TM 11-5826-302-12 Integrated Inertial Navigation System an ASN-132 1987

TM 11-5826-302-12 TECHNICAL MANUAL

OPERATOR’S AND AVIATION UNIT MAINTENANCE MANUAL

INTEGRATED INERTIAL NAVIGATION SYSTEM AN/ASN-132 (V)

(PART NO. 751500-1)

DISTRIBUTION AUTHORIZED TO THE DEPARTMENT OF DEFENSE AND DOD CONTRACTORS ONLY TO PROTECT TECHNICAL OR OPERATIONAL INFORMATION FROM AUTOMATIC DISSEMINATION UNDER THE INTERNATIONAL EXCHANGE PROGRAM OR BY OTHER MEANS. THIS PROTECTION APPLIES TO PUBLICATIONS REQUIRED SOLELY FOR OFFICIAL USE AND FOR THOSE CONTAINING VALUABLE TECHNICAL OR OPERATIONAL INFORMATION. THIS DETERMINATION WAS MADE ON 3 FEBRUARY 1987. OTHER REQUESTS WILL BE REFERRED TO HQ, U.S. ARMY COMMUNICATIONSELECTRONICS COMMAND, ATTN: AMSEL-ME-P, FORT MONMOUTH, N.J. 07703-5000. DESTRUCTION NOTICE-Destroy by any method that will prevent disclosure of contents or reconstruction of the document.

HEADQUARTERS, DEPARTMENT OF THE ARMY 1 DECEMBER 1987

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SAFETY STEPS TO FOLLOW IF SOMEONE IS THE VICTIM OF ELECTRICAL SHOCK

DO NOT TRY TO PULL OR GRAB THE INDIVIDUAL

IF POSSIBLE, TURN OFF THE ELECTRICAL POWER IF YOU CANNOT TURN OFF THE ELECTRICAL POWER, PULL, PUSH, OR LIFT THE PERSON TO SAFETY USING A DRY WOODEN POLE OR A DRY  ROPE OR SOME OTHER INSULATING MATERIAL

SEND FOR HELP AS SOON AS POSSIBLE

AFTER THE INJURED PERSON IS FREE OF CONTACT WITH THE SOURCE OF ELECTRICAL SHOCK, MOVE THE PERSON A SHORT DISTANCE AWAY AND IMMEDIATELY START ARTIFICIAL RESUSCITATION

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Ensure that aircraft power is removed prior to performing any maintenance.

The NPU weighs approximately 90 pounds. Use at least two persons to lift and move it.

High SIX surface temperatures are present during SDC operation and for a short period of time after a flight (even if the equipment was never turned on). To prevent injury to personnel, allow SDC to cool or wear protective hand covering prior to removing the SDC.

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HEADQUARTERS DEPARTMENT OF THE ARMY

TECHNICAL MANUAL

Washington, DC, 1 December 1987

No. 11-5826-302-12 OPERATOR’ S AND AVIATION UNIT MAINTENANCE MANUAL INTEGRATED INERTIAL NAVIGATION

SYSTEM AN/ASN-132

REPORTING ERRORS AND RECOMMENDING IMPROVEMENTS

If you find any mistakes or If you know of a way to You can help Improve this manual. i m p r o v e t h e p r o c e d u r e s , p l e a s e l e t u s k n o w . Mall your letter, DA Form 2028 (Recommended C h a n g e s t o P u b l i c a t i o n s a n d B l a n k F o r m s ) , o r D A F o rm 2 0 2 8 - 2 l o c a t e d I n t h e b a c k o f t h i s manual direct to: C o mm an de r, U S A rm y Co mm un ic at i on s- El ec t ro ni cs C om ma nd an d Fo rt A reply will be Monmouth, ATTN: AMSEL-ME-MP, Fort Monmouth, New Jersey 07703-5000. furnished direct to you.

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HOW TO USE THIS MANUAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . l

CHAPTER 1

INTRODUCTION .

Section I II III CHAPTER 2

Section I

II III

IV CHAPTER 3

Section I II

III IV

V

VI

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General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Equipment Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Pri nci ple s of Ope rat ion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1-1

OPERATING INSTRUCTIONS .

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Section I II III

IV

APPENDIX C Section I

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1-2 2-1 2-42

2-42 2-69 3-1

AVIATION UNIT MAINTENANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4-1

Lubrication Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IINS Service Upon Receipt . . . . . . . . . . . . . . . . . . . , . . . . . . ........ . . Aviation Unit Preventive Maintenance Checks and Services (PMCS) . . . . . IINS Troubleshooting Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IINS Aviation Unit Maintenance Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . IINS Preparation for Storage or Shipment. . . . . . . . . . . . . . . . . . . . . . . . . . . .

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B-1

Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Maintenance Allocation Chart . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Tools and Test Equipment Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Remarks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B-1 B-5 B-7 B-8

COMPONENTS OF END ITEM AND BASIC ISSUE ITEMS . . . . . . . . . . . . . . . . . . . . . . . .

C-1

Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Components of End Item . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

C-1 C-2

MAINTENANCE ALLOCATION CHART .

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Description and Use of Operator’s Controls and Indicators . . . . . . . . . . . Operator Preventive Maintenance Checks and Services (PMCS) . . . . . . . . . . Operation Under Usual Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Operation Under Unusual Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

REFERENCES

APPENDIX A

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OPERATOR MAINTENANCE

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Page APPENDIX D SectIon I II GLOSSARY . .

EXPENDABLE SUPPLIES AND MATERIALS LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

D-1

Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E x p en d a bl e S u p pl i es a n d M a t e r i a l s L i s t . . . . . . . . . . . . . . . . . . . . . . . . . . . , .

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Section I II

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Abbreviatlons . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Definitions of Unusual Terms . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ALPHABETICAL INDEX . . . . . . . . . . . . . . . . ... . . .

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Glossary 1 Glossary 1 Glossary 2 Index 1

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HOW TO USE THIS MANUAL 1. You must familiarize yourself with the entire maintenance procedures before beginning the maintenance task. 2. The content of this manual is limited to: a. Information on the Integrated Inertial Navigation System. b. Only those maintenance tasks authorized at aviation unit maintenance level. 3. This manual consists of:

a. An introduction to Integrated Inertial Naviga tion System. b. A chapter on system operating instructions, c. A chapter on operator maintenance instructions.

d. A chapter on aviation unit maintenance instructions. e. Lists of references, maintenance allocation chart, components of end item and basic issue items, and expendable supplies and materials in the appendices. f. A glossary of abbreviations and definitions of  unusual terms. g. An alphabetical index. 4. To find information quickly a. A detailed Table of Contents is on page i. b. An alphabetical index is on page Index 1. c. A summmy of all warnings that appear in the manual is at the front of the manual.

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Figure 1-1. Integrated Inertial Navigation System AN/ASN-132(lfJ 

1-0

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CHAPTER 1

INTRODUCTION

Section 1. GENERAL INFORMATION

1-1 SCOPE. 1-1.1 This manual contains information required to perform operator and aviation unit maintenance on the Integrated Inertial Navigation System AN/ASN-132(V) (IINS). 1-1,2 T e of Manual, This manual provides the instructions required to operate, maintain, test, troubleshoot, and repair the IINS at the operator and aviation unit maintenance levels. Functional descriptions, diagrams, tools and test equipment, and material lists are provided to support these functions as dictated by the Maintenance Allocation Chart (MAC). 1-1.3 Model Number and Equipment Name. This manual covers the following model/equipment. Integrated Inertial Navigation System AN/ASN-132(V) 1-1.4 Purpose of Equipment. The IINS provides selfcontained navigation capability to U.S. Army EH-60A Aircraft for short- and/or long-range missions and which can be updated wherever TACAN navigational facilities exist or manually without TACAN data. 1-2 MAINTENANCE FORMS, RECORDS, AND REPORTS. 1-2.1 Reports of Maintenance and Unsatisfactory Equipment, Department of the Army forms and procedures used for equipment maintenance will be those prescribed by DA Pam 738-750, as contained in Maintenance Management Update. 1-2.2 Report of Packaging and Handling Deficiencies. Fill out and fonward SF 364 (Report of Discrepancy (ROD)) as prescribed in AR 735-11-2/DLAR 4140.55/  NAVMATINST 4355.73B/AFR 400-54/MCO 4430.3H. 1-2.3 Discrepancy in Shipment Report (DISREP) (SF 361). Fill out and forward Discrepancy in Shipment Report (DISREP) (SF 361) as prescribed in AR 55-38/  NAVSUPINST 4610.33C/AFR 75-18/MCO P4610.19D/DLAR 4500.15.

1-3 DESTRUCTION OF ARMY ELECTRONICS MATERIEL. 1-3.1 Destruction of  Army electronics materiel to prevent enemy use shall be in accordance with TM 750244-2. 1-4 PREPARATION FOR STORAGE OR SHIPMENT. 1-4.1 Refer to TM 740-90-1 for procedures, forms and records, and inspect ions required during administrative storage of this equipment and chapter 4, section VI of  this manual. 1-5 OFFICIAL NOMENCLATURE, COMMON NAMES, AND DESIGNATIONS. 1-5.1 The following listing includes the common name to official nomenclature cross-references used in this manual. Official Nomenclature

Common Name

Integrated Inertial Navigation System AN/ASN-132(V)

IINS

Inertial Navigation Set AN/ASN-141

INS

Inertial Navigation Set Mount

INS Mount

Data Processing Set AN/UYK-64 (V)2

Navigation Processor Unit (NPU)

Navigation Processor Unit Mount

NPU Mount

Control Display Unit C-11097/ASN-132(V)

CDU

Signal Data Converter CV-3739/ASN-132(V)

SDC

TACAN ReceiverTransmitter RT-1159/A

TACAN RT

1-1

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TACAN Mount

Electrical Equipment Mounting Base MT4915/A

1-6 REPORTING EQUIPMENT IMPROVEMENT

RECOMMENDATIONS (EIR).

1-6.1 If your equipment needs improvement, let us know. Send us an EIR. You, the user, are the only one who can tell us what you don’t like about the design. Put it on an SF 368 (Quality Deficiency Report). Mail it to Commander, US Army Communications-Electronics Command and Fort Monmouth, ATTN: AMSELPA-MA-D, Fort Monmouth, New Jersey 07703-5000. We’ll send you a reply.

1-7 WARRANTY INFORMATION.

1-7.1 The SDC is warranted by Litton Systems, Inc. for 42 months. The CDU is warranted by Rockwell International Corporation for 48 months. Warranty starts on the date found on DA Form 2410 or DA Form 2408-16 in the logbook. Report all defects in material or workmanship to your supervisor who will take appropriate action. Refer to Department of the Army Supply Bulletin SB 11-654 for additional warranty information, as required.

Section Il. EQUIPMENT DESCRIPTION 1-8 PURPOSE OF IINS.

1-8,1 The IINS provides self-contained navigation capability to U.S. ‘Army EH-60A Aircraft for shortand/or long-range missions and which can be updated wherever TACAN navigational facilities exist or manually without TACAN data The IINS employs a bidirectional serial data bus for data interchange within the IINS and with the external mission computer. The IINS also interfaces with the aircraft flight instruments and altimeter/encoder AAU-32A. Navigation sensor and path determination data is processed by the NPU. IINS control and data entry is accomplished by the CDU. 1-9 CAPABILITIES AND FEATURES OF IINS.

1-9.1 The following is a list of general system features. Tables 1-1 through 1-4 provide system alinement times and attitude accuracies in circular error for a 1 hour flight (CEP), CDU display capabilities, and CDU enterable data capabilities. Self-contained navigation system. High accuracy navigation system.

Multiple aircraft applications. Integrated inertial/TACAN navigation capabilities. TACAN updating features. Utilization of off-the-shelf hardware.

Aircraft flight instrumentation and mission system computer interface. MIL-STD-1553 dual redundant digital MUX bus interface communication. System level built-in-test capabilities.

1-2

High system reliability, efficient maintainability and ease of operation. System designed to minimize personnel/equipment hazards. System power interruptions/transients protection. No radioactive, explosive, or caustic chemical elements which require special handling and/or transportation. 1-10 LOCATION AND DESCRIPTION OF MAJOR COMPONENTS.

1-10.1 The illustrations following table 1-4 locate and describe the major components of the IINS units, 1-11 DIFFERENCES BETWEEN MODELS.

1-11.1 There is only one model of the IINS. 1-12 EQUIPMENT DATA.

1-12.1 IINS equipment data are given in table 1-5. 1-13 SAFETY, CARE, AND HANDLING,

1-13.1 Safety. To ensure safety to personnel, follow Army safety procedures for the use and handling of  electronic equipment. Before and while operating the equipment, adhere to the WARNINGS and CAUTIONS indicated throughout this manual. All WARNINGS are also summarized on the WARNING page at the front of this manual. In addition instructions on all WARNING and CAUTION decals attached to the equipment must be followed. 1-13.2 Care. To ensure that the IINS is always ready for operation, it must be inspected systematically so that defects may be discovered and corrected before

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Table 1-1. IINS Alinement Time Accuracies 

Table 1-2. IINS Attitude Accuracies 

they result in serious damage or failure. The preventive maintenance checks and services must be performed at the intervals prescribed to ensure that the IINS is operating properly. Note any defects during operation for correction after operation. Stop operation immediately if a deficiency is noted which would damage the equipment. 1-13.3 Handling. The IINS should be handled with extreme care to prevent damage to precision electronic equipment. The equipment is designed and constructed so that on-vehicle maintenance can be performed in all

specified environments by persomel wearing clothing, such as heavy gloves, required by the particular environment. Required maintenance, such as testing, removal, replacement, and hookup are possible over this expected range of flight line environments. The individual units are designed so that special handling or protective equipment is not needed for installation or for transport between the local maintenance and/or supply facility and the vehicle. Removal and replacement of  the units (except the NPU) in the vehicle can be accomplished by one person using standard tools. Two persons are required to lift the NPU.

1-3

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Table 1-3. CDU Display Data Capabilities

Data

Range

Resolution

Present true heading (inertial)

0 to 359.9 degrees

0.1 degree

Present magnetic heading (inertial)

0 to 359.9 degrees

0.1 degree

Bearing to destination (inertial - true)

0 to 359.9 degrees

0.1 degree

Distance to destination (inertial)

0 to 1852 km (0 to 999 nmi)

0.1 km (0.1 nmi)

Time to steering point (inertial)

0 to 1092.2 min (time)

0.1 min (time) /or 1.0 sec

Distance to steering point (inertial)

0 to 1852 km (0 to 999 nmi)

0.1 km (0.1 nmi)

Course to steering point (inertial true) Bearing to steering point (inertial true )

0 to 359.9 degrees

0.1 degree

0 to 359.9 degrees

0.1 degree

Computed magnetic variation (inertial)

E 179.9 degrees

0.1 degree

W 180 degrees

1-4

Aline time and status (inertial)

0 to 102.3 min (time)

0.1 min time - N/A

Present true ground track (inertial)

0 to 359.9 degrees

0.1 degree

Position error north (inertial)

N/S 0 to 606.8 km (0 to 327.7 nmi)

0.1 km (0.1 nmi)

Position error east (inertial)

E/W 0 to 606.8 km (0 to 327.7 nmi)

0.1 km (0.1 nmi)

TACAN derived present position (latitude - available only if INS fails with NPU functional)

N 0 to 89 °59’9”

0.1 min

S 0 to 90°00’0”

TACAN derived present position (longitude - available only if INS fails with NPU functional )

E 0 to 179°59’9”

Time to destination (inertial)

0 to 1092.2 min (time)

0.1 min (time) /or 1.0 sec

Raw TACAN slant range to station

0 to 200 nmi

0.1 nmi

Raw TACAN mag bearing from station

0 to 359 degrees

1.0 degree

Built In Test (BIT) indicator

System status

0.1 min

W 0 to 180°00’0”

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Table 1-4. CDU Enterable Data Capabilities

Data Destination position (latitude inertial)

Range N 0 to 89°59’59”

Resolution

1.0 arc sec

S 0 to 90°00’00” Destination position (UTM - inertial)

Requirements set forth by UTM MGRS coordinates

10 meter grid

Selected true course to destination (inertial)

0 to 359.9 degrees

0.1 degree

Present position (latitude - inertial)

N 0 to 89°59’59”

1.0 arc sec

S 0 to 90°00’00” Present position (UTM - inertial)

Requirements set forth by UTM MCRS coordinates

10 meter grid

Entered true heading (inertial)

0 to 359.9 degrees

0.1 degree

Entered magnetic heading (inertial)

0 to 359.9 degrees

0.1 degree

Entered magnetic variation (inertial)

E 0 to 179.9

0.1 degree

W 0 to 180.0 Manually entered altitude

-1000 to + 65,000 ft

100 ft

TACAN station position (latitude)

N 0 to 89°59’59”

1.0 arc sec

S 0 to 90°00’00” TACAN station position (UTM)

Requirements set forth by UTM MCRS coordinates

10 meter grid

TACAN station altitude

-1000 to +9,900 ft

100 ft

TACAN station channel

001 to 126, X or Y

Units

TACAN station magnetic variation

E 0 to 179.9°

0.1 degree

W 0 to 180.0° Destination position (longitude inertial)

E 0 to 179°59’59”

1.0 arc sec

W 0 to 180°00’00” Present position (longitude - inertial)

E 0 to 179°59’59”

1.0 arc sec

W 0 to 180°0’00’” TACAN station position (longitude)

E 0 to 179°59’59”

1.0 arc sec

W 0 to 180°00’00”

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1-6

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1. CAUTION DECAL. Provides possible equipment damage information. 2. POWER CONNECTOR. Provides main power inputs to the INS. 3. COOLING AIR OUTLET. Allows cooling air to exhaust through the sides of the INS. 4. LATCH RELEASE. Provides lock release when latch assembly is in locked position. 5. LATCH LOCK. Maintains the latch assembly locking mechanism in the locked position.

6. ELAPSED TIME INDICATOR. Displays total INS operating time in hours. 7. LATCH ASSEMBLY. Provides unit to mount locking mechanism, 8. FAULT INDICATORS. Provides fault detection and isolation information. 9. TEST CONNECTOR. Provides testing interface for intermediate level maintenance. 10. GYRO BIAS DECAL. Provides gyro bias data determined during alinement or test, 11. CALIBRATION DECAL. Provides calibration data determined during alinement or test, 12.

REMOVE/INSTALL DECAL. Provides INS/aircraft installation history data.

1-7

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LOCATION AND DESCRIPTION OF MAJOR INS MOUNT COMPONENTS

1-8

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1. INPUT/OUTPUT CONNECTOR LOCATION. Provides mounting area for aircraft wiring connector.

2. NAMEPLATE. Provides mount identification information. 3. COOLING AIR INLET. Provides mount heat exchanger interface with aircraft cooling air supply. 4. POWER CONNECTOR LOCATION. Provides mounting area for aircraft wiring connector, 5. ROUND GUIDE PIN. Ensures proper positioning and attachment of INS. 6. GASKET, Provides an air seal between the mount and the INS.

7. FLAPPER GUIDE. Provides flapper alinement with INS air intakes.

8. DIAMOND GUIDE PIN, Ensures proper positioning and attachment of INS. 9. KEEPER ASSEMBLY. Provides latch points for the INS latch assembly. 10. HARD BOSSES. Provides correct height alinement for installation of INS.

11. FLAPPER. Allows cooling air to pass through the mount to the INS. 12. COOLING AIR EXIT. Provides cooling air from mount plenum to the INS. 13. DIAMOND GUIDE PIN. Ensures proper positioning and attachment of INS,

1-9

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LOCATION AND DESCRIPTION OF MAJOR NPU COMPONENTS

1-10

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and 9. HANDLES. Provides lifting and transportability aids for maintenance personnel.

2. WARRANTY SEAL. Provides cover seals to preclude unauthorized entry into unit. 3. HEAT EXCHANGER. Provides airfIow to remove heat from the chassis. 4. RUN /RESET SWITCH-INDICATOR, Provides NPU program run indication and reset control. 5. IDENTIFICATION DECAL. Provides NPU nomenclature, part number, and serial number. 6. MOUNTING HOOK. Provides mounting point for NPU mount holddown retainers. 7. , CONSOLE LOCK. Locks out the Virtual Console Port and causes the NPU to begin processing the operational flight program at power-up. 8.

SIGNAL 1/0 CONNECTORS. Connector J3 is used for loading the computer memory. The 1553 data bus connects to cnnector J1O.

10. POWER CONNECTOR. Provides main power inputs to the NPU. 11. ELAPSED TIME METER. Displays total NPU operating time in hours.

Operator must not activate the POWER ON/RESET or BITE/BOOT switches. 12.

POWER ON/RESET SWITCH-INDICATOR. Provides NPU main power on indication and power reset control.

13.

BITE/BOOT SWITCH-INDICATOR. Provides NPU BITE indication and boot control for loading during maintenance.

14. GROUND LUG. Provides NPU chassis to aircraft wiring ground connection. 15. FUSES. Provides 10 amp NPU circuit protection. 16. FUSES. Provides 30 amp NPU circuit protection.

1-11

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LOCATION AND DESCRIPTION OF MAJOR NPU MOUNT COMPONENTS

1. GUIDE PIN. Ensures proper positioning and attachment of NPU. 2. SHOCK MOUNT. Provides shock and vibration protection for the NPU. 3. IDENTIFICATION DECAL. Provides NPU mount nomenclature, part number, and serial number. 4. NPU SELF-LOCKING HOLDDOWN RETAINER Secures NPU to mount.

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LOCATION AND DESCRIPTION OF MAJOR CDU COMPONENTS

1. IDENTIFICATION DECAL. Provides CDU nomenclature, part number, and serial number. 2. ELAPSED TIME METER. Displays total CDU operating time in hours. 3.

CAUTION DECAL. Provides electrostatic sensitive devices caution information to prevent possible equipment damage.

4.

OPERATOR CONTROLS. Provides all controls required to operate the system and perform both operator and organizational maintenance,

5. CRT DISPLAY. Provides data display required for system operation and maintenance.

1-13

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LOCATION AND DESCRIPTION OF MAJOR SDC COMPONENTS

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1. COOLING FINS. Provides cooling by natural convection to side mounted fins. 2. POWER/SIGNAL 1/0 CONNECTOR, Provides input power and signal interface connection to aircraft wiring. 3. MOUNTING HOOK. Provides mounting point for TACAN mount holddown retainer. 4. WARRANTY SEAL. Provides seals to preclude unauthorized entry into the unit.

5.

INSTRUMENT 1/0 CONNECTOR. Provides interface for Aeronautical Radio Incorporated (ARINC) flight instruments buses.

6. BK DATA BUS CONNECTOR. Provides interface for backup serial data bus B. 7. PRI DATA BUS CONNECTOR. Provides interface for primary serial data bus A. 8. PS1 FAIL INDICATOR. Provides power supply card fault detection display. 9. A2 FAIL INDICATOR. Provides ARINC processor card fault detection display. 10. Al FAIL INDICATOR. Provides AMUX card fault detection display. 11. BRACKET. Provides for securing the SDC to the TACAN. 12. ELAPSED TIME METER. Displays total SDC operating time in hours. 13. IDENTIFICATION DECAL. Provides SDC nomenclature, part number, and serial number, 14. WARRANTY DECAL. Provides warranty information and instructions. 15. INSTALLATION /REMOVAL DECAL. Provides SDC/aircraft installation history data.

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LOCATION AND DESCRIPTION OF MAJOR TACAN RT COMPONENTS

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1. WARRANTY DECAL. Provides warranty information and instructions. 2. POWER CONNECTOR. Provides main power inputs to the TACAN RT. 3. RECORD CARD. Provides record of TACAN RT removal and installation dates. 4. MOUNTING HOOK. Provides mounting point for TACAN mount holddown retainers. 5. ANTENNA 2 CONNECTOR. Not used. Dummy load is connected. 6. SUPPRESSOR IN CONNECTOR. Provides interface connection to aircraft L-BAND equipment. 7. MODIFICATION PLATE. Provides for the recording of any equipment modifications. 8. ANTENNA I CONNECTOR. Provides interface connection to aircraft antenna. 9. SUPPRESSOR IN/OUT CONNECTOR. Provides interface connection to aircraft L-BAND equipment. 10. ELAPSED TIME INDICATOR. Displays total TACAN RT operating time in hours. 11. BLOWER INLET, Provides airflow inlet to the internal blower, 12. HANDLE.

Provides lifting and transportability aids for maintenance personnel.

13. TEST CONNECTOR. Provides testing interface connection for depot level maintenance.

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LOCATION AND DESCRIPTION OF MAJOR TACAN MOUNT COMPONENTS

1-18

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and 3. CONNECTORS. Provides signal and power interface connection to aircraft wiring.

2. FUSE. Provides 10 amp system power overload protection. 4.

SDC 1/0 CONNECTOR. Provides interface connection to SDC connector.

5 and 6. SHOCK MOUNTS. Provides shock and vibration protection for the TACAN RT and SDC. 7. SDC SELF-LOCKING HOLDDOWN RETAINER. Secures SDC to TACAN mount. 8

and 11. TACAN RT SELF-LOCKING HOLDDOWN RETAINERS. Secures TACAN RT to mount. 9. POWER CABLE. Provides input power to the TACAN RT.

10. MODIFICATION PLATE. Provides for the recording of any mount modifications. 12. WARRANTY DECAL. Provides warranty information and instructions. 13

and 14, GUIDE PINS. Ensures proper positioning and attachment of TACAN RT.

1-19

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Table 1-5. IINS   Equipment Data Item

Value

WEIGHTS AND DIMENSIONS

Item

Value

172.466 mm (6.79 in. )

Height

INS Weight

18.73 kg (41.20 lb)

Length

459.486 mm (18.09 in.)

Width

191.008 mm (7.52 in.)

Height

193.548 mm (7.62 in.)

TACAN Mount Weight

0.90 kg (2.00 lb)

Length

439,4 mm (17,30 in.)

Width

266.7 mm (10.50 in.)

Height

212.3 mm (8.36 in.)

INS Mount Weight

2.54 kg (5.60 lb)

Length

372.11 mm (14.65 in.)

Width

251.96 mm (9,92 in.)

Height

35.56 mm (1.40 in. )

POWER REQUIREMENTS IINS

Total system DC power requirements, 359 watts maximum

NPU Weight

40.82 kg (90.00 lb)

Length

614.426 mm (24.19 in. )

Width

337.82 mm (13.30 in.)

Height

193,548 mm (7.62 in.)

104 to 122V, 360 to 440 Hz, B-phase, 710 VA (starting), 70 VA (running)

Weight

2.27 kg (5.00 lb)

Length

567.944 mm (22.36 in.)

104 to 122V, 360 to 440 Hz, C-phase, 710 VA (starting), 70 VA (running)

Width

279.4 mm (11.00 in.)

Height

48.26 mm (1.90 in. )

INS

NPU Mount

Weight

4.54 kg (10.00 lb)

Length

165.1 mm (6.50 in.)

Width

146.05 mm (5.75 in.)

Height

180.975 mm (7. 125 in. )

SDC

Backup power (battery), 16.0 to 30.0 VDC, 240 watts maximum NPU

4.54 kg (10.00 lb)

Length

373.38 mm (14.70 in. )

Width

70.86 mm (2.79 in. )

Height

204.47 mm (8.05 in. )

TACAN RT Weight

13,61 kg (30.00 lb)

Length

369.316 mm (14.54 in.)

Width

171.196 mm (6.74 in. )

100 to 130V, 380 to 420 Hz, single-phase, 380 watts 24.0 to 32.0 VDC

CDU

Weight

104 to 122V, 360 to 440 Hz, A-phase, 340 VA (starting), 280 VA (running)

26V, 360 to 440 Hz, B-phase, 40 VA (starting), 35 VA (running)

CDU

1-20

Total system AC power requirements, 2500 volt amperes (VA) maximum

0 to 5V, 380 to 420 Hz, 10 VA maximum 24.0 to 28.5 VDC, 50 watts maximum

SDC

24.0 to 28.5 VDC. 50 watts maximum

TACAN RT

108 to 118V, 380 to 420 Hz, 200 VA (T/R mode), 250 VA (A/A mode)

TM 11-5826-302-12

Table 1-5. IINS Equipment Data - Continued  Item

Value

Item

ENVIRONMENTAL

Value

SDC Temperature:

INS

Temperature: Operating Non-operating

-40”C (-40”F) to +71°C (+ 160”F)” -54”c (-65”F) to +95”c (+203”F)

‘Provided proper cooling air requirements are met.

Operating

-54°c (-65°F) to +55°c (+131°F)

Non-operating

-62°C (-79°F) to +85°C (+185°F)

Altitude —

Cooling air Altitude: Steady-state

-457 m (-1500 ft) to + 18,288 m (+ 60,000 ft)

Intermittent (2 min max)

+ 18,288 m ( + 60,000 ft) to +24,384 m (+80,000 ft)

Cooling air

Temperature: Operating

Temperature:

Non-operating Altitude

-55”c (-67°F) to +71°c (+160°F) -62°C (-79°) to +95°C (+202°F)

Continuous: -54°c (-65°F) to +71°C (+ 160°F)

Intermittent and 0.5-hour intervals: + 95°C ( + 203°F) Non-operating

Operating

Natural convection to side mounted cooling fins

TACAN RT

3.6 pounds per minute maximum

NPU

+ 9144 m (30,000 ft) maximum

-62°C (-80°F) to +95°C ( +203°F)

Altitude

+21,336 m (70,000 ft) maximum

Cooling air

internal blower

+24,384 m ( +80,000 ft) maximum Natural conduction to side mounted heat exchanger. Heat exchanger fan draws 40 cubic feet per minute

CDU

Temperature: Operating

Continuous: -54°c (-65°F) to +55°C ( + 131°F)

Half-hour: -54°C (-65°F) to +71°C (+ 160ºF) Non-operating

-64°C (-83°F) to +71°C (+160°F)

Altitude

Sea level to 12,192 m (40,000 ft)

Cooling air

Natural convection and conduction to mounting panel

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TM 11-5826-302-12

Section III. PRINCIPLES OF OPERATION 1-14 PRINCIPLES OF OPERATION.

1-14.1 The IINS provides accurate knowledge of aircraft navigation parameters including present position, velocity, altitude, and heading information. The IINS is capable of short- and/or long-range missions and can be updated wherever TACAN navigation facilities exist or manually without TACAN data. A serial data bus is employed for data exchange within the IINS and the external avionic systems. The multiplex data bus system consists of two separate buses (A and B). Only one bus is active at any given time, with the other bus in a standby mode for redundancy purposes. As shown in figure 1-2, the multiplex data buses provide a path for data flow between the INS, SDC, NPU, CDU, and the external mission systems. Data to and from the TACAN RT is first processed by the SDC before it is applied to the multiplex data buses. 1-14.2 The INS provides inertial reference for the IINS which includes aircraft velocity, altitude, position heading, and attitude. The INS operates by sensing aircraft accelerations from a gyro-stabilized, four-gimbal, all-attitude platform. Output functions of the INS include accurate present-position and velocity data,

course-line computations, steering commands, and angular pitch, roll, and heading information. The navigation and guidance computations are performed by a general-purpose digital computer using a semiconductor memory. The computer steering commands are referenced either to great-circle route to the desired destination coordinates, or to a selected magnetic course from the coordinates of the position at which the selected magnetic course steering mode was selected. 1-14.3 The NPU provides computer processing and input /output operation for the IINS. System level computations are performed by the NPU to implement the following IINS integration functions: system executive and master schedular; TACAN RT/inertial updating; TACAN RT automatic tuning; primary bus controller; system level built-in test; NPU built-in self-test; backup mode logic/control (other than NPU failure); and altitude data processing/slant range compensation. The NPU contains a central processor unit (CPU) that directly addresses 64K 16-bit words of core memory for instructions and data. The CPU is microprogrammed and decodes the operands and performs the required

 Figure 1-2. IINS Block Diagram

1-22

TM 11-5826-302-12

arithmetic, logic and control functions. The CPU controls the operation of the 1/0 section of the NPU for communications with other units over the multiplex data buses. 1-14.4 The CDU displays data and controls the operating modes of the IINS. The CDU is capable of  entering, changing, and recalling data from the NPU, INS, and TACAN RT; receiving data from the aircraft altimeter encoder. This data is encoded and displayed on the CDU CRT as navigational and operational status information. In addition, the CDU provides mode control to the INS and TACAN RT. Electrical power to the INS and TACAN RT is also controlled by the CDU. The CDU also acts as backup bus controller for the multiplex data buses in the event of an NPU failure. 1-14.5 The SDC performs data processing to convert the TACAN RT Aeronautical Radio Incorporated (ARINC) inputs and outputs to corresponding serial data formats for transmission over the multiplex data buses to the NPU and CDU. The SDC can communicate via one of the two multiplex data buses, Although the SDC communicates over only one multiplex data bus at a time, it can monitor both buses continuously to determine over which bus valid data communications are taking place. Redundant portions of the SDC circuitry are isolated to ensure that a failure of one bus does not degrade performance of the remaining bus. The

SDC also provides ARINC characteristic digital parameters to the aircraft flight instruments. 1-14.6 The position error of an inertial navigation system increases with time, therefore, a position reference sensor is used to update the inertial data, and thereby bound the time-growing position error. The IINS derives position updates from the TACAN RT range and bearing measurements. The TACAN RT determines the relative bearing of the aircraft from a selected TACAN ground station and determines the distance or range of the station. The TACAN RT operates within 390 nautical miles of a TACAN ground station. Since the TACAN system operating limit is line of sight, the actual operating range is dependent on aircraft altitude. The TACAN system operates on a selected channel from 252 available channels. The 252 channels are equally divided into 126 x-channels and 126 y-channels with both x- and y-channels spaced at 1 MHz intervals. Upon being interrogated by the TACAN RT, the ground station beacon transmits a signal. From this signal the TACAN RT computes the values of  bearing and distance for updating the inertial system information. The TACAN RT outputs are processed by the SDC for compatibility with the multiplex data buses. The TACAN RT also produces and transmits distance information when interrogated in the air-to-air operation by another TACAN-equipped aircraft, however, this air-to-air mode precludes using the TACAN information to update the IINS.

1-23/(1-24 blank)

TM 11-5826-302-12

CHAPTER 2 OPERATING INSTRUCTIONS

Section 1. DESCRIPTION AND USE OF OPERATOR’S CONTROLS AND INDICATORS 2-1 OPERATORS CONTROLS AND INDICATORS.

2-1.1 The IINS operating controls and indicators are contained on the CDU. The CDU controls and indicators are illustrated in in figure 2-1 2-1 and listed, with functional descriptions, in  in  table 2-1. 2-2 CDU DATA DISPLAY PAGE DESCRIPTIONS.

2-2.1 When the IINS is operating, various pages can be displayd on the CDU data display. These pages provide navigation information for the operator during

preflight and flight. Each page consists of eight lines with up to 19 characters on each line. In most cases each line is divided into the left side and right side. Each side contains information pertinent to the operation of the IINS. On both sides of lines 1, 3, 5, and 7 there are line select keys which perform functions as defined by the line legend adjacent to the line select key.  key.  Table 2-1  2-1  describes the function of the line select keys. Following are typical illustrations and descriptions of each CDU data display page.

2-1

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Figure 2-1. Controls and Indicators 

2-2

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Table 2-1. CDU Controls and Indicators

Key

Control or Indicator

Function

1

Data display

Displays multiple flight parameters to the operator on seven data lines and a scratch pad line on the face of the cathode ray tube (CRT)

2

Line select keys

On both sides of data display lines 1, 3, 5, and 7 are pushbuttons (line select keys) which perform functions as defined by the legend adjacent to the key on the data display. If a line select key is active on a particular page, an arrow will appear in the character space closest to the key. Arrows will be oriented toward the legend, up, or toward the key (away from the legend). These orientations (with examples) are defined as follows: 1.

legend (TH 358.3 ). If the arrow points toward the legend a numeric entry (entered into the scratch pad on line 8) is allowed by pressing the adjacent line select key

2.

legend (MAC ). If the arrow points away from the legend, pressing the adjacent line select key will initiate the function described by the legend. For example, pressing the line select key adjacent to “MAC will change the display to MAC Heading (MH) and MAG VAR (MV)

3.

legend ( T/R). If the arrow points up, the legend indicates current mode status and pressing the adjacent line select key will change the mode. If no arrow appears next to a legend then that line select key performs no operation or down pointing arrows on the sixth line of the data display allows operator to slew display one page up or down by pressing page

4. Up

slew toggle switch up or down 3

Alphanumeric keys

Alphanumeric entries are made by pressing one of the ten character keys on the keyboard and will appear first in the scratch pad (line 8), Each actuation of a key will cause a character to be displayed from left to right in the scratch pad. When using multiple letter keys (e.g., KLM /  5), letters K, L, or M can be entered into the scratch pad by successive actuations of the KLM /5 key. The 0-9 and . keys shall enter the respective number or decimal point unless the keyboard is in the letter mode. When the LTR/USE key is pressed, LTR is annunciated to the right of the scratch pad, and the next keystroke will enter an alpha character. When the desired data appears in the scratch pad, it will be entered by pressing the line select key adjacent to the data being updated, When the line select key is pressed, the scratch pad contents will be checked for proper range and format. If the entry is valid, it will be transferred to the IINS, read back, and displayed adjacent to the line select key. Completion of this cycle will clear the scratch pad

4

CLR key

Used for erasing scratch pad parameters before entry. First actuation clears the last number or letter entered, second actuation clears the entire entry

5

B RT

6 

0 key

control

Controls brightness of the data display from full on to full 05 Used to enter number 0 into the scratch pad

2-3 2- 3

TM 11-5826-302-12

Table 2-1. CDU Controls and indicators - Continued 

Key

Control or Indicator

Function

7

-/. key

Used to enter a minus symbol or decimal into the scratch pad. When pressed, . will be entered into the scratch pad. When LTR/USE key is pressed, then - /. key is pressed, - will be entered into the scratch pad. To use the - in the scratch pad, the LTR/USE key must be pressed again

8

LTR/USE key

When pressed, allows letters to be entered into the scratch pad. When pressed a second time, signals the CDU to use the character that was  just entered, and deletes LTR entry mode

9

FACK key

When pressed, signals the system that an annunciated failure has been recognized by the operator, and causes the flashing annunciation to go to a steady annunciation

10

Page select switch

Selects the type of information to be displayed. The following five categories of display pages can be selected: 1. POS. Provides provisions for entering present position; universal transverse mercator (UTM) or latitude/longitude (L/L) selection. Provides provisions for entering magnetic variation, true and magnetic; ground track; and ground speed. TTG and TO/FROM annunciators; failed RT annunciation; NAV RDY in aline mode; UPDT in NAV mode 2. INS. Provides inertial alinement status; barometric pressure; altitude; data zeroize; and access to system data and unit tests; time in aline mode; steering and destination number selected; failed RT; UPDT in NAV; TTG and TO/FROM NAV RDY in aline annunciations 3. DEST. Provides selected course entry; destination coordinates; UTM or L/L selection; range, bearing, and time to destination; cardinal heading/distance; steering and destination number selected; failed RT annunciation; UPDT annunciator in NAV; NAVRDY; last mark  designation 4. STR. Provides selected course; range, bearing and time to steerpoint; present position; UTM or L/L selection; cardinal heading/distance; failed RT annunciator; NAVRDY annunciator in aline; UPDT in NAV; TTG and TO/FROM annunciators 5. TCN. Provides both TACAN control and station data. The TACAN control page provides power control; mode selection; slant range and bearing to station; update enable; and access to station pages. The TACAN station pages provide station number magnetic variation entry; coordinates, channel entry; slant range/bearing entry; and elevation entry. Number of selected station and number of station updating. Failed RT numbers; NAVRDY; UPDT; TO/FROM; channel selection and selection of auto or manual mode

2-4

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Table 2-1. CDU Controls and Indicators - Continued 

Key

Control or Indicator

Function NOTE

All five pages above provide scratchpad for entering data.

11

Mode select switch

Selects eight different modes of operation for theIINS. The mode select switch selects the following IINS modes of operation: 1. OFF. Turns off the IINS (removes power from TACAN RT, INS, and CDU) 2.

FAST. In this position the INS either performs a stored heading alinement or best available true heading (BATH) alinement. If a BATH alinement is performed, true or magnetic heading information must be entered not later than 1 minute after selecting the FAST mode. If magnetic heading information is not entered, system will assume a stored heading. After heading information is entered, present position may be entered if desired

3.

NORM. In this position the INS performs a gyrocompass alinement. Present position coordinates must be entered not later than 2 minutes after selecting the NORM mode

4.

NAV. This is the INS primary flight mode of operation. NAV is entered after satisfactory alinement conditions have been met

5.

UPDT. In this position the NPU freezes present position data for a later manual position update by overflying a known position designated by a mark 

6.

ATTD. In this position the INS initiates an attitude reference mode of  operation. Although navigation processing is discontinued, the INS continues to provide a stable reference frame for generation of roll, pitch, and inertial heading angles

7.

CAL. In this position the INS performs an automatic calibration of  the gyro biases

8.

TEST. In this position the INS performs fictional performance tests, fault detection; and fault localization checks

12

DEST switch

Three position toggle switch used to increment/decrement selected destination. The number of the selected destination appears on line 1 of the data display. Up increases and down decreases the selected destination

13

BIT indicator

Used to indicate the results of all internal CDU tests. White indicates a failure and black indicates test passed

2-5

TM 11-5826-302-12 Table 2-1. CDU Controls and Indicators – Continued 

Key

Control or Indicator

Function

14

STR switch

Three position toggle switch used to increment/decrement selected steerpoint. The number of the selected steerpoint appears on line 1 of  the data display. Up increases and down decreases the steerpoint number

15

MRK key

Used to signal the INS to note the current present position and use it for one of two of the following purposes: 1. Store as a markpoint (destination A thru F) when the mode select switch is in the NAV position 2. Store present position relative to selected destination for possible updating when mode select switch is in the UPDT position

16

2-6

Page slew switch

Three position toggle switch used to slew data display one page up or down by pressing page slew switch up or down

TM 11-5826-302-12

POSITION PAGE (UTM)

NOTE To select this page, set CDU page select switch to POS and press line 7 right line select keys as required to obtain the above display.

(2-7 blank)/2-8

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1. LINE 1. The left side displays the page label. The right side displays true beading (TH). Entered true heading will be accepted only during the first 80 seconds of a fast alinement. Arrow indication goes off after navigation mode is selected. 2. LINE 2. This line is reserved for annunciations described later. 3.

LINE 3. The left side displays magnetic variation (MV). At power turon, the INS computed variation is indicated. If a magnetic variation is entered, the entered value will be displayed and used by the INS, An equal sign will appear for entered magnetic variation. If adjacent line select key is pressed with an empty scratch pad, the entered value will be ‘replaced with the computed value. The right side displays the magnetic heading (MH). Entered magnetic heading will be accepted only during the first 60 seconds of a fast alinement. Arrow indication goes off after the navigation mode is selected.

4.

LINE 4. The left side displays the true aircraft ground track (GTK). The right side displays current ground speed (GS) in kilometers/hour in UTM mode and nautical miles/hour in L/L mode.

5.

LINE 5, The left side displays universal transverse mercator (UTM) grid zone and spheroid. UTM grid zone and spheroid can only be entered during the first 2 minutes of NORM or FAST alinement. Arrow indication goes off  after navigation mode is selected.

6. LINE 6. The left side is reserved for annunciations described later. 7.

LINE 7. The left side displays area, casting, and northing. Easting and northing are displayed to 10 meters. Area, casting, and northing can only be entered during the first 2 minutes of gyrocompass or BATH alinement. Arrow indication goes off after navigation mode is selected. The right side displays that the UTM coordinates are displayed on lines 5 and 7, If adjacent line select key is pressed, the latitude and longitude (L/L) coordinates are displayed on lines 5 and 7, respectively. Latitude and longitude are displayed in degrees/minutes/seconds.

8.

LINE 8. This line is the scratch pad, Data entered from the CDU keyboard first appears on this line before it is entered into the system and onto the applicable line by pressing the applicable line select switch.

2-9

TM 11-5826-302-12

POSITION PAGE (L/L)

NOTE To select this page, set CDU page select switch to POS and press line 7 right line select key as required to obtain the above display.

2-10

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1. LINE 1. The left side displays the page label. The right side displays true heading (TH). Entered true heading will be accepted only during the first 60 seconds of a fast alinement. Arrow indication goes off after navigation mode is selected. 2. LINE 2. This line is reserved for annunciations described later. 3. LINE 3. The left side displays magnetic variation (MV). The right side displays magnetic heading (MH). 4. LINE 4. The left side displays the true aircraft ground track (CTK). The right side displays current ground speed (GS) in kilometers/hour in UTM mode and nautical miles/hour in L/L mode. 5. LINE 5. The left side displays present position latitude. Present position latitude can only be entered during the first 2 minutes of gyrocompass or BATH alinement. Arrow indication goes off after navigation mode is selected. 6. LINE 6. The left side is reserved for annunciations described later. 7. LINE 7. The left side displays present position longitude. Present position longitude can only be entered during the first 2 minutes of gyrocompass or BATH alinement. Arrow indication goes off after navigation mode is selected. The right side displays that latitude and longitude (L/L) coordinates are indicated. If adjacent line select key is pressed, the universal transverse mercator (UTM) coordinates are displayed on lines 5 and 7. 8. LINE 8. This line is the scratch pad. Data entered from the CDU keyboard first appears on this line before it is entered into the system and onto the applicable line by pressing the applicable line select switch,

2-11

TM 11-5826-302-12

NOTE To select this page, set CDU page select switch to INS.

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TM 11-5826-302-12

1. LINE 1. The left side displays the page label and selected destination and steerpoint. The right side displays that the zeroize page can be selected by pressing the adjacent line select key. 2. LINE 2. This line is reserved for annunciations described later. 3.

LINE 3. The left side displays one of three sources of altitude; manually entered altitude (MALT), encoding altimeter altitude (MLT), or baro inertial altitude (IALT). Altitude can only be entered during gyrocompass or BATH alinement. Arrow indication goes off after navigation mode is selected. The right side displays . . that the TESTS page can be selected by pressing the adjacent line select key.

4. LINE 4. Not used. 5. LINE 5. The left side displays barometric pressure (BARO), Barometric pressure must be entered during NORM or FAST alinement. Arrow indication goes off after navigation mode is selected. The right side displays that the DATA page can be selected by pressing the adjacent line select key. 6. LINE 6. The left side is reserved for annunciations described later. The right side displays the destination location in which the last mark was stored. 7.

LINE 7, The left side displays INS alinement time and goes from 0.0 (INS turn on) to a maximum of 99,9 minutes. The right side displays alinement status (STAT) as follows: initialize (INIT), attitude available (ATTD), attitude and heading available (A + H), or relative measure of circular error probability (8.0 - 0.8).

8.

LINE 8. This line is the scratch pad. Data entered from the CDU keyboard first appears on this line before it is entered into the system and onto the applicable line by pressing the applicable line select switch.

2-13

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ZEROIZE PAGE

NOTE This page is selected from the INS page by pressing line 1 right line select key.

2-14

TM 11-5826-302-12 1. LINE L This line displays the page label. 2. LINE 2. This line is reserved for annunciations described later. 3. LINE 3. The left side displays that sensitive data can be zeroized by pressing the adjacent line select key. The right side is not used. 4. LINE 4. The left side will display DATA CLEAR after line 3 left line select key has been pressed, confirming that the sensitive data (TACAN destination data) has been erased. 5. LINE 5. Not used. 6. LINE 6. The left side is reserved for annunciations described later. The right side displays that the INS page can be selected by pressing the CDU page slew switch down. 7. LINE 7. Not used. 8. LINE 8. Not used.

2-15

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TESTS PAGE

NOTE This page is selected from the INS page by pressing line 3 right line select key.

2-16

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1. LINE L The left side displays the page label. The right side displays CDU version number. 2. LINE 2. This line is reserved for annunciations described later, 3. LINE 3. The left side displays that the CDU test can be initiated by pressing the adjacent line select key. After the line select key is pressed, the word GO will be replaced with a blank. After completion of the test, the the word GO or FAIL will be displayed. The right side displays the status of the NPU. Either GO or FAIL will be continuously displayed. 4. LINE 4. The left side displays ARINC GO, This test is automatic. The right side displays the status of the INS, Either GO or FAIL will be continuously displayed. 5. LINE 5. The left side displays that TCN test can be initiated by pressing the adjacent line select key. After the line select key is pressed, the word GO will be replaced with a blank, After completion of the test, the word GO or FAIL will be displayed. The right side displays the status of the mission system computer interface (MSC). Either GO or FAIL will be continuously displayed. 6. LINE 6. The left side is reserved for annunciations described later. The right side displays that the INS page can be selected by pressing the CDU page slew switch down. 7. LINE 7. Not used. 8. LINE 8. Not used.

2-17

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NOTE This page is selected from the INS page by pressing line 5 right line select key.

2-18

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1. LINE 1. This line displays the page label. 2. LINE 2. This line is reserved for annunciations described later. 3. LINE 3. The left side displays that the NPU data page can be selected by pressing the adjacent line select key, The right side displays that the pitch, roll, and velocity (P/R VEL) page can be selected by pressing the adjacent line select key. 4. LINE 4. Not used. 5. LINE 5. The left side displays that the I06 data page can be selected by pressing the adjacent line select key. The right side displays that the I07 data page can be selected by pressing the adjacent line select key. 6. LINE 6. The left side is reserved for annunciations described later. The right side displays that the INS page can be selected by pressing the CDU page slew switch down. 7. LINE 7. The left side displays INS miscellaneous data addresses. Addresses that can be entered should be in decimal format with a range of 0 to 65,535. The right side displays the contents of the addressed memory location. The contents of INS memory will be displayed in alphanumeric characters. 8. LINE 8. This line is the scratch pad. Data entered from the CDU keyboard first appears on this line before it is entered into the system and onto the applicable line by pressing the applicable line select switch.

2-19

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NOTE This page is selected from the DATA page by pressing line 3 left line select key.

2-20

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1.

LINE 1. The left side displays an address. To access information from the NPU, a five digit octal address is entered followed by an alpha character (A thru E) to indicate format. If fixed point format (B) is desired a two digit binary scale factor must follow the B. The arrow pointing down on the right side indicates that the contents of the addressed memory location is displayed on the right side of line 2.

2. LINE 2. This line displays contents of memory location for address displayed on left side of line 1. 3.

LINE 3. The left side displays an address. The arrow pointing down on the right side indicates that the contents of the addressed memory location is displayed on the right side of line 4.

4. LINE 4. This line displays contents of memory location for address displayed on left side of line 3. 5. LINE 5. The left side displays an address. The arrow pointing down on the right side indicates that the contents of the addressed memory location is displayed on line 6.

6. LINE 6. This line displays contents of memory location for address displayed on left side of line 5. 7. LINE 7. This line displays that the DATA page can be selected by pressing the CDU page slew switch down. 8.

LINE 8. This line is the scratch pad. Data entered from the CDU keyboard first appears on this line before it is entered into the system and onto the applicable line by pressing the applicable line select switch,

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NOTE These pages are selected from the DATA page by pressing line 5 left or right line select keys. These pages are identical except line 4 will indicate 106 or 107, depending upon which page was selected from the DATA page. This page is not used at the operator or aviation unit level.

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1, 3, 5, and 7. LINES 1, 3, 5, and 7. These four lines contain data coming from the INS. All words are in octal format on four pages. 106 contains 30 words and I07 contains 32 words.

2. LINE 2. This line is reserved for annunciations described later. 4, LINE 4. This line displays the page label. 6. LINE 6. The left side is reserved for annunciations described later. The arrow indicates that new sets of words (total of four sets) can be selected by pressing the CDU page slew switch up. Pressing the page slew switch a fourth time will reset back to displaying set one. 8. LINE 8. Not used<

2-23

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NOTE

This page is selected from the DATA page by pressing line 3 right line select key.

2-24

TM 11-5826-302-12

1. LINE 1. This line displays the page label. 2. LINE 2. This line is resewed for annunciations described later. 3 and 4. LINES 3 and 4. These two lines display X, Y, and Z velocities in units of feet/second. 5. LINE 5. This line displays pitch in units of degrees/minutes. 6. LINE 6. The left side is reserved for annunciations described later. The right side indicates that the DATA page can be selected by pressing the CDU page slew switch down. 7. LINE 7. This line displays roll in units of degrees/minutes. 8. LINE 8. Not used.

2-25

TM 11-5826-302-12

DESTINATION PAGE

NOTE

To select this page, set CDU page select switch to DEST and press line 7 right line select key as required to obtain the above display.

2-26

TM 11-5826-302-12

L LINE L The left side displays the page label and selected destination (D2) and steerpoint (83). A new destination may be selected by pressing the CDU DEST switch up or down to increment or decrement the selected destination by one. The right side displays desired course (true) to destination. When the system is first turned on all courses to destination will default to previously entered data. 2. LINE 2. This line is reserved for annunciations described later. 3. LINE 3. The left side displays current range (RNG) to the selected destination in kilometers. The right side displays bearing (BRG) from true north to the selected destination. 4. LINE 4. The left side displays time-to-go (TTG) to the selected destination. If TTC is greater than 2 minutes, it is displayed in minutes and tenths of minutes. If TTG is less than 2 minutes, it is displayed in minutes and seconds. The right side displays the north/south distance in kilometers to a true east/west line intersecting the selected destination. The distance is calculated assuming a flat earth. 5. LINE 5. The left side displays military grid reference system (MGRS) or universal transverse mercator (UTM) grid zone and spheroid (refer to the glossary for spheroid definition) of the destination. The right side displays east/  west distance in kilometers to a true north/south line intersecting the selected destination. The distance is calculated assuming a flat earth. 6. LINE 6. The left side is reserved for annunciations described later. The right side is not used. 7. LINE 7. The left side displays destination area casting, and northing. The right side indicates that the UTM coordinates are displayed on lines 5 and 7. If adjacent line select key is pressed, the latitude and longitude (L/L) coordinates will be displayed on lines 5 and 7, respectively. Latitude and longitude are indicated in degrees/  minutes/seconds. Distances are measured in nautical miles. 8. LINE 8. This line is the scratch pad. Data entered from the CDU keyboard first appears on this line before it is entered into the system and onto the applicable line by pressing the applicable line select switch.

2-27

TM 11-5826-302-12

STEER PAGE

N O T E

To select this page, set CDU pagesekct switch to STR and press line 7 right line select key as required to obtain the above display.

2-28

TM 11-5826-302-12

1. LINE 1. The left side displays the page label and selected destination (D2) and steerpoint (S3). A new steerpoint may be selected by pressing the CDU STR switch up or down to increment or decrement the selected steerpoint by one provided the steer points have been entered as destinations. The right side displays desired selected true course to the selected steerpoint. If a course to destination has not been previously entered, the CDU will command the INS to use zero degrees as the desired course. 2. LINE 2. This line is reserved for annunciations described later, 3.

LINE 3. The left side displays current range (RNG) to the selected steerpoint in kilometers. The right side displays bearing (BRG ) from true north to the selected steerpoint.

4. LINE 4. The left side displays time-to-go (TTG) to the selected steerpoint. If TTG is greater than 2 minutes, it is displayed in minutes and tenths of minutes, If TTG is less than 2 minutes, it is displayed in minutes and seconds. The right side displays the north/south distance in kilometers to a true east/west line intersecting the selected steerpoint. The distance is calculated assuming a flat earth. 5.

LINE 5. The left side displays the universal transverse mercator (UTM) steerpoint grid zone and spheroid. The right side displays east /west distance in kilometers to a true north/south line intersecting the selected steerpoint. The distance is calculated assuming a flat earth.

6. LINE 6. The left side is resewed for annunciations described later. 7.

LINE 7. The left side displays steerpoint area casting, and northing. The right side indicates that the UTM coordinates are displayed on lines 5 and 7. If adjacent line select key is pressed the latitude and longitude (L/L) coordinates are displayed on lines 5 and 7, respectively. Latitude and longitude are displayed in degrees/minutes/  seconds. Distances are measured in nautical miles.

8. LINE 8. Not used.

2-29

TM 11-5626-202-12

TACAN CONTROL PACE

NOTE

To select this page, set CDU page select switch to TCN.

2-30

TM 11-5826402-12

1.

LINE 1. The left side displays TACAN RT power. Pressing the adjacent line select key will either apply or remove power to the TACAN RT with ON or OFF appearing to the right of TACAN. The right side displays the number of the current tuned station in the automatic mode or MAN in the manual mode.

2. LINE 2, This line is reserved for annunciations described later. 3.

LINE 3, The left side displays TACAN RT mode. Four modes are available through successive actuation of the adjacent line select key. They are receive (REC), air-to-air receive (A/A REC), transmit/receive (T/R), and air-toair transmit/receive (A/ A T/R). The right side displays the currently tuned TACAN RT channel. In the automatic mode, the channel number will be controlled by the NPU as the active stations are scanned. Manual TACAN control is provided by entry of the desired channel on the TACAN control page. The TACAN RT will be tuned to the entered channel and remain at that channel until a 00 channel number is entered. Updating will continue to the data from this manual channel (STA MAN on line 1 right) if the data is acceptable to the filter or unless UPDT is deleted by pressing line 5 right line select key. After a 00 channel is entered, computer control of the TACAN RT will resume.

4.

LINE 4. The left side displays slant range (SRNG) in nautical miles from the aircraft to the currently tuned TACAN station, The right side displays bearing (BRG) from magnetic north to the currently tuned TACAN station,

5. LINE 5. This line displays system update mode, either no updates (NORM) or the TACAN update mode (UPDT), as selected by the adjacent line select key. When in the UPDT mode, the NPU will process the TACAN data and provide automatic updates to the INS, Also, when in UPDT mode, numbers will appear to indicate the number of  stations updating out of the number of active stations. 6.

LINE 6. The left side is reserved for annunciations described later. The right side indicates that the TACAN station (STA) page can be selected by pressing the CDU page slew switch up.

7

LINE 7. The left side displays the number of TACAN stations failing to pass the 3 sigma internal test within the TACAN. The right side is not used.

8. LINE 8. This line is the scratch pad. Data entered from the CDU keyboard first appears on this line before it is entered into the system and onto the applicable line by pressing the applicable line select switch.

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TM 11-3826-302-12

TACAN STATION PAGE

NOTE

This page is selected from the TACAN control page by pressing the CDU page slew switch up.

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TM 11-5824-302-12

1. LINE 1. The left side displays the age label and TACAN station number. The right side displays whether a TACAN station has been enabled ACT) or disabled (INACT) by actuation of the adjacent line select key. Disabling a TACAN station will preclude it from being scanned or used for update purposes. 2. LINE 2. This line is reserved for annunciations described later. 3. LINE 3. The left side displays magnetic variation (MV) which must be entered for each TACAN station. System will assume previously entered data or zero if not entered. The right side displays the TACAN station channel (CH) number. Channel X is assumed unless a Y is entered. 4. LINE 4. The left side displays slant range (SRNG) in nautical miles from the aircraft to the currently tuned TACAN station. The right side displays bearing (BRG) from magnetic north to the currently tuned TACAN station. 5. LINE 5. The left side displays the universal transverse mercator (UTM) TACAN station grid zone and spheroid or latitude, The right side displays TACAN station elevation (thousands of feet). Resolution is provided to the nearest 10 feet. 6. LINE 6. The left side is reserved for annunciations described later. The right side displays that additional TACAN station (STA) pages can be selected by pressing the CDU page slew switch up or down to increment or decrement the station number displayed. 7. LINE 7. The left side displays TACAN station area, casting, and northing or longitude. The right side indicates that the UTM coordinates are displayed on lines 5 and 7. If adjacent line select key is pressed, the latitude and longitude (L/L) coordinates are displayed on lines 5 and 7, respectively. Latitude and longitude are displayed in degrees/minutes/seconds. 8. LINE 8. This line is the scratch pad. Data entered from the CDU keyboard first appears on this line before it is entered into the system and onto the applicable line by pressing the applicable line select switch.

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TM 11-5826-302-12

MARK OPERATION PAGE

NOTE

To select this page, set CDU page select switch to STR press MRK key, and press line 7 right line select key as required to obtain the above display,

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TM 11-5826-302-12

1. LINE 1. The left side displays the page label and selected destination (D2) and steerpoint (S3). A new steerpoint may be selected by pressing the CDU STR switch up or down to increment or decrement the selected steerpoint by one provided the steer points have been entered as destinations. The right side displays current desired true course to the selected steerpoint. If a course to destination has not been previously entered, the CDU will command the INS to use zero degrees as the desired course. 2. LINE 2. This line is reserved for annunciations described later, 3.

LINE 3. The left side displays current range (RNG) to the selected steerpoint in kilometers. The right side displays bearing (BRG) from true north, to the selected steerpoint.

4. LINE 4. The left side displays time-to-go (TTG) to the selected steerpoint. If TTG is greater than 2 minutes, it is displayed in minutes and tenths of minutes. If TTG is less than 2 minutes, it is displayed in minutes and seconds. The right side displays the north/south distance in kilometers to a true east/west line intersecting the selected steerpoint. The distance is calculated assuming a flat earth.

5.

LINE 5. The left side displays the universal transverse mercator (UTM) steerpoint grid zone and spheroid. The right side displays east /west distance in kilometers to a true north/south line intersecting the selected steerpoint, The distance is calculated assuming a flat earth,

6.

LINE 6. The left side is reserved for annunciations described later,

7.

LINE 7. The left side displays steerpoint area, easting, and northing. The right side indicates that the UTM coordinates are displayed on lines 5 and 7. If adjacent line select key is pressed, the latitude and longitude (L/L) coordinates are displayed on lines 5 and 7, respectively. Latitude and longitude are displayed in degrees/minutes/  seconds. Distances are measured in nautical miles.

8. LINE 8. This line is the scratch pad. It displays the markpoint location (MARK C) in sequence (A, B, C, D, E, F, A, B, etc.). The markpoint location will remain on the scratch pad until cleared with the CDU CLR key, or the scratch pad is used to enter some other data.

2--35

TM 11-5826-302-12

NOTE

To select this page, set CDU mode select switch to UPDT. When this page is selected, TACAN updating is deleted,

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TM 11-5826-302-12

1. LINE 1. The left side displays the page label and selected destination and steerpoint. The right side is not used. 2. LINE 2. This line is reserved for annunciations described later. 3. LINE 3. The left side displays current range (RNG) to the selected destination in kilometers in UTM mode and nautical miles in L/L mode. The right side displays bearing (BRG) from true north, to the selected destination. 4. LINE 4. The left side displays time-to-go (TTC) to the selected destination. If TTC is greater than 2 minutes, it is displayed in minutes and tenths of minutes. If TTG is less than 2 minutes, it is displayed in minutes and seconds. The right side displays the north/south distance in kilometers in UTM mode and nautical miles in L/L mode, to a true east /west line intersecting the selected destination. The distance is calculated assuming a flat earth. 5. LINE 5. The left side is not used. The right side displays east/west distance in kilometers in UTM mode and nautical miles in L/L mode, to a true north/south line intersecting the selected destination. The distance is calculated assuming a flat earth. 6. LINE 6. The left side is reserved for annunciations described later. The right side is not used. 7. LINE 7. Not used. 8. LINE 8. Not used.

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TM 11-5826-302-12

ACCEPT/REJECT PAGE

NOTE

To select this page, set CDU mode select switch to UPDT and press MRK key to obtain the above display.

2-38

TM 11-5826-302-12

1. LINE 1. The left side displays the page label and selected destination and steerpoint. The right side is not used. 2. LINE 2. This line is reserved for annunciations described later. 3. LINE 3, The left side displays current range (RNG) to the selected destination in kilometers in UTM mode and nautical miles in L/L mode. The right side displays bearing (BRG) from true north, to the selected destination, 4. LINE 4, The left side displays time-to-go (TTG) to the selected destination. If TTG is greater than 2 minutes, it is displayed in minutes and tenths of minutes. If TTG is less than 2 minutes, it is displayed in minutes and seconds. The right side displays the north/south distance in kilometers in UTM mode and nautical miles in L/L mode, to a true east /west line intersecting the selected destination. The right side displays the north/south correction that will be sent to the NPU to correct the system present position if that update is accepted. The distance is calculated assuming a flat earth. 5. LINE 5. The left side is not used. The right side displays east/west distance in kilometers in UTM mode and nautical miles in L/L mode, to a true north/south line intersecting the selected destination. This distance will be applied as the east/west correction to the system present position if the update is accepted. The distance is calculated assuming a flat earth, 6. LINE 6. The left side is reserved for annunciations described later. The right side is not used, 7. LINE 7. The left side displays ACCEPT. If the adjacent line select key is pressed, the update is accepted and the data display returns to the update page. The right side displays REJECT. If the adjacent line select key is pressed, the update is rejected and the data display returns to the update page. NOTE

Prior to accepting an update to the system, be certain that the aircraft was directly over the entered destination at the time of MARK and that the proper destination is displayed at the top of the page. Verification that the cardinal distances on lines 4 and 5 are reasonable (within a few tenths of a kilometer if manual position updating has been performed or within current system error indications if position updating was not performed) is an approved method of this verification. 8. LINE 8. Not used.

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TM 11-5826-302-12

ANNUNCIATIONS

System status messages appear on line 2 (2) and the left side of line 6 (6) regardless of selected page (except NPU data page). Data appearing on lines 1 (l), 3 (3), 4 (4), 5 (5), 7 (7), and 8 (8) will be whatever is applicable to the page selected. The following is a summary of messages that are presented and the failures /condition they represent:

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TM 11-5826-302-12

Message

Failure/Condition

Line

MSC

Mission system computer interface has failed

2

NPU

NPU has failed

2

INU

INS navigation processing has failed. Attitude may be valid

2

ADC

Air data (altimeter) is invalid

2

TCN

TACAN RT has failed or is turned off 

2

PFM

Post flight maintenance is required

2

TTG (flashing)

Aircraft is within 2 minutes of selected steerpoint

2

TO

Distance to steerpoint is decreasing

2

FROM

Distance to steerpoint is increasing

2

Scu

Signal data converter has failed or ARINC bus has failed

2

NAVRDY (steady)

During alinement. INS attitude data and degraded navigation performance are available

6

NAVRDY (flashing)

During alinement. Full INS navigation performance is available

6

ATTD

The INS is in attitude mode due to:

6

a. Operator selection b. INS failure c. DATA bus failure. Attitude data are valid DEGRD

The INS is in navigate mode and a degraded performance alinement, not a full performance alinement, was performed

6

UPDT

The INS is being updated by an external device, such as the TACAN RT

6

DEGUPD

Degraded navigation mode updated by TACAN RT

6

NOTE

Messages MSC, NPU, INU, ADC, TCN, and SDC will alternate on and off at approximately 2 Hz rate when a failure occurs to attract the operator’s attention. Pressing the fault acknowledge (FACK) key will cause these annunciations to go from flashing to steady. If a line replaceable unit (LRU) recovers from failure its annunciation will be removed from the screen.

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TM 11-5826-302-12

Section Il. OPERATOR PREVENTIVE MAINTENANCE CHECKS AND SERVICES (PMCS) 2-3 GENERAL. 2-3.1 There are no operator PMCS procedures. Refer to aircraft technical manual TM 55-1520-237-10CL for aircraft preoperational procedures. Section III. OPERATION UNDER USUAL CONDITIONS

During operation no combination of  CDU control settings will cause damage to the equipment or create a hazard to personnel, however, if the aircraft INS power circuit breakers were disengaged within 10 seconds after setting the CDU to OFF mode, equipment damage will occur. 2-4 ASSEMBLY AND PREPARATION FOR USE.

2-4.1 There is no assembly of the IINS at the operator level, The equipment is installed in the aircraft by aviation unit level maintenance personnel. There is no special switch settings required before the equipment is put into operation. 2-5 INITIAL ADJUSTMENTS AND SELF TEST. 2-5.1 Initial Adjustments. There are no initial adjustments for the IINS. 2-5.2 Self Test. Self test procedures are performed by aviation unit level personnel. 2-6 OPERATING PROCEDURE. 2-6.1 The operating procedure for the IINS consists of  a description of each type of data that can be entered from the CDU into the system, typical data entry, preoperational, inflight, and shutdown procedures. 2-6.2 Data Entry Description. The following paragraphs describe each type of data that can be entered into the IINS. 2-6.2.1 Alphanumeric Entry. Alphanumeric entries are made by pressing one of the ten character keys on the keyboard. The character first appears on the data display scratch pad (line 8). Actuation of a key causes a character to be displayed from left to right on the

2-42

scratch pad. The numbered and decimal keys enter the respective number or decimal point unless the keyboard is in the letter mode. When the LTR/USE key is pressed, LTR will be indicated on the right side of the scratch pad, and the next key pressed will enter an alpha character. In the UTM mode, pressing keys with alpha characters above them will put the first alpha character associated with that key on the scratch pad. Successive actuations of the key will cause the second and third characters to appear. When the desired character is displayed, pressing the LTR/USE key a second time signals the CDU to use that character. When the CDU is signaled to use the character displayed, it automatically reverts back to the numeric mode, In the case where successive alpha characters appear, the LTR/USE key must be pressed twice to use the character previously entered, and enter the alpha mode for the next character. When the position, destination, and TACAN pages are displayed and latitude/longitude format is selected, actuation of ABC/N2, GHJ/W4, NPQ/E6, and UVW/S8 keys will enter N, W, E, and S respectively. These are the only letters that can be entered in this mode. In all other circumstances when in the alpha mode, the alphas above the key pressed will appear. Once the desired data appears on the scratch pad, it is entered by pressing the line select key adjacent to the data being updated. When the line select key is pressed, the scratch pad contents will be checked for proper range and format. If the entry is valid, it will be transferred to the IINS, read back, and displayed adjacent to the line select key. Completion of this cycle clears the scratch pad. 2-6.2.2 Error Checking. Several checks are performed on entered data bef ore it appears on the line and the scratch pad is cleared. Failure to pass these checks will cause one of three of the following messages to be displayed alternately with the unused entry in the scratch pad: ENTRY ERROR - indicates that the entered data has not passed range and format checks performed by the CDU (e.g., course of 3700).

TM 11-5826-302-12

2-43

TM 11-5826-302-12

ILLEGAL ENTRY - indicates that the entered data is inconsistent with IINS operation (e.g., entry of true heading in navigation mode).

1

Clark 1866

CL6

2

Clark 1880

CL0

3

Everest

EVR

ENTRY IGNORED – IINS has neither accepted nor rejected entered data. Entry status is undetermined.

4

Bessel

BSL

5

Australian National

AUS

6

Airy

ARY

7

Hough

HGH

8

South American

SAM

9

Modified Everest

MEV

10

WGS-72

WGS

2-6.2.3 Magnetic Heading or True Heading Entry. Magnetic heading or true heading may be entered during the first 60 seconds of a best available true heading (BATH) alinement. Scratch pad entries may be up to four numeric digits including an optional decimal point. If no decimal point is entered, whole degrees are assumed. Leading zeros are optional. 2-6.2.4 Present Position Entry. Present position may he entered only during the first 2 minutes of normal alinement, or first 2 minutes of a BATH alinement after magnetic or true heading has been entered. Arrows adjacent to present position coordinates cue the operator when entry is permitted. Either latitude/longitude or universal transverse mercator (UTM) coordinates may be entered. Coordinate selection is provided on data display line 7 right. 2-6,2.4.1 Latitude Entry. Scratch pad entries may be 2, 3, 4, 5, or 6 numeric digits preceded by an optional N or S. The first two digits are degrees, the third and fourth are minutes, and the fifth and sixth are seconds. If any digits are not entered, zeroes will be assumed. If  the N or S is not entered, the previously displayed value will be assumed. If the entered latitude is less than 10°, a leading zero must be entered. If a leading zero is not entered, an error message will flash. 2-6.2.4.2 Longitude Entry. Scratch pad entries may be 3, 4, 5, 6, or 7 numeric digits preceded by an optional E or W. The first three digits are degrees, the fourth and fifth are minutes, and the sixth and seventh are seconds. If any digits are not entered, zeroes will be assumed. If  the E or W is not entered, the previously displayed value will be assumed. If the entered longitude is less than 100°, a leading zero (two leading zeros if less than 10°) must be entered. If a leading two zeros are not entered, an error message will flash. 2-6.2.4.3 Spheroid and Grid Zone Entry. Scratch pad entries may be made for spheroid and grid zone, just spheroid or just grid zone. Spheroids are numeric entry and alpha indication according to the following codes for spheroid models:

Code 0

2-44

Spheroid Model

International

Abbreviation

INT

Grid zone entries consist of one or two numbers and an alpha character. Spheroid entries consist of code numbers 0 thru 10. 2-6.2.4.4 Area/Eastings/Northings Entry. Scratch pad entries may be made for area and eastings/northings,  just area, or just eastings/northings. Entries for area must consist of two alpha characters. Entries for eastings/northings must be 2, 4, 6, 8 or 10 digits. Any data not entered, the system will presume all previous entries are valid. Digits will be evenly split between castings and northings with trailing zeros inserted. Although entries may be made and sent to the INS to a resolution of 2 meters, the display will round to the nearest 10 meters. 2-6.2.5 Magnetic Variation Entry. Scratch pad entries consist of an E or w and up to four numeric digits including decimal point. If no-decimal point is entered, O whole degrees are assumed. The range of entries is O.O to E 179.9° or W 180.0°. 2-6.2.6 Manually Entered Field Altitude. Field altitude must be entered to the nearest 100 feet (mean sea level) during alinement. The range of valid entries is from -1000 to +65,520 feet in increments of 100 feet. 2-6.2.7 Barometric Pressure Entry, Barometric pressure must be entered to the nearest 0.01 inches Hg during alinement. 2-6.2.8 Destination Coordinate Entry. Destination coordinates may be entered during any phase of the mission. Either latitude/longitude or UTM coordinates may be entered. The operator can enter up to 16 destinations. These destinations can be used for steerpoints or overfly fixes. When a destination is selected as a steerpoint, steering information (range, bearing, time to go, course deviation) is computed for the CDU and aircraft instruments. An overfly fix requires that the flyover point be entered as a destination. When a mark  is performed the stored coordinates in destinations A

TM 11-5826-302-12

thru F are replaced with markpoint position data. The mark locations are used in sequence (A, B, C, D, E, F, A, B, etc.). Entry of destination coordinates is identical to entry of present position coordinates as described in paragraph 2-6.2.4, 2-6.2.9 Course to Destination Entry. The desired true course to destination may be entered for each destination during any phase of the mission. Scratch pad entry requirements are the same as for magnetic or true heading as described in paragraph 2-6.2.3, Up to four numeric digits may be entered with an optional decimal point. If no decimal point is entered, whole degrees are assumed. 2-6.2.10 TACAN Station Magnetic Variation Entry. TACAN station magnetic variation can be entered during any phase of the mission and entry is the same as magnetic variation entry described in paragraph 2-6.2.5. 2-6.2.11 TACAN Station Position Entry. TACAN station position entry can be made during any phase of the mission. Station position entry is performed the same as present position coordinates as described in  paragraph 2-6.2.4. Either latitude/longitude or UTM coordinates may be entered. 2-6.2.12 TACAN Station Channel Entry. TACAN station channel entry can be made during any phase of the mission. The TACAN station pages provide the capability to enter station channel for each of the 16 stations. A total of 252 channels are possible (126 X channels and 126 Y channels). Unless otherwise specified, it is assumed an X channel has been entered.

placed in the navigation mode of operation and the aircraft can be moved, Entry of destination and TACAN data can be performed during alinement, after alinement, or during any phase of the mission if desired. Refer to paragraphs 2-6.2.8 thru 2-6.2.12 for a description of destination and TACAN data that can be entered. 2-6.4.1 NPU Loading Procedure. Refer to technical manual TM 11-6625-3099-13 for the NPU loading procedure. NOTE

TACAN and destination data (except desired course) will be retained in memory from turnon to turnon unless zeroized. 2-6.4.2 Alinement Procedures. Alinement procedures are performed on the ground when the IINS is first turned on. The alinement procedures consist of a normal or fast alinement. Fast alinement consists of two types of stored alinements and a best available true heading (BATH) alinement. A stored alinement (providing limited degraded system accuracies) can be performed if the aircraft has not been moved since last normal alinement (and the mode switch not set to NAV) and turnoff. A second stored alinement (providing degraded systems accuracies as indicated in table 1-1) can be performed if the aircraft has not been moved since the last normal alinement (and the mode switch set to NAV) and turnoff. BATH alinement is performed if the aircraft has been moved since last normal alinement and turnoff.

2-6.3 Typical Data Entry. Data entry onto the CDU scratch pad and into the system is basically the same for all data that can be entered. For any particular data that is required to be entered, the correct CDU data display page must be selected, the mode select switch must be in the applicable position, and the correct keyboard and line select keys pressed.

2-6.4.3 Destination/Steering Data Entry Procedure. Destination/steering data entry procedures can be performed during alinement, after alinement, or during any phase of the mission. The following procedure is performed after alinement with the system in the NAV mode.

2-6.4 Preoperational Procedures. The preoperational procedures consist of NPU loading, alinement, destination/steering data entry, and TACAN data entry procedures. The NPU loading and alinement procedures must be performed on the ground before the IINS can be

2-6.4.4 TACAN Data Entry Procedure, TACAN data entry procedures can be performed during alinement, after alinement, or during any phase of the mission. The following procedure is performed after alinement with the system in the NAV mode.

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TM 11-5826-302-12

NORMAL ALINEMENT

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TM 11-5826-302-12

NORMAL ALINEMENT NOTE

CDU display will remain blank for 30 seconds after turnon. Present position must be entered within 2 minutes of turnon. Barometric pressure and altitude must be entered during alinement. During alinement, data display line 6 left (6) may have a steady indication of  NAVRDY. Alinement will be complete when NAVRDY begins to flash. 1.

Ensure that aircraft power is applied to the system. NOTE

Prior to entering present position latitude/longitude, ensure that the correct spheroid identifier for your area has been entered in the system. 2.

Set mode select switch (28) to NORM,

3.

Set page select switch (30) to POS.

4. Observe that data display line 7 right (7) displays L/L T. If data display line 7 right (7) displays UTM press adjacent line select key (12). 5. If data display line 8 right (8) does not display LTR, press LTR/USE key (26) to place the keyboard in the alpha mode. NOTE

Present position data must be entered for each normal alinement. The following steps are examples of entering present position data. Substitute your own present position data when performing these steps. When making keyboard entries, if an incorrect key is pressed, press CLR key (22), as required, and begin again. 6. Enter present position latitude on data display line 8 (8) by pressing in sequence ABC/N2 (14), LTR/USE (26), DEF/3 (15), GHJ/W4 (18), 1 (13),0 (24), DEF/3 (15), and 0 (24) keys. Observe that data display line 8 (8) displays N341030. 7. Press data display line 5 left (5) line select key (36). Observe that data display line 5 left (5) displays N34°10 30. 8. Enter present position longitude on data display line 8 (8) by pressing in sequence LTR/USE (26), GHJ/W4 (18), LTR/USE (26), 1 (13) twice, UVW/S8 (20), DEF/3 (15), KLM/5 (16), DEF/3 (15), and 0 (24) keys. Observe that data display line 8 (8) displays W 1183530.

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TM 11-5826-302-12

9. Press data display line 7 left (7) line select key (35). Observe that data display line 7 left (7) displays W118°35 30. 10. Set page select switch (30) to INS. NOTE

When entering position altitude, altitude must entered to the nearest 100 feet (mean sea level). The range of valid entries is from -1000 to +65,520 feet in increments of 100 feet. Entries are made in thousands of feet. 11. Enter present position altitude on data display line 8 (8) by pressing in sequence UVW/S8(20), -/. (25), and NPQ/E6(17) keys. Observe that data display line 8 (8) displays 8.6. This represents an altitude of 8,600 feet.

12. Press data display line 3 left (3) line select key (37). Observe that data display line 3 left (3) displays -AALT 8.6. NOTE

Enter local barometric pressure to the nearest 0.01 inches Hg. 13. Enter local barometric pressure on data display line 8 (8) by pressing in sequence ABC/N2 (14), XYZ/9 (19), -/. (25), O (24), and 1 (13) keys. Observe that data display line 8 (8) displays 29.01. 14. Press data display line 5 left (5) line select key (36). Observe that data display line 5 left (5) displays -BARO 29.01. 15. Observe that data display line 7 (7) displays alinement time and status. NOTE

Do not set mode select switch (28) to NAV position and move the aircraft if a stored alinement (with limited degraded accuracies) is to be performed following the normal alinement. 16. When data display line 6 left (6) displays a flashing NAVRDY, set mode select switch (28) to NAV.

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STORED ALINEMENT

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STORED ALINEMENT NOTE

CDU display will remain blank for 30 seconds after turnon. Barometric pressure must be entered during alinement. Alinement will be complete when data display line 6 (6) displays a flashing NAVRDY if a normal alinement was performed and the mode select switch was not set to

NAV. L Ensure that aircraft power is applied to the system. 2. Set mode select switch (28) to FAST. 3. Set page select switch (30) to POS. 4. Observe that data display line 7 right (7) displays L/L adjacent line select key (12).

If data display line 7 right (7) displays UTM press

5. If data display line 8 right (8) displays LTR press LTR/USE key (26) to place the keyboard in the numeric mode. 6. Observe that data display line 5 left (5) and line 7 left (7) display present position latitude and longitude, respectively. If not, a normal or BATH alinement must be performed. 7. Set page select switch (30) to INS. Observe that data display line 3 left (3) displays present position altitude. If not, a change must be made within the first 60 seconds of this alinement. NOTE

The following steps are an example of entering barometric pressure. Substitute your own barometric pressure when performing these steps. Enter local barometric pressure to the nearest 0,01 inches Hg. When making keyboard entries, if an incorrect key is pressed press CLR key (22) as required, and begin again. 8. Enter local barometric pressure on data display line 8 (8) by pressing in sequence ABC/N2 (14), XYZ/9 (19), -/. (25), 0 (24), and 1 (13) keys. Observe that data display line 8 (8) displays 29.01. 9. Press data display line 5 left (5) line select key (36). Observe that data display line 5 left (5) displays -BARO 29.01. 10. Observe that data display line 7 (7) displays alinement time and status. Data display line 6 left (6) displays a flashing NAVRDY if a normal alinement was performed and the mode select switch was not set to NAV. 11. When data display line 6 left (6) displays NAVRDY, set mode select switch (28) to NAV.

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BATH ALINEMENT

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BATH ALINEMENT NOTE

CDU display will remain blank for 30 seconds after turnon. True or magnetic heading must be entered during the first 60 seconds of turnon. Present position must be entered within 2 minutes of turnon. Barometric pressure and altitude must be entered during alinement. Alinement will be complete when data display line 6 (6) displays NAVRDY.

1. Ensure that aircraft power is applied to the system. 2. Set mode select switch (28) to FAST. 3. Set page select switch (30) to POS.

4. Observe that data display line 7 right (7) displays L/L adjacent line select key (12).

If data display line 7 right (7) displays UTM

, press

5. If data display line 8 right (8) displays LTR press LTR/USE key (26) to place the keyboard in the numeric mode. NOTE

The following steps are examples of entering present position data. Substitute your own present position and heading data when performing these steps. Either true heading or magnetic heading can be entered. Magnetic heading is entered by pressing line select key (10). The following example uses true heading. When making keyboard entries, if an incorrect key is pressed, press CLR key (22) as required, and begin again. 6. Enter true heading on data display line 8 (8) by pressing in sequence DEF/3 (15), KLM/5 (16), UVW/S8 (20), -/. (25), and DEF/3 (15) keys. Observe that data display line 8 (8) displays 358.3. 7. Press data display line 1 right (1) line select key (9). Observe that data display line 1 right (1) displays TH = 358.3. 8. If required, enter present position latitude on data display line 8 (8) by pressing in sequence LTR/USE (26), ABC/N2(14), LTR/USE (26), DEF/3 (15), CHJ/W4 (18), 1 (13), 0 (24), DEF/3 (15), and O (24) keys. Observe that data display line 8 (8) displays N341030. 9. Press data display line 5 left (5) line select key (36). Observe that data display line 5 left (5) displays N34°10 30. 10. If required, enter present position longitude on data display line 8 (8) by pressing in sequence LTR/USE (26), GHJ/W4 (18), LTR/USE (26), 1 (13) twice, UVW/S8 (20), DEF/3 (15), KLM/5 (16), DEF/3 (15), and O (24) keys. Observe that data display line 8 (8) indicates W1183530.

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11. Press data display line 7 left (7) line select key (35). Observe that data display line 7 left (7) displays W118°35 30. 12, Set page select switch (30) to INS. NOTE

When entering present position altitude, altitude must be entered to the nearest 100 feet (mean sea level). The range of valid entries is from -1000 to +65,520 feet in increments of 100 feet. Entries are made in thousands of feet. 13. If required, enter present position altitude on data display line 8 (8) by pressing in sequence UVW/S8 (20), -/.(25), and NPQ/E6 (17) keys. Observe that data display line 8 (8) displays 8.6. This represents an altitude of 8,600 feet. 14. Press data display line 3 left (3) line select key (37). Observe that data display line 3 left (3) displays -AALT 8.6. NOTE

Enter local barometric pressure to the nearest 0.01 inches Hg. 15. Enter local barometric pressure on data display line 8 (8) by pressing in sequence ABC/N2 (14), XYZ/9 (19), - /. (25), 0 (24), and 1 (13) keys. Observe that data display line 8 (8) displays 29.01. 16. Press data display line 5 left (5) line select key (36). Observe that data display line 5 left (5) displays -BARO 29.01. 17. Observe that data display line 7 (7) displays alinement time and status, 18. When data display line 6 left (6) displays NAVRDY, set mode select switch (28) to NAV.

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DESTINATION/STEERING DATA ENTRY

1. Ensure that system has been alined and mode select switch (28) is set to NAV. 2. Set page select switch (30) to DEST. 3. Press DEST switch (29) up or down as required to display D1 on data display line 1 left (l). 4. If data display line 8 right (8) does not display LTR, press LTR/USE key (26) to place the keyboard in the alpha mode. NOTE

When making keyboard entries, if an incorrect key is pressed, press CLR key (22), as required, and begin again. 5: Enter destination latitude on data display line 8 (8) by pressing in sequence ABC/N2 (14), LTR/USE (26), DEF/3 (15), KLM/5 (16), GHJ/W4 (18) and KLM/5 (16) three times, keys. Observe that data display line 8 (8) displays N354555. 6. Press data display line 5 left (5) line select key (36). Observe that data display line 5 left (5) displays -N35°45 55, 7. Enter destination longitude on data display line 8 (8) by pressing in sequence LTR/USE (26), GHJ/ W4(18), LTR/USE (26), 1 (13) twice, XYZ/9(19), KLM/5 (16), DEF/3 (15), 1 (13), and RST/7 (21) keys. Observe that data display line 8 (8) displays W 1195317. 8. Press data display line 7 left (7) line select key (35). Observe that data display line 7 left (7) displays -W119°53 17. 9. Enter desired course to destination 1 on data display line 8 (8) by pressing in sequence 1 (13), ABC/N2 (14), DEF/3 (15), -/. (25), and GHJ/ W4 (18) keys. Observe that data display line 8 (8) displays 123,4. 10. Press data display line 1 right (1) line select key (9). Observe that data display line 1 right (1) displays 123.4

11. Observe that data display line 7 right (7) displays UTM adjacent line select key (12). Observe that data display changes to grid format, 12. Enter zone on data display line 8 (8) by pressing in sequence 1 (13), UVW/S8 (20), LTR/USE (26), RST/7 (21) three times, and LTR/USE 26 keys. Observe that data display line 8 (8) displays 18T.

NOTE Refer to paragraph 2-6.2.4.3 for spheroid code numbers. 13. Enter Clark 1866 spheroid on data display line 8 (8) by pressing 1 key (13). Observe that data display line 8 (8) displays 18T1. 14, Press data display line 5 left (5) line select key (36). Observe that data display line 5 left (5) displays - 18T CL6.

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15. If data display line 8 right (8) does not display LTR press LTR/USE key (26) to place the keyboard in the alpha mode, 16. Enter area on data display line 8 (8) by pressing in sequence UVW/S8 (20), LTR/USE (26) twice, UVW/S8 (20) twice, and LTR/USE (26) keys. Observe that data display line 8 (8) displays UV. 17. Enter castings and northings on data display line 8 (8) by pressing in sequence ABC/N2 (14), DEF/3 (15), CHJ/W4 (18), KLM/5 (16), NPQ/E6 (17), RST/7 (21), UVW/S8 (20), and XYZ/9 (19) keys. Observe that data display line 8 (8) displays UV23456789. 18. Press data display line 7 left (7) line select key (35). Observe that data display line 7 left (7) displays -UV 23456780. 19. Set mode select switch (28) to OFF.

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TACAN DATA ENTRY

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TACAN DATA ENTRY 1, Ensure that system has been alined and mode select switch (28) is set to NAV. 2. Set page select switch (30) to TCN. 3. Press data display line 1 left (1) line select key (38), Observe that data display line 1 left (1) displays TACAN ON. 4. Observe that data display line 3 left (3) displays T/R. If it does not, press data display line 3 left (3) line select key (37). NOTE

Allow 90 seconds for TACAN warmup, X in the following steps represents some number. 5. Observe that data display line 5 left (5) displays NORM X of X. If it does not, press data display line 5 left (5) line select key (36). 6. Observe that data display line 7 left (7) displays number of failed stations 3SIG = X. 7. Press page slew switch (34) up or down as required to display STATION 1 on data display line 1 left (1). 8. Observe that data display line 7 right (7) displays L/L. If data display line 7 right (7) displays UTM , press adjacent line select key (12). NOTE

When making keyboard entries, if an incorrect key is pressed, press CLR key (22) as required, and begin again. 9. Enter station magnetic variation on data display line 8 (8) by pressing in sequence LTR/USE (26), CHJ/W4 (18), LTR/USE (26), RST/7 (21), XYZ/9 (19), -/. (25), and XYZ/9 (19) keys. Observe that data display line 8 (8) displays W79.9. 10. Press data display line 3 left (3) line select key (37). Observe that data display line 3 left (3) displays -MV W79.9. 11. If data display line 8 right (8) does not display LTR, press LTR/USE key (26) to place the keyboard in the alpha mode. 12. Enter station latitude on data display line 8 (8) by pressing in sequence ABC/N2 (14), LTR/USE (26), DEF/  3 (15) twice, 1 (13), 0 (24), DEF/3 (15), and 0 (24) keys. Observe that data display line 8 (8) displays N331030. 13. Press data display line 5 left (5) line select key (36). Observe that data display line 5 left (5) displays -N33°10 30.

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14. Enter station longitude on data display line 8 (8) by pressing in sequence LTR/USE (26), GHJ/W4 (18), LTR/USE (26), 1 (13) twice, UVW/S8 (20), DEF/3 (15), KLM/5 (16), DEF/3 (15), and 0 (24) keys. Observe that data display line 8 (8) displays W1183530. 15. Press data display line 7 left (7) line select key (35). Observe that data display line 7 left (7) displays -Wl18°35 30. 16. Observe that data display line 1 right (1) indicates ACT. If it does not, press data display line 1 right (1) line select key (9). 17. Enter station channel number on data display line 8 (8) by pressing in sequence 1 (13) and 0 (24) keys. Observe that data display line 8 (8) displays 10. 18. Press data display line 3 right (3) line select key (10). Observe that data display line 3 right (3) displays CH 10X. 19. Enter station elevation on data display line 8 (8) by pressing 0 (24) key. Observe that data display line 8 (8) displays O. 20. Press data display line 5 right (5) line select key (11). Observe that data display line 5 right (5) displays EL 0.00. 21. Press data display line 7 right (7) line select key (12). Observe that entered station latitude and longitude coordinates change to UTM coordinates. 22. Press data display line 1 left (1) line select key (38). Observe that data display line 1 left (1) displays TACAN OFF. 23, Set mode select switch (28) to OFF.

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2-6.5 Inflight Procedures. Inflight procedures consists of selecting various data diplay pages for viewing navigation data, entering destination and TACAN data selecting steerpoints, selecting the update mode, mark  opertion, and manual (overfly) position updating. The

following procedures explain mark opertion, manual (overfly) position updating, and selecting steerpoints. Refer to paragraphs 2-6.2.8 thru 2-6.2.12 for a description of destination and TACAN data that can be entered.

MARK OPERATION NOTE

Current aircraft position may be stored in one of the markpoint locations (destinations A thru F) by pressing the MRK key. The mark indication will appear in line 8 on any page selected. The following procedure uses the steer page, The mark  locations are used in sequence (A, B, C, D, E, F, A, B, etc.). 1. Set page select switch (30) to STR. Observe that the steer page is displayed. 2. Press MRK key (33), to store the desired markpoint in memory. The location in memory where this latest mark is stored is displayed in the scratch pad; such as MARK A.

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MARK OPERATION

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MANUAL (OVERFLY) POSITION UPDATING

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MANUAL (OVERFLY) POSITION UPDATING NOTE

An overfy update represents a manual position update technique which the pilot overflies his selected destination and signals the INS by pressing the MRK key, and subsequently the ACCEPT or REJECT line select key. 1. Set mode select switch (28) to UPDT. Observe that the update page is displayed. 2. At time of overfly press MRK key (33). Obseeve that data display line 7 left (7) displays display line 7 right (7) displays REJECT 3. If the update data is acceptable, press line select key (35) that is adjacent to data display displayed on line 7 left (7). Observe that data display returns to update page. 4. If the update data is unacceptable, press line select key (12) that is adjacent to data display REJECTdisplayed on line 7 right (7). Observe that data display returns to update page. 5. After update is performed, return mode select switch (28) to NAV.

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SELECTING STEERPOINTS

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SELECTING STEERPOINTS NOTE

The operator can enter up to 16 destinations. These destinations can be used for steerpoints during an phase of the mission. When a destination is selected as a steering information range, bearing, time to go, course deviation) is computed for the CDU and aircraft instruments. If a mark(s) has been performed during the mission, the stored coordinates in destinations A thru F have been replaced with markpoint position data. 1. Set page select switch (30) to STR. Observe that the steer page is displayed. 2. Press STR switch (32) up or down as required to display selected steerpoint on data display line 1 left (l).

The INS circuit breakers must not be disengaged for at least 10 seconds after selecting the OFF mode. 2-6.6 Shutdown Procedure. Shutting down the IINS consists of setting the CDU mode select switch to OFF. 2-7 OPERATION OF AUXILIARY EQUIPMENT. 2-7.1 There is no auxiliary equipment supplied with the IINS. For operation of interfacing avionics equipment, refer to the applicable manual. Section IV. OPERATION UNDER UNUSUAL CONDITIONS 2-8 OPERATION IN UNUSUAL WEATHER. 2-8.1 The IINS can operate in any weather that the aircraft is capable of flying in. 2-9 EMERGENCY PROCEDURES, 2-9.1 In the event of loss of any subsystem, the IINS will provide backup mode capability to the maximum feasible extent. If there is an NPU failure, the CDU assumes the data bus control functions, and IINS navigational performance will be as specified for free inertial performance. If an INS failure should occur, TACAN-derived position will be available if the NPU and

interface functions remain operational. The degraded modes of performance are listed in table 2-2. 2-1O JAMMING AND ECM PROCEDURES. 2-10.1 The only piece of equipment subject to jamming or electronic countermeasures (ECM) would be the TACAN. If the TACAN signal is interfered with, the TACAN can be shut down and the system can provide inertial navigation without the aid of the TACAN, however, updating can be accomplished manually.

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2   -  7    0  

T  M

1  1  -   5   8  2   6  -   3   0  2  -  1  2 

2  -  7  1   /   2  -  7  2   b  l    a  n k   )  

T  M

1  1  -   5   8  2   6  -   3   0  2  -  1  2 

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CHAPTER 3 OPERATOR MAINTENANCE There are no operator maintenance procedures. Refer to aircraft technical manual TM 55-1520-237-10CL for aircraft preoperational procedures.

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CHAPTER 4 AVIATION UNIT MAINTENANCE

Section 1. LUBRICATION INSTRUCTIONS 4-1 GENERAL.

4-1.1 There are no lubrication instructions for the IINS.

Section Il. IINS

UPON RECEIPT

4-2 SERVICE UPON RECEIPT OF MATERIEL.

4-5 DEPROCESSING UNPACKED EQUIPMENT.

4-2.1 This section contains instructions to unpack, inspect, and deprocess the IINS. IINS service upon receipt inspection data are summarized in table 4-1.

4-5.1 Reprocessing of unpacked IINS units is performed by AVIM personnel.

4-3 UNPACKING INSTRUCTIONS.

4-3.1 The IINS is not packaged in a single container. IINS units are packaged separately and unpacked by Aviation Intermediate Maintenance (AVIM) personnel.

4-6 TOOLS, TEST EQUIPMENT, AND MATERIALS REQUIRED FOR INSTALLATION.

4-6.1 No special tools, special test equipment, or materials are required to install the INS, NPU, CDU, SDC, or the TACAN RT. The CDU is installed with a 9/32 in. flat-tip screwdriver. 4-7 INSTALLATION OF INS, NPU, AND TACAN

4-4 CHECKING UNPACKED EQUIPMENT.

4-4.1 IINS units are inspected for damage incurred during shipment, checked for complete shipment, and equipment modifications by AVIM personnel. Equipment checking by Aviation Unit Maintenance (AVUM) personnel consists of performing the actions listed in table 4-1.

MOUNTS. 4-7.1 Refer to aircraft technical manual TM 11-1520237-23 for installation of the INS, NPU, and TACAN mounts. 4-8 INSTALLATION OF INS.

4-8.1 Perform INS installation as follows:

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Table 4-1. IINS Service Upon Receipt Inspection Data Remarks

Action

Location

Item

1 INS and INS mount, NPU and NPU mount, CDU, SDC, and TACAN RT and TACAN mount

Control surfaces and covers

a. Inspect for dents and scratches

2. I N S , N P U , C D U , SIX, and TACAN RT

Controls and indicators

a. Inspect for broken, bent, or scratched parts

4

b. Reject control surfaces and covers if damage prevents them from functioning properly

Process to Aviation Intermediate Maintenance (AVIM) —

Process to AVIM

b. Reject control or indicator (1)

—

..

If damage prevents them from functioning properly

(2) If control cannot be rotated through its complete range without any binding or scraping

(3) If toggle and pushbutton switches cannot operate smoothly (4) If glass surfaced indicators cannot be cleaned properly

NPU, CDU, 3. INS, SDC, and TACAN RT and TACAN mount

Connector

4. INS and INS mount, NPU and NPU mount, CDU, SDC, and TACAN RT and TACAN mount

Mounting hardware

5. NPU, CDU, and TACAN mount

Lamps and fuses

a. Inspect for bent, burned or broken pins b. Reject connectors

Knobs

---

b. Reject mounting hardware if  damage prevents it from functioning properly

Process to AVIM

a. Inspect for broken or burned parts

a. Inspect for broken parts b. Reject knobs

4-2

Process to AVIM

a. Inspect for bent or broken parts

b. Reject lamps or fuses

6. CDU

—

Refer to section V for replacement -. Refer to section V for replacement

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INS INSTALLATION

Ensure that aircraft power is removed from the INS mount before installing INS.

When handling the INS, use extreme care to prevent damage to precision electronic equipment, When handling the INS, do not lift or carry by the latch assembly. 1. Refer to aircraft technical manual TM 11-1520-23723 for procedures to gain access to the INS mount.

3. Check that mount gasket is in proper position and is not deformed or damaged.

2. Ensure that INS mount is installed in accordance with paragraph 4-7.

4. Remove plastic protective dust covers from INS

5. Press two latch releases (1) to release latch assembly (2).

connectors.

6. Place latch assembly (2) in open position. Hold the INS (3) by the latch assembly and support it from the bottom. Place INS on mount (4) and slide inward engaging guide pins and the connectors.

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7. When INS is seated in mount, raise latch assembly (2) until latch lock (5) clicks to indicate latch assembly has engaged keeper assembly (6) and is in lock  position. Verify the latch assembly has latched by pulling forward on latch assembly.

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4-9 INSTALLATION OF NPU.

4-9.1 Perform NPU installation as follows:

NPU INSTALLATION

Ensure that aircraft power is removed from the NPU interconnecting cables before installing NPU. Refer to aircraft technical manual TM 11-1520-237-23 for NPU power removal procedure. The NPU weighs approximately 90 pounds. Use at least two persons to lift and move it,

When handling the NPU, use extreme care to prevent damage to precision electronic equipment. 1. Refer to aircraft technical manual TM 11-1520-23723 for procedures to gain access to the NPU mount.

3. Remove plastic protective dust covers from NPU connectors.

2. Ensure that NPU mount is installed in accordance with paragraph 4-7.

4. Place NPU (1) on mount (2) and slide inward engaging the guide pins.

5. Position two self-locking holddown retainers (3) on two mounting hooks (4) and tighten self-locking holddown retainers securing NPU to mount.

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6. For NPU interconnecting cable information refer to aircraft technical manual TM 11-1520-237-23. Connect aircraft cables to connectors (5, typical) of NPU (l). 7. Ensure that console lock (6) is connected to connector J11.

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4-10 INSTALLATION OF CDU.

4-10.1 Perform CDU installation as follows:

CDU INSTALLATION

Ensure that aircraft power is removed from the CDU interconnecting cables before installing CDU.

When handling the CDU, use extreme care to prevent damage to precision electronic equipment. 1. Remove plastic protective dust covers from CDU connectors.

3. Carefully push CDU (3) into aircraft panel (4).

2. For CDU interconnecting cable information, refer to aircraft technical manual TM 11-1520-237-23. Connect aircraft cable connectors (1 and 2) to CDU (3).

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4. Using screwdriver, tighten eight captive screws (5) securing CDU (3) to aircraft panel (4).

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4-11 INSTALLATION OF SIX. 4-11.1 Perform SDC installation as follows:

SDC INSTALLATION

Ensure that aircraft power is removed from the TACAN mount and SIX interconnecting cables before installing SIX.

When handling the SIX, use extreme care to prevent damage to precision electronic equipment. L Ensure that TACAN mount is installed in accordance with  paragraph 4-7.

3. Place SDC (1) on TACAN mount (2) and slide inward engaging the connector.

2. Remove plastic protective dust covers from SDC connectors.

4. Position self-locking holdown retainer (3) on mounting hook (4) and tighten self-locking holddown retainer securing SDC to mount.

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5. For SDC interconnecting cable information refer to aircraft technical manual TM 11-1520-237-23. Connect aircraft cables to connectors (5, 6, and 7) of  SDC (1).

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4-12 INSTALLATION OF TACAN RT.

4-12.1 Perform TACAN RT installation as follows:

TACAN RT INSTALLATION

Ensure that aircraft power is removed from the TACAN mount and TACAN RT interconnecting cables before installing TACAN RT.

When handling the TACAN RT, use extreme care to prevent damage to precision electronic equipment. 1. Ensure that TACAN mount is installed in accordance with paragraph 4-7.

3. Place TACAN RT (1) on TACAN mount (2) and slide. inward engaging the guide pins. Ensure that bracket (3) has been lifted to the up position and held in place with two knurled screws (4).

2. Remove plastic protective dust covers from TACAN RT connectors.

4. Position two self-locking holddown retainers (5) on two mounting hooks (6) and tighten self-locking holddown retainers securing TACAN RT to mount.

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4-13 INTERCONNECTIONS.

4-13.1 The IINS units are interconnected to aircraft avionics by aircraft cabling. Refer to aircraft technical manual TM 11-1520-237-23 for cabling diagrams. 4-14 PRELIMINARY SERVICING AND ADJUSTMENT OF EQUIPMENT.

4-14.1 No prelimimary servicing or adjustment of the equipment is required at the organizational level, however when replacing an INS, ensure that unit is in current calibration.

5. For TACAN RT interconnecting cable information, refer to aircraft technical manual TM 11-1520-23723. Connect aircraft cables to connectors (7, 8, and 9) of TACAN RT (l). 6. Position bracket (3) over TACAN RT (1) handle and secure with two knurled screws (4).

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Section Ill. AVIATION UNIT PREVENTIVE MAINTENANCE CHECKS AND SERVICES (PMCS) 4-15 PMCS PROCEDURES.

4-15.1 The PMCS procedures are contained in table 4-2. Progressive phase maintenance concepts permit maintenance intervals to be determined by the maintenance office.

Table 4-2.  Aviation Unit Preventive Maintenance Checks and Services Item

Item To Be Procedures

No. 1

Fault indicators

Check for fault indicator being set (all white)

2

Airflow

Check that airflow is not blocked to rack mounted units

3

Surfaces and covers

Check for scratches and dents. Cheek that covers are secure

4

Mounting surfaces

Check that mounting surfaces on mounts do not have dents or scratches

5

Mount guide pins

Check that mount guide pins are not bent

6 

Controls and indicators

Check for broken, bent, or scratched parts

7 

Connectors

Check for bent, burned, or broken pins

8 

Mounting hardware

Check for bent or broken parts

9

Lamp and fuse covers

Check for broken or missing parts

10

Lamps and fuses

Check for broken or missing parts

11

Knobs

Check for broken cracked parts

12

Panel nomenclature

Check for illegible or obliterated markings

13

CDU CRT surface

Check for excessive accumulation of dirt

14

Equipment in general

Check for excessive accumulation of dirt and debris

or

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Section IV. IINS TROUBLESHOOTING PROCEDURES 4-16 GENERAL.

4-16.1 Organizational troubleshooting of the IINS consists of performing the INS/NPU, CDU, and TACAN RT/SDC self test procedures in the sequence given. Whenever a corrective action is required, refer to section V and replace the defective unit then rerun the required self test procedure to verify the repair. If  the CDU indicates a PFM system status message on line 2, regardless of selected page (except NPU data page),

at any time during the mission, a bus failure has occurred, refer to aircraft technical manual TM 11-1520-23723 for corrective action. All IINS units must be installed in the aircraft during troubleshooting. Refer to aircraft technical manual TM 11-1520-237-23 for coverage of the INS, NPU, and TACAN mounts. 4-17 INS/NPU SELF TEST PROCEDURE.

4-17.1 Perform INS self test procedure as follows:

INS/NPU SELF TEST PROCEDURE NOTE

This test takes approximately 14 minutes. If  allowed to continue beyond approximately 14 minutes, the system will perform an aline gyro bias. 1. Ensure that aircraft power is applied to the system. 2. Set CDU mode select switch (28) to TEST, data display screen illuminates after 30 seconds. Adjust BRT control for desired illumination. 3. Set page select switch (30) to INS. 4. Observe that data display line 7 (7) displays elapsed time. After approximately 14 minutes the timer will reset to 0, indicating the end of the test, and the system will begin a gyrocompass alinement. 5. At the conclusion of approximately 14 minutes, press data display line 3 right line select key (10) to access the TESTS page. 6. If data display line 3 right (3) displays NPU FAIL during step 5, check fuses located on the NPU front panel, if fuses are good, replace the NPU. 7. Observe that INS CO is indicated on data display line 4 right (4) if test passes. 8. If step 7 indicates a fail condition, replace the INS.

To prevent equipment damage, do not disengage aircraft INS power circuit breakers within 10 seconds after setting CDU to OFF mode. 9. Set CDU mode select switch (28) to OFF.

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4-15

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4-18 CDU SELF TEST PROCEDURE.

4-18.1 Perform CDU self test procedure as follows: CDU SELF TEST PROCEDURE

1. Ensure that aircraft power is applied to the system. 2. Set CDU mode select switch (28) to NORM, data display screen illuminates after 30 seconds. Adjust BRT control for desired illumination. 3. Set page select switch (30) to INS. 4. Press line select key (10), observe TESTS page on data display. NOTE Observe BIT indicator (31) immediately after data display line 3 left line select key (37) is pressed. 5. Press data display line 3 left line select key (37), this will initiate the CDU self test.

6. Observe data display on line 3 left (3), the words CDU GO, will be replaced with either a CDU GO or CDU FAIL display and the BIT indicator (31) will show white for five seconds at completion of the test. 7. If step 6 displays a fail condition, or the BIT indicator fails to reset, replace the CDU.

To prevent equipment damage, do not disengage aircraft INS power circuit breakers within 10 seconds after setting CDU to OFF mode. 8. Set CDU mode select switch (28) to OFF.

4-16

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4-17

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4-19 TACAN RT/SDC SELF TEST PROCEDURE.

4-19.1 Perform TACAN/RT SDC self test procedure as follows: TACAN RT/SDC SELF TEST PROCEDURE 1. Ensure that aircraft power is applied to the system. 2. Set CDU mode select switch (28) to NORM, data display screen illuminates after 30 seconds. Adjust BRT control for desired illumination. 3. Set page select switch (30) to TCN. 4. Press data display line 1 left line select key (38). Observe data display line 1 left (1) displays

5. Observe that data display line 3 left (3) displays

TACAN ON.

T/R. If it does not, press line select key (37).

6. Set page select switch (30) to INS,

Observe line 7 left (7) (elapsed time) and allow 90 seconds for TACAN warmup. 7. Press line select key (10), observe TESTS page on data display, 8. Press data display line 5 line select key (36), this will initiate the TACAN RT/SDC self test. 9. Observe data display on line 5 left (5), the words TCN GO will be replaced with either a TCN GO or TCN FAIL display within 10 seconds. 10. If data display line 2 (2) displays SCU during step 9, replace the SDC. 11. If step 9 indicates a fail condition at the completion of the test, check fuse located on TACAN RT mount, if  fuse is good, replace the TACAN RT. 12. Set page select switch (30) to TCN. 13. Press data display line 1 left (1) line select key (38). Observe data display line 1 left (1) displays OFF.

To prevent equipment damage, do not disengage aircraft INS power circuit breakers within 10 seconds after setting CDU to OFF mode. 14. Set CDU mode select switch (28) to OFF.

4-18

TACAN

TM 11-5826-302-12

4-19

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4-20. CALIBRATION (GYRO BIAS).

4-20.1 The calibration mode is used during ground maintenance for the purpose of automatically computing gyro bias correction for all three platform axes. Gyro bias mode requires approximately 90 minutes to

complete. The gyro bias factors are automatically updata and corrected when a flashing NAVRDY is &played. If deemed necessary by degraded navigation performance, the gyro bias function is accomplished as follows:

CALIBRATION (GYRO BIAS) 1. Ensure that aircraft power is applied to the system. 2. Set mode select switch (28) to NORM for 20 minutes. 3. Set mode select switch (28) to OFF for 1 minute. NOTE

Present position must be entered within 2 minutes of turnon. 4. Set mode select switch (28) to CAL. 5. Observe that data display line 7 right (7) displays adjacent line select key (12).

If data display line 7 right (7) displays UTM

press

6. If data display line 8 right (8) does not display LTR, press LTR/USE key (26) to place the keyboard in the alph mode. NOTE

Present position data must be entered for calibration. The following steps are examples of entering present data. Substitute your own present position data when performing these steps. When making keyboard entries, if an incorrect key is pressed, press CLR key (22), as required, and begin again, 7. Enter present position latitude on data display line 8 (8) by pressing in sequence ABC/N2 (14), LTR/USE (26), DEF/3 (15), GHJ/W4 (18), 1 (13), 0 (24), DEF/3(15), and 0 (24) keys. Observe that data display line 8 (8) displays N341030. 8. Press data display line 5 left (5) line select key (36). Observe that data display line 5 left (5) displays N3410 30.

9. Enter present position longitude on data display line 8 (8) by pressing in sequence LTR/USE (26), GHJ/W4 (18), LTR/USE (26), 1 (13) twice, UVW/S8 (20), DEF/3 (15), KLM/5 (16), DEF/3 (15), and 0 (24) keys. Observe that data display line 8 (8) displays W1183530.

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10. Press data display line 7 left (7) line select key (35). Observe that data display line 7 left (7) displays W11835 30.

NOTE The calibrate mode requires approximately 90 minutes to accomplish. Successful completion is indicated by a flashing NAVRDY. The gyro bias information will be automatically stored in memory. Turning the system off prior to issuance of the flashing NAVRDY will result in retention of the old gyro bias values. 11. In approximately 90 minutes, data display line 6 left (6) displays a flashing NAVRDY.

To prevent equipment damage, do not disengage aircraft INS power circuit breakers within 10 seconds after CDU to OFF mode. 12. Set CDU mode select switch (28) to OFF.

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4-21 GENERAL. 4-21.1 IINS unit maintenance includes repair of the IINS by replacement of NPU fuses, CDU lamps and knobs, TACAN mount fuse, and replacement of INS, NPU, CDU, SDC, and TACAN RT units. Failed units are forwarded to AVIM. 4-21.2 The normal test procedure is to perform the operational check to verify the malfunction. The malfunction symptoms should be furnished by the aircrew/  operator but can be obtained or verified by maintenance personnel performing the IINS troubleshooting procedures in section IV. 4-21.3 Repairs are verified by repeating the operational check.

4-21.4 Refer to  TM 1l-5826-302-20P for repair parts and special tools list. 4-22 IINS OPERATIONAL CHECK.

4-22.1 The operational check of the IINS consists of  performing the STD INS/NPU, CDU, and TACAN RT/SDC self test procedures in  paragraphs 4-17, 4-18, and 4-19. 4−23

REMOVAL AND INSTALLATION OF NPU FUSES.

4-23.1 Perform NPU fuses removal and installation as follows:

REMOVING/INSTALLING NPU FUSES

TOOLS: None

Ensure that aircraft power is removed from NPU before removing/installing fuses. Refer to aircraft technical manual TM 11-1520-237-23 for NPU power removal procedure.

NOTE Refer to aircraft technical manual TM 11-1520-237-23 for procedures to gain access to the NPU.

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1. Unscrew and remove each fuseholder cap (1) from NPU (2). 2. Unscrew each fuseholder (3) from NPU (2).

3. Remove fuseholder (3) from NPU and separate fuse (4) from fuseholder by pulling one from the other. I N S TA L L A T I O N , 1. Install fuse (4) into fuseholder (3) and install fuseholder into NPU. 2. Screw fuseholder (3) to NPU (2).

3. Install and screw fuseholder cap (1) to NPU (2).

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4-24 REMOVAL AND INSTALLATION OF CDU LAMPS.

4-24.1 Perform CDU lamps removal and installation as follows: REMOVING/INSTALLING CDU LAMPS

TOOLS: None

Ensure that aircraft power is removed from CDU before removing/ installing lamp.

REMOVAL:

INSTALLATION : 1. Install lamp (4) into cap (1).

To prevent damage to caps, do not use tools to remove caps from front panel assembly.

2. Carefully push each cap (1 and 2) into CDU front panel assembly (3).

1. Carefully pull each cap (1 and 2) out of CDU front panel assembly (3). 2. Remove lamp (4) from cap (1).

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4-25 REMOVAL AND INSTALLATION OF CDU KNOBS.

4-25.1 Perform CDU knobs removal and installation as follows: REMOVING/INSTALLING CDU KNOBS

TOOLS: 5/64 in. hex head wrench .035 in. hex head wrench

Ensure that aircraft power is removed from the CDU before removing/installing knobs.

When removing/installing CDU knobs, ensure that knobs are replaced in the same position to prevent system damage during operation.

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TM 11-5826-302-12

REMOVAL:

1. Using 5/64 in. hex head wrench, loosen two setscrews (1) on each knob (2 and 3) securing knobs to CDU front panel assembly (4). 2, Remove knobs (2 and 3) from CDU front panel

assembly (4). 3. Using .035 in. hex head wrench, loosen two setscrews (5) securing knob (6) to CDU front panel assembly (4). 4. Remove knob (6) from CDU front panel assembly (4).

INSTALLATION, 1. Install knob (6) to CDU front panel assembly (4). 2. Using .035 in. hex head wrench, tighten two set-

screws (5) securing knob (6) to CDU front panel assembly (4). 3. Install knobs (2 and 3) to CDU front panel assembly

(4). 4. Using 5/64 in. hex head wrench, tighten two setscrews (1) on each knob (2 and 3) securing knobs to CDU front panel assembly (4).

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TM 11-5826-302-12

4-26 REMOVAL AND INSTALLATION OF TACAN

MOUNT FUSE.

4-26.1 Perform TACAN mount fuse removal and installation as follows: REMOVING/INSTALLING TACAN MOUNT FUSE

TOOLS: None

Ensure that aircraft power is removed from the TACAN mount before removing/  installing fuse. REMOVAL:

1. Remove TACAN RT as described i n paragraph 4-32 to gain access to TACAN mount fuse. 2. Unscrew fuseholder (1) from TACAN mount (2).

3. Remove fuseholder (1) from TACAN mount (2) and separate fuse (3) from fuseholder by pulling one from the other. INSTALLATION: 1. Install fuse (3) into fuseholder (1) and install fuseholder into TACAN mount (2). 2. Screw fuseholder (1) to TACAN mount (2). 3. Install TACAN RT as described in paragraph 4-32.

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4-28 REMOVAL AND INSTALLATION OF INS.

4-27 REMOVAL AND INSTALLATION OF INS, NPU, AND TACAN MOUNTS. 4-27.1 Refer to aircraft technical manual TM 11-1520237-23 for installation of the INS, NPU, and TACAN mounts.

4-28.1 Perform INS removal and installation as follows:

REMOVING/INSTALLING INS TOOLS: None

Ensure that aircraft power is removed from the INS mount before removing/  installing INS.

When handling the INS, use extreme care to prevent damage to precision electronic equipment, When handling the INS, do not lift or carry by the latch assembly. NOTE

Refer to aircraft manual TM 11-1520-237-23 for procedures to gain access to the INS.

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TM 11-5826-302-12

REMOVAL:

INSTALLATION,

1. Press two latch releases (1) to release latch assembly (2).

1. Remove plastic protective dust covers from INS connectors.

2. Place latch assembly (2) in open position. Hold the INS (3) by the latch assembly and support it from the bottom, Slide INS out of mount (4).

2. With latch assembly (2) in the open position, hold the INS (3) by the latch assembly and support it from the bottom. Place INS on mount (4) and slide inward engaging guide pins and the connectors.

3. Install plastic protective dust covers on INS connectors.

4-30

3. When INS is seated in mount, raise latch assembly (2) until latch assembly latch lock clicks to indicate latch assembly has engaged keeper assembly and is in lock position. Verify the latch assembly has latched by pulling forward on latch assembly.

TM 11-5826-302-12

4-29 REMOVAL AND INSTALLATION OF NPU.

4-29.1 Perform NPU removal and installation as follows: REMOVING/INSTALLING NPU

TOOLS: None

Ensure that aircraft power is removed from the NPU interconnecting cables before removing/installing NPU. Refer to technical manual TM 11-1520-237-23 for NPU power removal procedure. The NPU weighs approximately 90 pounds. Use at least two persons to lift and move it.

When handling the NPU, use extreme care to prevent damage to precision electronic equipment.

NOTE Refer to aircraft technical manual TM 11-1520-237-23 for procedures to gain access to the NPU.

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TM 11-2826-202-12

3. Slide NPU (2) out of mount (5). 4. Install plastic protective dust covers on NPU connec-

tors. INSTALLATION: 1. Remove plastic protective dust covers from NPU connectors. 2. Place NPU (2) on mount (5) and slide inward engaging the guide pins. 3. Position two self-locking holddown retainers (3) on two mounting hooks (4) and tighten self-locking holddown retainers securing NPU to mount. REMOVAL:

1. DiSConneCt aircraft cables from connectors (1, typical) of NPU (2). 2. Loosen and release two self-locking holddown retainers (3) from two mounting hooks (4).

4-32

4. For NPU interconnecting cable information, refer to aircraft technical manual TM 11-1520-237-23. Connect aircraft cables to connectors (1, typical) of NPU (2). 5. Ensure that console lock (6) is connected to connector J11.

TM 11-5826-302-12

4-30 REMOVAL AND INSTALLATION OF CDU.

4-30.1 Perform CDU removal and installation as follows: REMOVING/INSTALLING CDU

TOOLS: 9/32 in. flat-tip screwdriver

Ensure that aircraft power is removed from the CDU interconnecting cables before removing/installing CDU.

When handling the CDU, use extreme care to prevent damage to precision electronic equipment.

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TM 11-5826-302-12

2. Carefully pull CDU (2) out of aircraft panel (3). 3. Disconnect two aircraft cable connectors (4) from CDU (2). 4. Install plastic protective dust covers on CDU connectors. INSTALLATION: 1. Remove plastic protective dust covers from CDU connectors. 2. For CDU interconnecting cable information refer to aircraft technical manual TM 11-1520-237-23. Connect two aircraft cable connectors (4) to CDU (2). REMOVAL:

3. Carefully push CDU (2) into aircraft panel (3).

1. Using screwdriver, loosen eight captive screws (1) securing CDU (2) to aircraft panel (3).

4. Using screwdriver, tighten eight captive screws (1) securing CDU (2) to aircraft panel (3).

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TM 11-5826-302-12

4-31 REMOVAL AND INSTALLATION OF SDC.

4-31.1 Perform SDC removal and installation as follows: REMOVING/INSTALLING SDC

TOOLS: None

Ensure that aircraft power is removed from the TACAN mount before removing/  installing SDC. High SDC surface temperatures are present during SDC operation and for a short period of time after a flight (even if the equipment was never turned on). To prevent injury to personnel, allow SDC to cool or wear protective hand covering prior to removing the SDC.

When handling the SDC, use extreme care to prevent damage to precision electronic equipment.

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TM 11-5826-302-12

2. Loosen and release self-locking holddown retainer (5) from mounting hook (6). Loosen two knurled screws (7) and lift bracket (8). Retighten two knurled screws (7) to hold bracket (8) in place. 3. Slide SDC (4) out of mount (9).

4. Install plastic protective dust covers on SDC connectors. INSTALLATION:

1. Remove plastic protective dust covers from SDC connectors.

2. Place SDC (4) on mount (9) and slide inward engaging the connector. 3. Position self-locking holddown retainer (5) on mounting hook (6) and tighten self-locking holddown retainer securing SDC to mount. Position bracket (8) over TACAN RT handle and tighten two knurled screws (7). REMOVAL:

1. Disconnect aircraft cables from connectors (1, 2, and 3) of SDC (4).

4-38

4. For SDC interconnecting cable information refer to aircraft technical manual TM 11-1520-237-23. Connect aircraft cables to connectors (1, 2, and 3) of  SDC (4).

TM 11-5826-302-12

432 REMOVAL AND INSTALLATION OF TACAN RT.

4-32.1 Perform TACAN RT removal and installation as follows: REMOVING/INSTALLING TACAN RT TOOLS: None

Ensure that aircraft power is removed from the TACAN mount before removing/  installing TACAN RT.

When handling the TACAN RT, use extreme care to prevent damage to precision electronic equipment.

4-37

TM 11-5826-302-12

2. Loosen and release two self-locking holddown retainers (5) from two mounting hooks (6), Loosen two knurled screws (7) and lift bracket (8). Retighten two knurled screws (7) to hold bracket (8) in place. 3. Slide TACAN RT (4) out of mount (9).

4. Install plastic protective dust covers on TACAN RT Connectors. INSTALLATION: 1. Remove plastic protective dust covers from TACAN RT connectors. 2. Place TACAN RT (4) on mount (9) and slide inward engaging the guide pins. 3. Position two self-locking holddown retainers (5) on two mounting hooks (6) and tighten self-locking holddown retainers securing TACAN RT to mount. Position bracket (8) over TACAN RT (4) handle and tighten two knurled screws (7). REMOVAL:

1. Disconnect aircraft cables from connectors (1, 2, and 3) of TACAN RT (4).

4-38

4.

For TACAN RT interconnecting cable information, refer to aircraft technical manual TM 11-1520-23723. Connect aircraft cables to connectors (1, 2, and 3) of TACAN RT (4).

TM 11-5826-302-12

NOTE

4-33 PLACING IINS IN SERVICE.

4-33.1 Refer to paragraph 422 and perform the IINS operational check to verify repairs and complete lid checks. 434 CDU CLEANING.

4-34.1 The glass surface of the CDU CRT must be cleaned to prevent excessive accumulation of dirt.

Do not use sharp tools or volatile solvents. Avoid excessive pressure on glass. Failure to comply may result in damage to equipment. 4-34.1.1 Clean the CRT as follows: a. Using a dry strip of clean, lint-free cloth (item 1, App. D), wipe the glass surface of the CRT.

If glass cannot be cleaned thoroughly with a dry lint-free clod proceed with steps b thru f. b.

Prepare a cleaning solution of water and mild liquid detergent.

c.

Wipe glass surface with clean, lint-free cloth moistened with cleaning solution. Use cleaning solution sparingly and do not saturate area.

d.

Rinse area with clean, lint-free cloth moistened with clean water.

e.

Wipe dry with clean, lint-free cloth.

f.

Inspect glass surface for cleanliness making certain that no residue is present. If further cleaning is required, repeat steps b thru f.

Section VI. IINS PREPARATION FOR STORAGE OR SHIPMENT 4-35 PREPARING IINS FOR STORAGE OR SHIPMENT. 4-35.1 The IINS is not packaged in a single container. IINS units are prepared for storage or shipment by AVIM personnel.

4-39/(4-40 blank)

TM 11-5826-302-12

REFERENCES

A-1 SCOPE. A-1. 1 This appendix lists all forms and technical manuals referenced in this manual.

A-2 FORMS. Aircraft Component Historical Record-Time Change Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

DA Form 2408-16

Component Removal and Repair/Overhaul Record . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DA Form 2410 Discrepancy in Shipment Report. . . . ......... . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . SF 361 Quality Deficiency Report . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . ......... ...... SF 368

Recommended Changes to Publications and Blank Forms . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DA Form 2028 Recommended Changes to Equipment Technical Publications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DA Form 2028-2 Report of Discrepancy.................. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SF 364 A-3 TECHNICAL MANUALS. Administrative Storage of Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TM 740-90-1 Aviation Unit and Intermediate Maintenance Manual, EH-60A Helicopter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TM 11-1520-237-23

Series Intermediate Maintenance Manual, Inertial Navigation Set AN/ASN-141 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

T.O. 5N1-4-15-2

Maintenance Manual, Data Processing Set AN/UYK-64)2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

TM 11-7021-202

Series Operators Manual, EH-60A Helicopter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TM 55-1520-237-10CL Operator’s, Organizational, and Direct Support Maintenance Manual, Test Set Group OQ-329/U . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TM 11-6625-3099-13 Organizational Maintenance Manual, TACAN Navigational Set AN/ARN-118 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NAVAIR 16-30 ARN118-2 Procedures for Destruction of Electronics Materiel to Prevent Enemy Use (Electronics Command) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TM 750-244-2 Repair Parts and Special Tools List for Integrated InertiaI Navigation System AN/ASN-132(V) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TM 11-5826-302-20P The Army Maintenance Management Systems (TAMMS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DA Pam 738.750

A-1

TM 11-5826-302-12 A-4 MISCELLANEOUS PUBLICATIONS. Aircraft Internal Time Division Command/Response Multiplex Data Bus . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

MIL-STD-1553

Army Materiel Maintenance Concepts and Policies . . . . . . . . . . . . . . .

AR 750-50

Army Medical Department Expendable/Durable Items . . . . . . . . . . . . . .

CTA 8-100

Consolidated Index of Army Publications and Blank F o r m s . . . . . . .

DA Pam 25-30

Department of the Army Supply Bulletin . . . . . . . . . . . . . . . . . . . . . . . .

SB 11-654

Discrepancy in Shipment of Equipment . . . . .... . . . . .... . ......

AR 55-38

Expendable/Durable Items . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CTA 50-970

Functional Users Manual for the

Army Maintenance

Management System-Aviation (TAMMS-A)

A-2

.......................

DA Pam 738-751

TM 11-5826-302-12

APPENDIX B MAINTENANCE ALLOCATION CHART

Section 1. INTRODUCTION B-1 MAINTENANCE ALLOCATION CHART. B-1.l This Maintenance Allocation Chart (MAC) assigns maintenance functions in accordance with the Three Levels of Maintenance concept for Army aviation. These maintenance levels (categories) - Aviation Unit Maintenance (AVUM), Aviation Intermediate Maintenance (AVIM), and Depot Maintenance - are depicted on the MAC as: AVWM, which corresponds to an O Code in the Repair Parts and Special Tools List (RPSTL) AVIM, which corresponds to an F Code in the Repair Parts and Special Tools List (RPSTL) DEPOT, which corresponds to a D Code in the Repair Parts and Special Tools List (RPSTL) B-1.2 The maintenance to be performed below depot and in the field is described as follows: B-1.2.1 Aviation Unit Maintenance (AWM) activities will be staffed and equipped to perform high frequency “On-Aircraft” maintenance tasks required to retain or return aircraft systems to a serviceable condition. The maintenance capability of the AWUM will be governed by the Maintenance Allocation Chart (MAC) and limited by the amount and complexity of ground support equipment (CSE), facilities required, authorized manning strength and critical skills available. The range and quantity of authorized spare modules/components will be consistent with the mobility requirements dictated by the air mobility concept. (Assignments of  maintenance tasks to divisional company size aviation units will consider the overall maintenance capability of  the division, the requirement to conserve personnel and equipment resources, and air mobility requirements.) B-1.2.1.1 Company Size Aviation Units: Perform those tasks which consist primarily of preventive maintenance and maintenance repair and replacement functions associated with sustaining a high level of aircraft operational readiness. Perform maintenance inspections and servicing to include preflight, daily, intermediate, periodic (or phased), and special inspections as authorized by the MAC or higher headquarters, Identify the

cause of equipment/system malfunctions using applicable technical manual troubleshooting instructions, builtin test equipment (BITE), installed aircraft instruments, or test, measurement, and diagnostic equipment (TMDE). Replace worn or damaged modules/components that do not require complex adjustments or systern alinement and which can be removed/installed with available skills, tools, and ground support equipment. Perform operational and continuity checks and make minor repair to the electrical system. Inspect, service and make operational, capacity, and pressure checks to hydraulic systems. Perform servicing, functional adjustments, and minor repair/replacement to the flight control, propulsion, power train, and fuel systems. Accomplish air frame repair that does not require extensive disassembly, jigging, or alinement. The manufacture of air frame parts will be limited to those items which can be fabricated with tools and equipment found in current air mobile tool and shop sets. Evacuate unserviceable modules/components and end items beyond the repair capability of AVUM to the supporting AVIM. B-1.2.1.2 Less than Company Size Aviation Units: Aviation elements organic to brigade, group, battalion headquarter, and detachment size units are normally small and have less than ten aircraft assigned. Maintenance tasks performed by these units will be those which can be accomplished by the aircraft crew chief or assigned aircraft repairman and will normally be limited to preventive maintenance, inspections, servicing, spot painting, stop drilling, application of nonstress patches, minor adjustments, module/component fault diagnosis, and replacement of selected modules/components. Repair functions will normally be accomplished by the supporting AVIM unit. B-1.2.2 Aviation Intermediate Maintenance (AVIM) provides mobile, responsive “One-Stop” maintenance support. (Maintenance functions which are not conducive to sustaining air mobility will be assigned to depot maintenance). AVIM may perform all maintenance functions authorized to be done at A WM. Repair of  equipment for return to user will emphasize support or B-1

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operational readiness requirements. Authorized maintenance includes replacement and repair of modules/  components and end items which can be accomplished efficiently with available skills, tools, and equipment. AVIM establishes the Direct Exchange (DX) program for AWM units by repairing selected items for return to stock when such repairs cannot be accomplished at the AVUM level. The AVIM level inspects, troubleshoots, performs diagnostic tests, repairs, adjusts, calibrates, and alines aircraft system modules/components. AVIM units will have capability to determine the serviceability of specified modules/components removed prior to the expiration of the Time Between Overhaul (TBO) or finite life. Module/component disassembly and repair will support the DX program and will normally be limited to tasks requiring cleaning and the replacement of seals, fittings, and items of common hardware. Air frame repair and fabrication of parts will be limited to those maintenance tasks which can be performed with available tools and test equipment. Unserviceable reparable modules/components and end items which are beyond the capability of AVIM to repair will be evacuated to Depot Maintenance. AVIM will perform aircraft weight and balance inspections and other special inspections which exceed AWM capability. provides quick response maintenance support, including aircraft recovery and air evacuation, onthe-job training, and technical assistance through the use of mobile maintenance contact teams. Maintains authorized operational readiness float aircraft. Provides collection and classification services for serviceable/  unserviceable material. Operates a cannibalization activity in accordance with AR 750-50. (The aircraft maintenance company within the maintenance battalion of a division will perform AVIM functions consistent with air mobility requirements and conservation of  personnel and equipment resources. Additional intermediate maintenance support will be provided by the supporting nondivisional AVIM unit.)

B-2 USE OF THE MAINTENANCE ALLOCATION CHART (Section II), B-2.1 The Maintenance Allocation Chart assigns maintenance functions to the lowest category of maintenance based on past experience and the following considerations: B-2.1.1 Skills Available, B-2.1.2 Work time required. B-2.1.3 Tools and test equipment required and/or available.

B-2

B-2.2 Only the lowest category of maintenance authorized to perform a maintenance function is indicated, If  the lowest maintenance category cannot perform all tasks of any single maintenance function (e.g., test, repair), then the higher maintenance level(s) that can accomplish additional tasks will also be indicated. B-2.3 A maintenance function assigned to a maintenance category will automatically be authorized to be performed at any higher maintenance category. B-2.4 A maintenance function that cannot be performed at the assigned category of maintenance for any reason may be evacuated to the next higher maintenance category. Higher maintenance categories will perform the maintenance functions of lower maintenance categories when required or directed by the commander that has the authority to direct such tasking.

B-2.5 The assignment of a maintenance function will “not be construed as authorization to carry the related repair parts or spares in stock. Information to requisition or otherwise secure the necessary repair parts will be as specified in the associated Repair Parts and Special Tools List (RPSTL). B-2.6 Normally there will be no deviation from the assigned level of maintenance. In cases of operational necessity, maintenance functions assigned to a maintenance level may, on a one-time basis and at the request of the lower maintenance level, be specifically authorized by the maintenance officer of the level of maintenance to which the function is assigned. The special tools, equipment, etc. required by the lower level of  maintenance to perform this function will be furnished by the maintenance level to which the function is assigned. This transfer of a maintenance function to a lower maintenance level does not relieve the higher maintenance level of the responsibility for the function. The higher level of maintenance will provide technical supervision and inspection of the function being performed at the lower level. B-2.7 Changes to the Maintenance Allocation Chart will be based on continuing evaluation and analysis by responsible technical personnel and on reports received from field activities. B-3 MAINTENANCE FUNCTIONS. B-3.1 Maintenance functions will be limited to and defined as follows: B-3.2 Inspect. To determine the serviceability of an item by comparing its physical, mechanical, and/or electrical characteristics with established standards through examination (e.g., by sight, sound, or feel).

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B-3.3 Test. To verify serviceability by measuring the mechanical, pneumatic, hydraulic, or electrical characteristics of an item and comparing those characteristics with prescribed standards. B-3.4 Service. Operations required periodically to keep an in proper operating condition, i.e., to clean (includes decontaminate, when required), to preserve, to drain to paint, or to replenish fuel, lubricants, chemical fluids, or gases. B-3.5 Adjust. To maintain or regulate, within prescribed limits, by bringing into proper or exact position, or by setting the operating characteristics to specified parameters. B-3.6 Aline. To adjust specified variable elements of  an item to bring about optimum or desired performance, B-3.7 Calibrate, To determine and cause corrections to be made or to be adjusted on instruments or test, measuring, and diagnostic equipments used in precision measurement. Consists of comparisons of two instruments, one of which is a certified standard of known accuracy, to detect and adjust any discrepancy in the accuracy of the instrument being compared. B-3.8 Remove/Install. To remove and install the same item when required to perform service or other maintenance functions. Install may be the act of emplacing, seating, or fixing into position a spare, repair part, or module (component or assembly) in a manner to allow the proper functioning of an equipment or system. B-3.9 Replace. To remove an unserviceable item and install a serviceable counterpart in its place. “Replace” is authorized by the MAC and is shown as the 3d position code of the SMR code. B-3.10 Repair. The application of maintenance serv1 2 ices , including fault location/troubleshooting , removal/installation, and disassembly/assembl~ proce4 dures, and maintenance actions to identify troubles and restore serviceability to an item by correcting specific damage, fault, malfunction, or failure in a part, subassembly, module (component or assembly), end item, or system, 1

Services - inspect, test, service, adjust, aline, calibrate, and/or replace. 2

Fault locate/troubleshoot - the process of investigating and detecting the cause of equipment malfunctioning the act of isolating a fault within a system or unit under test (UUT).

B.3.11 Overhaul. That maintenance effort (service/  action) prescribed to restore an item to a completely sereviceable/operational condition as required by maintenance standards in appropriate technical publications (i.e., DMWR). Overhaul is normally the highest degree of maintenance performed by the Army. Overhaul does not normally return an item to like new condition. B-3.12 Rebuild. Consists of those services/actions necessary for the restoration of unserviceable equipment to a like new condition in accordance with original manufacturing standards. Rebuild is the highest degree of  materiel maintenance applied to Army equipment. The rebuild operation includes the act of returning to zero those age measurements (hours/miles, etc.) considered in classifying Army equipment/components, B-4 FUNCTIONAL GROUPS (Columns 1 and 2).

B-4.1 The functional groupings shown in the sample below identify maintenance significant components, assemblies, subassemblies, and modules with the next higher assembly. Group Number

Description

04

POWER PLANT

0401

ENGINE GENERAL Servicing, handling, inspection requirements, lubrication charts, overhaul and retirement schedules. External lines & hoses. (As applicable,)

0402

COMPRESSOR SECTION (COLD SECTION MODULE) Rotor, blades, vanes, impeller, stators, inlet guide vanes, main frame, particle separator, bleed valve, bearings, seals, external lines & hoses.

0403

COMBUSTION SECTION (HOT SECTION MODULE) Liners, nozzles, stators, rotor, seals, couplings, blades.

3

Disassemble/assemble - encompasses the stepby-step taking apart (or breakdown) of a spare/functional group coded item to the level of its least componency identified as maintenance significant (i.e., assigned an SMR code) for the category of maintenance under consideration. 4

Actions - welding, grinding, riveting, straightening, facing, remachining and/or resurfacing. B-3

TM 11-5826-202-12

0404

POWER-TURBINE (POWER TURBINE MODULE) Nozzles, rotors, blades, exit guide vanes, exhaust frame, drift shaft, bearings, seals, external lines and hoses.

0405

ACCESSORY GEAR BOX (ACCESSORY SECTION MODULE)

input and output gears, seals, chip detector, housing drive shaft, bearings, seals. 0406

FUEL SYSTEM

Fuel control, fuel boost pump, governors, fuel filter assembly, sequence valve, fuel manifold, fuel nozzle, external lines and hoses. 0407

ELECTRICAL SYSTEM

Electrical control units, exciters, thermocoupler, ignition harness, electrical cables, history record, torque overspeed sensor, Np sensor, alternate stator, blowers. 0408

OIL SYSTEM

Tanks, oil filter, oil cooler, lube and scavenge pumps, oil filter bypass sensors, external lines and hoses. 0409

DRIVE SYSTEM

Reduction gear assembly, output shaft, seal, bearing. 0410

MISCELLANEOUS EQUIPMENT (As applicable).

B-5 MAINTENANCE FUNCTION (Column 3). B-5.1 Column 3 lists the functions to be performed on the items listed in column 2. B-6 MAINTENANCE CATEGORIES AND WORK TIMES (Column 4). B-6.1 The maintenance categories (levels) AVUM, AVIM, and DEPOT are listed on the Maintenance Allocation Chart with individual columns that include

B-4

the work times for maintenance functions at each maintenance level. Work time presentations such as “0.1“ indicate the average time it requires a maintenance level to perform a specified maintenance function. If a work time has not been established, the columnar presentation shall indicate “ “. Maintenance levels higher than the level of maintenance indicated are authorized to perform the indicated function. B-7 TOOLS AND TEST EQUIPMENT (Column 5 and Section III).

B-7.1 Common tool sets (not individual tools), special tools, test, and support equipment required to perform maintenance functions are listed alphabetically in Section III with a reference number to permit cross-referencing to column 5 in the MAC. In addition the maintenance category authorized to use the device is listed along with the item National Stock Number (NSN) and if applicable, the tool number to aid in identifying the tool/device. B-8 REMARKS (Column 6 and Section IV). B-8.1 Remarks (identified by an alphabetic code in column 6) and other notes (identitfied by a number in parentheses in the applicable column) are listed in Section IV to provide a ready reference to the definition of the remark/note.

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Section II. MAINTENANCE ALLOCATION CHART

Integrated Inertial Navigation Set AN/ASN-132(V)

B-5

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Section Il. MAINTENANCE ALLOCATION CHART - Continued

 Integrated Inertial Navigation Set AN/ASN-132(V) - Continued 

B-6

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Section III. TOOL AND TEST EQUIPMENT REQUIREMENTS  Integrated Inertial Navigation Set AN/ASN-132(V)

Tool or Test Equipment Reference Code

Maintenance Level

Nomenclature

National/NATO Stock Number

1

DEPOT

Bag, Anti-Static

8105-01-120-3377

2

AVUM/DEPOT

Multimeter, Digital AN/PSM-45

6625-01-139-2512

3

AVUM/AVIM

Tool Kit, Electronic Equipment TK-101/G

5180-00-064-5178

4

DEPOT

Tool Kit, Electronic Equipment TK-105/G

5180-00-610-8177

5

DEPOT

Work Station, Static

4940-01-087-3458

Tool Number

B-7

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Section IV. REMARKS

 Integrated Inertial Navigation Set AN/ASN-132(V) Reference Code

B-8

Remarks/Notes

A

The AN/ASN-132(V) built-in-test (BIT) is used to test for a defective line replaceable unit (LRU). The TACAN ramp test set is required to perform complete end-toad testing of the TACAN system, including the antenna. Test of the 1553 data bus and other cables will be performed using a multimeter and TACAN ramp test set.

B

Calibration (gyro bias) is performed on a powered-up aircraft when performance exceeds the circular error for one hour flight (CEP) per technical manual, TM 115826-302-12.

c

Repair is limited to replacement of defective knobs, lamps, fuses, LRU’s, INS latch assembly and simple mounting hardware, and TACAN antenna.

D

Built-in-test (BIT), automatic and switch activated, at the installed system level is performed to verify system operational status. In the event of a malfunction the failed LRU status is displayed on the CDU.

E

Reference technical manual for repair, NAVAIR 16-30ARN118-2 (AN/ARN-118).

F

Reference technical manual for repair, T.O. 5N1-4-15-2(AN/ASN-141).

G

Reference technical manual for repair, TM 11-7021-202 series (AN/UYK-64(V)2).

H

Repaired through Depot Maintenance Interservice Support Agreement (DMISA).

I

Mounts are provisioned as part of the aircraft, see TM 11-1520-237-23-3.

J K

Antenna is provisioned as part of the aircraft, see TM 11-1520-237-23-3. INS Mount requires special precision alinement relative to the airframe. Removal of  INS mount is performed at AVIM level. Refer to reference code I above.

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APPENDIX C COMPONENTS OF END ITEM AND BASIC ISSUE ITEMS

Section I. INTRODUCTION C-1 SCOPE.

C-l-1 This appendix lists components of end item and basic issue items for the IINS to help you inventory items required for safe and efficient operation. C-2 GENERAL.

C-2.1 The Components of End Item and Basic Issue Items Lists are divided into the following sections: C-2.2 Section II. Components of End Item. This listing is for inf ormational purposes only, and is not authority to requisition replacements. These items are part of the end item, but are removed and separately packaged for transportation or shipment. AS part of the end item, these items must be with the end item whenever it is issued or transferred between property accounts. Illustrations are furnished to assist you in identifying the items. C-2.3 Section 111, Basic Issue Items. There are no additional items required to place the IINS in operation, to operate it, and to perform emergency repairs.

C-3.3 Column (2) - National Stock Number. Indicates the National Stock Number assigned to the item and will be used for requisitioning purposes C-3.4 Column (3) - Description. Indicates the Federal item name and, if required a minimum description to identify and locate the item, The last line for each item indicates the Federal Supply Code for Manufacturer (FSCM) (in parentheses) followed by the part number. (Enter portions of next two sentences, only if applicable.) If item needed differs for different models of this equipment, the model is shown under the “Usable On” heading in this column. These codes are identified as: Code

Used On

TBS

AN/ASN-132(V)

C-3.1 The following provides an explanation of columns found in the tabular listings:

C-3.5 Column (4) - Units of Measure (U/M). Indicates the measure used in performing the actual operational/maintenance function. This measure is expressed by a two-character alphabetical abbreviation (e.g., ea, in, pr).

C-3.2 Column (1) - Illustration Number (Illus Number). This column indicates the number of the illustra. tion in which the item is shown,

C-3.6 Column (5) - Quantity required (Qty Rqr). Indicates the quantity of the item authorized to be used with/on the equipment.

C-3 EXPLANATION OF COLUMNS.

C-1

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Section II. COMPONENTS OF END ITEM

C-2

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Section Il. COMPONENTS OF END ITEM - Continued

(1) Illus Number

(2) National Stock  Number

(4)

(3)

Description FSCM and Part Number

Usable On Code

U/M

(5) Qty Rqr

1

6605-01-135-6328

Control Display Unit C-l1097/ASN132(V) (57045) 622-6143-001

EA

1

2

5826-01-012-1938

TACAN Receiver-Transmitter RT-1159/  A (57045) 622-0507-001

EA

1

3

5826-01-142-3059

Signal Data Converter CV-3739/ASN132(V) (06481) 886510-1

EA

1

4

5826-01-041-2044

Electrical Equipment Mounting Base MT-4915/A (57045) 662-2041-001

EA

1

5

7035-01-166-7857

Data Processing Set AN/UYK-64(V)2 (14345) 1666B-C

EA

1

Navigation Processor Unit Mount (14345) 105794

EA

1

6 7

6605-01-107-2380

Inertial Navigation Set Mount (06481) 880100-1

EA

1

8

6605-01-206-8954

Inertial Navigation Set AN/ASN-141 (06481) 880200-33

EA

1

C-3/(C-4blank)

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APPENDIX D EXPENDABLE SUPPLIES AND MATERIALS LIST

Section 1. INTRODUCTION D-1 SCOPE.

D-1.1 This appendix lists expendable supplies and materials you will need to operate and maintain the IINS. This listing is for informational purposes only and is not authority to requisition the listed items. These items are authorized to you by CTA 50-970, Expendable/Durable Items (Except Medical, Class V, Repair Parts; and Heraldic Items), or CTA 8-100, Army Medical Department Expendable/Durable Items. D-2 EXPLANATION OF COLUMNS,

D-2.1 Column (1) – Item Number. This number is assigned to the entry in the listing and is referenced in the narrative instructions to identify the material (e.g., “Use cleaning compound, item 5, App. D“). D-2.2 Column (2) - Level. This column identifies the lowest level of maintenance that requires the listed item.

(Enter as applicable) AVUM - Aviation Unit Maintenance AVIM - Aviation Intermediate Maintenance DEPOT - Depot Maintenance D-2.3 Column (3) - National Stock Number. This is the National Stock Number assigned to the item; use it to request or requisition the item. D-2.4 Column (4) - Description. Indicates the Federal item name and, if required, a description to identify the item. The last line for each item indicates the Federal Supply Code for Manufacturer (FSCM) in parentheses followed by the part number. D-2.5 Column (5) – Unit of Measure (U/M). Indicates the measure used in performing the actual maintenance function. This measure is expressed by a two-character alphabetical abbreviation (e.g., ea, in, pr). If the unit of  measure differs from the unit of issue, requisition the lowest unit of issue that will satisfy your requirements.

D-1

TM 11-5826-302-12

Section II. EXPENDABLE SUPPLIES AND MATERIALS LIST (1) Item Number 1

D-2

(4)

(5)

Level

(3) National Stock  Number

Description

U/M

AVUM

7920-00-044-9291

Cloth, Lint-Free

BX

(2)

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GLOSSARY

Section L ABBREVIATIONS Ground speed

AALT . . . . . . . . . . . . . . . . . . . . . . . . .

Altimeter altitude

GS

ACT . . . . . . . . . . . . . . . . . . . . . . . . . . .

Active

CASE . . . . . . . . . . . . . . . . . . . . . . . . . . .

Ground support equipment

AVIM . . . . . . . . . . . . . . . . . . . . . . .

Aviation intermediate maintenance

GTK . . . . . . . . . . . . . . . . . . . . . . . . . . .

Ground track 

HI... . . . . . . . . . . . . . . . . . . . . . . . . . .

Horizontal situation indicator

IALT . . . . . . . . . . . . . . . . . . . . . . . . . .

Inertial altitude

AIM . . . . . . . . . . . . . . . . . . . . . . .

Aviation unit maintenance

A/A REC . . . . . . . . . . . . . . . . . .

Air-to-air receive

..............................

..........................

Initialize

A/A T/R . . . . . . . . . . . . . . . . . . Air-to-air transmit/receive

INIT

A/R . . . . . . . . . . . . . . . . . . . . . . . . . . . .

IINS . . . . . . . . . . . . . . . . . . . . . . . . . . .

Integrated inertial navigation system

INACT . . . . . . . . . . . . . . . . . . . . . .

Inactive

INS . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Inertial navigation set

1/0 . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Input/output

L/L

Latitude/longitude

...........................

Accept/reject Air data computer

A+H......................

Altitude and heading

ARINC . . . . . . . . . . . . . . . . . . . . . .

Aeronautical radio incorporated

ATTD.. . . . . . . . . . . . . . . . . . . . Attitude

............................

BAR . . . . . . . . . . . . . . . . . . . . . . .

Barometric pressure

LOU . . . . . . . . . . . . . . . . . . . . . . . . . . .

Line replaceable unit

BATH.. . . . . . . . . . . . . . . . . . . . . .

Best available true heading

MAC . . . . . . . . . . . . . . . . . . . . . . . . . .

Maintenance allocation chart

BIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Built-in test

MALT . . . . . . . . . . . . . . . . . . . . . . . .

Manually entered altitude

BITE . . . . . . . . . . . . . . . . . . . . . . . . . .

Built-in test equipment

MARS . . . . . . . . . . . . . . . . . . . . . . . .

BRG . . . . . . . . . . . . . . . . . . . . . . . . . . .

Bearing

Military grid reference system

BAT . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Brightness

MH . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Magnetic heading

CAL . . . . . . . . . . . . . . . . . . . . . .

Calibrate

MRK . . . . . . . . . . . . . . . . . . . . . . . . . .

Mark

CDU . . . . . . . . . . . . . . . . . . . . . . . . . . .

Control display unit

MSC . . . . . . . . . . . . . . . . . . . . . . . . . .

Mission system computer

MTOE . . . . . . . . . . . . . . . . . . . . . . .

Modified table of  organization and equipment

CEP

...........................

Circular error probability

CF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Convergence factor

MA . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Magnetic variation

CH . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Channel

NAV . . . . . . . . . . . . . . . . . . . . . . . . . .

Navigate

CPU . . . . . . . . . . . . . . . . . . . . . . . . . . .

Central processor unit

NAVRDY . . . . . . . . . . . . . . . . . .

Navigate ready

DEGRD . . . . . . . . . . . . . . . . . . . . .

Degraded

NORM . . . . . . . . . . . . . . . . . . . . . . .

Normal

DEGUPT . . . . . . . . . . . . . . .

Degraded mode update by TACAN

NPU . . . . . . . . . . . . . . . . . . . . . . . . . .

Navigation processor unit

DEST . . . . . . . . . . . . . . . . . . . . . . . . .

NSN . . . . . . . . . . . . . . . . . . . . . . . . . . .

Destination

National stock number

PAM . . . . . . . . . . . . . . . . . . . . . . . . . . .

DISREP . . . . . . . . . . . . . . . . . . . . .

Discrepancy in shipment report

Post flight maintenance required

PMCS . . . . . . . . . . . . . . . . . . . . . . . . .

DMISA . . . . . . . . . . . . . . . . . . . . . .

Depot maintenance interservice support agreement

Preventive maintenance checks and services

Pod . . . . . . . . . . . . . . . . . . . ..... Position

DX..,,, . . . . . . . . . . . . . . . . . . . . . . . . .

Direct exchange

P/R VEAL . . . . . . . . . . . . . . . . .

Pitch, roll, and velocity

ECM . . . . . . . . . . . . . . . . . . . . . . . . . .

Electronic countermeasures

REC . . . . . . . . . . . . . . . . . . . . . . . . . . .

Receive

EAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Equipment improvement recommendation

RNG . . . . . . . . . . . . . . . . . . . . . . . . . .

Range

ROD . . . . . . . . . . . . . . . . . . . . . . . . . . .

Report of discrepancy

Fault acknowledge

RPSTL . . . . . . . . . . . . . . . . . . . . . . .

Federal supply code for manufacturer

Repair parts and special tools list

RAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Receiver-transmitter

FACE . . . . . . . . . . . . . . . . . . . . . . . . .

FSCM

........................

Glossary 1

TM 11-5826-302-12

Section 1. ABBREVIATIONS - Continued

SCU . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Signal converter unit

TH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

True heading

SDC . . . . . . . . . . . . . . . . . . . . . . . . . . .

Signal data converter

TIO . . . . . . . . . . . . . . . . . . . . . . . . . . . .

TACAN input/output

SRNG . . . . . . . . . . . . . . . . . . . . . . . .

Slant range

TMDE . . . . . . . . . . . . . . . . . . . . . . .

STA . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Station

Test measurement diagnostic equipment

STAT . . . . . . . . . . . . . . Status

T/R . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Transmit/receive

SIR . . . . . . . . . . . . . . Steer

TTG . . . . . . . . . . . . . . . . . . . . . . . . . . .

Time-to-go

TACAN . . . . . . . . . . . . . . . . . . . . .

Tactical air navigation

UPDT . . . . . . . . . . . . . . . . . . . . . . . .

Update

TAMES . . . . . . . . . . . . . . . . . . . . .

The Army maintenance management system

UTM . . . . . . . . . . . . . . . . . . . . . . . . . .

Universal transverse mercator

TBO . . . . . . . . . . . . . . . . . . . . . . . . . . .

Time between overhaul

UUT . . . . . . . . . . . . . . . . . . . . . . . . . . .

Unit under test

VA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Volt amperes

TAN . . . . . . . . . . . . . . . . . . . . . . . . . . . TACAN

Section II. DEFINITIONS OF UNUSUAL TERMS

Built-in test - A test built into the equipment to test for proper functioning.

Clark 1866

CL6

Clark 1880

CL0

Easting - The east-west position (UTM grid).

Everest

EVR

Northing - The north-south position (UTM grid).

Bessel

BSL

Australian National

AUS

Airy Hough

ARY

South American

SAM

Modified Everest

MEV

WGS-72

WGS

Spheroid - An earth spheroid model used for computing geodetic positions. Different models are used in various parts of the world, IINS can accommodate the following spheroid models:

Spheroid Model International

Glossary 2

Abbreviation

INT

HGH

Universal Transverse Mercator (UTM) - A rectangular coordinate system.

TM 11-5826-302-12

ALPHABETICAL INDEX

Subject, Para

Subject, Para

A

Longitude,  2-6.2.4.2

Adjustment of equipment, preliminary,  4-14

Magnetic heading,  2-6.2.3

Alinement procedures,  2-6.4.2

Magnetic variation,  2-6.2.5

Alphanumeric entry,  2-6.2.1

Northings,  2-6.2.4.4

Area entry, 2-6.2.4.4

Present position,  2-6.2.4

Assembly and preparation for use, 2-4

Spheroid,  2-6.2.4.3 TACAN station channel,  2-6.2.12

B

TACAN station magnetic variation, 2-6.2.10

Barometric pressure entry,  2-6.2.7

TACAN station position,  2-6.2.11

c

True heading,  2-6.2.3

Calibration (gyro bias),  4-20

Data processing set, see NPU

Capabilities and features, IINS, 1-9

Reprocessing unpacked equipment, 4-5

CDU

Destination coordinate entry,  2-6.2.8

Cleaning,  4-34

Destination/steering data entry procedure, 2-6.4.3

Controls and indicators, 2-1

Destruction of Army electronics materiel, 1-3

Installation,  4-10,  4-30

Differences between models, 1-11

Page descriptions, 2-2 Removal,  4-30

E Eastings entry,  2-6.2.4.4

Self test,  4-18

Checking unpacked equipment, 4-4 Cleaning, CDU,  4-34

Control and display unit, see CDU Controls and indicators, operator’s, 2-1

Emergency procedures, 2-9

Equipment data, 1-12 Equipment, purpose, 1-1.4 Error checking,  2-6.2.2

F

Course to destination entry, 2-6.2.9 D Data entry description, 2-6.2

G Grid zone entry,  2-6.2.4.3

Alphanumeric,  2-6.2.1

H

Area, 2-6.2.4.4

I

Barometric pressure, 2-6,2.7

Course to destination, 2-6.2.9

IINS

Destination coordinate,  2-6.2.8

Capabilities and features, 1-9

Eastings,  2-6.2.4.4

Operational check, 4-22

Error checking,  2-6.2.2

Purpose, 1-8

Field altitude, 2-6.2.6

Semite, placing in, 4-33

Grid zone,  2-6.2.4.3

Shipment, preparation for, 4-35

Latitude,  2-6.2.4.1

Storage, preparation for, 4-35 Index 1

TM 11-5826-302-12

ALPHABETICAL INDEX - Continued

Subject, Para

Subject, Para

M

Unpacking instruction 4-3 Inflight procedures,  2-6.5

Magnetic heading entry,  2-6.2.3

Initial adjustments,  2-5.1

Magnetic variation entry,  2-6.2.5

Initial adjustments and self test 2-5

Maintenance forms, records, and reports, 1-2

Initial adjustments,  2-5.1

Manual

Self test, 2-5.2

scope, 1-1

INS

Type,  1-1.2

Installation 4-8,4-28

Manually entered field altitude,  2-6.2.6

Removal,  4-28

Model number and equipment name, 1-1.3

self test, 4-17

Mounts Installation,  4-7,  4-27

Installation

Removal,  4-27

CDU, 4-10,4-30 CDU knobs,  4-25

N

CDU lamps,  4-24

Navigation processor unit, see NPU

INS, 4-8,4-28

Northings entry,  2-6.2.4.4

Materials required, 4-6

NPU

Mounts, 4-7,4-27

Installation,  4-9,  4-29

NPU, 4-9,4-29

Loading procedure,  2-6.4.1

NPU fuses,  4-23

Removal,  4-29

SDC, 4-11,4-31

Self test, 4-17

TACAN mount fuse, 4-26 TACAN RT, 4-12,4-32

0

Test equipment required, 4-6

Official nomenclature, common names, and designations, 1-5

Tools required, 4-6

Operating procedure, 2-6

Integrated inertial navigation system, see IINS

Operation in unusual weather, 2-8

Interconnections, 4-13

Operation of auxiliary equipment, 2-7 J

Operational check, IINS, 4-22 Operator’s controls and indicators, 2-1

Jamming and ECM procedures, 2-10

K L

P Placing IINS in service, 4-33 PMCS procedures, 4-15

Latitude entry, 2-6.2.4.1

Preoperational procedures,  2-6.4

Location and description of major components, 1-10

Preparation for storage or shipment, 1-4

Longitude entry,  2-6.2.4.2

Principles of operation, 1-14

Index 2

Present position entry, 2-6.2.4

TM 11-5826-302-12

ALPHABETICAL INDEX - Continued

Subject, Para

Subject, Para

Purpose of equipment,  1-1.4

Signal data converter, see SDC

purpose of IINS, 1-8

Spheroid entry,  2-6.2.4.3

Q R

Shipment, preparation for, I-4 Storage, preparation for, 1-4 T

Removal CDU, 4-30

TACAN data entry procedure, 2-6.4.4

CDU knobs, 4-25

TACAN station channel entry,  2-6.2.12

CDU lamps, 4-24

TACAN station magnetic variation entry, 2-6.2.10

 INS, 4-28 

TACAN station position entry,  2-6.2.11

Mounts, 4-27

TACAN RT Installation,  4-12,  4-32

NPU, 4-29

Removal, 4-32

NPU fuses, 4-23

Self test, 4-19

SDC, 4-31

TACAN mount fuse, 4-26

Tools, test equipment, and materials required for installation, 4-6

TACAN RT,  4-32

True heading entry,  2-6.2.3

Reporting equipment improvement recommendations, 1-6 s Safety, care, and handling,  1-13 Care,  1-13.2

Type of manual,  1-1.2 Typical data entry,  2-6.3

u Unpacking instructions, 4-3

Handling,  1-13.3

v

Safety,  1-13.1

w

Scope, 1-1 SDC Installation,  4-11,  4-31

Warranty information, 1-7 x

Removal, 4-31

Y

Self test,  4-19

z

Self test, 2-5.2 CDU, 4-18 INS, 4-17 SDC, 4-19

TACAN RT, 4-19 Servicing of equipment, preliminary,  4-14

Service upon receipt of material, 4-2 Shutdown procedure, 2-6.6

Index 3/(Index 4 blank)

By Order of the Secretary of the Army:

Official:

CARL E. VUONO General, United States Army Chief of Staff 

R.L. DILWORTH  Brigadier General, United States Army The Adjutant General

DISTRIBUTION: To be distributed in accordance with DA Form 12-31A literature requirements for EEC EH-60A.

U.S. GOVERNMENT PRINTING OFFICE: 1991 0-294-337