg (169756 lb)

75500 kg (166449 lb) 66000 kg (145505 lb)

61000 kg (134482 lb)

62500 kg (137789 lb)

With CFM Engines : 42144 kg (92912 lb) With IAE Engines : 41345 kg (91150 lb) 19756 kg (43555 lb)

21256 kg (46861 lb)

01-20-01

Page 9 Jul 01/09


Weight Variant WV008 WV009 WV010 WV011 21155 kg Maximum Payload 19655 kg (46639 lb) with IAE Engines (43332 lb) Typical Single Class Layout : 180 Seats Accommodation 23859 l (6303 US gal) Usable Fuel 26759 l (7069 US gal) with 1 ACT - 29659 l (7835 US gal) with 2 ACT Capacity (Density = 0.785 18729 kg (41290 lb) kg/l) 21005 kg (46308 lb) with 1 ACT - 23282 kg (51328 lb) with 2 ACT Volume of Cargo 37.42 m3 (1321.47 ft3) Compartments Aircraft Data TABLE 4 Weight Variant Maximum Ramp Weight (MRW) Maximum Taxi Weight (MTW) Maximum Takeoff Weight (MTOW) Maximum Land Weight (MLW) Maximum Zero Fuel Weight (MZFW) Operating Empty Weight (OEW) Typical Maximum Payload with CFM Engines Maximum Payload with IAE Engines Accommodation Usable Fuel Capacity (Density = 0.785 kg/l)

WV012

WV013

WV014

WV015

WV016

77400 kg (170638 lb)

71900 kg (158512 lb)

73900 kg (162922 lb)

78400 kg (172842 lb)

73900 kg (162922 lb)

77000 kg (169756 lb) 66000 kg (145505 lb)

71500 kg (157630 lb) 64500 kg (142198 lb)

73500 kg (162040 lb)

78000 kg (171961 lb)

73500 kg (162040 lb)

62500 kg (137789 lb)

61000 kg (134482 lb)

61500 kg (135584 lb)

61000 kg (134482 lb)

62500 kg (137789 lb)

With CFM Engines : 42144 kg (92912 lb) With IAE Engines : 41345 kg (91150 lb) 21256 kg 19756 kg 20256 kg 19756 kg 21256 kg (46861 lb) (43555 lb) (44657 lb) (43555 lb) (46861 lb) 21155 kg 19655 kg 20155 kg 19655 kg 21155 kg (46639 lb) (43332 lb) (44434 lb) (43332 lb) (46639 lb) Typical Single Class Layout : 180 Seats 23859 l (6303 US gal) 26759 l (7069 US gal) with 1 ACT - 29659 l (7835 US gal) with 2 ACT 18729 kg (41290 lb) 21005 kg (46308 lb) with 1 ACT - 23282 kg (51328 lb) with 2 ACT

01-20-01

Page 10 Jul 01/09


Weight Variant Volume of Cargo Compartments

WV012

WV013

WV014

WV015

WV016


01-20-01

Page 11 Jul 01/09


**ON A/C A321-100 A321-200 DESC 01-20-01-002-D01 General Aircraft Data **ON A/C A321-100 1.

This section gives general data (weight, payload, fuel capacity, ...) related to the A321-100 aircraft. Refer to the operator’s documentation for accurate values related to the specific aircraft. Weight Variant Maximum Ramp Weight (MRW) Maximum Taxi Weight (MTW) Maximum Takeoff Weight (MTOW) Maximum Land Weight (MLW) Maximum Zero Fuel Weight (MZFW) Operating Empty Weight (OEW) Typical Maximum Payload with CFM Engines Maximum Payload with IAE Engines Accommodation Usable Fuel Capacity (Density = 0.785 kg/l) Volume of Cargo Compartments

WV000

WV001

WV002

WV003

WV004

83400 kg (183865 lb)

85400 kg (188275 lb)

83400 kg (183865 lb)

85400 kg (188275 lb)

78400 kg (172842 lb)

83000 kg (182984 lb) 73500 kg (162040 lb)

85000 kg (187393 lb) 73500 kg (162040 lb)

83000 kg (182984 lb) 74500 kg (164244 lb)

85000 kg (187393 lb) 74500 kg (164244 lb)

78000 kg (171961 lb) 73500 kg (162040 lb)

69500 kg (153221 lb)

69500 kg (153221 lb)

70500 kg (155426 lb)

70500 kg (155426 lb)

69500 kg (153221 lb)

With CFM Engines : 46856 kg (103300 lb) With IAE Engines : 46959 kg (103527 lb) 22644 kg 23644 kg 22644 kg TBD (49921 lb) (52126 lb) (49921 lb) 22541 kg 23541 kg 22541 kg TBD (49694 lb) (51899 lb) (49694 lb) Typical Single Class Layout : 220 Seats 23700 l (6261 US gal) 26692 l (7051 US gal) with 1 ACT - 29684 l (7842 US gal) with 2 ACT 18604 kg (41015 lb) 20953 kg (46193 lb) with 1 ACT - 23301 kg (51370 lb) with 2 ACT 51.72 m3 (1826.47 ft3) Aircraft Data TABLE 1

01-20-01

Page 12 Jul 01/09


Weight Variant Maximum Ramp Weight (MRW) Maximum Taxi Weight (MTW) Maximum Takeoff Weight (MTOW) Maximum Land Weight (MLW) Maximum Zero Fuel Weight (MZFW) Operating Empty Weight (OEW) Typical Maximum Payload with CFM Engines Maximum Payload with IAE Engines Accommodation Usable Fuel Capacity (Density = 0.785 kg/l) Volume of Cargo Compartments

WV005

WV006

WV007

WV008

83400 kg (183865 lb)

78400 kg (172842 lb)

80400 kg (177252 lb)

89400 kg (197093 lb)

83000 kg (182984 lb) 75000 kg (165347 lb)

78000 kg (171961 lb) 74500 kg (164244 lb)

80000 kg (176370 lb) 73500 kg (162040 lb)

89000 kg (196211 lb) 75000 kg (165347 lb)

71000 kg (156528 lb)

70500 kg (155426 lb)

69500 kg (153221 lb)

71500 kg (157630 lb)

With CFM Engines : 46856 kg (103300 lb) With IAE Engines : 46959 kg (103527 lb) 24144 kg 23644 kg 22644 kg (53228 lb) (52126 lb) (49921 lb) 24041 kg 23541 kg 22541 kg (53001 lb) (51899 lb) (49694 lb) Typical Single Class Layout : 220 Seats 23700 l (6261 US gal) 26692 l (7051 US gal) with 1 ACT - 29684 l (7842 US gal) with

24644 kg (54331 lb) 24541 kg (54104 lb)

2 ACT

18604 kg (41015 lb) 20953 kg (46193 lb) with 1 ACT - 23301 kg (51370 lb) with 2 ACT 51.72 m3 (1826.47 ft3) Aircraft Data TABLE 2

**ON A/C A321-200 2.

This section gives general data (weight, payload, fuel capacity, ...) related to the A321-200 aircraft. Refer to the operator’s documentation for accurate values related to the specific aircraft. Weight Variant Maximum Ramp Weight (MRW) Maximum Taxi Weight (MTW)

WV000 89400 kg (197093 lb)

WV001

WV002

WV003

93400 kg (205912 lb)

89400 kg (197093 lb)

91400 kg (201502 lb)

01-20-01

Page 13 Jul 01/09


Weight Variant Maximum Takeoff Weight (MTOW) Maximum Land Weight (MLW) Maximum Zero Fuel Weight (MZFW) Operating Empty Weight (OEW) Typical Maximum Payload with CFM Engines Maximum Payload with IAE Engines

WV000 89000 kg (196211 lb) 75500 kg (166449 lb)

WV001 93000 kg (205030 lb) 77800 kg (171520 lb)

WV002 89000 kg (196211 lb) 77800 kg (171520 lb)

WV003 91000 kg (200621 lb) 77800 kg (171520 lb)

71500 kg (157630 lb)

73800 kg (162701 lb)

73800 kg (162701 lb)

73800 kg (162701 lb)

Accommodation Usable Fuel Capacity (Density = 0.785 kg/l)

Typical Single Class Layout : 220 Seats 23700 l (6261 US gal) 26692 l (7051 US gal) with 1 ACT - 29684 l (7842 US gal) with 2 ACT 18604 kg (41015 lb) 20953 kg (46193 lb) with 1 ACT - 23301 kg (51370 lb) with 2 ACT


51.72 m3 (1826.47 ft3)


26944 kg (59401 lb)

24541 kg (54104 lb)

26841 kg (59174 lb)

Aircraft TABLE 3 Weight Variant Maximum Ramp Weight (MRW) Maximum Taxi Weight (MTW) Maximum Takeoff Weight (MTOW) Maximum Land Weight (MLW) Maximum Zero Fuel Weight (MZFW)

WV004

WV005

WV006

87400 kg (192684 lb)

85400 kg (188275 lb)

83400 kg (183865 lb)

83400 kg (183865 lb)

87000 kg (191802 lb) 75500 kg (166449 lb)

85000 kg (187393 lb) 75500 kg (166449 lb)

83000 kg (182984 lb) 75500 kg (166449 lb)

83000 kg (182984 lb) 73500 kg (162040 lb)

71500 kg (157630 lb)

71500 kg (157630 lb)

71500 kg (157630 lb)

69500 kg (153221 lb)

01-20-01

WV007

Page 14 Jul 01/09


Weight Variant Operating Empty Weight (OEW) Typical Maximum Payload with CFM Engines Maximum Payload with IAE Engines Accommodation Usable Fuel Capacity (Density = 0.785 kg/l)

WV004

WV005

WV006

WV007


22644 kg (49921 lb)

24541 kg (54104 lb)

22541 kg (49694 lb)




Weight Variant Maximum Ramp Weight (MRW) Maximum Taxi Weight (MTW) Maximum Takeoff Weight (MTOW) Maximum Land Weight (MLW) Maximum Zero Fuel Weight (MZFW) Operating Empty Weight (OEW) Typical Maximum Payload with CFM Engines

WV008

WV009

WV010

WV011

80400 kg (177252 lb)

78400 kg (172842 lb)

85400 kg (188275 lb)

93900 kg (207014 lb)

80000 kg (176370 lb) 73500 kg (162040 lb)

78000 kg (171961 lb) 73500 kg (162040 lb)

85000 kg (187393 lb) 77800 kg (171520 lb)

93500 kg (206132 lb) 77800 kg (171520 lb)

69500 kg (153221 lb)

69500 kg (153221 lb)

73800 kg (162701 lb)

73800 kg (162701 lb)


26944 kg (59401 lb)

01-20-01

Page 15 Jul 01/09


Weight Variant Maximum Payload with IAE Engines

WV008

WV009

WV010

22644 kg (49921 lb)

WV011 26841 kg (59174 lb)

Accommodation Usable Fuel Capacity (Density = 0.785 kg/l)




01-20-01

Page 16 Jul 01/09


SURVEY 02-00-00

SURVEY


Introduction The objective is to define a recovery scenario based on a recovery plan and implement it: - Without causing secondary damage, - By ensuring traceability of actions performed. The recovery must be set up and controlled according to a recovery process. If a recovery contributing factor (see FIGURE 02-00-00-991-001-A) changes or is not as expected, each section must be reviewed to reconsider the recovery process. The recovery process is detailed in chapter 02-10-01 and is valid when there is no worldwide recovery standard procedure for events of an infinite variety, even if there are basic leveling techniques: - Use of Jacks (see 06-30-00), - Use of Pneumatic Lifting Bags (see 06-40-00), - Use of Cranes (see 06-50-00). The ARM planning chart, aircraft recovery logic chart or the IATA aircraft recovery quick reference checklist could be used to support this recovery process (see 09-20-01).

2.

Recovery Secondary Damage The objective of a successful aircraft recovery operation is to move the aircraft from the incident or accident site to a repair area or facility without causing any secondary damage. The secondary damage is a damage which is not due to the initial event, and can increase the repair time. However, due to time or cost constraints, secondary damage will be accepted from involved parties. In that case make sure that the time saving is acceptable in comparison with the cost. The insurance underwriters can probably contest any secondary damage. Therefore every step of the recovery process must be continually monitored with appropriate action taken to prevent it. NOTE : The damage on airport infrastructure or field can be considered as secondary damage if adequate action is not done in due time.

02-00-00

Page 1 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

LOCATION OF RECOVERY

AIRCRAFT SECURITY

OPERATION CONTROL− MONITORING REPORTING

AIRCRAFT DAMAGE ASSESSMENT FOR RECOVERY PURPOSE

AIRCRAFT RELEASE FROM INVESTIGATIVE AUTHORITY − PLANNING − LEAD TIME − LOGISTICS − CONTRACT

REPAIR TO ENABLE RECOVERY

AIRCRAFT AND TOOLING STABILITY

RECOVERY SCENARIO POST RECOVERY ACTIONS DUE TO RECOVERY SCENARIO

TERRAIN ANALYSIS

MISCELLANEOUS TOOLING AVAILABILITY TOWING / DEBOGGING

INTENTIONAL SECONDARY DAMAGE

AIRCRAFT LEVELING

AIRCRAFT LIFTING

AIRCRAFT TETHERING

AIRCRAFT WEIGHT AND BALANCE MANAGEMENT

N_AR_020000_1_0010101_01_01

Recovery Process Contributing Factors FIGURE-02-00-00-991-001-A01

02-00-00

Page 2 Jul 01/09


02-10-01

CHARTS AND GUIDES

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 02-10-01-001-A01 Aircraft Recovery Process 1.

General The recovery methods used are specific to each recovery operation, are dependent on multiple drivers and constraints, including non aircraft specific drivers, as well as the individual aircraft recovery considerations. The recovery process can be divided into five basic sections: - Survey, - Planning, - Preparation, - Recovery, - Reporting. A.

Survey (1) Before you get access to the incident or accident site and while waiting for release of the aircraft from the Investigative Authorities, some preliminary tasks can be carried out. Some general issues are: - Get and record the initial incident or accident data, - Secure the site: fire, theft and access control, - Confirm that members of the Aircraft Recovery Team are available, - Arrange delivery of any local aircraft recovery equipment, - Make communication with airport and Investigative Authorities, - Identify the hazardous materials which are on board, - Get an airport plan to assess aircraft or recovery team travel path difficulty, etc. (2) After access to the incident or accident site, you must do a detailed inspection and a record of the items that follow: - Integrity of the aircraft structure and landing gear, - Survey of the soil conditions, - Local weather conditions, - Personnel health and safety issues, - Environmental concerns. (3) The other issues to consider if the incident took place at a secondary or international airport are: - Transportation of personnel and equipment, - Visas, passports and vaccinations certificates, - Hotels and local transport.

B.

Planning The main planning issues are (not in order of importance) :

02-10-01

Page 1 Jul 01/09


-

Identification of your recovery drivers, Adverse weather conditions or critical forecast which can have an impact on material required, recovery plan and recovery team operation, etc. Limitation of airport use with the disabled aircraft, Type of leveling, lifting or removal plan, Aircraft weight and balance management operation, if necessary, Unserviceable aircraft systems, Storage of removed fuel, Aircraft movement possibility and path, Compilation of all corrective actions, necessary logistics and planning, Necessary tooling.

C.

Preparation The main preparation issues are (not necessary in the applicable order) : - Control weight and CG by removal or transfer of the required amount of fuel and payload, - Make the aircraft stable, - Assemble the required equipment for the leveling/lifting method that you will use, - Remove components which are damaged, - Remove components to help the weight reduction, - Test and stabilize the soil if necessary.

D.

Recovery The main recovery issues are (in priority order) : - Obey the safety conditions for personnel, - Monitor and record load when you level, lift and move the aircraft, - Level the aircraft as required, - Lift the aircraft as required, - Move the aircraft.

E.

Reporting It is necessary to do the recovery records. The Recovery Manager must hand these records over to the maintenance team. They will be used to do the necessary corrective action and release the aircraft back to service, for systems and structure.

02-10-01

Page 2 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 02-10-01-002-A01 Aircraft Recovery Logic Chart 1.

General The Aircraft Recovery Logic Charts (see DESC 09-20-01-002-A01) are an aid for the Aircraft Recovery Manager and his team. The recovery charts describe the necessary steps of the recovery process and can be used as a checklist by ticking off the boxes when completed. Although detailed, the chart must be used with the complete ARM. These charts give the specific areas of the ARM where you can find additional and more detailed data on a specific subject.

02-10-01

Page 3 Jul 01/09


02-20-01

INITIAL AIRCRAFT SURVEY

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 02-20-01-285-801-A01 Initial Aircraft Survey 1.

General A detailed aircraft condition report must be completed as soon as possible to help the basic approach to the recovery process, to ensure safety of the personnel and to anticipate the repairs. The inspection and the subsequent report do not need to be as detailed for the recovery as for repair of the aircraft. Photographs, sketches, measurements, notes, etc. can complete the documentation. Digital cameras, video recorders and pocket audio recorders can help to record the data. The documentation will help engineering staff, insurance surveyors and manufacturer representatives to discuss the details of the recovery scenarios/options. This information will be helpful to fill in a report when the recovery is completed. The future airworthiness of the aircraft can be dependent on the accuracy of the data recorded during the recovery operation. These records must include accurate figures on all loads applied to the aircraft during the recovery. In most cases, the accident investigation will be more important than the aircraft recovery process. The objective of the accident investigation is to determine the cause of the incident or accident and provide details to prevent the re-occurrence of such an event. Keep in mind that the time between the notification of the event and release of the aircraft by the Investigative Authorities can be several hours. If the Investigative Authority asks for removal of the Aircraft Flight Data and Cockpit Voice Recorders, qualified personnel must do it and obey AMM procedures. These units are to be handed over to the Investigative Authority. In return, the Investigative Authority will give you a receipt with the aircraft registration and the serial numbers of the removed units. It is necessary to note current and forecast weather.

2.

Inspections It is necessary to estimate the fuel quantity, the cargo on board. It is also necessary to identify and quantify hazardous materials with any required personnel protective equipment.

3.

Job Setup References Not Applicable.

02-20-01

Page 1 Jul 01/09


4.

Job Set-up Information A.

Referenced Information REFERENCE AMM

DESIGNATION Referenced Information TABLE 1

5.

Procedure WARNING : DO NOT CLIMB ON, GO INTO OR GO BELOW THE AIRCRAFT UNTIL THE AIRCRAFT IS STABLE. WARNING : MAKE SURE THAT THE AIRCRAFT IS CORRECTLY GROUNDED. NOTE : The information or principle contained in this chapter are given as a guide to assist an aircraft recovery. Subtask 02-20-01-284-001-A01 A.

Inspection of Damage (1) Without climbing on, going into or going below the aircraft, identify and record all obvious and visible damage. Note the location on the fuselage with frame (station) and stringer numbers, and on the wing with rib and station numbers. (2) The types of damage include cracked, creased, distorted or torn fuselage and wing skin panels and also missing or broken fasteners (bolts, rivets…) and fittings. (3) These types of damage are signs of failed structural components and must be considered as suspect. These failed structural components cannot be relied on to carry their designed loads. It is necessary to do a more detailed inspection on these areas prior to leveling, lifting or moving the aircraft. (4) It is necessary to record any evidence of fire or overheating. (5) It is also necessary to identify missing and damaged components such as landing gear, flap sections and non-structural fairings. Broken fairings can be a sign of hidden damage to other structural areas. (6) It is necessary to do a more detailed inspection on these areas prior to leveling, lifting or moving the aircraft.

Subtask 02-20-01-680-001-A01 B.

Fluid Leaks (1) Fluid leaks must be identified.

02-20-01

Page 2 Jul 01/09


(2) These fluid leakages can be fuel, hydraulic fluid, lavatory waste water, potable water and any fluid transported in the cargo compartments. At the first indication of a fluid leak, the airport or Investigative Authorities must call for a hazardous materials response company to contain these leaking fluids. (3) Cap lines and manually close valves to stop or control fluid leaks. Or temporarily plug holes or openings to stop the flow. If there is a fuel leak, defueling must be a primary task. NOTE : This step can be required at any point during the initial aircraft survey. Subtask 02-20-01-862-001-A01 C.

Batteries (1) If there is any structural damage on the fuselage or wings, it is necessary to remove or isolate the aircraft batteries as soon as the aircraft is stable. NOTE : This step can be required at any point during the initial aircraft survey. (2) It is possible to keep the batteries connected if there is no structural or system damage. This can be useful later for the recovery process. This decision can be re-examined during the survey and recovery. NOTE : At this point, it is possible to try to make the aircraft stable and safe so that it is possible to do a detailed inspection in and below the aircraft.

Subtask 02-20-01-869-001-A01 D.

Landing Gear WARNING : MAKE SURE THAT LANDING GEAR DOWNLOCK PINS ARE INSTALLED IF THEIR INSTALLATION IS POSSIBLE. (1) If a landing gear malfunction caused the event, it can be possible to continue to use the aircraft landing gear to move the aircraft when lifted. It is necessary to make sure that the structure and landing gear (when extended) can support the aircraft weight. Examples are: - One or more landing gear(s) remained retracted at touchdown, - One or more landing gear(s) collapsed after touchdown due to downlock failures, - One or more landing gear(s) folded or collapsed when the aircraft left the runway and bogged down in mud, snow or sand. (2) In these cases, it can be possible to extend and lock the landing gear down after lifting the aircraft and after carrying out temporary repairs to strengthen or brace damaged parts. If repairs are necessary, it is usually less difficult and less time consuming to do these repairs than to have secondary damage when moving the aircraft on a trailer or a recovery transport vehicle. (3) Make sure that spare landing-gear assemblies are available to replace damaged or missing ones, if required.

02-20-01

Page 3 Jul 01/09


02-20-02

INITIAL SITE SURVEY

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 02-20-02-285-801-A01 Initial Site Survey 1.

General This procedure gives details on how to do a full survey of the incident site around the aircraft.

2.

Inspections Not Applicable.

3.

Job Setup References Get an airport map from the airport authority (we recommend a topographical map, which includes subterranean infrastructure localization) of the incident area.

4.

Procedure NOTE : The information or principle contained in this chapter are given as a guide to assist an aircraft recovery. Subtask 02-20-02-285-001-A01 A.

Terrain (1) If the ground is sufficiently flat, the recovery process can be more direct. It will be more difficult to move the aircraft on a rolling terrain with hills and it can be necessary to grade the ground. You can report on the airport site plan the position of the aircraft, the flatness, slopes, hills, width and depth of any ditches or culverts and surrounding vegetation. You can examine the area to know if there is any animal life (rodents and snakes).

Subtask 02-20-02-285-002-A01 B.

Soil Characteristics (1) The load bearing capacity is very important. This information is necessary to set up the support equipment to level, lift or move the aircraft. It is also necessary to do the selection of the type of tethering. The type of ground anchors is dependent on the soil properties. (2) The type of soil can be noted in addition to the substrate. It is possible to use the ruts made by the landing gear to identify the subsurface soil type. (3) Subterranean airport infrastructure must be known. Signs of recent excavations must be noted. The airport site plan must be amended to indicate any of these areas. Signs of recent excavations usually show soft and unstable ground.

02-20-02

Page 1 Jul 01/09


This information is very important, as it will influence the path to move the aircraft during the recovery. (4) One of the standards used to compare different soil conditions is the California Bearing Ratio or CBR. This test measures the load necessary to make a plunger of a standard area penetrate a soil sample. The information is recorded on a standard graph and the plot of the test gives the CBR result of the soil test. The CBR is a procedure to put a figure on the inherent strength of the soil. The soil must have a homogeneous CBR rating through a sufficient depth. For more details, you can refer to a ground engineer. (5) The possible effect of rainfall on the ground load bearing capabilities can change with the surface hardness, smoothness or drainage. Use pumps to remove standing water and dig drainage ditches from the work area. Subtask 02-20-02-500-001-A01 C.

Access Routes (1) Access routes to the incident site can be planned with the airport site map. In most cases, it is necessary to go across active runways. The air traffic control service must plan and control these routes. (2) Carefully review of the path of the aircraft from the runway to the resting point. The distance to runways, taxiways and aprons, the type of soil, rut depth and terrain will all influence in which direction the aircraft will be moved once the actual recovery starts. (3) Pavement requirements for the particular aircraft are derived from the static analysis of loads imposed on the main landing gear struts. These main landing gear loads are used as the point of entry to the pavement design charts (See AC-07-00-00). Make sure that the surfaces you will move the aircraft on are able to support these loads. (4) Make sure that the specific ground tooling or road used to level, lift or move the aircraft are able to support aircraft load. (5) Make sure that the loads applied to the aircraft are not more than aircraft allowable loads.

Subtask 02-20-02-869-001-A01 D.

Weather (1) Weather conditions can play a major role during aircraft recovery operations. General meteorological conditions (temperature, wind speed and precipitation) must be recorded. (2) Temperature, both extreme heat and extreme cold, will determine the type of clothing, meals and liquid intake for the manpower involved in the recovery. The need for shelter from heat or cold will also have to be determined.

02-20-02

Page 2 Jul 01/09


(3) Forecast conditions must be acquired and recorded. The forecast will help to prepare the type of personal protective clothing and to determine the recovery plan. (4) Make sure that the required tooling can be used within forecast conditions. (5) Wind and projected wind gust speeds will determine the amount of tethering and will influence any attempts at lifting the aircraft. (6) Any type of precipitation will have consequences in the grading, soil support and general recovery operation.

02-20-02

Page 3 Jul 01/09


02-30-01

LANDING GEAR

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 02-30-01-200-801-A01 Landing Gear Survey 1.

General WARNING : LET THE BRAKES AND THE WHEELS BECOME COOL BEFORE YOU GO NEAR THE LANDING GEAR. DO NOT APPLY A LIQUID OR GAS FIRE EXTINGUISHER DIRECTLY ON A HOT WHEEL OR BRAKE UNIT. IF YOU DO NOT OBEY THESE PRECAUTIONS, THERE IS A RISK OF EXPLOSION. WARNING : MAKE SURE THAT THE LANDING GEAR AND DOOR TRAVEL RANGES ARE CLEAR. MOVEMENT OF THE LANDING GEAR AND DOORS CAN CAUSE INJURY AND/OR DAMAGE. WARNING : MAKE SURE THAT THE LANDING GEAR IS UPLOCKED BEFORE YOU OPEN THE GEAR DOORS MANUALLY. IF THE GEAR IS NOT UPLOCKED, THE WEIGHT OF THE GEAR CAN BE ON THE DOORS. IF YOU OPEN THE DOORS IN THIS CONDITION, THERE IS A RISK THAT THE LANDING GEAR WILL EXTEND BY GRAVITY AND CAUSE INJURY. The principles outlined in this chapter are provided as a guide to assist aircraft recovery. The chapter gives the general inspections required to find the extent of any damage to the landing gear and the recommended steps required to recover the aircraft. You must do the applicable inspections before moving the aircraft. For the description of the landing gears, see 09-10-16.

2.


Referenced Information REFERENCE TASK 02-30-01-481-801-A01 09-10-16 04-20-00 07-60-00 07-40-03 07-40-00 06-00-00 AMM 29-10-00-864 AMM 24-41-00-862 AMM 32-51-00-040 AMM 32-40-00-040

DESIGNATION TASK 02-30-01-481-801-A01-Installation of the Safety Devices on Landing Gears 09-10-16-LANDING GEARS 04-20-00-STABILIZING THE AIRCRAFT 07-60-00-MOVING DAMAGED AIRCRAFT 07-40-03-TOWING WITH DEFLATED TIRES 07-40-00-TOWING AND DEBOGGING 06-00-00-LEVELING AND LIFTING

02-30-01

Page 1 Jul 01/09


REFERENCE FIGURE 02-30-01-991-001-A FIGURE 02-30-01-991-002-A

DESIGNATION FIGURE 02-30-01-991-001-A-Landing Gear FIGURE 02-30-01-991-002-A-Landing Gear Referenced Information TABLE 1

3.

Procedure Subtask 02-30-01-867-001-A01 A.

Safety Precautions (1) Make sure that the aircraft is stable, see 04-20-00. (2) Make sure that the Ground Lock Pins are installed on the landing gear where possible, see TASK 02-30-01-481-801-A01. (3) Make sure that the MLG and NLG wheels are chocked where possible. (4) Make sure that the Landing Gear Control Lever (6GA) is in the DOWN position and put a warning notice to tell people not to operate the landing gear. (5) On the center pedestal, make sure that the Free-Fall Control-Handle is in normal position and safe, see FIGURE 02-30-01-991-001-A. (6) If the aircraft wheel brake hydraulic circuits are serviceable: (a) On the center pedestal, see FIGURE 02-30-01-991-002-A, set the PARK BRK switch to the ON position. (b) On the center panel, see FIGURE 02-30-01-991-002-A, make sure that the pressure indication on the triple-indicator is correct. The indicator must be in the Green area. (c) Make sure that the Green and Yellow hydraulic systems are depressurized, see AMM 29-10-00-864. (d) Make sure that the aircraft electrical circuits are de-energised, see AMM 24-41-00-862. (7) Put safety barriers around the Landing Gear(s) that are not correctly extended and downlocked.

Subtask 02-30-01-867-003-A01 B.

Landing Gear Positions (1) A Landing Gear can be found in the following conditions: (a) Fully extended and downlocked. (b) Not fully extended or retracted. (c) Retracted and uplocks released (Landing Gear Doors closed).

02-30-01

Page 2 Jul 01/09


(d) Retracted and uplocked. (e) Collapsed or missing. (f)

Bogged.

WARNING : IF THE LANDING GEAR DOES NOT FULLY EXTEND WHEN THE AIRCRAFT IS LEVEL, SAFETY THE LANDING GEAR TO PREVENT UNWANTED MOVEMENT. (2) Before doing the inspection, make sure you know the position of the Landing Gear. (a) Landing Gear fully extended and downlocked, see TASK 02-30-01-481-801-A01: 1

Do the applicable inspection for that Landing Gear (NLG or MLG).

(b) Landing Gear not fully extended or retracted: 1

See 06-00-00 for the procedure to level and lift the aircraft.

2

It will be necessary to secure the Landing Gear to prevent it travelling further and becoming a danger to anyone or to the recovery operations.

3

To support the gear, put a hydraulic lifting platform (lifting capacity 7 tonnes) under the Landing Gear to be supported. Make sure that the lifting surface is covered with support materials, such as tires or foam, to protect the Landing Gear from damage.

4

To further support the gear, raise the platform until the support materials make good contact with the Landing Gear to prevent accidental movement of the gear during the inspection.

5

You must make sure that all other ground lock pins are installed, then in the cockpit, rotate the free-fall extension-handle for three revolutions to clockwise. This will open the hydraulic system to RETURN and allow the unlocked leg to be lifted. See FIGURE 02-30-01-991-001-A.

6


(c) Landing Gear Retracted and uplocked: 1

If the NLG is retracted and uplocked, it must be lowered and downlocked before an inspection can be done, see TBD for the manual extension procedure.

2

If the MLG is retracted and uplocked, it must be lowered and downlocked before an inspection can be done, see TBD for the manual extension procedure.

(d) Landing Gear Retracted and uplocks released (Landing Gear Doors closed) : 1

If the NLG is retracted with the Landing Gear Doors closed, see TBD for the procedure to manually extend the gear, then do the applicable inspection.

2

If the MLG is retracted with the Landing Gear Doors closed, see TBD for the procedure to manually extend the gear, then do the applicable inspection.

02-30-01

Page 3 Jul 01/09


(e) Landing Gear Collapsed or missing: If a Landing Gear is collapsed, missing or unusable, see 07-60-00 for the procedure to move a damaged aircraft using special recovery vehicles. (f)

Landing Gear locked down and bogged down: 1


2

See TBD for the debogging procedure.

Subtask 02-30-01-867-004-A01 C.

Landing Gear Inspection (1) Main Landing Gear (a) Do a visual inspection of the Main Landing Gear, the attachments to the Airframe, the doors. Look for signs of distortions, cracks and ruptures. If this type of damage is found on a component, it must be replaced before you move the aircraft. (b) The following components can be removed if they are not usable or if they will impede the recovery operation: - The wheel brake components, see AMM 32-40-00-040 for information on the deactivation of brake components before you remove them - The Main Door - The Hinged and Fixed Fairings. (c) If the repair or replacement of damaged components is not possible because of general area damage, the aircraft must be recovered on specialist recovery vehicles, see 07-60-00. (d) Do a visual inspection of the tires. If there are deflated tires, see 07-40-03 for the applicable limitations. (2) Nose Landing Gear (a) Do a visual inspection of the Nose Landing Gear, the attachments to the Airframe, the two Forward and two Aft Doors. Look for signs of distortions, cracks and ruptures. If this type of damage is found on a component, it must be replaced before you move the aircraft. (b) The following components can be removed if they are not usable or if they will impede the recovery operation: - The Forward Doors - The Aft Doors - The Nosewheel Steering components. (c) See AMM 32-51-00-040 for the procedure to deactivate the NWS. (d) If the repair or replacement of damaged components is not possible because of general area damage, the aircraft must be recovered on specialized recovery vehicles, see 07-60-00.

02-30-01

Page 4 Jul 01/09


(e) If the NLG is bogged, see TBD. If the NLG is on a hard surface see 07-40-00 (f)

Do a visual inspection of the tires. If there are deflated tires, see 07-40-03 for the applicable limitations.

02-30-01

Page 5 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

B

L/G EXTENSION/RETRACTION LEVER

A G E A R

GRAVITY

GEAR EXTN

G E A R

PULL TURN

L/G MANUAL EXTENSION HANDLE

B N_AR_023001_1_0010101_01_00

Landing Gear LG Control Lever and Free-Fall Control Handle FIGURE-02-30-01-991-001-A01

02-30-01

Page 6 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

B ACCU

PRESS

0

4

3

3 1

1

0 BRAKES PSIx1000

A PARKING BRK

OFF

ON

PARK BRK

B

N_AR_023001_1_0020101_01_00

Landing Gear Brakes - Indication and Control FIGURE-02-30-01-991-002-A01

02-30-01

Page 7 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 02-30-01-481-801-A01 Installation of the Safety Device on Landing Gears 1.

General WARNING : LET THE BRAKES AND THE WHEELS BECOME COOL BEFORE YOU GO NEAR THE LANDING GEAR. DO NOT APPLY A LIQUID OR GAS FIRE EXTINGUISHER DIRECTLY ON A HOT WHEEL OR BRAKE UNIT. IF YOU DO NOT OBEY THESE PRECAUTIONS, THERE IS A RISK OF EXPLOSION. WARNING : MAKE SURE THAT THE LANDING GEAR AND DOOR TRAVEL RANGES ARE CLEAR. MOVEMENT OF THE LANDING GEAR AND DOORS CAN CAUSE INJURY AND/OR DAMAGE. WARNING : MAKE SURE THAT, IF THE LANDING GEAR DOORS ARE OPEN, THEY ARE SAFETIED BEFORE YOU INSTALL THE LANDING GEAR SAFETY-DEVICES. IF THE LANDUNG GEAR DOORS ARE OPEN BUT NOT SAFETIED THERE IS A RISK THAT THEY VCAN CLOSE AND CAUSE INJURY. WARNING : MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE IN POSITION BEFORE YOU START A TASK ON OR NEAR THE FLIGHT CONTROLS, THE FLIGHT CONTROL SURFACES, THE LANDING GEARS AND RELATED DOORS AND COMPONENTS THAT MOVE. MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND CAN CAUSE DAMAGE. The chapter gives the recommended steps to install the safety devices on the landing gears and landing gear doors prior to recover the aircraft. For the description of the landing gears, see 09-10-16.

2.


3.

Job Setup References A.

Safety Precautions Make sure that the aircraft is stable, see 04-20-00. Make sure that the MLG and NLG wheels are chocked where possible. Make sure that the Landing Gear Control Lever (6GA) is in the DOWN position and put a warning notice to tell people not to operate the landing gear. On the center pedestal, make sure that the Free-Fall Control-Handle is in normal position and safe.

02-30-01

Page 8 Jul 01/09


4.


Fixtures, Tools, Test and Support REFERENCE D23080000 MZ23080000 DRT68031 DRT68923 460005833 460007280 460005835 DAH602734 98D32203502000

DESIGNATION PIN-GROUND LOCK, NLG PIN - NLG DOWNLOCK SAFETY SLEEVE - GROUND LOCK SLEEVE-GROUND LOCK GROUND LOCK SLEEVE SLEEVE-GROUNDLOCK GROUND LOCK SLEEVE GROUND LOCK SLEEVE SAFETY PIN - NLG DOOR Fixtures, Tools, Test and Support TABLE 1

B.

Referenced Information REFERENCE 09-10-16 04-20-00 AMM 32-12-00-010-001 AMM 32-22-00-010-001

DESIGNATION 09-10-16-LANDING GEARS 04-20-00-STABILIZING THE AIRCRAFT

Referenced Information TABLE 2 5.


Installation of the Safety Devices on the Landing Gears (1) To install the left and right Main Landing Gear Safety Locks: (a) If a landing gear door is open, make sure: - the ground door-opening handle is in the open position - the ground door-safety lock is installed, see SUBTASK 02-30-01-481-004-A01. (b) Make sure that the piston rod of each lock stay actuating cylinder is clean. NOTE : There are four alternative tools that can be used for this task: - DRT68031 SLEEVE - GROUND LOCK - DRT68923 SLEEVE-GROUND LOCK - 460005833 GROUND LOCK SLEEVE - 460007280 SLEEVE-GROUNDLOCK

02-30-01

Page 9 Jul 01/09


(c) Remove the pin and open the GROUND LOCK SLEEVE. (d) Make sure that the GROUND LOCK SLEEVE is clean and in the correct condition. (e) Put the GROUND LOCK SLEEVE in position on the piston rod of each lock stay actuating cylinder. (f)

Close the GROUND LOCK SLEEVE and install the pin from the inboard side.

(g) Make sure that the flag is in view. (2) To install the Nose Landing Gear Safety Lock: (a) If a landing gear door is open, make sure: - the ground door-opening handle is in the open position - the ground door-safety lock is installed, see SUBTASK 02-30-01-481-004-A01. (b) Make sure that the holes in the NLG lock stay are aligned. NOTE : There are two alternative tools that can be used for this task: - D23080000 PIN-GROUND LOCK, NLG - MZ23080000 PIN - NLG DOWNLOCK SAFETY (c) Make sure that the D23080000 PIN-GROUND LOCK, NLG or the MZ23080000 PIN NLG DOWNLOCK SAFETY is in a clean and correct condition. (d) Install the D23080000 PIN-GROUND LOCK, NLG or the MZ23080000 PIN - NLG DOWNLOCK SAFETY in the holes in the NLG lock stay. (e) Make sure that the flag is in view. Subtask 02-30-01-481-004-A01 B.

Installation of the Safety Devices on the Landing Gears Doors (1) To install the safety devices on the main landing gear doors: (a) Open the applicable MLG door(s). See AMM 32-12-00-010-001. 1

Make sure that the piston rod of the MLG door actuating cylinder is clean.

(b) Remove the pins (1) and open the 460005835 GROUND LOCK SLEEVE or the DAH602734 GROUND LOCK SLEEVE. (c) Make sure that the ground lock sleeve is in a clean and correct condition. (d) Put a ground lock sleeve in position on the piston rod of each of the MLG door actuating cylinders. (e) Close the ground lock sleeve and install the pins (1) from the top. (f)

Make sure that the flag is in view.

(2) To install the safety devices on the nose landing gear doors: (a) Open the NLG doors. See AMM 32-22-00-010-001. (b) Make sure that the holes in the NLG doors and the hinges are aligned.

02-30-01

Page 10 Jul 01/09


(c) Make sure that each 98D32203502000 SAFETY PIN - NLG DOOR is in a clean and correct condition. (d) Install a 98D32203502000 SAFETY PIN - NLG DOOR through the holes in each NLG door and hinge. (e) Make sure that the flag is in view.

02-30-01

Page 11 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 LOCKSTAY ACTUATING CYLINDER

GROUND LOCK SLEEVE

LOCKSTAY ACTUATING CYLINDER

A

FLAG

A LOCKSTAY

B

DOWNLOCK SAFETY PIN FLAG

B

N_AR_023001_1_0200101_01_00

Landing Gear Installation of the Safety Devices FIGURE-02-30-01-991-020-A01

02-30-01

Page 12 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 1

DOOR ACTUATING CYLINDER

FLAG

MLG DOOR ACTUATING CYLINDER

A

A

MAIN DOOR

NLG DOOR SAFETY PIN

B

DOOR HINGE NLG DOOR

B FLAG

RH SHOWN LH SYMETRICAL

NOTE: FOR DETAIL B, PROXIMITY SENSORS OMITTED FOR CLARITY

N_AR_023001_1_0210101_01_00

Landing Gear Doors Installation of the Safety Devices FIGURE-02-30-01-991-021-A01

02-30-01

Page 13 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 02-30-01-867-802-A01 Jacking for Wheel Change 1.

General WARNING : LET THE BRAKES AND THE WHEELS BECOME COOL BEFORE YOU GO NEAR THE LANDING GEAR. DO NOT APPLY A LIQUID OR GAS FIRE EXTINGUISHER DIRECTLY ON A HOT WHEEL OR BRAKE UNIT. IF YOU DO NOT OBEY THESE PRECAUTIONS, THERE IS A RISK OF EXPLOSION. WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY INSTALLED ON THE LANDING GEAR. THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR. CAUTION :

DO NOT DO THIS JACKING FOR WHEEL CHANGE PROCEDURE DURING REFUELING OR DEFUELING PROCEDURES. IF THE AIRCRAFT IS ON JACKS AND IF A FIRE OR IMPORTANT FUEL SPILLAGE OCCURS IT WILL NOT BE POSSIBLE TO MOVE THE AIRCRAFT. This procedure gives details for the replacement of a wheel with deflated tires. 2.


3.

Job Setup References You can lift the aircraft at its maximum weight. Hydraulic Jack Data

Capacity (min) 10000 daN (22481 lbf)

Closed Height (max) 130 mm (5.12 in)

Hydraulic Stroke (min) 171 mm (6.73 in)

10000 daN (22481 lbf)

200 mm (7.87 in)

171 mm (6.73 in)

35000 daN (78683 lbf)

215 mm (8.46 in)

334 mm (13.15 in)

Main Gear (Four Wheel 35000 daN (78683 lbf) Bogie)

125 mm (4.92 in)

255 mm (10.04 in)

Nose Gear Nose Gear (using Inclined Blocks) Main Gear (Twin Wheel)

Hydraulic Jack Specifications TABLE 1 NOTE : If both tires of the nose landing gear are deflated at the same time, the maximum closed height of the hydraulic jack must be 128 mm (5.04 in). Use specific tool TMHCP07-00-00 WHEEL CHANGE AXLE JACK.

02-30-01

Page 14 Jul 01/09


4.


Fixtures, Tools, Test and Support REFERENCE GSE TMHCP07-00-00

DESIGNATION WHEEL CHANGE JACK WHEEL CHANGE AXLE JACK Fixtures, Tools, Test and Support TABLE 2

B.

Referenced Information REFERENCE AMM 32-41-12PB401 AMM 05-51-15-200-001 AMM 32-41-11PB401 FIGURE 02-30-01-991-019-A FIGURE 02-30-01-991-022-A FIGURE 02-30-01-991-023-A

DESIGNATION

FIGURE 02-30-01-991-019-A-Nose Landing Gear FIGURE 02-30-01-991-022-A-Nose Landing Gear FIGURE 02-30-01-991-023-A-Jacking for Wheel Change Referenced Information TABLE 3

5.


Safety Precautions (1) Make sure that the wheels are on the aircraft axis. (2) Make sure that there is sufficient space around the aircraft. (3) Make sure that the aircraft is clear to lift. (4) Make sure that the aircraft is stable. (5) Make sure that the jack adapter is in correct condition.

Subtask 02-30-01-581-001-A01 B.

Jacking of the Nose Landing Gear (1) See FIGURE 02-30-01-991-019-A. See TABLE 1 for hydraulic jack specifications. (2) Install the wheel chocks on the main landing-gear wheels.

02-30-01

Page 15 Jul 01/09


(3) Put the GSE WHEEL CHANGE JACK so that its adapter touches the ball-pad of the shock absorber. NOTE : If both tires of the nose landing gear are deflated at the same time, the maximum closed height of the hydraulic jack must be 128 mm (5.04 in). Use specific tool TMHCP07-00-00 WHEEL CHANGE AXLE JACK. (4) Make sure that the wheel jack is stable and in the vertical position. (5) Make sure that this assembly is level. (6) Operate the jack to lift the tire off the ground. (7) Change the wheel, see AMM 32-41-12PB401. (8) Operate the control of the hydraulic jack slowly to lower the aircraft. Do not lower the aircraft on its wheels suddenly. (9) When the aircraft is on its wheels, remove the hydraulic jack. Subtask 02-30-01-581-002-A01 C.

Towing of the NLG on Inclined Blocks Before Jacking (1) This procedure is necessary when the height of the closed jack is more than the height between the ground and the jacking dome. See FIGURE 02-30-01-991-022-A. Inclined Block Nose Gear

Angle (max) 5 degrees

Height (min) 100 mm (3.94 in)

Inclined Blocs Specifications TABLE 4 The inclined blocks must have sufficient strength to support the aircraft weight. The inclined blocks can be made from: - Heavy timbers or railroad crossties, - Plywood sheets covered with a steel plate of 6 mm (0.24 in) minimum thickness, - Plywood sheets covered with a light-alloy sheet of 20 mm (0.79 in) minimum thickness. (2) Tow the aircraft a small distance to make sure that the nose wheels turn freely. (3) Do the inspection after a tire burst or thread throw or wheel failure, see AMM 05-51-15-200-001. (4) Make sure that GSE WHEEL CHANGE JACK and the INCLINED BLOCKS are in correct condition. (5) Put one inclined block below each nose wheel. Make sure that: - The axes of the inclined block are aligned with the A/C centerline, - The position of the inclined block lets you install the hydraulic jack below the jacking dome.

02-30-01

Page 16 Jul 01/09


(6) For the towing on the inclined blocks, there must be one person in the cockpit to operate the brakes if necessary, and two persons to monitor the wing tips. (7) Pull or push the aircraft on the top flat area of the inclined block. (8) Put the wheel chocks in position in front of and behind the MLG wheels. (9) Remove the towbar from the NLG fitting. (10) Set the PARKING BRK control switch to OFF. (11) Put the GSE WHEEL CHANGE JACKin position and adjust the jack until its adapter touches the jacking dome of the shock absorber. (12) Make sure that the wheel jack is stable and in the vertical position. (13) Operate the jack to lift the tire off the inclined block. (14) Remove the inclined block. (15) Change the wheel, see AMM 32-41-12PB401. (16) Operate the control of the hydraulic jack slowly to lower the aircraft. Do not lower the aircraft on its wheels suddenly. (17) When the aircraft is on its wheels, remove the hydraulic jack. Subtask 02-30-01-581-003-A01 D.

Jacking of the Main Landing Gear (1) See FIGURE 02-30-01-991-023-A. See TABLE 1 for hydraulic jack specifications. (2) Install the wheel chocks on the main landing-gear that is not necessary to change. Install the wheel chocks on the nose landing-gear. (3) Put the GSE WHEEL CHANGE JACK so that its adapter touches the ball-pad of the shock absorber. (4) Make sure that the wheel jack is stable and in the vertical position. (5) Operate the jack to lift the tire off the ground. (6) Change the wheel, see AMM 32-41-11PB401. (7) Operate the control of the hydraulic jack slowly to lower the aircraft. Do not lower the aircraft on its wheels suddenly. (8) When the aircraft is on its wheels, remove the hydraulic jack.

02-30-01

Page 17 Jul 01/09


40 mm APPROX (1.57 in)

A

9°

A

128 mm (5.04 in)

N_AR_023001_1_0190101_01_00

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A A

JACKING POINT

198 mm (7.79 in)

25.4 mm (1 in)

301 mm (11.85 in)

Nose Landing Gear Jacking for Wheel Change FIGURE-02-30-01-991-019-A01

02-30-01

Page 18 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 A

9°

INCLINED BLOCK FLAT AREA

200 mm MIN (APPROX.) (7.87 in)

INCLINED BLOCK 5° MAX

100 mm MIN (3.93 in)

A

198 mm (7.79 in)

=

= D

A A NOTE: DIMENSION "D" MUST BE MORE THAN HYDRAULIC JACK WIDTH.

N_AR_023001_1_0220101_01_00

Nose Landing Gear Inclined Blocks FIGURE-02-30-01-991-022-A01

02-30-01

Page 19 Jul 01/09


N_AR_023001_1_0230101_01_00

TWIN WHEEL TRACK CONTOUR OF TIRES ON GROUND

25.4 mm MIN (1 in)

JACKING POINT

FORK

LH SHOWN RH SYMMETRICAL

927.10 mm (36.5 in)

25.4 mm MIN (1 in)

25.4 mm (1 in)

6.5°

563 mm (22.16 in)

655 mm (25.78 in)

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

Jacking for Wheel Change Twin Wheel Main Landing Gear (Sheet 1 of 2) FIGURE-02-30-01-991-023-A01

02-30-01

Page 20 Jul 01/09


N_AR_023001_1_0230102_01_00

25.4 mm (1 in)

CONTOUR OF TIRES ON GROUND

25.4 mm MIN (1 in)

780 mm (30.70 in) JACKING POINTS

25.4 mm MIN (1 in)

25.4 mm (1 in)

CANTILEVER ARM


380 mm (14.96 in)

FORK

380 mm (14.96 in)

CANTILEVER ARM

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

Jacking for Wheel Change Four Wheel Bogie Main Landing Gear (Sheet 2 of 2) FIGURE-02-30-01-991-023-A01

02-30-01

Page 21 Jul 01/09


02-40-01

HEALTH AND SAFETY ISSUES


The emphasis during all aircraft recovery operations is SAFETY. All necessary precautions must be taken to avoid injury to personnel and the occurrence of secondary damage to the aircraft. Not only the members of aircraft recovery team, but everyone at the incident site must know all the safety issues as they evolve. A number of different factors must be taken into account to make sure the safety issue is properly controlled. Make sure that adherence to a recovery close loop process is ensured to control and set up mitigation plan if needed. By definition this implies that recovery plan engineering, tooling capability and personnel qualification or expertise are correctly assessed. Paragraphs are not in order of importance. A.

Communication Make sure sufficient and correct communication equipment is available for communication at the recovery site. Communication equipment can include two-way radios and cell phones. Voice activated, lightweight headsets with microphones are ideal for recovery operations. Extra batteries or a power supply must be available. A direct link with the air traffic control service will most likely be required, depending on the location of the incident site. The main problem will be to cross active runways and taxiways in order to access the incident or accident site. In most cases the local air traffic control service will provide an alternative access route to the site in order to reduce the amount of communication. It is absolutely mandatory that lines of communication are established and kept open between all groups at the site, including the recovery team, fire department, Investigative Authority, police, airport personnel and any contracted assistance. Short briefing sessions must be held between all groups and parties involved with the recovery process. These briefings will alert personnel to the upcoming steps, and to any possible hazards and dangers.

B.

Personnel It should be understood that the aircraft is by definition not under normal maintenance or operational status. Therefore its recovery involves multiple personnel/parties competencies, which have not necessarily worked previously together and do not know each other’s constraints-outcomes. As parties have incompatible goals it is of prime importance that the recovery manager ensure that information, caution, etc. are well understood and put in practice by all. All personnel at the incident site must have proper and adequate personal protective clothing and equipment. This will change greatly if the existing climate and weather conditions change. Examples: Safety boots, personal breathing mask, rainwear, parkas and gloves, etc.

02-40-01

Page 1 Jul 01/09


Personnel must be kept at a safe distance during any leveling/lifting operation. The recovery manager must make sure that the personnel knows the dangers of steel cable during pulling and winching operations, as well as dangers arising due to the nature of the corrective actions embodiment Make sure that everyone knows the dangers of going into, climbing-on or going below the aircraft until it is stable and or adequately shored. First-aid kits must be available at the site to cope with minor injuries. Detailed information on how to contact and arrange for emergency medical attention must be available. WARNING : MAKE SURE THAT THE AIRCRAFT IS CORRECTLY GROUNDED. WARNING : MAKE SURE THAT THE AIRCRAFT ELECTRICAL NETWORK IS DE-ENERGIZED BEFORE YOU DISCONNECT THE EXTERNAL POWER CONNECTOR. IF YOU DISCONNECT THE EXTERNAL POWER CONNECTOR WHEN THE ELECTRICAL NETWORK IS ENERGIZED, DANGEROUS ARCING CAN OCCUR. WARNING : OPEN, SAFETY/LOCK AND TAG THE CIRCUIT BREAKERS RELATED TO THE BLUE HYDRAULIC SYSTEM ELECTRIC PUMP. THIS PUMP RUNS AUTOMATICALLY WHEN THE AIRCRAFT ELECTRICAL NETWORK IS ENERGIZED AND THE NLG LEG EXTENDED CAUTION :

C.

MAKE SURE THAT THE AIRCRAFT ELECTRICAL NETWORK IS DE-ENERGIZED BEFORE YOU DISCONNECT THE EXTERNAL POWER CONNECTOR. IF YOU DO NOT DO SO, THERE IS A RISK OF ARCING AND THIS CAN CAUSE DAMAGE TO THE AIRCRAFT.

Electrical Systems If you took the decision to leave the aircraft with the batteries connected, do an investigation before you energize the circuits. Leaving the batteries connected can help during the different steps of the recovery process. Before you use external aircraft power-supply to help the recovery operations, make sure that the systems are serviceable. If the aircraft structure is damaged, it is better to disconnect the batteries and not to try energize the aircraft with the external supply.

WARNING : MAKE SURE THAT YOU OBEY ALL THE APPLICABLE SAFETY PRECAUTIONS WHEN YOU WORK ON THE OXYGEN SYSTEM OR WITH OXYGEN EQUIPMENT. D.

Oxygen Systems When the aircraft is stable and it is possible to get into the aircraft, make sure that the oxygen bottle valves in the cockpit and cabin are closed. If they are not, close them manually. If possible, remove the bottles from the aircraft. Take the decision as to remove or secure the oxygen generators. As this is a time-consuming task, this decision will be based on the current dangers involved, the condition of the aircraft and the time available.

02-40-01

Page 2 Jul 01/09


WARNING : MAKE SURE THAT YOU OBEY ALL THE APPLICABLE SAFETY PRECAUTIONS WHEN YOU REMOVE FUEL OR WHEN YOU WORK IN AN ENVIRONMENT WHERE THERE IS FUEL. WARNING : MAKE SURE THAT THE TANKER AND THE AIRCRAFT ARE CONNECTED TO AN APPROVED GROUND AND THAT ELECTRICAL BONDING BETWEEN THE AIRCRAFT AND THE TANKER IS CONNECTED. ONLY IF THESE CONDITIONS ARE MET, YOU CAN CONNECT FUEL HOSES OR ADAPTERS BETWEEN THE AIRCRAFT AND THE FUEL TANKER. E.

Defueling Make sure that only qualified and approved personnel is near the aircraft during the defuel process. Steps should be taken to have the Fire Department stand by until the end of this process. If there is any sign of fuel leaks, a hazardous materials team must try to contain any fuel leakage.

F.

Equipment Make sure that contracted assistance, such as heavy-equipment operators, become part of the group safety team approach and are briefed on all relative safety issues. Keep in mind that most heavy-equipment operators never worked near an aircraft. It is necessary give them relevant safety issues. Discuss with these operators the concerns of overloading equipment and the subsequent possible dangers. Most heavy-equipment operators know these concerns but not as they relate to the aircraft. These discussions can include areas such as maximum lifting loads during crane lifts. Maximum jacking point loads and pneumatics lifting bags loading figures and charts must be available.

G.

Recovery Operations Make sure that all equipment in use is properly rated for the loaded anticipated. Make sure that the aircraft is stable during all the recovery actions and that tooling used will not cause aircraft instability. Adherence to maximum wind speeds is required during lifting and leveling operations. AIRBUS recommends that all loads imposed on the aircraft during a recovery operation must be recorded. If it is not possible to record the loads, record all the steps used to make sure that you do not exceed maximum loads. This will have a direct impact on corrective actions to do for return to service.

02-40-01

Page 3 Jul 01/09


WEIGHT AND CG MANAGEMENT 03-00-00

WEIGHT AND CG MANAGEMENT

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 03-00-00-558-801-A01 General 1.

General The aim is to calculate the weight of the aircraft and the CG location in order to anticipate aircraft stability changes. The weight of the aircraft and the CG location are the basic data used to calculate the expected loads and to select a recovery technique (selection of tooling and equipment). The choice of a leveling/lifting scenario (see TBD) and the use of the logic chart (see DESC 09-20-01-002-A01) will help to control aircraft weight and CG.

2.


3.

Job Setup References Use aircraft reference axes, glossary of terms (see 09-10-02) and the aircraft reference OEW or DOW. A.

4.

Worksheet Principle The worksheets are used to calculate the NRW and moments. Chapter 03-60-01 gives the source of the specific data used to complete the ”interim worksheets” and calculate the final NRW. The NRW and CG worksheet indicates in front of each item which ARM chapter will give relevant data to allow completion of ”interim worksheets” and final NRW calculation. It is understood that NRW, CG position and calculation of expected loads will not be accurate if generic data is used for the OEW, H-arm and Y-arm data. It should be noted that the OEW or DOW and the H-arm and Y-arm apply to a specific aircraft with all landing gears extended, flight controls retracted and thrust reversers in stowed position. See DESC 09-50-01-001-A01 for the calculation worksheets.


Referenced Information REFERENCE DESC 09-20-01-002-A01 DESC 09-50-01-001-A01 09-10-02 03-60-01 09-50-01 FIGURE 03-00-00-991-002-A FIGURE 03-00-00-991-002-B

DESIGNATION DESC 09-20-01-002-A01-Aircraft Recovery Logic Chart DESC 09-50-01-001-A01-Worksheets 09-10-02-GLOSSARY OF TERMS 03-60-01-REFERENCE FOR CALCULATION 09-50-01-WEIGHT AND CG CALCULATION WORKSHEETS FIGURE 03-00-00-991-002-A-CG Conversion Principle FIGURE 03-00-00-991-002-B-CG Conversion Principle

03-00-00

Page 1 Jul 01/09


REFERENCE FIGURE 03-00-00-991-002-C FIGURE 03-00-00-991-002-D

DESIGNATION FIGURE 03-00-00-991-002-C-CG Conversion Principle FIGURE 03-00-00-991-002-D-CG Conversion Principle Referenced Information TABLE 1

5.

Procedure WARNING : MAKE SURE THAT ALL PERSONNEL IS AT A SAFE DISTANCE DURING THE REMOVAL OF FUEL, CARGO OR LARGE COMPONENTS. AN UNEQUAL REMOVAL OF FUEL OR CARGO OR THE REMOVAL OF LARGE COMPONENTS CAN CHANGE THE CG AND THE LONGITUDINAL AND LATERAL STABILITY OF THE AIRCRAFT. DEATH OR SERIOUS INJURY MAY RESULT IF THE AIRCRAFT FALLS ON RECOVERY PERSONNEL. WARNING : YOU MUST MONITOR AIRCRAFT STABILITY, WEIGHT AND CG DURING THE RECOVERY PROCESS. NOTE : It is important to use accurate data for the calculation related to the recovery process. Some of the necessary data is the responsibility of the operator and to be accurate, it must be applicable to the specific MSN involved. Data supplied by the manufacturer as generic data is not necessarily accurate for a specific MSN. Refer to the operator’s documentation for precise calculations. If some of the necessary data is not available or if it is not possible to get it, then it is the responsibility of the recovery manager to decide to use estimated data and to continue with the process. **ON A/C A318-100 Subtask 03-00-00-558-001-A01 A.

CG Conversion Principle (1) The CG location (in the longitudinal axis) can be expressed in % of the Reference Chord (%RC) or in lever arm distance (H-arm). See FIGURE 03-00-00-991-002-A. In this manual, the lever arm distance (H-arm and Y-arm) is used to calculate the CG location calculation. (a) Use the formula that follows to convert the CG expressed in %RC from other manuals into H-arm. - H-arm (in meters) = (%RC × 0.041935) + 15.4139 - H-arm (in inches) = (%RC × 1.651) + 606.847 (b) Use the formula that follows to convert H-arm into %RC. - %RC = (H-arm -- 15.4139) / 0.041935 (H-arm in meters)

03-00-00

Page 2 Jul 01/09


-

%RC = (H-arm -- 606.847) / 1.651 (H-arm in inches)

**ON A/C A319-100 Subtask 03-00-00-558-001-B01 A.

CG Conversion Principle (1) The CG location (in the longitudinal axis) can be expressed in % of the Reference Chord (%RC) or in lever arm distance (H-arm). See FIGURE 03-00-00-991-002-B. In this manual, the lever arm distance (H-arm and Y-arm) is used to calculate the CG location calculation. (a) Use the formula that follows to convert the CG expressed in %RC from other manuals into H-arm. - H-arm (in meters) = (%RC × 0.041935) + 16.2016 - H-arm (in inches) = (%RC × 1.651) + 637.858 (b) Use the formula that follows to convert H-arm into %RC. - %RC = (H-arm -- 16.2016) / 0.041935 (H-arm in meters) - %RC = (H-arm -- 637.858) / 1.651 (H-arm in inches)

**ON A/C A320-100 A320-200 Subtask 03-00-00-558-001-C01 A.

CG Conversion Principle (1) The CG location (in the longitudinal axis) can be expressed in % of the Reference Chord (%RC) or in lever arm distance (H-arm). See FIGURE 03-00-00-991-002-C. In this manual, the lever arm distance (H-arm and Y-arm) is used to calculate the CG location calculation. (a) Use the formula that follows to convert the CG expressed in %RC from other manuals into H-arm. - H-arm (in meters) = (%RC × 0.041935) + 17.8015 - H-arm (in inches) = (%RC × 1.651) + 700.85 (b) Use the formula that follows to convert H-arm into %RC. - %RC = (H-arm -- 17.8015) / 0.041935 (H-arm in meters) - %RC = (H-arm -- 700.85) / 1.651 (H-arm in inches)

03-00-00

Page 3 Jul 01/09


**ON A/C A321-100 A321-200 Subtask 03-00-00-558-001-D01 A.

CG Conversion Principle (1) The CG location (in the longitudinal axis) can be expressed in % of the Reference Chord (%RC) or in lever arm distance (H-arm). See FIGURE 03-00-00-991-002-D. In this manual, the lever arm distance (H-arm and Y-arm) is used to calculate the CG location calculation. (a) Use the formula that follows to convert the CG expressed in %RC from other manuals into H-arm. - H-arm (in meters) = (%RC × 0.041935) + 22.0687 - H-arm (in inches) = (%RC × 1.651) + 868.85 (b) Use the formula that follows to convert H-arm into %RC. - %RC = (H-arm -- 22.0687) / 0.041935 (H-arm in meters) - %RC = (H-arm -- 868.85) / 1.651 (H-arm in inches)

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 Subtask 03-00-00-970-001-A01 B.

Principle of the NRW and Related CG Position Calculation NOTE : All calculations are based on OEW or DOW aircraft configuration and related CG. The weight differences between the OEW or DOW and the real status of the aircraft are then recorded on calculation worksheets. The data on these worksheets is used to calculate the NRW and CG location of the aircraft. (1) Find the weight and calculate the related H-arm moment of a known aircraft configuration (OEW or DOW). NOTE : For the OEW or DOW configuration, the Y-arm = 0. (2) Record the values on the NRW and CG worksheet (see 09-50-01) applicable to the configuration (OEW or DOW) that you will use for the calculation. (3) For each item on the NRW and CG worksheet, use the related chapter and related interim worksheet to record the weight, the H-arm moment and the Y-arm moment of each item which remains on the aircraft, which is removed or missing from the aircraft and which has an effect on the known OEW or DOW. NOTE : It is considered that the Y-arm of components located inside the fuselage is negligible for the calculation made, therefore they are ignored. NOTE : The ARM gives all necessary data (for each scenario) to allow completion of interim worksheet.

03-00-00

Page 4 Jul 01/09


(4) Use the ”NRW and Related H and Y Moment” worksheet (see 09-50-01) to find the NRW, the total H-arm moment and the total Y-arm moment. NET RECOVERABLE WEIGHT = TOTAL H-ARM MOMENT = TOTAL Y-ARM MOMENT = (5) Divide the ”total H-arm moment” value by the NRW value to find the longitudinal CG position (XG). (LONGITUDINAL CG POSITION) XG = (6) Divide the ”total Y-arm moment value” by the NRW value to find the lateral CG position (YG). (LATERAL CG POSITION) YG =

03-00-00

Page 5 Jul 01/09

Z

03-00-00

H−ARM= 0

0

2.540 m (100 in)

15.4139 m (606.847 in)

16.462 m (648.11 in)

25% RC

REFERENCE CHORD 4.1935 m (165.10 in)

X

N_AR_030000_1_0020101_01_00

7.000 m (275.591 in)

FUSELAGE DATUM LINE


**ON A/C A318-100

CG Conversion Principle Reference Chord Data - A318 FIGURE-03-00-00-991-002-A01

Page 6 Jul 01/09

Z

H−ARM= 0

0

2.540 m (100 in)

16.2016 m (637.860 in)

17.250 m (679.13 in)

OPTIONAL

25% RC


03-00-00

X

N_AR_030000_1_0020201_01_00

7.000 m (275.591 in)

FUSELAGE DATUM LINE


**ON A/C A319-100

CG Conversion Principle Reference Chord Data - A319 FIGURE-03-00-00-991-002-B01

Page 7 Jul 01/09


N_AR_030000_1_0020301_01_00

0

2.540 m (100 in)

17.8015 m (700.85 in)

Z

18.850 m (742.13 in)

25% RC


7.000 m (275.591 in)

X

FUSELAGE DATUM LINE

**ON A/C A320-100 A320-200

H−ARM= 0

CG Conversion Principle Reference Chord Data - A320 FIGURE-03-00-00-991-002-C01

03-00-00

Page 8 Jul 01/09


N_AR_030000_1_0020401_01_01

0

Z

2.540 m (100 in)

22.0687 m (868.85 in)

23.117 m (910.12 in)

25% RC


7.000 m (275.591 in)

X

FUSELAGE DATUM LINE

**ON A/C A321-100 A321-200

H−ARM= 0

CG Conversion Principle Reference Chord Data - A321 FIGURE-03-00-00-991-002-D01

03-00-00

Page 9 Jul 01/09


03-20-01

FUEL LOAD AND CG CONTROL


To safely level or lift a damaged aircraft so that it can be moved on it’s own Landing Gear (or on a suitable ground equipment trailer) you must establish the weight and center of gravity (CG) of the aircraft. This chapter contains the method and calculations needed to establish the effect of the fuel load on the position of the aircraft CG. The weight and CG positions of the aircraft will change due to the quantity of fuel in each tank. To find the changes in weight and CG position, calculate: - The H-arm dimension along the longitudinal plane from nose to tail (H-arm is a dimension from the CG of an item/component to the horizontal reference datum plane) - The Y-arm dimension along the lateral plane from wing tip to wing tip (Y-arm is a dimension from the CG of an item/component to the lateral arm reference datum plane). The tables (see DESC 03-20-01-002-A01) in this chapter contain fuel weight and CG data for selected incremental fuel volumes for each fuel tank and for each scenario. NOTE : Fuel density used in calculations is: 0.785 kg/liter and 1.7306138 lb/liter

03-20-01

Page 1 Jul 01/09


ADDITIONAL CENTER TANK WEIGHT (IF INSTALLED)

CENTER TANK WEIGHT

AIRCRAFT WEIGHT INNER TANK WEIGHT OUTER TANK WEIGHT

MOMENTS TAKEN AT CONTACT POINT

LIFTING LOAD

OUTER TANK WEIGHT

INNER TANK WEIGHT

N_AR_032001_1_0010101_01_03

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

Aircraft Loads Type and Position of Loads Acting on the Aircraft FIGURE-03-20-01-991-001-A01

03-20-01

Page 2 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 03-20-01-002-A01 Tables 1.

General To find the weight and associated CG of remaining fuel on board, you must know the quantity of fuel remaining in each tank. If you do not know the quantity of fuel remaining in each tank see 03-20-02 for information about how to assess the fuel quantity without serviceable aircraft systems. Using the fuel quantity, you must determine the weight and moment (generated by H-arm and Yarm) of the fuel, using the table for the given scenario. When you have found the data from the relevant tables, enter this data in the fuel remaining onboard effect ’worksheet’ boxes (see DESC 09-50-01-001-A01 for calculation worksheets) with the weight, the H-arm moment and the Y-arm moment values for the remaining fuel in each tank. For information on defuel procedures see 05-10-00. NOTE : The tables that follow give estimated values to help you estimate the CG position. The values are calculated without any pitch or roll angle of the aircraft. Accurate data are related to your aircraft configuration.

**ON A/C A318-100 2.

Tables The table that follow gives the H-arm and Y-arm related to important fuel capacities.

1/4 1/2 3/4

Full

Capacity 200 l (53 US gal) 1800 l (476 US gal) 3400 l (898 US gal) 5200 l (1374 US gal) 6925 l (1829 US gal)

Weight 157 kg (346 lb) 1413 kg (3115 lb) 2669 kg (5884 lb)

H-arm 15.4 m (606.30 in) 15.386 m (605.75 in) 15.489 m (609.80 in)

Harm Moment 2418 kgm (209780 lb.in) 21740 kgm (1886911 lb.in) 41340 kgm (3588063 lb.in)

Y-arm 2.183 m (85.94 in) 2.775 m (109.25 in) 3.151 m (124.06 in)

Y-arm Moment 343 kgm (29735 lb.in) 3921 kgm (340314 lb.in) 8410 kgm (729969 lb.in)

4082 kg (8999 lb)

15.642 m (615.83 in)

63851 kgm (5541854 lb.in)

3.629 m (142.87 in)

14814 kgm (1285687 lb.in)

87043 kgm (7554594 in)

4.535 m (178.54 in)

24653 kgm (54347 lb.in)

5436 kg 16.012 m (11984 lb) (630.39 in)

Inner Cell TABLE 1

03-20-01

Page 3 Jul 01/09


1/4 1/2 3/4 Full

Capacity 200 l (53 US gal) 400 l (106 US gal) 600 l (159 US gal) 880 l (232 US gal)

Weight 157 kg (346 lb) 314 kg (692 lb) 471 kg (1038 lb) 691 kg (1523 lb)

H-arm 18.622 m (733.15 in) 18.706 m (736.46 in) 18.786 m (739.61 in) 18.943 m (745.79 in)

Harm Moment 2924 kgm (253.670 lb.in) 5874 kgm (509630 lb.in) 8848 kgm (767715 lb.in) 13086 kgm (1135838 lb.in)

Y-arm 10.502 m (413.46 in) 10.751 m (423.27 in) 10.966 m (431.73 in) 11.364 m (447.40 in)

Y-arm Moment 1649 kgm (143057 lb.in) 3376 kgm (292903 lb.in) 5165 kgm (448136 lb.in) 7850 kgm (681390 lb.in)

Outer Cell TABLE 2

1/4 1/2

3/4

Full

Capacity 200 l (53 US gal) 2200 l (581 US gal) 4200 l (1110 US gal) 6200 l (1638 US gal 8250 l (2179 US gal)

Weight 157 kg (346 lb) 1727 kg (3807 lb)

H-arm 15.47 m (609.06 in) 15.195 m (598.23 in)

Harm Moment 2429 kgm (210735 lb.in) 26242 kgm (2277462 lb.in)

3297 kg (7269 lb)

15.053 m (592.64 in)

Y-arm

Y-arm Moment

-

-

-

-

49630 kgm (4307900 lb.in)

-

-

4867 kg 15.005 m (10730 lb) (590.75 in)

73029 kgm (6338748 lb.in)

-

-

6476 kg 14.968 m (14277 lb) (589.29 in)

96937 kgm (8413293 lb.in)

-

-

Center Tank TABLE 3 **ON A/C A319-100 3.


1/4

Capacity 200 l (53 US gal) 2000 kg (4409 lb)

Weight 157 kg (346 lb) 1570 kg (3461 lb)

H-arm 16.188 m (637.32 in) 16.187 m (637.28 in)


Y-arm 2.183 m (85.94 in) 2.827 m (111.30 in)

03-20-01

Y-arm Moment 343 kgm (29735 lb.in) 4438 kgm (385209 lb.in)

Page 4 Jul 01/09


1/2 3/4

Full

Capacity 3600 kg (7937 lb) 5200 l (1374 US gal) 6925 l (1829 US gal)

Weight 2826 kg (6230 lb)

H-arm 16.291 m (641.38 in)

Harm Moment 46038 kgm (3995797)

Y-arm 3.194 m (125.75 in)

Y-arm Moment 9026 kgm (783423 lb.in)

4082 kg (8999 lb)

16.43 m (646.85 in)

67067 kgm (5821003 lb.in)

3.629 m (142.87 in)

14814 kgm (1285687 lb.in)

5436 kg 16.8 m (11984 lb) (661.42 in)

91325 kgm (7926457 lb.in)

4.535 m (178.54 in)

24652 (2139623 lb.in)

Y-arm 10.502 m (413.46 in) 10.751 m (423.27 in) 10.966 m (431.73 in) 11.364 m (447.40 in)

Y-arm Moment 1649 kgm (143057 lb.in) 3376 kgm (292903 lb.in) 5165 kgm (448136 lb.in) 7853 kgm (681390 lb.in)

Inner Cell TABLE 4

1/4 1/2 3/4 Full



H-arm 19.41 m (764.17 in) 19.494 m (767.48 in) 19.574 m (770.63 in) 19.731 m (776.81 in)

Harm Moment 3047 kgm (264403 lb.in) 6121 kgm (531096 lb.in) 9219 kgm (799914 lb.in) 13634 kgm (1183082 lb.in)

Outer Cell TABLE 5

1/4 1/2

3/4


Weight 157 kg (346 lb) 1727 kg (3807 lb)

H-arm 16.258 m (640.08 in) 15.959 m (628.31 in)


3297 kg (7269 lb)

15.834 m (623.39 in)

4867 kg 15.79 m (10730 lb) (621.65 in)

Y-arm

Y-arm Moment

-

-

-

-

52205 kgm (4531422 lb.in)

-

-

76850 kgm (6670305 lb.in)

-

-

03-20-01

Page 5 Jul 01/09


Full

Capacity 8250 l (2179 US gal)

Weight

H-arm

Harm Moment

6476 kg 15.756 m (14277 lb) (620.31 in)

102036 kgm (8856166 lb.in)

Y-arm -

Y-arm Moment -

Center Tank TABLE 6 **ON A/C A320-100 A320-200 4.


1/4 1/2 3/4

Full

Capacity 200 l (53 US gal) 2000 kg (4409 lb) 3600 kg (7937 lb) 5200 l (1374 US gal) 6984 l (1845 US gal)


H-arm 17.79 m (700.39 in) 17.784 m (700.16 in) 17.885 m (704.13 in)


Y-arm 2.179 m (85.79 in) 2.815 m (110.83 in) 3.175 m (125.00 in)


4867 kg 18.012 m (10730 lb) (709.13 in)

73525 kgm (7608965 lb.in)

3.579 m (140.91 in)

14609 kgm (1511964 lb.in)

5482 kg 18.372 m (12086 lb) (723.31 in)

100715 kgm (8741925 lb.in)

4.469 m (175.94 in)

24499 kgm (2126411 lb.in)

Inner Cell TABLE 7

1/4 1/2 3/4

Capacity 200 l (53 US gal) 400 l (106 US gal) 600 l (159 US gal)


H-arm 21.01 m (827.17 in) 21.094 m (830.47 in) 21.174 m (833.62 in)


Y-arm 10.502 m (413.46 in) 10.751 m (423.27 in) 10.966 m (431.73 in)

03-20-01


Page 6 Jul 01/09


Full

Weight Capacity 880 l 691 kg (232 US gal) (1523 lb)

H-arm 21.331 m (839.80 in)

Harm Moment 14740 kgm (1279015 lb.in)

Y-arm 11.364 m (447.40 in)


Outer Cell TABLE 8

1/4 1/2

3/4

Full


Weight 157 kg (346 lb) 1727 kg (3807 lb)

H-arm 17.858 m (703.07 in) 17.559 m (691.30 in)


3297 kg (7269 lb)

17.434 m (686.38 in)

Y-arm

Y-arm Moment

-

-

-

-

57480 kgm (4989296 lb.in)

-

-

4867 kg 17.39 m (10730 lb) (684.65 in)

84637 kgm (7346295 lb.in)

-

-

6476 kg 17.362 m (14277 lb) (683.54 in)

110092 kgm (9758901 lb.in)

-

-

Center Tank (A320-200 only) TABLE 9 **ON A/C A321-100 A321-200 5.


1/4 1/2

3/4


Weight 157 kg (346 lb) 1570 kg (3461 lb)

H-arm 22.056 m (868.35 in) 22.039 m (867.68 in)


Y-arm 2.181 m (85.87 in) 2.789 m (109.80 in)

Y-arm Moment 342 kgm (29711 lb.in) 4379 kgm (380018 lb.in)

3140 kg (6923 lb)

22.174 m (872.99 in)

69626 kgm (6043710 lb.in)

3.204 m (126.14 in)

10061 kgm (873267 lb.in)

4710 kg 22.43 m (10384 lb) (883.07 in)

105645 kgm (9169799 lb.in)

3.9 m (153.54 in)

18369 kgm (1594359 lb.in)

03-20-01

Page 7 Jul 01/09


Full

Capacity 7745 l (2046 US gal)

Weight

H-arm

6080 kg 22.883 m (13404 lb) (900.91 in)

Harm Moment

Y-arm

139129 kgm 4.973 m (12.075768 lb.in) (195.79 in)


Wing Tank TABLE 10

1/4 1/2

3/4

Full


Weight 157 kg (346 lb) 1570 kg (3461 lb)

H-arm 22.069 m (868.86 in) 21.785 m (857.68 in)


3140 kg (6923 lb)

21.672 m (853.23 in)

Y-arm

Y-arm Moment

-

-

-

-

68050 kgm (5906911 lb.in)

-

-

4710 kg 21.634 m (10384 lb) (851.73 in)

101896 kgm (8844364 lb.in)

-

-

6445 kg 21.596 m (14209 lb) (850.24 in)

139186 kgm (12081060 lb.in)

-

Center Tank TABLE 11

03-20-01

Page 8 Jul 01/09


03-20-02

MANUAL FUEL QUANTITY INDICATION

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 03-20-02-970-801-A01 Use of Magnetic Level Indicators (MLI) 1.

General The Magnetic Level Indicators (MLI) are used on ground to calculate the fuel quantity in the wing and center tanks. See AMM 12-11-28-650-007 for detailed procedure. This procedure is valid only when the aircraft attitude is between minus 1.5˚ and plus 1.5˚ roll and minus 1.5˚ and plus 1.5˚ pitch.

2.

Inspections Not Applicable

3.

Job Setup References On A318, A319 and A320, there are five MLI in each wing tank and one in the center tank. On A321, there are seven MLI in each wing tank and one in the center tank. See FIGURE 03-20-02-991-001-AFIGURE 03-20-02-991-001-B.

4.


Fixtures, Tools, Test and Support REFERENCE 98A28104000000

DESIGNATION PURGER WATER DRAIN Fixtures, Tools, Test and Support TABLE 1

B.

Referenced Information REFERENCE AMM 12-11-28-650-007 AMM 12-11-28-650-001 AMM 12-11-28-650-002 AMM 12-32-28-281-001 FIGURE 03-20-02-991-001-A FIGURE 03-20-02-991-001-B FIGURE 03-20-02-991-002-A

DESIGNATION

FIGURE 03-20-02-991-001-A-Magnetic Level Indicators FIGURE 03-20-02-991-001-B-Magnetic Level Indicators FIGURE 03-20-02-991-002-A-Attitude Monitor Referenced Information TABLE 2

03-20-02

Page 1 Jul 01/09


5.

Procedure WARNING : THIS PROCEDURE IS FOR INFORMATION ONLY TO HELP YOU PREPARE THE RECOVERY OPERATION. TO DO THE PROCEDURE, YOU MUST REFER TO THE OPERATORS CUSTOMIZED DOCUMENTATION. WARNING : MAKE SURE THAT YOU OBEY ALL THE APPLICABLE SAFETY PRECAUTIONS WHEN YOU REMOVE FUEL OR WHEN YOU WORK IN AN ENVIRONMENT WHERE THERE IS FUEL. CAUTION :

DO NOT LET THE MLI’S FALL FREELY.

CAUTION :

RETRACT THE MLI’S AS SOON AS POSSIBLE. YOU CAN EASILY CAUSE DAMAGE TO AN EXTENDED MLI.

Subtask 03-20-02-869-001-A01 A.

Preparation (1) Safety Precaution (a) You must obey the refuel/defuel safety precautions. See AMM 12-11-28-650-001 and AMM 12-11-28-650-002. (b) Put the safety barriers in position. (2) Fuel Sampling (a) Use the 98A28104000000 PURGER WATER DRAIN to get a fuel sample from the aircraft. See AMM 12-32-28-281-001. (b) Measure the Specific Gravity (SG) of the fuel sample. (3) Get Access (a) Put an access platform below the applicable MLI. (b) Open the access door 192MB, see FIGURE 03-20-02-991-002-A. (4) Aircraft Attitude (a) Find and write down the aircraft attitude (pitch and roll). See TBD. (b) Or, if installed, read the aircraft attitude shown by the bubble on the attitude monitor, see FIGURE 03-20-02-991-002-A. See TABLE 3 to convert the attitude angles and grid square letters on the attitude monitor. Pitch Roll Ref Ref - 1.5˚ 1 - 1.5˚ A - 1.0˚ 2 - 1.0˚ B - 0.5˚ 3 - 0.5˚ C 4 0.0˚ 0.0˚ D

03-20-02

Page 2 Jul 01/09


Pitch + 0.5˚ + 1.0˚ + 1.5˚

Roll

Ref 5 6 7

+ 0.5˚ + 1.0˚ + 1.5˚ Aircraft Attitude

Ref E F G

TABLE 3 Subtask 03-20-02-970-001-A01 B.

Use of the Magnetic Level Indicators (MLI) (1) Use a screwdriver to push the applicable MLI and turn it through 90 deg. (2) Hold and carefully lower the MLI fully. Then carefully lift the MLI until you feel the magnets engage. (3) Read the units mark nearest to the bottom-skin of the wing and write down the number. (4) Retract the MLI and use a screwdriver to turn it through 90 deg. to lock it. (5) Find the volume of fuel in each tank: (a) Use the applicable MLI stick number and the applicable aircraft attitude grid-square letter to find the corresponding fuel quantity table. See AMM 12-11-28-650-007 for the fuel quantity tables. (b) Find the applicable MLI unit number row and the applicable A/C attitude (gridsquare letter and number) in the table. Find the intersection of the applicable rows to give the correct volume of fuel in the tank. (c) Multiply the total volume of the fuel by the specific gravity (SG) of the fuel to obtain the mass of the fuel. NOTE : The MLI are accurate to +/- 5 % of their indication.

03-20-02

Page 3 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200

CL

RIB2 RIB6 RIB10 RIB12

RIB21

CTR STICK

STICK No 1

STICK No 2 STICK No 3 STICK No 4

EXTERNAL VIEW OF RETRACTED AND LOCKED M.L.I.

STICK No 5

INDICATOR ROD EXTENDED

N_AR_032002_1_0010101_01_00

Magnetic Level Indicators Location - A318/A319/A320 FIGURE-03-20-02-991-001-A01

03-20-02

Page 4 Jul 01/09


**ON A/C A321-100 A321-200

CL


RIB21

CTR STICK

STICK No 1

STICK No 2 STICK No 3 STICK No 4 STICK No 5 STICK No 6

EXTERNAL VIEW OF RETRACTED AND LOCKED M.L.I.

STICK No 7

INDICATOR ROD EXTENDED

N_AR_032002_1_0010201_01_00

Magnetic Level Indicators Location - A321 FIGURE-03-20-02-991-001-B01

03-20-02

Page 5 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A 192MB

ATTITUDE MONITOR 39QM

A1 2 B C D E F G

3

4

5

6

7

A

N_AR_032002_1_0020101_01_00

Attitude Monitor Location FIGURE-03-20-02-991-002-A01

03-20-02

Page 6 Jul 01/09


03-50-01

MANAGING AIRCRAFT WEIGHT AND CG

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 03-50-01-001-A01 Introduction 1.

General Management of the aircraft weight and related CG is one of the key issues of the recovery plan and operation. It has a direct impact on aircraft stability, calculation of expected loads and the loads recorded for a given recovery process.

2.

Purpose For a given aircraft attitude (See TBD), it is necessary first to calculate the aircraft NRW and CG (See 03-00-00) to make the calculations of the expected loads, based on the leveling/lifting techniques that will be used. These expected loads, and then the applied loads must be in the limits that follow: - Aircraft allowable loads, - Tooling capabilities. If these loads are not in the limits, it will be necessary: - To find an alternative leveling/lifting procedure to make sure that the aircraft, tooling and equipment support loads are not more than the allowable loads, - To manage aircraft weight and related CG to bring the expected loads in the allowable loads, - To use other tooling, if the tool cannot support the expected loads. NOTE : The tooling should not only be able to support expected loads, but should also be appropriate for the travel range, arc movement, aircraft stability, ground stability, etc.… NOTE : It is important to make sure that the aircraft is stable before and during the implementation of the recovery phase/steps. The installation of ballast or the removal of equipment, payload, fuel, etc. can help to change the aircraft weight and CG location. Every effort should be made to reduce the Total Weight of the aircraft to the minimum possible by removal of significant amounts of payload. The easiest way to remove quickly large amounts of weight can be fuel and cargo removal. In some cases, it may be necessary to remove major aircraft components that are damaged. Before removal of these components, it is important to do a careful study because it may be better to secure them in place temporarily. Galley catering units (trolleys, etc.) have a significant weight and every effort should be made to remove them. If they remain on board, carefully evaluate their weight when you make the H-arm calculations. Food in the catering units can deteriorate quickly. During a long recovery operation, it may become a priority to remove the catering units for health reasons. Draining of potable water and lavatory waste and removal of the escape slides and slide rafts can also reduce the weight.

03-50-01

Page 1 Jul 01/09


It is not necessary to drain the fluids, such as hydraulic fluid, from closed systems unless there is significant leakage that it is not possible to contain. As every aircraft recovery is different, it will be necessary to decide what and how much must be removed. These decisions will be based on access, time, cost and the actual ability to do the task. The records made during the damage survey of the aircraft should include all major components that are missing or that it is necessary to remove because of damage. It is necessary to include the weight changes related to these components in the calculation of the aircraft weight and CG location. Removal of any aircraft components and equipment should be done in accordance with the Aircraft Maintenance Manual (AMM), and recorded with the data collected during the aircraft survey. 3.

Calculation Iteration The calculation iteration from NRW and CG up to expected loads, travel range, arc movement should be continued until aircraft stability, expected loads, travel range, arc movement etc.… are in the acceptable limits. Changes to the different inputs used in the calculations can help to get satisfactory value related to the settings of a recovery scenario.

4.

List of Item Used for NRW and CG Calculation See the related topic or task for the related item weight input. Weight Inputs OEW DOW Fuel Remaining on Board Effect Cargo and Baggage Remaining Effect

Total Traffic Load Remaining Effect Ballast Added Effect Waste Water Remaining Effect Non OEW Catering Equipment Added Effect Large Component Movement Effect

Potable Water Removed Effect Cockpit and Cabin Crew Removed Effect Catering Equipment Removed Effect

See 03-00-00 03-00-00 03-20-01 TASK 03-50-01-558-801A01TASK 03-50-01-558-801B01TASK 03-50-01-558-801C01TASK 03-50-01-558-801D01 TASK 03-50-01-558-802-A01 TASK 03-50-01-558-803-A01 TASK 03-50-01-558-804-A01 TASK 03-50-01-558-805-A01 TASK 03-50-01-558-811A01TASK 03-50-01-558-811B01TASK 03-50-01-558-811C01 TASK 03-50-01-558-806-A01 TASK 03-50-01-558-807-A01 TASK 03-50-01-558-808-A01

03-50-01

Page 2 Jul 01/09


Weight Inputs Large Component Removed /Missing Effect

See TASK 03-50-01-558-810A01TASK 03-50-01-558-810B01TASK 03-50-01-558-810C01TASK 03-50-01-558-810D01 TASK 03-50-01-558-809-A01

Hydraulic Fluids Removed Effect

List of Item Used for NRW and CG Calculation TABLE 1

03-50-01

Page 3 Jul 01/09


**ON A/C A318-100 TASK 03-50-01-558-801-A01 Cargo and Baggage Remaining Effect 1.

General The aircraft has three cargo compartments. - The FWD cargo compartment (N˚1) in zone 130, - The aft cargo compartment (N˚4) in zone 150, - The bulk cargo compartment (N˚5) in zone 160. NOTE : For location see 09-10-14

2.


3.

Job Setup References The tables that follow are built with a standard configuration. If the cargo compartments contain a different configuration, use the value given in the standard combination or in your WBM to find the applicable H-arm and Y-arm. A.

Forward Cargo Compartment The forward cargo compartment is designed for the transport of bulk cargo and baggage. See your WBM to determine applicable Y-arm. Section 11

Frame Station

Remaining Weight

28 to 34

Total

Moment to add

10.430 m (410.63 in) 11.748 m (462.52 in) 11.078 m (436.14 in)

24A to 28

12

Average H-Arm

24A to 34

FWD Cargo Compartment Remaining Weight and Related H-arm TABLE 1 B.

Aft Lower Cargo Compartment The aft cargo compartment is designed for the transport of bulk cargo and baggage. See your WBM to determine applicable Y-arm. Section 41

Frame Station 47/54 to 57

Remaining Weight

Average H-Arm

Moment to add

19.698 m (775.51 in)

03-50-01

Page 4 Jul 01/09


Section

Frame Station

42

Remaining Weight

Moment to add

21.374 m (841.50 in) 20.498 m (807.01 in)

57 to 60

Total

Average H-Arm

47/54 to 60

FWD Cargo Compartment Remaining Weight and Related H-arm TABLE 2 C.

Bulk Cargo Compartment The aft cargo compartment is designed for the transport of bulk cargo and baggage. See your WBM to determine applicable Y-arm. Section

Frame Station

51

Remaining Weight

62 to 65

Total

Moment to add

22.708 m (894.02 in) 24.062 m (947.32 in) 23.528 m (926.30 in)

60 to 62

51

Average H-Arm

60 to 65

FWD Cargo Compartment Remaining Weight and Related H-arm TABLE 3 4.


Referenced Information REFERENCE DESC 09-50-01-001-A01 09-10-14

DESIGNATION DESC 09-50-01-001-A01-Worksheets 09-10-14-CARGO COMPARTMENTS Referenced Information TABLE 4

03-50-01

Page 5 Jul 01/09


5.

Procedure WARNING : MAKE SURE THAT ALL PERSONNEL IS AT A SAFE DISTANCE DURING THE REMOVAL OF FUEL, CARGO OR LARGE COMPONENTS. AN UNEQUAL REMOVAL OF FUEL OR CARGO OR THE REMOVAL OF LARGE COMPONENTS CAN CHANGE THE CG AND THE LONGITUDINAL AND LATERAL STABILITY OF THE AIRCRAFT. DEATH OR SERIOUS INJURY MAY RESULT IF THE AIRCRAFT FALLS ON RECOVERY PERSONNEL. WARNING : YOU MUST MONITOR AIRCRAFT STABILITY, WEIGHT AND CG DURING THE RECOVERY PROCESS. WARNING : IF CARGO AND BAGGAGE ARE NOT - OR CANNOT BE - REMOVED, MAKE SURE THAT THEY ARE SAFELY FASTENED AND THAT LOADS ARE AS SYMMETRICAL AS POSSIBLE BEFORE YOU START THE RECOVERY PROCESS. NOTE : It is important to use accurate data for the calculation related to the recovery process. Some of the necessary data is the responsibility of the operator and to be accurate, it must be applicable to the specific MSN involved. Data supplied by the manufacturer as generic data is not necessarily accurate for a specific MSN. Refer to the operator’s documentation for precise calculations. If some of the necessary data is not available or if it is not possible to get it, then it is the responsibility of the recovery manager to decide to use estimated data and to continue with the process. Subtask 03-50-01-558-001-A01 A.

How to Find the Effect of Cargo and Baggage Remaining (1) Use the tables in Job Setup References to determine H-arm moments and Y-arm moments by reporting the masses of each container or pallet. (2) Record the calculated values on FWD Cargo Compartment (in Zone 130) , Aft Cargo Compartment (in Zone 150) , Bulk Cargo Compartment (in Zone 160) into boxes of the Cargo and Baggage Interim Worksheet (See DESC 09-50-01-001-A01).

03-50-01

Page 6 Jul 01/09


**ON A/C A319-100 TASK 03-50-01-558-801-B01 Cargo and Baggage Remaining Effect 1.

General The aircraft has two cargo compartments. - The FWD cargo compartment (N˚1) in zone 130, - The aft cargo compartment (N˚4) in zone 150 and the aft cargo compartment (N˚5) in zone 160. NOTE : For location see 09-10-14

2.


3.


Forward Cargo Compartment The forward cargo compartment is designed for the transport of bulk cargo and baggage or the following unit load devices: - 2 x half size containers LD3-46 (NAS 3610-2K2C, IATA contour AKG) - 2 x full size containers LD3-46W (NAS 3610-2K2C, IATA contour AKH) - 2 x 60.4x61.5 in pallets LD3-46P (NAS 3610-2K3P) See your WBM to determine applicable Y-arm. Section 11

Frame Station

Remaining Weight

28 to 34

Total

Moment to add

10.744 m (422.99 in) 12.371 m (487.05 in) 11.436 m (450.24 in)

24A to 28

12

Average H-Arm

24A to 34

Bulk Cargo in FWD Cargo Compartment Remaining Weight and Related H-arm TABLE 1 Position ULD 11

Remaining Weight

Average H-Arm 10.700 m (421.26 in)

03-50-01

Moment to add

Page 7 Jul 01/09


Position ULD

Remaining Weight

12

Average H-Arm 12.272 m (483.15 in)

Moment to add

Containers and Pallets in FWD Cargo Compartment Remaining Weight and Related H-arm TABLE 2 B.

Aft Cargo Compartment n˚4 The aft cargo compartment n˚4 is designed for the transport of bulk cargo and baggage or the following unit load devices: - 2 x half size containers LD3-46 (NAS 3610-2K2C, IATA contour AKG) - 2 x full size containers LD3-46W (NAS 3610-2K2C, IATA contour AKH) - 2 x 60.4x61.5 in pallets LD3-46P (NAS 3610-2K3P) See your WBM to determine applicable Y-arm. Section 41

Frame Station

Remaining Weight

54 to 59

Total

Moment to add

20.485 m (806.50 in) 22.695 m (893.50 in) 21.819 m (859.02 in)

47/51 to 54

42

Average H-Arm

47/51 to 59

Bulk Cargo in Aft Cargo Compartment Remaining Weight and Related H-arm TABLE 3 Position ULD 41 42

Remaining Weight

Average H-Arm 20.475 m (806.10 in) 22.047 m (867.99 in)

Moment to add

Containers and Pallets in Aft Cargo Compartment Remaining Weight and Related H-arm TABLE 4 C.

Aft Cargo Compartment n˚5 The aft cargo compartment n˚5 is designed for the transport of bulk cargo and baggage. See your WBM to determine applicable Y-arm.

03-50-01

Page 8 Jul 01/09


Section 51

Frame Station

Remaining Weight

Average H-Arm

Moment to add

25.649 m (1009.80 in)

59 to 65

Bulk Cargo in Aft Cargo Compartment Remaining Weight and Related H-arm TABLE 5 4.




5.

Procedure WARNING : MAKE SURE THAT ALL PERSONNEL IS AT A SAFE DISTANCE DURING THE REMOVAL OF FUEL, CARGO OR LARGE COMPONENTS. AN UNEQUAL REMOVAL OF FUEL OR CARGO OR THE REMOVAL OF LARGE COMPONENTS CAN CHANGE THE CG AND THE LONGITUDINAL AND LATERAL STABILITY OF THE AIRCRAFT. DEATH OR SERIOUS INJURY MAY RESULT IF THE AIRCRAFT FALLS ON RECOVERY PERSONNEL. WARNING : YOU MUST MONITOR AIRCRAFT STABILITY, WEIGHT AND CG DURING THE RECOVERY PROCESS. WARNING : IF CARGO AND BAGGAGE ARE NOT - OR CANNOT BE - REMOVED, MAKE SURE THAT THEY ARE SAFELY FASTENED AND THAT LOADS ARE AS SYMMETRICAL AS POSSIBLE BEFORE YOU START THE RECOVERY PROCESS. NOTE : It is important to use accurate data for the calculation related to the recovery process. Some of the necessary data is the responsibility of the operator and to be accurate, it must be applicable to the specific MSN involved. Data supplied by the manufacturer as generic data is not necessarily accurate for a specific MSN. Refer to the operator’s documentation for precise calculations. If some of the necessary data is not available or if it is not possible to get it, then it is the responsibility of the recovery manager to decide to use estimated data and to continue with the process.

03-50-01

Page 9 Jul 01/09


Subtask 03-50-01-558-018-A01 A.

How to Find the Effect of Cargo and Baggage Remaining (1) Use the tables in Job Setup References to determine H-arm moments and Y-arm moments by reporting the masses of each container or pallet. (2) Record the calculated values on FWD Cargo Compartment (in Zone 130) , Aft Cargo Compartment (in Zone 150) , Aft Cargo Compartment (in Zone 160) into boxes of the Cargo and Baggage Interim Worksheet (See DESC 09-50-01-001-A01).

03-50-01

Page 10 Jul 01/09


**ON A/C A319-100 FWD CARGO DOOR

11

12

A 2.630 m (103.54 in) 1.430 m (56.30 in)

FR24

FR34

1.213 m

0.051 m (2.00 in)

(47.76 in)

A

2.007 m (79.00 in)

(61.50 in)

IATA CODE AKH

1.534 m (60.40 in)

1.562 m (61.50 in)

1.168 m (46.60 in)

NAS 3610−2K2C LD3−46 IATA CODE AKG

1.562 m (61.50 in)

1.168 m (46.60 in)

1.562 m

1.168 m (46.60 in)

IATA CODE AKG

2.451 m (96.50 in) NAS 3610−2K2C LD3−46W IATA CODE AKH

1.534 m (60.40 in)

PALLET NAS 3610−2K3P LD3−46P

1.534 m in) (60.40 N_AR_035001_1_0030101_01_00

FWD Cargo Compartment Arrangement Pallets and Containers FIGURE-03-50-01-991-003-A01

03-50-01

Page 11 Jul 01/09


**ON A/C A319-100 FWD CARGO DOOR

A 41

2.630 m (103.54 in) 1.430 m (56.30 in)

42

FR47/51

FR59

0.051 m (2.00 in)

1.213 m (47.76 in)

A

2.007 m (79.00 in)

(61.50 in)

IATA CODE AKH

1.534 m (60.40 in)

1.562 m (61.50 in)

1.168 m (46.60 in)

NAS 3610−2K2C LD3−46 IATA CODE AKG

1.562 m (61.50 in)

1.168 m (46.60 in)

1.562 m

1.168 m (46.60 in)

IATA CODE AKG

2.451 m (96.50 in) NAS 3610−2K2C LD3−46W IATA CODE AKH

1.534 m (60.40 in)

PALLET NAS 3610−2K3P LD3−46P

1.534 m in) (60.40 N_AR_035001_1_0040101_01_00

Aft Cargo Compartment Arrangement Pallets and Containers FIGURE-03-50-01-991-004-A01

03-50-01

Page 12 Jul 01/09


**ON A/C A320-100 A320-200 TASK 03-50-01-558-801-C01 Cargo and Baggage Remaining Effect 1.

General The aircraft has three cargo compartments. - The FWD cargo compartment (N˚1) in zone 130, - The aft cargo compartment (N˚4) in zone 150, - The bulk cargo compartment (N˚5) in zone 160. NOTE : For location see 09-10-14

2.


3.


Forward Cargo Compartment The forward cargo compartment is designed for the transport of bulk cargo and baggage or the following unit load devices: - 3 x half size containers LD3-46 (NAS 3610-2K2C, IATA contour AKG) - 3 x full size containers LD3-46W (NAS 3610-2K2C, IATA contour AKH) - 3 x rectangular container LD3-46R (NAS 3610-2K2C, IATA contour AKJ) - 3 x 60.4x61.5 in pallets LD3-46P (NAS 3610-2K3P) See your WBM to determine applicable Y-arm. Section 11 12 13 Total

Frame Station

Remaining Weight

Average H-Arm

Moment to add

10.744 m (422.99 in) 12.433 m (489.49 in) 13.971 m (550.04 in) 12.283 m (483.58 in)

24A to 28 28 to 31 31 to 34 24A to 34

Bulk Cargo in FWD Cargo Compartment Remaining Weight and Related H-arm TABLE 1

03-50-01

Page 13 Jul 01/09


Position ULD

Remaining Weight

11 12 13

Average H-Arm 10.700 m (421.26 in) 12.272 m (483.15 in) 13.844 m (545.04 in)

Moment to add


Aft Lower Cargo Compartment The forward cargo compartment is designed for the transport of bulk cargo and baggage or the following unit load devices: - 3 x half size containers LD3-46 (NAS 3610-2K2C, IATA contour AKG) - 3 x full size containers LD3-46W (NAS 3610-2K2C, IATA contour AKH) - 3 x rectangular container LD3-46R (NAS 3610-2K2C, IATA contour AKJ) - 3 x 60.4x61.5 in pallets LD3-46P (NAS 3610-2K3P) See your WBM to determine applicable Y-arm. Section 41

Frame Station

Remaining Weight

50 to 52A/53

43

53 to 56

44

56 to 59

Total

Moment to add

22.085 m (869.49 in) 23.762 m (935.51 in) 25.362 m (998.50 in) 26.962 m (1061.50 in) 27.762 m (1092.99 in)

47 to 50

42

Average H-Arm

47 to 59

Bulk Cargo in Aft Cargo Compartment Remaining Weight and Related H-arm TABLE 3 Position ULD 41 42

Remaining Weight


03-50-01

Moment to add

Page 14 Jul 01/09


Position ULD

Remaining Weight

43 44


Moment to add


Bulk Cargo Compartment The aft cargo compartment is designed for the transport of bulk cargo and baggage. See your WBM to determine applicable Y-arm. Section 51

Frame Station

Remaining Weight

60 to 62

53

62 to 65

Total

Moment to add

28.029 m (1103.50 in) 28.829 m (1135.00 in) 30.182 m (1188.27 in) 29.382 m (1156.77 in)

59 to 60

52

Average H-Arm

59 to 65

Bulk Cargo in Aft Cargo Compartment Remaining Weight and Related H-arm TABLE 5 4.




03-50-01

Page 15 Jul 01/09


5.

Procedure WARNING : MAKE SURE THAT ALL PERSONNEL IS AT A SAFE DISTANCE DURING THE REMOVAL OF FUEL, CARGO OR LARGE COMPONENTS. AN UNEQUAL REMOVAL OF FUEL OR CARGO OR THE REMOVAL OF LARGE COMPONENTS CAN CHANGE THE CG AND THE LONGITUDINAL AND LATERAL STABILITY OF THE AIRCRAFT. DEATH OR SERIOUS INJURY MAY RESULT IF THE AIRCRAFT FALLS ON RECOVERY PERSONNEL. WARNING : YOU MUST MONITOR AIRCRAFT STABILITY, WEIGHT AND CG DURING THE RECOVERY PROCESS. WARNING : IF CARGO AND BAGGAGE ARE NOT - OR CANNOT BE - REMOVED, MAKE SURE THAT THEY ARE SAFELY FASTENED AND THAT LOADS ARE AS SYMMETRICAL AS POSSIBLE BEFORE YOU START THE RECOVERY PROCESS. NOTE : It is important to use accurate data for the calculation related to the recovery process. Some of the necessary data is the responsibility of the operator and to be accurate, it must be applicable to the specific MSN involved. Data supplied by the manufacturer as generic data is not necessarily accurate for a specific MSN. Refer to the operator’s documentation for precise calculations. If some of the necessary data is not available or if it is not possible to get it, then it is the responsibility of the recovery manager to decide to use estimated data and to continue with the process. Subtask 03-50-01-558-019-A01 A.

How to Find the Effect of Cargo and Baggage Remaining (1) Use the tables in Job Setup References to determine H-arm moments and Y-arm moments by reporting the masses of each container or pallet. (2) Record the calculated values on FWD Cargo Compartment (in Zone 130) , Aft Cargo Compartment (in Zone 150) , Bulk Cargo Compartment (in Zone 160) into boxes of the Cargo and Baggage Interim Worksheet (See DESC 09-50-01-001-A01).

03-50-01

Page 16 Jul 01/09


**ON A/C A320-100 A320-200 FWD CARGO DOOR

A 11

2.630 m (103.54 in) 1.430 m (56.30 in)

12

13

FR34

FR24A

0.051 m (2.00 in)

1.213 m (47.76 in)

A

CONTAINERS LD3−46

1.534 m (60.40 in)

1.562 m (61.50 in)

1.534 m in) (60.40

CONTAINERS LD3−46R

1.562 m (61.50 in )

CONTAINERS LD3−46W

1.534 m (60.40 in)

1.168 m (46.60 in)

1.562 m (61.50 in)

1.168 m (46.60 in)

1.562 m (61.50 in)

2.451 m (96.50 in) 1.168 m (46.60 in)

1.168 m (46.60 in)

2.007 m (79.00 in)

PALLET 60.4 x 41.5 in

1.534 m in) (60.40

N_AR_035001_1_0050101_01_00


03-50-01

Page 17 Jul 01/09


**ON A/C A320-100 A320-200

1.213 m (47.76 in)

2.630 m (103.54 in) 1.430 m (56.30 in)

0.051 m (2.00 in)

A FWD CARGO DOOR

41

42

43

44

FR59

FR47

A

CONTAINERS LD3−46

1.534 m (60.40 in)

1.562 m (61.50 in)

1.534 m in) (60.40

CONTAINERS LD3−46R

1.562 m (61.50 in)

1.534 m in) (60.40

CONTAINERS LD3−46W

1.534 m (60.40 in)

1.168 m (46.60 in)

1.562 m (61.50 in)

1.168 m (46.60 in)

1.562 m (61.50 in )

2.451 m (96.50 in) 1.168 m (46.60 in)

1.168 m (46.60 in)

2.007 m (79.00 in)

PALLET 60.4 x 41.5 in

N_AR_035001_1_0060101_01_00


03-50-01

Page 18 Jul 01/09


**ON A/C A321-100 A321-200 TASK 03-50-01-558-801-D01 Cargo and Baggage Remaining Effect 1.

General The aircraft has three cargo compartments. - The FWD cargo compartment (N˚1 and 2) in zone 130, - The aft cargo compartment (N˚ 3 and 4) in zone 150, - The bulk cargo compartment (N˚5) in zone 160. NOTE : For location see 09-10-14

2.


3.


Forward Cargo Compartment The forward cargo compartment is designed for the transport of bulk cargo and baggage or the following unit load devices: - 5 x half size containers LD3-46 (NAS 3610-2K2C, IATA contour AKG) - 5 x full size containers LD3-46W (NAS 3610-2K2C, IATA contour AKH) - 5 x 60.4x61.5 in pallets LD3-46P (NAS 3610-2K3P) See your WBM to determine applicable Y-arm. Section 11 12 21 22 23

Frame Station 24A to 28 28 to 31 31 to 34 34 to 35.2 35.2 to 35.5

Remaining Weight

Average H-Arm

Moment to add


03-50-01

Page 19 Jul 01/09


Section Total

Frame Station

Remaining Weight

Average H-Arm

Moment to add

13.883 m (546.57 in)

24A to 35.5

Bulk Cargo in FWD Cargo Compartment Remaining Weight and Related H-arm TABLE 1 Position ULD

Remaining Weight

11 12 21 22 23

Average H-Arm 10.700 m (421.26 in) 12.272 m (483.15 in) 13.844 m (545.04 in) 15.416 m (606.93 in) 16.988 m (668.82 in)

Moment to add


Aft Lower Cargo Compartment The forward cargo compartment is designed for the transport of bulk cargo and baggage or the following unit load devices: - 5 x half size containers LD3-46 (NAS 3610-2K2C, IATA contour AKG) - 5 x full size containers LD3-46W (NAS 3610-2K2C, IATA contour AKH) - 5 x 60.4x61.5 in pallets LD3-46P (NAS 3610-2K3P) See your WBM to determine applicable Y-arm. Section 31 32 33 41

Frame Station 47.2 to 47.5 47.5 to 50 50 to 52A/53 52A/53 to 56

Remaining Weight

Average H-Arm

Moment to add

27.419 m (1079.49 in) 29.096 m (1145.51 in) 30.696 m (1208.50 in) 32.296 m (1271.50 in)

03-50-01

Page 20 Jul 01/09


Section 42

Frame Station

Remaining Weight

Moment to add

33.896 m (1334.49 in) 30.619 m (1205.47 in)

56 to 59

Total

Average H-Arm

47.2 to 59

Bulk Cargo in Aft FWD Cargo Compartment Remaining Weight and Related H-arm TABLE 3 Position ULD

Remaining Weight

31 32 33 41 42

Average H-Arm 27.445 m (1080.51 in) 29.017 m (1142.40 in) 30.589 m (1204.29 in) 32.161 m (1266.18 in) 33.733 m (1328.07 in)

Moment to add


Bulk Cargo Compartment The aft cargo compartment is designed for the transport of bulk cargo and baggage. See your WBM to determine applicable Y-arm. Section 51 52 53

Frame Station 59 to 60 60 to 62 62 to 65

Remaining Weight

Average H-Arm

Moment to add

34.963 m (1376.50 in) 35.764 m (1408.03 in) 37.123 m (1461.54 in)

03-50-01

Page 21 Jul 01/09


Section Total

Frame Station

Remaining Weight

Average H-Arm

Moment to add

36.322 m (1430.00 in)

59 to 65

Bulk Cargo in Aft FWD Cargo Compartment Remaining Weight and Related H-arm TABLE 5 4.




5.

Procedure WARNING : MAKE SURE THAT ALL PERSONNEL IS AT A SAFE DISTANCE DURING THE REMOVAL OF FUEL, CARGO OR LARGE COMPONENTS. AN UNEQUAL REMOVAL OF FUEL OR CARGO OR THE REMOVAL OF LARGE COMPONENTS CAN CHANGE THE CG AND THE LONGITUDINAL AND LATERAL STABILITY OF THE AIRCRAFT. DEATH OR SERIOUS INJURY MAY RESULT IF THE AIRCRAFT FALLS ON RECOVERY PERSONNEL. WARNING : YOU MUST MONITOR AIRCRAFT STABILITY, WEIGHT AND CG DURING THE RECOVERY PROCESS. WARNING : IF CARGO AND BAGGAGE ARE NOT - OR CANNOT BE - REMOVED, MAKE SURE THAT THEY ARE SAFELY FASTENED AND THAT LOADS ARE AS SYMMETRICAL AS POSSIBLE BEFORE YOU START THE RECOVERY PROCESS. NOTE : It is important to use accurate data for the calculation related to the recovery process. Some of the necessary data is the responsibility of the operator and to be accurate, it must be applicable to the specific MSN involved. Data supplied by the manufacturer as generic data is not necessarily accurate for a specific MSN. Refer to the operator’s documentation for precise calculations. If some of the necessary data is not available or if it is not possible to get it, then it is the responsibility of the recovery manager to decide to use estimated data and to continue with the process.

03-50-01

Page 22 Jul 01/09


Subtask 03-50-01-558-020-A01 A.

How to Find the Effect of Cargo and Baggage Remaining on the Deck (1) Use the tables in Job Setup References to determine H-arm moments and Y-arm moments by reporting the masses of each container or pallet. (2) Record the calculated values on FWD Cargo Compartment (in Zone 130) , Aft Cargo Compartment (in Zone 150) , Bulk Cargo Compartment (in Zone 160) into boxes of the Cargo and Baggage Interim Worksheet (See DESC 09-50-01-001-A01).

03-50-01

Page 23 Jul 01/09


**ON A/C A321-100 A321-200

0.051 m (2.00 in)

1.213 m (47.76 in)

2.630 m (103.54 in) 1.430 m (56.30 in)

A FWD CARGO DOOR

11

FR24

12

21

22

23

FR35.5

A

ULD CONTAINER WIDEBODY COMPATIBLE

NAS3610 2K2C LD3−45 IATA CODE AKG

PALLET WIDEBODY COMPATIBLE

PALLET NSA3610 2K2P

CONTAINER FULL WIDTH

NAS3610 2K2C LD3−45 IATA CODE AKH N_AR_035001_1_0070101_01_00


03-50-01

Page 24 Jul 01/09


**ON A/C A321-100 A321-200

1.213 m (47.76 in)

2.630 m (103.54 in) 1.430 m (56.30 in)

0.051 m (2.00 in)

A

FWD CARGO DOOR

31

FR47.1

32

33

41

42

A

FR59

ULD CONTAINER WIDEBODY COMPATIBLE

NAS3610 2K2C LD3−45 IATA CODE AKG

PALLET WIDEBODY COMPATIBLE

PALLET NSA3610 2K2P

CONTAINER FULL WIDTH

NAS3610 2K2C LD3−45 IATA CODE AKH N_AR_035001_1_0080101_01_00


03-50-01

Page 25 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 03-50-01-558-802-A01 Total Traffic Load Remaining Effect 1.

General There are overhead stowage compartments for hand baggage and coats along the full length of the passenger compartments, above the passenger seats.

2.


3.


4.


Referenced Information REFERENCE DESC 09-50-01-001-A01

DESIGNATION DESC 09-50-01-001-A01-Worksheets Referenced Information TABLE 1

5.

Procedure WARNING : YOU MUST MONITOR AIRCRAFT STABILITY, WEIGHT AND CG DURING THE RECOVERY PROCESS. NOTE : It is important to use accurate data for the calculation related to the recovery process. Some of the necessary data is the responsibility of the operator and to be accurate, it must be applicable to the specific MSN involved. Data supplied by the manufacturer as generic data is not necessarily accurate for a specific MSN. Refer to the operator’s documentation for precise calculations. If some of the necessary data is not available or if it is not possible to get it, then it is the responsibility of the recovery manager to decide to use estimated data and to continue with the process. Subtask 03-50-01-558-002-A01 A.

How to Find the Effect of Traffic Load Remaining (1) Use data from the Weight and Balance Manual and/or from your specific aircraft configuration data to find the weight, H-arm values and related moment of traffic load remaining. (2) Calculate H-arm moments generated by the traffic load and record it on the Traffic Load Remaining Interim Worksheet (See DESC 09-50-01-001-A01).

03-50-01

Page 26 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 03-50-01-558-803-A01 Ballast Added Effect 1.

General Ballast is any heavy material that you use to add weight if you want to stabilize the aircraft with the CG change method. Ballast can be non recovery kit stock items (such as sand bags, drums filled with water, livestock feed sacks, etc.) that you can buy in-situ. It is important that the ballast is easily transportable to the site, easily managed by the personnel on site and that, if there is a shift in the aircraft CG, no secondary damage will occur if the ballast moves inside the aircraft or when it is necessary to transport the aircraft.

2.


3.


4.


Referenced Information REFERENCE DESC 09-50-01-001-A01 09-10-06 09-10-08

DESIGNATION DESC 09-50-01-001-A01-Worksheets 09-10-06-FUSELAGE FRAMES AND H-ARM TABLE 09-10-08-WING RIBS AND STATIONS Referenced Information TABLE 1

5.

Procedure WARNING : YOU MUST MONITOR AIRCRAFT STABILITY, WEIGHT AND CG DURING THE RECOVERY PROCESS. NOTE : It is important to use accurate data for the calculation related to the recovery process. Some of the necessary data is the responsibility of the operator and to be accurate, it must be applicable to the specific MSN involved. Data supplied by the manufacturer as generic data is not necessarily accurate for a specific MSN. Refer to the operator’s documentation for precise calculations. If some of the necessary data is not available or if it is not possible to get it, then it is the responsibility of the recovery manager to decide to use estimated data and to continue with the process.

03-50-01

Page 27 Jul 01/09


Subtask 03-50-01-558-003-A01 A.

How to find the Effect of Added Ballast (1) To find the effect of added ballast, you need to find the H-arm and, if applicable, the Yarm of the zone in which you added ballast. To calculate the necessary average H-arm and Y-arm: - See 09-10-06 for ballast added inside of fuselage, - See 09-10-08 for ballast added on the wing, (2) Calculate the H-arm and Y-arm moments generated by the weight of ballast you use and record them on the Ballast Added Effect Interim Worksheet (See DESC 09-50-01-001A01).

03-50-01

Page 28 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 03-50-01-558-804-A01 Waste Water Remaining Effect 1.

General The aircraft is equipped with a vacuum system. The waste water from the lavatories and galleys is stored in 1 waste tank (See DESC 09-10-12-006A01 for tank capacity and pre-charged chemical fluid quantities). The waste tank is installed in the pressurized underfloor area in the aft fuselage.

2.


3.

Job Setup References Tank Tank Tank Tank

N˚1 N˚1 N˚1 N˚1

Item - A318 - A319 - A320 - A321

Remaining Weight 25.928 28.316 32.050 38.984

H-arm m (1020.79 m (1114.80 m (1261.81 m (1534.80

Moment to add in) in) in) in)

Waste Water Remaining Weight and Relevant H-arm TABLE 1 4.


Referenced Information REFERENCE DESC 09-10-12-006-A01 DESC 09-50-01-001-A01

DESIGNATION DESC 09-10-12-006-A01-Waste Water Disposal System DESC 09-50-01-001-A01-Worksheets Referenced Information TABLE 2

5.

Procedure WARNING : YOU MUST MONITOR AIRCRAFT STABILITY, WEIGHT AND CG DURING THE RECOVERY PROCESS.

03-50-01

Page 29 Jul 01/09


NOTE : It is important to use accurate data for the calculation related to the recovery process. Some of the necessary data is the responsibility of the operator and to be accurate, it must be applicable to the specific MSN involved. Data supplied by the manufacturer as generic data is not necessarily accurate for a specific MSN. Refer to the operator’s documentation for precise calculations. If some of the necessary data is not available or if it is not possible to get it, then it is the responsibility of the recovery manager to decide to use estimated data and to continue with the process. Subtask 03-50-01-558-004-A01 A.

How to Find the Effect of Waste Water Remaining (1) To find the effect of waste water remaining, you must know the weight of the waste water remaining into tanks minus the pre-load. The generated H-arm moments must be calculated with the data given in the table in Job Setup References . NOTE : The assumptions are that: - After a flight, 2/3 of the potable water is in the waste tank and the volume of water remaining in the potable water tank is negligible, - At take off, the potable water tank are full. (2) Calculate the H-arm moments generated by the waste water and report them on the Waste Water Remaining Interim Worksheet (See DESC 09-50-01-001-A01).

03-50-01

Page 30 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 03-50-01-558-805-A01 Non OEW Catering Equipment Added Effect 1.

General If your Weight and CG calculation is based on OEW, you need to include the NON-OEW Catering Equipment effect.

2.


3.


4.




5.


How to Find the Effect of NON-OEW Catering Equipment Added (1) Use data from the Weight and Balance Manual and/or from your specific aircraft configuration data to find the weight and H-arm values and related moments of NONOEW catering equipment, which was removed. (2) Calculate H-arm moments generated by the NON-OEW Catering Equipment and record them on the NON-OEW Catering Equipment Interim Worksheet (See DESC 09-50-01-001A01).

03-50-01

Page 31 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 03-50-01-558-806-A01 Potable Water Removed Effect 1.

General The aircraft is equipped with a pressurized potable water system. Potable water for the toilets and galleys is stored in 1 tank, which is installed in the pressurized underfloor area. See DESC 09-10-12-005-A01 for potable water tanks capacities. NOTE : The number of items of equipment can change with the customer.

2.


3.

Job Setup References The table that follow gives the average H-arm, from standard aircraft configuration. Tank Tank Tank Tank

Item N˚ 1 - A318 N˚1 - A319 N˚1 - A320 N˚1 - A321

Remaining Weight

Average H-arm 25.663 m (1010.35 in) 28.051 m (1104.37 in) 31.785 m (1251.38 in) 38.719 m (1524.37 in)

Moment to subtract

Average H-arm TABLE 1 4.



DESIGNATION DESC 09-10-12-005-A01-Potable Water System DESC 09-50-01-001-A01-Worksheets Referenced Information TABLE 2

5.

Procedure WARNING : YOU MUST MONITOR AIRCRAFT STABILITY, WEIGHT AND CG DURING THE RECOVERY PROCESS.

03-50-01

Page 32 Jul 01/09


NOTE : It is important to use accurate data for the calculation related to the recovery process. Some of the necessary data is the responsibility of the operator and to be accurate, it must be applicable to the specific MSN involved. Data supplied by the manufacturer as generic data is not necessarily accurate for a specific MSN. Refer to the operator’s documentation for precise calculations. If some of the necessary data is not available or if it is not possible to get it, then it is the responsibility of the recovery manager to decide to use estimated data and to continue with the process. Subtask 03-50-01-558-006-A01 A.

How to Find the Effect of Potable Water Removed (1) Weight and CG calculation is based on OEW or DOW, which include full potable water tank. (2) To find the effect of removed potable water, you must know the weight of the potable water which was moved to the waste tank during flight or manually removed on recovery site. The generate H-arm moments have to be calculated with data provided in the table in Job Setup References . NOTE : The assumptions are that: - After a flight, 2/3 of the potable water is in the waste tank and the volume of water remaining in the potable water tank is negligible, - At take off, the potable water tank are full. (3) Calculate H-arm moments generated by the Potable Water Removed and record it on the Potable Water Removed Interim Worksheet (See DESC 09-50-01-001-A01).

03-50-01

Page 33 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 03-50-01-558-807-A01 Cockpit and Cabin Crew Removed Effect 1.

General Weight and CG calculation is based on OEW or DOW, which include cockpit and cabin crew.

2.


3.


4.




5.


How to Find the Effect of Removed Cockpit and Cabin Crew (1) Use data from Weight and Balance Manual and/or from your specific aircraft configuration data to find weight, H-arm value and related moment of cockpit and cabin crew included in the OEW or in the DOW, which were removed. (2) Calculate H-arm moments generated by the cockpit and cabin crew removed and report it on the Cockpit and Cabin Crew Removed interim worksheet (See DESC 09-50-01-001A01).

03-50-01

Page 34 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 03-50-01-558-808-A01 Catering Equipment Removed Effect 1.

General Weight and CG calculation is based on OEW or DOW, which include catering equipment. NOTE : For Non-OEW Catering Equipment Effect, see TASK 03-50-01-558-805-A01.

2.


3.


4.


Referenced Information REFERENCE TASK 03-50-01-558-805-A01 DESC 09-50-01-001-A01

DESIGNATION TASK 03-50-01-558-805-A01-Non OEW Catering Equipment Added Effect DESC 09-50-01-001-A01-Worksheets Referenced Information TABLE 1

5.


How to find the Effect of Catering Equipment Removed (1) Use data from the Weight and Balance Manual and/or from your specific aircraft configuration data to find the weight, H-arm and Y-arm and related moments of catering equipment which was removed from OEW or DOW configuration.

03-50-01

Page 35 Jul 01/09


(2) Calculate H-arm and Y-arm moments generated by the Catering Equipment Removed and report it on the Catering Equipment Removed Interim Worksheet (See DESC 09-50-01-001A01).

03-50-01

Page 36 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 03-50-01-558-809-A01 Hydraulic Fluid Removed Effect 1.

General The aircraft has 3 hydraulic circuits. See DESC 09-10-12-002-A01 for hydraulic circuit details.

2.


3.

Job Setup References The tables that follow give the average H-arm from standard aircraft configuration, with Hydraulic Fluid removed. Use these values with the total weight of Hydraulic Fluid. The Weights are based on an Hydraulic Fluid density of 1.002 kg per liter. Hydraulic System - A318 Remaining Weight

Item

Capacity

H-arm

Green Tank

14 l (3.70 US gal)

16.594 m (653.31 in)

Yellow Tank

12 l (3.17 US gal)

Blue Tank

6 l (1.59 US gal)

Systems

147 l (38.83 US gal)

15.944 m (627.72 in) 20.294 m (798.98 in) 16.708 m (657.80 in)

A/C Total

202 l (53.36 US gal)

16.769 m (660.20 in)

Moment to subtract

Hydraulic Fluid Tank Remaining Weight and Relevant H-arm - A318 TABLE 1 Hydraulic System - A319 Remaining Weight

Item

Capacity

Green Tank

14 l (3.70 US gal)

Yellow Tank

12 l (3.17 US gal)

Blue Tank

6 l (1.59 US gal)

H-arm

Moment to subtract

17.382 m (684.33 in) 16.732 m (658.74 in) 21.082 m (830.00 in)

03-50-01

Page 37 Jul 01/09


Item

Capacity

Systems

148 l (39.10 US gal) 180 l (47.55 US gal)

A/C Total

Hydraulic System - A319 Remaining Weight

H-arm

Moment to subtract

18.462 m (726.85 in) 18.350 m (722.44 in)


Item

Capacity

Green Tank

14 l (3.70 US gal)

Yellow Tank

12 l (3.17 US gal)

Blue Tank

6 l (1.59 US gal)

Systems

152 l (40.15 US gal) 184 l (48.61 US gal)

A/C Total

H-arm

Moment to subtract



Item

Capacity

Green Tank

14 l (3.70 US gal)

Yellow Tank

12 l (3.17 US gal)

Blue Tank

6 l (1.59 US gal)

Systems

170 l (44.91 US gal)

H-arm

Moment to subtract

23.249 m (915.31 in) 22.599 m (889.72 in) 26.949 m (1060.98 in) 24.150 m (950.79 in)

03-50-01

Page 38 Jul 01/09


Hydraulic System - A321 Remaining Weight

Item

Capacity

A/C Total

202 l (53.36 US gal)

H-arm

Moment to subtract

24.079 m (947.99 in)

Hydraulic Fluid Tank Remaining Weight and Relevant H-arm - A321 TABLE 4 4.



DESIGNATION DESC 09-10-12-002-A01-Hydraulic System DESC 09-50-01-001-A01-Worksheets Referenced Information TABLE 5

5.


How to Find the Effect of Hydraulic Fluid Removed (1) Weight and CG calculation is based on OEW or DOW which include hydraulic fluid. (2) Use the table in Job Setup References to calculate H-arm moment to subtract. (3) Calculate H-arm moments generated by the hydraulic fluids removed and record them on the Hydraulic Fluids Removed Interim Worksheet. (See DESC 09-50-01-001-A01).

03-50-01

Page 39 Jul 01/09


**ON A/C A318-100 TASK 03-50-01-558-810-A01 Large Components Removed / Missing 1.

General The equipment or aircraft parts that follow may have a significant effect on weight and balance management for the recovery. - APU and tail cone - APU - Pax doors - Cargo doors - Radome - Pylon - Thrust reversers - Bare engines - Complete power plant - Rudders - VTP equipped - HTP equipped - Elevators - Slats - Flaps - Ailerons - Spoilers - Winglet / wingtip - Landing gear equipped - Landing gear Leg Fairing - Wheels - Brakes If you need to remove some of these large components during recovery or if some of these large components are missing when you start the recovery process, use the data that follow and calculation tables to determine the effect on NRW and the CG position.

2.


3.


Wing Equipment Table Item Slat 1


H-Arm 14.092 m (554.80 in)

03-50-01

H-Arm Moment 605.956 kgm (52706 lb.in)

Page 40 Jul 01/09


Item Slat 2 Slat 3 Slat 4 Slat 5 Inner Flap Outer Flap Spoiler 1 Spoiler 2 Spoiler 3 Spoiler 4 Spoiler 5 Aileron Wing Tip and Winglet

Weight 30 kg (66 lb) 28 kg (62 lb) 25 kg (55 lb) 24 kg (53 lb) 107 kg (236 lb) 120 kg (265 lb) 16 kg (35 lb) 14 kg (31 lb) 13 kg (29 lb) 12 kg (26 lb) 14 kg (31 lb) 24 kg (53 lb) 26 kg (57 lb)

H-Arm 16.064 m (632.44 in) 17.412 m (685.51 in) 18.698 m (736.14 in) 19.912 m (783.94 in) 18.331 m (721.69 in) 19.466 m (766.38 in) 18.159 m (714.92 in) 18.528 m (729.45 in) 19.099 m (751.93 in) 19.671 m (774.45 in) 20.258 m (797.56 in) 21.231 m (835.87 in) 21.504 m (846.61 in)

H-Arm Moment 481.920 kgm (41741.04 lb.in) 487.536 kgm (42501.62 lb.in) 467.45 kgm (40487.7 lb.in) 477.888 kgm (41548.82 lb.in) 1961.417 kgm (170318.84 lb.in) 2335.92 kgm (203090.7 lb.in) 290.544 kgm (25022.2 lb.in) 259.392 kgm (22612.95 lb.in) 248.287 kgm (21805.97 lb.in) 236.052 kgm (22459.05 lb.in) 283.612 kgm (24724.36 lb.in) 509.544 kgm (44301.11 lb.in) 559.104 kgm (48256.77 lb.in)

H-Arm 7.579 m (298.39 in) 25.960 m (1022.05 in) 15.430 m (607.48 in)

H-Arm Moment 742.742 kgm (64452.24 lb.in) 2492.16 kgm (216674.6 lb.in) 200.59 kgm (17616.92 lb.in)

Equipment on Wing TABLE 1 B.

Fuselage Equipment Table Item Forward Passenger/Crew Door Aft Passenger/Crew Door Emergency Exit


03-50-01

Page 41 Jul 01/09


Item Forward Cargo Door Aft Cargo Door Radome APU and Tailcone APU

Weight 91 kg (201 lb) 103 kg (227 lb) 26 kg (57 lb) 470 kg (1036 lb) 139 kg (306 lb)

H-Arm 10.433 m (410.75 in) 21.507 m (846.73 in) 3.300 m (129.92 in) 31.862 m (1254.41 in) 32.032 m (1261.10 in)

H-Arm Moment 949.403 kgm (82560.75 lb.in) 2215.221 kgm (192207.71 lb.in) 85.8 kgm (7405.44 lb.in) 14975.14 kgm (1299568.76 lb.in) 4452.448 kgm (385896.6 lb.in)



H-Arm 30.413 m (1197.36 in) 31.909 m (1256.26 in) 30.219 m (1189.72 in)


Fuselage Equipment TABLE 2 C.

Vertical Stabilizer Equipment Table Item Box Rudder Removable Leading Edge Tip Fuselage Fairing

Weight 270 kg (595 lb) 95 kg (209 lb) 75 kg (165 lb) 20 kg (44 lb) 11 kg (24 lb) VTP Equipment TABLE 3

D.

Horizontal Stabilizer Equipment Table Item Box Elevator Removable Leading Edge


03-50-01

Page 42 Jul 01/09


Item

Weight

Tip

6 kg (13 lb) 7 kg (15 lb)

Tailplane Fuselage Fairing

H-Arm 32.355 m (1273.82 in) 31.135 m (1225.79 in)

H-Arm Moment 194.13 kgm (16559.66 lb.in) 217.945 kgm (18386.85 lb.in)

H-Arm 11.960 m (470.87 in) 12.820 m (504.72 in) 12.820 m (504.72 in) 13.943 m (548.94 in) 13.943 m (548.94 in) 13.541 m (533.11 in) 13.565 m (534 in) 15.118 m (595.20 in)

H-Arm Moment 1650.48 kgm (143144.48 lb.in) 474.34 kgm (41387.04 lb.in) 538.44 kgm (834806.88 lb.in) 2691 kgm (233299.5 lb.in) 2955.916 kgm (256354.98 lb.in) 3766.898 kgm (3264765.64 lb.in) 47491.065 kgm (4121412 lb.in) 8964.974 kgm (777926.4 lb.in)

HTP Equipment TABLE 4 E.

Power Plant Equipment Table Item Inlet Cowl Fan Cowl LH Fan Cowl RH Thrust Reverser LH Thrust Reverser RH Bare Engine Complete Power Plant Pylon

Weight 138 kg (304 lb) 37 kg (82 lb) 42 m (1654 in) 193 kg (425 lb) 212 kg (467 lb) 2778 kg (6124 lb) 3501 kg (7718 lb) 593 kg (1307 lb)

Power Plant Equipment - CFM 56 Engine TABLE 5 Item Inlet Cowl Fan Cowl Thrust Reverser


H-Arm 11.921 m (469.33 in) 12.803 m (504.06 in) 13.290 m (523.23 in)

03-50-01


Page 43 Jul 01/09


Item


Bare Engine Complete Power Plant Pylon

H-Arm 13.640 m (537.01 in) 13.673 m (538.31 in) 15.227 m (599.49 in)


Power Plant Equipment - PW 6000 Engine TABLE 6 F.

Landing Gear Equipment Table Item Nose Landing Gear Complete Wheel with Tire

Weight 327 kg (721 lb) 35 kg (77 lb)

H-Arm 7.600 m (299.21 in) 7.605 m (299.41 in)


H-Arm 17.225 m (678.15 in) 17.670 m (695.67 in) 17.862 m (703.23 in) 17.862 m (703.23 in)

H-Arm Moment 275.6 kgm (23735.25 lb.in) 17846.7 kgm (1549257.09 lb.in) 2411.37 kgm (209562.54 lb.in) 1232.478 kgm (106890.96 lb.in)

NLG Equipment TABLE 7 Item MLG Leg Fairing Main Landing Gear Complete Wheel with Tire Brake

Weight 16 kg (35 lb) 1010 kg (2227 lb) 135 kg (298 lb) 69 kg (152 lb) MLG Equipment TABLE 8

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4.




5.

Procedure WARNING : MAKE SURE THAT ALL PERSONNEL IS AT A SAFE DISTANCE DURING THE REMOVAL OF FUEL, CARGO OR LARGE COMPONENTS. AN UNEQUAL REMOVAL OF FUEL OR CARGO OR THE REMOVAL OF LARGE COMPONENTS CAN CHANGE THE CG AND THE LONGITUDINAL AND LATERAL STABILITY OF THE AIRCRAFT. DEATH OR SERIOUS INJURY MAY RESULT IF THE AIRCRAFT FALLS ON RECOVERY PERSONNEL. WARNING : YOU MUST MONITOR AIRCRAFT STABILITY, WEIGHT AND CG DURING THE RECOVERY PROCESS. WARNING : YOU MUST CONTACT AIRBUS BEFORE YOU MANUALLY OPERATE A SYSTEM OR REMOVE A COMPONENT WHEN THE AIRCRAFT IS IN AN ABNORMAL ATTITUDE OR DISABLED. THE AMM PROCEDURES ARE APPLICABLE ON AN AIRCRAFT IN A LEVEL CONFIGURATION ONLY. NOTE : It is important to use accurate data for the calculation related to the recovery process. Some of the necessary data is the responsibility of the operator and to be accurate, it must be applicable to the specific MSN involved. Data supplied by the manufacturer as generic data is not necessarily accurate for a specific MSN. Refer to the operator’s documentation for precise calculations. If some of the necessary data is not available or if it is not possible to get it, then it is the responsibility of the recovery manager to decide to use estimated data and to continue with the process. Subtask 03-50-01-558-010-A01 A.

How to find the Effect of Large Components Removed / Missing (1) See the tables in Job Setup References to determine the weight, H-arm, Y-arm and Z-arm Moment. (2) Record Weight, H-arm, Y-arm and Z-arm moment into the relevant boxes of the Large Component Removed / Missing Effect Interim Worksheet (See DESC 09-50-01-001-A01).

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**ON A/C A319-100 TASK 03-50-01-558-810-B01 Large Components Removed / Missing 1.


2.


3.




H-Arm 14.092 m (554.80 in)

03-50-01

H-Arm Moment 605.956 kgm (52706 lb.in)

Page 46 Jul 01/09


Item Slat 2 Slat 3 Slat 4 Slat 5 Inner Flap Outer Flap Spoiler 1 Spoiler 2 Spoiler 3 Spoiler 4 Spoiler 5 Aileron Wing Tip and Winglet

Weight 30 kg (66 lb) 28 kg (62 lb) 25 kg (55 lb) 24 kg (53 lb) 107 kg (236 lb) 120 kg (265 lb) 16 kg (35 lb) 14 kg (31 lb) 13 kg (29 lb) 12 kg (26 lb) 14 kg (31 lb) 24 kg (53 lb) 26 kg (57 lb)

H-Arm 16.064 m (632.44 in) 17.412 m (685.51 in) 18.698 m (736.14 in) 19.912 m (783.94 in) 18.331 m (721.69 in) 19.466 m (766.38 in) 18.159 m (714.92 in) 18.528 m (729.45 in) 19.099 m (751.93 in) 19.671 m (774.45 in) 20.258 m (797.56 in) 21.231 m (835.87 in) 21.504 m (846.61 in)

H-Arm Moment 481.92 kgm (41741.04 lb.in) 487.536 kgm (42501.62 lb.in) 467.45 kgm (40487.7 lb.in) 477.888 kgm (41548.82 lb.in) 1961.41 kgm (170318.84 lb.in) 2335.92 kgm (203090.7 lb.in) 290.544 kgm (25022.2 lb.in) 259.392 kgm (22612.95 lb.in) 248.287 kgm (21805.97 lb.in) 236.052 kgm (20135.7 lb.in) 283.612 kgm (24724.36 lb.in) 509.544 kgm (44301.11 lb.in) 559.104 kgm (48256.77 lb.in)

H-Arm 7.579 m (298.39 in) 28.351 m (1116.18 in) 15.371 m (605.16 in)



Fuselage Equipment Table Item Forward Passenger/Crew Door Aft Passenger/Crew Door Emergency Exit (Optional)


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Item Emergency Exit Forward Cargo Door Aft Cargo Door Radome APU and Tailcone APU

Weight 15 kg (33 lb) 112 kg (247 lb) 112 kg (247 lb) 26 kg (57 lb) 460 kg (1014 lb) 137 kg (302 lb)

H-Arm 16.217 m (638.46 in) 13.240 m (521.26 in) 25.635 m (1009.25 in) 3.300 m (129.92 in) 34.241 m (1348 in) 34.420 m (1355.12 in)

H-Arm Moment 243.255 kgm (31069.18 lb.in) 1482.88 kgm (128751.22 lb.in) 2871.12 kgm (249284.75 lb.in) 85.8 kgm (7405.44 lb.in) 15750.86 kgm (1366872 lb.in) 4715.54 kgm (409246.24 lb.in)


H-Arm Moment 8671.59 kgm (752347.75 lb.in) 3090.633 kgm (268763.13 lb.in) 2378.838 kgm (206771 lb.in) 341.76 kgm (29601.22 lb.in) 471.6 kgm (40847.4 lb.in)

H-Arm 32.800 m (1291.34 in) 34.296 m (1350.24 in)



Vertical Stabilizer Equipment Table Item Box Rudder Removable Leading Edge Tip Fuselage Fairing

Weight 270 kg (595 lb) 91 kg (201 lb) 77 kg (170 lb) 10 kg (22 lb) 15 kg (33 lb) VTP Equipment TABLE 3

D.

Horizontal Stabilizer Equipment Table Item Box Elevator

Weight 417 kg (919 lb) 96 kg (212 lb)

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Item Removable Leading Edge


Tip Tailplane Fuselage Fairing

H-Arm 32.606 m (1283.70 in) 34.742 m (1367.80 in) 33.522 m (1319.76 in)


H-Arm 12.748 m (501.89 in) 13.608 m (535.75 in) 13.608 m (535.75 in) 14.731 m (579.96 in) 14.731 m (579.96 in) 14.329 m (564.13 in) 14.353 m (565.08 in) 15.906 m (626.22 in)

H-Arm Moment 1759.224 kgm (152574.56 lb.in) 503.496 kgm (43931.5 lb.in) 571.536 kgm (886130.5 lb.in) 2843.083 kgm (246440.5 lb.in) 3122.972 kgm (270841.32 lb.in) 39805.962 kgm (3454732.12 lb.in) 50249.853 kgm (4361287.44 lb.in) 9432.258 kgm (818469.54 lb.in)




Power Plant Equipment - CFM 56 Engine TABLE 5 Item Inlet Cowl Fan Cowl

Weight 121 kg (267 lb) 98 kg (216 lb)

H-Arm 12.479 m (491.30 in) 13.577 m (534.53 in)

03-50-01


Page 49 Jul 01/09


Item Thrust Reverser


Bare Engine Complete Power Plant Pylon


H-Arm Moment 7772.59 kgm (674636.5 lb.in) 38285.39 kgm (3322841.25 lb.in) 50878.08 kgm (4415905.6 lb.in) 9468.42 kgm (821723.56 lb.in)

Power Plant Equipment - IAE V2500 Engine TABLE 6 F.


Weight 327 kg (721 lb) 35 kg (77 lb)

H-Arm 7.600 m (299.21 in) 7.605 m (299.41 in)



H-Arm Moment 288.208 kgm (24820.95 lb.in) 18642.58 kgm (1618338.63 lb.in) 2517.75 kgm (218806.5 lb.in) 1286.85 kgm (111606 lb.in)

NLG Equipment TABLE 7 Item MLG Leg Fairing Main Landing Gear Complete Wheel with Tire Brake

Weight 16 kg (35 lb) 1010 kg (2227 lb) 135 kg (298 lb) 69 kg (152 lb) MLG Equipment TABLE 8

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4.




5.

Procedure WARNING : MAKE SURE THAT ALL PERSONNEL IS AT A SAFE DISTANCE DURING THE REMOVAL OF FUEL, CARGO OR LARGE COMPONENTS. AN UNEQUAL REMOVAL OF FUEL OR CARGO OR THE REMOVAL OF LARGE COMPONENTS CAN CHANGE THE CG AND THE LONGITUDINAL AND LATERAL STABILITY OF THE AIRCRAFT. DEATH OR SERIOUS INJURY MAY RESULT IF THE AIRCRAFT FALLS ON RECOVERY PERSONNEL. WARNING : YOU MUST MONITOR AIRCRAFT STABILITY, WEIGHT AND CG DURING THE RECOVERY PROCESS. WARNING : YOU MUST CONTACT AIRBUS BEFORE YOU MANUALLY OPERATE A SYSTEM OR REMOVE A COMPONENT WHEN THE AIRCRAFT IS IN AN ABNORMAL ATTITUDE OR DISABLED. THE AMM PROCEDURES ARE APPLICABLE ON AN AIRCRAFT IN A LEVEL CONFIGURATION ONLY. NOTE : It is important to use accurate data for the calculation related to the recovery process. Some of the necessary data is the responsibility of the operator and to be accurate, it must be applicable to the specific MSN involved. Data supplied by the manufacturer as generic data is not necessarily accurate for a specific MSN. Refer to the operator’s documentation for precise calculations. If some of the necessary data is not available or if it is not possible to get it, then it is the responsibility of the recovery manager to decide to use estimated data and to continue with the process. Subtask 03-50-01-558-012-A01 A.


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**ON A/C A320-100 A320-200 TASK 03-50-01-558-810-C01 Large Components Removed / Missing 1.


2.


3.




H-Arm 16.470 m (648.43 in)

03-50-01

H-Arm Moment 642.33 kgm (55764.98 lb.in)

Page 52 Jul 01/09


Item Slat 2 Slat 3 Slat 4 Slat 5 Inner Flap Outer Flap Spoiler 1 Spoiler 2 Spoiler 3 Spoiler 4 Spoiler 5 Aileron Wing Tip (A320-100) Wing Tip and Winglet (A320-200)

Weight 30 kg (66 lb) 28 kg (62 lb) 25 kg (55 lb) 23 kg (51 lb) 114 kg (251 lb) 122 kg (269 lb) 15 kg (33 lb) 13 kg (29 lb) 12 kg (26 lb) 12 kg (26 lb) 14 kg (31 lb) 24 kg (53 lb) 15 kg (33 lb) 26 kg (57 lb)

H-Arm 18.460 m (726.77 in) 19.790 m (779 in) 21.070 m (829.53 in) 22.290 m (877.56 in) 20.716 m (815.59 in) 21.872 m (861.10 in) 20.394 m (802.91 in) 20.824 m (819.84 in) 21.424 m (843.46 in) 21.984 m (865.51 in) 22.519 m (886.57 in) 23.582 m (928.43 in) 23.680 m (932.28 in) 23.960 m (943.31 in)

H-Arm Moment 553.8 kgm (47966.82 lb.in) 554.12 kgm (48298 lb.in) 526.75 kgm (45624.15 lb.in) 512.67 kgm (44755.56 lb.in) 2361.624 kgm (204713.09 lb.in) 2668.384 kgm (231635.9 lb.in) 305.91 kgm (26496.03 lb.in) 270.712 kgm (23775.36 lb.in) 257.088 kgm (21929.96 lb.in) 263.808 kgm (22503.26 lb.in) 315.266 kgm (27483.67 lb.in) 565.968 kgm (49206.79 lb.in) 355.2 kgm (30765.24 lb.in) 622.96 kgm (53768.67 lb.in)

H-Arm 7.579 m (298.39 in) 32.085 m (1263.19 in)



Fuselage Equipment Table Item Forward Passenger/Crew Door Aft Passenger/Crew Door

Weight 98 kg (216 lb) 96 kg (212 lb)

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Item Emergency Exit Emergency Exit Forward Cargo Door Aft Cargo Door Bulk Cargo Door Radome APU and Tailcone APU

Weight 15 kg (33 lb) 15 kg (33 lb) 121 kg (267 lb) 121 kg (267 lb) 37 kg (82 lb) 26 kg (57 lb) 460 kg (1014 lb) 136 kg (300 lb)


H-Arm Moment 267.27 kgm (2248.95 lb.in) 267.27 kgm (23149.5 lb.in) 1294.7 kgm (265203.09 lb.in) 3052.709 kgm (265203.09 lb.in) 1067.783 kgm (93166.76 lb.in) 85.8 kgm (7405.44 lb.in) 17473.1 kgm (1516406.58 lb.in) 5189.08 kgm (450651 lb.in)

H-Arm 36.003 m (1417.44 in) 37.702 m (1484.33 in) 35.332 m (1391.02 in) 37.910 m (1492.52 in) 33.067 m (1301.85 in) 35.174 m (1384.80 in)

H-Arm Moment 13141.095 kgm (1141039.2 lb.in) 3317.776 kgm (287960.02 lb.in) 1695.936 kgm (147448.12 lb.in) 341.19 kgm (39850.4 lb.in) 859.742 kgm (74205.45 lb.in) 527.61 kgm (45698.4 lb.in)


Vertical Stabilizer Equipment Table Item Box Rudder Removable Leading Edge Tip Dorsal Fin Fuselage Fairing

Weight 365 kg (805 lb) 88 kg (194 lb) 48 kg (106 lb) 9 kg (20 lb) 26 kg (57 lb) 15 kg (33 lb) VTP Equipment TABLE 3

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D.

Horizontal Stabilizer Equipment Table Item

Weight 418 kg (922 lb) 97 kg (214 lb) 84 kg (185 lb) 6 kg (13 lb) 7 kg (15 lb)

Box Elevator Removable Leading Edge Tip Tailplane Fuselage Fairing




H-Arm Moment 1994.514 kgm (172982.08 lb.in) 565.952 kgm (49380.4 lb.in) 642.432 kgm (996038.8 lb.in) 3159.217 kgm (273891.25 lb.in) 3470.228 kgm (300958.15 lb.in) 44345.214 kgm (3848689.04 lb.in) 55970.487 kgm (4857786.38 lb.in) 9480.291 kgm (822638.87 lb.in)




Power Plant Equipment - CFM 56 Engine TABLE 5

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Page 55 Jul 01/09


Item


Inlet Cowl Fan Cowl Thrust Reverser Bare Engine Complete Power Plant Pylon


H-Arm Moment 1707.31 kgm (148321.17 lb.in) 1481.76 kgm (128580.48 lb.in) 8559.432 kgm (742928.1 lb.in) 42573.375 kgm (3695022.5 lb.in) 56541.76 kgm (4907424 lb.in) 10455.858 kgm (907421.48 lb.in)



Weight 323 kg (712 lb) 36 kg (79 lb)

H-Arm 7.617 m (299.88 in) 7.628 m (300.31 in)


16 kg (35 lb) 931 kg (2053 lb) 204 kg (450 lb)

H-Arm 19.675 m (774.61 in) 20.067 m (790.04 in) 20.250 m (797.24 in)

H-Arm Moment 314.8 kgm (27111.35 lb.in) 18682.377 kgm (1621952.12 lb.in) 4131 kgm (358758 lb.in)

1234 kg (2721 lb)

20.056 m (789.61 in)

24749.104 kgm (2148528.81 lb.in)

NLG Equipment TABLE 7 Item MLG Leg Fairing Main Landing Gear Complete (Twin Wheel MLG) Wheel with Tire and Brake (Twin Wheel MLG) Main Landing Gear Complete (Optional Four Wheel Bogie MLG)

Weight

03-50-01

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Item Wheel with Tire and Brake (Optional Four Wheel Bogie MLG)

Weight

H-Arm

114 kg (251 lb)

20.266 m (797.87 in)


MLG Equipment TABLE 8 4.




5.

Procedure WARNING : MAKE SURE THAT ALL PERSONNEL IS AT A SAFE DISTANCE DURING THE REMOVAL OF FUEL, CARGO OR LARGE COMPONENTS. AN UNEQUAL REMOVAL OF FUEL OR CARGO OR THE REMOVAL OF LARGE COMPONENTS CAN CHANGE THE CG AND THE LONGITUDINAL AND LATERAL STABILITY OF THE AIRCRAFT. DEATH OR SERIOUS INJURY MAY RESULT IF THE AIRCRAFT FALLS ON RECOVERY PERSONNEL. WARNING : YOU MUST MONITOR AIRCRAFT STABILITY, WEIGHT AND CG DURING THE RECOVERY PROCESS. WARNING : YOU MUST CONTACT AIRBUS BEFORE YOU MANUALLY OPERATE A SYSTEM OR REMOVE A COMPONENT WHEN THE AIRCRAFT IS IN AN ABNORMAL ATTITUDE OR DISABLED. THE AMM PROCEDURES ARE APPLICABLE ON AN AIRCRAFT IN A LEVEL CONFIGURATION ONLY. NOTE : It is important to use accurate data for the calculation related to the recovery process. Some of the necessary data is the responsibility of the operator and to be accurate, it must be applicable to the specific MSN involved. Data supplied by the manufacturer as generic data is not necessarily accurate for a specific MSN. Refer to the operator’s documentation for precise calculations. If some of the necessary data is not available or if it is not possible to get it, then it is the responsibility of the recovery manager to decide to use estimated data and to continue with the process.

03-50-01

Page 57 Jul 01/09


Subtask 03-50-01-558-013-A01 A.


03-50-01

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**ON A/C A321-100 A321-200 TASK 03-50-01-558-810-D01 Large Components Removed / Missing 1.


2.


3.




H-Arm 20.747 m (816.81 in)

03-50-01


Page 59 Jul 01/09


Item Slat 2 Slat 3 Slat 4 Slat 5 Inner Flap Inner Flap Tab Outer Flap Outer Flap Tab Spoiler 1 Spoiler 2 Spoiler 3 Spoiler 4 Spoiler 5 Aileron Wing Tip and Winglet

Weight 31 kg (68 lb) 28 kg (62 lb) 27 kg (60 lb) 25 kg (55 lb) 124 kg (273 lb) 85 kg (187 lb) 120 kg (265 lb) 80 kg (176 lb) 16 kg (35 lb) 14 kg (31 lb) 13 kg (29 lb) 12 kg (26 lb) 14 kg (31 lb) 24 kg (53 lb) 26 kg (57 lb)

H-Arm 22.719 m (894.45 in) 24.067 m (947.52 in) 25.353 m (998.15 in) 26.567 m (1045.94 in) 25.195 m (991.93 in) 25.195 m (991.93 in) 26.143 m (1029.25 in) 26.139 m (1029.09 in) 24.754 m (974.57 in) 25.205 m (992.32 in) 25.754 m (1013.94 in) 26.267 m (1034.13 in) 26.913 m (1059.57 in) 27.854 m (1096.61 in) 28.165 m (1108.86 in)

H-Arm Moment 704.289 kgm (60822.6 lb.in) 673.876 kgm (58746.24 lb.in) 684.531 kgm (59889 lb.in) 664.175 kgm (57526.7 lb.in) 3124.18 kgm (270796.89 lb.in) 2141.575 kgm (185490.91 lb.in) 3137.16 kgm (272751.25 lb.in) 2091.12 kgm (181119.84 lb.in) 396.064 kgm (34109.95 lb.in) 352.87 kgm (30761.92 lb.in) 334.802 kgm (39404.26 lb.in) 315.204 kgm (26887.38 lb.in) 376.782 kgm (32846.67 lb.in) 668.496 kgm (58120.33 lb.in) 732.29 kgm (63205.02 lb.in)

H-Arm 7.579 m (298.39 in)



Fuselage Equipment Table Item Forward Passenger/Crew Door


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Page 60 Jul 01/09


Item Aft Passenger/Crew Door Emergency Exit FWD RH Emergency Exit FWD LH Emergency Exit Aft Forward Cargo Door Aft Cargo Door Bulk Cargo Door Radome APU and Tailcone APU

Weight 96 kg (212 lb) 70 kg (154 lb) 81 kg (179 lb) 70 kg (154 lb) 112 kg (247 lb) 112 kg (247 lb) 34 kg (75 lb) 26 kg (57 lb) 460 kg (1014 lb) 145 kg (320 lb)

H-Arm 39.016 m (1536.06 in) 16.384 m (645.04 in) 16.384 m (645.04 in) 27.331 m (1076.02 in) 10.681 m (420.51 in) 32.139 m (1265.32 in) 35.793 m (1409.17 in) 3.300 m (129.92 in) 44.923 m (1768.62 in) 45.089 m (1775.16 in)

H-Arm Moment 3745.536 kgm (325644.72 lb.in) 1146.88 kgm (99336.16 lb.in) 1327.104 kgm (115462.16 lb.in) 1913.17 kgm (165707.08 lb.in) 1196.272 kgm (103865.97 lb.in) 3599.568 kgm (312534.04 lb.in) 1216.962 kgm (105687.75 lb.in) 85.8 kgm (7405.44 lb.in) 20664.58 kgm (1793380.68 lb.in) 6537.905 kgm (598051.2 lb.in)


H-Arm Moment 11555.19 kgm (1002527.4 lb.in) 4061.421 kgm (353183.13 lb.in) 3200.274 kgm (278171 lb.in) 448.44 kgm (38841.22 lb.in)


Vertical Stabilizer Equipment Table Item Box Rudder Removable Leading Edge Tip


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Item Fuselage Fairing


H-Arm 42.108 m (1657.80 in)


H-Arm 43.468 m (1711.34 in) 44.964 m (1770.24 in) 43.274 m (1703.70 in) 45.410 m (1787.80 in) 44.190 kg (97.42 lb)

H-Arm Moment 18126.156 kgm (1572721.46 lb.in) 4316.544 kgm (375.290.88 lb.in) 359.016 kgm (315184.5 lb.in) 272.46 kgm (23241.4 lb.in) 309.33 kgm (1461.3 lb.in)

H-Arm 18.615 m (732.87 in) 19.475 m (766.73 in) 19.475 m (766.73 in) 20.598 m (810.94 in) 20.598 m (810.94 in) 20.196 m (795.12 in) 20.220 m (796.06 in)

H-Arm Moment 2568.87 kgm (222792.48 lb.in) 720.575 kgm (62871.86 lb.in) 817.95 kgm (1268171.42 lb.in) 3975.414 kgm (344649.5 lb.in) 4366.776 kgm (378708.98 lb.in) 56104.488 kgm (4869314.88 lb.in) 70790.22 kgm (6143991.08 lb.in)

VTP Equipment TABLE 3 D.

Horizontal Stabilizer Equipment Table Item Box Elevator Removable Leading Edge Tip Tailplane Fuselage Fairing

Weight 417 kg (919 lb) 96 kg (212 lb) 84 kg (185 lb) 6 kg (13 lb) 7 kg (15 lb) HTP Equipment TABLE 4

E.

Power Plant Equipment Table Item Inlet Cowl Fan Cowl LH Fan Cowl RH Thrust Reverser LH Thrust Reverser RH Bare Engine Complete Power Plant

Weight 138 kg (304 lb) 37 kg (82 lb) 42 m (1654 in) 193 kg (425 lb) 212 kg (467 lb) 2778 kg (6124 lb) 3501 kg (7718 lb)

03-50-01

Page 62 Jul 01/09


Item


Pylon

H-Arm 21.773 m (857.20 in)


Power Plant Equipment - CFM 56 Engine TABLE 5 Item


Inlet Cowl Fan Cowl Thrust Reverser Bare Engine Complete Power Plant Pylon


H-Arm Moment 2219.866 kgm (192848.76 lb.in) 1905.512 kgm (165350.16 lb.in) 10811.696 kgm (938415.66 lb.in) 53920.945 kgm (4679848.75 lb.in) 71529.92 kgm (6208310.4 lb.in) 12971.019 kgm (1125693.24 lb.in)



Weight 327 kg (720.91 lb) 35 kg (77 lb)

H-Arm 7.600 m (299.21 in) 7.605 m (299.41 in)


H-Arm 23.960 m (943.31 in) 24.339 m (958.23 in)


NLG Equipment TABLE 7 Item MLG Leg Fairing Main Landing Gear Complete

Weight 23 kg (51 lb) 1176 kg (2593 lb)

03-50-01

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Item Wheel with Tire Brake

Weight 166 kg (366 lb) 93 kg (205 lb)

H-Arm 24.517 m (965.24 in) 24.517 m (965.24 in)


MLG Equipment TABLE 8 4.




5.

Procedure WARNING : MAKE SURE THAT ALL PERSONNEL IS AT A SAFE DISTANCE DURING THE REMOVAL OF FUEL, CARGO OR LARGE COMPONENTS. AN UNEQUAL REMOVAL OF FUEL OR CARGO OR THE REMOVAL OF LARGE COMPONENTS CAN CHANGE THE CG AND THE LONGITUDINAL AND LATERAL STABILITY OF THE AIRCRAFT. DEATH OR SERIOUS INJURY MAY RESULT IF THE AIRCRAFT FALLS ON RECOVERY PERSONNEL. WARNING : YOU MUST MONITOR AIRCRAFT STABILITY, WEIGHT AND CG DURING THE RECOVERY PROCESS. WARNING : YOU MUST CONTACT AIRBUS BEFORE YOU MANUALLY OPERATE A SYSTEM OR REMOVE A COMPONENT WHEN THE AIRCRAFT IS IN AN ABNORMAL ATTITUDE OR DISABLED. THE AMM PROCEDURES ARE APPLICABLE ON AN AIRCRAFT IN A LEVEL CONFIGURATION ONLY. NOTE : It is important to use accurate data for the calculation related to the recovery process. Some of the necessary data is the responsibility of the operator and to be accurate, it must be applicable to the specific MSN involved. Data supplied by the manufacturer as generic data is not necessarily accurate for a specific MSN. Refer to the operator’s documentation for precise calculations. If some of the necessary data is not available or if it is not possible to get it, then it is the responsibility of the recovery manager to decide to use estimated data and to continue with the process.

03-50-01

Page 64 Jul 01/09


Subtask 03-50-01-558-014-A01 A.


03-50-01

Page 65 Jul 01/09


**ON A/C A318-100 A319-100 TASK 03-50-01-558-811-A01 Large Components Movement Effect 1.

General The CG positions of the OEW or the DOW apply to specific aircraft conditions which include the landing gear extended and the flaps and slats retracted. NOTE : The thrust reverser extension effect is negligible on the A/C CG.

2.


3.


Landing Gear Retraction Landing Gear Retraction

H-arm Moment to Subtract 204 kgm (17706 lb.in) 801 kgm (69523 lb.in)

NLG MLG

L/G Retraction Effect TABLE 1 B.

Droop Nose, Slats and Flaps Extension Effect H-arm Moments Cockpit Indication Slats / Flaps Flaps Slats 0 0.0 0.0 - 96.5 kgm 0.0 AUTOMATIC (- 8376 lb.in) - 96.5 kgm 220.0 kgm 1 (- 8376 lb.in) (19095 lb.in) - 106.0 kgm 275.5 kgm 2 (- 9200 lb.in) (23912 lb.in) - 106.0 kgm 330.5 kgm 3 (- 9200 lb.in) (28686 lb.in) - 118.1 kgm 358.1 kgm FULL (- 10251 lb.in) (31082 lb.in)

Total 0.0 - 96.5 kgm (- 8376 lb.in) 123.5 kgm (10719 lb.in) 169.5 kgm (14712 lb.in) 224.5 kgm (19486 lb.in) 240.0 kgm (20831 lb.in)

Slats and Flaps Extension Effect TABLE 2 NOTE : Add or subtract H-arm moments in accordance with the positive or negatives values.

03-50-01

Page 66 Jul 01/09


4.




5.

Procedure WARNING : MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL SURFACES AND THE LANDING GEARS AND RELATED DOORS ARE CLEAR. MOVEMENT OF THE CONTROL SURFACES AND LANDING GEARS/DOORS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO THE AIRCRAFT OR EQUIPMENT. WARNING : YOU MUST MONITOR AIRCRAFT STABILITY, WEIGHT AND CG DURING THE RECOVERY PROCESS. WARNING : YOU MUST CONTACT AIRBUS BEFORE YOU MANUALLY OPERATE A SYSTEM OR REMOVE A COMPONENT WHEN THE AIRCRAFT IS IN AN ABNORMAL ATTITUDE OR DISABLED. THE AMM PROCEDURES ARE APPLICABLE ON AN AIRCRAFT IN A LEVEL CONFIGURATION ONLY. NOTE : It is important to use accurate data for the calculation related to the recovery process. Some of the necessary data is the responsibility of the operator and to be accurate, it must be applicable to the specific MSN involved. Data supplied by the manufacturer as generic data is not necessarily accurate for a specific MSN. Refer to the operator’s documentation for precise calculations. If some of the necessary data is not available or if it is not possible to get it, then it is the responsibility of the recovery manager to decide to use estimated data and to continue with the process. Subtask 03-50-01-558-011-A01 A.

How to Find the Effect of Large Component Movement (1) To find the effect of large component movement, you must know the moments (generated by H-arm and Y-arm) depending of Aircraft Landing Gear retraction and Slats and Flaps extension. (2) To know this, see Job Setup References and record the H-arm and Y-arm moment on the Large Component Movement Effect Interim Worksheet (See DESC 09-50-01-001-A01).

03-50-01

Page 67 Jul 01/09


**ON A/C A320-100 A320-200 TASK 03-50-01-558-811-B01 Large Components Movement Effect 1.


2.


3.




NLG MLG

L/G Retraction Effect - Twin Wheel MLG TABLE 1 Landing Gear Retraction


NLG MLG

L/G Retraction Effect - Optional Four Wheel Bogie MLG TABLE 2 B.

Droop Nose, Slats and Flaps Extension Effect Cockpit Indication Slats / Flaps 0 AUTOMATIC 1 2 3

H-arm Moments Flaps

Slats 0.0 - 96.5 kgm (- 8376 lb.in) - 96.5 kgm (- 8376 lb.in) - 96.5 kgm (- 8376 lb.in) - 96.5 kgm (- 8376 lb.in)

0.0 0.0 220.0 kgm (19095 lb.in) 275.5 kgm (23912 lb.in) 330.5 kgm (28686 lb.in)

03-50-01

Total 0.0 - 96.5 kgm (- 8376 lb.in) 123.5 kgm (10719 lb.in) 179.0 kgm (15536 lb.in) 234.0 kgm (20310 lb.in)

Page 68 Jul 01/09


Cockpit Indication Slats / Flaps FULL

H-arm Moments Slats - 118.1 kgm (- 10251 lb.in)

Flaps 358.1 kgm (31081 lb.in)

Total 240.0 kgm (20831 lb.in)

Slats and Flaps Extension Effect TABLE 3 NOTE : Add or subtract H-arm moments in accordance with positive or negative values. 4.




5.

Procedure WARNING : MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL SURFACES AND THE LANDING GEARS AND RELATED DOORS ARE CLEAR. MOVEMENT OF THE CONTROL SURFACES AND LANDING GEARS/DOORS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO THE AIRCRAFT OR EQUIPMENT. WARNING : YOU MUST MONITOR AIRCRAFT STABILITY, WEIGHT AND CG DURING THE RECOVERY PROCESS. WARNING : YOU MUST CONTACT AIRBUS BEFORE YOU MANUALLY OPERATE A SYSTEM OR REMOVE A COMPONENT WHEN THE AIRCRAFT IS IN AN ABNORMAL ATTITUDE OR DISABLED. THE AMM PROCEDURES ARE APPLICABLE ON AN AIRCRAFT IN A LEVEL CONFIGURATION ONLY. NOTE : It is important to use accurate data for the calculation related to the recovery process. Some of the necessary data is the responsibility of the operator and to be accurate, it must be applicable to the specific MSN involved. Data supplied by the manufacturer as generic data is not necessarily accurate for a specific MSN. Refer to the operator’s documentation for precise calculations. If some of the necessary data is not available or if it is not possible to get it, then it is the responsibility of the recovery manager to decide to use estimated data and to continue with the process.

03-50-01

Page 69 Jul 01/09


Subtask 03-50-01-558-015-A01 A.


03-50-01

Page 70 Jul 01/09


**ON A/C A321-100 A321-200 TASK 03-50-01-558-811-C01 Large Components Movement Effect 1.


2.


3.




NLG MLG

L/G Retraction Effect TABLE 1 B.

Droop Nose, Slats and Flaps Extension Effect Cockpit Indication Slats / Flaps 0 AUTOMATIC 1 2 3 FULL

H-arm Moments Flaps

Slats 0.0 -101.8 kgm (- 8836 lb.in) -101.8 kgm (- 8836 lb.in) - 111.9 kgm (- 9712 lb.in) - 111.9 kgm (- 9712 lb.in) -124.6 kgm (-10815 lb.in)

0.0 0.0 285.0 kgm (24737 lb.in) 328.4 kgm (28504 lb.in) 377.0 kgm (32722 lb.in) 395.7 kgm (34345 lb.in)

Total 0.0 -101.8 kgm (- 8836 lb.in) 183.2 kgm (15901 lb.in) 216.5 kgm (18791 lb.in) 265.1 kgm (23009 lb.in) 271.1 kgm (23530 lb.in)

Slats and Flaps Extension Effect TABLE 2 NOTE : Add or subtract H-arm moments in accordance with positive or negative values.

03-50-01

Page 71 Jul 01/09


4.




5.

Procedure WARNING : MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL SURFACES AND THE LANDING GEARS AND RELATED DOORS ARE CLEAR. MOVEMENT OF THE CONTROL SURFACES AND LANDING GEARS/DOORS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO THE AIRCRAFT OR EQUIPMENT. WARNING : YOU MUST MONITOR AIRCRAFT STABILITY, WEIGHT AND CG DURING THE RECOVERY PROCESS. WARNING : YOU MUST CONTACT AIRBUS BEFORE YOU MANUALLY OPERATE A SYSTEM OR REMOVE A COMPONENT WHEN THE AIRCRAFT IS IN AN ABNORMAL ATTITUDE OR DISABLED. THE AMM PROCEDURES ARE APPLICABLE ON AN AIRCRAFT IN A LEVEL CONFIGURATION ONLY. NOTE : It is important to use accurate data for the calculation related to the recovery process. Some of the necessary data is the responsibility of the operator and to be accurate, it must be applicable to the specific MSN involved. Data supplied by the manufacturer as generic data is not necessarily accurate for a specific MSN. Refer to the operator’s documentation for precise calculations. If some of the necessary data is not available or if it is not possible to get it, then it is the responsibility of the recovery manager to decide to use estimated data and to continue with the process. Subtask 03-50-01-558-016-A01 A.


03-50-01

Page 72 Jul 01/09


03-60-01

REFERENCE FOR CALCULATION

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 03-60-01-001-A01 Information Required and Source Data 1.

General CAUTION :

THE NRW AND CG LOCATION CAN ONLY BE AS ACCURATE AS THE DATA USED TO CALCULATE THEM. IF ACCURATE DATA IS NOT AVAILABLE OR IF THE DATA USED ARE EXTRAPOLATIONS, THIS WILL HAVE AN EFFECT ON THE RESULTS THAT YOU GET. This section gives the details on definitions related to CG management, and the source of the required data. It also tells you how to use these data to calculate the NRW and CG location. In most cases, several sources exist to find the required data. Accurate calculations require specific data based on the specific aircraft MSN and actual airline load and trim sheet information. In case of a serious aircraft accident and subsequent freeze of the aircraft documentation, generic aircraft type data can be used. This can also apply if it is impossible to power the onboard computers. NOTE : Contact telephone numbers for the load and weight and balance office should be readily available. **ON A/C A318-100 2.

OEW (Operating Empty Weight) or DOW (Dry Operating Weight) and associated H-arm: CAUTION :

It -

IF YOU USE THE OEW GENERIC DATA TO CALCULATE THE NRW, THE CG POSITION AND THE EXPECTED LOADS, THE RESULTS YOU GET WILL NOT BE ACCURATE. is possible to take the data from these sources: Airline Load and Trim Sheet, Onboard Computers, Weight and Balance Manual, The generic OEW with an associated CG at 25 %RC is about 38818 kg (85579 lb) with CFM engines or 38661 kg (85233 lb) with PW Engines.

NOTE : The OEW or DOW and the associated H-arm are given for a specific aircraft configuration: all landing gear extended flight control retracted and thrust reversers in stored position.

03-60-01

Page 1 Jul 01/09


**ON A/C A319-100 3.


It -

IF YOU USE THE OEW GENERIC DATA TO CALCULATE THE NRW, THE CG POSITION AND THE EXPECTED LOADS, THE RESULTS YOU GET WILL NOT BE ACCURATE. is possible to take the data from these sources: Airline Load and Trim Sheet, Onboard Computers, Weight and Balance Manual, The generic OEW with an associated CG at 25 %RC is about 39725 kg (87579 lb) with CFM engines or 39826 kg (87801 lb) with IAE engines.

NOTE : The OEW or DOW and the associated H-arm are given for a specific aircraft configuration: all landing gear extended flight control retracted and thrust reversers in stored position. **ON A/C A320-100 4.


It -

IF YOU USE THE OEW GENERIC DATA TO CALCULATE THE NRW, THE CG POSITION AND THE EXPECTED LOADS, THE RESULTS YOU GET WILL NOT BE ACCURATE. is possible to take the data from these sources: Airline Load and Trim Sheet, Onboard Computers, Weight and Balance Manual, The generic OEW with an associated CG at 25 %RC. is about 41244 kg (90927 lb) with CFM engines.

NOTE : The OEW or DOW and the associated H-arm are given for a specific aircraft configuration: all landing gear extended flight control retracted and thrust reversers in stored position. **ON A/C A320-200 5.


It -


03-60-01

Page 2 Jul 01/09


NOTE : The OEW or DOW and the associated H-arm are given for a specific aircraft configuration: all landing gear extended flight control retracted and thrust reversers in stored position. **ON A/C A321-100 A321-200 6.


It -


NOTE : The OEW or DOW and the associated H-arm are given for a specific aircraft configuration: all landing gear extended flight control retracted and thrust reversers in stored position. **ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 7.

Source Data A.

Flight Crew - Weight and H-arm are specific to the operator, - Use generic data from the Weight and Balance Manual.

B.

Cabin Crew - Weight and H-arm are specific to the operator, - Use generic data from the Weight and Balance Manual.

C.

Remaining fuel (1) The means of extracting data that can be used: - Use data from the total fuel weight from load and trim sheet, - Use data from MCDU, - Do the measurements from dip sticks or do an estimation based on fuel load of 1/4, 1/2, 3/4 (See 03-20-02 and 03-20-01), - Do an estimation of the remaining fuel weight from the trim load sheet based on the operator’s known fuel consumption. (2) Find the associated H-arm and Y-arm. Theses values depend on the distribution of the fuel load. See 03-20-02 to assess the fuel quantity (dip stick, MCDU, or specific method), and associated H-arm and Y-arm.

D.

Payload This could be split in passengers and cargo:

03-60-01

Page 3 Jul 01/09


(1) Passenger Payload In most cases, the passengers will have removed carry on luggage, unless an emergency evacuation took place in which case it is necessary to take the weight of the carry on luggage into account. - Take the total passenger weight from the load and trim sheet, - H-arm: The operator should provide the H-arm relevant to its cabin sections. - H-arm should be calculated from 03-50-01. (2) Cargo Payload - Use the total cargo payload weight from the load and trim sheet, - H-arm : the operator should give the H-arm associated to cargo compartments, - H-arm : extract generic data from the Weight and Balance Manual, - Calculate H-arm see 03-50-01 - Do approximate weight and position estimations based on observation, - Ask for assistance of airline load office. E.

Weight and H-arm of any Missing or Removed Large Components - Take the weight of the removed units, - Use weights and moments listed in chapter 03-50-01, - Use details from the Weight and Balance Manual.

F.

Weight of the operator’s equipment - Use data from the Weight and Balance Manual. - H-arm calculated in chapter 03-50-01,

G.

Weight of Fluids either Removed or On Board - Use data from the Weight and Balance Manual. - H-arm calculated in 03-50-01,

H.

Weight and Location of Catering Equipment and Water Remaining On Board. Weight and H-arm depend on the aircraft configuration, the operator’s route being flown and the season of operation: - Use generic data from the Weight and Balance Manual.

J.

Change of the moment with landing gear retracted or leading edge and trailing edge surfaces extended. - See 03-50-01

03-60-01

Page 4 Jul 01/09


PREPARATION 04-00-00

PREPARATION


Tethering It is generally agreed that the aircraft must be tethered during recovery leveling and lifting operations. However, it is necessary to evaluate carefully the benefit and purpose. A.

During leveling or lifting, make sure that the aircraft is stable, and prevent uncontrolled movement of the aircraft. This movement can be caused by: - Change of CG position during aircraft lifting/leveling - Weather conditions - Terrain conditions change: humidity, temperature, soil capability.

B.

These conditions will help you decide whether to tether the aircraft or not: - Aircraft attitude - Leveling/lifting procedure used - Terrain conditions - Wind/weather condition - Increase of aircraft stability foreseen. It is necessary to do an evaluation of the tethering loads. They must be in the aircraft allowable limits. During the tethering operation, it is necessary to continuously monitor these loads.

2.

Shoring Shoring of the aircraft can also be necessary to make it stable prior to remove fuel or cargo payload or to allow a change/repositioning of the recovery tooling. For the shoring operation, it is possible to use large timbers to support or stabilize the forward or aft fuselage and/or the lower wing surfaces. These supports must be placed in the correct load bearing areas and be adequately padded to prevent damage. For example, it is possible to make fuselage supports or cradles to match the contours of the fuselage frames. Adequate padding can consist of heavy felt, rubber sheets, rubber tires, mattresses or sand bags. The same conditions as above will help you decide whether to shore the aircraft or not. The shoring loads must be evaluated, be in the aircraft allowable limits and monitored. All applied loads for allowable skin pressure and fuselage bending moment calculations must also be in the ARM limits.

3.

Lifting and Tethering Material See 09-30-01.

04-00-00

Page 1 Jul 01/09


04-20-00

STABILIZING THE AIRCRAFT

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 04-20-00-588-801-A01 Stabilizing the Aircraft 1.

General The operations that follow are necessary to stabilize the aircraft.

2.


3.


4.


Referenced Information REFERENCE TASK 02-30-01-200-801-A01 03-50-01 04-30-00 05-30-00 FIGURE 04-20-00-991-001-A FIGURE 04-20-00-991-001-B FIGURE 04-20-00-991-001-C FIGURE 04-20-00-991-001-D

DESIGNATION TASK 02-30-01-200-801-A01-Landing Gear Survey 03-50-01-MANAGING AIRCRAFT WEIGHT AND CG 04-30-00-TETHERING THE AIRCRAFT 05-30-00-MOVING FUEL FOR CG CONTROL FIGURE 04-20-00-991-001-A-Aircraft Stability FIGURE 04-20-00-991-001-B-Aircraft Stability FIGURE 04-20-00-991-001-C-Aircraft Stability FIGURE 04-20-00-991-001-D-Aircraft Stability Referenced Information TABLE 1

5.


General (1) Make sure that maximum weight has been removed to make the aircraft as light as possible. (2) Calculate the NRW and CG position (see 03-50-01). (3) You must also make sure that the wind speed is not more than the maximum allowable speed. See FIGURE 04-20-00-991-001-AFIGURE 04-20-00-991-001-BFIGURE 04-20-00-991-001-CFIGURE 04-20-00-991-001-D.

04-20-00

Page 1 Jul 01/09


(4) Monitor visually the ground contact point of the A/C (either L/G or jack) to detect any movement or attitude change during the leveling and lifting operation. If load cells are available on recovery jacks, monitor load indication shift. The monitoring of the vertical position of the shock absorber in the strut with a reference line can be also an indicator of A/C stability. (5) Select the method that you will use to control the CG during the leveling/lifting operation by addition or removal of ballast and transfer of fuel. (6) Make sure the aircraft is correctly grounded. (7) Install landing gear downlock pins in all landing gears that are extended (see TASK 02-30-01-200-801-A01). (8) Install tethers as soon as possible if the aircraft is unstable and moves in the wind (see 04-30-00). (9) Install temporary shoring timbers in relation with the tethers to help stabilize the aircraft when necessary. (10) Transfer fuel from the low wing to the opposite wing to move weight and leveling/lifting load from the low wing (see 05-30-00). It is also possible to use this procedure to reduce the loads on an engine resting on the ground. (11) The shock absorber of the low wing landing gear can be inflated while the shock absorber of the landing gear on the high wing can be deflated to help raise a low wing. (12) It is possible to operate the spoilers in strong wind conditions to help stabilize the aircraft (see TBD). (13) Put the horizontal stabilizer to a slightly nose down position. NOTE : You can do this only if power is available on the aircraft. (14) Stabilize the soil around the aircraft so that cargo loading equipment and fuel tankers can come near to the aircraft. (15) Make sure that the aircraft CG position stays at least 500 mm (20 in) forward the aircraft balance point (which is the aircraft support point: the main landing gear or the wing main jacks). NOTE : Other operations may be necessary depending on the specific recovery conditions. (16) To determine the aircraft stability refer to FIGURE 04-20-00-991-001-AFIGURE 04-20-00-991-001-BFIGURE 04-20-00-991-001-CFIGURE 04-20-00-991-001-D.

04-20-00

Page 2 Jul 01/09


65 60 Kt)

50

0 Kt)

m/h (6

111 k

35

/h (50

Kt)

15

20

93 km

km

)

55 Kt

m/h (

102 k

9

40

km

(1

5

45

Kt)

/h (65

m 120 k

Kt

55

28

NRW IN TONS

/h (70

m 130 k

83 ) 7 4 km 6 4 37 6 1 0 5 5 km (5 9 k km km (45 km km 6 k K ( m (0 t) m ( (2 (25 (3 (35 40 Kt) 10 Kt Kt 0 Kt Kt Kt 0 K ) Kt ) ) ) ) t) )

**ON A/C A318-100

30 10

25

30

35

40

45

50

CG % RC

N_AR_042000_1_0010101_01_00

Aircraft Stability Wheels on Dry Ground (Sheet 1 of 3) FIGURE-04-20-00-991-001-A01

04-20-00

Page 3 Jul 01/09


**ON A/C A318-100

)

65

)

55 Kt

m/h (

102 k

55 /h (50

93 km

50 45

Kt)

/h (45

Kt)

/h (40

Kt)

30

35

83 km

40 74 km

35 30

10

15

20

25

0

NRW IN TONS

60

9 19 2 km km km 8 k 37 46 56 65 k (0 (5 (1 m ( km km km m Kt Kt 0 K 15 (2 (2 (3 (35 ) ) t) Kt) 0 K 5 K 0 K Kt ) t) t) t)

60 Kt

m/h (

111 k

40

45

50

CG % RC

N_AR_042000_1_0010102_01_00

Aircraft Stability Wheels on Wet Ground (Sheet 2 of 3) FIGURE-04-20-00-991-001-A01

04-20-00

Page 4 Jul 01/09


**ON A/C A318-100

AIRCRAFT CG (% RC) SHIF

km

/h)

TING

15

Kt

(28

65

60

/h) km (19 /h)

10

Kt

50

0K

t (0

km

45

t (9

km

/h)

40

35

5K

NRW IN TONS

55

30 10

15

20

25

30

35

40

45

50

CG (% RC)

N_AR_042000_1_0010103_01_00

Aircraft Stability Wheels on Ice Ground (Sheet 3 of 3) FIGURE-04-20-00-991-001-A01

04-20-00

Page 5 Jul 01/09


**ON A/C A319-100

75 SHIF m/h (

W

)

75 Kt

IN

/h

km

74 )

(5

55 Kt

m/h (

9

102 k

/h

40

56 (4 /h 0 k 37 46 m/h (35 Kt) Kt 28 k km ( Kt ) ) km m/ /h 30 19 /h h (2 (2 Kt) 5 0 0 ( km 15 K K km /h K t) t) /h (1 t) (0 0 Kt Kt ) )

5 (4

km

km

83

0 Kt)

m/h (6

111 k

km

45

)

65 Kt

m/h (

120 k

D

65

50

130 k

/h

/h

t)

70 K m/h (

SP

EE

)

Kt 0 (5

60 55

D

)

m/h (

139 k

93

NRW IN TONS

65

Kt

148 k

TING

km

70

80 Kt)

TI PP IN G

80

35 8 10 12 14 16 1820 22 24 26 28 30 32 34 36 38 40 42 44 46 48 50

CG %RC

N_AR_042000_1_0010201_01_00

Aircraft Stability Wheels on Dry Ground (Sheet 1 of 3) FIGURE-04-20-00-991-001-B01

04-20-00

Page 6 Jul 01/09


**ON A/C A319-100

75 )

65 Kt

m/h (

/h (60

W

IN

D

EE

Kt)

(55 2 km/h

D

10

50

40

93 km

Kt)

/h (45

83 km

56

/h (50

45

SP

km

55

Kt)

74

60

m 111 k

65

NRW IN TONS

65

/h (4 /h k 46 m (3 0 K 9 t) / 5 h 37 km ( km Kt ) /h 28 km /h 30 (5 km /h (25 Kt ) /h (2 Kt ) (1 0 K Kt) 5 0 Kt t) km ) /h 19 (0 km Kt /h ) (1 0 Kt )

120 k

TING

km

70

SHIF

TI PP IN G

80

Kt)

35 8 10 12 14 16 1820 22 24 26 28 30 32 34 36 38 40 42 44 46 48 50

CG % RC

N_AR_042000_1_0010202_01_00

Aircraft Stability Wheels on Wet Ground (Sheet 2 of 3) FIGURE-04-20-00-991-001-B01

04-20-00

Page 7 Jul 01/09


**ON A/C A319-100

20 K t

AIRCRAFT CG (% RC) 80

(37 k m/h)

75

/h)

70

km

SHIF

(28

TING

60

/h)

t (0

/h)

45

0K

10

Kt

(19

50

km

km

/h)

55

t (9

km

40 5K

NRW IN TONS

15

Kt

65

35 10

15

20

25

30

35

40

45

50

AIRCRAFT CG (% RC)

N_AR_042000_1_0010203_01_00

Aircraft Stability Wheels on Ice Ground (Sheet 3 of 3) FIGURE-04-20-00-991-001-B01

04-20-00

Page 8 Jul 01/09


**ON A/C A320-100 A320-200

IN

G

80

TI

PP

75 70

W

IN

D

t)

65 K m/h (

40

km

/h

(4 5 k Kt 0 46 56 m/h ) K k 37 km m t ( ) 3 / h 5 km /h ( Kt /h (25 30 ) (2 K Kt) 0 t) Kt )

45

65

74

50

)

60 Kt

m/h (

)

55 Kt

m/h (

102 k

/h (50

93 km

D

(4

55 111 k

SP

EE

120 k

/h

SH

km

60

G IFTIN

83

NRW IN TONS

)

70 Kt

m/h (

130 k

65

/h (45

83 km

Kt)

Kt)

35 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44 46 48 50

CG (% RC)

N_AR_042000_1_0010301_01_00

Aircraft Stability Wheels on Dry Ground (Sheet 1 of 3) FIGURE-04-20-00-991-001-C01

04-20-00

Page 9 Jul 01/09


**ON A/C A320-100 A320-200

75

SHIF

TING /h (55

m 102 k

Kt)

W

IN

D

50

/h (45

83 km

km /h 37 46 km/ (3 km km h ( 5 K 3 / t) /h h ( 0 (2 25 Kt) 0 K Kt t) )

93

D

Kt)

(50 km/h

Kt)

65

55

45 40

SP

EE

60

56

NRW IN TONS

65

)

60 Kt

m/h (

111 k

70

TI PP IN G

80

/h (40

74 km

Kt)

/h (35

65 km

Kt)

35 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44 46 48 50

CG (% RC)

N_AR_042000_1_0010302_01_00

Aircraft Stability Wheels on Wet Ground (Sheet 2 of 3) FIGURE-04-20-00-991-001-C01

04-20-00

Page 10 Jul 01/09


**ON A/C A320-100 A320-200

80

75

70 SHIFT

ING

60

t (19

10 K

)

km/h

t (9

50

km

/h)

55

5K

NRW IN TONS

65

)

m/h

28 k

t( 15 K

45

40

35 10

15

20

25

30

35

40

45

50

CG (% RC)

N_AR_042000_1_0010303_01_00

Aircraft Stability Wheels on Ice Ground (Sheet 3 of 3) FIGURE-04-20-00-991-001-C01

04-20-00

Page 11 Jul 01/09


**ON A/C A321-100 A321-200

TI PP IN G

80 75 70

W

TING

SP

km / km h (4 65 5 /h Kt (4 56 km ) 0 / Kt 46 km h ( ) 3 / km h 5 /h (30 Kt) 37 ( K 25 t km Kt ) /h ) (2 0 Kt )

55

EE

) 60 Kt m/h ( 111 k

50

)

55 Kt

m/h (

102 k

D

83

120

(6 km/h

D

5 Kt)

74

NRW IN TONS

60

IN

SHIF

65

45 /h (50

40

93 km

Kt)

Kt) /h (40 74 km

35 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44 46 48 50

CG % RC

N_AR_042000_1_0010401_01_00

Aircraft Stability Wheels on Dry Ground (Sheet 1 of 3) FIGURE-04-20-00-991-001-D01

04-20-00

Page 12 Jul 01/09


**ON A/C A321-100 A321-200

75

m 102 k 70

/h (55

TI PP IN G

80

Kt)

TING

SHIF

/h (50

Kt)

/h (45

Kt)

93 km

W

60

D

IN km km /h km /h (30 /h (25 Kt) (2 0 Kt) Kt )

D

83 km

EE

55

SP

50 /h (40

Kt)

37

74 km

56

45

46

NRW IN TONS

65

40

/h (35

65 km

m/h

56 k

Kt)

t)

(30 K

35 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44 46 48 50

CG % RC

N_AR_042000_1_0010402_01_00

Aircraft Stability Wheels on Wet Ground (Sheet 2 of 3) FIGURE-04-20-00-991-001-D01

04-20-00

Page 13 Jul 01/09


**ON A/C A321-100 A321-200

AIRCRAFT CG (% RC)

80

75 15

28 Kt (

h)

km/

70 SHIFTIN

G

60

5K

45

km

t (9

50

/h)

km

/h)

/h) 9 km t (1 K 10

t (0

55

0K

NRW IN TONS

65

40

35 10

15

20

25

30

35

40

45

50

CG (% RC)

N_AR_042000_1_0010403_01_00

Aircraft Stability Wheels on Ice Ground (Sheet 3 of 3) FIGURE-04-20-00-991-001-D01

04-20-00

Page 14 Jul 01/09


04-30-00

TETHERING THE AIRCRAFT


Tethering the aircraft CAUTION :

YOU MUST NOT USE THE SAME FITTING TO TETHER THE AIRCRAFT AND TO LIFT IT AT THE SAME TIME.IF YOU USE THE SAME FITTING, THERE IS A RISK THAT THE LOADS APPLIED WILL BE MORE THAN THE ALLOWABLE LOADS. THIS CAN CAUSE DAMAGE TO THE STRUCTURE.

CAUTION :

YOU MUST INSTALL TENSIONING DEVICES AND A SCALE OR A DYNAMOMETER ON EACH TETHERING LINE. USE THE TENSIONING DEVICES TO ADJUST THE LENGTH OF THE LINE AND KEEP A POSITIVE LOAD. DURING THE LEVELING AND LIFTING PROCESS, YOU MUST MONITOR AND ADJUST THE TENSIONING DEVICES TO MAKE SURE THAT THE LOADS APPLIED ARE NOT MORE THAN THE MAXIMUM LOADS.

NOTE : The information or principle contained in this chapter are given as a guide to assist an aircraft recovery. During the lifting operations of a damaged aircraft with cranes, jacks and/or pneumatic lifting bags, you should tether the aircraft to prevent horizontal movement due to lifting side force (weight of the aircraft, wind force, etc...). You can attach the tether to fabric straps installed around the fuselage or the engine pylons or to different fittings such as pylon hoist fittings, fuselage fittings and vertical stabilizer fittings. To make sure that the horizontal stability is satisfactory, it is necessary to safely attach the aircraft tethering cables to heavy vehicles or to a deadman anchors tightly attached to the ground. The tethers should make different angles with the fuselage centerline to prevent aircraft movement in all the directions. A tensioning device should be provided for each tethering line so that tension is satisfactory at each tether during the lifting operation. The number of tethers changes with the type of recovery operation and is related to the strength and direction of the wind. See FIGURE 04-30-00-991-001-A for wind loads applied on the aircraft on ground. **ON A/C A318-100 A319-100 2.

Tethering Using the Mooring Fittings Mooring fittings can be installed on the fuselage. See FIGURE 04-30-00-991-002-AFIGURE 04-30-00-991-002-B for the location of the Mooring fittings. At each position, remove the blanking screws and the remaining sealant before you install the mooring fitting.

04-30-00

Page 1 Jul 01/09


Tethering Position FR8 LH FR8 RH FR15 LH FR15 RH FR21 LH FR21 RH FR 30 LH FR 30 RH FR 62/63 LH FR 62/63 RH

98D07203000 98D07203000 98D07203000 98D07203000 98D07203000 98D07203000 98D07203000 98D07203000 98D07203000 98D07203000

MOORING MOORING MOORING MOORING MOORING MOORING MOORING MOORING MOORING MOORING

Fitting P/N - Item FITTING - 040 FITTING - 041 FITTING - 042 FITTING - 043 FITTING - 044 FITTING - 045 FITTING - 046 FITTING - 047 FITTING - 048 FITTING - 050

Mooring Fitting Positions TABLE 1 **ON A/C A320-100 A320-200 A321-100 A321-200 3.

Tethering Using the Mooring Fittings Mooring fittings can be installed on the fuselage. See FIGURE 04-30-00-991-002-CFIGURE 04-30-00-991-002-D for the location of the Mooring fittings. At each position, remove the blanking screws and the remaining sealant before you install the mooring fitting. Tethering Position FR8 LH FR8 RH FR15 LH FR15 RH FR21 LH FR21 RH FR 33 LH FR 33 RH FR 62/63 LH FR 62/63 RH

98D07203000 98D07203000 98D07203000 98D07203000 98D07203000 98D07203000 98D07203000 98D07203000 98D07203000 98D07203000

MOORING MOORING MOORING MOORING MOORING MOORING MOORING MOORING MOORING MOORING

Fitting P/N - Item FITTING - 040 FITTING - 041 FITTING - 042 FITTING - 043 FITTING - 044 FITTING - 045 FITTING - 046 FITTING - 047 FITTING - 048 FITTING - 050

Mooring Fittings Positions TABLE 2 **ON A/C A318-100 A319-100 4.

Tethering Using Straps or Cables You can install straps or cables around the engine pylons and the fuselage main frames: FR15, 30 and 62, 63.

04-30-00

Page 2 Jul 01/09


You must install a protection (plywood sheet covered with thick padding) between these straps or cables and the fuselage and engine pylons. You can attach the tethers, tightly connected to the ground, to these straps or cables. **ON A/C A320-100 A320-200 A321-100 A321-200 5.

Tethering Using Straps or Cables You can install straps or cables around the engine pylons and the fuselage main frames: FR15, 32, 33 and 62,63. You must install a protection (plywood sheet covered with thick padding) between these straps or cables and the fuselage and engine pylons. You can attach the tethers, tightly connected to the ground, to these straps or cables.

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 6.

Tether Lines Installation The tethering load distribution must be symmetric around the fuselage. For this purpose, you must install the tethering lines on each side of the fuselage. Chapter 04-40-00 gives details on the ground anchors that you can use for tethering the aircraft. FIGURE 04-30-00-991-003-A gives an example of tethering line installation.

04-30-00

Page 3 Jul 01/09

04-30-00

CASE 3 45° STRIKE

CASE 1: WILL CAUSE NOSE TO RISE (My) CASE 2: WILL CAUSE AIRCRAFT TO ROLL AND YAW (Mx + Mz) CASE 3: WILL CAUSE AIRCRAFT TO ROLL, YAW AND PITCH (Mx + Mz + My)

CASE 1 FRONTAL STRIKE

Mx

Fy

Mz

Fz

Fx

My

N_AR_043000_1_0010101_01_00

CASE 2 SIDE STRIKE


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

Tethering Ground Wind Loads FIGURE-04-30-00-991-001-A01

Page 4 Jul 01/09


**ON A/C A318-100

FR15

FR21

B

C

FR62 FR63

FR30

FR8

A

D

E

7 HOLES

4 HOLES

4 HOLES

B

A

C

4 HOLES

4 HOLES

E D N_AR_043000_1_0020101_01_00

Tethering Location of the Mooring Fittings FIGURE-04-30-00-991-002-A01

04-30-00

Page 5 Jul 01/09


**ON A/C A319-100

FR15

FR21

FR30

FR62 FR63

D

E

FR8

A

B

C

7 HOLES

4 HOLES

4 HOLES

B

A

C

4 HOLES

4 HOLES

E D N_AR_043000_1_0020201_01_00

Tethering Location of the Mooring Fittings FIGURE-04-30-00-991-002-B01

04-30-00

Page 6 Jul 01/09


**ON A/C A320-100 A320-200

FR15

FR21

FR33

FR62 FR63

D

E

FR8

A

B

C

7 HOLES

4 HOLES

4 HOLES

B

A

C

4 HOLES

4 HOLES

E D N_AR_043000_1_0020301_01_00

Tethering Location of the Mooring Fittings FIGURE-04-30-00-991-002-C01

04-30-00

Page 7 Jul 01/09


**ON A/C A321-100 A321-200

FR15 FR8

A

FR21

C

B

FR33

FR62 FR63

D

E

7 HOLES

4 HOLES

4 HOLES

B

A

C

4 HOLES

4 HOLES

E D N_AR_043000_1_0020401_01_00

Tethering Location of the Mooring Fittings FIGURE-04-30-00-991-002-D01

04-30-00

Page 8 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_043000_1_0030101_01_00

Tethering Typical Tethering Lines Installation FIGURE-04-30-00-991-003-A01

04-30-00

Page 9 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 04-30-00-556-801-A01 Mooring 1.

General During the recovery operation, you can moor the aircraft to help the tethering.

2.

Inspections Make sure that there is no damage on the landing gears.

3.


4.

Preparation Make sure that the landing gear safety devices are in position (see TASK 02-30-01-200-801A01). Install the wheel chocks in front and behind the wheels.


Fixtures, Tools, Test and Support REFERENCE 98D10203500

DESIGNATION MOORING KIT - NLG Fixtures, Tools, Test and Support TABLE 1

B.

Referenced Information REFERENCE TASK 02-30-01-200-801-A01 04-40-00 FIGURE 04-30-00-991-004-A

DESIGNATION TASK 02-30-01-200-801-A01-Landing Gear Survey 04-40-00-GROUND ANCHORS FIGURE 04-30-00-991-004-A-Mooring on the Nose Landing Gear Referenced Information TABLE 2

5.


Mooring of the Nose Landing Gear (1) With the mooring kit (a) Put the 98D10203500 MOORING KIT - NLG in position. See FIGURE 04-30-00-991-004-A. See 04-40-00 for details on the ground anchors.

04-30-00

Page 10 Jul 01/09


(2) With ropes (a) Attach the ropes (3) and (4) of a diameter of 50.8 mm (2.0 in) on the towing lug and the debogging lug of the nose landing gear. NOTE : If manila or sisal rope is used, make sure that there is not too much tension on the rope because contraction can occur in wet weather. (b) Attach the other ropes (2) of a diameter of 50.8 mm (2.0 in). (c) Attach all the ropes on the ground with the mooring points. Put tension on this assembly. Subtask 04-30-00-556-002-A01 B.

Mooring on the Main Landing Gears with Ropes (1) Attach the ropes (3) and (4) of a diameter of 50.8 mm (2.0 in) on the towing lug and the debogging lug of the main landing gear. NOTE : If manila or sisal rope is used, make sure that there is not too much tension on the rope because contraction can occur in wet weather. (2) Attach the ropes on the ground with the mooring points. Put tension on this assembly.

04-30-00

Page 11 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TOWING FITTING

TOWING FITTING

B

A GROUND ANCHOR

A

FWD

B N_AR_043000_1_0040101_01_00

Mooring on the Nose Landing Gear NLG Mooring Kit FIGURE-04-30-00-991-004-A01

04-30-00

Page 12 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

TOWING FITTING

2

1

GROUND ANCHOR

A

N_AR_043000_1_0050101_01_00

Mooring on the Nose Landing Gear Installation of the Mooring Ropes FIGURE-04-30-00-991-005-A01

04-30-00

Page 13 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

DEBOGGING LUG

TOWING LUG

4 3

FWD

A N_AR_043000_1_0060101_01_00

Mooring on the Main Landing Gear Installation of the Mooring Ropes FIGURE-04-30-00-991-006-A01

04-30-00

Page 14 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

SHORT ROPE FWD OF NOSE LANDING GEAR

45°

TYPICAL ALL POSITIONS

N_AR_043000_1_0070101_01_00

Mooring Position of the Mooring Ropes FIGURE-04-30-00-991-007-A01

04-30-00

Page 15 Jul 01/09


04-40-00

GROUND ANCHORS


Ground Anchors for Tethers NOTE : The information or principle contained in this chapter are given as a guide to assist an aircraft recovery. There are three basic ways of supplying anchors for the tether lines: - Commercial type ground anchors, - Dead-man anchors, - Heavy vehicles.

2.

A.

Commercial Type Ground Anchors There are several types of commercially manufactured ground anchors on the market. Before installation of any type of ground anchor the manufacturer’s instructions must be reviewed and the stability of the soil must be analyzed. Different sizes of these anchors are available to cater for the various loads. Most anchor units must be hammered or turned to a necessary depth depending on the stability of the soil. Generally longer models are required for loose soils and shorter ones for harder soils.

B.

Dead-Man Anchors Dead-man anchors are those constructed on the site from available materials such as vehicle wheels complete with tires, heavy cribbing timbers or railroad ties. A hole is excavated to an adequate depth and the materials are buried after being attached to cables. The hole is then back-filled with the cables forming an angle of approximate of 30 degrees between the wheel or timber and the ground. Use of this type of anchors requires a good experience of their use to ensure adequate strength.

C.

Heavy Vehicles It is possible to use large and/or heavy vehicles, if there is an adequate supply. Once the vehicle is used as anchor, it cannot be used for its original purpose during the recovery operation.

Anchor Holding Capacity A.

Anchor holding capacity is dependent on the type of soil and the depth of the anchor.

B.

The holding capacity of the anchor will decrease as the moisture content of the soil increases.

C.

It is necessary to test the soil stability: - Evaluate the type of anchoring method, - Determine the holding capacity of a given anchor in various soil types.

D.

The soil stability can be tested in the field using a number of portable soil test probes.

04-40-00

Page 1 Jul 01/09


04-50-00

SOIL STABILITY


Soil stability is of prime importance to ensure personnel safety, avoidance of secondary damage, selection of ground corrective action or of tooling to be used to allow implementation of the recovery procedure. NOTE : The information or principle contained in this chapter are given as a guide to assist an aircraft recovery. Basically you must make sure that ground remains stable for the intended purpose and keep in mind that load bearing capacity of soil might change with weather conditions.

04-50-00

Page 1 Jul 01/09


WEIGHT REDUCTION 05-00-00

WEIGHT REDUCTION


You must control aircraft weight. WARNING : PUT SAFETY DEVICES ON THE CARGO DOOR OPENING MECHANISM TO PREVENT UNWANTED CLOSURE OF THE DOOR. WARNING : YOU MUST CONTROL ALL MOVEMENT OF THE PAYLOAD DURING REMOVAL TO PREVENT TAIL TIPPING. WARNING : YOU MUST CONTROL MOVEMENT AND SPEED OF CONTAINERS AND PALLETS TO PREVENT RAPID MOVEMENT OF PAYLOAD BECAUSE OF AIRCRAFT ATTITUDE. WARNING : YOU MUST MONITOR CHANGE TO CG AND AIRCRAFT ATTITUDE DURING REMOVAL OF PAYLOAD. Aircraft weight change will affect CG, aircraft stability and expected loads. It is commonly accepted that NRW should be the minimum possible, which implies removal of maximum weight. Make sure that actions taken to reduce weight have an efficient effect. Make sure that you get the expected results. You can get maximum weight reduction if you remove weight from: - Fuel tanks - Cargo compartments. NOTE : For disposition and locations of containers and pallets in the cargo compartments, see 09-10-14. Sometimes, it is not necessary to remove the cargo payload or fuel. This depends on main factors such as: - CG control - Weight and amount of the cargo payload on board - Need to excavate and build roadways for access - Need to stabilize the ground so that cargo loaders and fuel trucks can go near the aircraft - Expected removal: defueling time versus the time requirements to move the aircraft - Capacity of the available lifting means - Expected leveling/lifting loads - Structural limitations on allowable leveling/lifting loads - On-site storage capability of removed fuel. Fuel and cargo payload can also remain on the aircraft to be used as ballast.

05-00-00

Page 1 Jul 01/09


NOTE : Always be prepared for sudden attitude changes of the aircraft as the payload or fuel, etc. is removed. The changes can affect both the longitudinal and lateral axes of the aircraft. For Fuel Weight Reduction see 05-10-00. For Cargo Weight Reduction see 05-50-00.

05-00-00

Page 2 Jul 01/09


05-10-00

DEFUELING


Defueling Defueling is one of the most important tasks to be carried out during an aircraft recovery operation. The importance relates not only to weight reduction, but also to control of the Center of Gravity (CG). The total mass of fuel on board the aircraft can be many tons. When the aircraft is in an abnormal attitude a significant shift in CG can take place as the aircraft is returned to a normal attitude. The procedures chosen to defuel a disabled aircraft should be made only after a thorough investigation has been carried out to determine: - The aircraft attitude - The extent of damage to the structure and the functional status of the fuel and electrical systems. The ability to energize the aircraft electrical power system through an external ground power source (or the aircraft batteries) will reduce the total time required for the defuel process. The lack of electrical power due to an inoperative electrical system, is the most common problem associated with the defuel process. The defuel system uses the same valves and fuel lines as the refuel system and components of the engine feed and transfer systems. The aircraft can be defueled through one or more of the four hose adapter couplings at the wing leading edges. The quantity of fuel removed will vary considerably dependant on the aircraft attitude and the method used to defuel. Sufficient storage for the removed fuel must be available. This is a very important issue specially when large amounts of fuel are involved. If the aircraft was involved in an incident where fuel contamination is suspected, it is necessary to quarantine the removed fuel. Only when the applicable authorities have made sure that this fuel is safe to use can it be used according to company and state regulations. Remove as much fuel as is possible prior to lifting the aircraft. Large quantities of fuel can be trapped in the tanks due to abnormal aircraft attitudes. It is possible that this fuel cannot be removed until the aircraft is level. When one main landing gear has collapsed (or is deeply bogged in mud) the transfer of fuel from the low wing to the opposite wing will reduce the weight of the low wing. This weight reduction will shift the CG of the opposite wing outboard from the main landing gear. This transfer process is only available when the fuel system is intact and power can be supplied to the fuel pumps and valves. The defuel process may have to be carried out in several steps, as the aircraft is levelled and stabilized several times.

05-10-00

Page 1 Jul 01/09


Although the removal of the fuel is important, not all recovery operations will require its removal. Where relatively small quantities of fuel remain, it is not necessary to remove it. This decision can only be made once the survey has been completed. Decisions can also be made to reduce weight only to the point where maximum lifting and jacking loads will not be exceeded. This is not a recommended procedure and should be evaluated thoroughly. 2.

General Preparation WARNING : MAKE SURE THAT YOU OBEY ALL THE APPLICABLE SAFETY PRECAUTIONS WHEN YOU REMOVE FUEL OR WHEN YOU WORK IN AN ENVIRONMENT WHERE THERE IS FUEL. WARNING : DO NOT SPILL FUEL ON THE ENGINES OR THE BRAKES. IF YOU SPILL FUEL ON ENGINES OR BRAKES THAT ARE HOT, IT CAN CAUSES FIRE. Before you start the defuel, you must make sure that: A.

You obey all the safety precautions applicable to refuelling/defuelling.

B.

The safety area is clearly identified and the tankers are in correct position, see FIGURE 05-10-00-991-004-A.

C.

The aircraft is correctly grounded, see 09-10-13.

D.

A ground cable connects the tanker to the MLG ground connection.

E.

There are no open flames or smoking in the safety area.

F.

Only personnel qualified to do the defuel operation are in the safety area.

G.

All the equipment and material not necessary for the defuel procedure are moved out of the safety area.

H.

The correct safety and fire fighting equipment is in position with the qualified personnel to operate it.

J.

The escape lanes for the fuel tankers are clear of obstruction.

K.

The fuel tankers have sufficient capacity for the quantity to be defueled.

L.

Only the electrical equipment necessary for the defuel procedure is used.

M. You do not operate the aircraft main engines or the APU during the defuel procedure. N.

The electrical equipment you use will not create a spark.

P.

Caps are installed on all damaged fuel pipes.

Q.

All damaged electrical wiring and fuel pumps are isolated.

R.

You only use pumps that are serviceable.

S.

Do not do the defuel procedure in bad weather conditions. Lightning is dangerous.

T.

Do not operate radio, radar equipment or mobile phone during the defuel procedure.

U.

Immediately remove all fuel spillage in accordance with local procedures.

05-10-00

Page 2 Jul 01/09


V.

You have stopped all fuel leaks.

W. Trained personnel are available to contain all fuel spills. X.

If necessary put a GPU in position as far as practicable from the A/C. The GPU must have 3 phases, with 115 Volts AC, 400 Hz and 20 KVA.

05-10-00

Page 3 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

NOTE: THIS AREA MUST BE KEPT CLEAR TO LET THE TANKER MOVE AWAY IN AN EMERGENCY

NOTE: THIS AREA MUST BE KEPT CLEAR TO LET THE TANKER MOVE AWAY IN AN EMERGENCY

15 (49)

15 (49)

15 (49)

N TA

KE

TA

R

NK

ER

7 (23)

7 (23)

15 (49)

SAFETY AREA

15 (49)

15 (49)

15 (49)

15 (49)

NOTE: ALL SAFETY ZONE CLEARANCES ARE SUBJECT TO CHANGE ACCORDING TO LOCAL OR AIRPORT REGULATIONS

NOTE: DIMENSIONS IN METERS (FEET IN BRACKETS)

N_AR_051000_1_0040101_01_00

Defuelling Safety Area FIGURE-05-10-00-991-004-A01

05-10-00

Page 4 Jul 01/09


05-20-00

FUEL SYSTEM DESCRIPTION

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 05-20-00-001-A01 Fuel System Basic Description 1.

Basic Description The fuel system: - controls and supplies fuel in the correct quantities to the fuel tanks during refuel operations, - supplies fuel to the engines via the engine feed tanks during flight, - supplies fuel to the Auxiliary Power Unit (APU), - gives indications in the cockpit of system operation, - gives indications in the cockpit of a malfunction in the system that could cause an unusual condition, - controls defuel and fuel ground transfers. See DESC 09-10-12-004-A01 for the ground service connections (refuel/defuel coupling and refuel/defuel control panel).

05-20-00

Page 1 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 05-20-00-002-A01 Tanks **ON A/C A318-100 A319-100 A320-100 A320-200 1.

The A318/A319/A320 has the following fuel tanks: Capacity

Tank liters Outer Wing Tank LH Outer Wing Tank RH Inner Wing Tank LH Inner Wing Tank RH Centre Tank Total fuel capacity

880 880 6924 6924 8250 23859

US Gallons 232 232 1829 1829 2179 6303

Tank Capacities TABLE 1 NOTE : On A319 and A320, Additional Centre Tanks (ACT) can be installed with a capacity of 2992 l (790 US gal) per tank. **ON A/C A321-100 A321-200 2.

The A321 has the following fuel tanks: Capacity

Tank liters Wing Tank LH Wing Tank RH Centre Tank Total fuel capacity

7750 7750 8200 23700

US Gallons 2047 2047 2166 6261

Tank Capacities TABLE 2 NOTE : On A321, Additional Centre Tanks (ACT) can be installed with a capacity of 2900 l (766 US gal) per tank.

05-20-00

Page 2 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 3.

Each tank has one or more water drain valves. These are used to: - drain the water, which could possibly come out of the fuel in the tank - drain the fuel that remains after a defuel procedure has been completed (for maintenance).

4.

All of the fuel tanks are fueled/defueled through a standard 2.5 inch fuel coupling, located in the right wing leading edge.

5.

Each wing tank is vented through the vent/surge tanks.

6.

The system uses the fuel transfer-pump to move the fuel.

7.

The FQIC (Fuel Quantity Indication Computer) automatically controls the system, but if necessary, the system can be manually controlled in the cockpit.

8.

The fuel is delivered to the engines by booster pumps (2 per tank).

05-20-00

Page 3 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200

CENTER TANK

OUTER TANK

OUTER TANK

VENT/SURGE TANK VENT/SURGE TANK

INNER TANK

INNER TANK

N_AR_052000_1_0130101_01_00

Fuel System Fuel Tank General Arrangement FIGURE-05-20-00-991-013-A01

05-20-00

Page 4 Jul 01/09


**ON A/C A321-100 A321-200

CENTER TANK

WING TANK

WING TANK

VENT/SURGE TANK

VENT/SURGE TANK

N_AR_052000_1_0130201_01_00

Fuel System Fuel Tank General Arrangement FIGURE-05-20-00-991-013-B01

05-20-00

Page 5 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200

CL CENTER TANK FUEL PUMP

CENTER TANK FUEL PUMP STRAINER

STRAINER

CENTER TANK

APU LP VALVE

CENTER TANK FUEL PUMP PRESSURE SWITCH

APU FUEL PUMP PRESSURE SWITCH

APU FUEL PUMP

DEFUEL TRANSFER VALVE CROSSFEED VALVE

CENTER TANK FUEL PUMP PRESSURE REFUEL SWITCH VALVE

N_AR_052000_1_0010101_01_00

Fuel System Schematic Centre Tank FIGURE-05-20-00-991-001-A01

05-20-00

Page 6 Jul 01/09


**ON A/C A321-100 A321-200

CL RIB1

JET PUMP

CONTROL VALVE

CENTER TRANSFER TANK

DIFFUSER

REFUEL VALVE

APU LP VALVE APU FUEL PUMP PRESSURE SWITCH

APU FUEL PUMP

CROSSFEED VALVE

DEFUEL TRANSFER VALVE

N_AR_052000_1_0010201_01_00

Fuel System Schematic Centre Tank FIGURE-05-20-00-991-001-B01

05-20-00

Page 7 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 LEGEND VALVE ACTUATOR (SINGLE MOTOR)

SOLENOID OPERATED VALVE CLACK VALVE (

VALVE ACTUATOR (TWIN MOTOR)

DIRECTION OF FLOW)

OVERPRESSURE PROTECTOR

FLOAT VALVE

MAGNETIC FUEL LEVEL INDICATOR (MLI)

VENT SYSTEM FUEL DRAIN VALVE

PRESSURE RELIEF VALVE

WATER DRAIN VALVE FUEL QUANTITY INDICATOR PROBE

CHECK VALVE (

TEMPERATURE SENSOR

JET PUMP

HIGH LEVEL SENSOR

DIFFUSER

DIRECTION OF FLOW) STRAINER SEQUENCE VALVES

LOW LEVEL SENSOR MAIN FUEL PUMPS

CADENSICON SENSOR

RIB2 CENTER TANK VENT PIPE

ENGINE CL

FUEL SUPPLY PIPE LP VALVE SUCTION VALVE

AIR RELEASE VALVE

RIB1

RIB4

FUEL DRAIN VALVE STRAINER MAIN FUEL PUMP PRESSURE SWITCH

RIB6 RIB8 RIB11

RIB9

REFUEL GALLERY N_AR_052000_1_0020101_01_00

Fuel System Schematic Inner and Outer Wing Tanks (Sheet 1 of 2) FIGURE-05-20-00-991-002-A01

05-20-00

Page 8 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 RIB14 RIB15 RIB16 RIB17

WING TANK VENT DUCT

FROM THE MAIN FUEL PUMPS

REFUEL/DEFUEL COUPLING R/H STANDARD L/H OPTIONAL

FROM THE SURGE TANK

REFUEL VALVE

RIB11

RIB14

AIR INLET VALVE

RIB16

OVERWING REFUEL ADAPTOR

WING TANK NACA VENT INTAKE FUEL VENT PROTECTOR

RIB13 WING TANK VENT DUCT

RIB15

RECIRCULATION PIPE


RIB27

RIB25

RIB23

REFUEL SPILL PIPE

PRESSURE HOLDING VALVE

INNER TANK OUTER TANK

N_AR_052000_1_0020102_01_00

Fuel System Schematic Inner and Outer Wing Tanks (Sheet 2 of 2) FIGURE-05-20-00-991-002-A01

05-20-00

Page 9 Jul 01/09


**ON A/C A321-100 A321-200 LEGEND SOLENOID OPERATED VALVE

VALVE ACTUATOR (SINGLE MOTOR)

CLACK VALVE ( VALVE ACTUATOR (TWIN MOTOR)

DIRECTION OF FLOW)

OVERPRESSURE PROTECTOR

FLOAT VALVE MAGNETIC FUEL LEVEL INDICATOR (MLI)

VENT SYSTEM FUEL DRAIN VALVE

T

WATER DRAIN VALVE

PRESSURE RELIEF VALVE

FUEL QUANTITY INDICATOR PROBE

CHECK VALVE (

TEMPERATURE SENSOR

JET PUMP

HIGH LEVEL SENSOR

DIFFUSER

DIRECTION OF FLOW)

DIFFUSER

LOW LEVEL SENSOR REFUEL/DEFUEL COUPLING R/H STANDARD L/H OPTIONAL

DUALCOMP ULTRACOMP

RIB11

SENSOR RIB14 REFUEL VALVE AIR INLET VALVE

RIB16 WING TANK

OVERWING REFUEL ADAPTOR CLACK VALVE NACA VENT INTAKE

RIB23 RIB13 RECIRCULATION PIPE RIB17 RIB19

WING TANK VENT DUCT RIB15


PRESSURE HOLDING VALVE AIR INLET PIPE

FUEL VENT PROTECTOR N_AR_052000_1_0020201_01_00

Fuel System Schematic Wing Tanks (Sheet 1 of 2) FIGURE-05-20-00-991-002-B01

05-20-00

Page 10 Jul 01/09


**ON A/C A321-100 A321-200

STRAINER MAIN FUEL PUMPS

RIB2 CENTER TANK VENT PIPE ENGINE CL FUEL SUPPLY PIPE

CHECK VALVE

LP VALVE

SUCTION VALVE

AIR RELEASE VALVE

T

RIB1 STRAINER

FUEL DRAIN VALVE

RIB4 MAIN FUEL PUMP PRESSURE SWITCH

RIB6 RIB8 RIB9

REFUEL GALLERY

RIB11

N_AR_052000_1_0020202_01_00

Fuel System Schematic Wing Tanks (Sheet 2 of 2) FIGURE-05-20-00-991-002-B01

05-20-00

Page 11 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 05-20-00-004-A01 Fuel Quantity Indicating System 1.

The Fuel Quantity Indicating (FQI) system measures the total quantity of fuel in the fuel tanks. It gives indications for these areas: - The LH and RH wing tanks, For A318, A319 and A320, it gives indications for the inner and outer tank. - The center tank, - The ACT, if installed - Fuel on board (FOB).

2.

The Magnetic Level Indicator (MLI) provides a secondary method to measure the fuel quantity. See TASK 03-20-02-970-801-A01.

05-20-00

Page 12 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 B F.USED 1 3100

KG

FUEL

F.USED 2 3100

FOB 14360

APU

A LEFT

CTR

RIGHT

C 750 −11

5030

5030

2800

750

+ 1 0 ° C −11

°C + 10

FUEL SYSTEM PAGE (TYPICAL DISPLAY)

ECAM SDU

A X FEED ENG 1

F U E L

ENG 2

APU OPEN ON

L TK 1

CTR TK CTR TK PUMP 1 MODE SEL PUMP 2

PUMPS 2

FAULT

FAULT

FAULT

FAULT

OFF

OFF

OFF

MAN

B ECAM

A U T O

1

R TK PUMPS 2

FAULT

FAULT

FAULT

OFF

OFF

OFF

F U E L

FUEL CONTROL PANEL 40VU

TO CONFIG

CANC

UPPER DISPLAY

OFF

ENG

BLEED

PRESS

HYD

ELEC

FUEL

APU

COND

DOOR

F/CTL

WHEEL

ALL

STS

RCL

FUEL SYSTEM PAGE PUSHBUTTON SWITCH

BRT

LOWER DISPLAY

CLR OFF

CIR

BRT

C

ECAM CONTROL PANEL 11VU N_AR_052000_1_0140101_01_00

Fuel System Control and Indications - Typical View FIGURE-05-20-00-991-014-A01

05-20-00

Page 13 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 A

REFUEL/DEFUEL CONTROL PANEL

FUEL QTY kg x 1000

LEFT

RIGHT

CTR

LVL

HI LEFT

RIGHT

CTR

VALVES

REFUEL OPEN

OPEN

OPEN

NORM

NORM

NORM

SHUT

SHUT

SHUT

MODE SELECT

TEST

BATT POWER

HI LVL

ON

REFUEL OFF

DEFUEL / XFR OPEN

LTS

ACTUAL

REFUEL

PRESELECTED

NORM

kg x 1000

DEC

CKPT

INC

END

A NOTE: DEPENDING ON YOUR AIRCRAFT CONFIGURATION

N_AR_052000_1_0150101_01_00

Refuel/Defuel Control Panel Typical View FIGURE-05-20-00-991-015-A01

05-20-00

Page 14 Jul 01/09


05-30-00

MOVING FUEL FOR CG CONTROL

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 05-30-00-650-801-A01 Fuel Transfer 1.

General WARNING : DO NOT TRY TO GET ACCESS TO THE FUEL VALVE ACTUATORS IN A LANDING GEAR BAY IF THE RELATED GEAR IS RETRACTED AND THE GEAR DOORS ARE CLOSED. IN THIS CONDITION, THE WEIGHT OF THE LANDING GEAR CAN BE ON THE GEAR DOORS. IF YOU OPEN THESE GEAR DOORS, THERE IS A RISK THAT THE LANDING GEAR WILL EXTEND BY GRAVITY. WARNING : MAKE SURE THAT THE AIRCRAFT IS STABLE AND SAFE BEFORE YOU TRY TO GET ACCESS TO THE FUEL SYSTEM VALVES OR OTHER COMPONENTS. WARNING : THIS PROCEDURE IS FOR INFORMATION ONLY TO HELP YOU PREPARE THE RECOVERY OPERATION. TO DO THE PROCEDURE, YOU MUST REFER TO THE OPERATORS CUSTOMIZED DOCUMENTATION. CAUTION :

BEFORE YOU TRANSFER FUEL, MAKE SURE THAT THERE IS SUFFICIENT SPACE IN THE APPLICABLE TANKS FOR THE FUEL YOU WILL TRANSFER.

CAUTION :

WITHOUT A SERVICEABLE ELECTRICAL SYSTEM, YOU MUST MONITOR THE QUANTITY OF FUEL IN THE TANKS AND MAKE SURE TO STOP THE TRANSFER TO A TANK WHEN THE FUEL IN THE TANK IS NEAR THE HIGH LEVEL QUANTITY. THERE IS NO HIGH LEVEL PROTECTION FOR THE TANKS IF THE ELECTRICAL SYSTEM IS NOT SERVICEABLE. If the aircraft is in a wing high position, it can be necessary to transfer fuel from the low wing to the high wing. This helps to move the aircraft lateral CG to the correct position. Before you do a fuel transfer, you must find the fuel quantity in each fuel tank. 2.


3.


4.


Referenced Information REFERENCE AMM 28-00-00-910-001 AMM 24-41-00-861-002

DESIGNATION

05-30-00

Page 1 Jul 01/09


REFERENCE AMM 31-60-00-860-001


5.


Preparation (1) Obey the fuel safety procedures when you work on the fuel system. See AMM 28-00-00-910-001. (2) Put safety barrier in position and a warning notice to tell persons not to operate the flight controls. (3) Energize the aircraft electrical circuits (see AMM 24-41-00-861-002) and do an EIS start procedure (lower ECAM DU) (see AMM 31-60-00-860-001). (4) On the ECAM control panel push the FUEL pushbutton switch (P/BSW) to show the FUEL page. (5) Open the access door192MB.

Subtask 05-30-00-650-003-A01 B.

Fuel Transfer (1) On the refuel/defuel panel 800VU: (a) Hold the TEST switch in the LTS position and make sure that: - all the panels lights come on, - the FUEL QTY and REFUEL displays show figure eights. (b) Hold the TEST switch in the HI LVL position and make sure that all the HI LVL lights change state. That is, those that were off come on and those that were on go off. (c) Release the TEST switch and make sure that the HI LVL lights, for the tanks which are not full, go off. (d) Put the MODE SELECT switch to the DEFUEL XFR position and make sure that the OPEN light comes on. (e) To move the fuel from on of the wing tanks: - put the REFUEL VALVES switch of the tank you are to move fuel from, to the NORM and guarded position, - put the REFUEL VALVES switch of the tank you are to move fuel into, to the OPEN position.

05-30-00

Page 2 Jul 01/09


(f)

On the fuel control panel 40VU: - push the X FEED P/BSW, - make sure that the P/BSW ON and OPEN lights come on.

(g) On the ECAM SDU, make sure that the crossfeed valve shows green in-line (open). (2) To move fuel from the wing tanks: (a) On the fuel control panel 40VU: - push the applicable TK PUMPS P/BSWs, - make sure that the applicable P/BSW OFF lights go off. (b) On the ECAM SDU monitor the fuel quantity indications. (c) When the fuel quantity indications are correct, on the fuel control panel 40VU: - release the applicable P/BSW, - make sure that the applicable P/BSW OFF lights come on. (3) To move all the fuel from a wing tank: (a) On the fuel control panel 40VU, push the L (or R) TK PUMPS 1 and 2 P/BSWs. Make sure that the applicable P/BSW OFF lights go off. (b) Operate the pumps until the FAULT lights of the L (or R) TK PUMPS 1 and 2 P/BSW come on. (c) Release the L (or R) TK PUMPS 1 and 2 P/BSWs. Make sure that the applicable P/BSW OFF lights come on and the applicable FAULT lights go off. (4) To move fuel from the centre tank: (a) On the control panel 40VU: 1

Release the MODE SEL P/BSW.

2

Make sure that the P/BSW MAN light comes on. NOTE : You can only transfer fuel from the center tank with the centre tank pumps in manual control.

3

Push the CTR TK PUMPS 1 an 2 P/BSWs. Make sure that the P/BSW OFF lights go off.

(b) On the ECAM SDU, monitor the fuel quantity indications. (c) When the fuel quantity indications are correct, on the fuel control panel 40VU: - release the CTR TK PUMPS 1 and 2 P/BSWs, - make sure that the P/BSW OFF lights come on and that the P/BSW FAULT lights go off. (5) To move all the fuel from the center tank: (a) On the fuel control panel 40VU, push the CTR TK PUMPS 1 and 2 P/BSWs. Make sure that the P/BSW OFF lights go off.

05-30-00

Page 3 Jul 01/09


(b) Operate the pumps until the FAULT lights of the CTR TK PUMPS 1 and 2 P/BSW come on. (c) Release the CTR TK PUMP P/BSW. Make sure that the P/BSW OFF lights come on and the P/BSW FAULT lights go off.

05-30-00

Page 4 Jul 01/09


05-40-00

DEFUEL SCENARIOS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 05-40-00-001-A01 Defuel Scenarios 1.

You can use one of the procedures that follow to defuel the aircraft: A.

Normal pressure defuel (with aircraft fuel pumps), with all systems serviceable, see TASK 05-40-01-650-801-A01.

B.

Drain remaining fuel, see TASK 05-40-02-650-801-A01.

C.

Pressure defuel, using an External Wiring Harness (EWH) to supply power to the aircraft fuel pumps, see TASK 05-40-03-650-802-A01.

05-40-00

Page 1 Jul 01/09


05-40-01

DEFUEL SCENARIO 1 NORMAL PRESSURE DEFUEL WITH ALL AIRCRAFT SYSTEMS SERVICEABLE

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 05-40-01-650-801-A01 Normal Pressure Defuel With All Aircraft Systems Serviceable 1.

General You can use this procedure when the aircraft fuel pumps and electrical systems are serviceable. But only use this procedure when there is no structural damage and all systems are serviceable.

2.


3.

Job Setup References See DESC 05-10-00-001-A01 for general preparation before you start the defuel procedure. See DESC 09-10-12-004-A01 for the fuel system ground connections. See AMM 28-25-00-650-001 for the customized procedure.

4.


Referenced Information REFERENCE TASK 05-40-02-650-801-A01 DESC 05-10-00-001-A01 DESC 09-10-12-004-A01 AMM 28-25-00-650-001 AMM 24-41-00-861-002

DESIGNATION TASK 05-40-02-650-801-A01-Drain Remaining Fuel DESC 05-10-00-001-A01-General DESC 09-10-12-004-A01-Fuel System


Procedure WARNING : MAKE SURE THAT ALL PERSONNEL IS AT A SAFE DISTANCE DURING THE REMOVAL OF FUEL, CARGO OR LARGE COMPONENTS. AN UNEQUAL REMOVAL OF FUEL OR CARGO OR THE REMOVAL OF LARGE COMPONENTS CAN CHANGE THE CG AND THE LONGITUDINAL AND LATERAL STABILITY OF THE AIRCRAFT. DEATH OR SERIOUS INJURY MAY RESULT IF THE AIRCRAFT FALLS ON RECOVERY PERSONNEL. WARNING : MAKE SURE THAT YOU OBEY ALL THE APPLICABLE SAFETY PRECAUTIONS WHEN YOU REMOVE FUEL OR WHEN YOU WORK IN AN ENVIRONMENT WHERE THERE IS FUEL.

05-40-01

Page 1 Jul 01/09


WARNING : DO NOT SPILL FUEL ON THE ENGINES OR THE BRAKES. IF YOU SPILL FUEL ON ENGINES OR BRAKES THAT ARE HOT, IT CAN CAUSES FIRE. Subtask 05-40-01-869-001-A01 A.

Preparation (1) Make sure that the aircraft and the tanker are correctly grounded and bonded. (2) Open the access door 192MB. (3) Put access platforms and safety barriers in position. (4) Remove the applicable refuel coupling cap. (5) Make sure that the hose-coupling of the fuel tanker/pump is clean. (6) Make sure that there is no damage on the refuel/defuel coupling. In case of any damage, contact AIRBUS. (7) Connect the hose-coupling of the fuel tanker/pump to the A/C refuel/defuel coupling. (8) Energize the A/C electrical circuits, see AMM 24-41-00-861-002. (9) Start the ECAM system. On the ECAM Control Panel, push the FUEL system page P/BSW. (10) On the refuel/defuel control panel 800VU: (a) Make sure that the refuel valve switches are in the NORM and guarded position. (b) Put the MODE SELECT switch to the DEFUEL XFR position and make sure that the OPEN light comes on. (11) On the panel 40VU, push the X FEED P/BSW and make sure that the ON and OPEN lights come on. (12) On the SD FUEL page, make sure that the crossfeed valve indication is shown green in-line (valve open).

Subtask 05-40-01-650-003-A01 B.

Pressure Defuel Procedure WARNING : THIS PROCEDURE IS FOR INFORMATION ONLY TO HELP YOU PREPARE THE RECOVERY OPERATION. TO DO THE PROCEDURE, YOU MUST REFER TO THE OPERATORS CUSTOMIZED DOCUMENTATION. (1) On the panel 40VU: (a) Push the MODE SEL P/BSW. Make sure that the MAN light goes off (CTR tank pumps now in automatic control). (b) Push the applicable TK PUMPS P/BSWs. Make sure that the applicable P/BSW OFF lights go off. (2) On the SD FUEL page, monitor the fuel quantity indications.

05-40-01

Page 2 Jul 01/09


(3) When the fuel quantity has decreased to the necessary level, on panel 40VU: (a) Release the applicable TK PUMPS P/BSWs. Make sure that the related P/BSW OFF lights comes on. (b) Release the MODE SEL P/BSW. Make sure that the MAN light of the P/BSW comes on (CTR tank pumps now in manual control). (c) On the SD FUEL page, make sure that the tank contents become stable. (4) To defuel the tanks until empty: (a) Operate the related pumps until the related P/BSW FAULT light comes on. (b) Release the applicable TANK PUMPS P/BSWs. Make sure that the applicable P/BSW OFF lights come on and the FAULT lights go off. (5) Drain the remaining fuel from the tank(s), see TASK 05-40-02-650-801-A01.

05-40-01

Page 3 Jul 01/09


05-40-02

DEFUEL SCENARIO 2 DRAIN REMAINING FUEL

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 05-40-02-650-801-A01 Drain Remaining Fuel 1.

General This procedure can be used: - to drain the fuel that remains in the fuel tanks. - to defuel the aircraft when no other procedure can be done.

2.


3.

Job Setup References See DESC 05-10-00-001-A01 for general preparation before you start the defuel procedure. See DESC 09-10-12-004-A01 for the fuel system ground connections. See AMM 28-25-00-650-003 for the customized procedure. To do this procedure, you can use: - 97A28002117002 PURGING TOOL for wing and center tank. or - 98A28104000002 TOOL - PURGING for center tank only. or - 98A28203000000 TEST EQUIPMENT JET PUMP for wing and center tank.

4.


Fixtures, Tools, Test and Support REFERENCE 98A28104000002

DESIGNATION TOOL - PURGING Fixtures, Tools, Test and Support TABLE 1

B.

Referenced Information REFERENCE TASK 02-30-01-481-801-A01 DESC 05-10-00-001-A01 DESC 09-10-12-004-A01 AMM 28-25-00-650-003

DESIGNATION TASK 02-30-01-481-801-A01-Installation of the Safety Devices on Landing Gears DESC 05-10-00-001-A01-General DESC 09-10-12-004-A01-Fuel System

05-40-02

Page 1 Jul 01/09


REFERENCE FIGURE 05-40-02-991-004-A

DESIGNATION FIGURE 05-40-02-991-004-A-Drain Remaining Fuel Referenced Information TABLE 2

5.

Procedure WARNING : MAKE SURE THAT ALL PERSONNEL IS AT A SAFE DISTANCE DURING THE REMOVAL OF FUEL, CARGO OR LARGE COMPONENTS. AN UNEQUAL REMOVAL OF FUEL OR CARGO OR THE REMOVAL OF LARGE COMPONENTS CAN CHANGE THE CG AND THE LONGITUDINAL AND LATERAL STABILITY OF THE AIRCRAFT. DEATH OR SERIOUS INJURY MAY RESULT IF THE AIRCRAFT FALLS ON RECOVERY PERSONNEL. WARNING : MAKE SURE THAT YOU OBEY ALL THE APPLICABLE SAFETY PRECAUTIONS WHEN YOU REMOVE FUEL OR WHEN YOU WORK IN AN ENVIRONMENT WHERE THERE IS FUEL. WARNING : DO NOT SPILL FUEL ON THE ENGINES OR THE BRAKES. IF YOU SPILL FUEL ON ENGINES OR BRAKES THAT ARE HOT, IT CAN CAUSES FIRE. Subtask 05-40-02-869-001-A01 A.

Preparation (1) Make sure that the ground safety locks are installed on the landing gears, see TASK 02-30-01-481-801-A01. (2) On the panel 400VU: - Make sure that the L/G control lever is in the DOWN position. - put a warning notice in position to tell persons not to operate the landing gear. (3) Put warning notices in position to tell persons not to operate L/G doors. (4) Put safety barriers and access platforms in position. (5) If the fuel temperature is less that -5 ˚C (+23.00 ˚F) and/or the water drain valves are frozen, heat the drain valve areas with an approved hot air blower. (6) For access to the CTR tank water drain valves, open access panels 195BB and 196BB.

Subtask 05-40-02-650-002-A01 B.

Drain Fuel WARNING : THIS PROCEDURE IS FOR INFORMATION ONLY TO HELP YOU PREPARE THE RECOVERY OPERATION. TO DO THE PROCEDURE, YOU MUST REFER TO THE OPERATORS CUSTOMIZED DOCUMENTATION.

05-40-02

Page 2 Jul 01/09


NOTE : To drain fuel from the center tank, it is recommended to use 98A28104000002 TOOL - PURGING to prevent leaks. (1) On the PURGING TOOL, fully retract the nut (4), the screw (3) and the plunger assembly (1). (2) Install the PURGING TOOL, see FIGURE 05-40-02-991-004-A: (a) Put the hexagonal end of the bush (2) into the base plate of the applicable drain valve. (b) Turn the bush (2) through 30 degrees. (c) Turn the nut (4) until it touches and seals against the surface (wing surface or bottom of the water drain valve). (d) Put the end of the hose into the container. (e) Hold the bush (2) and turn the screw (3) to the end of its travel. This causes the plunger (1) to open the drain valve and the fuel to flow. (3) When the fuel flow stops, hold the bush (2) and turn the screw (3) until the drain valves closes. (4) Remove the PURGING TOOL: - Turn the nut (4) until it is clear of the surface (wing surface or bottom of the water drain valve). - Turn the bush (2) back through 30 degrees and remove the purging tool from the water drain valve. (5) Examine the water drain valve for leakage. Leaks are not permitted. NOTE : To increase the defueling rate, you can use a suction pump driven by an air drill.

05-40-02

Page 3 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 A

25QM (26QM) (A318/A319/A320 ONLY) 23QM (24QM)

21QM (22QM) 95QM

94QM

A

WATER DRAIN VALVE

FUEL TANK BOTTOM−SKIN

1 4 2

3

TYPICAL SUCTION PUMP

HOSE

HOSE OUTLET

AIR DRILL

A N_AR_054002_1_0040101_01_00

Drain Remaining Fuel Purging Tool Installation FIGURE-05-40-02-991-004-A01

05-40-02

Page 4 Jul 01/09


05-40-03

DEFUEL SCENARIO 3 DEFUEL USING AN EXTERNAL WIRING HARNESS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 05-40-03-650-802-A01 Defuel Using an External Wiring Harness 1.

General WARNING : DO NOT SPILL FUEL ON THE ENGINES OR THE BRAKES. IF YOU SPILL FUEL ON ENGINES OR BRAKES THAT ARE HOT, IT CAN CAUSES FIRE. WARNING : MAKE SURE THAT THE AIRCRAFT CENTER OF GRAVITY STAYS CORRECT WHEN YOU DEFUEL THE AIRCRAFT. YOU MUST MONITOR THE AIRCRAFT CG AT ALL TIMES WARNING : BEFORE YOU DO THIS PROCEDURE, MAKE SURE THAT THE AIRCRAFT ELECTRICAL SYSTEM IS DE-ENERGIZED AND ISOLATED. This procedure can be used when: - There is no structural damage to the aircraft, - The aircraft electrical system cannot be energized.

2.


3.

Job Setup References See DESC 05-10-00-001-A01 for general preparation before you start the defuel procedure. See DESC 09-10-12-004-A01 for the fuel system ground connections.

4.


Referenced Information REFERENCE TASK 05-40-02-650-801-A01 DESC 05-10-00-001-A01 DESC 09-10-12-004-A01 DESC 05-20-00-001-A01 FIGURE 05-40-03-991-001-A

DESIGNATION TASK 05-40-02-650-801-A01-Drain Remaining Fuel DESC 05-10-00-001-A01-General DESC 09-10-12-004-A01-Fuel System DESC 05-20-00-001-A01-Fuel System Basic Description FIGURE 05-40-03-991-001-A-Defuel Using An External Wiring Harness Referenced Information TABLE 1

05-40-03

Page 1 Jul 01/09


5.


Preparation (1) See FIGURE 05-40-03-991-001-A for details on the external wiring harness. (2) Make sure that the aircraft electrical system is de-energized and isolated. (3) Make sure that there is no GPU connected to the aircraft electrical system. (4) Make sure that the aircraft and the tanker are correctly grounded and bonded. (5) Put access platforms and safety barriers in position. (6) Remove the applicable refuel coupling cap. (7) Make sure that the hose-coupling of the fuel tanker/pump is clean. (8) Make sure that there is no damage on the refuel/defuel coupling. In case of any damage, contact AIRBUS. (9) Connect the hose-coupling of the fuel tanker/pump to the A/C refuel/defuel coupling.

**ON A/C A318-100 A319-100 A320-100 A320-200 Subtask 05-40-03-010-001-A01 B.

External Wiring Harness Installation (1) The valves that you will use to defuel the aircraft are: - the crossfeed valve 10QM, - the transfer/defuel valve 11QM, - the intercell transfer valves 27QM (29QM) or 28QM (30QM). See DESC 05-20-00-001-A01 for the fuel system description and the location of the valves. NOTE : The valves can be operated manually if you remove their electrically operated actuators. (2) Open the MLG doors. (3) Open the crossfeed valve 10QM: - Get access to the crossfeed valve actuator 5QM through the MLG door. - Remove the crossfeed valve actuator 5QM. - Engage a suitable tool in the slot of the crossfeed valve 10QM to manually open the valve. (4) Open the transfer/defuel valve 11QM: - Get access to the transfer/defuel valve actuator 11QU through the MLG door. - Remove the transfer/defuel valve actuator 11QU. - Engage a suitable tool in the slot of the transfer/defuel valve 11QM to manually open the valve.

05-40-03

Page 2 Jul 01/09


(5) Operate the intercell transfer valves 27QM (29QM) or 28QM (30QM): NOTE : When you defuel an outer cell, it is sufficient to open one intercell transfer valve. (a) Intercell transfer valve operation 27QM (29QM). 1

Remove the access panel 522JB (622JB) to get access to the intercell transfer valve actuator 9QP (10QP).

2

Find the position of the valve using the see/feel indicator on the actuator: a

If the valve is open leave, leave it in the open position.

b

If the valve is closed: - Remove the actuator, - Engage a suitable tool in the slot of the drive shaft of the intercell transfer valve to manually open the valve.

(b) Intercell transfer valve operation 28QM (30QM). 1

Remove the access panel 575DB (675DB) to get access to the intercell transfer valve actuator 11QP (12QP).

2

Find the position of the valve using the see/feel indicator on the actuator: a

If the valve is OPEN leave, leave it in the OPEN position.

b

If the valve is closed: - Remove the actuator, - Engage a suitable tool in the slot of the drive shaft of the intercell transfer valve to manually open the valve.

(6) To defuel the wing tanks, connect the external wiring harness to the pumps 25QA and 21QA or 22QA and 26QA: - Remove the pump cover plates from pump 25QA and 21QA to defuel the LH wing. - Remove the pump cover plates from pump 22QA and 26QA to defuel the RH wing. - Remove the electrical plugs from the pumps. - Connect the plugs of the external wiring harness to the pumps 25QA and 21QA or 22QA and 26QA. - Connect the external wiring harness to the GPU. (7) To defuel the center tank, connect the external wiring harness to the pumps 37QA and 38QA: - Get access to the center tank pumps 37QA and 38QA. - Remove the pump cover plates from pump 37QA and 38QA. - Remove the electrical plugs from the pumps. - Connect the external wiring harness plugs to the pumps.

05-40-03

Page 3 Jul 01/09


**ON A/C A321-100 A321-200 Subtask 05-40-03-010-001-B01 B.

External Wiring Harness Installation (1) The valves that you will use to defuel the aircraft are: - the crossfeed valve 10QM, - the transfer/defuel valve 11QM, - the control valves 153QM (154QM). See DESC 05-20-00-001-A01 for the fuel system description and the location of the valves. NOTE : The valves can be operated manually if you remove their electrically operated actuators. (2) Open the MLG doors. (3) Open the crossfeed valve 10QM: - Get access to the crossfeed valve actuator 5QE through the MLG door. - Remove the crossfeed valve actuator 5QE. - Engage a suitable tool in the slot of the crossfeed valve 10QM to manually open the valve. (4) Open the transfer/defuel valve 11QM: - Get access to the transfer/defuel valve actuator 11QU through the MLG door. - Remove the transfer/defuel valve actuator 11QU. - Engage a suitable tool in the slot of the transfer/defuel valve 11QM to manually open the valve. (5) Operate the control valves 153QM (154QM): (a) Remove the access panel 195BB (196BB) to get access to the control valves actuator 11QL (12QL). (b) Find the position of the valve using the see/feel indicator on the actuator: 1

If the valve is OPEN, leave it in the OPEN position.

2

If the valve is closed: - Remove the actuator, - Engage a suitable tool in the slot of the drive shaft of the control valve 153QM ( 154QM) to manually open the valve.

(6) Connect the external wiring harness to the pumps 25QA and 21QA or 22QA and 26QA: - Remove the pump cover plates from pump 25QA and 21QA to defuel the LH wing. - Remove the pump cover plates from pump 22QA and 26QA to defuel the RH wing. - Remove the electrical plugs from the pumps. - Connect the plugs of the external wiring harness to the pumps 25QA and 21QA or 22QA and 26QA. - Connect the external wiring harness to the GPU.

05-40-03

Page 4 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 Subtask 05-40-03-650-002-A01 C.

Defuel Procedure (1) On the control panel of the external wiring harness, select both pump switches to ON. (2) Monitor the pumped fuel on the fuel tanker gauge. (3) Operate the pump until the tank is empty (the fuel flow stops). (4) On the control panel of the external wiring harness, select both pump switches to OFF. Do not operate the pumps when the fuel tank is empty. (5) Drain the remaining fuel, see TASK 05-40-02-650-801-A01.

05-40-03

Page 5 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

SWITCH 10 AMPS

OFF

115VAC

A

R

R

16AWG COPPER

B

Y

Y

16AWG COPPER

C

B

B

16AWG COPPER

P1 NSA938 027E15FSN

ON OFF

115VAC

A

R

R

16AWG COPPER

B

Y

Y

16AWG COPPER

C

B

B

16AWG COPPER

P2 NSA938 028E15FSN

ON PANEL WIRING DIAGRAM EXTERNAL WIRING HARNESS

t)

6f

2.5

m

1 (8.

P1

30 m (98.3 ft) MINIMUM

115VAC

2.5 m

PANEL

P2 (8. 16 ft)

EXTERNAL WIRING HARNESS

N_AR_054003_1_0010101_01_00

Defuel Using An External Wiring Harness External Wiring Harness FIGURE-05-40-03-991-001-A01

05-40-03

Page 6 Jul 01/09


05-50-00

CARGO COMPARTMENTS


See 09-10-14 for the description of the cargo compartments. For data related to the different cargo compartment doors see DESC 09-10-10-003-A01.

05-50-00

Page 1 Jul 01/09


05-50-01

CARGO REMOVAL

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 05-50-01-005-A01 Cargo Removal 1.

General This chapter gives data related to the removal of the cargo from the aircraft. The removal of the cargo is an important task carried out during an aircraft recovery operation. Cargo removal will remove a large amount of weight from the aircraft and can also control the Center of Gravity (CG). The procedure you select to remove the cargo during the aircraft recovery operation should only be made after a survey has been carried out to find: - The aircraft stability and attitude. - The extent of damage to the aircraft structure and components. - The condition of the aircraft electrical systems. - The condition of the cargo loading system. - If an external ground power source is available. - If the equipment necessary to remove the cargo is available. The removal of the cargo is important but not all recovery operations will require its removal. When a small amount of cargo is loaded it is possible that it is not necessary to remove it. This decision can only be made once the survey has been completed. Decisions can also be made to remove the cargo only to the point where the maximum lifting and jacking loads will not be exceeded or the aircraft recovery operation can be completed. See the Cargo Loading Manual (CLS) for the cargo removal procedure.

05-50-01

Page 1 Jul 01/09


05-60-00

REMOVAL OF LARGE COMPONENTS


Large aircraft components are not usually removed during a recovery operation. WARNING : YOU MUST CONTACT AIRBUS BEFORE YOU MANUALLY OPERATE A SYSTEM OR REMOVE A COMPONENT WHEN THE AIRCRAFT IS IN AN ABNORMAL ATTITUDE OR DISABLED. THE AMM PROCEDURES ARE APPLICABLE ON AN AIRCRAFT IN A LEVEL CONFIGURATION ONLY. Removal can be necessary when: - Damaged components such as flap sections, ailerons, elevators, etc. are not safely attached, - It is necessary to decrease the weight and/or to control CG, - The runway or the airport was closed because of the accident. In this case, it is necessary to remove the vertical stabilizer. This is an unusual event which can occur only if the runway or airport would be closed for a long time, - You used escape slides during evacuation. After the evacuation, it is necessary to carefully disconnect and remove the escape slides, - Landing gear and/or other components are broken.

05-60-00

Page 1 Jul 01/09


LEVELING AND LIFTING 06-00-00

LEVELING AND LIFTING


Leveling and Lifting Families There are 5 basic leveling families (see TBD).

2.

Aircraft Pitch and Roll Angles Before you start the recovery, it is possible to find the aircraft pitch and roll angles when no electrical power is available. The items of equipment that you can use are: - An attitude monitor (clinometer), located in the belly fairing - A spirit level, a clinometer or similar device located on the forward cargo-compartment floor beams or on the cabin floor seat tracks. It is possible to use the same equipment to find when the aircraft is leveled.

3.

Leveling/Lifting of the Aircraft CAUTION :

YOU MUST DO THE LATERAL LEVELING BEFORE YOU DO THE LONGITUDINAL LEVELING. There are three general methods to level/lift the aircraft. They are given in the chapters that follow: - Use of Jacks (see 06-30-00), - Use of Pneumatic Lifting Bags (see 06-40-00.), - Use of Cranes (see 06-50-00), - Step by step combination: use of one method and then another one. A.

The leveling/lifting items of equipment are: - Jacks, - Pneumatic lifting bags, - Cranes and slings. It is possible to use one of these items of equipment alone or more than one in any step-by-step combination.

B.

The procedures in the chapters above describe how to level/lift the aircraft to a height at which the fuselage datum is 4600 mm (181.10 in) above the ground. This is the height necessary: - To put the aircraft in a hangar or on maintenance jacks, - To make the extension of the landing gear possible, - To put the aircraft, or part of it, on a mobile device. However, to replace a landing gear, the necessary height of the fuselage datum is 5210 mm (205.12 in) above the ground.

06-00-00

Page 1 Jul 01/09


C.

The aircraft can be in such an attitude that it is necessary to do the leveling operation before the lifting operation. In this case, you must keep the aircraft in a level attitude during the lifting phase. NOTE : As each aircraft recovery situation is different, you must analyze the conditions and available equipment before you decide which leveling or lifting procedure you will use.

06-00-00

Page 2 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 06-00-00-002-A01 Leveling/Lifting Obstructions 1.

It may be necessary to remove the items that follow to make the leveling / lifting operation easier. NOTE : The list is not exhaustive. The optional items of equipment can change as they are related to the customer configuration. Name GPS Antenna 1 & 2 VHF 1 Antenna ATC Antenna 1 & 2 (Top & Bottom)

Zone 220 220 120/230

TCAS Antenna (Top & Bottom) DME 2 Antenna MARKER Antenna Angle of Attack Sensors Drain Mast

130/230 IPC 34-43-11 120/130 IPC 34-51-11 130 IPC 34-55-18 IPC 34-11-19 127/231/232 130 IPC 30-71-51 FWD Fuselage

IPC IPC 34-36-16 IPC 23-12-11 IPC 34-52-11

AMM AMM 34-36-16-000-001 AMM 23-12-11-000-001 AMM 34-52-11-000-001 AMM AMM AMM AMM AMM

34-43-11-000-001 34-51-11-000-002 34-55-18-000-001 34-11-19-000-001 30-71-51-000-001

TABLE 1 Name Drain Mast Radio Altimeter 1 & 2 VHF 2 Antenna

Zone IPC 150 IPC 30-71-51 150 IPC 34-42-11 150 IPC 23-12-11 AFT Fuselage

AMM AMM 30-71-51-000-001 AMM 34-42-11-000-001 AMM 23-12-11-000-001

TABLE 2

06-00-00

Page 3 Jul 01/09


**ON A/C A318-100

GPS 1

GPS 2

VHF 1

ATC TOP 1−2

TCAS TOP

FR23

AOA SENSOR 1−2

MARKER

FR25

AOA SENSOR 3

ATC BOTTOM 1−2

DME 2

FR35

TCAS BOTTOM DRAIN MAST

N_AR_060000_1_0010101_01_00

Antennas Location FWD Fuselage (Sheet 1 of 2) FIGURE-06-00-00-991-001-A01

06-00-00

Page 4 Jul 01/09


**ON A/C A318-100

FR57

VHF 2

FR69

RA 1

RA 2

DRAIN MAST

N_AR_060000_1_0010103_01_00

Antennas Location AFT Fuselage (Sheet 2 of 2) FIGURE-06-00-00-991-001-A01

06-00-00

Page 5 Jul 01/09


**ON A/C A319-100

GPS 1

GPS 2

VHF 1

ATC TOP 1−2

TCAS TOP

FR20

FR34

AOA SENSOR 1−2

AOA SENSOR 3

FR15

ATC BOTTOM 1−2

DME 2

MARKER

TCAS DRAIN MAST BOTTOM

N_AR_060000_1_0010201_01_00

Antennas Location FWD Fuselage (Sheet 1 of 2) FIGURE-06-00-00-991-001-B01

06-00-00

Page 6 Jul 01/09


**ON A/C A319-100

FR53

DRAIN MAST

FR62

VHF 2

RA 1

RA 2

N_AR_060000_1_0010202_01_00

Antennas Location AFT Fuselage (Sheet 2 of 2) FIGURE-06-00-00-991-001-B01

06-00-00

Page 7 Jul 01/09


**ON A/C A320-100 A320-200 A321-100 A321-200

GPS 1

GPS 2

VHF 1

TCAS TOP

ATC TOP 1−2

FR20

FR32

AOA SENSOR 1−2

AOA SENSOR 3

FR15

ATC BOTTOM 1−2

DME 2

TCAS BOTTOM

DRAIN MAST

MARKER

N_AR_060000_1_0010301_01_00

Antennas Location FWD Location (Sheet 1 of 2) FIGURE-06-00-00-991-001-C01

06-00-00

Page 8 Jul 01/09


**ON A/C A320-100 A320-200 A321-100 A321-200

FR51

VHF 2

FR59

DRAIN MAST

RA 1

RA 2

N_AR_060000_1_0010302_01_00

Antennas Location AFT Fuselage (Sheet 2 of 2) FIGURE-06-00-00-991-001-C01

06-00-00

Page 9 Jul 01/09


06-10-00

LOAD DETERMINATION

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 06-10-00-970-801-A01 Vertical Loads Determination 1.

General This section gives data about the vertical loads related to aircraft leveling/lifting during the recovery operation and about the way to calculate them. NOTE : The information or principle contained in this chapter are given as a guide to assist an aircraft recovery.

2.


3.


General The theoretical calculations that follow help to find the loads necessary for leveling/lifting. They also help to: - Make sure the aircraft is stable, - Do a selection of applicable methods of leveling/lifting, - Do a check of the local structural capability of the aircraft to prevent secondary damage, - Make sure the recovery procedure is applicable to the related weight condition of the aircraft. The simplified calculations are related to the assumptions that follow: - The aircraft structure is considered as rigid. The calculations do not take into account the flexibility in the aircraft structure, - The leveling/lifting is done at 3 points (isostatic conditions), - The calculation take into account only the vertical loads, - You do the leveling/lifting operations on solid ground conditions and the slings are without elongation, - The calculation do not take into account the effects of wind and temperature.

B.

Location of the 3 lifting points on the aircraft X and Y reference axes See FIGURE 06-10-00-991-001-A. - For the left wing: X1 and Y1 position of the lifting point, - For the right wing: X3 and Y3 position of the lifting point, - For the fuselage: X2 and Y2 position of the lifting point. As the fuselage lifting point is located on the aircraft centerline, Y2 = 0. NOTE : During the leveling/lifting procedure, it can be necessary to use only one lifting point. The aircraft will then pivot around a fixed point such as a main landing gear. For example, with the nose landing gear collapsed, there is only one lifting point and the aircraft will pivot around main landing gears.

06-10-00

Page 1 Jul 01/09


4.


Referenced Information REFERENCE 03-00-00 FIGURE 06-10-00-991-001-A FIGURE 06-10-00-991-002-A

DESIGNATION 03-00-00-WEIGHT AND CG MANAGEMENT FIGURE 06-10-00-991-001-A-Load Determination FIGURE 06-10-00-991-002-A-Load Determination Referenced Information TABLE 1

5.


Load Calculation NOTE : Principle for the calculation of the loads at the recovery leveling/lifting points. (1) Find the 3 leveling/lifting points and related X and Y values, applicable to the attitude of the aircraft and the related scenario (see TBD). (2) Find the values of the NRW, XG and YG (X and Y coordinates of aircraft CG position) calculated for your aircraft condition (see 03-00-00). (3) Record these values in the load calculation worksheet (see FIGURE 06-10-00-991-002-A) and calculate the necessary intermediate values. (4) Use the results of the load calculation worksheet (see FIGURE 06-10-00-991-002-A) the values of the vertical loads (Fz) at the 3 leveling/lifting points. Fz1 = NRW × ((YG - Y2)(X2 - X3) - (XG - X2)(Y2 - Y3)) / ((X1 - X2)(Y2 - Y3) Y2)(X2 - X3)) Fz1 = Fz2 = NRW × ((YG - Y3)(X3 - X1) - (XG - X3)(Y3 - Y1)) / ((X2 - X3)(Y3 - Y1) Y3)(X3 - X1)) Fz2 = Fz3 = NRW × ((YG - Y1)(X1 - X2) - (XG - X1)(Y1 - Y2)) / ((X3 - X1)(Y1 - Y2) Y1)(X1 - X2)) Fz3 =

to find - (Y1 -

- (Y2 -

- (Y3 -

Subtask 06-10-00-869-001-A01 B.

Load Distribution Compared to Allowable Loads (1) For jacks: You must compare the vertical load directly with the allowable load. (2) For pneumatic lifting bags: Use the formula that follows to calculate the pressure of the pneumatic lifting bag: p = Fz / (L × W)

06-10-00

Page 2 Jul 01/09


L = length and W = width of the pneumatic lifting bag. This pressure must be less than or equal to: - The maximum pressure of the pneumatic lifting bag, - The maximum allowable pressure that the pneumatic lifting bag can apply to the aircraft structure. (3) For slings: Use the formula that follows to calculate the load on each sling: f = Fz / N N = number of slings. This load must be less than or equal to the aircraft maximum allowable load at the related frame. NOTE : If loads at leveling/lifting points are not in the allowable values, it is necessary to make new calculations for the recovery configuration, with: - A modified weight and balance, - A change in the recovery means arrangements, - The use of other applicable recovery methods, - Or any combinations of these modifications.

06-10-00

Page 3 Jul 01/09


X1

Y1

NOTE: LIFTING POINT

CL

−Y

X2

Y2 = 0

2540 mm (100 in)

X3

Y3

+X

N_AR_061000_1_0010101_01_02

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

Load Determination Location of the 3 Lifting Points FIGURE-06-10-00-991-001-A01

06-10-00

Page 4 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 NET RECOVERABLE WEIGHT

XG

YG

LEVELING/LIFTING POINT 1 SEE 06−00−00

X1

Y1


X2

Y2


X3

Y3

X1−X2

X2−X3

X3−X1

XG−X1

XG−X2

XG−X3

Y1−Y2

Y2−Y3

Y3−Y1

YG−Y1

YG−Y2

YG−Y3

SEE 03−00−00

INTERMEDIATE CALCULATIONS

N_AR_061000_1_0020101_01_00

Load Determination Load Calculation Worksheet FIGURE-06-10-00-991-002-A01

06-10-00

Page 5 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 06-10-00-970-802-A01 Side loads on Jack Fittings 1.

General This section gives data about the side loads on jack fittings related to the aircraft leveling/lifting phase during the recovery operation and about the way to calculate them. When you level the aircraft from an unusual attitude, an arc movement (horizontal translation) of the jacking point is related to the displacement. If you use a special recovery jack, the jack head can move along the arc movement. Thus, there are no related side loads applied on the jacking point. If you use a jack that cannot move along the arc movement, the jack will apply side loads to the aircraft structure. If these side loads are more than the allowable loads, they will cause damage to the aircraft structure. It is necessary to calculate the side loads for each leveling/lifting scenario. NOTE : The information or principle contained in this chapter are given as a guide to assist an aircraft recovery.

2.


3.


4.


Referenced Information REFERENCE TASK 06-10-00-970-801-A01 03-00-00

DESIGNATION TASK 06-10-00-970-801-A01-Vertical Loads Determination 03-00-00-WEIGHT AND CG MANAGEMENT Referenced Information TABLE 1

5.

Procedure CAUTION :

BE CAREFUL WHEN YOU USE A JACK THAT CANNOT MOVE ALONG THE ARC MOVEMENT. THE JACK WILL APPLY SIDE LOADS TO THE AIRCRAFT STRUCTURE. IF THESE LOADS ARE MORE THAN THE ALLOWABLE LOADS, THEY WILL CAUSE DAMAGE TO THE STRUCTURE.

Subtask 06-10-00-970-002-A01 A.

Load Calculation (1) Find the aircraft recovery configuration and a leveling/lifting method.

06-10-00

Page 6 Jul 01/09


(2) Measure the aircraft pitch (β) and lateral (α) angles with one of the tools or the method that follow: - An attitude monitor (clinometer), in the belly fairing, 192MB, - A spirit level, a clinometer or equivalent device that can be used on the forward cargocompartment floor beams or on the cabin floor seat tracks, - The aircraft geometry and characteristic points. See TBD to find the applicable recovery scenario and the related typical aircraft possible angles. NOTE : The typical angles are given as an example. For all scenarios, you must measure the aircraft pitch and lateral angles for each recovery operation before you start any leveling/lifting procedure. The actual angles are related to the weight and CG configuration of the recovery aircraft. (3) Calculate the NRW and CG position (see 03-00-00) and calculate the vertical loads (Fz) (see TASK 06-10-00-970-801-A01) at the leveling/lifting point. (4) Calculate the Fx side load (component on the X axis). Fx = tan β × Fz (5) Calculate the Fy side load (component on the Y axis). Fy = tan α × Fz (6) Calculate the resultant (R) of Fx and Fy: R = √(Fx2 + Fy2) (7) Make sure the resultant R is less than the maximum allowable side load. If the side load is not less than or equal to the maximum allowable load, you must reduce the applied vertical load until the resultant side load is less than the allowable side load. To reduce the applied vertical load, you can reduce the weight of the aircraft.

06-10-00

Page 7 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 06-10-00-970-803-A01 Arc Movement Calculation 1.

General This section gives data about the arc movement of the leveling/lifting point related to the aircraft leveling/lifting during the recovery operation and about the way to calculate it. NOTE : The information or principle contained in this chapter are given as a guide to assist an aircraft recovery.

2.


3.

Job Setup References When you level the aircraft, it will rotate around a fixed pivot point on the ground and this will cause movement along the X or Y axis. This movement is called Arc Movement. You must control this movement during all the recovery procedure.

4.


Referenced Information REFERENCE FIGURE 06-10-00-991-003-A FIGURE 06-10-00-991-004-A

DESIGNATION FIGURE 06-10-00-991-003-A-Arc Movement Calculation FIGURE 06-10-00-991-004-A-Arc Movement Calculation Referenced Information TABLE 1

5.


Arc Movement Calculation at Fuselage Leveling/Lifting Points (1) Measurement at Aircraft Basic Position See FIGURE 06-10-00-991-003-A. You must make the measurements at the points that follow: - Fixed pivot point: the point around which the aircraft will rotate (X axis). - Fuselage/ground contact point: the contact point between the fuselage and the ground. This point must be lifted to a level attitude (X axis). - Leveling/Lifting point: the point where you apply the loads and where you calculate the arc movement (X axis). - Characteristic point: a point on the lower part of fuselage that you will use for angle calculation (both X and Z axes).

06-10-00

Page 8 Jul 01/09


(2) Arc Movement Calculation (a) Calculate the angle: tan β = dz / dx Where: dx is the distance from the fuselage ground contact point to the characteristic point on the lower part of the fuselage. dz is the height from the ground to the characteristic point. (b) Calculate the arc movement. ∆X = (L - L’) - √((L - L’)2 + tan2 β × (L’2 - L2)) Where: ∆X is the arc movement. L is the distance from the fuselage ground contact point to the fixed pivot point (for example: main landing gear). L’ is the distance from the fuselage ground contact point to the leveling/lifting point. Subtask 06-10-00-970-004-A01 B.

Arc Movement Calculation at Wing Leveling/Lifting Points (1) Measurement at Aircraft Basic Position See FIGURE 06-10-00-991-004-A. You must make the measurements at the points that follow: - Fixed pivot point: the point around which the aircraft will rotate (Y axis). - Wing/ground contact point on the lower wing: the contact point between the wing and the ground. This point must be lifted to a level attitude (Y axis). - Leveling/Lifting point: the point were you apply the loads and where you calculate the arc movement (Y axis). - Characteristic point: a point on the lower part of the engine nacelle on the high wing that you use for angle calculation (the two Y and Z axes). (2) Arc Movement Calculation (a) Calculate the angle. tan α = dz / dy Where: dy is the distance from the wing ground contact point (lower wing) to the characteristic point on the lower part of the engine nacelle on the higher wing. dz is the height from the ground to the characteristic point. (b) Calculate the arc movement. ∆Y = (L - L’) - √((L - L’)2 + tan2 α × (L’2 - L2)) Where: ∆Y is the arc movement. L is the distance from the wing ground contact point to the fixed pivot point (for example: main landing gear). L’ is the distance from the wing ground contact point to the leveling/lifting point.

06-10-00

Page 9 Jul 01/09


X H

L’

LIFTING POINT

FUSELAGE/GROUND CONTACT POINT

L

dx

FIXED PIVOT POINT MAIN LANDING GEAR

dz

CHARACTERISTIC POINT ON FUSELAGE FOR ANGLE CALCULATION

N_AR_061000_1_0030101_01_00

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

Arc Movement Calculation Fuselage Leveling/Lifting Point FIGURE-06-10-00-991-003-A01

06-10-00

Page 10 Jul 01/09


CHARACTERISTIC POINT ON OPPOSITE WING INBOARD NACELLE FOR ANGLE CALCULATION

dz

FIXED PIVOT POINT MAIN LANDING GEAR

dy

L

Y

L’

LIFTING POINT

INBOARD NACELLE/GROUND CONTACT POINT

N_AR_061000_1_0040101_01_00

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

Arc Movement Calculation Wing Leveling/Lifting Point FIGURE-06-10-00-991-004-A01

06-10-00

Page 11 Jul 01/09


06-30-00

USE OF JACKS

**ON A/C A318-100 DESC 06-30-00-001-A01 General 1.

Location of Primary Jacking Points CAUTION :

YOU CAN USE ALL COMBINATIONS OF THE JACKING POINTS (ONE OR MORE) TO LEVEL/LIFT THE AIRCRAFT. THE JACK LOADS AT EACH JACKING POINT MUST NOT BE MORE THAN THE ALLOWABLE LOADS (VERTICAL (FZ) AND HORIZONTAL (FH).

CAUTION :

WHEN YOU LEVEL/LIFT THE AIRCRAFT, YOU MUST CONTINUOUSLY MONITOR AND RECORD THE LOADS AND MAKE SURE THAT THE LOADS YOU APPLY ARE NOT MORE THAN THE MAXIMUM ALLOWABLE LOADS. IF THE LOADS ARE MORE THAN THE ALLOWABLE LOADS, THIS CAN CAUSE DAMAGE TO THE AIRCRAFT STRUCTURE.

CAUTION :

DO NOT USE THE SAME FITTING FOR TETHERING AND LIFTING OF THE AIRCRAFT AT THE SAME TIME. THE LOADS ON THE FITTING WILL CAUSE DAMAGE TO THE AIRCRAFT STRUCTURE.

NOTE : The information or principle contained in this chapter are given as a guide to assist an aircraft recovery. There are three primary jacking points on the aircraft (See FIGURE 06-30-00-991-006-A): - One under the left wing, at RIB 9 - One under the right wing, at RIB 9 - One on the lower forward fuselage, in front of the nose landing gear doors, at FR 8. 2.

Location of Auxiliary Jacking Points An auxiliary jacking point for a safety stay is located on the lower aft fuselage, between FR 73 and FR 74. (See FIGURE 06-30-00-991-006-A) A jack must be installed in this position only once the aircraft is level. This point must be used to make the aircraft stable only.

3.

Maximum Jacking Weight The maximum aircraft weight for jacking is 53000 kg (116844.97 lb).

4.

Maximum Loads See 06-10-00 to determine the loads related to the aircraft attitude, to select the leveling/lifting procedure. See FIGURE 06-30-00-991-010-A to determine loads on jacking points Fz is the load applied in the vertical direction. Fh is the load applied in all horizontal directions. See TASK 06-10-00-970-802-A01 to calculate the side loads.

06-30-00

Page 1 Jul 01/09


Airbus recommends that you use load cells and lifting devices with side load measuring equipment that can accurately record and report the jacking point side loads. Jacking Point RH Wing LH Wing Nose

Fz (daN) 28500 28500 6800 Allowable

Fz (lbf) Fh (daN) 64070 9405 64070 9405 15287 2244 Loads on Primary Jacking Points

Fh (lbf) 21143 21143 5045

TABLE 1 Jacking Point Safety Stay

Fz (daN) 2000

Fz (lbf) 4496

Fh (daN) 660

Fh (lbf) 1484

Allowable Loads on the Safety Stay TABLE 2 5.

Permissible wind speed See FIGURE 06-30-00-991-010-A to determine permissible wind speed.

06-30-00

Page 2 Jul 01/09

CL

2.74 m (8.99 ft)

FWD JACKING POINT WING JACKING POINT

15.18 m (49.8 ft)

26.44 m (86.75 ft)

6.5 m (21.33 ft)

WING JACKING POINT

SAFETY POINT

N_AR_063000_1_0060101_01_00


**ON A/C A318-100

Jacking Points Location FIGURE-06-30-00-991-006-A01

06-30-00

Page 3 Jul 01/09


**ON A/C A318-100 PERMISSIBLE WIND SPEED (Kt) 10 20 30 40 15 25 35 55

45

40

35

AIRCRAFT

CG (% RC

30

)

B

25

20

15

60

70 65

50

60 55

40

50

C

45

30

40 TIP UP SECURITY MARGIN

NRW (kg x 1000)

LOAD ON WING JACKING POINTS (kg x 1000)

CG

50

70

A NRW

35

20

30 0

1

2

3

4

D 5

6

7

8

9

10

LOAD ON FORWARD FUSELAGE JACKING POINT (kg x 1000)

EXAMPLE : ASSUME AIRCRAFT WITH NRW OF 40000 kg A AND CENTER OF GRAVITY AT 20% RC B . THE REACTION AT THE WING JACKING POINTS IS 35300 kg (17650 kg PER SIDE) C AND THE REACTION AT THE FORWARD FUSELAGE JACKING POINT IS 4700 kg D . IF THE AIRCRAFT MUST BE LIFTED OUTSIDE THE WIND SPEED MUST NOT BE IN EXCESS OF 29 Kt. N_AR_063000_1_0100101_01_00

Aircraft Stability Aircraft on Jacks FIGURE-06-30-00-991-010-A01

06-30-00

Page 4 Jul 01/09


**ON A/C A319-100 DESC 06-30-00-001-B01 General 1.



CAUTION :


CAUTION :




3.


4.

Maximum Loads See 06-10-00 to determine the loads related to the aircraft attitude, to select the leveling/lifting procedure. See FIGURE 06-30-00-991-011-Ato determine loads on jacking points. Fz is the load applied in the vertical direction. Fh is the load applied in all horizontal directions. See TASK 06-10-00-970-802-A01 to calculate the side loads.

06-30-00

Page 5 Jul 01/09





Fh (lbf) 21143 21143 5045


Fz (daN) 2000

Fz (lbf) 4496

Fh (daN) 660

Fh (lbf) 1484


Permissible Wind Speed See FIGURE 06-30-00-991-011-Ato determine permissible wind speed.

06-30-00

Page 6 Jul 01/09

CL

2.74 m (8.99 ft)


15.97 m (52.4 ft)

28.83 m (94.59 ft)

6.5 m (21.33 ft)

WING JACKING POINT

SAFETY POINT

N_AR_063000_1_0070101_01_00


**ON A/C A319-100


06-30-00

Page 7 Jul 01/09


**ON A/C A319-100

PERMISSIBLE WIND SPEED (Kt) 10 20 30 40 15 25 35 55

50

45

40

CG FT CG (%

35

RC)

B

30

25

20

15

10 70

60

65 50

60 55

40 C

50

NRW (kg x 1000)


70

AIRCRA

45 A

30


NRW

35

20

30 0

1

2

3

4 D

5

6

7

8

9

10




06-30-00

Page 8 Jul 01/09


**ON A/C A320-100 A320-200 DESC 06-30-00-001-C01 General 1.



CAUTION :


CAUTION :




3.

The maximum aircraft weight for jacking is 59000 kg (130072.70 lb).

4.

Maximum Loads See 06-10-00 to determine the loads related to the aircraft attitude, to select the leveling/lifting procedure. See FIGURE 06-30-00-991-012-A to determine loads on jacking points. Fz is the load applied in the vertical direction. Fh is the load applied in all horizontal directions. See TASK 06-10-00-970-802-A01 to calculate the side loads. Airbus recommends that you use load cells and lifting devices with side load measuring equipment that can accurately record and report the jacking point side loads.

06-30-00

Page 9 Jul 01/09


Jacking Point RH Wing LH Wing Nose



Fh (lbf) 21143 21143 5045


Fz (daN) 2000

Fz (lbf) 4496

Fh (daN) 660

Fh (lbf) 1484


Permissible Wind Speed See FIGURE 06-30-00-991-012-A to determine permissible wind speed.

06-30-00

Page 10 Jul 01/09

CL

2.74 m (8.99 ft)


17.56 m (57.61 ft)

32.57 m (106.86 ft)

6.5 m (21.33 ft)

WING JACKING POINT

N_AR_063000_1_0080101_01_00

SAFETY POINT


**ON A/C A320-100 A320-200


06-30-00

Page 11 Jul 01/09


**ON A/C A320-100 A320-200 PERMISSIBLE WIND SPEED (Kt)

55

B

35

30

25

AIRCRA 20

FT CG

15

(% RC) 10

60

70 65

50

60 55

40

50

C

45

30

NRW (kg x 1000)


70

CG

10 20 30 40 15 25 35 50 45 40

40 A

TIP UP SECURITY MARGIN

35

20 0

1

2

3 D

NRW

30 4

5

6

7

8

9

10




06-30-00

Page 12 Jul 01/09


**ON A/C A321-100 A321-200 DESC 06-30-00-001-D01 General 1.



CAUTION :


CAUTION :




3.


4.

Maximum Loads See 06-10-00 to determine the loads related to the aircraft attitude, to select the leveling/lifting procedure. See FIGURE 06-30-00-991-013-A to determine load on jacking points. Fz is the load applied in the vertical direction. Fh is the load applied in all horizontal directions. See TASK 06-10-00-970-802-A01 to calculate the side loads.

06-30-00

Page 13 Jul 01/09





Fh (lbf) 24778 24778 5045


Fz (daN) 2000

Fz (lbf) 4496.18

Fh (daN) 660

Fh (lbf) 1484


Permissible Wind speed See FIGURE 06-30-00-991-013-A to determine permissible wind speed.

06-30-00

Page 14 Jul 01/09

CL

2.74 m (8.99 ft)


21.83 m (71.62 ft)

39.5 m (129.56 ft)

6.5 m (21.33 ft)

WING JACKING POINT

06-30-00

N_AR_063000_1_0090101_01_00

SAFETY POINT


**ON A/C A321-100 A321-200


Page 15 Jul 01/09


**ON A/C A321-100 A321-200 PERMISSIBLE WIND SPEED (Kt) 10 25 35 45 20 30 40 CG 55

80

50

45

B

40

35

30

25

20

AIRCRAF T CG (% RC) 15 10 80 75

60 C

70 65 A

50

60

NRW

55 40

50 45

30


35

20 0

1

NRW (kg x 1000)


70

2

3

30 6 7 8 9 10 D 5 LOAD ON FORWARD FUSELAGE JACKING POINT (kg x 1000) 4



06-30-00

Page 16 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 06-30-00-002-A01 Type of Jacks 1.

There are three general types of jacks: A.

Special Aircraft Recovery Jacks This type of jack can move along the arc movement in the specified limits. The jack manufacturer instructions must be obeyed. There are two primary types of aircraft recovery jacks: hydraulic and low profile multi-stage jacks: - Monopole design: This is a multi stage single ram attached to a large base plate. The jacking head can move along the arc movement in the specified limits. - Tripod design: This type of jack is almost the same as a hanger or maintenance tripod jack. The difference is that it is possible to operate and control each multi-stage leg independently. Pressure gauges are installed on each leg to monitor loads independently. The operator can make sure the jack head moves in a limited arc. It is possible to operate the jack manually with a lever or control it from a powered console.

B.

Standard Maintenance Tripod Jacks This type of jack is can only do a very limited arc movement. We recommend you do not use a standard maintenance jack for recovery operations. When you use a standard maintenance jack, it is necessary to do the lifting operation in small steps and reposition the jack between each step.

C.

Bottle or Wheel Jacks They can be used for initial leveling or lifting in constricted areas. They have the same limit as the standard maintenance tripod jacks.

06-30-00

Page 17 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 06-30-00-581-802-A01 Jacking 1.

General This section gives the data related to the aircraft jacking for leveling or lifting. NOTE : If you use jacks to level or lift the aircraft, you must put them in position on a satisfactory base. The surface must be flat and the jack must be plumb in place.

2.

Inspections Do an inspection of the area of each jacking point that you will use. Make sure there is no damage and that each jacking point is serviceable.

3.

Job Setup References For jacking point locations, see DESC 06-30-00-001-A01DESC 06-30-00-001-B01DESC 06-30-00-001C01DESC 06-30-00-001-D01. For general data on jack adaptors, see FIGURE 06-30-00-991-004-A.

4.


Fixtures, Tools, Test and Support REFERENCE 98D07103500000 98D104000001 98D07104081000 98D07103000000

DESIGNATION JACK ADAPTER - FUSELAGE JACKING PAD SET (A318, A319, A320) JACKING PAD SET (A321) DYNAMOMETER - SAFETY STAY Fixtures, Tools, Test and Support TABLE 1

B.

Referenced Information REFERENCE DESC 06-30-00-001-A01 DESC 06-30-00-001-B01 DESC 06-30-00-001-C01 DESC 06-30-00-001-D01 FIGURE 06-30-00-991-004-A

DESIGNATION DESC 06-30-00-001-A01-General DESC 06-30-00-001-B01-General DESC 06-30-00-001-C01-General DESC 06-30-00-001-D01-General FIGURE 06-30-00-991-004-A-Installation of the Jack Adaptors Referenced Information TABLE 2

06-30-00

Page 18 Jul 01/09


5.

Procedure WARNING : YOU MUST MONITOR AIRCRAFT STABILITY, WEIGHT AND CG DURING THE RECOVERY PROCESS. CAUTION :


CAUTION :

YOU MUST NOT USE THE SAFETY STAY TO LEVEL OR LIFT THE AIRCRAFT.

CAUTION :

BEFORE YOU LIFT OR YOU LOWER THE AIRCRAFT MAKE SURE THAT THERE IS NO EQUIPMENT ADJACENT TO IT THAT CAN CAUSE DAMAGE. MAKE SURE THAT NO OTHER WORK IS BEING DONE.

NOTE : The information or principle contained in this chapter are given as a guide to assist an aircraft recovery. Subtask 06-30-00-581-003-A01 A.

Installation of the jack adaptors (1) At the FWD jacking point, FR8: See FIGURE 06-30-00-991-004-A. (a) Examine the 98D07103500000 JACK ADAPTER - FUSELAGE (1) and make sure that there is no damage. (b) Install the 98D07103500000 JACK ADAPTER - FUSELAGE (1) at the FWD jacking point. (2) At the wing Jacking Points, RIB9: See FIGURE 06-30-00-991-004-A. (a) Remove the blanking plugs from the wing. (b) Install the dowels (3) (c) Put the 98D104000001 JACKING PAD SET (A318, A319, A320) or 98D07104081000 JACKING PAD SET (A321) (2) in position under the wing and install the bolt. (3) At the Auxiliary Jacking Point, between FR73 and FR74: See FIGURE 06-30-00-991-004-A (a) Install the 98D07103000000 DYNAMOMETER - SAFETY STAY (4) at the safety stay point.

06-30-00

Page 19 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 FR8 RIB9

A B

RIB9

B C

FR74 FR73

LOWER SURFACE

1 2

A C 01

03

3

NOTE: 01 FOR DETAILS, SEE SHEET 2 02

FOR DETAILS, SEE SHEET 3

03

FOR DETAILS, SEE SHEET 4

02

B

N_AR_063000_1_0040101_01_00

Installation of the Jack Adaptors General (Sheet 1 of 4) FIGURE-06-30-00-991-004-A01

06-30-00

Page 20 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 FR8

FITTING PART 98D07103500000

R 19.0 mm (0.75 in)

ADAPTATOR PART 98A07003906200

LOAD CELL 343A100KN2

ADAPTATOR PART 98A07003907200

JACK

N_AR_063000_1_0040102_01_00

Installation of the Jack Adaptors Forward Jacking Point (Sheet 2 of 4) FIGURE-06-30-00-991-004-A01

06-30-00

Page 21 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

JACK PAD 98D07104000001 (FOR A318, A319, A320) 98D07104081000 (FOR A321) R 32 mm (1.26 in)

ADAPTOR 98A07003911200

LOAD CELL 343A400KN2

ADAPTOR 98A07003907200

JACK

N_AR_063000_1_0040103_01_00

Installation of the Jack Adaptors Wing jacking Point (Sheet 3 of 4) FIGURE-06-30-00-991-004-A01

06-30-00

Page 22 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

19D53571595

R 19 mm (0.75 in)

LOAD CELL

98D07103000000

ADAPTATOR

SAFETY JACK

N_AR_063000_1_0040104_01_00

Installation of the Jack Adaptors Auxiliary Jacking Point - Safety Stay (Sheet 4 of 4) FIGURE-06-30-00-991-004-A01

06-30-00

Page 23 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 06-30-00-581-801-A01 General Preparation and Instructions for Leveling and Lifting the Aircraft with Jacks 1.

General This section gives the data related to the use of jacks to level and lift the aircraft: allowable loads, general preparation and instructions. NOTE : If you use jacks to level or lift the aircraft, you must put them in position on a satisfactory base. The surface must be flat and the jack must be plumb in place.

2.


3.

Job Setup References

4.

A.

General See DESC 06-30-00-001-A01DESC 06-30-00-001-B01DESC 06-30-00-001-C01DESC 06-30-00-001-D01 for the localization of the jacking points and allowable jacking loads. See TASK 06-30-00-581-802-A01 for data about the installation of a jack adaptor. When you lift the aircraft with three jacks, the weight of the aircraft must not be more than the maximum jacking weight. The maximum jacking weight is not applicable for leveling with one or two jacks but the load on each jack must not be more than the maximum allowable loads. When you lift the aircraft with jacks, it is necessary to monitor the loads at the related jacking points. You must also make sure that the wind speed is not more than the maximum allowable speed. See DESC 06-30-00-001-A01DESC 06-30-00-001-B01DESC 06-30-00-001-C01DESC 06-30-00-001-D01

B.

Aircraft Jacking Stability When you use jacks to level or lift the aircraft, you must put them in position on a satisfactory base. The surface must be flat and the jack must be plumb when it is in position. The load bearing capacity of the soil must support the loads applied at the jack footprint. You can use plywood sheets with steel plates on top to make the ground more rigid. In some conditions, it can be necessary to excavate and prepare a base of coarse gravel before you place the plywood sheets and steel plates.


Referenced Information REFERENCE TASK 06-30-00-581-802-A01 TASK 06-10-00-970-801-A01 TASK 06-10-00-970-803-A01 TASK 06-10-00-970-802-A01

DESIGNATION TASK 06-30-00-581-802-A01-Jacking TASK 06-10-00-970-801-A01-Vertical Loads Determination TASK 06-10-00-970-803-A01-Arc Movement Calculation TASK 06-10-00-970-802-A01-Side loads on Jack Fittings Determination

06-30-00

Page 24 Jul 01/09


REFERENCE TASK 02-20-02-285-801-A01 TASK 02-30-01-481-801-A01 DESC 06-30-00-001-A01 DESC 06-30-00-001-B01 DESC 06-30-00-001-C01 DESC 06-30-00-001-D01 04-30-00 03-50-01 05-50-01 05-60-00 07-60-00 AMM 07-11-00-581-001

DESIGNATION TASK 02-20-02-285-801-A01-Initial Site Survey TASK 02-30-01-481-801-A01-Installation of the Safety Devices on Landing Gears DESC 06-30-00-001-A01-General DESC 06-30-00-001-B01-General DESC 06-30-00-001-C01-General DESC 06-30-00-001-D01-General 04-30-00-TETHERING THE AIRCRAFT 03-50-01-MANAGING AIRCRAFT WEIGHT AND CG 05-50-01-CARGO REMOVAL 05-60-00-REMOVAL OF LARGE COMPONENTS 07-60-00-MOVING DAMAGED AIRCRAFT Referenced Information TABLE 1

5.

Procedure WARNING : OBEY THESE PRECAUTIONS WHEN YOU DO LEVELING/LIFTING OF THE AIRCRAFT. MAKE SURE THAT THE LIFTING EQUIPMENT IS APPLICABLE FOR THE SPECIFIC CONDITIONS. MAKE SURE THAT THE PERSONS WHO OPERATE THE LIFTING EQUIPMENT ARE CORRECTLY TRAINED AND HAVE A GOOD KNWOLEDGE OF THE SYSTEM. MAKE SURE THAT THE NECESSARY SAFETY AREA IS KNOWN AND THAT PERSONS DO NOT GO IN THIS AREA DURING THE LEVELING/LIFTING OPERATIONS. LEVELING/LIFTING OF THE AIRCRAFT CAN BE DANGEROUS IF YOU DO NOT OBEY THESE PRECAUTIONS. CAUTION :

MAKE SURE THAT THE LOADS APPLIED AT EACH JACKING POINT ARE NOT MORE THAN THE MAXIMUM ALLOWABLE LOADS.

CAUTION :


CAUTION :

IF THE LOADS APPLIED DURING THE RECOVERY PROCEDURE ARE MORE THAN THE MAXIMUM ALLOWABLE LOADS, YOU MUST CONTACT AIRBUS FOR SPECIFIC INSPECTIONS.

06-30-00

Page 25 Jul 01/09


CAUTION :


CAUTION :

YOU MUST CORRECTLY TETHER THE AIRCRAFT BEFORE YOU LEVEL OR LIFT IT.

NOTE : The information or principle contained in this chapter are given as a guide to assist an aircraft recovery. NOTE : It is the responsibility of the recovery manager to make the decision about the applicable method and related equipment/personnel for the leveling/lifting of the aircraft. Subtask 06-30-00-581-002-A01 A.

General NOTE : Before you start to level or lift the aircraft with jacks, you must make sure that the personnel know the instructions and conditions below and that they obey these instructions and conditions. (1) Do not level or lift the aircraft with jack(s) in gusty wind conditions. (2) Do not lift the aircraft with jacks during steady wind conditions. (3) Find the maximum allowable wind speed related to your aircraft configuration. See DESC 06-30-00-001-A01DESC 06-30-00-001-B01DESC 06-30-00-001-C01DESC 06-30-00-001D01. (4) Correctly tether the aircraft before leveling or lifting with jacks. This is to prevent aircraft movement that you cannot control during the leveling or lifting operation. See 04-30-00. (5) Read the manufacturer instructions related to the special jack(s) used. (6) Only the personnel who knows the operation of jacks and aircraft jacking procedures are in charge of the jacking operation. (7) Confirm the NRW and CG position. See 03-50-01. (8) Calculate the anticipated vertical load on each jacking point to be used to make sure this load is not more than the maximum allowable load. (See TASK 06-10-00-970-801-A01 and DESC 06-30-00-001-A01DESC 06-30-00-001-B01DESC 06-30-00-001-C01DESC 06-30-00-001-D01) If the necessary load on the jacking point is more than the allowable load for that jacking point, reduce the aircraft weight until the lifting load is less than the allowable load or make a selection of different leveling or lifting procedure.

06-30-00

Page 26 Jul 01/09


(9) Make sure each available jack can support the necessary load (vertical and side), arc movement and travel range. Also make sure it can be put in the boundaries of the fuselage or wing jacking points. To reduce the necessary lifting load, it is recommended to reduce the aircraft weight with the removal of cargo or payload from the aircraft before a leveling or lifting operation (See 05-50-01 and 05-60-00). (10) Calculate the expected arc movement at each jacking point during the leveling operation. (See TASK 06-10-00-970-803-A01) Calculate the side load if necessary. (See TASK 06-10-00-970-802-A01) (11) If the jack cannot move along the necessary arc movement, you must calculate the expected side load on the jacking point and make sure the expected side load is not more than the allowable load on the jacking point. (12) Install fittings and/or jack pad adapters at the necessary jacking points. See TASK 06-30-00-581-802-A01. (13) If necessary, excavate a sufficiently large area to make a stable platform as a base for each jack. Make sure that the ground/soil can support the load at each jack footprint, and that will stay stable during the leveling or lifting operation. See TASK 02-20-02-285-801-A01) Make a platform that is satisfactory for the jack height when in compressed position. Make sure that the platform is sufficiently large to change the position of the jack during the leveling operation if necessary. If the jack in the extended position cannot lift the aircraft sufficiently, it is necessary to make a timber platform that is sufficiently high. (14) Put wheel chocks in front of and behind the wheels of each extended landing gear in contact with the ground. (15) Install the landing gear downlock pins in all extended landing gears. See TASK 02-30-01-481-801-A01. (16) Put each jack in position below the jacking point and extend the jack to engage it in the fitting. (17) Before you start the jacking operation, we recommend that you mark the values of the necessary lifting load to be applied on the jack on each load cell indicator (use a strip of colored adhesive tape for example). Also, we recommend that you mark the maximum allowable load of each jacking point to prevent overload. This gives the recovery personnel better visibility from the ground. (18) Each jack operator must have a good visibility to the person in charge of the lifting operation. Coordination between all jack operators is very important. Two-way voice activated headsets are very good for this type of operation. (19) You must use and monitor plumb bobs and levels during a leveling or lifting operation. (20) Monitor the CG during the full leveling procedure and be prepared to control with ballast if necessary. See 03-50-01.

06-30-00

Page 27 Jul 01/09


(21) If you use tethers, they must be adjusted and the loads must be monitored when you level or lift the aircraft. (22) Install aft tipping protection if necessary. (23) When you use a jack at the safety stay position to make the aircraft stable, you must monitor the jack and correctly adjust the loads. (24) Make sure the loads at each jack are not more than the allowable loads and that you record all the loads applied. See DESC 06-30-00-001-A01DESC 06-30-00-001-B01DESC 06-30-00-001-C01DESC 06-30-00-001-D01. (25) Level the aircraft: (a) With a special recovery jack: If you use a special recovery jack that can move along the arc movement, make sure the jack can do the necessary arc movement to level the aircraft. Include side loads caused by the jack. If the jack cannot do the total necessary arc movement, gradually level the aircraft in small steps and change the position of the jack between each step. (b) With a standard jack: If the jack cannot sufficiently move along the arc movement or if you use a standard jack, gradually level the aircraft in small steps and change the position of the jack between each step. - Start jacking until you get the maximum jack extension or maximum arc movement. - Lock the jack at this position and make sure the aircraft is in a stable configuration. - At the same time, make shoring under the closest load bearing frame or frames and make sure the loads are not more the maximum allowable loads. - Compress the jack, make the necessary stable-base platform and change the position of the jack. Do the procedure again until the aircraft is level. NOTE : If possible, you should use a special recovery jack. Step by step leveling is not the recommended method to level the aircraft. (26) It is possible to use axle jacks with shoring and timber bases at the primary jacking points to lift the aircraft to the height where recovery jacks can be fitted. This is not a recommended procedure because of the limited arc movement capacity of the jack. (27) When the fuselage and wings are level, and if it is necessary to lift the aircraft, use the 3 primary jacking points to lift the aircraft to the necessary height. (See AMM 07-11-00-581-001) Do not lift the aircraft until all the aircraft (wings and fuselage) is in a level attitude. (28) When the aircraft is at the necessary height: (a) Make shoring to support the fuselage and/or wings, or leave the jacks in place as a safety measure during work on the landing gears.

06-30-00

Page 28 Jul 01/09


(b) Extend the landing gear(s) and install the downlock pin(s). (c) Or repair or replace the landing gear(s). (d) Or, if it is not possible to make the landing gear(s) serviceable, place the forward fuselage and/or the wing(s) on a mobile device. See 07-60-00.

06-30-00

Page 29 Jul 01/09


06-40-00

USE OF PNEUMATIC LIFTING BAGS


This section gives data about the use of pneumatic lifting bags for leveling and lifting : location of bearing areas, allowable loads, general preparation and instructions. Pneumatic lifting bags have different sizes and lifting capacities. In general, multiple-element pneumatic lifting bags with internal drop threads are the most usual. Single-element pneumatic lifting bags (balloon bags) are not recommended as floating loads could appear. Operator must have a specific training to operate the equipments. You must know and obey the operating instructions given by the manufacturer of the pneumatic lifting bags. For leveling and lifting on the fuselage, see DESC 06-40-00-001-A01. For leveling and lifting on wings, see DESC 06-40-00-003-A01. For general information and instruction related to the use of pneumatic lifting bags, see TASK 06-40-00-581-801-A01.

06-40-00

Page 1 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 06-40-00-001-A01 Pneumatic Lifting Bags on Fuselage 1.

For the leveling and lifting of the fuselage with pneumatic lifting bags, contact AIRBUS. CAUTION :

MAKE SURE THAT THE PNEUMATIC LIFTING BAGS APPLY LOADS IN THE BEARING AREA ONLY. IF THE LIFTING BAGS APPLY LOADS OUT OF THE LIMITS OF THE BEARING AREA, SECONDARY DAMAGE CAN OCCUR.

CAUTION :

MAKE SURE THAT THE PNEUMATIC LIFTING BAGS DO NOT APPLY LOADS ON THE BELLY FAIRING STRUCTURE. IF NECESSARY, REMOVE THE BELLY FAIRINGS AND THE BELLY FAIRING STRUCTURE TO GET ACCESS TO THE ALLOWABLE BEARING AREA.

CAUTION :

DO NOT PUT THE LIFTING BAGS UNDER PROTRUDING STRUCTURES (FLAP TRACKS,PYLON FAIRINGS, ETC.), SHARP EDGES OR ANGLES BECAUSE THEY CAN CAUSE DAMAGE TO THE LIFTING BAGS.

06-40-00

Page 2 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 06-40-00-003-A01 Pneumatic Lifting Bags on Wings 1.

Bearing Areas on Wing Lower Surface CAUTION :


CAUTION :

MAKE SURE THAT THE LOADS ON THE AIRFRAME ARE LESS THAN THE ALLOWABLE LOADS WHEN YOU USE SUPPORTS. THE SUPPORTS APPLY LOADS THAT DO NOT OCCUR IN NORMAL OPERATION.

CAUTION :

DO NOT PUT THE LIFTING BAGS UNDER PROTRUDING STRUCTURES (FLAP TRACKS,PYLON FAIRINGS, ETC.), SHARP EDGES OR ANGLES BECAUSE THEY CAN CAUSE DAMAGE TO THE LIFTING BAGS. This part gives data about the installation of pneumatic lifting bags under the wings. A.

Location Pneumatic lifting bags can be installed under the wing lower surfaces between Rib 1 and Rib 17*, see FIGURE 06-40-00-991-001-A.

B.

Restricted Areas The limits of the allowable bearing areas for the pneumatic lifting bags are shown in FIGURE 06-40-00-991-003-A.

C.

Allowable Loads Bearing Area Rib 1 to Rib 17

Maximum Allowable Pressure hPa PSI 7 480 Maximum Allowable Pressure

Bar 0.48

TABLE 1 D.

After you use pneumatic lifting bags on wings for leveling/lifting of the aircraft, you must do an inspection of the wing tank access panels in the contact area. Report any sign of damage.

06-40-00

Page 3 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

RIB17

RIB1 FRONT SPAR

REAR SPAR FWD

A

LH SHOWN RH SYMMETRICAL BEARING AREA ON WING LOWER SURFACE (7PSI)

CAUTION: MAKE SURE THAT THE PNEUMATIC LIFTING BAGS APPLY LOADS IN THE BEARING AREA ONLY. IF THE PNEUMATIC LIFTING BAGS APPLY LOADS OUT OF THE LIMITS OF THE BEARING AREA, SECONDARY DAMAGE CAN OCCUR. N_AR_064000_1_0010101_01_00

Pneumatic Lifting Bags on Wings Bearing Area on Wing Lower Surface FIGURE-06-40-00-991-001-A01

06-40-00

Page 4 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

RIB17

RIB13 RIB12

JACKING POINT RESTRICTED AREA

WING JACKING POINT RIB8

RIB6

RIB1 FRONT SPAR FWD

A

REAR SPAR

LH SHOWN RH SYMMETRICAL BEARING AREA ON WING LOWER SURFACE CAUTION: MAKE SURE THAT THE PNEUMATIC LIFTING BAGS APPLY LOADS IN THE BEARING AREA ONLY. IF THE PNEUMATIC LIFTING BAGS APPLY LOADS OUT OF THE LIMITS OF THE BEARING AREA, SECONDARY DAMAGE CAN OCCUR.

NOTE: THE JACK FOOTPRINT IS MEASURED FROM THE CENTERLINE OF THE JACK TO THE CENTERLINE OF THE TRIPOD FOOT. THE FOOTPRINT IS RELATED TO THE TYPE OF JACK. IT IS IMPORTANT TO KNOW THE FOOTPRINT OF THE JACK YOU WILL USE BEFORE YOU PUT THE LIFTING BAG(S) IN POSITION. N_AR_064000_1_0030101_01_00

Pneumatic Lifting Bags on Wings Wing Restricted Area FIGURE-06-40-00-991-003-A01

06-40-00

Page 5 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 06-40-00-581-801-A01 General Preparation and Instructions for Leveling and Lifting the Aircraft with Pneumatic Lifting Bags 1.

General This section gives the data about the use of pneumatic lifting bags for leveling and lifting: allowable loads, general preparation and instructions. NOTE : If you use pneumatic lifting bags to level or lift the aircraft they must be put in position on a stable base. The surface must be flat.

2.


3.

Job Setup References Pneumatic lifting bag movement is related to the attitude of the aircraft. See TBD for data about the applicable scenario.

4.


Referenced Information REFERENCE TASK 06-10-00-970-801-A01 TASK 06-10-00-970-803-A01 TASK 02-30-01-481-801-A01 DESC 06-00-00-002-A01 04-30-00 03-00-00 05-00-00 06-10-00 04-50-00 03-20-01 06-30-00 07-60-00 AMM 07-11-00-581-001

DESIGNATION TASK 06-10-00-970-801-A01-Vertical Loads Determination TASK 06-10-00-970-803-A01-Arc Movement Calculation TASK 02-30-01-481-801-A01-Installation of the Safety Devices on Landing Gears DESC 06-00-00-002-A01-Leveling/Lifting Obstructions 04-30-00-TETHERING THE AIRCRAFT 03-00-00-WEIGHT AND CG MANAGEMENT 05-00-00-WEIGHT REDUCTION 06-10-00-LOAD DETERMINATION 04-50-00-SOIL STABILITY 03-20-01-FUEL LOAD AND CG CONTROL 06-30-00-USE OF JACKS 07-60-00-MOVING DAMAGED AIRCRAFT Referenced Information TABLE 1

06-40-00

Page 6 Jul 01/09


5.



CAUTION :

THE STIFFNESS AND LATERAL STABILITY OF PNEUMATIC LIFTING BAG CAN CHANGE DURING THE INFLATION PROCESS OF THE PNEUMATIC LIFTING BAG STACK. IT IS THE RESPONSIBILITY OF THE PNEUMATIC LIFTING BAG MANUFACTURER TO PROVIDE ADEQUATE DATA ON THE USE OF ITS LIFTING BAGS. IT IS THE RESPONSIBILITY OF THE RECOVERY MANAGER TO MAKE SURE THAT USE OF THE PNEUMATIC LIFTING BAG WILL NOT LEAD TO AIRCRAFT MOVEMENT DUE TO THE INFLUENCE OF WIND AND/OR CHANGE OF CG POSITION DURING AIRCRAFT LIFTING/LEVELING.

CAUTION :


CAUTION :


CAUTION :

DO NOT PUT THE LIFTING BAGS UNDER PROTRUDING STRUCTURES (FLAP TRACKS,PYLON FAIRINGS, ETC.), SHARP EDGES OR ANGLES BECAUSE THEY CAN CAUSE DAMAGE TO THE LIFTING BAGS.

CAUTION :

MAKE SURE THAT THE PNEUMATIC LIFTING BAGS DO NOT APPLY LOADS ON THE BELLY FAIRING STRUCTURE. IF NECESSARY, REMOVE THE BELLY FAIRINGS AND THE BELLY FAIRING STRUCTURE TO GET ACCESS TO THE ALLOWABLE BEARING AREA.

06-40-00

Page 7 Jul 01/09


CAUTION :


CAUTION :


NOTE : The information or principle contained in this chapter are given as a guide to assist an aircraft recovery. NOTE : It is the responsibility of the recovery manager to make the decision about the applicable method and related equipment/personnel for the leveling/lifting of the aircraft. Subtask 06-40-00-581-001-A01 A.

General NOTE : Before you start to level or lift the aircraft with pneumatic lifting bags, you must make sure that the personnel know the instructions and conditions below and that they obey these instructions and conditions. (1) Read the pneumatic lifting bag manufacturer instructions applicable to the pneumatic lifting bags that you use. (2) Only the personnel that knows the operation of pneumatic lifting bags and aircraft jacking procedures should be in charge of the pneumatic lifting bags operation. (3) Do not lift the aircraft with pneumatic lifting bags in gusty wind conditions. Follow the manufacturer limitations. (4) Do not lift the aircraft with pneumatic lifting bags during steady wind conditions. Follow the manufacturer limitations. (5) Correctly tether the aircraft before leveling or lifting with pneumatic lifting bags. This is to prevent aircraft movement that you cannot control during the leveling or lifting operation. See 04-30-00. (6) Confirm the aircraft NRW and CG. See 03-00-00. (7) Calculate the anticipated vertical load on each lifting bag position to be used to make sure the necessary load is not more than the maximum allowable load on the skin. See TASK 06-10-00-970-801-A01. If the necessary load on the bearing area of the pneumatic lifting bag is more than the allowable load for that leveling/lifting point, reduce the aircraft weight until the lifting load is less than the allowable load or install additional pneumatic lifting bags to increase contact surface to reduce applied loads or make a selection of another leveling or lifting procedure.

06-40-00

Page 8 Jul 01/09


(8) Calculate the total lift of each pneumatic lifting bag used. Make sure each available lifting bag can support the necessary loads (vertical and side), arc movement and travel range, and can fit in the limits of the fuselage or wing contact zone. To reduce the necessary leveling/lifting load, we recommend that you reduce the aircraft weight with the removal of cargo and/or fuel if necessary (05-00-00) from the aircraft before a leveling/lifting operation, see 06-10-00. (9) Calculate the expected arc movement during the leveling/lifting operation, at the center of the bearing area of each pneumatic lifting bag . Also calculate the side load if necessary, see 06-10-00. (10) Before you use pneumatic lifting bags, do an inspection of the structure to make sure there is no damage in the leveling/lifting area. If there is damage, the pneumatic lifting bags must be installed at least at one non-damaged rib/fuselage frame away from the damaged area. Remove all sharp edges from the contact area. Use a heavy tarpaulin or foam rubber mattress between the aircraft skin and the pneumatic lifting bag to prevent damage. (11) Put the pneumatic lifting bags in the allowable bearing areas, and make sure no sharp edges or peaks (damaged skin , protruding structure, antennas ...) are in the area where the bags will be installed. (12) Remove some unwanted items (antennas, ...) from the aircraft before you install the pneumatic lifting bags, see DESC 06-00-00-002-A01. (13) If necessary, excavate a sufficiently large area to make a stable base for the pneumatic lifting bags. Make sure that the ground/soil can support the load at each lifting bag footprint, and will stay stable during the leveling/lifting operation, see 04-50-00. Make a satisfactory base for the height of the compressed pneumatic lifting bags. Make sure that the base is sufficiently large to change the position of the pneumatic lifting bags during the leveling/lifting operation if necessary. If the inflated pneumatic lifting is not sufficiently high to lift the aircraft, it will be necessary to make a sufficiently high platform. It is possible to make this platform with timber or to use an inflatable type platform. (14) The arc movement will cause a transversal translation of the aircraft. If this movement is more than the allowable limit of the pneumatic lifting bag (see manufacturer instructions), a leveling/lifting operation with several steps is necessary to reposition the pneumatic lifting bags. The use of a secondary method of lifting (for example jacks) is necessary. (15) If necessary, put wheel chocks in front and behind the wheels of each landing gear that is extended and in contact with the ground. (16) If possible, install landing gear downlock pins in all landing gears that are extended. (17) Each operator at the pneumatic-lifting bag control console must have a good visibility of the leveling/lifting operation. Coordination between all the console operators is very important. Two-way voice headsets are recommended for this type of operation. (18) No personnel must be in or below the aircraft during the leveling/lifting process.

06-40-00

Page 9 Jul 01/09


(19) Movement of fuel in the wing tanks because of aircraft leveling/lifting can cause a change in the aircraft CG position. It is thus recommended that all fuel is removed from the aircraft before leveling/lifting, see 03-20-01. This will also reduce the necessary lifting loads. (20) Anticipate the CG movement before you start the leveling/lifting process and be prepared to control with ballast. (21) Monitor and record the applied loads (pressure in the pneumatic lifting bags) at all times during the leveling/lifting process. (22) Before the leveling/lifting operation, make an estimate of the arc movement, see TASK 06-10-00-970-803-A01. During the leveling/lifting operation, you must monitor the lateral translation of the aircraft (with the use of a plumb-line) and compare it to the calculation and the pneumatic lifting bag limitations (see manufacturer instructions) to prevent any aircraft sudden movement or sliding. (23) Install aft tipping protection if necessary. (24) Before you inflate the pneumatic lifting bags, make sure that you know all the warnings and safety precautions. Make sure that all equipment (such as shoring material or jacks) is prepared and available to use. (25) Obey the manufacturer’s instructions: inflate the lifting bags slowly and adjust the tethers when the aircraft starts to move. (26) When the fuselage and wing are level, and if the aircraft needs to be lifted, it is recommended to use the 3 jacking points to lift the aircraft to the necessary height, see AMM 07-11-00-581-001. It is mandatory that the aircraft is in a level attitude (wing and fuselage) before you lift it. (27) When the aircraft is at the necessary height: (a) Use shoring to support the fuselage and/or wings, or install jacks (see 06-30-00) as a safety measure during any work on the landing gears. (b) Extend the landing gear(s) and install downlock pin(s), see TASK 02-30-01-481-801A01, (c) Or repair or replace the landing gear(s), (d) Or, if it is not possible to make the landing gear(s) serviceable, place the forward fuselage and/or the wing(s) on a mobile device, see 07-60-00. (28) After the recovery process, do an inspection of the skin in the contact areas of the pneumatic bag for scratches, nicks and gouges caused by sand or stones trapped between the contact surfaces. You must also do an inspection of the wing tank access panels in the contact area. Report any sign of damage.

06-40-00

Page 10 Jul 01/09


06-50-00

USE OF CRANES


This chapter gives detail on the use of cranes for leveling or lifting the aircraft. The lifting of an aircraft with crane is a specific lifting procedure with specific tools, accurate engineering planning and risk/hazard assessment. A process management chart gives all the steps of the crane lifting, see FIGURE 06-50-00-991-020-A. See TASK 06-50-00-581-803-A01 for lifting by the forward fuselage. See TASK 06-50-00-581-802-A01 for lifting by the wings. See TASK 06-50-00-581-801-A01 for general preparation and instruction for leveling and lifting with cranes. NOTE : The information or principle contained in this chapter are given as a guide to assist an aircraft recovery.

06-50-00

Page 1 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

CRANE LIFTING PROCESS

DO A CHECK OF THE STRUCTURAL INTEGRITY OF MOORING FITTINGS, ATTACHMENT CABLE SYSTEMS AND CARDAN PIN EYE END OF THE LG SIDE STAY MOUNTING BRACKET

RECORD WEATHER CONDITIONS

MAKE SURE THAT THE SOIL IS STABLE

CALCULATE CG AND DECREASE WEIGHT IF NECESSARY

CALCULATE THE LOADS THAT WILL BE APPLIED

PLAN PREPARATION MEETING

PLAN TOOLING INSTALLATION AND LIFTING PROCEDURE

DO THE LIFTING AS PLANNED

N_AR_065000_1_0200101_01_02

Crane Lifting Process Management Chart FIGURE-06-50-00-991-020-A01

06-50-00

Page 2 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 06-50-00-581-803-A01 Forward Fuselage Crane Lifting 1.

General This section gives the data related to the leveling and lifting from the forward fuselage with cranes.

2.


3.

Job Setup References There are two methods to lift the forward fuselage with cranes and slings: - With a spreader beam and a strap installed at FR15 or FR20, see SUBTASK 06-50-00-581-002A01. - With mooring fittings installed at FR15, see SUBTASK 06-50-00-581-003-A01. You can use this task in combination with the Wing Crane Lifting procedure (see TASK 06-50-00-581-802-A01) or one other lifting method (jacking or use of pneumatic lifting bags). A.

Straps / slings The straps touch directly the aircraft fuselage skin. They must be made from soft nylon to prevent scratches and gouges. The minimum width of the straps must be 200 mm (8 in). The two ends of the straps must have adapted loops for attachment to the crane hook or spreader bar. The straps must be in good condition without broken fibers, cuts, nicks or gouges.

B.

Transversal Spreader Beam If only one crane is available, you can use a spreader beam between each end of the sling. The distance between the hook attachment points of the slings on the spreader beam must be equal to 3950 mm (155.51 in) to have a sling angle of 180˚ around the lower fuselage. See FIGURE 06-50-00-991-014-A If this distance is less than 3950 mm (155.51 in), this can cause lateral loads and secondary damage can occur on the fuselage sides. If this distance is more than 3950 mm (155.51 in), the contact surface between the fuselage and the strap will not be sufficient and excessive loads can be applied on the lower fuselage.

C.

Crane The crane must be able to hold the maximum lifting load. It is recommended that you use a crane with at least a 11 m (433.07 in) high jib.

D.

Allowable Loads The maximum lifting load on FR15 or Fr 20 is 6700 daN (150.62 lbf). See FIGURE 06-50-00-991-021-A to find the lifting load on FR15 or FR20 related to the aircraft weight and CG position.

06-50-00

Page 3 Jul 01/09


4.


Fixtures, Tools, Test and Support REFERENCE 98D07203000

DESIGNATION MOORING FITTING Fixtures, Tools, Test and Support TABLE 1

B.

Referenced Information REFERENCE TASK 06-50-00-581-802-A01 TASK 06-50-00-581-801-A01 06-40-00 FIGURE 06-50-00-991-014-A FIGURE 06-50-00-991-021-A FIGURE 06-50-00-991-015-A

DESIGNATION TASK 06-50-00-581-802-A01-Wing Crane Lifting TASK 06-50-00-581-801-A01-General Preparation and instructions for Leveling and Lifting th 06-40-00-USE OF PNEUMATIC LIFTING BAGS FIGURE 06-50-00-991-014-A-FWD Fuselage Crane Lifting FIGURE 06-50-00-991-021-A-FWD Fuselage Crane Lifting FIGURE 06-50-00-991-015-A-FWD Fuselage Crane Lifting Referenced Information TABLE 2

5.


Strap installation at FR15 or FR20 (1) Use a strap with a minimum length of 10300 mm (405.51 in). See FIGURE 06-50-00-991-014-A for minimum dimensions of the strap and approximate lifting height. (2) Install the strap at FR15 or FR20. The attitude of the aircraft (clearance to install strap) or the weight and CG condition will be the basic data for the selection of the frame. NOTE : During the lifting operation, the loads applied to FR20 will be more than the load applied to FR15. (3) With one crane, the jib head must be vertically aligned with the fuselage centerline and the frame position (FR15 or FR20). With two cranes, the jib heads must be vertically aligned with each side of the fuselage and the frame position (FR15 or FR20). (4) Attach the slings to each crane if you use two cranes. Or Attach the spreader bar to the single crane and attache the straps to the spreader beam.

06-50-00

Page 4 Jul 01/09


(5) See TASK 06-50-00-581-801-A01 for the general instructions for leveling and lifting with cranes. It is recommended to install a pneumatic lifting bag (see 06-40-00) below the aft fuselage to prevent tail tipping. (6) Lift the aircraft very slowly and avoid any dynamic effort. If other cranes or lifting method are used simultaneously, make sure that all the operators work at the same time. The use of a two-way speaking system is recommended. Subtask 06-50-00-581-003-A01 B.

Fitting installation at FR15 (1) At FR15, remove the blanking screw. (2) Install the 98D07203000 MOORING FITTING - 042 at FR15 LH and 98D07203000 MOORING FITTING - 043 at FR15 RH. See FIGURE 06-50-00-991-015-A. (3) If you use one crane with the spreader beam: (a) Attach the spreader beam to the crane. (b) Attach the slings to the spreader beam. (c) Put the crane in position. Make sure that the jib is directly above the fuselage centerline. (d) Attach the slings to the fittings at FR15 LH/RH. It is recommended that you install load cells on the slings to monitor the loads during the leveling/lifting operation. (4) If you use two cranes: (a) Attach the slings to each crane. (b) Put both cranes in position. Make sure that each jib head is directly above FR15 LH/RH. (c) Attach the slings to the fittings at FR15 LH/RH. It is recommended that you install load cells on the slings to monitor the loads during the leveling/lifting operation. (5) See TASK 06-50-00-581-801-A01 for the general instructions for leveling and lifting with cranes. It is recommended to install a pneumatic lifting bag (see 06-40-00) below the aft fuselage to prevent tail tipping.

06-50-00

Page 5 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

1.975 m (6.48 ft)

3.95 m (12.95 ft)

CL

1.975 m (6.48 ft)

180° SLING ANGLE

6.20 m (20.34 ft)

N_AR_065000_1_0140101_01_02

FWD Fuselage Crane Lifting Strap at FR15 or FR20 FIGURE-06-50-00-991-014-A01

06-50-00

Page 6 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

7 HOLES

A

3.95 m (12.95 ft)

2.37 m (7.76 ft)

10.10 m (31.14 ft)

=

=

CL

FDL

A

A

HOISTING USING 1 CRANE: UTILISATION OF FITTING SLINGS AND HOISTING BEAM

HOISTING USING 2 CRANES: UTILISATION OF FITTING AND SLINGS N_AR_065000_1_0150101_01_00

FWD Fuselage Crane Lifting Fittings at FR15 FIGURE-06-50-00-991-015-A01

06-50-00

Page 7 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 LOADS AT FR15 OR FR20 100 kg 100 lb

CG 15%

242 110

CG 20% CG 25%

220 100

198

90 CG 30%

176

80

154

70

132

60

110

50

88

40

66

30

44

20

22

10

MAXIMUM LOAD FOR LIFTING BY SLINGS = 6700 kg (14771 lb)

30

40 80

50 100

60 120

70 140

160

80 180

CG 35%

90

100

200

220

AIRCRAFT WEIGHT 1000 kg 1000 lb

N_AR_065000_1_0210101_01_00

FWD Fuselage Crane Lifting Reaction at FR15 or FR 20 for Lifting by Sling (Sheet 1 of 2) FIGURE-06-50-00-991-021-A01

06-50-00

Page 8 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 LOADS AT FR15 100 lb 100 kg

CG 15%

242 110

CG 20%

220 100 CG 25% 198

90

176

80

154

70

CG 30%

MAXIMUM LOAD AT FRAME 15 FOR LIFTING BY 2 FITTINGS = 6700 kg (14771 lb)

132

60

110

50

88

40

66

30

44

20

22

10

30

40 80

50 100

60 120

70 140

160

80 180

CG 35%

90

100

200

220

AIRCRAFT WEIGHT 1000 kg 1000 lb

N_AR_065000_1_0210102_01_00

FWD Fuselage Crane Lifting Reaction at FR15 for Lifting by Mooring Fittings (Sheet 2 of 2) FIGURE-06-50-00-991-021-A01

06-50-00

Page 9 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 06-50-00-581-802-A01 Wing Rib Attachment Tool 1.

General This task gives the procedure to install and lift the aircraft with the 7K804427D520 CRANE ATTACHMENT - WING LIFTING BRACKET attachment tool.

2.

Inspections Do a detailed visual inspection of the wing and specially of the side stay mounting bracket and the cardan pin. Report any sign of damage (nick, crack, etc.). In case of damage, contact AIRBUS.

3.

Job Setup References This procedure gives details to level/lift the aircraft by the wings when one or the two main landing gear(s) or all the landing gears are retracted, collapsed or missing. See TASK 06-50-00-581-803-A01. You can use this task in combination with the Forward-Fuselage Crane Lifting procedure (see TASK 06-50-00-581-803-A01) or one other lifting method (jacking or use of pneumatic lifting bags).

4.

A.

Allowable loads The maximum allowable lifting load on each cardan pin eye-end is 25500 daN (56200 lbf).

B.

Limitations To do this procedure, the pitch or roll angle of the aircraft must be less than 10˚. If the pitch or roll angle is more than 10˚, lateral loads can be applied to the mounting bracket and secondary damage can occur. Contact AIRBUS to determine an alternative solution.


Fixtures, Tools, Test and Support REFERENCE 7K804427D520

DESIGNATION CRANE ATTACHMENT - WING LIFTING BRACKET Fixtures, Tools, Test and Support TABLE 1

B.

Referenced Information REFERENCE TASK 06-50-00-581-803-A01 TASK 02-30-01-481-801-A01 TASK 06-50-00-581-801-A01 03-00-00 06-10-00

DESIGNATION TASK 06-50-00-581-803-A01-Forward Fuselage Crane Lifting TASK 02-30-01-481-801-A01-Installation of the Safety Devices on Landing Gears TASK 06-50-00-581-801-A01-General Preparation and instructions for Leveling and Lifting th 03-00-00-WEIGHT AND CG MANAGEMENT 06-10-00-LOAD DETERMINATION

06-50-00

Page 10 Jul 01/09


REFERENCE FIGURE 06-50-00-991-016-A FIGURE 06-50-00-991-018-A FIGURE 06-50-00-991-013-A

DESIGNATION FIGURE 06-50-00-991-016-A-Cardan Pin FIGURE 06-50-00-991-018-A-Crane Lifting FIGURE 06-50-00-991-013-A-Over wing Panel Referenced Information TABLE 2

5.

Procedure WARNING : BE CAREFUL WHEN YOU DO THIS PROCEDURE. OBEY THE EQUIPMENT MANUFACTURERS’ HEALTH AND SAFETY INSTRUCTIONS AND YOUR LOCAL REGULATIONS. INJURY CAN OCCUR IF YOU DO NOT OBEY THESE INSTRUCTIONS. CAUTION :

BEFORE YOU USE THE WING RIB ATTACHMENT TOOL, YOU MUST DO A FULL INSPECTION OF THE WING. IF YOU FIND DAMAGE, YOU MUST NOT USE THE WING RIB ATTACHMENT TOOL TO LIFT THE AIRCRAFT.

CAUTION :

THE ANGLE OF THE LIFTING CABLE AT MLG POSITION MUST NOT BE MORE THAN 10 DEGREES IN ANY DIRECTION. THIS CAN CAUSE DAMAGED TO THE TOP WING SKIN AND THE STRUCTURE.

Subtask 06-50-00-010-001-A01 A.

Preparation WARNING : BEFORE YOU START WORK ON THE WINGS, PYLONS OR LANDING GEAR, YOU MUST PUT ON AND ATTACH A SAFETY HARNESS. WITHOUT A SAFETY HARNESS, YOU CAN FALL. THIS CAN KILL YOU OR CAUSE YOU INJURY. WARNING : YOU MUST MONITOR AIRCRAFT STABILITY, WEIGHT AND CG DURING THE RECOVERY PROCESS. (1) Before you start work, make sure that: - The aircraft is stable - The aircraft defueled, if necessary or possible - The electrical systems are de-energized - The hydraulic systems are de-pressurized - No weight or load is applied to the main landing gears before you disconnect the side stay assembly. If weight or load is applied to the main landing gears, you must support the wings with jacks, pneumatic lifting bags, shoring cradles or a combination of these. (2) Calculate the weight and CG of the aircraft, see 03-00-00.

06-50-00

Page 11 Jul 01/09


(3) Calculate the lifting loads at each attachment position, see 06-10-00. (4) Make sure that the lifting loads are not more than the allowable load of the cardan pin eye-end. Subtask 06-50-00-581-004-A01 B.

Installation of the Crane Attachment WARNING : THE MAIN LANDING GEAR WILL NOT SUPPORT THE WEIGHT OF THE AIRCRAFT WHEN THE SIDE-STAYS ARE DISCONNECTED. ONCE LIFTED, YOU MUST SUPPORT THE AIRCRAFT WITH JACK, PNEUMATIC LIFTING BAGS, SHORING CRADLES OR A COMBINATION OF THESE. ALTERNATIVELY, PUT THE AIRCRAFT ON A SUITABLE ADAPTED FLATBED TRAILER FOR TOWING AWAY FROM THE CRASH SITE. (1) Get access to the upper cardan pin of the MLG side-stay, use one of the methods that follow: - Remove the overwing panel Or - Cut an access hole in the overwing panel to the dimension of the 7K804427D520 CRANE ATTACHMENT - WING LIFTING BRACKET with sufficient clearance, see FIGURE 06-50-00-991-013-A. WARNING : BE CAREFUL WHEN YOU REMOVE COMPONENTS FOR ACCESS. BEFORE YOU REMOVE THE COMPONENTS, MAKE SURE THAT THE RELATED SYSTEM(S) IS(ARE) DE-ENERGIZED/DEPRESSURIZED. IF YOU USE TOOLS TO REMOVE COMPONENTS, MAKE SURE THAT YOU DO NOT CAUSE DAMAGE TO THE ADJACENT STRUCTURE OR SYSTEMS. (2) Remove all the pipes, ducts or electrical wirings that can touch the lifting bracket when installed. (3) Make sure that the aircraft is fully supported and no load is applied to the landing gears. (4) Disconnect the MLG side-stay assembly from the eye-end attachment of the upper cardan pin as follow (see FIGURE 06-50-00-991-016-A): (a) Unlock the tab washer and remove the attachment bolt. (b) Remove the two end caps. (c) Remove the pin from the attachment joint. (d) Disconnect the MLG side-stay from cardan pin eye-end attachment. WARNING : BE CAREFUL WHEN YOU HANDLE THIS EQUIPMENT. THIS EQUIPMENT IS HEAVY (MORE THAN 12KG (26.5 LB)) AND CAN CAUSE INJURY AND/OR DAMAGE.

06-50-00

Page 12 Jul 01/09


(5) Put the 7K804427D520 CRANE ATTACHMENT - WING LIFTING BRACKET in position on the eye-end of the upper cardan pin. See FIGURE 06-50-00-991-018-A. NOTE : You can attach the bracket to the crane with the sling first to help you install the tool on the aircraft. (6) Install the pin on the eye-end of the cardan pin and through the lifting bracket. NOTE : The pin dimension can change with aircraft variants. Make sure that you use the correct pin through the eye-end of the cardan pin and lifting bracket. The thread of the pin is 87 mm (3.43 in) for A318, A319, A320 and A321-100 and is 27 mm (1.06 in) for A321-200. (7) Install the safety bolt to safety the pin. (8) Make sure that the MLG and its attachment are safe and will no move during the recovery operation. If necessary and if possible, use cable slings or other attachment system (see TASK 02-30-01-481-801-A01 for the installation of the L/G safety devices) to safely attach the main landing gear and prevent sudden retraction. (9) If it is necessary to lift the two wings of the aircraft, do again the steps for the other wing. Subtask 06-50-00-581-005-A01 C.

Lifting WARNING : THE AIRCRAFT MUST NOT REST ON ITS MAIN LANDING GEAR WHEN YOU LIFT THE WING WITH THE CRANE LIFTING BRACKET. THE MLG WILL NOT SUPPORT THE WEIGHT OF THE AIRCRAFT AND CAN COLLAPSE. CAUTION :

THE ANGLE OF THE LIFTING CABLE AT MLG POSITION MUST NOT BE MORE THAN 10 DEGREES IN ANY DIRECTION. THIS CAN CAUSE DAMAGED TO THE TOP WING SKIN AND THE STRUCTURE.

CAUTION :

YOU MUST DO THE LATERAL LEVELING BEFORE YOU DO THE LONGITUDINAL LEVELING.

(1) Attach the lifting cables to the mobile crane(s). (2) Put the crane(s) in position. Make sure that the jib head of the crane is directly above the lifting bracket. (3) Attach the lifting cables to the lifting bracket. See FIGURE 06-50-00-991-018-A for an example of general configuration. (4) See TASK 06-50-00-581-801-A01 for the general instructions for leveling and lifting with cranes. (5) Level the aircraft wings.

06-50-00

Page 13 Jul 01/09


(6) If necessary, level the aircraft fuselage. See TASK 06-50-00-581-803-A01. (7) Lift the aircraft: (a) Make sure that the aircraft is always level during the lifting operation. (b) Make sure that the angle of the lifting cable is not more than 10 degrees from the vertical in all directions. See FIGURE 06-50-00-991-018-A. (8) During the complete leveling and lifting operation, use load cells to monitor the loads and make sure that the loads applied are not more than the maximum allowable loads. (9) When the lifting is completed, install the aircraft on prepared supports (jacks, pneumatic lifting bags, recovery trailers, etc.).

06-50-00

Page 14 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

EDGE OF FAIRING SEAL

610 mm (24 in) 100 mm (3.93 in) 100 mm (3.93 in)

10 mm (0.39 in) FROM AFT EDGE OF JOINT STRIP 30 mm (1.18 in) FROM CENTRE OF STIFFENER FASTENERS, FORWARD ROW

ACCESS HOLE

F W D

A N_AR_065000_1_0130101_01_00

Over wing Panel Access FIGURE-06-50-00-991-013-A01

06-50-00

Page 15 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

B

B

A REAR SPAR

END CAP

SIDE STAY MOUNTING BRACKET

CARDAN PIN

PIN SIDE STAY ASSEMBLY

END CAP

TAB WASHER ATTACHMENT BOLT

B B N_AR_065000_1_0160101_01_00

Cardan Pin Side Stay Assembly FIGURE-06-50-00-991-016-A01

06-50-00

Page 16 Jul 01/09

B

B

10°

10°

SAFETY BOLT

JACK FITTING

SIDE STAY FITTING

LIFTING BRACKET

SHACKLE

10°

10°

PIN

N_AR_065000_1_0170101_01_01

CARDAN PIN EYE−END

MAXIMUM ALLOWABLE DEVIATION OF THE CRANES LIFTING CABLES FROM THE VERTICAL IS 10 DEGREES IN ALL DIRECTIONS.

B B

CARDAN PIN

SIDE STAY MOUNTING BRACKET


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

Crane Attachment Wing Lifting Bracket FIGURE-06-50-00-991-017-A01

06-50-00

Page 17 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

THE OVERWING PANEL IS REMOVED OR CUT TO GAIN ACCESS

NOTE: TYPICAL ARRANGEMENT N_AR_065000_1_0180101_01_01

Crane Lifting Example of Crane Arrangement FIGURE-06-50-00-991-018-A01

06-50-00

Page 18 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 06-50-00-581-801-A01 General Preparation and Instructions for Leveling and Lifting the Aircraft with Cranes 1.

General This section gives the data related to the use of crane for leveling and lifting.

2.


3.

Job Setup References Crane/sling travel range is related to the attitude of the aircraft. See TBD for information related to the applicable scenario.

4.


Fixtures, Tools, Test and Support REFERENCE 98D07203003 98D57004031

DESIGNATION FUSELAGE SHORING CRADLE WING SHORING CRADLE Fixtures, Tools, Test and Support TABLE 1

B.

Referenced Information REFERENCE TASK 03-50-01-558-803-A01 TASK 06-50-00-581-803-A01 TASK 02-30-01-481-801-A01 DESC 06-00-00-002-A01 DESC 06-40-00-001-A01 04-30-00 03-50-01 05-50-00 05-60-00 06-10-00 05-10-00 07-20-00 07-40-00

DESIGNATION TASK 03-50-01-558-803-A01-Ballast Added Effect TASK 06-50-00-581-803-A01-Forward Fuselage Crane Lifting TASK 02-30-01-481-801-A01-Installation of the Safety Devices on Landing Gears DESC 06-00-00-002-A01-Leveling/Lifting Obstructions DESC 06-40-00-001-A01-Pneumatic Lifting Bags on Fuselage 04-30-00-TETHERING THE AIRCRAFT 03-50-01-MANAGING AIRCRAFT WEIGHT AND CG 05-50-00-CARGO COMPARTMENTS 05-60-00-REMOVAL OF LARGE COMPONENTS 06-10-00-LOAD DETERMINATION 05-10-00-DEFUELING 07-20-00-PREPARING A ROADWAY 07-40-00-TOWING AND DEBOGGING

06-50-00

Page 19 Jul 01/09


REFERENCE AMM 07-11-00-581-001


5.



CAUTION :


CAUTION :


CAUTION :

USE ONLY RECOVERY SLINGS AND SPREADER BEAMS SPECIFIED BY AIRBUS. NON-APPROVED LIFTING DEVICES CAN CAUSE SECONDARY DAMAGE TO THE AIRCRAFT.

CAUTION :

MAKE SURE THAT THE CRANE YOU USE CAN LIFT THE ESTIMATED LOAD PLUS THE WEIGHT OF THE LIFTING EQUIPMENT BEFORE YOU START TO LIFT THE AIRCRAFT.

CAUTION :


NOTE : The information or principle contained in this chapter are given as a guide to help an aircraft recovery.

06-50-00

Page 20 Jul 01/09


NOTE : It is the responsibility of the recovery manager to make the decision about the applicable method and related equipment/personnel for the leveling/lifting of the aircraft. Subtask 06-50-00-581-001-A01 A.

General NOTE : Before you start a leveling or lifting procedure with slings/cranes, make sure that the instructions that follow are obeyed. (1) Do not level or lift the aircraft with cranes during gusty wind conditions. (2) The common maximum permissible wind speed for mobile cranes is 50 km/h (27 kt) with steady wind. Airbus recommends not to lift the aircraft if the wind speed is higher. It is also recommended not to use cranes during thunderstorm to prevent lightning. (3) Before you start the leveling or lifting operation with cranes, you must correctly tether the aircraft. This is to prevent uncontrolled movement of the aircraft during this operation specially in case of high wind condition (See 04-30-00). (4) Only personnel familiar with the operating procedures of the slings, spreader beams and cranes should be in charge of the lifting operation. (5) Calculate the NRW and CG position (See 03-50-01). (6) Calculate the anticipated vertical load on the fuselage or fitting points and make sure that the necessary load is not more than the maximum allowable load. If the necessary load is more than the allowable load, you must either decrease the aircraft weight until the lifting load is less than the allowable load or use another leveling or lifting procedure. (7) Calculate the total lifting capacity of the slings and cranes that you use are able to hold. Make sure that each available sling or crane can hold the necessary load, and can fit within the boundaries of the fuselage contact zone. The crane lifting strength must be higher than the lifting loads and the jib length must be sufficient to allow aircraft movement (lateral and vertical) To decrease the necessary lifting load, it is recommended to decrease the aircraft weight by removal of cargo or payload from the aircraft before start of the leveling or lifting operation (See 05-50-00 and/or 05-60-00). (8) Calculate the possible arc movement during the leveling operation, at each lifting point. Also calculate the side load if necessary (See 06-10-00). (9) For the wing lifting, make sure that the hook and slings can hold the lifting loads. (10) The frame station and lifting points that will be used for lifting must no be damaged. In case of damage, contact Airbus. (11) Make sure that there are no sharp edges or peaks (skin damages, protruding structure, antenna ... ) in the zones where the fuselage recovery slings will be installed. See DESC 06-00-00-002-A01 for the list of leveling/lifting obstructions.

06-50-00

Page 21 Jul 01/09


(12) If necessary, put wheel chocks in front of and behind the wheels of the main landing gear that is extended and in contact with the ground. (13) Install the landing gear downlock pins in all landing gears that are extended. (14) All the persons who work on the leveling/lifting operation should be connected with mobile communication devices. Two-way voice activated headsets are ideal for this type of operation. (15) No personnel must be in or below the aircraft during the leveling process. The personnel who is not directly involved in the lifting operation must be at least 20 m (65 ft) far from the aircraft and cranes. (16) Movement of fuel in the wing tanks caused by aircraft leveling can change the aircraft CG position. Therefore, it is recommended to remove all fuel from the aircraft before leveling. (See 05-10-00) This will also decrease the necessary lifting loads. (17) Monitor the CG during all the aircraft leveling process and be prepared to control with ballast if necessary (See TASK 03-50-01-558-803-A01). (18) Monitor the position of the slings carefully at all times during the leveling/lifting process. For the fuselage lifting, it is necessary to instal each sling at a frame station and all slings must be in the area listed in TASK 06-50-00-581-803-A01. (19) You must monitor and record the applied loads at all times during the leveling and lifting process. If at one step of the process the maximum load (related to the lifting scenario) is more than the allowable load, contact Airbus for definition of structure inspection tasks. Airbus recommends that you use load cells and monitoring equipment to record the applied loads. (20) Level or lift the aircraft slowly, obey the instructions given by the manufacturer of the lifting/leveling equipment and adjust the tethers as the aircraft starts to move. (21) When the fuselage and the wing are leveled and if it is necessary to lift the aircraft, it is recommended to use the 3 main jacking points to lift the aircraft to the necessary height. See AMM 07-11-00-581-001. The aircraft should not be lifted until the entire aircraft (wing and fuselage) is in a level attitude. (22) When the aircraft is leveled and at the necessary height: (a) Assemble a shoring device to support the fuselage and/or wings, or install jacks as a safety precaution if you work on the landing gear. Use shoring cradles on a prepared area: - Under the fuselage FR9, F24-56 and FR60: 98D07203003 FUSELAGE SHORING CRADLE, - Under the wing RIB 4, RIB 13 and RIB 22: 98D57004031 WING SHORING CRADLE. If the above tools are not available on site, you can use wood cribbing with rubber protections under the fuselage. In that case, the bearing area is the same as for pneumatic lifting bags installation: see DESC 06-40-00-001-A01.

06-50-00

Page 22 Jul 01/09


(b) If possible on site, when the aircraft is on shoring cradles, extend the landing gear and install the downlock pins, see TASK 02-30-01-481-801-A01 or repair or replace the landing gear. Then prepare a roadway (see 07-20-00) and tow the aircraft (see 07-40-00). (c) Or place the forward fuselage and/or the wing(s) on a mobile trailers if it is not possible to make the landing gear serviceable. (23) After the recovery operation, you must do an inspection of the skin surface and the wing for any sign of damage which may have been caused during the leveling/lifting.

06-50-00

Page 23 Jul 01/09


MOVING THE AIRCRAFT 07-00-00

MOVING THE AIRCRAFT

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 07-00-00-002-A01 General Preparation 1.

2.

General This chapter gives the procedures for moving the aircraft to a hard surface. There are different procedures for moving the aircraft if the landing gear is serviceable, or if it is damaged. A.

Before moving the aircraft you must: - Do a detailed inspection of the landing gear to confirm its structural integrity. The landing gear must be capable of supporting the weight of the aircraft during Towing/Debogging operations, see 02-30-01 - Do a check to make sure that the landing gear is in the downlocked position with the groundlock pins fitted. If it is not possible to fit the groundlock pins, a more detailed inspection must be done to find the cause. See 02-30-01 for groundlock pin installation details.

B.

Use one of the following procedures when the landing gear is damaged or missing: - Repair or replace the landing gear to make it capable of supporting the aircraft weight during Towing/Debogging operations. - Use an aircraft recovery transport vehicle or vehicles to move the aircraft. See 07-60-00.

C.

Before moving the aircraft, make sure that: - Fuel and cargo have been removed to make the aircraft as light as possible. - The weight and Center of Gravity (CG) are adequate for towing stability, seeTBD - The relevant authorities have confirmed that the aircraft can be moved. - The airport authority and fire department have been told that the recovery process has moved to the next phase. - There are no fluid leaks.

Returning Undamaged Aircraft to a Hard Surface A planned recovery will allow the undamaged aircraft to be returned to the runway in the least possible time. A.

The recovery plan can include: - Confirmation that the aircraft is in the correct condition to be moved. - The need to remove fuel and cargo from the aircraft. - The type of ground over which the aircraft must be moved. - The direction in which the aircraft will be moved. - The type and quantity of ground equipment and recovery vehicles needed.

07-00-00

Page 1 Jul 01/09


B.

The following procedures may be necessary to return an undamaged aircraft to the runway or taxiway: - For an aircraft that has moved onto soft ground or snow, it may be necessary to use the Debogging procedure, TBD and the procedure to prepare a roadway 07-20-00. When a roadway is prepared, the width of the roadway must be sufficient to let the towing vehicle turn the aircraft if necessary. - To make sure that the towing loads are not exceeded; use a load measuring tool to monitor the loads at all times. - To make sure that the Debogging loads are not exceeded; use a load measuring tool to monitor the loads at all times unless the fuse assembly is being used, see TBD.

07-00-00

Page 2 Jul 01/09


07-20-00

PREPARING A ROADWAY


For each aircraft recovery, the recovery manager must contact the relevant specialists to obtain correct data applicable to the ground strength. If the aircraft has moved off the runway or taxiway, it may be necessary to build a roadway to move the aircraft on. The roadway must be excavated to a depth that will let the finished roadway safely support the weight of the aircraft. The width of the roadway must let the aircraft be turned as necessary and let the routing of the aircraft be changed. The width of the roadway must let heavy recovery vehicles manoeuvre safely. NOTE : The information or principle contained in this chapter are given as a guide to assist an aircraft recovery.

2.

If the ground is soft or is not stable, you must excavate the ground along the route to the runway and build a roadway. If the aircraft wheels have made ruts that are not too deep, the ruts can be filled with a foundation material. This material can be compacted gravel or railway ties/sleepers covered with sheet steel or thick plywood, see FIGURE 07-20-00-991-001-A. See chapter 04-50-00 for information on soil characteristics. Normally, general construction contractors will have sufficient knowledge and experience to make a safe roadway. Some of the materials that can be used in the construction of a roadway are: - Compacted stone, gravel and/or broken asphalt, - Railway ties/sleepers, - Sheet steel, - Plywood See chapter 09-30-01 for details of materials that can be used for the recovery operation. You must make sure that materials used for recovery are safe to be used, can cope with the forecasted weather conditions and will not break under load or cause a change in aircraft stability. When sheet material is used on top of the compacted material, it is recommended that two layers of sheet material are used. Lay the sheets with the joints of the bottom layer covered by the top layer, see FIGURE 07-20-00-991-001-A. When using sheet steel be careful to avoid fluid spills. Fluid spills on sheet steel can cause a loss of towing traction for the towing vehicles and will be a hazard for the recovery team. Steel or aluminum sections that can be bolted together are available commercially in most cities. Fabric matting that is made of different types of glass fibre is also available commercially. There are different types, sizes and strengths of these materials. If there is not sufficient sheet material to make the roadway, the materials that the aircraft has been moved over can be re-used to complete the roadway.

07-20-00

Page 1 Jul 01/09


If heavy timbers are used directly on the roadway, they must be covered with a layer of plywood or steel. If this is not done, the load from individual wheels can push one of the timbers into soft ground and cause the aircraft to stop. When the ground is not level, the roadway must normally be made with a slope of 5˚ or less. If possible, position the towing/winching vehicle on the runway to give maximum traction.

07-20-00

Page 2 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

5° SLOPE TYPICAL USE OF RAILWAY TIES/SLEEPERS

EXCAVATED AREA FILLED WITH FOUNDATION MATERIAL

SHEET MATERIAL OVERLAP

N_AR_072000_1_0010101_01_00

Preparing a Roadway Typical Roadway Construction (Sheet 1 of 3) FIGURE-07-20-00-991-001-A01

07-20-00

Page 3 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

RUNWAY MATING (STEEL PLATES, FIBERGLASS, ALUMINIUM, ...)

N_AR_072000_1_0010102_01_00


07-20-00

Page 4 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

CONCRETE

N_AR_072000_1_0010103_01_00


07-20-00

Page 5 Jul 01/09


07-40-00

TOWING AND DEBOGGING


This chapter gives the towing procedures to be used during an aircraft recovery. WARNING : STAY IN COMMUNICATION WITH THE AIRFIELD OPERATING AUTHORITY/AIR TRAFFIC CONTROLLER DURING THIS PERIOD AND GET THEIR PERMISSION TO MOVE THE AIRCRAFT. - For towing load and angle limits, see 07-40-04, - For towing with the nose gear, see 07-40-01. - For towing with the main gear from the front, see TASK 07-40-02-584-801-A01, - For towing with the main gear from the rear, see TASK 07-40-02-584-802-A01, - For towing with deflated tires, see 07-40-03. For AMM towing procedure, see AMM 09-10-00PB201.

2.

Debogging definition : Airbus considers that debogging is towing on soft ground, with or without slope consideration.

07-40-00

Page 1 Jul 01/09


07-40-01

TOWING FROM THE NOSE LANDING GEAR

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 07-40-01-584-801-A01 Towing on the NLG with a Towbar 1.

General This procedure gives details to push the aircraft rearward or to tow the aircraft forward using a towbar installed on the NLG.

2.

Inspections - Make sure that the safety devices are installed on the landing gears, see TASK 02-30-01-481-801A01. - Make sure that the aircraft is stable, see TBD or AMM 05-57-00-200-001. - Make sure that the engine cowl are closed.

3.

Job Setup References For towing limits, see 07-40-04.

4.


Fixtures, Tools, Test and Support REFERENCE D23156000

DESIGNATION PIN-SAFETY Fixtures, Tools, Test and Support TABLE 1

B.

Referenced Information REFERENCE TASK 02-30-01-481-801-A01 07-40-04 AMM 05-57-00-200-001 AMM 31-60-00-860-001 AMM 29-24-00-863-001 FIGURE 07-40-01-991-002-A FIGURE 07-40-01-991-001-A

DESIGNATION TASK 02-30-01-481-801-A01-Installation of the Safety Devices on Landing Gears 07-40-04-TOWING LOAD LIMITS

FIGURE 07-40-01-991-002-A-Towing on the NLG FIGURE 07-40-01-991-001-A-Towing on the NLG Referenced Information TABLE 2

07-40-01

Page 1 Jul 01/09


5.


Preparation (1) If possible, do an EIS start procedure, see AMM 31-60-00-860-001. (2) On the N/W steering deactivation electrical-box 5GC (see FIGURE 07-40-01-991-002-A): (a) Set the ground-towing control lever to the towing position. (b) Install the D23156000 PIN-SAFETY.

Subtask 07-40-01-500-002-A01 B.

Installation of the Towbar CAUTION :

MAKE SURE THAT THE TOW BAR AS A DAMPING SYSTEM, A CALIBRATED SHEAR PIN AND TWO CALIBRATED TURN SHEAR PINS. THIS IS TO PREVENT HIGH LOADS WHICH CAN CAUSE DAMAGE TO THE LANDING GEAR.

(1) Install the towbar on the tow fitting. (2) Connect the towbar to the tractor. See FIGURE 07-40-01-991-001-A. Subtask 07-40-01-869-001-A01 C.

Aircraft Configuration (1) On the panel 400VU: - Make sure that the pressure indication on the yellow brake-pressure triple-indicator is correct: 3000 psi (206.84 bar). The pointer must be in the green area. The pointer must be in the green range. - If necessary, pressurize the yellow hydraulic system, see AMM 29-24-00-863-001. (2) On the panel 110VU, set the PARKING-BRK control-switch to OFF. (3) During towing, make sure that the pressure indication on the yellow brake-pressure tripleindicator is correct: 3000 psi (206.84 bar). The pointer must be in the green area. The pointer must be in the green range. If necessary, pressurize the yellow hydraulic system, see AMM 29-24-00-863-001.

07-40-01

Page 2 Jul 01/09


Subtask 07-40-01-584-001-A01 D.

Towing WARNING : DURING TOWING / TAXIING OPERATION (LOW-SPEED OPERATION INCLUDED), EACH PERSON IN THE AIRCRAFT MUST BE IN A SEAT AND THE SEAT BELT MUST BE FASTENED. IF THE SEAT BELT IS NOT FASTENED, THERE IS A RISK OF INJURY IF THE AIRCRAFT STOPS SUDDENLY. CAUTION :

PUT THE PARKING BRAKE CONTROL SWITCH IN THE OFF POSITION BEFORE YOU TOW OR PUSH BACK THE AIRCRAFT. THIS IS TO PREVENT HIGH LOADS WHICH CAN CAUSE DAMAGE TO THE NOSE LANDING GEAR.

(1) Tow slowly and smoothly. During the towing operations, put: - one person in the cockpit to operate the brakes if necessary, - two persons to monitor the wing tips. NOTE : The shock absorber reaction can cause the aircraft to move forward and rearward when you stop the wheels. Because of this, make sure that there is sufficient space around the aircraft when you tow with the nose gear. Subtask 07-40-01-869-002-A01 E.

Close-up (1) Visual Inspection (a) After you complete the towing operation, make sure that the nose wheels are aligned with the aircraft centerline. (2) Aircraft Configuration (a) Put the wheel chocks in position in front of and behind the wheels. (b) On the panel 110VU, set the PARKING BRK control switch to ON. (c) On the panel 400VU, make sure that the pressure indication on the yellow brakepressure triple-indicator is correct: 3000 psi (206.84 bar). The pointer must be in the green area. The pointer must be in the green range. If necessary, pressurize the yellow hydraulic system, see AMM 29-24-00-863-001. (3) Removal of the Towbar (a) Remove the towbar from the fitting of the NLG. (b) Remove the tow-lever safety pin. (c) Set the ground-towing lever to its initial position.

07-40-01

Page 3 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A B

A

TORSION PUSH PULL TURNING POINT WITH RUBBER

B N_AR_074001_1_0010101_01_00

Towing on the NLG Towing Attachment FIGURE-07-40-01-991-001-A01

07-40-01

Page 4 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

TOWING LEVER

NORMAL POSITION (NOSE WHEEL STREERING OPERATIONAL)

SAFETY PIN (TOWING POSITION)

TOWING POSITION (NOSE WHEEL STEERING DEACTIVATED)

A N_AR_074001_1_0020101_01_00

Towing on the NLG N/W-Steering Deactivation Electrical-Box FIGURE-07-40-01-991-002-A01

07-40-01

Page 5 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 07-40-01-584-802-A01 Towing on the NLG with a Towbarless Tractor 1.

General This procedure gives details to push the aircraft rearward or to tow the aircraft forward using a towbarless tractor on the NLG.

2.

Inspections - Make sure that the safety devices are installed on the landing gears, see TASK 02-30-01-481-801A01. - Make sure that the aircraft is stable, see TBD or AMM 05-57-00-200-001. - Make sure that the engine cowl are closed.

3.


4.


Fixtures, Tools, Test and Support REFERENCE D23156000

DESIGNATION PIN-SAFETY Fixtures, Tools, Test and Support TABLE 1

B.

Referenced Information REFERENCE TASK 02-30-01-481-801-A01 TASK 07-40-01-584-801-A01 07-40-04 AMM 05-57-00-200-001 AMM 31-60-00-860-001 AMM 29-24-00-863-001

DESIGNATION TASK 02-30-01-481-801-A01-Installation of the Safety Devices on Landing Gears TASK 07-40-01-584-801-A01-Towing with the NLG with a Towbar 07-40-04-TOWING LOAD LIMITS

Referenced Information TABLE 2

07-40-01

Page 6 Jul 01/09


5.

Procedure WARNING : WHEN YOU TOW THE AIRCRAFT WITH A TOWBARLESS TRACTOR, THE PARKING BRAKE OR THE BRAKE PEDALS SHALL ONLY BE USED IN CASE OF EMERGENCY. IF YOU APLLY THE PARKING BRAKE OR THE BRAKE PEDALS, YOU CAN CAUSE OVERLOAD TO THE NLG, DAMAGE TO THE TOWBARLESS TRACTOR AND INJURY TO THE PERSONEL. IF THIS OCCURS, YOU MUST CONTACT AIRBUS. CAUTION :

WHEN YOU USE A TOWBARLESS TRACTOR, MAKE SURE THAT YOU OBEY FULLY ALL THE INSTRUCTIONS IN THIS PROCEDURE. IF YOU DO NOT, THE TRACTOR CAN CAUSE IMPORTANT SCRAPING OR OTHER DAMAGE TO THE NLG AND TO THE AIRFRAME STRUCTURE AROUND THE NLG.

Subtask 07-40-01-500-003-A01 A.

Preparation (1) If possible, do an EIS start procedure, see AMM 31-60-00-860-001. (2) On the N/W steering deactivation electrical-box 5GC (see TASK 07-40-01-584-801-A01): (a) Set the ground-towing control lever to the towing position. (b) Install the D23156000 PIN-SAFETY.

Subtask 07-40-01-500-004-A01 B.

Installation of the Towbarless Tractor CAUTION :

AIRBUS STRONGLY RECOMMENDS THAT THE OPERATORS OF TOWBARLESS TRACTORS CAREFULLY ALIGNS THE CLAMPING DEVICE OF THE TRACTOR WITH THE NOSE LANDING GEAR AXIS. THE GAP BETWEEN THE CRADDLE AND THE TORQUE-LINK IS VERY SMAL AND A MISALIGNMENT CAN CAUSE DAMAGE TO THE TORQUE-LINK PIN. A SIMPLE ALIGNMENT DEVICE ON THE TRACTOR (MARKING, METAL INDICATOR, ETC. SUPPLIED BY THE MANUFACTURER OF THE TOWBARLESS TRACTOR OR MANUFACTURED LOCALLY) CAN HELP THE DRIVER.

(1) There are special approval procedures for towbarless tractors. Before towing, make sure that the towbarless is approved for the towing of this aircraft. For more information on the towbarless tractors, see the SIL 090-002. (2) Set the aircraft type on the towbarless tractor, if necessary. (3) Align the clamping device of the tractor with the NLG axis. (4) Lock on and lift the NLG.

07-40-01

Page 7 Jul 01/09


(5) Make sure that the nose landing gear is correctly on the center of the tractor platform and cannot be disengaged from the tractor. Subtask 07-40-01-869-003-A01 C.

Aircraft Configuration (1) On the panel 400VU: - Make sure that the pressure indication on the yellow brake-pressure triple-indicator is correct: 3000 psi (206.84 bar). The pointer must be in the green area. The pointer must be in the green range. - If necessary, pressurize the yellow hydraulic system, see AMM 29-24-00-863-001. (2) On the panel 110VU, set the PARKING-BRK control-switch to OFF. (3) During towing, make sure that the pressure indication on the yellow brake-pressure tripleindicator is correct: 3000 psi (206.84 bar). The pointer must be in the green area. The pointer must be in the green range. If necessary, pressurize the yellow hydraulic system, see AMM 29-24-00-863-001.

Subtask 07-40-01-584-002-A01 D.

Towing WARNING : DURING TOWING / TAXIING OPERATION (LOW-SPEED OPERATION INCLUDED), EACH PERSON IN THE AIRCRAFT MUST BE IN A SEAT AND THE SEAT BELT MUST BE FASTENED. IF THE SEAT BELT IS NOT FASTENED, THERE IS A RISK OF INJURY IF THE AIRCRAFT STOPS SUDDENLY. CAUTION :


(1) Tow slowly and smoothly. During the towing operations, put: - one person in the cockpit to operate the brakes if necessary, - two persons to monitor the wing tips. NOTE : The shock absorber reaction can cause the aircraft to move forward and rearward when you stop the wheels. Because of this, make sure that there is sufficient space around the aircraft when you tow with the nose gear.

07-40-01

Page 8 Jul 01/09


Subtask 07-40-01-869-004-A01 E.

Close-up (1) Visual Inspection (a) After you complete the towing operation, make sure that the nose wheels are aligned with the aircraft centerline. (2) Aircraft Configuration (a) On the panel 110VU, set the PARKING BRK control switch to ON. (b) On the panel 400VU, make sure that the pressure indication on the yellow brakepressure triple-indicator is correct: 3000 psi (206.84 bar). The pointer must be in the green area. The pointer must be in the green range. If necessary, pressurize the yellow hydraulic system, see AMM 29-24-00-863-001. (3) Removal of the Towbarless Tractor (a) Remove the NLG from the towbarless tractor. (b) Put the wheel chocks in position in front of and behind the wheels. (c) Remove the tow-lever safety pin. (d) Set the ground-towing lever to its initial position.

07-40-01

Page 9 Jul 01/09


07-40-02

TOWING FROM THE MAIN LANDING GEAR

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 07-40-02-584-801-A01 Towing with the Main Gear from the Front 1.

General This procedure gives details to tow the aircraft forward with the MLG.

2.

Inspections - Make sure that the safety devices are installed on the landing gears, see TASK 02-30-01-481-801A01. - Make sure that the aircraft is stable, see TBD or AMM 05-57-00-200-001. - Make sure that the engine cowl are closed. - Only tow the aircraft if the ground conditions let you. If necessary, put down the applicable surface equipment: slopes, movable taxiway plates, etc. (see 07-20-00). Only try to turn if the ground conditions let you. Do a detail visual inspection of the towing cables, the fuse pins, the towing attachments before you do this procedure.

3.

Job Setup References Depending on the landing gear configuration, there are two methods of towing the aircraft from the front with the MLG: - Using a towing strap around the MLG, see SUBTASK 07-40-02-500-002-A01, - Using two 98D09104000001 ATTACHMENT - TOWING or 98D09104002000 ATTACHMENT TOWING (OPTIONAL 4 WHEEL BOGIE MLG), see SUBTASK 07-40-02-500-003-A01. For towing limits, see 07-40-04.

4.


Fixtures, Tools, Test and Support REFERENCE D23156000 98A09003500000 98D09104000001 98D09104002000

DESIGNATION PIN-SAFETY CABLE-TOWING, MLG ATTACHMENT - TOWING ATTACHMENT - TOWING (OPTIONAL 4 WHEEL BOGIE MLG) Fixtures, Tools, Test and Support TABLE 1

07-40-02

Page 1 Jul 01/09


B.

Referenced Information REFERENCE TASK 02-30-01-481-801-A01 07-40-04 07-20-00 AMM 05-57-00-200-001 AMM 31-60-00-860-001 AMM 29-24-00-863-001 FIGURE 07-40-02-991-001-A FIGURE 07-40-02-991-002-A FIGURE 07-40-02-991-003-A

DESIGNATION TASK 02-30-01-481-801-A01-Installation of the Safety Devices on Landing Gears 07-40-04-TOWING LOAD LIMITS 07-20-00-PREPARING A ROADWAY

FIGURE 07-40-02-991-001-A-Towing with the MLG from the Front FIGURE 07-40-02-991-002-A-Towing with the MLG from the Front FIGURE 07-40-02-991-003-A-Towing with the MLG from the Front Referenced Information TABLE 2

5.

Procedure WARNING : DO NOT USE A MANUAL NOSE WHEEL STEERING BAR DURING TOWING FROM THE FRONT BECAUSE THE TOWING CABLES WILL BE NEAR THE PERSON AT THE STEERING BAR. DEATH OR INJURY CAN OCCUR IF A TOWING CABLE BREAKS. Subtask 07-40-02-500-001-A01 A.

Preparation (1) If possible, do an EIS start procedure, see AMM 31-60-00-860-001. (2) On the N/W steering deactivation electrical-box 5GC: (a) Set the ground-towing control lever to the towing position. (b) Install the D23156000 PIN-SAFETY.

Subtask 07-40-02-500-002-A01 B.

Installation of the Towing Strap WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY INSTALLED ON THE LANDING GEAR. THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR.

07-40-02

Page 2 Jul 01/09


WARNING : MAKE SURE THAT NO PERSONS ARE NEAR THE TOWING CABLES WHEN THE TRACTOR APPLIES TENSION TO THE CABLES. DEATH OR INJURY CAN OCCUR IF A CABLE BREAKS. (1) Use a towing strap with the properties that follow: - Length 2160 mm (85 in), - Width 100 mm (4 in), - Safe Working Load 1300 daN (29225 lbf). (2) Wind the towing strap around the bottom of the MLG shock absorber and the axles. Make sure that the towing strap does not touch the links of the MLG. See FIGURE 07-40-02-991-001-A. (3) Connect the 98A09003500000 CABLE-TOWING, MLG to the towing strap. (4) Connect the 98A09003500000 CABLE-TOWING, MLG to the tractor. NOTE : Airbus recommends that you install bridge cables or ropes between the towing cables to prevent unwanted cable movement if a cable breaks. (5) Do SUBTASK 07-40-02-584-001-A01. Subtask 07-40-02-500-003-A01 C.

Installation of the Towing Attachment WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY INSTALLED ON THE LANDING GEAR. THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR. WARNING : MAKE SURE THAT NO PERSONS ARE NEAR THE TOWING CABLES WHEN THE TRACTOR APPLIES TENSION TO THE CABLES. DEATH OR INJURY CAN OCCUR IF A CABLE BREAKS. (1) Install the 98D09104000001 ATTACHMENT - TOWING (see FIGURE 07-40-02-991-002A) or 98D09104002000 ATTACHMENT - TOWING (OPTIONAL 4 WHEEL BOGIE MLG) (see FIGURE 07-40-02-991-003-A) on each MLG. (2) Install the 98A09003500000 CABLE-TOWING, MLG on the towing attachments. (3) Connect the 98A09003500000 CABLE-TOWING, MLG to the tractor. NOTE : Airbus recommends that you install bridge cables or ropes between the towing cables to prevent unwanted cable movement if a cable breaks. (4) Do SUBTASK 07-40-02-584-001-A01.

07-40-02

Page 3 Jul 01/09


Subtask 07-40-02-584-001-A01 D.

Towing WARNING : DURING TOWING / TAXIING OPERATION (LOW-SPEED OPERATION INCLUDED), EACH PERSON IN THE AIRCRAFT MUST BE IN A SEAT AND THE SEAT BELT MUST BE FASTENED. IF THE SEAT BELT IS NOT FASTENED, THERE IS A RISK OF INJURY IF THE AIRCRAFT STOPS SUDDENLY. WARNING : MAKE SURE THAT NO PERSONS ARE NEAR THE TOWING CABLES WHEN THE TRACTOR APPLIES TENSION TO THE CABLES. DEATH OR INJURY CAN OCCUR IF A CABLE BREAKS. CAUTION :


(1) Tow the aircraft slowly and smoothly. During the towing, put: - one person in the cockpit to operate the brakes if necessary, - two persons to monitor the wing tips. WARNING : DO NOT USE A MANUAL NOSE WHEEL STEERING BAR DURING TOWING FROM THE FRONT BECAUSE THE TOWING CABLES WILL BE NEAR THE PERSON AT THE STEERING BAR. DEATH OR INJURY CAN OCCUR IF A TOWING CABLE BREAKS. (2) Where possible, keep the tractor aligned with the aircraft centerline. The maximum lateral position that is permitted is the width of the aircraft. NOTE : Airbus recommend that you install load cells on the towing cables to record and monitor the loads applied on the MLG during the towing. Subtask 07-40-02-869-001-A01 E.

Close-up (1) Visual Inspection (a) After you complete the towing operation, make sure that the nose wheels are aligned with the aircraft centerline. (2) Aircraft Configuration (a) Put the wheel chocks in position in front of and behind the wheels. (b) On the panel 110VU, set the PARKING BRK control switch to ON.

07-40-02

Page 4 Jul 01/09


(c) On the panel 400VU, make sure that the pressure indication on the yellow brakepressure triple-indicator is correct: 3000 psi (206.84 bar). The pointer must be in the green area. The pointer must be in the green range. If necessary, pressurize the yellow hydraulic system, see AMM 29-24-00-863-001. (3) Removal of the Tooling (a) Remove the towing cable. (b) Remove the towing attachment or the towing strap from each MLG. (c) Remove the tow-lever safety pin. (d) Set the ground-towing lever to its initial position.

07-40-02

Page 5 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

TOWING CABLE

TOWING STRAP

A N_AR_074002_1_0010101_01_00

Towing with the MLG from the Front Strap Installation FIGURE-07-40-02-991-001-A01

07-40-02

Page 6 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

TOWING CABLE

TOWING ATTACHMENT

A N_AR_074002_1_0020101_01_00

Towing with the MLG from the Front Towing Attachment Tool - Two Wheel MLG FIGURE-07-40-02-991-002-A01

07-40-02

Page 7 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

TOWING ATTACHMENT

TOWING CABLE

A N_AR_074002_1_0030101_01_00

Towing with the MLG from the Front Towing Attachment Tool - Four Wheel Bogie MLG (Optional A320 Only) FIGURE-07-40-02-991-003-A01

07-40-02

Page 8 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 07-40-02-584-802-A01 Towing with the Main Gear from the Rear 1.

General This procedure gives details to tow the aircraft rearward with the MLG.

2.

Inspections - Make sure that the safety devices are installed on the landing gears, see TASK 02-30-01-481-801A01. - Make sure that the aircraft is stable, see TBD or AMM 05-57-00-200-001. - Make sure that the engine cowl are closed. - Only tow the aircraft if the ground conditions let you. If necessary, put down the applicable surface equipment: slopes, movable taxiway plates, etc. (see 07-20-00). Only try to turn if the ground conditions let you. Do a detail visual inspection of the towing cables, the fuse pins, the towing attachments before you do this procedure.

3.


4.


Consumable Materials REFERENCE 05-047 09-016

DESIGNATION Anti Corrosion Compound (High Temperature Silicone Sealant) Corrosion Inhibiting Fillet Consistency Consumable Materials TABLE 1

B.

Fixtures, Tools, Test and Support REFERENCE D23156000 98D09104001000 98D09104002000 98A09003500000 98A09003000001

DESIGNATION PIN-SAFETY ATTACHEMENT-TOWING ATTACHMENT - TOWING (OPTIONAL 4 WHEEL BOGIE MLG) CABLE-TOWING, MLG BAR-STEERING, NOSE WHEEL Fixtures, Tools, Test and Support TABLE 2

07-40-02

Page 9 Jul 01/09


C.

Referenced Information REFERENCE TASK 02-30-01-481-801-A01 07-40-04 07-20-00 AMM 05-57-00-200-001 AMM 31-60-00-860-001 AMM 29-24-00-863-001 FIGURE 07-40-02-991-004-A FIGURE 07-40-02-991-005-A FIGURE 07-40-02-991-006-A FIGURE 07-40-02-991-007-A

DESIGNATION TASK 02-30-01-481-801-A01-Installation of the Safety Devices on Landing Gears 07-40-04-TOWING LOAD LIMITS 07-20-00-PREPARING A ROADWAY

FIGURE FIGURE FIGURE FIGURE

07-40-02-991-004-A-Towing 07-40-02-991-005-A-Towing 07-40-02-991-006-A-Towing 07-40-02-991-007-A-Towing

with with with with

MLG MLG MLG MLG

from from from from

the the the the

Rear Rear Rear Rear



Preparation (1) If possible, do an EIS star procedure, see AMM 31-60-00-860-001. (2) On the N/W steering deactivation electrical-box 5GC: (a) Set the ground-towing control lever to the towing position. (b) Install the D23156000 PIN-SAFETY.

Subtask 07-40-02-020-001-A01 B.

Removal of Components for Access (1) See FIGURE 07-40-02-991-004-A. (2) Remove the nuts (1), the washers (2) and the bolts (3). (3) Remove the block (4). (4) Remove the split pin (7), nut (6) and washer (5). (5) Remove the bolt (9) and sleeve (8). (6) Disconnect the rod end of the lower slave link sub-assembly (10).

07-40-02

Page 10 Jul 01/09


Subtask 07-40-02-500-006-A01 C.

Installation of the Towing Attachment WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY INSTALLED ON THE LANDING GEAR. THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR. WARNING : MAKE SURE THAT NO PERSONS ARE NEAR THE TOWING CABLES WHEN THE TRACTOR APPLIES TENSION TO THE CABLES. DEATH OR INJURY CAN OCCUR IF A CABLE BREAKS. (1) Install the 98D09104001000 ATTACHEMENT-TOWING (see FIGURE 07-40-02-991-005A) or 98D09104002000 ATTACHMENT - TOWING (OPTIONAL 4 WHEEL BOGIE MLG) (see FIGURE 07-40-02-991-006-A) on each MLG. (2) Install the 98A09003500000 CABLE-TOWING, MLG on the towing attachments. (3) Connect the 98A09003500000 CABLE-TOWING, MLG to the tractor. NOTE : Airbus recommends that you install bridge cables or ropes between the towing cables to prevent unwanted cable movement if a cable breaks. WARNING : BE CAREFUL WHEN YOU USE THE NOSE WHEEL STEERING-BAR DURING TOWING OF THE AIRCRAFT. THERE IS A RISK OF INJURY IF SUDDEN UNWANTED MOVEMENT OF THE AIRCRAFT OR STEERING BAR OCCURS. (4) Install the 98A09003000001 BAR-STEERING, NOSE WHEEL on the NLG, see FIGURE 07-40-02-991-007-A.

Subtask 07-40-02-584-002-A01 D.

Towing WARNING : DURING TOWING / TAXIING OPERATION (LOW-SPEED OPERATION INCLUDED), EACH PERSON IN THE AIRCRAFT MUST BE IN A SEAT AND THE SEAT BELT MUST BE FASTENED. IF THE SEAT BELT IS NOT FASTENED, THERE IS A RISK OF INJURY IF THE AIRCRAFT STOPS SUDDENLY. WARNING : MAKE SURE THAT NO PERSONS ARE NEAR THE TOWING CABLES WHEN THE TRACTOR APPLIES TENSION TO THE CABLES. DEATH OR INJURY CAN OCCUR IF A CABLE BREAKS. WARNING : BE CAREFUL WHEN YOU USE THE NOSE WHEEL STEERING-BAR DURING TOWING OF THE AIRCRAFT. THERE IS A RISK OF INJURY IF SUDDEN UNWANTED MOVEMENT OF THE AIRCRAFT OR STEERING BAR OCCURS.

07-40-02

Page 11 Jul 01/09


CAUTION :


(1) Tow the aircraft slowly and smoothly. During the towing, put: - one person in the cockpit to operate the brakes if necessary, - two persons to monitor the wing tips. (2) Where possible, keep the tractor aligned with the aircraft centerline. The maximum lateral position that is permitted is the width of the aircraft. NOTE : Airbus recommend that you install load cells on the towing cable to record and monitor the loads applied on the MLG during the towing. Subtask 07-40-02-869-002-A01 E.

Close-up (1) Visual Inspection (a) After you complete the towing operation, make sure that the nose wheels are aligned with the aircraft centerline. (2) Aircraft Configuration (a) Put the wheel chocks in position in front of and behind the wheels. (b) On the panel 110VU, set the PARKING BRK control switch to ON. (c) On the panel 400VU, make sure that the pressure indication on the yellow brakepressure triple-indicator is correct: 3000 psi (206.84 bar). The pointer must be in the green area. The pointer must be in the green range. If necessary, pressurize the yellow hydraulic system, see AMM 29-24-00-863-001. (3) Removal of the Tooling (a) Remove the 98A09003000001 BAR-STEERING, NOSE WHEEL. (b) Remove the towing cable. (c) Remove the towing attachment of the towing strap from each MLG. (d) Remove the tow-lever safety pin. (e) Set the ground-towing lever to its initial position.

Subtask 07-40-02-500-007-A01 F.

Install Components (1) Put the rod end of the lower slave link sub-assembly (10) in position. See FIGURE 07-40-02-991-004-A.

07-40-02

Page 12 Jul 01/09


WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 05-047 ANTI CORROSION COMPOUND (HIGH TEMPERATURE SILICONE SEALANT). OBEY THE MATERIAL MANUFACTURER’S INSTRUCTIONS. (2) Apply Material No. 05-047 Anti Corrosion Compound (High Temperature Silicone Sealant) on the plain shank of the bolt (9). (3) Install the bolt (9), the sleeve (8), the washer (5) and the nut (6). Torque the nut (6) to between 2.1 and 2.7 m.daN (15.48 and 19.91 lbf.ft). (4) Install the new split (7). (5) Make sure that the lower slave link sub-assembly (10) is free to turn around the bolt (9). WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 09-016 CORROSION INHIBITING FILLET CONSISTENCY. OBEY THE MATERIAL MANUFACTURER’S INSTRUCTIONS. (6) Apply Material No. 09-016 Corrosion Inhibiting Fillet Consistency on the bolt (9) and nut (6). (7) Put the block (4) in position on the flexible hoses and loosely install bolts (3), the washers (2) and the nuts (1). (8) Make sure that the dimension ”Y” is 150 mm (5.91 in). (9) Torque the nuts (1) to between 0.4 and 0.45 m.daN (35.39 and 39.82 lbf.in).

07-40-02

Page 13 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 1

2

3

A

B

Y

A 10

9

8 5

6

7

B N_AR_074002_1_0040102_01_00

Towing with MLG from the Rear Removal of Lower Slave Link FIGURE-07-40-02-991-004-A01

07-40-02

Page 14 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

TOWING CABLE

A N_AR_074002_1_0050101_01_00

Towing with MLG from the Rear Towing Attachment Tool - Two Wheel MLG FIGURE-07-40-02-991-005-A01

07-40-02

Page 15 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

TOWING CABLE

TOWING ATTACHMENT

A N_AR_074002_1_0060101_01_00

Towing with MLG from the Rear Towing Attachment Tool - Four Wheel Bogie MLG (Optional A320 Only) FIGURE-07-40-02-991-006-A01

07-40-02

Page 16 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

A

N_AR_074002_1_0070101_01_00

Towing with MLG from the Rear Manual Steering Bar FIGURE-07-40-02-991-007-A01

07-40-02

Page 17 Jul 01/09


07-40-03

TOWING WITH DEFLATED TIRES

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 07-40-03-584-801-A01 Towing with Deflated Tires 1.

General This procedure gives details and limitations to tow the aircraft when one or more tires are deflated.

2.

Inspections Not Applicable

3.

Job Setup References The steering angle must be kept to a limit when you tow the aircraft with one or more tires deflated on one or more landing gears. - For aircraft equipped with the twin wheel MLG, see SUBTASK 07-40-03-584-001-A01, - For aircraft equipped with the optional four wheel bogie MLG (A320 only), see SUBTASK 07-40-03-584-002-A01.

4.


Referenced Information REFERENCE TASK 07-40-01-584-801-A01 TASK 07-40-02-584-801-A01

DESIGNATION TASK 07-40-01-584-801-A01-Towing with the NLG with a Towbar TASK 07-40-02-584-801-A01-Towing with the Main Gear from the Front Referenced Information TABLE 1

5.


Twin Wheel Main Landing Gear (1) One tire is deflated on one or more gears (a maximums of three deflated tires). - Tow by the nose gear, see TASK 07-40-01-584-801-A01. The maximum permitted lateral angle of the towbar is plus or minus 10 degrees. (2) One tire is deflated on one main gear. - Tow by the nose gear, see TASK 07-40-01-584-801-A01. The maximum permitted lateral angle of the towbar is plus or minus 40 degrees. (3) Two tires are deflated on the same gear. - Tow by the main gear only, see TASK 07-40-02-584-801-A01. - The towbar must not move laterally at all.

07-40-03

Page 1 Jul 01/09


Subtask 07-40-03-584-002-A01 B.

Optional Four Wheel Bogie Main Landing Gear (A320 only) (1) One tire is deflated on one or more gears (a maximum of three deflated tires). - Tow by the nose gear, see TASK 07-40-01-584-801-A01. The maximum permitted lateral angle of the towbar is plus or minus 10 degrees. (2) One tire or two tires (one on each axle) deflated on one main gear. - Tow by the nose gear, see TASK 07-40-01-584-801-A01. The maximum permitted lateral angle of the towbar is plus or minus 40 degrees. (3) Two tires on the same axle or more than two tires deflated on the same gear (with the two tires on the NLG inflated). - Tow by the main gears, see TASK 07-40-02-584-801-A01. - Steer by the NLG with the towbar or the normal steering control, see TASK 07-40-01-584-801-A01. (a) Two tires on the same axle or three tires deflated on the same gear. - The maximum permitted steering angle of the NLG is plus or minus 50 degrees. (b) All the four tires are deflated on the same MLG. - The towbar must not move laterally at all. - The speed must be kept to a limit of approximately 1.3 m/s (4.27 ft/s).

07-40-03

Page 2 Jul 01/09


07-40-04

TOWING LOAD LIMITS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 07-40-04-001-A01 Load and Angle Limits 1.

Towing WARNING : OBEY THE SAFETY PRECAUTIONS DURING TOWING OR MOVEMENT OF THE AIRCRAFT. MAKE SURE THAT THE PATH OF THE AIRCRAFT IS CLEAR. MAKE SURE THAT NO PERSONS SIT OR STAND ON THE TOW BAR OR USE THE TRACTOR AS TRANSPORT, THIS IS TO PREVENT THE RISK OF INJURY. WARNING : DURING TOWING / TAXIING OPERATION (LOW-SPEED OPERATION INCLUDED), EACH PERSON IN THE AIRCRAFT MUST BE IN A SEAT AND THE SEAT BELT MUST BE FASTENED. IF THE SEAT BELT IS NOT FASTENED, THERE IS A RISK OF INJURY IF THE AIRCRAFT STOPS SUDDENLY. CAUTION :

DO NOT TOW OR MOVE THE AIRCRAFT ON THE GROUND IF THE ENGINE COWLS ARE OPEN. MOVEMENT OF THE AIRCRAFT WITH THE COWLS OPEN CAN CAUSE DAMAGE TO THE COWLS AND THE NACELLE STRUCTURE. It is recommended that you use a towbar with a damping system.

2.

A.

You can use the NLG towbar fitting to tow or push the aircraft: - with maximum weight, - with the engines between zero and idle.

B.

You can use the MLG attachments to tow the aircraft: - with the engines stopped, - when it is bogged.

C.

Do not tow the aircraft if the dimension H is more than 300 mm (11.8110 in), see FIGURE 07-40-04-991-001-A). If you do so, you can cause damage to the cams that make the nose gear wheels go back to the center position.

D.

Keep a minimum of 3 m (9.84 ft) separation from the nose wheels, towbar and tractor while the aircraft moves.

Speed Limits The maximum permitted towing speed changes with the aircraft configuration. A.

Doors closed and locked or removed: (1) For a tractor with a towbar, a maximum speed of 25 km/h (15.5 mph) is permitted. (2) For a towbarless tractor, a maximum speed of 32 km/h (19.9 mph) is permitted.

07-40-04

Page 1 Jul 01/09


B.

Passenger/crew doors fully open and locked and/or cargo doors open in vertical position: (1) The maximum permitted speed is 10 km/h (6.2 mph).

C.

In wind conditions, calculate the permitted towing speed before towing: (1) Measure the wind speed. (2) Do a check of aircraft stability, see TBD or AMM 05-57-00-200-001. (3) Substract measured wind speed from wind speed limit shown on the stability curve. This gives the maximum permitted towing speed.

3.

Approximate Towing Loads See FIGURE 07-40-04-991-002-A. NOTE : In all the formulas, MTW = Maximum Taxi Weight. A.

When you push the aircraft rearward with the engines at idles, you must add the engine thrust resistance to the towing loads. NOTE : The engine thrust resistance at ground idle is 400 daN (for each engine in operation).

B.

Use these coefficients for the friction between the tires of the tow tractor and the ground to calculate the tractor weight: - Dry concrete or asphalt: 0.80 - Wet asphalt: 0.75 - Wet asphalt: 0.57 - Hard snow: 0.20 - Ice: 0.05 Minimum Tractor Weigh = 6% MTW / (friction coefficient)

**ON A/C A318-100 A319-100 A320-100 A320-200 4.

Limit Loads and Angles See FIGURE 07-40-04-991-003-A. A.

In all the towing configurations, the safety pin locks the control lever on the interphone box in the disengaged position.

B.

The maximum permitted steering angle on each side of the aircraft centerline is: - +/- 95 degrees with towbar, - +/- 85 degrees without towbar.

C.

During towing, the towing angle must not be more that then angle shown on the FWD NLG doors.

D.

Tow the aircraft (slowly and smoothly) with the main landing gear: - The maximum towing angle in the vertical plane is 11 degrees. - The NLG gives the limits for the maximum towing angle in the horizontal plane.

07-40-04

Page 2 Jul 01/09


E.

Use a towbar with: - The towing shear pins, calibration 9425 daN (21188.24 lbf) for the protection of the landing gear against too high loads, - The safety shear pin, calibration 826 m.daN (6091.44 lbf.ft) for the protection of the landing gear against to high torsion.

F.

Use: - The tow special fork fitting and a cable to tow the main landing gear forward or rearward. Attach these special fork fittings to the lugs at each end of the landing gear. - The safety shear pin, calibration 29000 daN (65194.58 lbf) which comes with the twofitting/cable net.

**ON A/C A321-100 A321-200 5.

Limit Loads and Angles See FIGURE 07-40-04-991-003-A. A.

In all the towing configurations, the safety pin locks the control lever on the interphone box in the disengaged position.

B.

The maximum permitted steering angle on each side of the aircraft centerline is: - +/- 95 degrees with towbar, - +/- 85 degrees without towbar.

C.

During towing, the towing angle must not be more that then angle shown on the FWD NLG doors.

D.

Tow the aircraft (slowly and smoothly) with the main landing gear: - The maximum towing angle in the vertical plane is 4 degrees. - The NLG gives the limits for the maximum towing angle in the horizontal plane.

E.

Use a towbar with: - The towing shear pins, calibration 9425 daN (21188.24 lbf) for the protection of the landing gear against too high loads, - The safety shear pin, calibration 826 m.daN (6091.44 lbf.ft) for the protection of the landing gear against to high torsion.

F.

Use: - The tow special fork fitting and a cable to tow the main landing gear forward or rearward. Attach these special fork fittings to the lugs at each end of the landing gear. - The safety shear pin, calibration 29000 daN (65194.58 lbf) which comes with the twofitting/cable net.

07-40-04

Page 3 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

H

N_AR_074004_1_0010101_01_00

Towing Limits Maximum Extension of the NLG Shock Absorber FIGURE-07-40-04-991-001-A01

07-40-04

Page 4 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

F

TOWING FORCES BREAKAWAY

6% MTW

ROLLING

3% MTW

BREAKAWAY ON SLOPE

6% MTW + 1% MTW PER 1% SLOPE

ROLLING ON SLOPE

3% MTW + 1% MTW PER 1% SLOPE

N_AR_074004_1_0020101_01_00

Towing Limits Towing Forces FIGURE-07-40-04-991-002-A01

07-40-04

Page 5 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

B

B

B

B

MAX ANGLE WITH TOWBAR = 95°

MAX ANGLE WITH TOWBARLESS = 85°

A

MAXIMUM GEAR LOADS A B

daN 9425

lbf 21188

29000

65200

A

N_AR_074004_1_0030101_01_01

Towing Limits Towing Loads and Angles FIGURE-07-40-04-991-003-A01

07-40-04

Page 6 Jul 01/09


07-60-00

MOVING DAMAGED AIRCRAFT


This section describes the moving of aircraft with damaged or missing landing gear. If it is possible, the aircraft must always be moved the landing gear supporting the weight of the aircraft. Before moving the aircraft, you must verify the structural integrity of the landing gear and the structural attachments in accordance with the landing gear inspection procedure 02-30-01. For landing gears that are not correctly extended, see TBD for information on the manual extension of the landing gear. If any of the landing gear are damaged, you must always try to repair or replace the damaged landing gear. This could include: - The repair of the existing landing gear, - The installation of a replacement landing gear, - The temporary bracing of the landing gear to support the weight of the aircraft. The repair or replacement of damaged landing gear is the recommended solution if a replacement landing gear is available and the structural attachments for the landing gear are not damaged. If it is not possible to move the aircraft using it’s landing gears, then you must use a different support system to move the aircraft, see 07-60-03. It may be necessary to use one of the following vehicles or a combination of vehicles to move the aircraft. - Flat bed trailers, - Movable cranes, - Specialist aircraft recovery transportation systems, - General purpose trucks, - Commercial transport equipment. Moving the aircraft using aircraft recovery vehicles must be the last method to be used after all other methods have been analyzed. When aircraft recovery transport vehicles are used, secondary damage is possible.

07-60-00

Page 1 Jul 01/09


07-60-01

MOVING DAMAGED AIRCRAFT ON TRAILERS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 07-60-01-001-A01 Moving Damaged Aircraft on Trailers 1.

If the Landing Gear cannot be made serviceable, the use of trailers gives a safe and correct method of supporting the aircraft fuselage and/or the wings. WARNING : MAKE SURE THAT THE TRAILERS, AND ALL OTHER EQUIPMENT YOU USE WITH THE TRAILERS, ARE SAFE FOR THE WEIGHT THEY MUST SUPPORT. CAUTION :

BE CAREFUL WHEN YOU USE SUPPORTS. MAKE SURE THAT THE LOADS ON THE AIRFRAME ARE LESS THAN THE ALLOWABLE LOADS (SKIN LOADING LIMITS) WHEN YOU USE SUPPORTS. THE SUPPORTS APPLY LOADS THAT DO NOT OCCUR IN NORMAL OPERATION.

CAUTION :

SECONDARY DAMAGE CAN OCCUR WHEN YOU USE TRAILERS TO SUPPORT AND MOVE THE AIRCRAFT.

CAUTION :

DO NOT APPLY LOADS TO THE ENGINE NACELLE STRUCTURE BECAUSE SECONDARY DAMAGE WILL OCCUR.

CAUTION :

DO NOT APPLY LOADS TO THE FLAP-TRACK FAIRING STRUCTUE BECAUSE SECONDARY DAMAGE WILL OCCUR

A.

See 06-40-00 for the bearing area under the fuselage and wings.

B.

You must inspect the aircraft structure for damage in the bearing areas. Make sure that the structure is capable of supporting the weight of the aircraft on the trailers.

C.

You can support the forward fuselage on a turntable, this will help to turn the aircraft during the move. If a turntable is used, it must conform to the weight requirements and general aircraft specifications to prevent secondary damage and assist in the removal of the aircraft.

D.

Install supports between the aircraft and the trailer surface. These can be made of timber and must be covered with padded material to avoid damage to the aircraft surfaces. The supports that you use must be able to support the expected loading.

E.

Materials such as mattresses, rubber padding, tires, pneumatic bags and sand bags can be used as padding. It is important that the padding is arranged to follow the contour of the aircraft surfaces, this will helps to spread the loads on the surface and to avoid point loads. Filler foam can be used at the support areas to fill gaps and make a correct contoured support. You must not exceed the allowable skin loading limits on the aircraft surfaces, see 06-40-00.

F.

It is important that the supports (timber) and padding remain stable while you move the aircraft. It may also be necessary to tie down the aircraft structure to the trailer to prevent relative movement between the aircraft and the trailer.

07-60-01

Page 1 Jul 01/09


G.

Some aircraft recovery trailers have hydraulically controlled supports, that conform to the fuselage and wing contours.

H.

Monitor the loads during all the moving operation.

07-60-01

Page 2 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

SOME TRAILERS HAVE HYDRAULICALLY CONTROLLED SUPPORTS

MAXIMUM 15 DEGREE TILT

HYDRAULIC PLATFORM BOGIES FOR SMALLER LOADS

CABLE AND CHAIN CONNECTION

NOSE TRAILER WITH ADJUSTABLE TURNTABLE

N_AR_076001_1_0020101_01_00

Moving Damaged Aircraft on Trailers Configuration of Trailers FIGURE-07-60-01-991-002-A01

07-60-01

Page 3 Jul 01/09


FLATBED TRAILER

FLATBED TRAILER

TYPICAL TURNTABLE

PADDING MATERIALS (PLYWOOD, PNEUNATIC LIFTING BAGS, TIRES, ETC)

TIEDOWN STRAP

N_AR_076001_1_0030101_01_00

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

Moving Damaged Aircraft on Trailers Typical Use of Trailers with Aircraft FIGURE-07-60-01-991-003-A01

07-60-01

Page 4 Jul 01/09


07-60-02

MOVING DAMAGED AIRCRAFT WITH CRANES

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 07-60-02-001-A01 Moving Damaged Aircraft with Cranes 1.

General CAUTION :


CAUTION :

BE CAREFUL WHEN YOU USE SUPPORTS. MAKE SURE THAT THE LOADS ON THE AIRFRAME ARE LESS THAN THE ALLOWABLE LOADS (SKIN LOADING LIMITS) WHEN YOU USE SUPPORTS. THE SUPPORTS APPLY LOADS THAT DO NOT OCCUR IN NORMAL OPERATION.

CAUTION :

USE ONLY RECOVERY SLINGS AND SPREADER BEAMS SPECIFIED BY AIRBUS. NON-APPROVED LIFTING DEVICES CAN CAUSE SECONDARY DAMAGE TO THE AIRCRAFT.

CAUTION :

MAKE SURE THAT THE CRANE YOU USE CAN LIFT THE ESTIMATED LOAD PLUS THE WEIGHT OF THE LIFTING EQUIPMENT BEFORE YOU START TO LIFT THE AIRCRAFT.

CAUTION :

MAKE SURE THAT THE LOADS ON THE AIRFRAME ARE LESS THAN THE ALLOWABLE LOADS WHEN YOU USE SUPPORTS. THE SUPPORTS APPLY LOADS THAT DO NOT OCCUR IN NORMAL OPERATION. The principles outlined in this chapter are provided as a guide to assist an aircraft recovery. See 06-50-00 for information on the use of cranes. If it is possible, damaged landing gears must be repaired or replaced. This will allow the aircraft to be moved with it’s own landing gear supporting the weight of the aircraft. If it is not possible to repair or replace the damaged landing gear, an alternative method is to use mobile crane or crawler crane to help move the aircraft. NOTE : You must analyze other methods of supporting and moving the aircraft before using this method. If the aircraft is in this condition, then it is possible to use cranes and sling assembly to level and lift the aircraft. The cranes can then be left in place to support and move the aircraft. Roadways must be properly prepared to support the weight of the crane and the aircraft as they are moved, see 07-20-00. 2.

Moving the Aircraft with Cranes The crane must be positioned close enough to the aircraft and the lifting point, to let the crane use its lifting capacity safely.

07-60-02

Page 1 Jul 01/09


A.

You must monitor and record the loads on the slings when you use this process.

B.

The moveable cranes must begin to move at the same time, and must move steadily at the same speed during the entire aircraft movement operation.

C.

The person controlling the operation must be in constant contact with the crane drivers/operators.

D.

See 06-50-00 for tooling specification, procedures and limitations to level/lift the aircraft using cranes.

07-60-02

Page 2 Jul 01/09


07-60-03

MOVING DAMAGED AIRCRAFT WITH SPECIALIZED EQUIPMENT

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 07-60-03-001-A01 Moving Damaged Aircraft with Specialized Vehicles 1.

Specialized recovery vehicles include sledges and patent trailer systems made by different manufacturers. CAUTION :

DO NOT APPLY LOADS OUT OF THE ALLOWABLE LIMITS BECAUSE SECONDARY DAMAGE WILL OCCUR

CAUTION :

DO NOT APPLY LOADS TO THE ENGINE NACELLE STRUCTURE BECAUSE SECONDARY DAMAGE WILL OCCUR.

A.

The sledge systems are simple systems that are used to support the aircraft while it is towed on soft ground.

B.

The patent trailer systems are complex systems and can be used to move damaged aircraft that has no serviceable landing gear, see 07-60-01. This type of trailer normally: - Has hydraulically controlled supports that can conform to the fuselage and wing contours. - Has a multi-wheel steering function. - Can be linked with beams or cables to other trailers.

07-60-03

Page 1 Jul 01/09


POST RECOVERY CORRECTIVE ACTIONS 08-00-00

POST RECOVERY CORRECTIVE ACTIONS


Records Airbus recommends that you make records on the full recovery operation. These records can help you: - To make aircraft maintenance operations easier for the return to service - To have a feedback of the recovery operation - To have traceability after the recovery. The records can include: - The aircraft inspection report - Results of loads and CG calculations - The technique used to level/lift and move the aircraft - Loads applied during the recovery operation - ...

2.

Post Recovery Inspections If necessary, do the ”Inspection After Leaving Runway or Taxiway”, see AMM 05-51-24-200-001.

08-00-00

Page 1 Jul 01/09


APPENDIX 09-00-00

APPENDIX

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-00-00-001-A01 Introduction 1.

This chapter has the structure that follows: A.

General Information (09-10) (1) General charts and formulae for metric and imperial measurement conversion. (2) Definitions related to aircraft recovery (glossary). (3) General aircraft dimensions, fuselage, wing and horizontal stabilizer stations, frames and ribs, door sizes, ground clearances, ground service connections illustrations, etc.).

B.

Recovery Preparation (09-20) (1) Guides or planning charts not related to the aircraft type. (2) Possible composition of the recovery team.

C.

Tooling and Equipment (09-30) (1) General aircraft recovery materials and equipment. (2) Specific aircraft tooling and aircraft recovery kits. (3) Aircraft Recovery Kits.

D.

Calculation Worksheets (09-50) (1) Weight and balance calculation worksheets.

09-00-00

Page 1 Jul 01/09


09-10-01

UNITS AND CONVERSIONS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-10-01-002-A01 Units of Measurements 1.

This topic gives the ISO and NON-ISO units used in this manual. Length Area Volume Weight Density Force Moment Pressure Velocity Capacity and Quantity Temperature Angle

meters (m) millimeters (mm) square meters (m2) cubic meters (m3) kilograms (kg) kilograms per cubic meter (kg/m3) kilograms per liter (kg/l) Newtons (N) Newton-meters (N.m) product of weight and length in kilogram-meters (kgm) Pascals (Pa) bars (bar) meters per second (m/s) kilometers per hour (km/h) liters (l) degrees Celsius (˚C) radians (rad) degrees (˚) ISO and Derived Measurement System TABLE 1

Length Area Volume Weight Density

feet (ft) inches (in) square feet (ft2) cubic feet (ft3) pounds (lb) pounds per cubic foot (lb/ft3) pounds per US gallon (lb/US gal)

09-10-01

Page 1 Jul 01/09


Force Moment Pressure Velocity Capacity and Quantity Temperature Angle

pound-force (lbf) pound-force feet (lbf.ft) product of weight and length in pounds-inches (lb.in) pounds per square inch (psi) feet per seconds (ft/s) miles per hour (mph) US gallons (US gal) degrees Fahrenheit (˚F) radians (rad) degrees (˚) US Customary System TABLE 2

09-10-01

Page 2 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-10-01-001-A01 Conversion Tables 1.

This topic gives the conversion values to use for the conversion of units. MULTIPLY

Length

Area Volume Weight

Density

Force

Moment

Meters (m) Meters (m) Millimeters (mm) Millimeters (mm) Inches (in) Inches (in) Feet (ft) Feet (ft) Square meters (m2) Square feet (ft2) Cubic meters (m3) Cubic feet (ft3) Kilograms (kg) Pounds (lb) Kilograms per liter (kg/l) Kilograms per liter (kg/l) Kilograms per cubic meter (kg/m3) Kilograms per cubic meter (kg/m3) Pounds per cubic foot (lb. ft3) Pounds per cubic foot (lb. ft3) Pounds per US gallon (lb/US gal) Pounds per US gallon (lb/US gal) Newtons (N) Pound-forces (lbf) Newtons (N) Decanewtons (daN) Newton-meters (N.m) Pound-force feet (lbf.ft) Newton-meters (N.m) Decanewton-meters (daN.m)

BY 39.37008 3.280840 0.03937008 0.00328084 0.0254 25.4 0.3048 304.8 10.763910 0.09290304 35.31466 0.02831685 2.204622 0.4535924 62.42797 8.3456459 0.06242797 0.0083457 0.016018463 16.018463 0.119823 119.8225188 0.2248089 4.448222 10 0.1 0.7375621 1.355818 10 0.1

TO OBTAIN Inches (in) Feet (ft) Inches (in) Feet (ft) Meters (m) Millimeters (mm) Meters (m) Millimeters (mm) Square feet (ft2) Square meters (m2) Cubic feet (ft3) Cubic meters (m3) Pounds (lb) Kilograms (kg) Pounds per cubic foot (lb. ft3) Pounds per US gallon (lb/US gal) Pounds per cubic foot (lb. ft3) Pounds per US gallon (lb/US gal) Kilograms per liter (kg/l) Kilograms per cubic meter (kg/m3) Kilograms per liter (kg/l) Kilograms per cubic meter (kg/m3) Pound-forces (lbf) Newtons (N) Decanewtons (daN) Newtons (N) Pound-force feet (lbf.ft) Newton-meters (N.m) Decanewton-meters (daN.m) Newton-meters (N.m)

09-10-01

Page 3 Jul 01/09


Pressure

Velocity

MULTIPLY Pascals (Pa) Bars (bar) Pounds per square inch (psi) Pounds per square inch (psi) Meters per second (m/s) Meters per second (m/s) Kilometers per hour (km/h) Kilometers per hour (km/h) Feet per second (ft/s) Feet per second (ft/s) Miles per hour (mph) Miles per hour (mph) Knots (kt) Kilometers per hour (km/h)

Knots (kt) Miles per hour (mph) Capacity Liters (l) Quantity US gallons (US gal)

BY TO OBTAIN 0.0001450377 Pounds per square inch (psi) Pounds per square inch (psi) 14.50377 Pascals (Pa) 6894.757 Bars (bar) 0.06894757 Feet per second (ft/s) 3.2808399 Miles per hour (mph) 2.2369 Feet per second (ft/s) 0.9113 Miles per hour (mph) 0.6214 Meters per second (m/s) 0.3048 Kilometers per hour (km/h) 1.0973 Meters per second (m/s) 0.4470 Kilometers per hour (km/h) 1.6093 Kilometers per hour (km/h) 1.852 Knots (kt) 0.5399568 1.150 0.86897 0.264172 3.785412

Miles per hour (mph) Knots (kt) US gallons (US gal) Liters (l)

Conversion Table TABLE 1 Temperature conversion: - Temperature conversion from degrees Celsius (˚C) to degrees Fahrenheit (˚F): ˚F = 1.8 × ˚C + 32 - Temperature conversion from degrees Fahrenheit (˚F) to degrees Celsius (˚C): ˚C = 0.5555 × (˚F - 32)

09-10-01

Page 4 Jul 01/09


09-10-02

GLOSSARY OF TERMS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-10-02-001-A01 Definition of Terms 1.

2.

General The terms that follow are used in the ARM. A.

Aircraft Recovery An aircraft recovery operation is the action of moving any aircraft that is disabled and unable to move with its power or with the standard use of a correct tow tractor and standard tow bar, but can be economically repairable. Examples of aircraft recovery incidents are: - One or more landing gears off the hard surface of a runway, taxiway or apron, - Aircraft bogged down in mud, snow or sand, - One or more landing gears retracted, collapsed, damaged, or missing.

B.

Warnings, Cautions and Notes These definition of these are as follow: - WARNING: Calls attention to the use of materials, processes, methods, procedures or limits that must be obeyed to prevent injury or death to persons. - CAUTION: Calls attention to methods and procedures that must be obeyed to prevent damage to equipment. - NOTE: Calls attention to methods that make the job easier or give more information.

Weight Terms A.

Manufacturer Empty Weight (MEW) The weight of the structure, power plant, systems, furnishings and other items of equipment, part of a special aircraft configuration, with the fluids in closed systems (e.g. hydraulic fluid). The weights of all operator items are not included.

B.

Operator Items These items include: - Unusable fuel, - Oil for engines, IDG and APU, - Water for galleys and lavatories, - Chemical fluids for waste tanks, - Aircraft documents and tool kits, - Passenger seats and life vests, - Galley structures and fixed equipment, - Catering, - Flight and cabin crew and their baggage, - Emergency equipment that includes:

09-10-02

Page 1 Jul 01/09


Evacuation aids, life rafts, portable oxygen bottles and stowage boxes, extinguishers, megaphones, flash lights, axes, first aid kits, emergency radio beacons, fire resistant gloves and smoke goggles, demonstration kits, life vests for crew and children. C.

Operational Empty Weight (OEW) The OEW is the sum of the Manufacturer Empty Weight plus the operator items.

D.

Dry Operating Weight (DOW) The DOW is the total weight of an aircraft prepared for a special type of operation without all the usable fuel and traffic load. It is the sum of the OEW and the special items for the type of flight (e.g. catering, newspapers, pantry equipment etc.).

E.

Recoverable Empty Weight (REW) The REW is the sum of the MEW and the weight of the different operator items which are part of the aircraft. The REW does not include the crew and their baggage or catering equipment and supplies.

F.

Net Recoverable Weight (NRW) The NRW is the REW of the aircraft without the missing or removed aircraft equipment and components. It includes fuel, liquids and cargo remaining on board. The applicable recovery scenario is based on the NRW.

G.

Payload (P/L) The payload is the weight of the passengers, cargo and baggage.

H.

Center of Gravity (CG) The CG is the point where the aircraft can balance if it hangs at that point. It is the point where the aircraft weight is applied. If more weight is put in a different point, it causes an unbalancing force which is the ”moment”. In case of recovery action, the position of CG has to stay within certain predefined limits to ensure aircraft general stability

J.

Reference Chord (RC) or Mean Aerodynamic Chord (MAC) Usually the position of the CG is defined by a percentage of Reference Chord (%RC). The Reference Chord is a reference line used in the design of the wing. Its position relative to the wing and fuselage is accurately known. It represents the variation of position of the CG, according to the weight and balance management or other parameters. The normal position of the CG is considered at 25%RC. The position and dimensions of this reference are mentioned in TASK 03-00-00-558-801-A01. These dimensions are specially dedicated to an aircraft type.

K.

Maximum Design Landing Weight (MLW) The MLW is the maximum permitted weight at which the aircraft can land.

L.

Maximum Ramp Weight (MRW) / Maximum Taxi Weight (MTW) The MRW / MTW is the maximum permitted weight for ground maneuvers, that include taxi and run-up fuel.

09-10-02

Page 2 Jul 01/09


M. Maximum Takeoff Weight (MTOW) The MTOW is the maximum permitted weight when the brakes are released for takeoff, or at the start of the takeoff roll. N.

Maximum Zero Fuel Weight (MZFW) The MZFW is the maximum operating weight without usable fuel.

P.

Actual Zero Fuel Weight (AZFW) The AZFW is the sum of the operational empty weight and payload. The AZFW must never be more the maximum design zero fuel weight (MZFW).

Q.

Engineered Lifting An engineered lifting is a lifting of the aircraft in controlled conditions, with a predefined process using specific GSE. Before this procedure is started, it is necessary to do: - An accurate analysis of the requirements - An accurate engineering planning and a risk/hazard assessment - A lifting procedure approved by the local authority regulations.

09-10-02

Page 3 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-10-02-003-A01 Abbreviations 1.

List of Abbreviations The abbreviations that follow are used in the ARM. Aircraft A/C Aircraft Characteristics for Airport Planning AC AD Aircraft Datum AFRP Aramid Fiber Reinforced Plastic AMM Aircraft Maintenance Manual APU Auxiliary Power Unit ARM Aircraft Recovery Manual ARWG Aircraft Recovery Working Group ATA Air Transport Association of America AZFW Actual Zero Fuel Weight CBR California Bearing Ratio CFRP Carbon Fiber Reinforced Plastic CG Center of Gravity CL Center Line Cargo Loading System CLS CLSM Cargo Loading System Manual CRC Crew Rest Compartment CTR Center DBP Drawbar Pull DOW Dry Operating Weight Electronic Centralized Aircraft Monitoring ECAM EIS Electronic Instrument System EWH External Wiring Harness FDL Fuselage Datum Line FQI Fuel Quantity Indicator FR Frame FWD Forward GFRP Glass Fiber Reinforced Plastic GPU Ground Power Unit IATA International Air Transport Association IATP International Airline Technical Pool ICAO International Civil Aviation Organization

09-10-02

Page 4 Jul 01/09


IDG INBD INR IPC L/G LDG LDMCR LGCIU LH LRE MCDU MEW MFP MID MLG MLW MMI MRW MSN MTOW MTW MZFW NAS NLG NRW NWS OEW OUTBD P/BSW P/L PAX PSU RC RCT REW RH SRM

Integrated Drive Generator Inboard Inner Illustrated Parts Catalog Landing Gear Landing Lower Deck Mobile Crew Rest Landing Gear Control and Interface Unit Left Hand List of Radioactive and Hazardous Elements Manual Multipurpose Control & Display Unit Manufacturer’s Empty Weight Maintenance Facility Planning Manual Middle Main Landing Gear Maximum Design Landing Weight Manual Magnetic Indicator Maximum Ramp Weight Manufacturer’s Serial Number Maximum Design Take Off Weight Maximum Taxi Weight Maximum Design Zero Fuel Weight Navy and Army Standard Nose Landing Gear Net Recoverable Weight Nose Wheel Steering Operating Empty Weight Outboard Push Button Switch Payload Passenger Passenger Service Unit Reference Chord Rear Center Tank Recoverable Empty Weight Right Hand Structural Repair Manual

09-10-02

Page 5 Jul 01/09


STA STGR T TBD TBIL TEM THS TK TPIS ULD W&B WBM XFR

Station Stringer Trim To Be Define / Determined To Be Issued Later Illustrated Tool and Equipment Manual Trimmable Horizontal Stabilizer Tank Tire Pressure Indicating System Unit Load Device Weight and Balance Weight and Balance Manual Transfer List of Abbreviations TABLE 1

09-10-02

Page 6 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-10-02-002-A01 Aircraft Reference Axes 1.

Definitions See FIGURE 09-10-02-991-001-A. A.

AD (Aircraft Datum) Vertical plane (equation Y=0). It is shown as a line on XY and YZ drawings.

B.

FD (Fuselage Datum) Horizontal plane (equation Z=0). It is shown as a line (FDL) on XZ and YZ drawings.

C.

Fuselage Datum Line (FDL) View of FD plan on 2D drawings (XZ and YZ planes).

D.

Center Line (C/L) Intersection of AD and FD planes.

E.

H-arm Horizontal arm from X=0 in length unit.

F.

Y-arm Lateral arm Y=0 in length unit.

G.

Z-arm Vertical arm Z=0 in length unit.

09-10-02

Page 7 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

AD

+Z +X 2.540 m (100 in)

7.000 m (275.59 in)

0

+Y

N_AR_091002_1_0010101_01_00

Aircraft Reference Axes General FIGURE-09-10-02-991-001-A01

09-10-02

Page 8 Jul 01/09


09-10-03

AIRCRAFT DIMENSIONS


This chapter gives the main dimensions of the A318 aircraft: - See FIGURE 09-10-03-991-001-A and FIGURE 09-10-03-991-002-A.

09-10-03

Page 1 Jul 01/09


**ON A/C A318-100 30.96 m (101.57 ft)

6.62 m (21.72 ft)

5.07 m (16.63 ft)

10.25 m (32.62 ft) 31.45 m (103.18 ft)

34.10 m (111.88 ft) 12.45 m (40.85 ft)

7.59 m (12.93 ft) 11.51 m (37.76 ft)

NOTE: RELATED TO AIRCRAFT ATTITUDE AND WEIGHT

N_AR_091003_1_0010101_01_01

Aircraft Dimensions - A318 Side and Front View FIGURE-09-10-03-991-001-A01

09-10-03

Page 2 Jul 01/09


**ON A/C A318-100

30.64 m (100.52 ft)

A

A = CFM56: 8.97 m (29.43 ft) PW6000: 8.85 m (29.0 ft) N_AR_091003_1_0020101_01_01

Aircraft Dimensions - A318 Top View FIGURE-09-10-03-991-002-A01

09-10-03

Page 3 Jul 01/09




09-10-03

Page 4 Jul 01/09


**ON A/C A319-100

33.11 m (108.63 ft) 5.87 m (19.26 ft)

OPTIONAL

5.07 m (16.63 ft)

11.04 m (36.22 ft)

33.84 m (111.02 ft)

34.10 m (111.88 ft) 12.45 m (40.85 ft)

7.59 m (12.93 ft) 11.51 m (37.76 ft)


N_AR_091003_1_0030101_01_01


09-10-03

Page 5 Jul 01/09


**ON A/C A319-100

33.024 m (108.35 ft)

A

A = CFM56: 9.76 m (32.02 ft) IAE V2500: 9.60 m (31.5 ft) N_AR_091003_1_0040101_01_01


09-10-03

Page 6 Jul 01/09



This chapter gives the main dimensions of the A320 aircraft: - SeeFIGURE 09-10-03-991-005-AFIGURE 09-10-03-991-005-B and FIGURE 09-10-03-991-006-A.

09-10-03

Page 7 Jul 01/09


**ON A/C A320-100

36.84 m (120.87 ft)

5.87 m (19.26 ft)

5.07 m (16.63 ft)

12.63 m (41.44 ft) 37.57 m (123.36 ft)

33.91 m (111.25 ft) 12.45 m (40.85 ft)

7.59 m (12.93 ft) 11.51 m (37.76 ft)


N_AR_091003_1_0050101_01_01

Aircraft Dimensions - A320-100 Side and Front View FIGURE-09-10-03-991-005-A01

09-10-03

Page 8 Jul 01/09


**ON A/C A320-200

36.84 m (120.87 ft)

5.87 m (19.26 ft)

5.07 m (16.63 ft)

12.64 m (41.47 ft) 37.57 m (123.36 ft)

34.10 m (111.88 ft) 12.45 m (40.85 ft)

7.59 m (12.93 ft) 11.51 m (37.76 ft)


N_AR_091003_1_0050201_01_01

Aircraft Dimensions - A320-200 Side and Front View FIGURE-09-10-03-991-005-B01

09-10-03

Page 9 Jul 01/09


**ON A/C A320-100 A320-200

37.57 m (123.26 ft)

A


Aircraft Dimensions - A320-100/-200 Top View FIGURE-09-10-03-991-006-A01

09-10-03

Page 10 Jul 01/09




09-10-03

Page 11 Jul 01/09


**ON A/C A321-100 A321-200

43.69 m (143.34 ft) 5.87 m (19.26 ft)

5.07 m (16.63 ft)

16.91 m (55.48 ft) 44.51 m (146.03 ft)

34.10 m (111.88 ft) 12.45 m (40.85 ft)

7.59 m (12.93 ft) 11.51 m (37.76 ft) NOTE: RELATED TO AIRCRAFT ATTITUDE AND WEIGHT

N_AR_091003_1_0070101_01_01


09-10-03

Page 12 Jul 01/09


**ON A/C A321-100 A321-200

44.51 m (146.03 ft)

A



09-10-03

Page 13 Jul 01/09


09-10-04

AIRCRAFT STRUCTURAL SECTIONS


Sections and Components For the different structural sections and components of the aircraft see FIGURE 09-10-04-991-001AFIGURE 09-10-04-991-001-BFIGURE 09-10-04-991-001-CFIGURE 09-10-04-991-001-D.

09-10-04

Page 1 Jul 01/09


42

11/12

51

13/14

21

15

41

16/17

52

26

18

25

23 24

31

27

19

22

28

32

29

35

36

19.1

**ON A/C A318-100

N_AR_091004_1_0010101_01_01

Aircraft Structural Sections Structure Sections and Components - A318 (Sheet 1 of 2) FIGURE-09-10-04-991-001-A01

09-10-04

Page 2 Jul 01/09


**ON A/C A318-100

SECTION

DESIGNATION

11/12

NOSE FORWARD FUSELAGE

13/14

FORWARD FUSELAGE

15

CENTER FUSELAGE

16/17

REAR FUSELAGE

18

REAR FUSELAGE

19

CONE/REAR FUSELAGE

19.1

CONE/REAR FUSELAGE

21

CENTER WING

22

OUTER WING

23

LEADING EDGES

24

LEADING EDGES

25

SPOILERS

26

INBOARD FLAP

27

OUTBOARD FLAP

28

AILERON

29

WING−TIP

31

VERTICAL STABILIZER

32

RUDDER

35

HORIZONTAL STABILIZER

36

ELEVATOR

41

PYLONS

42

NACELLE SECTION

51

NOSE GEAR AND DOORS

52

MAIN GEAR AND DOORS

N_AR_091004_1_0010103_01_00

Aircraft Structural Sections Structure Sections and Components - A318 (Sheet 2 of 2) FIGURE-09-10-04-991-001-A01

09-10-04

Page 3 Jul 01/09


11/12

51

13/14

21

15

42

41

16/17

52

26

18

25

23 24

31

27

19

22

28

32

29

35

36

19.1

**ON A/C A319-100

N_AR_091004_1_0010201_01_01

Aircraft Structural Sections Structure Sections and Components - A319 (Sheet 1 of 2) FIGURE-09-10-04-991-001-B01

09-10-04

Page 4 Jul 01/09


**ON A/C A319-100

SECTION

DESIGNATION

11/12


13/14

FORWARD FUSELAGE

15

CENTER FUSELAGE

16/17

REAR FUSELAGE

18

REAR FUSELAGE

19

CONE/REAR FUSELAGE

19.1

CONE/REAR FUSELAGE

21

CENTER WING

22

OUTER WING

23

LEADING EDGES

24

LEADING EDGES

25

SPOILERS

26

INBOARD FLAP

27

OUTBOARD FLAP

28

AILERON

29

WING−TIP

31

VERTICAL STABILIZER

32

RUDDER

35


36

ELEVATOR

41

PYLONS

42

NACELLE SECTION

51

NOSE GEAR AND DOORS

52

MAIN GEAR AND DOORS

N_AR_091004_1_0010202_01_00

Aircraft Structural Sections Structure Sections and Components - A319 (Sheet 2 of 2) FIGURE-09-10-04-991-001-B01

09-10-04

Page 5 Jul 01/09


11/12

51

13/14

21

15

42

41

16/17

52

26

18

25

23 24

31

27

19

22

28

32

29

35

36

19.1

**ON A/C A320-100 A320-200

N_AR_091004_1_0010301_01_01

Aircraft Structural Sections Structure Sections and Components - A320 (Sheet 1 of 2) FIGURE-09-10-04-991-001-C01

09-10-04

Page 6 Jul 01/09


**ON A/C A320-100 A320-200

SECTION

DESIGNATION

11/12


13/14

FORWARD FUSELAGE

15

CENTER FUSELAGE

16/17

REAR FUSELAGE

18

REAR FUSELAGE

19

CONE/REAR FUSELAGE

19.1

CONE/REAR FUSELAGE

21

CENTER WING

22

OUTER WING

23/24

FIXED AND MOVING LEADING EDGES

25

SPOILERS

26

INBOARD FLAP

27

OUTBOARD FLAP

28

AILERON

29

WING−TIP

31

VERTICAL STABILIZER

32

RUDDER

35


36

ELEVATOR

41

PYLONS

42

NACELLE SECTION

51

NOSE GEAR AND DOORS

52

MAIN GEAR AND DOORS

N_AR_091004_1_0010302_01_00

Aircraft Structural Sections Structure Sections and Components - A320 (Sheet 2 of 2) FIGURE-09-10-04-991-001-C01

09-10-04

Page 7 Jul 01/09


36

29

11/12

51

13/14

14A

21

42

15

41

16A

26

23 52 24

25

16/17

27

22

28

18

31

19

35

32

19.1

**ON A/C A321-100 A321-200

N_AR_091004_1_0010401_01_01

Aircraft Structural Sections Structure Sections and Components - A321 (Sheet 1 of 2) FIGURE-09-10-04-991-001-D01

09-10-04

Page 8 Jul 01/09


**ON A/C A321-100 A321-200

DESIGNATION

SECTION 11/12


13/14

FORWARD FUSELAGE

14A

FORWARD FUSELAGE

15

CENTER FUSELAGE

16A

REAR FUSELAGE

16/17

REAR FUSELAGE

18

REAR FUSELAGE

19

CONE/REAR FUSELAGE

19.1

CONE/REAR FUSELAGE

21

CENTER WING

22

OUTER WING

23

LEADING EDGES

24

LEADING EDGES

25

SPOILERS

26

INBOARD FLAP

27

OUTBOARD FLAP

28

AILERON

29

WING−TIP

31

VERTICAL STABILIZER

32

RUDDER

35


36

ELEVATOR

41

PYLONS

42

NACELLE SECTION

51

NOSE GEAR AND DOORS

52

MAIN GEAR AND DOORS

N_AR_091004_1_0010402_01_00

Aircraft Structural Sections Structure Sections and Components - A321 (Sheet 2 of 2) FIGURE-09-10-04-991-001-D01

09-10-04

Page 9 Jul 01/09


09-10-05

COMPOSITE MATERIALS


Types of Material Some components and sections of the aircraft structure are made from composite materials see FIGURE 09-10-05-991-001-AFIGURE 09-10-05-991-001-BFIGURE 09-10-05-991-001-CFIGURE 09-10-05-991-001-D. The types of materials used are: - Carbon Fiber Reinforced Plastic (CFRP). - Glass Fiber Reinforced Plastic (GFRP). - Quartz Fiber Reinforced Plastic (QFRP).

09-10-05

Page 1 Jul 01/09


**ON A/C A318-100

CARBON FIBER REINFORCED PLASTIC (CFRP) GLASS FIBER REINFORCED PLASTIC (GFRP) ARAMID FIBER REINFORCED PLASTIC (AFRP) N_AR_091005_1_0010101_01_00

Composite Materials - A318 Location of Composite materials on the External surfaces of the Aircraft FIGURE-09-10-05-991-001-A01

09-10-05

Page 2 Jul 01/09


**ON A/C A319-100


Composite Materials - A319 Location of Composite materials on the External surfaces of the Aircraft FIGURE-09-10-05-991-001-B01

09-10-05

Page 3 Jul 01/09


**ON A/C A320-100 A320-200


Composite Materials - A320 Location of Composite materials on the External surfaces of the Aircraft FIGURE-09-10-05-991-001-C01

09-10-05

Page 4 Jul 01/09


**ON A/C A321-100 A321-200


Composite Materials - A321 Location of Composite materials on the External surfaces of the Aircraft FIGURE-09-10-05-991-001-D01

09-10-05

Page 5 Jul 01/09


09-10-06

FUSELAGE FRAMES AND H-ARM TABLE


This chapter gives the H-Arm of each frame. The H-arm is used to calculate the CG. The H-arm is the length of the lever arm from the datum point to the specific station. The datum point is at 2540 mm (100 in) forward of the radome.

09-10-06

Page 1 Jul 01/09


**ON A/C A318-100 FR24 FR24A FR22 FR26 FR20 FR28 FR18 FR30 FR16 FR34 FR14 FR36 FR12 FR38 FR10 FR40 FR8 FR42 FR6 FR4 FR2

X=0

CL

2.540m (100.00in)

FR1 FR25

FR3 FR5 FR7 FR9 FR11 FR13

FR

H−ARM

FR

m (in)

FR29

FR35 FR37 FR39

FR21 FR19

FR41

FR17 FR15

H−ARM m (in)

FR

NOSE

2.540 (100.00)

10

5.594 (220.24)

1

3.500 (137.80)

11

5.794 (228.10)

21

2

3.850 (151.57)

12

6.053 (238.30)

22

20

H−ARM m (in) 8.077 (318.00)

FR

H−ARM m (in)

30

11.913 (469.00)

8.433 (332.00)

34

12.446 (490.00)

8.700 (342.50)

35

12.979 (511.00)

3

4.090 (161.02)

13

6.311 (248.46)

23

8.966 (353.00)

36

13.513 (532.00)

4

4.330 (170.47)

14

6.570 (258.64)

24

9.500 (374.00)

37

14.021 (552.00)

5

4.546 (178.98)

15

6.828 (268.82)

24A

9.766 (384.50)

38

14.300 (563.00)

6

4.762 (187.48)

16

7.087 (279.00)

25

10.033 (395.00)

39

14.867 (585.32)

7

4.967 (195.55)

17

7.318 (288.11)

26

10.566 (416.00)

40

15.147 (596.32)

8

5.194 (204.49)

18

7.599 (299.17)

28

11.100 (437.00)

41

15.714 (618.64)

9

5.394 (212.36)

19

7.830 (308.27)

29

11.633 (458.00)

42

16.307 (642.00)

N_AR_091006_1_0010102_01_00

Fuselage Frames and H-arm - A318 Frame 1 to 42 (Sheet 1 of 2) FIGURE-09-10-06-991-001-A01

09-10-06

Page 2 Jul 01/09


**ON A/C A318-100

FR64 FR66

FR68 FR70 FR72 FR74 FR76 FR78 FR80 FR82 FR84 FR86

FR62 FR60 FR58 FR56 FR47 FR54 FR42 FR44 FR46

CL

FR87 FR85 FR83 FR81

FR43

FR55 FR45

FR61 FR63

FR57

FR65

FR57A FR59

FR

FR79 FR77 FR75 FR73 FR71

H−ARM

FR

m (in)

FR67

H−ARM m (in)

FR

FR69

H−ARM m (in)

FR

H−ARM m (in)

42

16.307 (642.00)

58

21.107 (531.00)

68

26.450 (1041.33)

78

30.536 (1202.21)

43

16.840 (663.00)

59

21.641 (852.00)

69

26.975 (1062.02)

79

30.855 (1214.77)

44

17.374 (684.00)

60

22.174 (873.00)

70

27.534 (1084.02)

80

31.174 (1227.33)

45

17.907 (705.00)

61

22.708 (894.00)

71

27.934 (1099.77)

81

31.544 (1241.89)

46

18.440 (726.00)

62

23.241 (915.00)

72

28.385 (1117.52)

82

31.914 (1256.46)

47/54

18.974 (747.00)

63

23.774 (936.00)

73

28.785 (1133.27)

83

32.369 (1274.37)

55

19.507 (768.00)

64

24.308 (957.00)

74

29.185 (1149.02)

84

32.824 (1292.29)

56

20.041 (789.00)

65

24.892 (980.00)

75

29.598 (1165.28)

85

33.279 (1310.20)

57

20.574 (810.00)

66

25.456 (1002.21)

76

30.011 (1181.54)

86

33.734 (1328.11)

57A

20.841 (820.50)

67

25.953 (1021.77)

77

30.424 (1197.80)

87

33.992 (1338.28)

N_AR_091006_1_0010103_01_00

Fuselage Frames and H-arm - A318 Frame 42 to 87 (Sheet 2 of 2) FIGURE-09-10-06-991-001-A01

09-10-06

Page 3 Jul 01/09


**ON A/C A319-100 FR22 FR20 FR18 FR16 FR14 FR12 FR10 FR8 FR6 FR4 FR2

X=0

FR24 FR24A FR26 FR28 FR30 FR34 FR36 FR38 FR40 FR42

CL

OPTIONAL 2.540m (100.00in)

FR1 FR3 FR5 FR7 FR9 FR11 FR13


FR15 FR17 FR19

FR

H−ARM

FR

m (in)

NOSE

2.540 (100.00)

11

FR43

FR25 FR23 FR21

H−ARM m (in) 5.794 (228.11)

FR

H−ARM m (in)

FR

H−ARM m (in)

22

8.700 (342.50)

35

13.767 (542.00)

1

3.500 (137.80)

12

6.052 (238.27)

23

8.966 (353.00)

36

14.300 (563.00)

2

3.850 (151.57)

13

6.311 (248.46)

24

9.500 (374.00)

37

14.808 (583.00)

3

4.090 (161.02)

14

6.570 (258.64)

24A

9.766 (384.50)

38

15.088 (594.00)

4

4.330 (170.47)

15

6.828 (268.82)

25

10.033 (395.00)

39

15.655 (616.32)

5

4.546 (178.98)

16

7.087 (279.00)

26

10.566 (416.00)

40

15.934 (627.32)

6

4.762 (187.48)

17

7.318 (288.11)

27

11.100 (437.00)

41

16.501 (649.64)

7

4.967 (195.55)

18

7.599 (299.17)

28

11.633 (458.00)

42

17.094 (673.00)

8

5.194 (204.49)

19

7.830 (308.27)

29

12.167 (479.00)

43

17.628 (694.00)

9

5.394 (212.36)

20

8.077 (318.00)

30

12.700 (500.00)

10

5.594 (220.24)

21

8.433 (332.00)

34

13.233 (521.00) N_AR_091006_1_0010201_01_00

Fuselage Frames and H-arm - A319 Frame 1 to 43 (Sheet 1 of 2) FIGURE-09-10-06-991-001-B01

09-10-06

Page 4 Jul 01/09


**ON A/C A319-100 FR64

FR66 FR68

FR62


FR60 FR58 FR56 FR55A FR54 FR52 FR46 FR44

CL



FR69

FR55

FR67

FR57

FR65

FR59 FR61

FR

H−ARM

FR

m (in)

FR63

H−ARM m (in)

FR

H−ARM m (in)

FR

H−ARM m (in)

43

17.628 (694.00)

57

22.962 (904.00)

68

28.843 (1135.35)

79

33.242 (1308.75)

44

18.161 (715.00)

58

23.495 (925.00)

69

29.362 (1156.00)

80

33.561 (1321.31)

45

18.694 (736.00)

59

24.028 (946.00)

70

29.921 (1178.00)

81

33.931 (1335.87)

46

19.228 (757.00)

60

24.562 (967.00)

71

30.321 (1193.75)

82

34.301 (1350.44)

47/51

19.761 (778.00)

61

25.095 (988.00)

72

30.772 (1211.50)

83

34.756 (1368.36)

52

20.295 (799.00)

62

25.629 (1009.00)

73

31.172 (1227.25)

84

35.211 (1386.27)

53

20.828 (820.00)

63

26.162 (1030.00)

74

31.572 (1243.00)

85

35.666 (1404.18)

54

21.361 (841.00)

64

26.695 (1051.00)

75

31.985 (1259.26)

86

36.121 (1422.10)

87

36.379 (1432.26)

55

21.895 (862.00)

65

27.280 (1074.00)

76

32.398 (1275.52)

55A

22.162 (872.50)

66

27.861 (1096.88)

77

32.811 (1291.78)

56

22.428 (883.00)

67

28.352 (1116.22)

78

32.923 (1296.19) N_AR_091006_1_0010202_01_00

Fuselage Frames and H-arm - A319 Frame 43 to 87 (Sheet 2 of 2) FIGURE-09-10-06-991-001-B01

09-10-06

Page 5 Jul 01/09


**ON A/C A320-100 A320-200 FR24 FR20

X=0

FR26 FR28 FR30


FR32 FR34 FR36 FR38 FR40 FR42

FR1 CL

2.540 m (100.00 in)

FR3 FR41 FR39 FR37


FR35 FR33 FR31

FR15 FR17 FR19 FR21

FR

H−ARM

FR

m (in)

FR29 FR27 FR25 FR23

H−ARM m (in)

FR

H−ARM m (in)

FR

H−ARM m (in)

NOSE

2.540 (100.00)

11

5.794 (228.11)

23

8.966 (352.99)

34

14.834 (584.02)

1

3.500 (137.80)

12

6.052 (238.27)

24

9.500 (374.02)

35

15.367 (605.00)

2

3.850 (151.57)

13

6.311 (248.46)

25

10.033 (395.00)

36

15.900 (625.98)

3

4.090 (161.02)

14

6.570 (258.66)

26

10.566 (415.98)

37

16.408 (645.98)

4

4.330 (170.47)

15

6.828 (268.82)

27

11.100 (437.01)

38

16.688 (657.01)

5

4.546 (178.98)

16

7.087 (279.02)

28

11.633 (457.99)

39

17.255 (679.33)

6

4.762 (187.48)

17

7.318 (288.11)

29

12.167 (479.02)

40

17.534 (690.31)

7

4.967 (195.55)

18

7.599 (299.17)

30

12.700 (500.00)

41

18.101 (712.64)

8

5.194 (204.49)

19

7.830 (308.27)

31

13.233 (520.98)

42

18.694 (735.98)

9

5.394 (212.36)

20

8.077 (317.99)

32

13.767 (542.01)

10

5.594 (220.24)

21

8.433 (332.01)

33

14.300 (562.99)

N_AR_091006_1_0010301_01_00

Fuselage Frames and H-arm - A320 Frame 1 to 42 (Sheet 1 of 2) FIGURE-09-10-06-991-001-C01

09-10-06

Page 6 Jul 01/09


**ON A/C A320-100 A320-200 FR64 FR62 FR60

FR66 FR68 FR70 FR72 FR74 FR76 FR78 FR80 FR82 FR84 FR86


CL

FR87 FR43 FR45 FR47 FR49 FR51 FR53 FR55 FR57 FR59 FR61 FR63

FR

H−ARM

FR

m (in)

H−ARM m (in)

FR

FR85 FR83 FR81 FR79 FR77 FR75 FR73 FR71 FR69 FR67 FR65 H−ARM m (in)

FR

H−ARM m (in)

42

18.694 (735.98)

54

25.095 (987.99)

66

31.577 (1243.19)

78

36.657 (1443.19)

43

19.228 (757.01)

55

25.629 (1009.02)

67

32.074 (1262.76)

79

36.976 (1455.75)

44

19.761 (777.99)

56

26.162 (1030.00)

68

32.571 (1282.32)

80

37.295 (1468.31)

45

20.295 (799.02)

57

26.695 (1050.98)

69

33.096 (1302.99)

81

37.665 (1482.87)

46

20.828 (820.00)

58

27.229 (1072.01)

70

33.655 (1325.00)

82

38.035 (1497.44)

47

21.361 (840.98)

59

27.762 (1092.99)

71

34.055 (1340.75)

83

38.490 (1515.35)

48

21.895 (862.01)

60

28.296 (1114.02)

72

34.506 (1358.50)

84

38.945 (1533.27)

49

22.426 (882.99)

61

28.829 (1135.00)

73

34.906 (1374.25)

85

39.400 (1551.18)

50

22.962 (904.02)

62

29.362 (1155.98)

74

35.306 (1390.00)

86

39.855 (1569.09)

51

23.495 (925.00)

63

29.896 (1177.01)

75

35.719 (1406.26)

87

40.113 (1579.25)

52

24.028 (945.98)

64

30.429 (1197.99)

76

36.132 (1422.52)

53

24.562 (967.01)

65

31.013 (1220.98)

77

36.545 (1438.78) N_AR_091006_1_0010302_01_00

Fuselage Frames and H-arm - A320 Frame 42 to 87 (Sheet 2 of 2) FIGURE-09-10-06-991-001-C01

09-10-06

Page 7 Jul 01/09


**ON A/C A321-100 A321-200 X=0



CL

2.540 m (100.00 in)

FR35 FR33 FR31 FR29


FR

H−ARM m (in)

NOSE

2.540 (100.00)

FR 12


H−ARM m (in)

FR

H−ARM m (in)

6.052 (238.27)

25

10.033 (395.00)

1

3.500 (137.80)

13

6.311 (248.46)

26

10.566 (415.98)

2

3.850 (151.57)

14

6.570 (258.66)

27

11.100 (437.01)

3

4.090 (161.02)

15

6.828 (268.82)

28

11.633 (457.99)

4

4.330 (170.47)

16

7.087 (279.02)

29

12.167 (479.02)

5

4.546 (178.98)

17

7.318 (288.11)

30

12.700 (500.00)

6

4.762 (187.48)

18

7.599 (299.17)

31

13.233 (520.98)

7

4.967 (195.55)

19

7.830 (308.27)

32

13.767 (542.01)

8

5.194 (204.49)

20

8.077 (317.99)

33

14.300 (562.99)

9

5.394 (212.36)

21

8.433 (332.01)

34

14.834 (584.02)

35

15.367 (605.00)

10

5.594 (220.24)

23

8.966 (352.99)

11

5.794 (228.11)

24

9.500 (374.02) N_AR_091006_1_0010401_01_00

Fuselage Frames and H-arm - A321 Frame 1 to 35 (Sheet 1 of 3) FIGURE-09-10-06-991-001-D01

09-10-06

Page 8 Jul 01/09


**ON A/C A321-100 A321-200

FR44

FR46 FR47 FR47 2

FR42 FR40 FR38 FR36 FR35 8 FR35 6

FR47 4 FR48 FR50 FR52

FR35 4

FR54 FR56

FR35 2 FR35

CL

FR35 1

FR55

FR35 3 FR35 5 FR35 7

FR 35 35 1 35 2 35 3 35 4 35 5 35 6 35 7 35 8 36

FR37 FR39 FR41 FR43

H−ARM m (in)

FR

FR45 FR47 1 FR47 3

H−ARM

FR

m (in)

15.367 (605.00)

39

21.522 (847.32)

15.900 (625.98)

40

21.801 (858.31)

16.433 (646.97)

41

16.967 (667.99) 17.501 (689.02)

47

FR53 FR51 FR49 FR47 5

H−ARM m (in)

22.368 (880.63)

4 47 5 48

27.762 (1092.99)

42

22.962 (904.02)

49

29.362 (1155.98)

43

23.495 (925.00)

50

29.896 (1177.01)

18.034 (710.00)

44

24.025 (945.87)

51

30.429 (1197.99)

18.567 (730.98)

45

24.562 (967.01)

52

30.963 (1219.02)

19.101 (752.01)

46

25.095 (987.01)

53

31.496 (1240.00)

19.634 (772.99)

47 47 1 47 2 47 3

25.629 (1009.02)

54

32.029 (1260.98)

26.162 (1030.00)

55

32.563 (1282.01)

26.695 (1050.98)

56

33.096 (1302.99)

20.168 (794.02)

37

20.676 (814.02)

38

20.955 (825.00)

28.296 (1114.02) 28.829 (1135.00)

27.229 (1072.01) N_AR_091006_1_0010402_01_00


09-10-06

Page 9 Jul 01/09


**ON A/C A321-100 A321-200

FR74

FR72 FR70 FR68 FR66

FR76 FR78 FR80 FR82


FR84 FR86

CL


FR57 FR59

FR77 FR75

FR61 FR63 FR65

FR73 FR71

FR67

FR

H−ARM m (in)

56

33.096 (1302.99)

57

33.629 (1323.98)

58

34.163 (1345.00)

FR

FR69

H−ARM

FR

m (in)

H−ARM m (in)

39.008 (1535.75)

78

43.591 (1716.18)

68

39.505 (1555.32)

79

43.910 (1728.74)

69

40.030 (1575.99)

80

44.229 (1741.30) 44.599 (1755.87)

67

59

34.696 (1365.98)

70

40.589 (1597.99)

81

60

35.230 (1387.01)

71

40.989 (1613.74)

82

44.969 (1770.43)

61

35.763 (1407.99)

72

41.440 (1631.50)

83

45.424 (1788.35)

62

36.297 (1429.02)

73

41.840 (1647.24)

84

45.879 (1806.26)

63

36.830 (1450.00)

74

42.240 (1662.99)

85

46.334 (1824.17)

64

37.363 (1470.99)

75

42.653 (1679.25)

86

46.789 (1842.09)

65

37.948 (1494.02)

76

43.066 (1695.51)

87

47.047 (1852.25)

66

38.511 (1516.18)

77

43.479 (1711.77)

N_AR_091006_1_0010403_01_00


09-10-06

Page 10 Jul 01/09


09-10-08

WING RIBS AND STATIONS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-10-08-001-A01 Wing Ribs and Stations 1.

General This chapter gives the Wing Ribs and stations, see FIGURE 09-10-08-991-001-AFIGURE 09-10-08-991-001-B The position of each Wing Rib is identified by a station (STA). All measurements are: - At 90 degrees to Rib 1 - Measured between Rib 1 and the intersection of each rib datum with the Front Spar datum at the lower outside skin surface. NOTE : The stations are given in centimeters with no conversion

09-10-08

Page 1 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A

A 1868 mm (73.543 in)

AD

RIB1

STA0 WY

RIB2

STA70

RIB3 RIB4

STA141 STA196

RIB5

STA251

RIB6

STA306

RIB6B

STA360 STA376

RIB9

STA407

RIB11

STA551 STA613

RIB16 RIB17 RIB18 RIB19 RIB20 RIB21

STA670 STA732 STA779 STA827 STA874 STA924 STA970 STA1020


RIB10


STA486

A

RIB8 RIB7

RIB22 RIB23

STA1073 STA1120 STA1166

RIB24 RIB25

STA1228 NOTE : ALL STA NUMBERS ARE GIVEN IN cm STATION REFERENCES GIVEN, APPLY TO THE INTERSECTION OF THE RIB DATUMS WITH THE FRONT SPAR DATUM AT THE OUTSIDE SKIN SURFACE.

RIB26

STA1287 STA1346 STA1406 STA1446

RIB27 N_AR_091008_1_0010101_01_00

Wing Ribs and Stations A318/A319/A320 FIGURE-09-10-08-991-001-A01

09-10-08

Page 2 Jul 01/09


**ON A/C A321-100 A321-200 A

A 1868 mm (73.543 in)

AD

RIB1

STA0 WY

RIB2

STA70 RIB3 RIB4

STA141 STA196 STA251

RIB5 RIB6

STA306

RIB6B

STA360 STA376 RIB10

STA407

RIB9

RIB8

RIB7

RIB11 RIB12 RIB13 RIB14 RIB15


RIB16 RIB17

STA670 STA732


STA779 STA827 STA874 STA924 STA970 STA1020

A LH SHOWN RH SYMMETRICAL

RIB22 RIB23

STA1073 STA1120 STA1166

RIB24 RIB25

STA1228 STA1287 NOTE : ALL STA NUMBERS ARE GIVEN IN cm STATION REFERENCES GIVEN, APPLY STA1346 TO THE INTERSECTION OF THE RIB STA1406 DATUMS WITH THE FRONT SPAR DATUM STA1446 AT THE OUTSIDE SKIN SURFACE.

RIB26

RIB27 N_AR_091008_1_0010201_01_00

Wing Ribs and Stations A321 FIGURE-09-10-08-991-001-B01

09-10-08

Page 3 Jul 01/09


09-10-09

HORIZONTAL STABILIZERS RIBS AND STATIONS


This chapter gives the horizontal stabilizer ribs and stations (see FIGURE 09-10-09-991-001-A). The position of each horizontal stabilizer rib is identified with a station (STA) which is the distance between the rib and RIB1 datum. NOTE : The stations are given in centimeters with no conversion.

09-10-09

Page 1 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

A

RIB2

RIB1

CL STA0

RIB3

RIB4 RIB5 UPPER SURFACE

STA82

RIB6

STA69

RIB7 RIB8

STA131

RIB9


RIB10

STA297 RIB11

STA342 STA404

A

RIB12

STA466


RIB13 STA527 STA589

NOTE: ALL STA NUMBERS ARE GIVEN IN cm.

RIB14

STA601 N_AR_091009_1_0010101_01_00

Horizontal Stabilizer Ribs and Stations FIGURE-09-10-09-991-001-A01

09-10-09

Page 2 Jul 01/09


09-10-10

DOOR SIZES AND LOCATIONS


This chapter gives data related to the aircraft doors. There are different types of door installed on the aircraft. The different doors are given in the sections that follow: - For the passenger/crew doors and emergency exit doors, see DESC 09-10-10-002-A01. - For the cargo compartment doors, see DESC 09-10-10-003-A01. - For the nose landing gear doors, see DESC 09-10-10-004-A01. - For the main landing gear doors, see DESC 09-10-10-005-A01. - For the APU doors, see DESC 09-10-10-006-A01.

09-10-10

Page 1 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-10-10-002-A01 Passenger/Crew Doors and Emergency Exit Doors 1.

General This section gives data related to the identification, location and clearances of the passenger/crew and emergency exit doors.

2.

Location For the location of the passenger/crew and emergency exit doors see FIGURE 09-10-10-991-001AFIGURE 09-10-10-991-001-BFIGURE 09-10-10-991-001-CFIGURE 09-10-10-991-001-D.

3.

Clearances For the clearances of these doors: - FWD Pax/Crew doors, see FIGURE 09-10-10-991-002-A. - AFT Pax/Crew doors, see FIGURE 09-10-10-991-004-A. - Emergency Exits, see FIGURE 09-10-10-991-003-AFIGURE 09-10-10-991-003-BFIGURE 09-10-10-991-003-CFIGURE 09-10-10-991-003-D.

09-10-10

Page 2 Jul 01/09


5.02 m (16.5 ft)

N_AR_091010_1_0010101_01_00

FORWARD PASSENGER/CREW DOOR

12.89 m (42.29 ft)

23.52 m (77.17 ft)

EMERGENCY EXIT

REAR PASSENGER/CREW DOOR

**ON A/C A318-100

Passenger/Crew Doors and Emergency Exits Location - A318 FIGURE-09-10-10-991-001-A01

09-10-10

Page 3 Jul 01/09

09-10-10 EMERGENCY EXIT (OPTIONAL)


5.02 m (16.5 ft)

12.83 m (42.1 ft)

13.68 m (44.9 ft)

EMERGENCY EXIT

25.91 m (85 ft)

N_AR_091010_1_0010201_01_00



**ON A/C A319-100

Passenger/Crew Doors and Emergency Exits Location - A319 FIGURE-09-10-10-991-001-B01

Page 4 Jul 01/09


5.02 m (16.5 ft)

N_AR_091010_1_0010301_01_00


14.43 m (47.34 ft)

15.28 m (50.13 ft)

29.64 m (97.24 ft)

EMERGENCY EXIT


**ON A/C A320-100 A320-200

Passenger/Crew Doors and Emergency Exits Location - A320 FIGURE-09-10-10-991-001-C01

09-10-10

Page 5 Jul 01/09


5.02 m (16.5 ft)

N_AR_091010_1_0010401_01_00


13.84 m (45.41 ft)

27.49 m (81.33 ft)

36.57 m (119.98 ft)

EMERGENCY EXIT


**ON A/C A321-100 A321-200

Passenger/Crew Doors and Emergency Exits Location - A321 FIGURE-09-10-10-991-001-D01

09-10-10

Page 6 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 1.80 m (70.87 in) 0.81 m (31.89 in) 0.48 m (18.9 in)

CL 2.54 m (100 in)

0.51 m (20.08 in)

CRITICAL CLEARANCE LIMIT

CL 2.375 m (93.5 in)

1.85 m (72.83 in)

CL

0.03 m (1.18 in)

SEE 09−10−11

N_AR_091010_1_0020101_01_00

Forward Passenger/Crew Doors Clearances FIGURE-09-10-10-991-002-A01

09-10-10

Page 7 Jul 01/09


**ON A/C A318-100 CL

A 0.56 m (22.05 in)

SEE 09−10−11

A CL 0.9 m (35.43 in) 0.12 m (4.72 in)

0.495 m (19.49 in) (TOP OF FLOOR)

A A N_AR_091010_1_0030101_01_00

Emergency Exits Clearances - A318 FIGURE-09-10-10-991-003-A01

09-10-10

Page 8 Jul 01/09


**ON A/C A319-100 OPTIONAL

CL

0.85 m (33.46 in)

A 0.50 m (19.68 in)

SEE 09−10−11

A CL 0.9 m (35.43 in) 0.12 m (4.72 in)

0.495 m (19.49 in) (TOP OF FLOOR)

A A N_AR_091010_1_0030201_01_00

Emergency Exits Clearances - A319 FIGURE-09-10-10-991-003-B01

09-10-10

Page 9 Jul 01/09


**ON A/C A320-100 A320-200

CL

0.85 m (33.46 in)

A 0.50 m (19.68 in)

SEE 09−10−11

A CL 0.9 m (35.43 in) 0.12 m (4.72 in)

0.495 m (19.49 in) (TOP OF FLOOR)

A A N_AR_091010_1_0030301_01_00

Emergency Exits Clearances - A320 FIGURE-09-10-10-991-003-C01

09-10-10

Page 10 Jul 01/09


**ON A/C A321-100 A321-200 CENTER OF FREE AISLE

CENTER OF FREE AISLE

CL 0.56 m (22.05 in)

0.56 m (22.05 in)

CRITICAL CLEARANCE LIMIT

CRITICAL CLEARANCE LIMIT 1.73 m (68.11 in)

1.73 m (68.11 in) 0.83 m (32.68 in)

FREE AISLE 0.76 m (29.92 in)

0.83 m (32.68 in)

B

A

FREE AISLE 0.76 m (29.92 in)

0.04 m (1.57 in)

0.04 m (1.57 in)

B

A CL 2.36 m (92.91 in)

2.38 m (93.7 in)

CL

0.39 m (15.35 in)

2.36 m (92.91 in)

1.52 m (59.84 in)

1.85 m (72.83 in)

1.52 m (59.84 in)

(TOP OF FLOOR)

0.43 m (16.93 in)

A A

0.4 m (15.75 in)

B B

0.39 m (15.35 in)

N_AR_091010_1_0030401_01_00

Emergency Exits Clearances - A321 FIGURE-09-10-10-991-003-D01

09-10-10

Page 11 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 1.79 m (70.47 in) 0.81 m (31.89 in)

CL

A CRITICAL CLEARANCE LIMIT

A

0.58 m (22.83 in)

CL

2.44 m (96.06 in)

1.85 m (72.83 in)

CL

SEE 09−10−11

0.60 m (23.62 in)

0.03 m (1.18 in)

A A N_AR_091010_1_0040101_01_00

Aft Passenger/Crew Doors Clearances FIGURE-09-10-10-991-004-A01

09-10-10

Page 12 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-10-10-003-A01 Cargo Compartment Doors 1.

General This section gives data related to the identification, location and clearances of the different cargo compartment doors (see FIGURE 09-10-10-991-006-AFIGURE 09-10-10-991-006-BFIGURE 09-10-10-991-006-CFIGURE 09-10-10-991-006-D). There are three cargo compartment doors: - The forward cargo compartment door. - The aft cargo compartment door. - The bulk cargo compartment door (A320 and A321 only).

09-10-10

Page 13 Jul 01/09


N_AR_091010_1_0060101_01_00

REAR CARGO COMPARTMENT DOOR

18.96 m (62.2 ft)

7.89 m (25.89 ft)

FORWARD CARGO COMPARTMENT DOOR

**ON A/C A318-100

Cargo Compartments - A318 Location (Sheet 1 of 3) FIGURE-09-10-10-991-006-A01

09-10-10

Page 14 Jul 01/09


**ON A/C A318-100

A

1.495 m (58.858 in)

CL

1.24 m (48.82 in)

1.33 m (52.36 in)

SEE 09−10−11

A 3.945 m (151.31 in)

A A

CL

2.9 m (114.17 in)

A

A = CFM ENGINES 0.24 m (0.78 ft) PW ENGINES 0.39 m (1.27 ft) N_AR_091010_1_0060102_01_01

Cargo Compartments - A318 Clearances - Forward Cargo Compartment Door (Sheet 2 of 3) FIGURE-09-10-10-991-006-A01

09-10-10

Page 15 Jul 01/09


**ON A/C A318-100 A 1.43 m (56.3 in)

CL

1.33 m (52.36 in)

1.23 m (48.43 in)

SEE 09−10−11

A 3.945 m (155.31 in)

A A

CL

1.00 m (39.37 in)

N_AR_091010_1_0060103_01_00

Cargo Compartments - A318 Clearances - Aft Cargo Compartment Door (Sheet 3 of 3) FIGURE-09-10-10-991-006-A01

09-10-10

Page 16 Jul 01/09


N_AR_091010_1_0060201_01_00


20.58 m (67.52 ft)

8.16 m (26.77 ft)


**ON A/C A319-100

Cargo Compartments Location (Sheet 1 of 3) FIGURE-09-10-10-991-006-B01

09-10-10

Page 17 Jul 01/09


**ON A/C A319-100

A

1.495 m (58.86 in)

CL

1.24 m (48.82 in)

1.82 m (74.65 in)

SEE 09−10−11

A 3.945 m (151.31 in)

A A

CL

2.71 m (106.69 in)

A

A = CFM ENGINES 0.67 m (2.20 ft) IAE ENGINES 0.51 m (1.67 ft) N_AR_091010_1_0060202_01_01

Cargo Compartments Clearances - Forward Cargo Compartment Door (Sheet 2 of 3) FIGURE-09-10-10-991-006-B01

09-10-10

Page 18 Jul 01/09


**ON A/C A319-100 A 1.43 m (56.3 in)

CL

1.82 m (71.65 in)

1.23 m (48.43 in)

SEE 09−10−11

A 3.945 m (155.31 in)

A A

CL

1.60 m (62.90 in)

N_AR_091010_1_0060203_01_00

Cargo Compartments Clearances - Aft Cargo Compartment Door (Sheet 3 of 3) FIGURE-09-10-10-991-006-B01

09-10-10

Page 19 Jul 01/09


N_AR_091010_1_0060301_01_00

27.27 m (89.46 ft)

BULK CARGO COMPARTMENT DOOR


22.69 m (77.44 ft)

8.16 m (26.77 ft)


**ON A/C A320-100 A320-200

Cargo Compartments Location (Sheet 1 of 4) FIGURE-09-10-10-991-006-C01

09-10-10

Page 20 Jul 01/09


**ON A/C A320-100 A320-200

A

1.495 m (58.86 in)

CL

1.24 m (48.82 in)

1.82 m (71.65 in)

SEE 09−10−11

A 3.945 m (155.31 in)

A A

CL

2.71 m (106.69 in)

A

A = CFM ENGINE 2.27 m (7.45 ft) V2500 ENGINE 2.11 m (6.92 ft) N_AR_091010_1_0060302_01_01

Cargo Compartments Clearances - Forward Cargo Compartment Door (Sheet 2 of 4) FIGURE-09-10-10-991-006-C01

09-10-10

Page 21 Jul 01/09


**ON A/C A320-100 A320-200 A 1.43 m (56.3 in)

CL

1.82 m (71.65 in)

1.23 m (48.43 in)

SEE 09−10−11

A 3.945 m (155.31 in)

A A

CL

2.03 m (79.92 in)

N_AR_091010_1_0060303_01_00

Cargo Compartments Clearances - Aft Cargo Compartment Door (Sheet 3 of 4) FIGURE-09-10-10-991-006-C01

09-10-10

Page 22 Jul 01/09


**ON A/C A320-100 A320-200

A

CL

0.77 m (30.32 in)

0.95 m (37.4 in)

A

SEE 09−10−11 0.89 m (35.04 in)

A A

CL

2.19 m (86.22 in) 6.10 m (240.16 in)

N_AR_091010_1_0060304_01_00

Cargo Compartments Clearances - Bulk Cargo Compartment Door (Sheet 4 of 4) FIGURE-09-10-10-991-006-C01

09-10-10

Page 23 Jul 01/09


33.20 m (108.91 ft)

BULK CARGO COMPARTMENT DOOR


29.62 m (97.18 ft)


8.16 m (26.77 ft)

N_AR_091010_1_0060401_01_00

**ON A/C A321-100 A321-200

Cargo Compartments Location (Sheet 1 of 4) FIGURE-09-10-10-991-006-D01

09-10-10

Page 24 Jul 01/09


**ON A/C A321-100 A321-200

A

1.495 m (58.86 in)

1.24 m (48.82 in)

1.82 m (71.65 in)

A

SEE 09−10−11

3.945 m (155.31 in)

A A CL

2.71 m (106.69 in)

A

A = CFM ENGINE 6.54 m (21.45 ft) V2500 ENGINE 6.38 m (20.93 ft) N_AR_091010_1_0060402_01_02

Cargo Compartments Clearances - Forward Cargo Compartment Door (Sheet 2 of 4) FIGURE-09-10-10-991-006-D01

09-10-10

Page 25 Jul 01/09


**ON A/C A321-100 A321-200 A 1.43 m (56.3 in)

1.23 m (48.43 in)

1.82 m (71.65 in)

SEE 09−10−11

A 3.945 m (155.31 in)

A A

CL

4.69 m (184.65 in)

N_AR_091010_1_0060403_01_00

Cargo Compartments Clearances - Aft Cargo Compartment Door (Sheet 3 of 4) FIGURE-09-10-10-991-006-D01

09-10-10

Page 26 Jul 01/09


**ON A/C A321-100 A321-200 A

CL

A 0.95 m (37.4 in)

0.77 m (30.32 in)

A A

SEE 09−10−11

0.89 m (35.04 in)

CL

2.19 m (86.22 in) 8.76 m (344.88 in)

N_AR_091010_1_0060404_01_00

Cargo Compartments Clearances - Bulk Cargo Compartment Door (Sheet 4 of 4) FIGURE-09-10-10-991-006-D01

09-10-10

Page 27 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-10-10-004-A01 Nose Landing Gear Doors 1.

General This section gives data related to the location and clearances of the nose landing gear doors. The nose landing gear has two pair of doors, the forward NLG doors and the rear NLG doors.

2.

Location and Clearances For the location and clearances of the nose landing gear doors see FIGURE 09-10-10-991-010-A.

09-10-10

Page 28 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

0.49 m (19.29 in)

2.13 m (83.86 in)

0.50 m (19.69 in)

0.52 m (20.47 in)

01

1.50 m 01 (59.01 in)

1.40 m 01 (55.19 in)

CG = 25% RC N_AR_091010_1_0100101_01_00

Door Sizes and Locations Nose Landing Gear Doors FIGURE-09-10-10-991-010-A01

09-10-10

Page 29 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-10-10-005-A01 Main Landing-Gear Doors 1.

General This section gives data related to the location and clearances of the main landing-gear doors. See FIGURE 09-10-10-991-011-AFIGURE 09-10-10-991-011-BFIGURE 09-10-10-991-011-CFIGURE 09-10-10-991-011-D.

09-10-10

Page 30 Jul 01/09


**ON A/C A318-100

CL

A 1.83 m (72.1 in)

13.97 m (550 in)

CL 1.94 m (76.38 in) 0.485 m (19.095 in)

0.207 m (8.14 in)

84°

1 (69 .76 m .29 in)

0.14 m 01 (5.51 in)

1.23 m (48.43 in)

GROUND LINE

A 01

CG = 25% RC

LH SHOWN RH SYMMETRICAL N_AR_091010_1_0110101_01_00

Location and Clearances Main Landing Gear Doors - A318 FIGURE-09-10-10-991-011-A01

09-10-10

Page 31 Jul 01/09


**ON A/C A319-100

CL

A 1.83 m (72.1 in)

14.76 m (581.1in)

CL 1.94 m (76.38 in) 0.485 m (19.095 in)

0.207 m (8.14 in)

84°

1 (69 .76 m .29 in)

0.14 m 01 (5.51 in)

1.23 m (48.43 in)

GROUND LINE

A 01

CG = 25% RC


Location and Clearances Main Landing Gear Doors - A319 FIGURE-09-10-10-991-011-B01

09-10-10

Page 32 Jul 01/09


**ON A/C A320-100 A320-200

CL

A 1.83 m (72.1 in)

16.36 m (644.09 in)

CL 1.94 m (76.38 in) 0.485 m (19.095 in)

0.207 m (8.14 in)

84°

1 (69 .76 m .29 in)

0.14 m 01 (5.51 in)

1.23 m (48.43 in)

GROUND LINE

A 01

CG = 25% RC


Location and Clearances Main Landing Gear Doors - A320 - Twin Wheel MLG (Sheet 1 of 2) FIGURE-09-10-10-991-011-C01

09-10-10

Page 33 Jul 01/09


**ON A/C A320-100 A320-200

CL

A 2.23 m (87.8 in)

16.23 m (638.98 in)

CL 1.94 m (76.38 in) 0.485 m (19.095 in)

82.5°

1 (6 .76 9.2 m 9i n)

0.16 m (6.3 in) 1.27 m (50.0 in)

GROUND LINE

A LH SHOWN RH SYMMETRICAL N_AR_091010_1_0110302_01_02

Location and Clearances Main Landing Gear Doors - A320 - Optional Four Wheel Bogie MLG (Sheet 2 of 2) FIGURE-09-10-10-991-011-C01

09-10-10

Page 34 Jul 01/09


**ON A/C A321-100 A321-200

CL

A 1.83 m (72.1 in)

20.62 m (811.81 in)

CL 1.94 m (76.38 in) 0.485 m (19.095 in)

0.207 m (8.14 in)

84°

1 (69 .76 m .29 in)

0.14 m 01 (5.51 in)

1.23 m (48.43 in)

GROUND LINE

A 01

CG = 25% RC


Location and Clearances Main Landing Gear Doors - A321 FIGURE-09-10-10-991-011-D01

09-10-10

Page 35 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-10-10-006-A01 APU Doors 1.

General This section gives data related to the location and clearances of the APU doors.

2.

Location and Clearances For the location and clearances of the APU doors see FIGURE 09-10-10-991-014-A.

09-10-10

Page 36 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

FR80 FR84

CL

4.05 m (159.45 in) 01

3.42 m (134.65 in) 01

01

CG = 25% RC N_AR_091010_1_0140101_01_01

Location and Clearances APU Doors FIGURE-09-10-10-991-014-A01

09-10-10

Page 37 Jul 01/09


09-10-11

AIRCRAFT GROUND CLEARANCES


This chapter gives data related to the distance from different components/points on the aircraft to the ground. For the basic ground clearances of the aircraft see FIGURE 09-10-11-991-001-A. The dimensions given are approximate and can change with: - The aircraft weight. - The type of tire installed. - The aircraft attitude. - The climate conditions. For the ground clearances of the: - Extended leading edge slats see FIGURE 09-10-11-991-002-A. - Extended trailing edge flaps see FIGURE 09-10-11-991-003-A. - Extended spoilers see FIGURE 09-10-11-991-004-A. - Ailerons in the down position see FIGURE 09-10-11-991-005-A. - Ailerons in the up position see FIGURE 09-10-11-991-006-A. - Flap tracks with the flaps extended see FIGURE 09-10-11-991-007-A.

09-10-11

Page 1 Jul 01/09


**ON A/C A318-100

J

G

H

F

M

E

B

C

L

A

D

K2

A

m

ft

3.44

11.29

G

m

ft

2.31

7.58

B

2.08

6.62

H

3.72

12.21

C

1.79

5.87

J

12.93

42.42

D

5.93

19.46

K

5.06

16.60

E (PW)

0.77

2.53

K2

4.06

13.32

E (CFM)

0.65

2.13

L

5.60

18.37

F

1.70

5.58

M

3.95

12.96

K

N_AR_091011_1_0010101_01_00

Aircraft Ground Clearances Basic Ground Clearances FIGURE-09-10-11-991-001-A01

09-10-11

Page 2 Jul 01/09


**ON A/C A318-100

X

Y

Z

A’ B’

C’ D’

E’ F’

G’

HEIGHT FROM GROUND m

ft

X

2.55

8.36

Y

2.97

9.74

Z

3.06

10.03

A’

3.36

11.02

B’

3.36

11.02

C’

3.61

11.84

D’

3.61

11.84

E’

3.86

12.66

F’

3.86

12.66

G’

4.10

13.45

N_AR_091011_1_0020101_01_00

Aircraft Ground Clearances Leading Edge Slats - Extended FIGURE-09-10-11-991-002-A01

09-10-11

Page 3 Jul 01/09


**ON A/C A318-100

D

B C

A


ft

A

2.05

6.72

B

2.77

9.08

C

2.81

9.21

D

3.65

11.97

N_AR_091011_1_0030101_01_00

Aircraft Ground Clearances Trailing Edge Flaps - Extended FIGURE-09-10-11-991-003-A01

09-10-11

Page 4 Jul 01/09


**ON A/C A318-100

Q

R

S

T

U

V

W


ft

Q

4.60

15.09

R

4.48

14.69

S

4.35

14.27

T

4.21

13.81

U

4.07

13.35

V

4.01

13.15

W

3.75

12.30

N_AR_091011_1_0040101_01_00

Aircraft Ground Clearances Spoilers - Extended FIGURE-09-10-11-991-004-A01

09-10-11

Page 5 Jul 01/09


**ON A/C A318-100

L

M


ft

L

4.19

13.74

M

3.84

12.60

N_AR_091011_1_0050101_01_00

Aircraft Ground Clearances Ailerons - Down FIGURE-09-10-11-991-005-A01

09-10-11

Page 6 Jul 01/09


**ON A/C A318-100

N

P


ft

N

4.57

15.0

P

4.37

14.3

N_AR_091011_1_0060101_01_00

Aircraft Ground Clearances Ailerons - Up FIGURE-09-10-11-991-006-A01

09-10-11

Page 7 Jul 01/09


**ON A/C A318-100

H

K

J


ft

H

2.18

7.15

J

2.66

8.73

K

3.10

10.17

N_AR_091011_1_0070101_01_00

Aircraft Ground Clearances Flap Track Fairings - Flaps Extended FIGURE-09-10-11-991-007-A01

09-10-11

Page 8 Jul 01/09




09-10-11

Page 9 Jul 01/09


**ON A/C A319-100

OPTIONAL

J

G

H

F

M

B

E

C

A

D

NOTE: POINTS A, B, G, H, M AND P ARE MID DOOR AT FLOOR LEVEL.

L

K

A

m

ft

3.45

11.32

m

ft

F

1.71

5.61

B

2.09

6.86

G

2.25

7.38

C (AFT)

1.98

6.50

H

3.73

12.24

C (FWD)

1.80

5.91

J

12.17

39.93

D (AFT)

6.12

20.08

K

4.02

13.19

D (FWD)

5.94

19.49

L

5.51

18.08

E (CFM)

0.67

2.20

M

3.96

12.99

E (IAE)

0.77

2.53 N_AR_091011_1_0140101_01_00


09-10-11

Page 10 Jul 01/09


**ON A/C A319-100

X

Y

Z

A’ B’

C’ D’

E’ F’

G’


ft

X

2.54

8.33

Y

2.96

9.71

Z

3.05

10.00

A’

3.35

10.99

B’

3.35

10.99

C’

3.61

11.84

D’

3.61

11.84

E’

3.86

12.66

F’

3.86

12.66

G’

4.10

13.45

N_AR_091011_1_0150101_01_00


09-10-11

Page 11 Jul 01/09


**ON A/C A319-100

D

B C

A


ft

A

2.05

6.72

B

2.77

9.08

C

2.81

9.21

D

3.65

11.97

N_AR_091011_1_0160101_01_00


09-10-11

Page 12 Jul 01/09


**ON A/C A319-100

Q

R

S

T

U

V

W


ft

Q

4.60

15.09

R

4.48

14.69

S

4.35

14.27

T

4.21

13.81

U

4.07

13.35

V

4.01

13.15

W

3.75

12.30

N_AR_091011_1_0170101_01_00


09-10-11

Page 13 Jul 01/09


**ON A/C A319-100

L

M


ft

L

4.18

13.71

M

3.84

12.60

N_AR_091011_1_0180101_01_00


09-10-11

Page 14 Jul 01/09


**ON A/C A319-100

N

P


ft

N

4.56

14.96

P

4.36

14.3

N_AR_091011_1_0190101_01_00


09-10-11

Page 15 Jul 01/09


**ON A/C A319-100

H

K

J


ft

H

2.09

6.86

J

2.59

8.49

K

3.04

9.97

N_AR_091011_1_0200101_01_00


09-10-11

Page 16 Jul 01/09




09-10-11

Page 17 Jul 01/09


**ON A/C A320-100 A320-200

J

H

M

G

F N

E

C

B

A

D

NOTE: POINTS C AND D ARE HALFWAY BETWEEN NOSE AND MAIN GEARS.

L

K

A

m

ft

3.47

11.38

G

m

ft

2.25

7.38

B

2.09

6.86

H

3.73

12.24

C

1.86

6.10

J

12.14

39.93

D

6.00

19.68

K

4.04

13.25

E (CFM)

0.68

2.23

L

5.57

18.27

E (IAE)

0.78

2.56

M

2.51

8.23

F

1.72

5.64

N

3.96

12.99 N_AR_091011_1_0210101_01_00


09-10-11

Page 18 Jul 01/09


**ON A/C A320-100 A320-200

W

X

Y

Z A’

B’ C’

D’ E’

F’


ft

W

2.57

8.43

X

2.98

9.78

Y

3.07

10.07

Z

3.36

11.02

A’

3.36

11.02

B’

3.61

11.84

C’

3.61

11.84

D’

3.86

12.66

E’

3.86

12.66

F’

4.09

13.42

N_AR_091011_1_0220101_01_00


09-10-11

Page 19 Jul 01/09


**ON A/C A320-100 A320-200

D

B C

A


ft

A

2.05

6.72

B

2.77

9.08

C

2.81

9.21

D

3.64

11.94

N_AR_091011_1_0230101_01_00


09-10-11

Page 20 Jul 01/09


**ON A/C A320-100 A320-200

P

Q

R

S

T

U

V


ft

P

4.59

15.06

Q

4.47

14.67

R

4.35

14.27

S

4.21

13.81

T

4.07

13.35

U

4.01

13.16

V

3.75

12.30

N_AR_091011_1_0240101_01_00


09-10-11

Page 21 Jul 01/09


**ON A/C A320-100 A320-200

L

M


ft

L

4.17

13.68

M

3.83

12.57

N_AR_091011_1_0250101_01_00


09-10-11

Page 22 Jul 01/09


**ON A/C A320-100 A320-200

N

P


ft

N

4.55

14.93

P

4.35

14.27

N_AR_091011_1_0260101_01_00


09-10-11

Page 23 Jul 01/09


**ON A/C A320-100 A320-200

H

K

J


ft

H

2.18

7.15

J

2.66

8.73

K

3.10

10.17

N_AR_091011_1_0270101_01_00


09-10-11

Page 24 Jul 01/09




09-10-11

Page 25 Jul 01/09


**ON A/C A321-100 A321-200

J

H

F

M

G

N

E

P

C

B

A

D

NOTE: POINTS A, B, G, H, M, N AND P ARE MID DOOR AT FLOOR LEVEL. POINTS C AND D ARE EXTREMES OF STRAIGHT PORTION.

L

K

m

ft

m

ft

A

3.46

11.35

G

2.25

7.38

B

2.08

6.82

H

3.71

12.17

C (AFT)

1.99

6.53

J

12.10

39.70

C (FWD)

1.80

5.91

K

4.02

13.19

D (AFT)

6.13

20.11

L

5.54

18.18

D (FWD)

5.94

19.49

M

2.50

8.20

E (CFM)

0.68

2.23

N

3.62

11.88

E (IAE)

0.79

2.59

P

3.53

11.58

F

1.72

5.64 N_AR_091011_1_0280101_01_00


09-10-11

Page 26 Jul 01/09


**ON A/C A321-100 A321-200

W

X

Y Z A’

B’ C’

D’ E’

F’


ft

W

2.58

8.46

X

2.98

9.77

Y

3.07

10.07

Z

3.36

11.02

A’

3.61

11.02

B’

3.61

11.84

C’

3.85

11.84

D’

3.85

12.63

E’

3.86

12.63

F’

4.08

13.38

N_AR_091011_1_0290101_01_00


09-10-11

Page 27 Jul 01/09


**ON A/C A321-100 A321-200

A

G1

B

H1

C

D


ft

A

1.95

6.39

B

2.84

9.31

C

2.71

8.89

D

3.74

12.27

G1

2.49

8.16

H1

3.53

11.58

N_AR_091011_1_0300101_01_00


09-10-11

Page 28 Jul 01/09


**ON A/C A321-100 A321-200

P

R

Q

S

T

U

V


ft

P

4.59

15.05

Q

4.46

14.63

R

4.34

14.23

S

4.20

13.77

T

4.08

13.38

U

4.04

13.25

V

3.74

12.27

N_AR_091011_1_0310101_01_00


09-10-11

Page 29 Jul 01/09


**ON A/C A321-100 A321-200

L

M


ft

L

4.15

13.61

M

3.81

12.50

N_AR_091011_1_0320101_01_00


09-10-11

Page 30 Jul 01/09


**ON A/C A321-100 A321-200

N

P


ft

N

4.53

14.86

P

4.33

14.20

N_AR_091011_1_0330101_01_00


09-10-11

Page 31 Jul 01/09


**ON A/C A321-100 A321-200

H

K

J


ft

1.91

6.26

J

2.31

7.57

K

2.96

9.71

H

N_AR_091011_1_0340101_01_00


09-10-11

Page 32 Jul 01/09


09-10-12

AIRCRAFT GROUND SERVICE CONNECTIONS


This chapter gives data about the ground service connections of the aircraft. See FIGURE 09-10-12-991-001-AFIGURE 09-10-12-991-001-BFIGURE 09-10-12-991-001-CFIGURE 09-10-12-991-001-D for the ground service connections general layout. This chapter gives data about the systems that follow: - Hydraulic System, see DESC 09-10-12-002-A01, - Electrical System, see DESC 09-10-12-003-A01, - Fuel System, see DESC 09-10-12-004-A01, - Potable Water System, see DESC 09-10-12-005-A01, - Waste Water Disposal System, see DESC 09-10-12-006-A01.

09-10-12

Page 1 Jul 01/09


**ON A/C A318-100

7 6 10

9

2

1

3

4 14 11

4 3

8

13

1

5

7

6 2

10

12 9 3 4 11

14

1 − EXTERNAL POWER PANEL 2 − LOW PRESSURE CONDITIONED AIR CONNECTOR 3 − IDG OIL FILLING 4 − ENGINE OIL FILLING 5 − WASTE SERVICE PANEL 6 − POTABLE WATER SERVICE PANEL 7 − APU OIL FILLING 8 − YELLOW HYDRAULIC GROUND CONNECTOR

9 − GREEN HYDRAULIC GROUND CONNECTOR 10 − BLUE HYDRAULIC GROUND CONNECTOR 11 − PRESSURE REFUEL/DEFUEL COUPLING 12 − HIGH PRESSURE AIR GROUND CONNECTORS FOR ENGINE STARTING 13 − REFUEL/DEFUEL CONTROL PANEL 14 − OVERWING REFUEL COUPLING N_AR_091012_1_0010101_01_00

Ground Service Connections General Layout FIGURE-09-10-12-991-001-A01

09-10-12

Page 2 Jul 01/09


**ON A/C A319-100

7 6 2

1

10

9 4

3

14 11 4 3

8

13

1

5

7

6 2

12

10 9 3 4 11

14



Ground Service Connections General Layout FIGURE-09-10-12-991-001-B01

09-10-12

Page 3 Jul 01/09


**ON A/C A320-100 A320-200

7 6 2

1

10

9 4

3

14 11 4 3

8

13

1

5

7

6 2

10

12 9 3 4 11

14



Ground Service Connections General Layout FIGURE-09-10-12-991-001-C01

09-10-12

Page 4 Jul 01/09


**ON A/C A321-100 A321-200

7 6 2

1

9

10

4

3

14 11 4 3

8

13

1

5

7

6 2

10

12 9 3 4 11 14



Ground Service Connections General Layout FIGURE-09-10-12-991-001-D01

09-10-12

Page 5 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-10-12-002-A01 Hydraulic System **ON A/C A318-100 1.

Access This section gives data related to the location of the ground service connections. Access

Position from Aft of Nose

Position from Aircraft Centerline LH Side RH Side

Green Hydraulic 1.27 m (4.17 ft) Ground Connectors 16.70 m (54.79 ft) Access Door 197CB Yellow Hydraulic Ground connectors 16.70 m (54.79 ft) 1.27 m (4.17 ft) Access Door 198CB Hydraulic Reservoir 17.76 m (58.27 ft) 1.27 m (4.17 ft) Servicing Panel Access Door 197EB Ground Service Panels

Height from Ground 1.76 m (5.77 ft)

1.76 m (5.77 ft)

1.76 m (5.77 ft)

TABLE 1 NOTE : Distances are approximate. **ON A/C A319-100 2.




Green Hydraulic Ground Connectors 17.49 m (57.38 ft) Access Door 197CB Yellow Hydraulic Ground connectors 17.49 m (57.38 ft) 1.27 m (4.17 ft) Access Door 198CB

1.27 m (4.17 ft)


1.76 m (5.77 ft)

09-10-12

Page 6 Jul 01/09


Access



Hydraulic Reservoir 18.55 m (60.86 ft) 1.27 m (4.17 ft) Servicing Panel Access Door 197EB Ground Service Panels


TABLE 2 NOTE : Distances are approximate. **ON A/C A320-100 A320-200 3.




Green Hydraulic 1.27 m (4.17 ft) Ground Connectors 19.08 m (62.60 ft) Access Door 197CB Yellow Hydraulic Ground connectors 19.08 m (62.60 ft) 1.27 m (4.17 ft) Access Door 198CB Hydraulic Reservoir 20.15 m (66.11 ft) 1.27 m (4.17 ft) Servicing Panel Access Door 197EB Ground Service Panels


1.76 m (5.77 ft)

1.76 m (5.77 ft)


Access This section gives data related to the location of the ground service connections. Position from Aft of Nose


Green Hydraulic Ground Connectors 23.35 m (76.61 ft) Access Door 197CB

1.27 m (4.17 ft)

Access

09-10-12


Page 7 Jul 01/09


Access



Yellow Hydraulic Ground connectors 23.35 m (76.61 ft) 1.27 m (4.17 ft) Access Door 198CB Hydraulic Reservoir 24.23 m (79.49 ft) 1.27 m (4.17 ft) Servicing Panel Access Door 197EB Ground Service Panels


1.76 m (5.77 ft)

TABLE 4 NOTE : Distances are approximate. **ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 5.

Technical Specifications This section gives data related to the specifications of the ground service connections. A.

Ground Test Reservoir Pressurization On each ground service panel: - One connector AE80532N (suction). - One connector AE80531K (delivery).

B.

Reservoir Filling On the Green system ground service panel: One connection AE96993E for pressurized supply. - One handpump filling connection for unpressurized (suction) supply.

09-10-12

Page 8 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

197CB RESERVOIR FILL SYSTEM HAND PUMP FILL CONNECTION 1698GM

GROUND TEST PRESSURE CONNECTION 1008GM AE80531K

GROUND SUPPLY RESERVOIR FILL CONNECTION 1007GM AE96993GM

GROUND TEST SUCTION CONNECTION 1006GM AE80532N

A

N_AR_091012_1_0020101_01_00

Ground Service Connections Green System Ground Service Panel FIGURE-09-10-12-991-002-A01

09-10-12

Page 9 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A Z197

GROUND CONNECTION SUCTION 2006GM AE80532N

GROUND CONNECTION DELIVERY 2008GM AE80531K

A N_AR_091012_1_0030101_01_00

Ground Service Connections Blue System Ground Service Panel FIGURE-09-10-12-991-003-A01

09-10-12

Page 10 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A 198CB

GROUND TEST PRESSURE CONNECTION 3008GM AE80531K

GROUND TEST SUCTION CONNECTION 3006GM AE80532N

A N_AR_091012_1_0140101_01_00

Ground Service Connections Yellow System Ground Service Panel FIGURE-09-10-12-991-014-A01

09-10-12

Page 11 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-10-12-003-A01 Electrical System 1.



External Power 2.55 m (8.37 ft) Receptacle Access Door 121AL



on centerline Ground Service Panels TABLE 1

NOTE : Distances are approximate. 2.


External Power Receptacles: - One MS90362-3 - 90 KVA

B.

Power Supply: - Three Phases, 115 V, 400 Hz

C.

Electrical Connectors for Servicing: - AC Outlets: HUBBEL 5258 - DC Outlets: HUBBEL 7472 - Vacuum Cleaner Outlets: HUBBEL 5258

09-10-12

Page 12 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

121AL

108VU

A N_AR_091012_1_0040101_01_00

Ground Service Connections External Power Receptacles FIGURE-09-10-12-991-004-A01

09-10-12

Page 13 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-10-12-004-A01 Fuel System **ON A/C A318-100 1.

Access This section gives data related to the location of the ground service connections. Access Refuel/Defuel Integrated Panel Access Door 192MB Refuel/Defuel Coupling, Left Access Door 522HB (Optional) Refuel/Defuel Coupling, Right Access Door 622HB Gravity Refuel Coupling



12.00 m (39.37 ft)

1.80 m (5.91 ft)

14.80 m (48.56 ft)

10.00 m (32.81 ft)


3.50 m (11.48 ft)

14.80 m (48.56 ft)

10.00 m (32.81 ft) 3.50 m (11.48 ft)

16.70 m (54.79 ft)

12.40 m (40.68 ft) 12.40 m (40.68 ft) 3.70 m (12.14 ft) Ground Service Panels TABLE 1

NOTE : Distances are approximate. **ON A/C A319-100 2.

Access This section gives data related to the location of the ground service connections. Access Refuel/Defuel Integrated Panel Access Door 192MB Refuel/Defuel Coupling, Left Access Door 522HB (Optional)



12.80 m (41.99 ft) 15.60 m (51.18 ft)

1.80 m (5.91 ft)

10.00 m (32.81 ft)

09-10-12


3.50 m (11.48 ft)

Page 14 Jul 01/09


Access Refuel/Defuel Coupling, Right Access Door 622HB Gravity Refuel Coupling



Height from Ground

15.60 m (51.18 ft)

10.00 m (32.81 ft) 3.50 m (11.48 ft)

17.40 m (57.09 ft)


NOTE : Distances are approximate. **ON A/C A320-100 A320-200 3.

Access This section gives data related to the location of the ground service connections. Access Refuel/Defuel Integrated Panel Access Door 192MB Refuel/Defuel Coupling, Left Access Door 522HB (Optional) Refuel/Defuel Coupling, Right Access Door 622HB Gravity Refuel Coupling



14.40 m (47.24 ft) 17.20 m (56.43 ft)

1.80 m (5.91 ft)

10.00 m (32.81 ft)


3.50 m (11.48 ft)

17.20 m (56.43 ft)

10.00 m (32.81 ft) 3.50 m (11.48 ft)

19.10 m (62.66 ft)



Access This section gives data related to the location of the ground service connections.

09-10-12

Page 15 Jul 01/09


Access Refuel/Defuel Integrated Panel Access Door 192MB Refuel/Defuel Coupling, Left Access Door 522HB (Optional) Refuel/Defuel Coupling, Right Access Door 622HB Gravity Refuel Coupling



18.70 m (61.35 ft)

1.80 m (5.91 ft)

21.50 m (70.54 ft)

10.00 m (32.81 ft)


3.50 m (11.48 ft)

21.50 m (70.54 ft)

10.00 m (32.81 ft) 3.50 m (11.48 ft)

23.40 m (76.77 ft)


NOTE : Distances are approximate. **ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 5.


Refuel/Defuel Couplings: - Rigth wing: one standard ISO R45, 2.5 in. - Left wing: one optional standard ISO R45, 2.5 in.

B.

Refuel Pressure: - Max. pressure: 3.45 bar (50 psi).

C.

Refuel Flow: - 1400 l/minute (369.84 US gal/minute)

09-10-12

Page 16 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 A

REFUEL/DEFUEL CONTROL PANEL

FUEL QTY kg x 1000

LEFT

RIGHT

CTR

LVL

HI LEFT

RIGHT

CTR

VALVES

REFUEL OPEN

OPEN

OPEN

NORM

NORM

NORM

SHUT

SHUT

MODE SELECT

SHUT

TEST

BATT POWER

HI LVL

ON

REFUEL OFF

DEFUEL / XFR OPEN

LTS

ACTUAL

REFUEL

PRESELECTED

NORM

kg x 1000

DEC

CKPT

INC

END

A NOTE: STANDARD CONFIGURATION OF REFUEL/DEFUEL PANEL.

N_AR_091012_1_0080101_01_01

Ground Service Connections Refuel/Defuel Panel FIGURE-09-10-12-991-008-A01

09-10-12

Page 17 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 RIB14 RIB15

A

LEADING EDGE

WING FRONT SPAR

40QM

41QM

A N_AR_091012_1_0090101_01_00

Ground Service Connections Refuel/Defuel Couplings FIGURE-09-10-12-991-009-A01

09-10-12

Page 18 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

RIB19

A

RIB20

ADAPTER (REF ONLY)

GROUND CONNECTION (REF ONLY)

44QM (45QM)

F W D

A N_AR_091012_1_0150101_01_00

Ground Service Connections Gravity Refuel Couplings FIGURE-09-10-12-991-015-A01

09-10-12

Page 19 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-10-12-005-A01 Potable Water System **ON A/C A318-100 1.




Potable Water Ground Service 22.60 m (74.15 ft) 0.40 m (1.31 ft) Panel Access Door 171AL Drain Panel 8.80 m (28.87 ft) 0.10 m (0.33 ft) Access Door 133AL Drain Panel 10.20 m (33.46 ft) 0.50 m (1.64 ft) Access Door 192NB Ground Service Panels


1.70 m (5.58 ft) 1.80 m (5.91 ft)







1.70 m (5.58 ft) 1.80 m (5.91 ft)

TABLE 2

09-10-12

Page 20 Jul 01/09








1.70 m (5.58 ft) 1.80 m (5.91 ft)


Access This section gives data related to the location of the ground service connections. Access Potable Water Ground Service Panel Access Door 171AL Drain Panel Access Door 133AL Drain Panel Access Door 192NB



Height from Ground

38.20 m (125.33 ft)

0.40 m (1.31 ft)

2.60 m (8.53 ft)

9.40 m (30.84 ft)

0.10 m (0.33 ft)

1.70 m (5.58 ft)

12.50 m (41.01 ft)

0.50 m (1.64 ft)

1.80 m (5.91 ft)

Ground Service Panels TABLE 4 NOTE : Distances are approximate.

09-10-12

Page 21 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 5.


Connections (1) On the potable ground service panel (Access Door Access Door 171AL): - One standard 3/4 in. quick release filling connection. - One ground pressurization connection. (2) On drain panel (Access Door 133AL): - One standard 3/4 in. drain connection. (3) On drain panel (Access Door 192NB): - One standard 3/4 in. drain connection. with back- up mechanical control. - One standard 3/4 in. overflow and discharge connection with back up mechanical control.

B.

Capacity - 200 l (52.83 US gal).

C.

Filling Rate - Max Filling Pressure: 3.45 bar (50 psi). - Flow rate: 67 l/minute (17.70 US gal/minute)

09-10-12

Page 22 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

C B

Z171

A Z138

DRAIN CONNECTION

Z133

A

DISCHARGE AND OVERFLOW PORT

DRAIN CONNECTION

B

FILL AND DRAIN PORT

GROUND CONNECTION PRESSURIZATION

C N_AR_091012_1_0100101_01_00

Ground Service Connections Potable Water Ground Service Panel FIGURE-09-10-12-991-010-A01

09-10-12

Page 23 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-10-12-006-A01 Waste Water Disposal-System **ON A/C A318-100 1.




Waste Water Ground Service 22.90 m (75.13 ft) 0.80 m (2.62 ft) Panel Access Door 172AR Ground Service Panels






Waste Water Ground Service 24.90 m (81.69 ft) 0.80 m (2.62 ft) Panel Access Door 172AR Ground Service Panels


TABLE 2 **ON A/C A320-100 A320-200 3.


09-10-12

Page 24 Jul 01/09


Access



Waste Water Ground Service 28.60 m (93.83 ft) Panel Access Door 172AR Waste Water Ground Service Panel 3.40 m (11.15 ft) 1.20 m (3.94 ft) Access Door 125AL (Optional)

0.80 m (2.62 ft)


2.40 m (7.87 ft)

Ground Service Panels TABLE 3 **ON A/C A321-100 A321-200 4.



Waste Water 35.50 m (116.47 Ground Service ft) Panel Access Door 172AR Waste Water Ground Service Panel 3.40 m (11.15 ft) Access Door 125AL (Optional)

Position from Aircraft Centerline LH Side RH Side 0.80 m (2.62 ft)

1.20 m (3.94 ft)


2.40 m (7.87 ft)

Ground Service Panels TABLE 4 **ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 5.


Connections - One standard 1 in. flushing connection. - One standard 4 in. drain connection.

09-10-12

Page 25 Jul 01/09


B.

Single Toilet Capacity - Waste: 200 l (52.83 US gal) - Chemical fluid: 10 l (2.64 US gal).

C.

Flushing Pressure - Maximum flushing pressure : 2.41 bar (35 psi)

D.

Flow Rate - Maximum flow rate : 38 l/min (10.04 US gal/min)

09-10-12

Page 26 Jul 01/09


**ON A/C A318-100 A319-100

A

Z172

FR66

FR65

FILL AND RINSE CONNECTION

TOILET DRAIN CONNECTION

A

N_AR_091012_1_0130101_01_00

Ground Service Connections Waste Water Ground Service Panel FIGURE-09-10-12-991-013-A01

09-10-12

Page 27 Jul 01/09


**ON A/C A320-100 A320-200 A321-100 A321-200 FR11

FR12

Z172


Z125

B

A TOILET DRAIN CONNECTION

A FR66


FR65

FORWARD TOILET SERVICE PANEL (OPTIONAL)

TOILET DRAIN CONNECTION

B AFT TOILET SERVICE PANEL N_AR_091012_1_0130201_01_00

Ground Service Connections Waste Water Ground Service Panel FIGURE-09-10-12-991-013-B01

09-10-12

Page 28 Jul 01/09


09-10-13

AIRCRAFT GROUNDING POINTS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-10-13-001-A01 General **ON A/C A318-100 1.

Access This section gives data related to the location of the ground service connections. Access NLG LH MLG RH MLG

Position from Aircraft Centerline Position from Aft of Nose LH Side RH Side 5.07 m (16.63 ft) On Centerline 15.32 m (50.26 ft) 3.79 m (12.43 ft) 15.32 m (50.26 ft) 3.79 m (12.43 ft)

Height from Ground 0.94 m (3.08 ft) 1.07 m (3.51 ft) 1.07 m (3.51 ft)

Grounding Points Locations TABLE 1 NOTE : Distances are approximate. **ON A/C A319-100 2.




Grounding Points Locations TABLE 2 NOTE : Distances are approximate. **ON A/C A320-100 A320-200 3.


09-10-13

Page 1 Jul 01/09


Access NLG LH MLG RH MLG



Grounding Points Locations TABLE 3 NOTE : Distances are approximate. **ON A/C A321-100 A321-200 4.




Grounding Points Locations TABLE 4 NOTE : Distances are approximate. **ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 5.

Technical Specifications The grounding stud on each landing gear is designed for use with a clip-on connector, such as the Appleton TGR. The grounding stud are used to connect the aircraft to approved ground connection on the ramp, in the hangar or through a ground earth spike for: - Refuel/Defuel operations, - Maintenance operations, - Bad Weather conditions. There is an additional grounding point located over the wing near the gravity refuel coupling, see DESC 09-10-12-004-A01.

09-10-13

Page 2 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A A

NOSE LANDING GEAR

MAIN LANDING GEAR

LANDING GEAR GROUND CABLE

A N_AR_091013_1_0010101_01_00

Grounding Point Location FIGURE-09-10-13-991-001-A01

09-10-13

Page 3 Jul 01/09


09-10-14

CARGO COMPARTMENTS


The lower deck of the aircraft has three cargo compartments: - Forward cargo compartment, - Aft cargo compartment, - Bulk cargo compartment. The total volume of the three cargo compartments is 21.30 m3 (752.20 ft3). NOTE : See your customized WBM for accurate data related to the aircraft configuration. A.

FWD Cargo Compartment The fwd cargo compartment (n˚ 1) is designed for bulk cargo and baggage. The volume of the FWD cargo compartment is 6.72 m3 (237.31 ft3). See FIGURE 09-10-14-991-007-A for location and dimensions of the FWD compartment.

B.

Aft Cargo Compartment The aft cargo compartment (n˚ 4) is designed for bulk cargo and baggage. The volume of the aft cargo compartment is 8.87 m3 (313.24 ft3). See FIGURE 09-10-14-991-008-A for location and dimensions of the aft compartment.

C.

Bulk Cargo Compartment The bulk cargo compartment (n˚ 5) is designed for bulk cargo. The volume of the bulk cargo compartment is 5.71 m3 (201.65 ft3). See FIGURE 09-10-14-991-009-A for location and dimensions of the bulk compartment.

09-10-14

Page 1 Jul 01/09


**ON A/C A318-100

FR24A

FR34

FR34

A

FR28

2.6 (8. 30 m 62 ft)

1.243 m (4.07 ft)

FR24A

m 37 ) 2.6 65 ft (8. 1.4 (4. 29 m 68 ft)

FR34

FR28

FR24A

A N_AR_091014_1_0070101_01_00

Forward Cargo Compartment Location and Dimensions FIGURE-09-10-14-991-007-A01

09-10-14

Page 2 Jul 01/09


**ON A/C A318-100

FR47/54

FR60

A FR60 FR57A FR47/54

1.4 2 (4. 9 m 68 f 2. t) (8. 630 62 m ft)

(4.07 ft)

1.243 m

m 53 t) 3.3 .00 f (11

FR60 FR57A FR57

FR47/54

A N_AR_091014_1_0080101_01_00

Aft Cargo Compartment Location and Dimensions FIGURE-09-10-14-991-008-A01

09-10-14

Page 3 Jul 01/09


**ON A/C A318-100

FR60

FR65

A FR65 FR63 1.5 (5. 58 m 11 ft)

FR60

m 08 ) 2.7 .88 ft (8 FR65 FR63 FR62 FR60

A N_AR_091014_1_0090101_01_00

Bulk Cargo Compartment Location and Dimensions FIGURE-09-10-14-991-009-A01

09-10-14

Page 4 Jul 01/09



The lower deck of the aircraft has two cargo compartments: - Forward cargo compartment, - Aft cargo compartment, The total volume of the two cargo compartments is 27.56 m3 (973.27 ft3). NOTE : See your customized WBM for accurate data related to the aircraft configuration. A.

FWD Cargo Compartment The FWD cargo compartment (n˚ 1) is designed for bulk cargo and baggage or transport of ULDs. The volume of the FWD cargo compartment is 8.51 m3 (300.53 ft3). See FIGURE 09-10-14-991-010-A for location and dimensions of the FWD compartment.

B.

Aft Cargo Compartment The aft cargo compartment (n˚ 4 and 5) is designed for bulk cargo and baggage or transport of ULDs. The volume of the AFT cargo compartment is 19.05 m3 (672.74 ft3). See FIGURE 09-10-14-991-011-A for location and dimensions of the aft compartment.

09-10-14

Page 5 Jul 01/09


**ON A/C A319-100

FR24A

FR34

A

FR34 FR28

2.6 (8. 30 m 62 ft)

1.243 m (4.07 ft)

FR24A

m 45 ft) 3.3 .97 (10 1.4 (4. 30 m 69 ft)

A

N_AR_091014_1_0100101_01_00


09-10-14

Page 6 Jul 01/09


**ON A/C A319-100

FR47/51

FR59

FR65

A

FR65 FR63 1.5 (5. 58 m 11 ft)

FR59 FR55A FR47/51

m 41 t) 3.2 .63 f (10

m 62 t) 7.6 .13 f (25

(4.07 ft)

1.4 3 (4. 0 m 69 ft) 2.6 (8. 30 m 62 ft)

1.243 m

m 21 t) 4.4 .50 f (14

A N_AR_091014_1_0110101_01_00


09-10-14

Page 7 Jul 01/09




FWD Cargo Compartment The FWD cargo compartment (n˚ 1) is designed for bulk cargo and baggage or transport of ULDs. The volume of the FWD cargo compartment is 13.28 m3 (468.98 ft3). See FIGURE 09-10-14-991-013-A for location and dimensions of the FWD compartment.

B.

Aft Cargo Compartment The aft cargo compartment (n˚ 3 and 4) is designed for bulk cargo and baggage or transport of ULDs. The volume of the aft cargo compartment is 18.26 m3 (644.85 ft3). See FIGURE 09-10-14-991-014-A for location and dimensions of the aft compartment.

C.

Bulk Cargo Compartment The bulk cargo compartment (n˚ 5) is designed for bulk cargo and baggage. The volume of the bulk cargo compartment is 5.91 m3 (208.71 ft3). See FIGURE 09-10-14-991-015-A for location and dimensions of the bulk compartment.

09-10-14

Page 8 Jul 01/09


**ON A/C A320-100 A320-200

FR34

FR24A

A FR34

2.6 (8. 30 62 m ft)

FR31 FR28 FR24A

1.243 m (4.07 ft)

m 50 t) 4.8 .91 f (15

1.4 (4. 30 69 m ft)

FR34 FR31 FR28

FR24A

A N_AR_091014_1_0130101_01_00


09-10-14

Page 9 Jul 01/09


**ON A/C A320-100 A320-200

FR47

FR59

A

FR59 FR56 FR53 FR52A

1.4 (4. 08 61 m ft)

FR47

m 00 ft) 3.2 6.00 (12

2.6 (8. 30 62 m ft)

m 54 t) 3.3 .00 f (11

m 54 t) 6.5 .50 f (21 FR59

1.4 (4. 30 69 m ft)

FR56 1.242 m (4.07 ft)

FR53 FR52A FR50

FR47

A N_AR_091014_1_0140101_01_00


09-10-14

Page 10 Jul 01/09


**ON A/C A320-100 A320-200

FR59

FR65

A FR65

1.5 (5. 58 11 m ft)

FR63

0.9 (3. 68 m 17 ft)

m 41 ft) 3.2 .63 (10

(2.69 ft)

0.820 m

1.211 m (3.97 ft)

FR59

FR65

1.4 (4. 08 62 m ft) 2. (8. 630 62 m ft)

FR63

FR59

A N_AR_091014_1_0150101_01_00


09-10-14

Page 11 Jul 01/09




FWD Cargo Compartment The FWD cargo compartment (n˚ 1 and 2) is designed for bulk cargo and baggage or transport of ULDs. The volume of the FWD cargo compartment is 22.81 m3 (805.53 ft3). See FIGURE 09-10-14-991-016-A for location and dimensions of the FWD compartment.

B.

Aft Cargo Compartment The aft cargo compartment (n˚ 3 and 4) is designed for bulk cargo and baggage or transport of ULDs. The volume of the AFT cargo compartment is 22.255 m3 (785.93 ft3). See FIGURE 09-10-14-991-017-A for location and dimensions of the aft compartment.

C.

Bulk Cargo Compartment The bulk cargo compartment (n˚ 5) is designed for bulk cargo and baggage. The volume of the bulk cargo compartment is 5.88 m3 (207.65 ft3). See FIGURE 09-10-14-991-018-A for location and dimensions of the bulk compartment.

09-10-14

Page 12 Jul 01/09


**ON A/C A321-100 A321-200

FR24A

FR35.5

FR35.5

A FR35.2

2.6 (8. 30 m 62 ft)

FR34 FR31 FR28

m 75 ft) 4.6 .33 (15

1.242 m (4.07 ft)

FR24A

m 49 t) 8.1 .73 f (26

m 74 ft) 3.4 .39 (11

FR35.5

FR35.2 FR34

1.4 3 (4. 0 m 69 ft)

FR31 FR28

FR24A

A N_AR_091014_1_0160101_01_00


09-10-14

Page 13 Jul 01/09


**ON A/C A321-100 A321-200

FR47.2

A

FR59

FR59

2.6 (8. 30 m 62 ft)

FR56 FR52A

FR47.2

1.242 m (4.07 ft)

m 54 t) 8.1 .75 f (26

FR59

FR56 FR53 FR52A

1.4 3 (4. 0 m 69 ft)

FR50 FR47.5

FR47.2

A N_AR_091014_1_0170101_01_00


09-10-14

Page 14 Jul 01/09


**ON A/C A321-100 A321-200

FR59

FR65

FR65

A

1.5 (5. 58 m 11 ft 0.9 ) (3. 68 m 17 ft)

FR62 FR60

0.821 m (2.69 ft)

FR59

m 41 t) 3.2 .63 f (10

FR65 FR64 1.211 m (3.97 ft)

1.4 (4. 08 m 61 ft) 2.6 3 (8. 0 m 62 ft)

FR63 FR62

FR60 FR59

A N_AR_091014_1_0180101_01_00


09-10-14

Page 15 Jul 01/09


09-10-15

LOCATION OF HAZARDOUS MATERIALS


A number of items and areas on the aircraft contain Hazardous Materials. WARNING : IDENTIFY WHICH HAZARDOUS MATERIALS WERE TRANSPORTED IN THE CARGO COMPARTMENTS. NOTE : The List of Radioactive and hazardous Element manual (LRE) gives information on these materials. The FIGURE 09-10-15-991-001-AFIGURE 09-10-15-991-001-BFIGURE 09-10-15-991-001-CFIGURE 09-10-15-991-001-D gives the general location of the Hazardous Materials that you can find on the aircraft. NOTE : The number and arrangement of the portable equipment depend on the aircraft configuration.

09-10-15

Page 1 Jul 01/09

COCKPIT OXYGEN CYLINDERS

BATTERY 1

09-10-15 BATTERY 2

AVIONICS COMPARTMENT ACCESS DOOR

ENGINE FIRE EXTINGUISHER BOTTLES

INNER FUEL TANK

VENT SURGE TANK

CENTER FUEL TANK

(IF INSTALLED)

OUTER FUEL TANK

APU FUEL LINE

APU FIRE EXTINGUISHER LINES

APU OIL TANK

APU FIRE DETECTORS

NITROGEN BOTTLE

IDG OIL TANKS

FUEL LP VALVES CARGO FIRE EXTINGUISHER BOTTLE

N_AR_091015_1_0010101_01_00

PASSENGER AND CREW OXYGEN BOTTLE PORTABLE FIRE EXTINGUISHER BOTTLE

HYDRAULIC RESERVOIR

VENT SURGE TANK

OUTER FUEL TANK

SHADED AREAS IDENTIFY PERMITTED BREAK−IN AREAS ON EACH SIDE OF THE AIRCRAFT INNER FUEL TANK

APU FIRE EXTINGUISHER BOTTLE


**ON A/C A318-100

Hazardous Materials Location - A318 FIGURE-09-10-15-991-001-A01

Page 2 Jul 01/09

09-10-15 BATTERY 2



BATTERY 1

ACT 4 (IF INSTALLED)

INNER FUEL TANK

OUTER FUEL TANK

VENT SURGE TANK


(IF INSTALLED)

CENTER FUEL TANK



(IF INSTALLED)

HYDRAULIC RESERVOIR

NITROGEN BOTTLE

IDG OIL TANKS


N_AR_091015_1_0010201_01_00

ACT: ADDITIONAL CENTER TANK


VENT SURGE TANK

OUTER FUEL TANK


APU FUEL LINE


APU OIL TANK

APU FIRE DETECTORS






**ON A/C A319-100

Hazardous Materials Location - A319 FIGURE-09-10-15-991-001-B01

Page 3 Jul 01/09

09-10-15 BATTERY 2



BATTERY 1

INNER FUEL TANK

OUTER FUEL TANK

VENT SURGE TANK

CENTER FUEL TANK (IF INSTALLED)




NITROGEN BOTTLE HYDRAULIC RESERVOIR

N_AR_091015_1_0010301_01_00



VENT SURGE TANK

OUTER FUEL TANK


IDG OIL TANKS

APU FUEL LINE


APU OIL TANK

APU FIRE DETECTORS


(IF INSTALLED)



**ON A/C A320-100 A320-200

Hazardous Materials Location - A320 FIGURE-09-10-15-991-001-C01

Page 4 Jul 01/09

09-10-15 BATTERY 2



BATTERY 1

WING FUEL TANK

VENT SURGE TANK

CENTER FUEL TANK


WING FUEL TANK


HYDRAULIC RESERVOIR

NITROGEN BOTTLE

IDG OIL TANKS


APU OIL TANK

APU FIRE DETECTORS

N_AR_091015_1_0010401_01_00



VENT SURGE TANK

SHADED AREAS IDENTIFY PERMITTED BREAK−IN AREAS ON EACH SIDE OF THE AIRCRAFT



APU FUEL LINE



**ON A/C A321-100 A321-200

Hazardous Materials Location - A321 FIGURE-09-10-15-991-001-D01

Page 5 Jul 01/09


09-10-16

LANDING GEARS


This chapter gives details on the landing gears. - For Landing Gear footprint, see FIGURE 09-10-16-991-001-AFIGURE 09-10-16-991-001BFIGURE 09-10-16-991-001-CFIGURE 09-10-16-991-001-D, - For Nose Landing Gear description, see FIGURE 09-10-16-991-002-A, - For Main Landing Gear description, see FIGURE 09-10-16-991-003-A, - For Landing Gear Doors description, see FIGURE 09-10-16-991-004-A.

09-10-16

Page 1 Jul 01/09


**ON A/C A318-100

CL

0.50 m (19.7 in)

10.252 m (33.64 ft)

0.927 m (36.5 in)

7.59 m (24.90 ft) N_AR_091016_1_0010101_01_00

Footprint Landing Gear FIGURE-09-10-16-991-001-A01

09-10-16

Page 2 Jul 01/09


**ON A/C A319-100

CL

0.50 m (19.7 in)

11.039 m (36.22 ft)

0.927 m (36.5 in)

7.59 m (24.90 ft) N_AR_091016_1_0010201_01_00

Footprint Landing Gear FIGURE-09-10-16-991-001-B01

09-10-16

Page 3 Jul 01/09


**ON A/C A320-100 A320-200 0.50 m (19.7 in)

CL

12.64 m (41.47 ft)

0.927 m (36.5 in)

7.59 m (24.90 ft) N_AR_091016_1_0010301_01_00

Footprint Landing Gear - Twin Wheel MLG (Sheet 1 of 2) FIGURE-09-10-16-991-001-C01

09-10-16

Page 4 Jul 01/09


**ON A/C A320-100 A320-200 0.50 m (19.7 in)

CL

12.64 m (41.47 ft)

0.78 m (30.7 in)

1.005 m (39.5 ft)

7.59 m (24.90 ft) N_AR_091016_1_0010302_01_00

Footprint Landing Gear - Four Wheel Bogie MLG (Optional, A320 only) (Sheet 2 of 2) FIGURE-09-10-16-991-001-C01

09-10-16

Page 5 Jul 01/09


**ON A/C A321-100 A321-200 0.50 m (19.7 in)

CL

16.91 m (55.47 ft)

0.927 m (36.5 in)

7.59 m (24.90 ft) N_AR_091016_1_0010401_01_00

Footprint Landing Gear FIGURE-09-10-16-991-001-D01

09-10-16

Page 6 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

ACTUATING CYLINDER

NOSE WHEEL STEERING SERVO CONTROL

DOWNLOCK PROXIMITY DETECTORS

STEERING ACTUATING CYLINDER SHOCK ABSORBER

TORQUE LINK

TOWING FITTING

N_AR_091016_1_0020101_01_00

Description Nose Landing Gear FIGURE-09-10-16-991-002-A01

09-10-16

Page 7 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

LOCK STAY

ACTUATING CYLINDER

UNLOCK ACTUATOR MAIN FITTING

SIDE STAY

SHOCK ABSORBER

TORQUE LINK

N_AR_091016_1_0030101_01_00

Description Twin Wheel MLG (Sheet 1 of 2) FIGURE-09-10-16-991-003-A01

09-10-16

Page 8 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

LOCK STAY

ACTUATING CYLINDER

DOWNLOCK ACTUATOR

LEG UNIT STRUT ASSEMBLY

SHOCK ABSORBER

PITCH TRIMMER

TORQUE LINK

BRAKE BAR

N_AR_091016_1_0030102_01_00

Description Four Wheel Bogie MLG (Optional A320 only) (Sheet 2 of 2) FIGURE-09-10-16-991-003-A01

09-10-16

Page 9 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

FR9


BELL CRANK

DOOR UPLOCK ASSENBLY DRAG STRUT ASSY GEAR UPLOCK ASSEMBLY

FR20

CONTROL ROD

FITTING ROTATING ROD ASSY

FWD DOORS

AFT DOORS

LEG DOOR

N_AR_091016_1_0040101_01_00

Doors Nose Landing Gear (Sheet 1 of 3) FIGURE-09-10-16-991-004-A01

09-10-16

Page 10 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

HINGED FAIRING (MECHANICALLY OPERATED)

HINGED FAIRING


FIXED FAIRING

PROXIMITY SENSORS

STEPS

ADJUSTABLE RAMP UPLOCK ROLLER FIXED RAMPS

MAIN DOOR (HYDRAULICALLY OPERATED)

NOTE: MAIN DOOR SHOWN OPEN IN GROUND MAINTENANCE POSITION.

N_AR_091016_1_0040102_01_00

Doors Twin Wheel MLG (Sheet 2 of 3) FIGURE-09-10-16-991-004-A01

09-10-16

Page 11 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

HINGED FAIRING

FIXED FAIRING


STEPS

AJUSTABLE RAMP UPLOCK ROLLER

MAIN DOOR DOOR RAMPS

NOTE: MAIN DOOR SHOWN OPEN IN GROUND MAINTENANCE POSITION.

N_AR_091016_1_0040103_01_00

Doors Four Wheel Bogie MLG (Optional A320 only) (Sheet 3 of 3) FIGURE-09-10-16-991-004-A01

09-10-16

Page 12 Jul 01/09


09-20-01

QUICK REFERENCE DATA


This chapter is broken down as follows: A.

Aircraft Recovery Logic Charts DESC 09-20-01-002-A01.

B.

Aircraft Recovery Process Document DESC 09-20-01-004-A01.

C.

IATA Aircraft Recovery Quick Reference Check List TASK 09-20-01-869-801-A01.

09-20-01

Page 1 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-20-01-002-A01 Aircraft Recovery Logic Chart NOTE : The charts are not in chronological sequence for recovery. Make a selection of the charts applicable to each recovery scenario. 1.

See DESC 02-10-01-002-A01 for description of aircraft recovery charts and the way to use them. When you use these charts, the conditions that follow are assumed: - Warnings and cautions are not included on the recovery charts. - The aircraft operator has full responsibility for all the aircraft recovery operation. - The recovery operation can only start when the local and state Investigative Authorities release the aircraft. - All company, local and state health and safety regulations are obeyed. - All hazardous materials are identified and correctly handled. - The standard ”Aircraft Status for Maintenance” is in general not available (see AMM 00 Introduction, Item 7). - The aircraft is possibly in an unusual attitude and can be unstable. - Some of the steps listed are possibly not in chronological sequence because each recovery operation is different and the recovery procedure must be adapted. - It is possible that some of the steps listed are completed more than one time.

09-20-01

Page 2 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 CHART I

INCIDENT

SEE 01−00−00

THE AIRCRAFT OPERATOR HAS FULL RESPONSIBILITY FOR THE RECOVERY

PERSONNEL FROM THE AIRLINE, INVESTIGATIVE AUTHORITIES AND AIRPORT TO BE ADVISED

ADVISE INTERNALLY ACCORDING TO AIRLINE PROCESSES

BASIC INCIDENT INFORMATION: −GET AND RECORD INITIAL DATA −FUEL ON BOARD −ANY HAZARDOUS MATERIALS −AIRCRAFT STATUS −CURRENT AND FORECAST WEATHER

RECOVERY MANAGER ASSUMES RESPONSIBILITY

RECOVERY TEAM SELECTED SEE 09−20−02

PREPARE PERSONAL EQUIPMENT COMMUNICATE WITH AIRPORT AND INVESTIGATIVE AUTHORITIES, RECORD NAMES, POSITIONS AND CONTACT NUMBERS

REMOVE FDR AND CVR PER INVESTIGATIVE AUTHORITIES

PREPARE LOCAL AIRCRAFT RECOVERY EQUIPMENT

LIAISE WITH RECOVERY MANAGER

AIRCRAFT RELEASED BY INVESTIGATIVE AUTHORITY

GO TO CHART IIA ( SEE FIGURE 09−20−01−991−002)

NOTE: THE CHARTS ARE NOT IN A CHRONOLOGICAL SEQUENCE FOR A RECOVERY. N_AR_092001_1_0010101_01_00

Aircraft Recovery Logic Chart Chart I FIGURE-09-20-01-991-001-A01

09-20-01

Page 3 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 CHART IIA

INITIAL SURVEY OF AIRCRAFT

SEE 02−40−01 FOR HEALTH & SAFETY DETAILS

STEP A

DO A CHECK FOR OBVIOUS STRUCTURAL DAMAGE

GO TO CHART IX ( SEE FIGURE 09−20−01−991−009 )

STEP B

IDENTIFY SIGNS OF DISTORTION, BUCKLING, CRACKING ETC.

SEE SRM 51−11−00 AND GO TO STEP C

YES STEP C

ARE THERE VISIBLE FLUID LEAKS?

NO

YES STEP D

DOES THE AIRCRAFT HAVE TO BE STABILIZED?

NO

GO TO CHART IV STEP A ( SEE FIGURE 09−20−01−991−004 ) GO TO STEP D

GO TO CHART VI ( SEE FIGURE 09−20−01−991−006 ) GO TO STEP E

STEP E

LANDING GEAR STATUS

GO TO CHART XIII ( SEE FIGURE 09−20−01−991−013 )

STEP F

IDENTIFY MISSING COMPONENTS SUCH AS LANDING GEAR, FLAPS, ETC.

GO TO CHART IIB STEP G


Aircraft Recovery Logic Chart Chart IIA (Sheet 1 of 2) FIGURE-09-20-01-991-002-A01

09-20-01

Page 4 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 CHART IIB

INITIAL SURVEY OF AIRCRAFT CONT’D

STEP G

GO TO CHART XI ( SEE FIGURE 09−20−01−991−011) AND COMPLETE WORKSHEETS ( SEE 03−00−00 AND SEE 09−50−01)

WEIGHT AND CG POSITION MANAGEMENT

YES STEP H

ARE THERE ANY STRUCTURAL CONCERNS?

NO

YES STEP I

ARE THERE ANY ENVIRONMENTAL CONCERNS?

NO

YES STEP J

ARE HAZARDOUS MATERIALS IDENTIFIED AND ARE THEY OF CONCERN? SEE 09−10−05 AND SEE 09−10−15 FOR LOCALIZATION

NO

YES STEP K

WILL THIS BE A LENGTHY RECOVERY? NO

SEE SRM 51−11−00 IF APPLICABLE AND GO TO STEP I

GO TO STEP I

ADVISE HAZMAT TEAM AND GO TO STEP J

GO TO STEP J

ADVISE HAZMAT RESPONSE TEAM AND GO TO STEP K

GO TO STEP E

INSTALL PROTECTIVE COVERS: ENGINES, PITOT HEADS, ETC. AND GO TO CHART III ( SEE FIGURE 09−20−01−991−003 )

GO TO STEP D


Aircraft Recovery Logic Chart Chart IIB (Sheet 2 of 2) FIGURE-09-20-01-991-002-A01

09-20-01

Page 5 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 CHART III

IS AIRCRAFT ECONOMICALLY RECOVERABLE? NOTE: MAKE THE DECISION WITH INPUT FROM THE OPERATOR, INSURANCE SURVEYER AND AIRCRAFT MANUFACTURER

PROCEED AS "YES" UNTIL FURTHER NOTIFICATION

NO

YES

PREPARE FOR RECOVERY AFTER RELEASE BY INVESTIGATIVE AUTHORITIES

WILL SECONDARY DAMAGE BE ACCEPTABLE? SEE 02−00−00

WHO WILL RECOVER AIRCRAFT?

AIRLINE

CONTRACTOR

GO TO CHART VII ( SEE FIGURE 09−20−01−991−007)

AIRPORT

SIGN CONTRACT, MAKE SURE THAT ARM PROCEDURES ARE FOLLOWED, RELEASE FORMS AND WAIVERS

ASSIGN AIRLINE REPRESENTATIVE TO OVERSEE RECOVERY AND OBTAIN REPORT

END


Aircraft Recovery Logic Chart Chart III FIGURE-09-20-01-991-003-A01

09-20-01

Page 6 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 CHART IV

IDENTIFY FLUID LEAKS MAKE SURE AIRCRAFT IS CORRECTLY GROUNDED

"B" HYDRAULIC OR ENGINE OIL

"A" FUEL

ISOLATE ELECTRICAL POWER (SEE CHART IX FOR DETAILS

IDENTIFY SOURCE

"C" LAVATORY

"D" CARGO

"E" WATER

ATTEMPT SPILL CONTAINMENT

ADVISE HAZMAT TEAM TO IDENTIFY, CONTAIN AND REMOVE

DRAIN SYSTEM

SEE FIGURE 09−20−01−991−009 )

IDENTIFY SOURCE



CAN LINES BE CAPPED, VALVES BE CLOSED, ETC?

CAN LINES BE CAPPED, VALVES BE CLOSED, HOLES PLUGGED, ETC.?

YES

NO

DEFUEL OF AIRCRAFT BECOMES PRIORITY

MAKE SURE HAZMAT TEAM AWARE OF ANY GROUND SPILLAGE

DRAIN SYSTEM IF ACCESS AVAILABLE

NO

GO TO "D"

GO TO "E"

YES

GO TO "B"

GO TO CHART IIA STEP D ( SEE FIGURE 09−20−01−991−002)

DRAIN SYSTEM

GO TO CHART X ( SEE FIGURE 09−20−01−991−010)

GO TO "C"


Aircraft Recovery Logic Chart Chart IV FIGURE-09-20-01-991-004-A01

09-20-01

Page 7 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 CHART V

REMOVAL OF CARGO

NO

REMOVAL CATERING

CAN CARGO DOOR BE ACCESSED?

SEE 05−50−00

YES

EXCAVATE/PREPA RE ROADWAY TO ALLOW ACCESS TO DOOR

CONTROL CG DURING OFF−LOAD

NO

CAN ELECTRICAL POWER TO THE AIRCRAFT BE ESTABLISHED?

YES

OPERATE DOORS NORMALLY

NO

CAN CARGO DOOR BE OPENED MANUALLY

YES

MANUALLY OPERATE DOORS NO

SEE 05−50−00 CAN DOOR BE UNLOCKED YES AND HOISTED WITH A CRANE?

NO

HOIST DOOR TO OPEN

UNLOAD AS MUCH AS POSSIBLE MANUALLY (MAY BE NECESSARY TO CUT CONTAINERS FOR ACCESS)

CAN CARGO LOADING SYSTEM (CLS) BE USED?

SEE 05−50−00

YES

UNLOAD CARGO COMPARTMENTS

CONTROL CG DURING OFF−LOAD

CONTACT AIRBUS FOR FURTHER INSTRUCTIONS GO TO CHART VI STEP G ( SEE FIGURE 09−20−01−991−006 ) NOTE: THE CHARTS ARE NOT IN A CHRONOLOGICAL SEQUENCE FOR A RECOVERY. N_AR_092001_1_0050101_01_00

Aircraft Recovery Logic Chart Chart V FIGURE-09-20-01-991-005-A01

09-20-01

Page 8 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 CHART VI STABILIZE AIRCRAFT

SEE 04−20−00

STEP A

MAKE SURE AIRCRAFT IS CORRECTLY GROUNDED

GO TO STEP B

STEP B

CALCULATE ANTICIPATED LOADS AND CONFIRM CG LOCATION

GO TO STEP C

SEE 03−00−00

STEP C

IS THIS STRAIGHT DEBOGGING?

STEP D

IS TETHERING/SHORING REQUIRED?

YES

NO

YES

NO

GO TO CHART XII ( SEE FIGURE 09−20−01−991−012 ) GO TO STEP D GO TO CHART XIV ( SEE FIGURE 09−20−01−991−014 ) GO TO STEP E

SEE 04−30−00 YES STEP E

STEP F MAKE SURE CG IS CONTROLLED STEP G

IS IT NECESSARY TO DEFUEL OR TRANSFER FUEL?

NO

REMOVE CARGO AND CATERING EQUIPMENT

GO TO CHART X ( SEE FIGURE 09−20−01−991−016 ) GO TO STEP F GO TO CHART V ( SEE FIGURE 09−20−01−991−005 )

REMOVE MAJOR COMPONENTS THAT ARE DAMAGED OR NECESSARY FOR WEIGHT REDUCTION OR CG CONTROL

GO TO CHART IIA STEP E ( SEE FIGURE 09−20−01−991−002 )

SEE 03−50−01 NOTE: THE CHARTS ARE NOT IN A CHRONOLOGICAL SEQUENCE FOR A RECOVERY. N_AR_092001_1_0060101_01_01

Aircraft Recovery Logic Chart Chart VI FIGURE-09-20-01-991-006-A01

09-20-01

Page 9 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 CHART VII

PREPARE TO LEVEL/LIFT AIRCRAFT

SELECT METHOD

PNEUMATIC LIFTING BAGS

JACKS

SEE 06−00−00

CRANE

STEP−BY−STEP COMBINATION

SEE 06−60−00

CALCULATE EXPECTED LOADS AND RECORD

CONFIRM STRUCTURAL INTEGRITY OF LIFTING POINTS/AREAS *

SELECT RECOVERY TOOLING *

CONTROL CG AND MONITOR LOAD RECORDS

SEE 06−10−00

CONFIRM SOIL STABILITY SEE 04−50−00 *

SEE 03−00−00

GO TO CHART VIII ( SEE FIGURE 09−20−01−991−008)

* : BEFORE CONSIDERING WHICH LEVELING /LIFTING OPTION TO USE YOU MUST MAKE AN ACCURATE WEIGHT AND CG ANALYSIS − THIS WILL GIVE YOU THE OPTIMUM POSTIONS AND LOADS FOR THE LIFTING EQUIPMENT. NOTE: THE CHARTS ARE NOT IN A CHRONOLOGICAL SEQUENCE FOR A RECOVERY. N_AR_092001_1_0070101_01_00

Aircraft Recovery Logic Chart Chart VII FIGURE-09-20-01-991-007-A01

09-20-01

Page 10 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

CHART VIII

PREPARE TO LIFT AIRCRAFT CONTROL CG WITH BALLAST, FUEL, TETHERING ETC.

SEE 06−00−00

SELECT LIFTING ENTRY POINTS CAUTION : THE INSTALLED BELLY FAIRING LIMITS SLING/AIRBAG LIFTING POINTS

FUSELAGE FWD SECTION

FUSELAGE AFT SECTION

WING

FWD JACK POINT

SEE 06−30−00 AND FOLLOW LIFTING PROCEDURE SEE 06−60−00



CRANE AND SLING




WING JACK POINT




CRANE


GO TO CHART XV ( SEE FIGURE 09−20−01−991−015)


Aircraft Recovery Logic Chart Chart VIII FIGURE-09-20-01-991-008-A01

09-20-01

Page 11 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 CHART IX

AIRCRAFT BATTERIES

NO

NO

IS THERE OBVIOUS STRUCTURAL DAMAGE AND/OR FUEL LEAKING?

IS IT BENEFICIAL TO LEAVE BATTERIES CONNECTED?

DISCONNECT AND ISOLATE BATTERIES, AS SOON AS AIRCRAFT IS STABILIZED

YES

YES

DISCONNECT AND ISOLATE BATTERIES (REMOVE IF POSSIBLE). AS SOON AS AIRCRAFT IS STABILIZED

LEAVE BATTERIES CONNECTED BUT MAKE SURE BATTERIE MASTER IS OFF UNLESS IF NEEDED

GO TO CHART IIA STEP B ( SEE FIGURE 09−20−01−991−002)


Aircraft Recovery Logic Chart Chart VIX FIGURE-09-20-01-991-009-A01

09-20-01

Page 12 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

CHART X

DEFUEL SEE 05−10−00 FOR DETAILS

CONSIDER LEAVING FUEL ONBOARD FOR CG CONTROL

1.

NORMAL PRESSURE DEFUEL WITH ALL AIRCRAFT SYSTEMS SERVICEABLE SEE 05−40−01

2.

DRAIN REMAINING FUEL

SEE 05−40−02

3.

DEFUEL USING AN EXTERNAL WIRING HARNESS (EWH) GO TO CHART IV STEP B (SEE FIGURE 09−20−01−991−004)

SEE 05−40−03

NOTE: THE CHARTS ARE NOT IN A CHRONOLOGICAL SEQUENCE FOR A RECOVERY.

N_AR_092001_1_0100101_01_01

Aircraft Recovery Logic Chart Chart X FIGURE-09-20-01-991-010-A01

09-20-01

Page 13 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 CHART XI

WEIGHT AND CG POSITION MANAGEMENT SEE 03−00−00 GET THE REQUIRED DATA TO CALCULATE NRW AND ASSOCIATED CG POSITION

GET OEW (OR DOW) AND ASSOCIATED CG POSITION

CALCULATE EFFECT OF REMAINING FUEL QTY

SEE 05−30−00 AND COMPLETE WORKSHEETS ( SEE 09−50−01)

CALCULATE EFFECT OF REMAINING/ADDED ITEMS


CALCULATE EFFECT OF LARGE COMPONENT MOVEMENT


CALCULATE EFFECT OF REMOVED/MISSING ITEMS

SEE 03−50−01 AND COMPLETE WORKSHEETS ( SEE 09−50−01 )

CALCULATE NRW AND ASSOCIATED CG POSITION

SEE 03−50−01 AND COMPLETE WORKSHEETS ( SEE 09−50−01 )

GO TO CHART IIB STEP H ( SEE FIGURE 09−20−01−991−002 )


Aircraft Recovery Logic Chart Chart XI FIGURE-09-20-01-991-011-A01

09-20-01

Page 14 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 CHART XII

DEBOGGING SEE 07−30−00

CONFIRM WEIGHT AND CG LOCATION SEE 03−00−00

CONFIRM NO FUEL LEAKS AND ALL LANDING GEARS INTACT

MAKE AIRCRAFT AS LIGHT AS PRACTICAL

CONSULT AIRPORT AUTHORITY FOR RECENT EXCAVATIONS

CONFIRM SOIL STABILITY USING APPROPRIATE METHOD

NO

YES

WILL SOIL REQUIRE STABILIZING?

EXCAVATE AREA AROUND LANDING GEAR CONFIRM NO ROADWAY PREPARATION REQUIRED

PREPARE ROADWAY USING GRAVEL, STEEL PLATES, PLYWOOD OR MATS AS NECESSARY SEE 07−20−00

PREPARE TO TOW OR WINCH AIRCRAFT SEE 07−40−00

GO TO CHART XV STEP A ( SEE FIGURE 09−20−01−991−015 )


Aircraft Recovery Logic Chart Chart XII FIGURE-09-20-01-991-012-A01

09-20-01

Page 15 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 CHART XIII

LANDING GEAR SEE 02−30−01 NO

1

ARE ALL LANDING GEARS DOWN AND LOCKED?

NLG RETRACTED, COLLAPSED OR MISSING

YES

INSTALL LANDING GEAR LOCKS

SEE 06−60−01 CONFIRM LANDING GEAR SECURE 2

ONE MLG RETRACTED, COLLAPSED OR MISSING GO TO CHART IIA STEP F ( SEE FIGURE 09−20−01−991−002)

SEE 06−60−02

3

ALL MLG RETRACTED, COLLAPSED OR MISSING SEE 06−60−03 GO TO CHART IIA STEP F ( SEE FIGURE 09−20−01−991−002)

4

NLG AND ONE MLG RETRACTED, COLLAPSED OR MISSING SEE 06−60−04

5

ALL LG RETRACTED, COLLAPSED OR MISSING

SEE 06−60−05


Aircraft Recovery Logic Chart Chart XIII FIGURE-09-20-01-991-013-A01

09-20-01

Page 16 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 CHART XIV

TETHERING / SHORING

SEE 04−30−00 FOR DETAILS NO

ARE TETHERING FITTINGS AVAILABLE?

ATTACH TETHERS TO DOORWAYS FIXTURES, FLAP BEAMS AND LANDING GEAR

YES

ATTACH FITTINGS TO AIRCRAFT

SEE 04−30−00

SEE 04−30−00

PREPARE SHORING IF REQUIRED

INSTALL GROUND ANCHORS

SELECT APPROPRIATE TETHER CABLES

INSTALL TENSIONING DEVICES MONITOR AND RECORD LOADS

GO TO CHART VI STEP E ( SEE FIGURE 09−20−01−991−006 ) NOTE: THE CHARTS ARE NOT IN A CHRONOLOGICAL SEQUENCE FOR A RECOVERY. N_AR_092001_1_0140101_01_00

Aircraft Recovery Logic Chart Chart XIV FIGURE-09-20-01-991-014-A01

09-20-01

Page 17 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 CHART XV

TOWING

SEE 07−40−00 YES "A"

NO "B"

ARE ALL LANDING GEARS SERVICEABLE?

CALCULATE PROJECTED LOADS

SEE 07−40−04

ATTACH SHACKLES TO MAIN LANDING GEAR TOW LUGS

PREPARE AND ATTACH CABLES FOR TOWING AND WINCHING

SEE 07−60−00 FOR DETAILS ON MOVING AIRCRAFT

ARRANGE PULLEY IF REQUIRED

MOVE AIRCRAFT TO INSPECTION FACILITY

ATTACH DYNAMOMETER TO CABLE SYSTEM

MAKE SURE SITE RETURNED TO NORMAL

PREPARE REPORT

USE APPROPRIATE MEANS TO STEER NOSE GEAR

PULL AIRCRAFT STEADILY BACK ON TO HARD SURFACE

SEE 08−00−00

END

RECORD BREAK−AWAY AND PULLING FORCES FROM DYNAMOMETER


Aircraft Recovery Logic Chart Chart XV FIGURE-09-20-01-991-015-A01

09-20-01

Page 18 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-20-01-004-A01 Airline Aircraft Recovery Process Document 1.

Airlines should consider the preparation of an internal Aircraft Recovery Process Document. This document will help the airline to prepare for an aircraft recovery, because it will contain full instructions about how to organize and prepare for a good recovery. It must give the steps on how each airline can do an aircraft recovery, from the time an incident is notified, to the movement of the aircraft to an inspection or repair facility. Help to prepare a process document of this type is available if you contact the IATA Aircraft Recovery Working Group at the website that follows: - http://www.iata.org NOTE : This chapter gives references to web sites for information only. Airbus shall not be held liable for web site or document content and for update or change of addresses. A.

Proposed Coverage (1) The goals of the Aircraft Recovery Team, these should be clearly stated. Some ideas to include are: - How the Recovery Team can react, - What authority the Recovery Team has, - The promotion of aircraft recovery awareness, - How to share aircraft recovery data with the manufacturer, other operators and special interested groups, - Coordination of resources. (2) A current and up-to-date list of the Recovery Team Managers and Recovery Team Leaders. This must include office, home, fax, pager and cell phone numbers. The same information should be available for all other members of the recovery team. (3) A list of applicable aircraft to recover by the Recovery Team. This could include aircraft owned or leased by the airline and aircraft from subsidiary airlines and/or contracted airlines. (4) Procedures to follow when there is a known incident. These must highlight the need to keep and record all important data. (5) Current list of applicable government agencies with contact numbers. (6) How each team member can prepare. This must include suggestions on what items of clothing and equipment should be available in a personal ”go kit”. Vaccinations and visas should also be done. (7) A full list of airline support staff and contact numbers. This should include structural and power plant engineering staff, tooling and equipment technicians, weight and balance, purchasing and logistic personnel.

09-20-01

Page 19 Jul 01/09


(8) A current and full list of all company-owned aircraft recovery equipment. This should include the location, size and weight of all containers in where the equipment is stored. (9) A current copy of the IATP D/E pools ground handling equipment, ground maintenance equipment and aircraft recovery kits. These data are now available at the website that follows: - http://www.iatp.com NOTE : IATP website and recovery kits are available for IATP members only. NOTE : This chapter gives references to web sites for information only. Airbus shall not be held liable for web site or document content and for update or change of addresses. (10) A list of the local availability of general aircraft recovery materials and equipment. made by the company. This list should include materials and equipment such as plywood and steel sheets, crushed rock, cribbing, cranes, heavy equipment etc. You can be prepare this list with the ICAO Removal of disabled aircraft Document 9137AN/898 as a guide. (11) An Aircraft Recovery Manual (ARM) for each fleet type operated and its storage locations. (12) The size of the cargo doors of each fleet type operated. This will helps to move equipment if the incident is at a different airport. (13) A list of all company-owned tooling, that includes recovery tooling such as pneumatic lifting bags, jacks, slings, etc. This can include their location and properties such as capacity, compressed and extended heights, arc movement capability, etc.

09-20-01

Page 20 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-20-01-005-A01 Off Runway Incident Reporting Proforma 1.

General This ”Off-Runway” Incident Form is designed to support the evaluation of ”off runway” in-service incidents. It helps to make technical judgement and to decide the quickest disposition of actions necessary to return the aircraft landing gear to service.

09-20-01

Page 21 Jul 01/09

MSN

AIRCRAFT REGISTRATION

AIRCRAFT TYPE INCLUDING DASH NUMBER

AIRPORT

DATE AND (LOCAL) TIME OF INCIDENT

AIRLINE

FILL IN ALL SECTIONS AS FULLY AS POSSIBLE AND SUPPLY AS MANY PHOTOGRAPHS AS POSSIBLE TO SHOW THE INCIDENT

THIS "OFF−RUNWAY" INCIDENT FORM IS DESIGNED TO SUPPORT THE EVALUATION OF "OFF−RUNWAY" IN−SERVICE INCIDENTS. IT HELPS TO MAKE TECHNICAL JUDGEMENT AND TO DECIDE THE QUICKEST DISPOSITION OF ACTIONS NECESSARY TO RETURN THE AIRCRAFT LANDING GEAR TO SERVICE.

EACH "OFF−RUNWAY" INCIDENT COMPRISES UNIQUE CIRCUMSTANCES WHICH REQUIRE INDIVIDUAL ASSESSMENT AND DISPOSITION.

N_AR_092001_1_0200101_01_00


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

Off Runway Proforma Introduction (Sheet 1 of 9) FIGURE-09-20-01-991-020-A01

09-20-01

Page 22 Jul 01/09

N_AR_092001_1_0200102_01_00

− THE APPLICABLE LANDING GEAR (THE TWO SIDES, FRONT, REAR ELEVATIONS AND ALL AREAS OF DAMAGE) BEFORE AND AFTER RECOVERY − THE AIRCRAFT BEFORE RECOVERY IN ITS REST POSITION OFF THE RUNWAY. − THE TRACKS MADE BY EACH LANDING GEAR OFF THE RUNWAY AND ALL SKID MARKS ON THE RUNWAY − RECOVERY OF THE AIRCRAFT

SUPPLY PHOTOS TO SHOW THE ITEMS BELOW :

SUPPLY PHOTOGRAPHS TO SHOW THE INCIDENT. THESE MUST INCLUDE VIEWS OF THE TAXIWAY, RUNWAY, AIRPORT, BUILDINGS AND THE POSITIONS OF ALL OBSTACLES THAT THE AIRCRAFT TOUCHED DURING THE INCIDENT. YOU MUST ALSO SHOW THE PATH OF THE LANDING GEAR. SHOW THE CROSS SECTION OF THE RUNWAY A AND THE ADJACENT GROUND THAT THE AIRCRAFT MOVED ACROSS, WITH THE APPROXIMATE DIMENSIONS OF ALL STEPS AND GRADIENTS. GIVE THE APPROXIMATE DISTANCES AND TRAJECTORY OF THE AIRCRAFT DURING THE INCIDENT, WITH THE ATTITUDE OF THE AIRCRAFT AFTER THE INCIDENT.

SECTION 1


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

Off Runway Proforma Section 1 (Sheet 2 of 9) FIGURE-09-20-01-991-020-A01

09-20-01

Page 23 Jul 01/09


DETAILED WRITTEN DESCRIPTION OF "OFF−RUNWAY" INCIDENT

SECTION 2

N_AR_092001_1_0200103_01_00

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200


09-20-01

Page 24 Jul 01/09


RUNWAY

10 KNOTS

WIND DIRECTION AND SPEED AT TIME OF INCIDENT

SECTION 3

N_AR_092001_1_0200104_01_00

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200


09-20-01

Page 25 Jul 01/09

METERS FROM CENTERLINE OR

METRIC TONNES OR

TOWING (WITH TOWBAR)

TOWING (TOWBARLESS)

HIGH SPEED TAXIING−TAKE−OFF OTHER

HIGH SPEED TAXIING−LANDING

FEET

METERS

RHMLG

RHMLG

FEET

METERS

LHMLG

LHMLG

FEET

METERS

KNOTS

AT END OF INCIDENT

DRY

DAMP

WET

FLOODED

(F) RUNWAY / TAXIWAY SURFACE CONDITION−TICK AS APPROPRIATE

EVALUATE AT THE TIME OF SUCH AN EVENT

SNOW

TIME FROM START OF INCIDENT (FIRST GEAR OFF RUNWAY) TO AIRCRAFT AT REST

AT BEGINNING OF INCIDENT

(E) APPROXIMATE AIRCRAFT GROUND SPEED AS FUNCTION OF INCIDENT TIME

NLG

OR

NLG

ICE

09-20-01

%MAC

N_AR_092001_1_0200105_01_00

OTHER

SECONDS DIFFICULT TO

KNOTS

(D) DISTANCE RUN OFF RUNWAY BY EACH GEAR (I.E. TRACK LENGTH MADE BY EACH GEAR).

TOUCH DOWN

LOW SPEED TAXIING / MANEUVERING

FEET FROM CENTERLINE OR

IMPERIAL TONS

(C) FLIGHT PHASE OF AIRCRAFT AT TIME OF INCIDENT−TICK APPROPRIATE PHASE

(B) AIRCRAFT CENTER OF GRAVITY

(A) APPROXIMATE AIRCRAFT WEIGHT

SECTION 4 − METRICS


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

Off Runway Proforma Section 4-1 (Sheet 5 of 9) FIGURE-09-20-01-991-020-A01

Page 26 Jul 01/09

SOFT

STONY

WATER LOGGED

WET

UNDULATING

CLAY

OTHER

FLOODED

DAY

NIGHT

VISIBILITY

RUNWAY LIGHTS

KERB STONE

DRAINAGE CHANNELS

ROCKS

HOLES, BURROW

METERS

ICE

OTHER

N_AR_092001_1_0200106_01_00

SUPPLY DRAWING OR PHOTOGRAPH AND APPROXIMATE DIMENSIONS OF ANY OBSTACLES RUN OVER

OTHER

NONE

(H) WERE ANY OBSTACLES TOUCHED DURING THE INCIDENT − PLEASE TICK AS APPROPRIATE.

(5) VISIBILITY −

SNOW

STEPPED/BANKED

OTHER

(4) WEATHER CONDITIONS AT TIME OF INCIDENT − PLEASE GIVE DETAILS

HARD

(3) CONDITION OF GROUND − DRY

(2) NATURE OF SURFACE − FLAT

(1) TYPE OF GROUND − SAND

(G) OFF−RUNWAY SURFACE NATURE AND CONDITIONS: TICK OR SPECIFY AS APPROPRIATE


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200


09-20-01

Page 27 Jul 01/09

YES

NO

m/s

FORWARD

FORWARD

START

ft/s

OR

OR

YES

°

FINISH

LATERAL

LATERAL

NO

FEET

FEET

09-20-01 AT REST

(N) RESTING ATTITUDE OF AIRCRAFT OFF RUNWAY

DURING OFF−RUNWAY TRAJECTORY

(M) ENGINE THRUST,

° °

ROLL PITCH

0%

0%

5%

5%

NOSE DOWN

PORT

10%

10%

MAX DEVIATION OF NOSE WHEEL STEERING ANGLE RELATED TO DIRECTION OF TRAVEL. DURING OFF−RUNWAY TRAJECTORY ° AT REST °

(L) NLG STEERING ANGLE (FUNCTION OF TIME IF POSSIBLE)

ft/s

SAME COMMENT AS ABOVE

VERTICAL

OR

VERTICAL

(K) APPROXIMATE AIRCRAFT VELOCITY IN 3 AXES m/s

METERS

OFF−RUNWAY SKID MARK DISTANCE

(J) WERE THRUST REVERSERS DEPLOYED DURING INCIDENT

METERS

ON−RUNWAY SKID MARK DISTANCE

PLEASE SUPPLY PHOTOGRAPHS OF SKID MARKS IF APPLICABLE

APPROXIMATE LENGTH OF ON−RUNWAY AND OFF−RUNWAY SKID MARKS IF APPLICABLE:

IF YES, AT WHAT POINT IN THE INCIDENT WERE THE BRAKES APPLIED

WERE BRAKES APPLIED DURING THE INCIDENT

(I) BRAKING APPLICATION

NOSE UP

STARBOARD

OTHER%

OTHER%

N_AR_092001_1_0200107_01_00

OR

OR

°

ft/s

m/s


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200


Page 28 Jul 01/09

09-20-01 6

5

NOTE: 01 A320 ONLY − OPTIONAL

01

2

1

9

7

3

10

01

8

4

10

9

01 8

01 7

01 6

01 5

4

3

2

1

WHEEL

DEPTH AND NUMBER OF WHEELS IN GROUND: ENTER VALUES IN TABLE. MARK WHEELS THAT RUN OFF−RUNWAY WITH A CROSS IN THE DIAGRAM BELOW, E.G.

SECTION 5

mm

in

in

N_AR_092001_1_0200108_01_00

mm

DURING RUN OFF RUNWAY

DEPTH IN GROUND IN RESTING ATTITUDE


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200


Page 29 Jul 01/09


DESCRIPTION OF TNE RECOVERY (SUPPLY PHOTOGRAPHS):

SECTION 6

N_AR_092001_1_0200109_01_00

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200


09-20-01

Page 30 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 TASK 09-20-01-869-801-A01 IATA Aircraft Recovery Quick Reference Check List 1.

General This guide was prepared and given by the IATA Aircraft Recovery Working Group. It is a general guide and for use as a checklist during an aircraft recovery incident.

2.


3.


4.


Before you are on the site (1) Get the initial information about the incident. (2) Contact local airline/agent/own representative. (3) Prepare and make a selection of personnel/equipment/manuals. (4) Check availability of IATP-kits and order if necessary. NOTE : IATP website and recovery kits are available for IATP members only.

Subtask 09-20-01-869-002-A01 B.

When you are on the site (1) Make necessary contact with local security/fire fighting brigade to secure the site, and give area map. (2) Give careful instructions for an aircraft recovery plan. (3) Get necessary approval from local authorities to start the recovery operation. (4) Make sure: (a) Communication to/from site works correctly, (b) Transportation to/from site is possible, (c) Necessary accommodation and facilities can be available on site. (5) Contact local airlines, airport authorities and local suppliers for help with. (a) Heavy machinery/cranes, etc. (b) Access roads, building materials. (c) Timber/gravel/sand/steel plates, etc.

09-20-01

Page 31 Jul 01/09


(d) Lighting equipment. (6) Remove all necessary weight possible from the aircraft if needed. (a) Make sure there are documents on restricted articles and hazardous material. (b) Remove fuel and liquids if possible. (c) Remove baggage and cargo if possible. (d) Remove all unwanted and discarded material from the galleys and lavatories. (7) Calculate the aircraft weight and CG. (8) Make sure the recovery plan is still valid and all safety precautions have been taken. (9) Remove all necessary aircraft components if needed. (a) To lighten aircraft, (b) To keep wind-induced loads to a minimum, (c) To observe instructions from local authorities. (10) Make preparation for (a) Tethering/Shoring. (b) Leveling/Lifting. (c) Moving the aircraft. (11) Prepare to put the aircraft in a hangar or to park it.

09-20-01

Page 32 Jul 01/09


09-20-02

RECOVERY TEAM

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-20-02-001-A01 Composition of the Recovery Team 1.

General Airbus recommends that each airline: - Prepare an internal Aircraft Recovery Process document (see DESC 09-20-01-004-A01). - Make an Aircraft Recovery Team, with reference to this document. For this team, it is recommended: - To take the volunteers from the aircraft maintenance branch. These volunteers should have a strong interest in the aircraft recovery process and a good technical background. - That the members of the Aircraft Recovery Team stay a part of the team (even when they have promotions or move to different internal departments) so that their experience is not lost.

2.

The Manager Airbus recommends that each Aircraft Recovery Team have a manager to control the activities of the Aircraft Recovery Team and any aircraft recovery incidents.

3.

A.

The Manager should have: - Experience as an Aircraft Maintenance Production Manager with the related responsibilities, - Experience and/or knowledge related to aircraft recovery.

B.

The Manager should: - Supervise the Aircraft Recovery Team and their related activities, - Organize regular meetings and exercises with the Aircraft Recovery Team, - Be the interface with the airport, local and state authorities for aircraft recovery, - Represent his airline, on the International Airline Transport Association’s (IATA), Aircraft Recovery Working Group (ARWG) and the International Airline Technical Pool (IATP) related to aircraft recovery.

Team Leaders Depending on the size of the airline, there can be one or more Team Leaders. A.

The Team Leaders should have: - Experience as an Aircraft Maintenance Production Team Leader or Foreman, - Good technical and leadership qualities, - Experience and/or knowledge of aircraft recovery, - Good knowledge of jacks, pneumatic lifting bags and cranes.

B.

The Team Leaders should: - Report to the Aircraft Recovery Manager, - Control the company-owned aircraft recovery equipment and make sure that it is always serviceable,

09-20-02

Page 1 Jul 01/09


-

Make recommendations and suggestions related to the purchase of aircraft recovery equipment, Supervise the on-site aircraft recovery steps.

4.

Structures Engineer and Systems Engineer The Structure Engineer and Systems Engineer should: - Analyze damage to the aircraft, - Prepare the drawings necessary for temporary repairs, - Help the Recovery Manager and Team Leader with decisions related to aircraft recovery.

5.

Planner or Purchasing Agent The Planner or Purchasing Agent should: - Know how to get access to the nearest aircraft recovery kit, - Have contact information for local heavy equipment operators, - Know where to get general aircraft recovery materials, - Organize the leasing of equipment when necessary.

6.

Licensed Aircraft Technicians The Licensed Aircraft Technicians should: - Have good technical knowledge, - Have a valid aircraft maintenance license for the specific aircraft type. - Report to the Aircraft Recovery Team Leader, - Do the specific aircraft maintenance tasks assigned by the Team Leader.

09-20-02

Page 2 Jul 01/09


09-30-01

AIRCRAFT RECOVERY EQUIPMENT TOOLING AND MATERIALS


General It can be necessary for operators to use tools during the recovery process. There are two categories of aircraft recovery tooling and equipment: - General recovery equipment - Specialized recovery equipment You can get these tools at the airport (contact the Airport Authorities or IATP if you are a member), or locally (contact local vendors).

2.

General Materials, Equipment and Tooling The general materials, equipment and tooling that follow are usually available locally (this is not a full list) : - Work lights, floodlights, - Ballast bags, - Sheets of plywood, steel plate, planking, etc., - Cribbing timber (railroad ties) to make platforms, - Stones, gravel, broken asphalt to be compacted to make roadways, - Trailers and padded materials (mattresses, rubber padding, tires, sandbags) to move damaged aircraft, - Bulldozers, forklifts, crane, winching vehicles, excavators, - Towing tractor, - Cables, ropes, pulley blocks, ladders, - Mobile shelter-trailer, commercial transport equipment, - Wooden/steel beams, - Flatbed trucks and trailers, - Pumps, hoses and storage for fuel and/or water, - Hand pump for manual doors opening/closing, - On-site communication equipment (telephones, faxes, interphone headsets), An electrical or air power supply can be necessary for some of these tools. Thus, other equipment can be necessary: - Mobile electrical power unit (min. 5 kW), - Mobile air power unit (min. 7 bar (102 psi)). NOTE : The ICAO Airport Services Manual, part 5, Document 9137-AN/898, ”Removal of Disabled Aircraft” gives a list of recommended materials and equipment.

3.

Lifting and Tethering Material The general materials, equipment and tooling that follow will be useful for the lifting and tethering of the aircraft.

09-30-01

Page 1 Jul 01/09


A.

Slings/straps - Nylon, Dacron, Carbon Fiber These slings/straps are moisture and mildew resistant. As they dry quickly, it is possible to put them into storage a short time after use. You can get them in almost all widths and lengths with different end attachments. You can get nylon straps/slings with single or double strength with single or multiple bands. All these slings/straps help prevent damage to the aircraft skins when you lift the aircraft at areas such as the forward fuselage. But it is important to protect the straps from sharp edges and small radiuses. Make sure that the slings/strap has a label, which gives the rate loads. Do an inspection of the straps before you use them.

B.

Wire Rope Usually, a 6X19 type rope made from improved plow strength steel can be used for recovery operations.

C.

Chain All types of hoisting chains made from good quality material will give very good results.

D.

Rope - Manila, Nylon, Polypropylene These are good general-purpose ropes but they are not recommended for lifting or tethering tasks.

09-30-01

Page 2 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-30-01-002-A01 Airbus Specific Recovery Tools 1.

For the wing lifting procedure using cranes (see 06-50-00), Airbus developed a specific tool, see TABLE 1. TOOL - DESCRIPTION (PART NUMBER) QTY VENDOR 7K804427D520 CRANE ATTACHMENT - WING 2 LIFTING BRACKET Airbus Specific Recovery Tools TABLE 1

09-30-01

Page 3 Jul 01/09


09-30-02

AIRCRAFT RECOVERY TOOLING


Table 1 gives the list of tools referenced in the ARM. NOTE : Any comparable equipment may be used provided that it satisfies the requirements of the procedure. Other conventional suppliers of recovery material can provide items of the kits set.

09-30-02

Page 1 Jul 01/09


PART NUMBER 460005833

NOMENCLATURE GROUND LOCK SLEEVE

460005835

GROUND LOCK SLEEVE

460007280

SLEEVE-GROUNDLOCK

7K804427D520

CRANE ATTACHMENT - WING LIFTING BRACKET

97A28002117002

PURGING TOOL

98A09003000001

BAR-STEERING, NOSE WHEEL

98A28104000000

PURGER WATER DRAIN

98A28104000002

TOOL - PURGING

98A28203000000

TEST EQUIPMENT JET PUMP

98D07103000000

DYNAMOMETER - SAFETY STAY

98D07103500000

JACK ADAPTER - FUSELAGE

98D07104081000

JACKING PAD SET (A321)

98D07203000

MOORING FITTING

VENDOR/SUPPLIER

09-30-02

REFERENCES TASK 02-30-01-481-801A01 TASK 02-30-01-481-801A01 TASK 02-30-01-481-801A01 TASK 06-50-00-581-802A01DESC 09-30-01-002A01 TASK 05-40-02-650-801A01 TASK 07-40-02-584-802A01 TASK 03-20-02-970-801A01 TASK 05-40-02-650-801A01 TASK 05-40-02-650-801A01 TASK 06-30-00-581-802A01 TASK 06-30-00-581-802A01 TASK 06-30-00-581-802A01 DESC 04-30-00-001A01TASK 06-50-00-581-803-A01

Page 2 Jul 01/09


PART NUMBER 98D07203003

NOMENCLATURE FUSELAGE SHORING CRADLE

98D09104000001

ATTACHMENT - TOWING

98D09104001000

ATTACHEMENT-TOWING

98D09104002000

ATTACHMENT - TOWING (OPTIONAL 4 WHEEL BOGIE MLG)

98D10203500

MOORING KIT - NLG

98D104000001

JACKING PAD SET (A318, A319, A320)

98D32203502000

SAFETY PIN - NLG DOOR

98D57004031

WING SHORING CRADLE

98F09103500000

CABLE-TOWING, MLG

D23080000

PIN-GROUND LOCK, NLG

D23156000

PIN-SAFETY

VENDOR/SUPPLIER

09-30-02

REFERENCES TASK 06-50-00-581-801A01 TASK 07-40-02-584-801A01 TASK 07-40-02-584-802A01 TASK 07-40-02-584-802A01TASK 07-40-02-584-801-A01 TASK 04-30-00-556-801A01 TASK 06-30-00-581-802A01 TASK 02-30-01-481-801A01 TASK 06-50-00-581-801A01 TASK 07-40-02-584-802A01TASK 07-40-02-584-801-A01 TASK 02-30-01-481-801A01 TASK 07-40-02-584-802A01TASK 07-40-01-584-802A01TASK 07-40-02-584-801A01TASK 07-40-01-584-801-A01 Page 3 Jul 01/09


PART NUMBER DAH602734

NOMENCLATURE GROUND LOCK SLEEVE

DRT68031

SLEEVE - GROUND LOCK

DRT68923

SLEEVE-GROUND LOCK

GSE

WHEEL CHANGE JACK

MZ23080000

PIN - NLG DOWNLOCK SAFETY

TMHCP07-00-00

WHEEL CHANGE AXLE JACK

VENDOR/SUPPLIER

REFERENCES TASK 02-30-01-481-801A01 TASK 02-30-01-481-801A01 TASK 02-30-01-481-801A01 TASK 02-30-01-867-802A01 TASK 02-30-01-481-801A01 TASK 02-30-01-867-802A01

Tools and Equipment TABLE 1

09-30-02

Page 4 Jul 01/09


09-30-03

IATP AIRCRAFT RECOVERY KITS


IATP Recovery Kits The International Airline Technical Pool provides a number of aircraft recovery kits at strategic locations around the world. Currently, there are ten of these kits and they are maintained by provider airlines. NOTE : The kits are also available on a rental basis to non-member operators. Information on kits content, purpose, capability, providers locations etc. should be available from: - http://www.iatp.com NOTE : IATP website and recovery kits are available for IATP members only. NOTE : This chapter gives references to web sites for information only. Airbus shall not be held liable for web site or document content and for update or change of addresses.

2.

Location of the Main Kits Current locations of the IATP kits and their provider are given in TABLE 1: London, England Paris, France Johannesbourg, South Africa Tokyo, Japan New York, USA Chicago, USA Los Angeles, USA Honolulu, USA Sydney, Australia Mumbai, India

LHR ORY JNB NRT JFK ORD LAX HNL SYD BOM

British Airways Air France South African Airways Japan Airlines Delta Airlines American Airlines American Airlines United Airlines Qantas Airlines Air India IATP Recovery Kits TABLE 1

The TABLE 2 gives details on kit suppliers and contacts.

09-30-03

Page 1 Jul 01/09


COMPANY CODE American Airlines

AA

KIT GIVEN LOCATION NAME LAX Julie ORD

FAMILY NAME McClain

Air France AF

ORY

Philippe

Guillem

Air India

AI

BOM

KG

Shekar

British Airways

BA

LHR

Brian

Deacon

Delta Airlines

DL

JFK

Terry

Lucas

Japan Airlines

JL

NRT

Satoru

Arasaki

Qantas

QF

SYD

JeanMarie

L’Eveille

SITA MAILING CODE ADDRESS HDQTPAA American Airlines 3800 N. Mingo Rd. MD 523 Tulsa OK 74158 ORYJOAF Air France Orly Sud 124 F-94396 Orly Aerogare Cedex BOMELAI Air India Line Stations, Engineering Dept Old Airport KALINA MAHARASTRA 400029 INDIA LHRKEBA British Airways PLC BA Maintrol 3rd Floor Europe House Waterside, PO Box 365 HARMONDSWORTH WEST DRAYTON UB7 0GB ATLTEDL Delta Airlines P.O. BOX 20706 ATLANTA GA 30320 USA TYOJPJL Japan Airlines 3-5-1, HANEDA AIRPORT M1 BLDG OTA-KU TOKYO 144-0041 SYDEDQF Qantas Airways Ltd Sydney Distribution Center SYDSDC/1 263-271 Coward Road Mascot N.S.W 2020 AUSTRALIA

09-30-03

Page 2 Jul 01/09


South African

SA

KIT GIVEN LOCATION NAME JNB Charlie

United Airlines

UA

HNL

COMPANY CODE

FAMILY NAME Haman

SITA MAILING CODE ADDRESS JNBMPSA South African South Africa Airways Technical Technical Area JOHANNESBURG International Airport Connie Showalter SFOPSUA United Airlines S.F. Maintenance Base SFOUS San Fransisco International Airport SAN FRANSISCO CA 94128 USA Kit Suppliers and Contacts TABLE 2

09-30-03

Page 3 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-30-03-002-A01 Example of IATP Recovery Kit 1.

This section gives an example of an IATP recovery kit that can be found at main airports. It is only an example and does not reflect the exact content of all main IATP kits. TABLE 1 gives an example of basic recovery kit. TABLE 2 gives an example of supplementary kit. Quantity 90 1 5 5 6 85 6 6 6 16 1 1 2

1

Description PNEUMATIC BAGS (SINGLE ELEMENT) MASTER CONTROL CONSOLE REMOTE CONTROL CONSOLE AIR DISTRIBUTORS MANIFOLD (CONTROL CONSOLE) PNEUMATIC HOSES WINCHES WIRE ROPES EARTH ANCHORS PLASTIC FOAM PROTECTION PADS (50 mm (2 in) thick) ROLL POLYTHENE SHEET (500 gauge, 7.3 m (287 in) wide) AIR COMPRESSOR REGENT TRIPOD CRASH JACKS Capacity - 710 mm (28 in) to 1730 mm (68 in), 80 tons Capacity - 1730 mm (68 in) to 3560 mm (140 in), 100 tons COMPRESSOR SPARES AND BAG REPAIR KIT Basic Recovery Kit TABLE 1

Quantity 2 2 4 4 4 2 1 2

Description PNEUMATIC BAGS PNEUMATIC HOSE REELS MANIFOLD CONTROL CONSOLE / AIR CONTROL CONSOLE WITH 10 OUTLETS PROTECTION PADS WIRE ROPE (CAPACITY OF TOWING A CODE E/F AIRCRAFT) BODY LIFTING SLING (CAPACITY OF LIFTING A CODE E/F AIRCRAFT ) AIR COMPRESSOR (FOR SYNCRO JACKS) SPREADER BARS (INCLUDES SLINGS AND SHACKLES)

09-30-03

Page 4 Jul 01/09


Quantity 1

Description AIR COMPRESSOR Supplementary Recovery Kit TABLE 2

09-30-03

Page 5 Jul 01/09


09-50-01

WEIGHT AND CG CALCULATION WORKSHEETS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 DESC 09-50-01-001-A01 Worksheets 1.

General It is necessary to use these worksheets in relation with chapter 03-50-01. A.

Interim Worksheet: - Fuel Remaining on Board Effect. See FIGURE 09-50-01-991-001-A. - Cargo and Baggage Remaining Effect. See FIGURE 09-50-01-991-002-A. - Total Traffic Load Remaining Effect. See FIGURE 09-50-01-991-003-A. - Ballast Added Effect. See FIGURE 09-50-01-991-004-A. - Waste Water Remaining Effect. See FIGURE 09-50-01-991-005-A. - Non OEW Catering Equipment Added Effect. See FIGURE 09-50-01-991-006-A. - Large Component Movement Effect. See FIGURE 09-50-01-991-007-A. - Potable Water Removed Effect. See FIGURE 09-50-01-991-008-A. - Cockpit and Cabin Crew Removed Effect. See FIGURE 09-50-01-991-009-A. - Catering Equipment Removed Effect. See FIGURE 09-50-01-991-010-A. - Large Component Removed/Missing Effect. See FIGURE 09-50-01-991-011-A. - Hydraulic Fluids Removed Effect. See FIGURE 09-50-01-991-012-A.

B.

NRW & Related H & Y Moment Worksheets - NRW & Related H, & Y Moment Worksheet Calculation from OEW. See FIGURE 09-50-01-991-013-A. - NRW & Related H, & Y Moment Worksheet Calculation from DOW. See FIGURE 09-50-01-991-014-A.

09-50-01

Page 1 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

WEIGHT (kg or lb) TO TO SUBTRACT ADD

MOMENT Weight x H−arm (kgm or lb.in)

MOMENT Weight x Y−arm (kgm or lb.in)

TO TO SUBTRACT ADD

TO TO SUBTRACT ADD

LH OUTER TANK

LH INNER TANK

CENTER TANK AUXILIARY CENTER TANK RH INNER TANK

RH OUTER TANK

TOTAL

N_AR_095001_1_0010101_01_00

Interim Worksheet Fuel Remaining on Board Effect FIGURE-09-50-01-991-001-A01

09-50-01

Page 2 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

WEIGHT (kg or lb)

TO TO SUBTRACT ADD



TO TO SUBTRACT ADD

TO TO SUBTRACT ADD

TOTAL FORWARD CARGO REMAINING EFFECT TOTAL AFT CARGO REMAINING EFFECT TOTAL BULK CARGO REMAINING EFFECT

TOTAL

N_AR_095001_1_0020101_01_00

Interim Worksheet Cargo and Baggage Remaining Effect FIGURE-09-50-01-991-002-A01

09-50-01

Page 3 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

WEIGHT (kg or lb)

TO TO SUBTRACT ADD



TO TO SUBTRACT ADD

TO TO SUBTRACT ADD

TOTAL TRAFFIC LOAD REMAINING

TOTAL

N_AR_095001_1_0030101_01_00

Interim Worksheet Total Traffic Load Remaining Effect FIGURE-09-50-01-991-003-A01

09-50-01

Page 4 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

WEIGHT (kg or lb)

TO TO SUBTRACT ADD



TO TO SUBTRACT ADD

TO TO SUBTRACT ADD

L/H WING BALLAST ADDED EFFECT R/H WING BALLAST ADDED EFFECT MAIN DECK BALLAST ADDED EFFECT FORWARD CARGO BALLAST ADDED EFFECT AFT CARGO BALLAST ADDED EFFECT BULK CARGO BALLAST ADDED EFFECT

TOTAL

N_AR_095001_1_0040101_01_00

Interim Worksheet Ballast Added Effect FIGURE-09-50-01-991-004-A01

09-50-01

Page 5 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

WEIGHT (kg or lb)

TO TO SUBTRACT ADD



TO TO SUBTRACT ADD

TO TO SUBTRACT ADD

WASTE WATER REMAINING

TOTAL

N_AR_095001_1_0050101_01_00

Interim Worksheet Waste Water Remaining Effect FIGURE-09-50-01-991-005-A01

09-50-01

Page 6 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

WEIGHT (kg or lb)

TO TO SUBTRACT ADD



TO TO SUBTRACT ADD

TO TO SUBTRACT ADD

NON OEW CATERING EQUIPMENT EFFECT

TOTAL

N_AR_095001_1_0060101_01_00

Interim Worksheet Non OEW Catering Equipment Added Effect FIGURE-09-50-01-991-006-A01

09-50-01

Page 7 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

WEIGHT (kg or lb)

TO TO SUBTRACT ADD



TO TO SUBTRACT ADD

TO TO SUBTRACT ADD

NLG RETRACTION EFFECT LH MAIN LG RETRACTION EFFECT RH MAIN LG RETRACTION EFFECT SLATS/FLAPS EXTENSION EFFECT

TOTAL

N_AR_095001_1_0070101_01_01

Interim Worksheet Large Component Movement Effect FIGURE-09-50-01-991-007-A01

09-50-01

Page 8 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

WEIGHT (kg or lb)

TO TO SUBTRACT ADD



TO TO SUBTRACT ADD

TO TO SUBTRACT ADD

POTABLE WATER REMOVED EFFECT

TOTAL

N_AR_095001_1_0080101_01_00

Interim Worksheet Potable Water Removed Effect FIGURE-09-50-01-991-008-A01

09-50-01

Page 9 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

WEIGHT (kg or lb)

TO TO SUBTRACT ADD



TO TO SUBTRACT ADD

TO TO SUBTRACT ADD

COCKPIT CREW REMOVED EFFECT CABIN CREW REMOVED EFFECT

TOTAL

N_AR_095001_1_0090101_01_00

Interim Worksheet Cockpit and Cabin Crew Removed Effect FIGURE-09-50-01-991-009-A01

09-50-01

Page 10 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

WEIGHT (kg or lb)

TO TO SUBTRACT ADD



TO TO SUBTRACT ADD

TO TO SUBTRACT ADD

CATERING EQUIPMENT

TOTAL

N_AR_095001_1_0100101_01_00

Interim Worksheet Catering Equipment Removed Effect FIGURE-09-50-01-991-010-A01

09-50-01

Page 11 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

WEIGHT (kg or lb)

TO TO SUBTRACT ADD



TO TO SUBTRACT ADD

TO TO SUBTRACT ADD

LH WING COMPONENT REMOVED/ MISSING EFFECT RH WING COMPONENT REMOVED/ MISSING EFFECT FUSELAGE COMPONENT REMOVED/ MISSING EFFECT FIN COMPONENT REMOVED/ MISSING EFFECT THS COMPONENT REMOVED/ MISSING EFFECT

TOTAL

N_AR_095001_1_0110101_01_00

Interim Worksheet Large Component Removed/Missing Effect FIGURE-09-50-01-991-011-A01

09-50-01

Page 12 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

WEIGHT (kg or lb)

TO TO SUBTRACT ADD



TO TO SUBTRACT ADD

TO TO SUBTRACT ADD

TOTAL HYDRAULIC FLUIDS REMOVED EFFECT

TOTAL

N_AR_095001_1_0120101_01_00

Interim Worksheet Hydraulic Fluids Removed Effect FIGURE-09-50-01-991-012-A01

09-50-01

Page 13 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200 WEIGHT (kg or lb)



TO TO SUBTRACT ADD

TO TO SUBTRACT ADD

TO TO SUBTRACT ADD

OEW FUEL REMAINING ON BOARD EFFECT CARGO AND BAGGAGE REMAINING EFFECT TOTAL TRAFFIC LOAD REMAINING EFFECT

BALLAST ADDED EFFECT WASTE WATER REMAINING EFFECT NON OEW CATERING EQUIPMENT ADDED EFFECT LARGE COMPONENT MOVEMENT EFFECT POTABLE WATER REMOVED EFFECT

COCKPIT AND CABIN CREW REMOVED EFFECT CATERING EQUIPMENT REMOVED EFFECT LARGE COMPONENT REMOVED/MISSING EFFECT HYDRAULIC FLUIDS REMOVED EFFECT TOTAL −

−

= RESULTS

NRW (kg or lb)

−

= H−arm moment (kgm or lb.in)

= Y−arm moment (kgm or lb.in) N_AR_095001_1_0130101_01_00

NRW & Related H, & Y Moment Worksheets NRW & Related H, & Y Moment Worksheet Calculation from OEW FIGURE-09-50-01-991-013-A01

09-50-01

Page 14 Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

WEIGHT (kg or lb)



TO TO SUBTRACT ADD

TO TO SUBTRACT ADD

TO TO SUBTRACT ADD

DOW FUEL REMAINING ON BOARD EFFECT CARGO AND BAGGAGE REMAINING EFFECT TOTAL TRAFFIC LOAD REMAINING EFFECT

BALLAST ADDED EFFECT WASTE WATER REMAINING EFFECT LARGE COMPONENT MOVEMENT EFFECT POTABLE WATER REMOVED EFFECT

COCKPIT AND CABIN CREW REMOVED EFFECT CATERING EQUIPMENT REMOVED EFFECT LARGE COMPONENT REMOVED/MISSING EFFECT HYDRAULIC FLUIDS REMOVED EFFECT TOTAL −

−

= RESULTS

NRW (kg or lb)

−

= H−arm moment (kgm or lb.in)

= Y−arm moment (kgm or lb.in) N_AR_095001_1_0140101_01_00

NRW & Related H, & Y Moment Worksheets NRW & Related H, & Y Moment Worksheet Calculation from DOW FIGURE-09-50-01-991-014-A01

09-50-01

Page 15 Jul 01/09

ARM_A318_A319_A320_A321_20090701

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