SIL 29-066.pdf

CUSTOMER SERVICES DIRECTORATE 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE TELEPHONE + 33 (0)5 61 93 33 33

SERVICE INFORMATION LETTER SUBJECT:

PREVENTING EXTERNAL HYDRAULIC LEAKS

ATA CHAPTER:

27, 29, 32, 52, 78

AIRCRAFT TYPE:

A330, A340, A340-500, A340-600

APPLICABILITY:

ALL A330, A340

REFERENCES:

AIRBUS

SERVICE INFORMATION LETTER

2.

BACKGROUND:

Due to their impact on aircraft dispatch reliability, hydraulic leaks are a concern for operators. The following charts have been produced based on the leak events reported by the operators from January 2005 to end of 2011 for A330, A340 basic and for A340-500/600. It presents the fleet wide operational interruption rate per 100 Take Offs (T/O) due to hydraulic leaks in ATA chapters 27, 29, 32, 52 and 78 for the A330, A340 basic and for A3456 aircraft.

AIRBUS


A330 / A340-200/300 Main Leak Driver OI Rates (2012 Symposium)

A340-500/600 Main Leak Driver OI Rates (2012 Symposium)

AIRBUS


Based on their impact on the operational reliability, information within this paragraph has been gathered addressing hydraulic leak situation that most likely result in long delays or in the loss of a hydraulic system in flight.

4.1 Components:

(1). ATA 27 

A330-200 / A340-500/600 - Rudder servo control seal protrusion

On several A340-600 aircraft, the scraper seal (CMM 27-21-20 IPL Fig.5 item 280) of the rudder servo controls PN 31115-060 / -070 was found extruded. These servo controls (PN 31115-0X0) are installed on A340-500/600 and A330-200 post-mod 49144 (electrical rudder). As long as the leakage rate is within AMM 29-00-00-790-801 limits, according to Goodrich SIL 31115-27-0A, the rudder servo controls that are affected by a piston rod scraper seal extrusion are still serviceable and do not need to be replaced. As final solution, Goodrich has selected a new design of scraper seal enabling to release pressure and avoid extrusion. This solution is introduced by Goodrich Service Bulletin 31115-27-03. For more details please refer to TFU 27.24.00.011 (Closed in April 2009).

AIRBUS

SERVICE INFORMATION LETTER 

A330 / A340-200/300 - Eaton (Former Vickers) – EDP union leaks and high pulsations level

EDP models PV3-300-13K (P/N 974976), PV3-300-13L (P/N 974800) and PV3-300-EA2 (P/N 3022053-000) have been affected by various leak issues that have been addressed through different modifications and Service Bulletins. From October 2007, the EDP model PV3-300-EA2A (P/N 3022053-001) was introduced on production aircraft through mod 56723 and through desirable SB’s A330-29-3106 / A340-294082 for in service aircraft. This model features several major improvements namely:  Parting lines  ROSAN fittings (assembly process change at Eaton)  Transfer tubes Please also refer to TFU :  TFU 29.10.00.030: low pressure regulation  TFU 29.10.00.029: adaptor block porosity  TFU 29.10.00.033: solenoid valve crack Note : all above Eaton EDP models are fully interchangeable. 

A340-500/600 Parker (EDP P/N 66198-01/-02)

Some external leakages have been suspected at the EDPs (P/N 66198-01/-02) parting lines. After in depth investigation by Parker, it is in fact O-ring assembly lube that has worked its way out of

AIRBUS


For more details on the above issues, please refer to TFU 29.11.00.009. 

A330 Trent 700

There have been a number of hydraulic leaks in service due to loss of torque at the union between the damper assembly and the hydraulic tube. The majority of these leaks lead to green hydraulic system loss. RR NMSB 29-F577 recommends repetitive inspection of the Green system hydraulic damper pressure line union tightness (check of witness torque stripe) every A check, pending final fix implementation. For more details please refer to TFU 29.11.00.009.



A330 / All A340 - Check Valve PN CAR400/CAR401 Leaks

Shortly after introduction of check valve CAR401, several cases of leaks and system losses were reported to AIRBUS. The Yellow hydraulic system was the most affected sometimes at a relatively low number of cycles (around 1000 FC). In October 2009, mandated AOT / ISB’s A330-29-3111 and A340-29-4086 were issued to verify the correct torque condition of the check valves (through red marking and traces of seepage/black

AIRBUS


For Aircraft in-service refer to SB A330-29-3104 & SB A340-29-4080. Screw replacements can be done either in-shop or directly on wing. For more details, please refer TFU 29.19.00.002 (Closed in August 2007).



A330 / All A340 - HP Filter

Some operators have reported leaks on the HP filter manifolds P/N FA00512A. Airbus introduced in production P/N FA04804A by MOD 200493 in July 2010 with enhanced fatigue properties. The modification consists of three changes:  New filter head design.  New raw material : Aluminium material of filter head has been replaced by new more resistant aluminium.  Manual deburring process replaced by electro deburring process. Note that the P/N FA04804A is 2-way interchangeable with the P/N FA00512A. For in-service aircraft, the VSB FA04804A-29-001 has been issued in 2010. Note : same filter P/N is used on normal brake system. Brake filters (see “Filter brake manifold” chapter) were more affected by leaks because they are submitted to a higher number of pressure cycles.

AIRBUS


Operators have reported leakage of L/G Selector Valve Manifold NRV Extractor plugs P/N D31AB4412 and P/N D31AB4411-2 due to plug cracks or loosening. The vendor Goodrich Actuation Systems has introduced a new extractor plug P/N D31AB4413 and P/N D31AB4411-3 made of stainless steel to prevent cracks. In addition, the torque value of subject plug has been modified. For more details, please refer to Vendor Service Bulletin D31AB441-32-05 covered by S B A33032-3152 and SB A340-32-4190. However, some operators have reported leakages on post SB A330-32-3152 or SB A340-324190. In order to minimize any potential risk of failure and leakage, Airbus recommends purchasing high quality seals as per SIL 29-064 and to follow standard practices for seal lubrication and installation as per AMM 20-29-00-911. Please, note that the O’ring seal shall be installed using the tool P/N 0U139171 or P/N 98A29103000000. Moreover, it is very important to pay particular attention when performing embodiment of SB A330-32-3152 or SB A340-324190 on-wing, to ensure that the counter torque tool P/N 0U300851 is used during removal of the NRV Plug from the selector valve. Removal without the use of this tool can potentially damage the LG selector valve structural attachment points due to the higher torque required to undo the NRV plug. The counter torque tool should also be used for re-installation of the NRV plug as detailed in SB A330-32-3152 or SB A340-32-4190.



NWS Steering Change Over Valve

AIRBUS




Brake Servo Valve

Brake Servo Valves P/N C20374000-1 led to leaks for both A330 and A340 aircraft due to extrusion of the static ‘O’ ring seal fitted between the valve body and the slide valve guide. Airbus SBs A330-32-3078, A340-32-4107 and Messier-Bugatti VSB C20374-32-030 were issued to introduce Brake Servo Valves P/N C20374000-2 with a modified brake servo valve assembly. For more details, refer to TFU 32.42.48.002. However, on post-mod Brake Servo Valves P/N C20374000-2, several cases of brake servo valve body cracking have been reported with seepage. Metallurgical investigations have shown the cracks on the servo valve body have developed from corrosion pits located at the interface between the servo valve body and the blanking plate. The final solution, adding some loctite 518 layer between the blanking plate edge and the servovalve body, has been proposed in the Messier-Bugatti VSB C20374-32-3350 rev 1 in 2011 with the new Brake Servo Valves P/N C20374000-2 Amdt A. It has been embodied in production from PN C20374000-2 with S/N F137C20374.



Filter brake manifold

AIRBUS




L/G Door Bypass Valve

The door bypass valve (PN HTE960023) was affected by leaks on A330 and A340 aircraft. A new design of the door bypass valve PN FRH530014D was introduced by FR-HITEMP. This improved valve was embodied in production from A/C MSN 281. As an option, operators may also install the new valve retrospectively to ‘in-service’ aircraft. For more details please refer to TFU 32.31.01.004 (closed in February 1999). Several operators have reported failures of the baulk pin retaining plate bolts on PN FRH530014D for which Eaton (ex Fr-Hitemp) have carried out several fatigue / endurance tests over the last few months to try to reproduce the in-service failure. All tests have been passed without a bolt failure, which led Eaton to conclude that overtorquing in-service is the likely reason behind the failures. Eaton has dispatched a VSB ref FRH530014D-32-1 to propose new bolts (providing a higher margin to potential overtorquing) and tamper device (PRC sealant applied over and around the bolt head after tightening to the correct torque to reduce likelihood of in-service tampering). The VSB also replaces the seals on the baulk pin retainer with seals that are pre-scarf cut to provide a better maintenance. For more details please refer to TFU 32.00.00.009 (closed in May 2007).

AIRBUS


system operation. A one-time inspection is requested to be carried out and depending on the inspection results, further actions have to be done. For more details please refer to TFU 32.45.14.001 (closed in December 2001).



Auto Brake Selector Valve Seal NAS1612-8

On A330 / A340-200/300 , some operators have reported some leakages on Auto Brake Selector Valve Seal P/N NAS1612-8. AMM 32-42-13-400-801-A has been revised in January 2012 reflecting new torque values for both unions (2) and (5). Currently, Airbus advises the operator to follow recommendations for seal procurement given in MBD SIL F6137-32-865 issued in November 2009.

4.2 Lines:

(1). ATA 29 

LG Safety valv e return lin e

AIRBUS


Hydraulic connection loosening has been reported at the Braking Plate to which Brake Systems component such as Alternate Brake Dual Valve (5403GG), Alternate Brake Dual Shuttle Valve (5404GG), Alternate Brake Manifold (5405GG), Park Brake Operated Valve (5801GG) and Park Brake Control Valve (4GZ) are fitted. To solve this loose connection issue, on A330/A340-200/300 MSN0728 and subsequent, quality actions were initiated to make sure unions are effectively lubricated during installation. Moreover, on A330/A340 MSN0665 and subsequent (MOD 56013), tightening torque has been increased on 6 hydraulic pipes (12 connections). AMM has been updated, and these changes are reflected in component R/I procedures. Fractures of pipes connected to the Braking Plate have also been experienced. Most affected pipe is pipe PN F3241083100000 (IPC 32-44-03-06A item 100) connected to Brake Accumulators, but a few cases have also been reported on pipes PN F3241032200000, F3241033600000. Modification 200441 modifies brake accumulator line installation. A330-200/300 MSN 1150 and A330 Freighter MSN 1004 and up have been delivered with modification embodied. For aircraft in service, SBs A330-29-3113 and A340-29-4088 were released in August 2010. For more information, refer to TFU 32.43.00.004.

AIRBUS


Few cases of Green System leakage due to chafing of pipe IPC 32-31-03-29 item 200, item 40, item 120 and item 170 have been reported. Associated pipe attachment devices have also been found damaged, due to air trapped in the hydraulic lines. As final solution, Airbus issued SBs A330-32-3223 and A340-32-4266 that introduced one automatic bleeder on the RH MLG door uplock line. This automatic bleeder is similar to the ones used on A340-500/600 (TFU 29.00.00.032 refers), which demonstrated a good efficiency. However, even if embodiment of these SBs cancels the previous ISBs A330-29-3102 and A34029-4079, we recommend to check clamps and pipes to ensure that there are no premature failure signs of the uplock lines. For more details, please refer to TFU 29.00.00.034 (closed in May 2008).



Hydraulic flexible hoses in overwing panel area

Since 2003, on A330 and A340-200/300 aircraft, several operators mostly located in the Asia pacific area have reported failures of flexible hoses (20 items) located on the over wing panel area supplying :  The normal braking system  The pitch trimmer system  The main landing Gear retraction/extension system

AIRBUS




Tee in Spoiler 5 area

Several operators have reported loosening of the NSA855113 tee connections in the Spoiler N°5 area. The events occurred on both RH and LH wing and on both LP and HP lines. The consequence is a leakage at the loose connection, which could lead to a system loss. As final solution, MOD 53814 introducing swaged connections at the T fittings was issued. This modification is embodied from MSN0702 onwards and is covered by SBA340-29-5007 for A340-500/-600 in service aircraft, and by SB A330-29-3100 for A330-300 increased MTOW (ST8), A330-200 (ST7) aircraft. Following leak reports after SB A330-29-3100 embodiment, OIT SE 999.0073/08/LB was raised to inform operator that new SB revision 02 has been launched. SB A330-29-3100 rev02 validated on aircraft, has been dispatched in July 2009. For more details please refer to TFU 29.11.05.001 (closed in June 2009).



A340 CFM56-5C EDP Case Drain Line

Several operators have reported chafing and sometimes hydraulic leaks i nvolving EDP lower case drain line PN AE708820-1 (Goodrich Rohr PN 340D8661-501). Engineering and flight test led to define a new flexible line with a new routing, available through Goodrich SB RA34029-6.

AIRBUS


In-line and EDP integrated dampers have not proved to be the solution to the pressure pulsations causing the leaks. Therefore, in order to address this issue, Airbus and Rolls Royce have developed a new case drain line, which replaces the existing rigid pipe with a flexible hose. This new case drain line has been introduced through RR service bulletin RB211-29-C885, covered by Airbus SB A330-29-3077 (production embodiment rank MSN 382).

4.3 Hydraulic pipes:

Hydraulic tubing damage can be categorized into 2 families, chafing and cracking. This damage is usually induced by:  A wrong line installation (lack of clearance, stress installation, pipe ovality due to incorrect bending, etc.).  Clamping damage (breaking, loosening), spacers’ migration. With time, the hydraulic tubing leaks may increase mainly because of tube chafing. In order to anticipate this potential time-related phenomenon, Airbus recommends inspecting lines for chafing at the opportunity of major maintenance layover. This consists in checking:

AIRBUS


Any dents, kinks or deformation may hide underlying damage and is cause for hose removal. Replace wire braided hose:  If two or more wires in one plait or several wires in a concentrated area are broken,  If braid is protected by a neoprene overlay or a chafe guard and wear or chafing into the steel braid has occurred. If there is wear after chafing, measure the width of the wear (W) and the external diameter (D). If W x 100 / D x 3.14 > 10% replace the flexible hose. Refer to figure 284, AMM task 20-23-11991-089. The same installation recommendations as referenced above for rigid pipes apply for flexible hoses. During hose installation make sure to apply counter-torque to avoid twisting or unintended repositioning of the hose leading to a change of its’ routing.

4.5 Seals:

It is normal behaviour that a seal in contact with hydraulic fluid will swell. Swell or increase in volume is almost always accompanied by a decrease in hardness. Excessive swell, usually induced by seal of bad manufacturing quality, will result in marked softening of the rubber which will lead to reduced abrasion and tear resistance, and then they permit extrusion of the seal under high pressure. Consequently, whenever a component or manifold is removed, the interface seals must

AIRBUS


In order to prevent further issue due to use of seals as per NAS1613 specification from manufacturers not recommended by Airbus, a new seal specification has been defined: EN6109. Oring seals according to this standard are EN6075 and EN6076 seals. Up to date, two suppliers have been qualified and are able to provide these seals:  Greene Tweed and Co Inc  Polymod Technologies Inc To prevent leak issue related to seals, Airbus recommend operators to purchase the following seals:  NAS1611 and NAS1612 from Parker and Le Joint Français only.  EN6075 and EN6076 (all qualified suppliers by Airbus, see “seals as per EN6109 specification” section). For further information regarding Hydraulic system seal, please refer to SIL 29-064. In the early 90’s, Airbus did not recommend a large fleet campaign of hydraulic seal replacement. An A330 operator carried out a fleet seal replacement campaign and the results were not satisfactory. The fact is that a fleet replacement campaign on seals is a major disturbance on the hydraulic system, and could therefore introduce more issues rather than providing a real improvement. As general good practice, it is advised to pay particular attention at high-pressure manifolds and at ground service panels for seepage at the opportunity of the scheduled General Visual Inspections as per MPD tasks performed in the landing gear bay. Seepage on a manifold is usually a clear indication of a seal pre-damage calling for preventive rectification.

AIRBUS


MOD 45820 (embodied from A340 A/C MSN 235) introduced adjustable clamps in production to reduce lateral and longitudinal forces through a better control of the pipe installation tolerance build-up. Due to the extent of this modification, it was considered not retrofitable. New sliding unions HTE620196/197 with an enhanced internal sealing arrangement and new bearing were designed for A340-500/600 A/C in order to address the sensitivity to stress induced by side loads and therefore the hydraulic leakage issue, experienced on PNs HTE620071-1/72-1. After having been tested during A340-500/-600 flight test, sliding unions PN HTE620196 and PN HTE620197 have replaced the sliding unions PN HTE620071-1 and PN HTE620072-1 on A330/ A340 basic aircraft too. For more detail, please refer to VSB HTE620071-1-29-1. Side loads on the sliding union will appear if the sliding union is not correctly installed following the requirement of AMM 29-11-47 or if the counter wrench is not used to tighten lines equipped with sliding unions. This will generate torsion loads on the lines that will induce side loads on the sliding unions. The dynamic seal of the sliding union is more efficient under high pressure. This is why a leakage test with low pressure (7.3 psi) is more critical than a check under nominal system pressure regarding deformation of O-rings in the grooves. Consequently, the external leak limit for sliding unions is defined as follows:  Hydraulic system pressurized: Slight seepage without formation of a drop.  Hydraulic system unpressurized: 1 drop / 10 minutes. This has to be taken into account to avoid unnecessary sliding union removal due to seepage with the hydraulic system in the unpressurized condition.

AIRBUS


If one or more parts you assemble are new, the double torque procedure shall be applied. This double torque procedure can be found in AMM 20-23-11 and is applied on the production line since mid 1997 giving good results.



Cracked unions and sleeves on Titanium pipes

Several sleeves ASNA3759 and few unions ASNA3760 swaged on high-pressure hydraulic pipes have been reported by some operators cracked with no leakage. Further investigations have demonstrated that the cracks were induced by stress corrosion. Several tests have been performed showing that cracked sleeves are more robust that cracked unions which could lead to a leakage. Therefore, Inspection Service Bulletin has been issued in order to recommend repetitive visual inspection of all unions ASNA3760 located in non-pressurized areas. Moreover, to enhance corrosion prevention, it is recommended after the inspection to apply corrosion preventive compound on the inspected non-cracked unions ASNA3760. In case of cracked union finding, the affected pipe must be repaired as per AMM 20-23-11 or replaced. The final solution consists in changing the heat treatment of the fittings (sleeve : ASNA3759 and union : ASNA3760) from H900/H925 to H1075 in order to avoid stress corrosion cracking. The new unions (New PN: ASNA3760VAxx) are now available and new pipes are being manufactured for installation on production line aircraft. Due to lead-time for pipe manufacturing, before MSN 1020, aircraft will have mixed pre & post union configurations. The full embodiment i.e. with new unions and new pipes only, as per Mod 58346, will be effective from MSN 1020 onwards, with new pipe identification. The new sleeves are also available but due to the confirmed low impact, they will be incorporated without identification change. For more

AIRBUS


5.

MODIFICATION INFORMATION:

The summary of all these modifications and other modifications concerning hydraulic leaks can be found in the attachment 1 and attachment 2. 6.

PROCUREMENT:

For booklet and CD-ROM procurement, please refer to SIL 00-032

© AIRBUS S.A.S 2012. All rights reserved. Confidential and proprietary document. This document and all information contained herein is the sole property of AIRBUS S.A.S. No intellectual property rights are granted by the delivery of this document or the disclosure of its content. This document shall not be reproduced or disclosed to a third party without the express written consent of AIRBUS S.A.S. This document and its content shall not be used for any purpose other than that for which it is

AIRBUS INDUSTRIE


ATTACHMENT 1 : AVAILABLE LINE IMPROVEMENT COMPONENT

. t n e m u c o d y r a t e i r p o r p d n a l a i t n e d i f n o C . d e v r e s e r s t h g i r l l A . 2 1 0 2 . S . A . S S U B R I A ©

ATA

VENDOR

Goodrich Actuation System

TFU

SIL

A330 A340 A340-500 A340-600

29

Line at braking plate

29

32.43.00.004

A330, A340

Line hydraulic accumulator

29

29.10.00.031

A330, A340

RH MLG door uplock lines

29

Hydraulic flexible hoses in overwing panel

29

Tee in Spoiler 5 area

29

ALL

29.11.05.001

A340 CFM56-5C EDP Case Drain Line

29

Goodrich

29.10.00.021

Hyd leak from HCU line

29

A330 PW Pylon to Wing Interface Hose

29

HP Lines in Belly Fairing

29

D31AB443-32-03

VALIDITY

LG Safety Return Line

system

29.00.00.035

VSB

A330 A340

29.00.00.034

Aeroquip

29.12.06.001

F3231826400000 F0003170601500 F0003170600900 F0003170601400 F0003152800000 A2901098100000 F3241083100000 F3241032200000 F3241033600000

AIRBUS MOD

MODIFICATION EMBODIMENT

AIRBUS SB

NOTES

32-3219 32-4263 32-5086

29-3113 29-4088

200441

F3231042000000 F3231041900000 F3231040000000 F3231033500000 F0003154900000 A2901131900000 F53912373001 NSA5516CA10NJ

29-4079 29-3102 32-3223 32-4266

A330 A340 A340-500/-600

29-098

29.10.00.018

PN AFFECTED

A330 A340-500/-600 AOL A340/CFM56-00033 Goodrich SB RA34029-6

A340 A340 CFMI

NSA855113-30C NSA855113-10C NSA855113-8C 340D8661-501 340D8661-503 340D8660-509 F2901065200000

29-5007 29-3100

53814

IPC 29-11-05 IPC 29-11-50 IPC 27-64-50 AMM 29-11-49

50416

MSN 528

29-4063

A330

F0003160008400 F0003160008500 F0003160008600

48934 49603

MSN 466

54-3019

A330 A340

F291107XX0000

46199

MSN 138 MSN 139

29-3061 29-4053

SIL NUMBER:

29-066

PAGE:

21 of 27

DATE:

Mar 12/1997

REVISION:

05, July 31/2012

AIRBUS INDUSTRIE


ATTACHMENT 1 : AVAILABLE LINE IMPROVEMENT (cont’d) COMPONENT

Pylon Hydraulic damages

pipes

ATA

VENDOR

TFU

SIL

29

AS

29.10.00.017

29-068

Hoses in wing shroud box

29

Hose

29

MLG Door closing line

VSB

PN AFFECTED

AIRBUS MOD

A330

F29030XXXXXXX X

43547 43680 46553

Multiple PNs

42997 42067

F0003160007900

43696

A330 A340 A330

N/A

29

29.00.00.032

29

29.16.00.003

A340

A330 29-079

A340

F2911091700000 P95B06-201

51775 51931 53238 52597

AE708749-098 AE708749-099

43681

A340-500/-600 EDP Sense Lines

B-nut loosening accumulator

29

on

hyd

29

RR

RB211-29-C720

29.10.00.031 32.43.00.004

A330 RR

A330 A340 A340-500/-600

Avionic bay contamination by hyd leak

29

29.13.00.005

A340-500 A340-600

NLG Door Leakage

32

32.31.14.005

A330 A340

Uplock

Union


AIRBUS SB 29-3071 29-3070 29-3064 29-3068 29-3067

MSN 087

29-3007

MSN 089

29-4011

MSN 083

29-3013

MSN 078

29-4013 29-5006 32-5042 29-5052 32-5059 29-5009

52238 52937 54447 54585

A340-500 A340-600

Hydraulic Servicing Hand Pump and Pipe Damage . t n e m u c o d y r a t e i r p o r p d n a l a i t n e d i f n o C . d e v r e s e r s t h g i r l l A . 2 1 0 2 . S . A . S S U B R I A ©

VALIDITY

MSN 587

29-3098

MSN 585

29-4075

29-3107 29-4083 29-5013

NOTES

OIT 999.0009/95

OIT 999.0100/03 OIT 999.0129/04 OIT 999.0142/06

OIT 999.0077/07

29-3120 29-4092

58489

AOT 29A5014 OIT SE 999.078/08/LB 45220 44865

32-3067 32-4095

SIL NUMBER:

OIT 999.0144/96

29-066

PAGE:

22 of 27

DATE:

Mar 12/1997

REVISION:

05, July 31/2012

AIRBUS INDUSTRIE


ATTACHMENT 1 : AVAILABLE LINE IMPROVEMENT (cont’d) COMPONENT

Loose connection braking plate

ATA

at

the

Hydraulic pipe leak in GE / P&W Engine Pylons


VENDOR

32

TFU

SIL

VSB

VALIDITY

A330 A340

32.43.00.004

54

PN AFFECTED

AIRBUS MOD

F3241032200000 F3241040200000 F3241032400000 F3241032100000 F3241040100000 F3241033600000 F3241083100000

56013 200441


78

Rohr Industries

RR EDP Case Drain Line

78

Rohr

Hyd pressure hose inspection and replacement

78

T/R deploy pipe in CFM Engine

78

BF Goodrich

78.31.00.082

N/A

NOTES

29-3113 29-4088

A330

A340 CFM56-5C T/R actuator hyd pipe leakage

AIRBUS SB

54-3033

RA34078-61

A340 CFMI

4252035-1 4252047-1

RB211-29-C885

A330 RR

LJ51039

SB PW4G-100-72-125

A330/PW4000

4252-78-270

A340 CFMI

44065

MSN 123

48375

MSN 382

29-3077 OIT SE999.0024/08

4252036-1 4252049-1

N/A

N/A

SIL NUMBER:

N/A

AOL A340/CFM 56-99022

29-066

PAGE:

23 of 27

DATE:

Mar 12/1997

REVISION:

05, July 31/2012

AIRBUS INDUSTRIE


ATTACHMENT 2 : AVAILABLE COMPONENT IMPROVEMENT COMPONENT

. t n e m u c o d y r a t e i r p o r p d n a l a i t n e d i f n o C . d e v r e s e r s t h g i r l l A . 2 1 0 2 . S . A . S S U B R

ATA

VENDOR

TFU

SIL

VSB

VALIDITY

PN AFFECTED

AIRBUS MOD

SC4710

49629


AIRBUS SB 27-3125 27-4126

Yaw damper actuator external leakage

27

Goodrich

27.26.00.011

SC4710-27-02

A330 A340

Rudder servo control seal protrusion

27

Goodrich

27.24.00.011

31115-27-03

A330, A340

Engine driven pump (shaft seal assembly)

29

Vickers

29.11.51.001

848354-29-15

A330, A340

Engine Driven Pump (Adaptor block porosity)

3022053-000-29-01

A330

29-3106

29

Eaton

29.10.00.029

A340

29-4082

A330

29-3106

A340

29-4082

A330

29-3106

A340

29-4082

Engine Driven pump (low pressure regulation)

29

Engine Driven pump (Solenoïd valve crack)

29

Engine Driven Pump

29

Eaton

Eaton

3022053-000-29-05 3022053-000-29-04 (Amdt Letter D )

29.10.00.030

3022053-000-29-05 3022053-000-29-03 (Amdt letter C)

29.10.00.033

NOTES

31115-060 31115-070 31115-080 848354 971844 972630 974947 974976 974800

3022053-000-29-05 Parker

A340-500 A340-600

Parker SIL 29-215

EDP Damper Seal on RR engine

29

RR

29.11.00.009

CAR400 / 401

29

Goodrich

29.10.00.034

RR NMSB29-F577 RR NMSB29-E364 RR NMSB29-F727 RR SB29-E592 RR SB29-G062

66198-01/-02

A330 RR AMM 29-11-65 AMM 20-29-00

A340-500 A340-600 29-3111 29-3119 29-4086 29-4096

A330 A340

SIL NUMBER:

29-066

PAGE:

24 of 27

DATE:

Mar 12/1997

REVISION:

05, July 31/2012

AIRBUS INDUSTRIE


ATTACHMENT 2 : AVAILABLE COMPONENT IMPROVEMENT (cont’d) COMPONENT

m u c o d y r a t e i r p o r p d n a l a i t n e d i f n o C . d e v r e s e r s t h g i r l l A . 2 1 0 2 . S . A . S S U B R I A

VENDOR

Ground Service Manifold Screw rupture Sliding Union

29

Eaton Aerospace Steerer FR Hitemp

System Accumulator

29

Olaer

29

Multiple Vendors

29

EDP press. Union O-ring Pylon crossbeam nut

29

Aluminium Union

29

O-Ring manifold

. t n e

ATA

on

HP

29

Multiple vendors

T-fitting union

29

Check Valve Leaks

29

Goodrich

RAT WFI leakage

29

Hamilton Sundstran d

TFU

SIL

VSB

VALIDITY

PN AFFECTED

29.19.00.002

70902-29-04

A330, A340

70902 70902-3/-4

29.11.00.005

HTE620071-1-29-1

A330, A340 A330 A340

088259-29-02

A330 RR

29.00.00.030

29-064

A330 A330 A340 A330 A340 A330 A340 A330, A340, A340-500, A340-600

N/A

MSN234

46006

Multiple PNs

45737

NSA1612-XX NSA1611-XX

44216

NSA855115-25

44838

MSN 219 MSN 181 MSN 228 MSN 132 MSN 128 MSN 162 MSN 166

CAR400 CAR401

54491

ERPS33T-29-01

A340-500 A340-600

772722D

Goodrich SB RA34029-8 VSIL 450-1-3100-0029-01 VSIL 450-2-3100-0029-01

All

50-1-3100-00 50-2-3100-00

All

ASNA3760 ASNA3759

Elektro Metall

29.30.00.008

Cracked unions and sleeves on Titanium pipes

29

Eaton

29.00.00.036

29-082

MSN 234

AS25361-916 NSA1612-16 AN924

29.24.00.006

AIRBUS SB

NOTES

29-3104 29-4080 45820

CAR400-29-01

29


N/A 29A3074 29A4059

088259-04644

29.10.00.023

Hydraulic Pressure Switch Low Reliability

AIRBUS MOD

OIT999.049/98 N/A 29-3062 29-4054 29-3025 29-4025 29-3027 29-4028 29-3101 29-4078 29-5008

53932

AOT A330-29A3111 AOT A340-29A4086

29-4077

29-3105 29-4081 29-5012

SIL NUMBER:

29-066

PAGE:

25 of 27

DATE:

Mar 12/1997

REVISION:

05, July 31/2012

AIRBUS INDUSTRIE


ATTACHMENT 2: AVAILABLE COMPONENT IMPROVEMENT (cont’d) COMPONENT

ATA

VENDOR

TFU

SIL

VSB

VALIDITY

PN AFFECTED

AIRBUS MOD


Brake Unit

32

L/G Selector Manifold NRV Plug NLG Steering Over Valve NWS Actuator Over Valve

. t n e m u c o d y r a t e i r p o r p d n a l a i t n e d i f n o C . d e v r e s e r s t h g i r l l A . 2 1 0 2 . S . A . S S U B R I

Valve Change Change

Goodrich Actuation System

32

Messier Dowty

32.51.17.003

32

Messier Dowty

32.51.17.002

Brake Servo Valve

32

Filter brake manifold

32

Enhanced MLG retraction actuator leakage L/G Door by-pass vlv L/G Door by-pass vlv – Bolts failure NLG retraction actuator leakage NWS Actuator End Fitting Seals Parking valve

brake

operated

F6137-32-3341

32

Messier Bugatti

D31AB441-3205

32.42.48.002

32-104

D23581-32-050 D23581-32-052 A34/56C-32-007 A34/56N-32-042

A330, A340

68-1357 68-1364 2-1577 2-1578

A330 A340

D31AB4412 D31AB4411-2

A330, A340

FA04804A-29001

A330, A340

FA00512A

32.31.46.010

A33/34-32-289

A330, A340

32

FR Hitemp

32.31.01.004

HTE960023-32-1 FRH530014D32-1

A330, A340

32

32.31.22.002

32

Messier Dowty

32

Messier Bugatti

32.45.14.001

10-100501-001

C20374-32-030 C20374-32-3350

Messier Bugatti

32.00.00.009

32-3188 32-4235

C20374000-1 C20374000-2

32

32

A330, A340

D23581-32-071

A330, A340

D23449-32-036

A330 A340

A25315-32-057

32-3152 32-4190

50244

A330, A340 A340-500 A340-600

A330 A340

NOTES

2-1577-32-13 2-1578-32-9 2-1542-32-15 2-1545-12 2-1577-32-11 2-1578-32-7

A330, A340 GoodrichMessier

AIRBUS SB

52795

32-5038 32-3078 32-4107

200493 32-3243 32-4284

HTE960023

MSN 281

FRH530014D

32-3130 32-4170

D23449000

32A3139

A25315-1

32A4176

SIL NUMBER:

OIT 999.0079/01 OIT999.0120/01 CN 2001-517/516

29-066

PAGE:

26 of 27

DATE:

Mar 12/1997

REVISION:

05, July 31/2012

AIRBUS INDUSTRIE


ATTACHMENT 2: AVAILABLE COMPONENT IMPROVEMENT (cont’d) COMPONENT

ATA

VENDOR

TFU

SIL

VSB

VALIDITY A330

Brake Accumulator

32

Olaer

088256-32-05

Brake Accumulator

32

Olaer

SIL 0882560464432-1

Brake return Accumulator insp

32

Messier Bugatti

C20288-32A048

MLG downlock Actuator

32

Messier Dowty

32.31.47.001

Bogie Pitch Trimmer

32

Messier Dowty

32.11.15.005

CLG Door Actuator T/R isolation Valve Filter in PW pylon

32

Liebherr

32.31.75.001

78

Rohr Industries

A33/34-32-115 A33/34-32-116 A33/34-32-157 A33/34-32-158 PW4G-100-7865

A340

All

PN AFFECTED

AIRBUS MOD


088256-04644 68-1357 68-1364 2-1577 2-1578

AIRBUS SB 32A3104 32A4147

OIT 999.0016/04/CL

088259-04644

A330 A340 A330 A340 A330 A340 A340 CFM

114258004 201480002 S4-3300940

A330 PW

905587-19

32A3112 32A4151

C20288000-2 114354001 201481001

NOTES

46557

MSN 244 MSN 246

47458

MSN 325

32-3109 32-4149 AMM 29-11-49200-802

43547


SIL NUMBER:

29-066

PAGE:

27 of 27

DATE:

Mar 12/1997

REVISION:

05, July 31/2012

SIL 29-066.pdf

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