TM 11-5826-302-12 (1987_1201) OMM & AVUM, AN_ASN-132(V) IINS

TM 11-5826-302-12

TECHNICAL MANUAL

OPERATOR’S AND AVIATION UNITMAINTENANCE MANUAL

INTEGRATED INERTIAL NAVIGATIONSYSTEM AN/ASN-132 (V)

(PART NO. 751500-1)

DISTRIBUTION AUTHORIZED TO THE DEPARTMENT OF DEFENSE AND DOD CONTRACTORS ONLYTO PROTECT TECHNICAL OR OPERATIONAL INFORMATION FROM AUTOMATIC DISSEMINATIONUNDER THE INTERNATIONAL EXCHANGE PROGRAM OR BY OTHER MEANS. THIS PROTECTIONAPPLIES TO PUBLICATIONS REQUIRED SOLELY FOR OFFICIAL USE AND FOR THOSE CONTAININGVALUABLE TECHNICAL OR OPERATIONAL INFORMATION. THIS DETERMINATION WAS MADE ON 3FEBRUARY 1987. OTHER REQUESTS WILL BE REFERRED TO HQ, U.S. ARMY COMMUNICATIONS-ELECTRONICS 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 thedocument.

HEADQUARTERS, DEPARTMENT OF THE ARMY

1 DECEMBER 1987

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SAFETY STEPS TO FOLLOW IF SOMEONEIS 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 ELECTRICALPOWER, PULL, PUSH, OR LIFT THE PERSON TOSAFETY USING A DRY WOODEN POLE OR A DRYROPE OR SOME OTHER INSULATING MATERIAL

SEND FOR HELP AS SOON AS POSSIBLE

AFTER THE INJURED PERSON IS FREE OFCONTACT WITH THE SOURCE OF ELECTRICALSHOCK, MOVE THE PERSON A SHORT DISTANCEAWAY AND IMMEDIATELY START ARTIFICIALRESUSCITATION

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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 moveit.

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

B

TECHNICAL MANUAL

No. 11-5826-302-12

TM 11-5826-302-12

HEADQUARTERSDEPARTMENT OF THE ARMY

Washington, DC, 1 December 1987

OPERATOR’ S AND AVIATION UNITMAINTENANCE MANUAL

INTEGRATED INERTIAL NAVIGATIONSYSTEM AN/ASN-132

REPORTING ERRORS AND RECOMMENDING IMPROVEMENTS

You can he lp Improve th is manua l . I f you f ind any mis takes or I f you know o f a way toimprove the p rocedures , p lease le t us know. Mall your letter, DA Form 2028 (RecommendedChanges to Pub l ica t ions and B lank Forms) , o r DA Form 2028-2 loca ted In the back o f th ism a n u a l d i r e c t t o : Commander , US Army Communica t ions-E lec t ron ics Command and For tMonmouth, ATTN: AMSEL-ME-MP, Fort Monmouth, New Jersey 07703-5000. A r e p l y w i l l b ef u r n i s h e d d i r e c t t o y o u .

CHAPTER 1

Section II IIII

CHAPTER 2

S e c t i o n I

IIIIV

CHAPTER 3

4

S e c t i o n II IIIIIVVVI

APPENDIX A

B

S e c t i o n II IIIIIV

APPENDIX C

S e c t i o n II I

I I

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

INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . l .. . . . . . . . . . . . . . . . . . . .

General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Equipment Descr ip t ion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .P r i n c i p l e s o f O p e r a t i o n . . . . . . . . . . l . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

OPERATING INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . ..

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

OPERATOR MAINTENANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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

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

REFERENCES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

MAINTENANCE ALLOCATION CHART . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

I n t r o d u c t i o n . . . . . . . . . . . . . . . . . . . . . . . . . . . . l . . . . . . . . . . . . . . . . . . . l . . . . l

Main tenance A l loca t ion Char t . . . . . . l . . . . . . . . . . . . . . . . . . l . . . . . . . . . . . . . .Tools and Test Equipment Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Remarks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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

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

Page

2-1

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1-1

1-1

1-2

2-1

2-422-422-69

3-1

4-1

4-14-1

4-134-144-234-39

A-1

B-1

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

C-1

C-1C-2

1-2

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APPENDIX D

Page

EXPENDABLE SUPPLIES AND MATERIALS LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . D-1

Sect Ion I I n t r o d u c t i o n . . . . . . ● . . . . . . . . . . . . . . . . . . . . . . . . . . ● . ● . . ● ● . . . . . . . . . . . . . . . .I I Expendab le Supp l ies and Mater ia ls L is t . . . . . . . . . . . . . . . . . . . . . . . . . ● . . , . D-2

GLOSSARY . . . . . ● . . ● . . . . . . . ● . . . . . . . . . . . . . . . . ● . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . , . Glossary 1

S e c t i o n I A b b r e v i a t l o n s . . . . . . ● . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Glossary 1II Definitions of Unusual Terms . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Glossary 2

ALPHABETICAL INDEX . . . . . . . . . . . . . . . . ... . . . ● ● . . ● . . ● . . . . . . . . . . . ● . ● . . . . . ● . ● . . . . . . . . . . . . . . . . Index 1

i i

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HOW TO USE THIS MANUAL

1. You must familiarize yourself with the entire mainte-nance procedures before beginning the maintenancetask.

2. The content of this manual is limited to:

a. Information on the Integrated Inertial Naviga-tion System.

b. Only those maintenance tasks authorized at avia-tion unit maintenance level.

d. A chapter on aviation unit maintenance instruc-tions.

e. Lists of references, maintenance allocation chart,components of end item and basic issue items,and expendable supplies and materials in theappendices.

f. A glossary of abbreviations and definitions ofunusual terms.

g. An alphabetical index.

3. This manual consists of: 4. To find information quickly

a. An introduction to Integrated Inertial Naviga- a. A detailed Table of Contents is on page i. tion System. b. An alphabetical index is on page Index 1.

b. A chapter on system operating instructions, c. A summmy of all warnings that appear in thec. A chapter on operator maintenance instructions. manual is at the front of the manual.

iii

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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 toperform operator and aviation unit maintenance on theIntegrated Inertial Navigation System AN/ASN-132(V)(IINS).

1-1,2 T e of Manual, This manual provides the in-structions required to operate, maintain, test, trou-bleshoot, and repair the IINS at the operator andaviation unit maintenance levels. Functional descrip-tions, diagrams, tools and test equipment, and materiallists are provided to support these functions as dictatedby the Maintenance Allocation Chart (MAC).

1-1.3 Model Number and Equipment Name. Thismanual covers the following model/equipment.

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

1-1.4 Purpose of Equipment. The IINS provides self-contained navigation capability to U.S. Army EH-60AAircraft for short- and/or long-range missions andwhich can be updated wherever TACAN navigationalfacilities exist or manually without TACAN data.

1-2 MAINTENANCE FORMS, RECORDS, AND RE-PORTS.

1-2.1 Reports of Maintenance and UnsatisfactoryEquipment, Department of the Army forms and proce-dures used for equipment maintenance will be thoseprescribed by DA Pam 738-750, as contained in Mainte-nance 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) (SF361). Fill out and forward Discrepancy in ShipmentReport (DISREP) (SF 361) as prescribed in AR 55-38/NAVSUPINST 4610.33C/AFR 75-18/MCOP4610.19D/DLAR 4500.15.

1-3 DESTRUCTIONMATERIEL.

1-3.1 Destruction of

OF ARMY ELECTRONICS

Army electronics materiel toprevent enemy use shall be in accordance with TM 750-244-2.

1-4 PREPARATION FOR STORAGE OR SHIP-MENT.

1-4.1 Refer to TM 740-90-1 for procedures, forms andrecords, and inspect ions required during administrativestorage of this equipment and chapter 4, section VI ofthis manual.

1-5 OFFICIAL NOMENCLATURE, COMMONNAMES, AND DESIGNATIONS.

1-5.1 The following listing includes the commonname to official nomenclature cross-references used inthis manual.

Official Nomenclature

Integrated InertialNavigation SystemAN/ASN-132(V)

Inertial Navigation SetAN/ASN-141

Inertial Navigation SetMount

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

Navigation ProcessorUnit Mount

Control Display UnitC-11097/ASN-132(V)

Signal Data ConverterCV-3739/ASN-132(V)

TACAN Receiver-TransmitterRT-1159/A

Common Name

IINS

INS

INS Mount

NavigationProcessorUnit (NPU)

NPU Mount

CDU

SDC

TACAN RT

1-1

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Electrical Equipment TACAN MountMounting BaseMT4915/A

1-6 REPORTING EQUIPMENT IMPROVEMENTRECOMMENDATIONS (EIR).

1-6.1 If your equipment needs improvement, let usknow. Send us an EIR. You, the user, are the only onewho can tell us what you don’t like about the design.Put it on an SF 368 (Quality Deficiency Report). Mail itto Commander, US Army Communications-ElectronicsCommand and Fort Monmouth, ATTN: AMSEL-PA-MA-D, Fort Monmouth, New Jersey 07703-5000.

1-7 WARRANTY INFORMATION.

1-7.1 The SDC is warranted by Littonfor 42 months. The CDU is warranted

Systems, Inc.by Rockwell

International Corporation for 48 months. Warrantystarts on the date found on DA Form 2410 or DA Form2408-16 in the logbook. Report all defects in materialor workmanship to your supervisor who will take ap-propriate action. Refer to Department of the ArmySupply Bulletin SB 11-654 for additional warranty infor-mation, as required.

We’ll send you a reply.

Section Il. EQUIPMENT DESCRIPTION

1-8 PURPOSE OF IINS.

1-8,1 The IINS provides self-contained navigationcapability to U.S. ‘Army EH-60A Aircraft for short-and/or long-range missions and which can be updatedwherever TACAN navigational facilities exist or manu-ally without TACAN data The IINS employs a bidirec-tional serial data bus for data interchange within theIINS and with the external mission computer. The IINSalso interfaces with the aircraft flight instruments andaltimeter/encoder AAU-32A. Navigation sensor andpath determination data is processed by the NPU. IINScontrol 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 timesand attitude accuracies in circular error for a 1 hourflight (CEP), CDU display capabilities, and CDUenterable 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 com-puter interface.

MIL-STD-1553 dual redundant digitalface communication.

System level built-in-test capabilities.

1-2

MUX bus inter-

High system reliability, efficient maintainability andease of operation.

System designed to minimize personnel/equipmenthazards.

System power interruptions/transients protection.

No radioactive, explosive, or caustic chemical elementswhich require special handling and/or transportation.

1-10 LOCATION AND DESCRIPTION OF MAJORCOMPONENTS.

1-10.1 The illustrations following table 1-4 locate anddescribe 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, followArmy safety procedures for the use and handling ofelectronic equipment. Before and while operating theequipment, adhere to the WARNINGS and CAU-TIONS indicated throughout this manual. All WARN-INGS are also summarized on the WARNING page atthe front of this manual. In addition instructions on allWARNING and CAUTION decals attached to theequipment must be followed.

1-13.2 Care. To ensure that the IINS is always readyfor operation, it must be inspected systematically sothat 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 specified environments bymaintenance checks and services must be performed atthe intervals prescribed to ensure that the IINS isoperating properly. Note any defects during operationfor correction after operation. Stop operation immedi-ately if a deficiency is noted which would damage theequipment.

1-13.3 Handling. The IINS should be handled withextreme care to prevent damage to precision electronicequipment. The equipment is designed and constructedso that on-vehicle maintenance can be performed in all

persomel wearing clothing,such as heavy gloves, required by the particular envi-ronment. Required maintenance, such as testing, re-moval, replacement, and hookup are possible over thisexpected range of flight line environments. The individ-ual units are designed so that special handling or pro-tective equipment is not needed for installation or fortransport between the local maintenance and/or supplyfacility and the vehicle. Removal and replacement ofthe units (except the NPU) in the vehicle can be accom-plished by one person using standard tools. Two personsare required to lift the NPU.

1-3

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Table 1-3. CDU Display Data Capabilities

Data Range Resolution

true)

Present true heading (inertial)

Present magnetic heading (inertial)

Bearing to destination (inertial - true)

Distance to destination (inertial)

Time to steering point (inertial)

Distance to steering point (inertial)

Course to steering point (inertial -

Bearing to steering point (inertial -true)

Computed magnetic variation (inertial)

Aline time and status (inertial)

Present true ground track (inertial)

Position error north (inertial)

Position error east (inertial)

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

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

Time to destination (inertial)

Raw TACAN slant range to station

Raw TACAN mag bearing from station

Built In Test (BIT) indicator

0 to 359.9 degrees

0 to 359.9 degrees

0 to 359.9 degrees

0 to 1852 km(0 to 999 nmi)

0 to 1092.2 min(time)

0 to 1852 km(0 to 999 nmi)

0 to 359.9 degrees

0 to 359.9 degrees

E 179.9 degrees

W 180 degrees


0 to 359.9 degrees

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

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

N 0 to 89 °59’9”

S 0 to 90°00’0”

E 0 to 179°59’9”

W 0 to 180°00’0”


0 to 200 nmi

0 to 359 degrees

System status

0.1 degree

0.1 degree

0.1 degree

0.1 km(0.1 nmi)

0.1 min(time) /or1.0 sec

0.1 km(0.1 nmi)

0.1 degree

0.1 degree

0.1 degree

0.1 mintime - N/A

0.1 degree

0.1 km(0.1 nmi)

0.1 km(0.1 nmi)

0.1 min

0.1 min

0.1 min(time) /or1.0 sec

0.1 nmi

1.0 degree

1-4

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Table 1-4. CDU Enterable Data Capabilities

Data Range Resolution

Destination position (latitude -inertial)

Destination position (UTM - inertial)

Selected true course to destination(inertial)

Present position (latitude - inertial)

Present position (UTM - inertial)

Entered true heading (inertial)

Entered magnetic heading (inertial)

Entered magnetic variation (inertial)

Manually entered altitude

TACAN station position (latitude)

TACAN station position (UTM)

TACAN station altitude

TACAN station channel

TACAN station magnetic variation

Destination position (longitude -inertial)

Present position (longitude - inertial)

TACAN station position (longitude)

N 0 to 89°59’59”

S 0 to 90°00’00”

Requirements set forthby UTM MGRScoordinates

0 to 359.9 degrees

N 0 to 89°59’59”

S 0 to 90°00’00”

Requirements set forthby UTM MCRScoordinates

0 to 359.9 degrees

0 to 359.9 degrees

E 0 to 179.9

W 0 to 180.0

-1000 to + 65,000 ft

N 0 to 89°59’59”

S 0 to 90°00’00”

Requirements set forthby UTM MCRScoordinates

-1000 to +9,900 ft

001 to 126, X or Y

E 0 to 179.9°

W 0 to 180.0°

E 0 to 179°59’59”

W 0 to 180°00’00”

E 0 to 179°59’59”

W 0 to 180°0’00’”

E 0 to 179°59’59”

W 0 to 180°00’00”

1.0 arc sec

10 meter grid

0.1 degree

1.0 arc sec

10 meter grid

0.1 degree

0.1 degree

0.1 degree

100 ft

1.0 arc sec

10 meter grid

100 ft

Units

0.1 degree

1.0 arc sec

1.0 arc sec

1.0 arc sec

1-5

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1-6

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1.

2.

3.

4.

5.

6.

7.

8.

9.

10.

11.

12.

CAUTION DECAL. Provides possible equipment damage information.

POWER CONNECTOR. Provides main power inputs to the INS.

COOLING AIR OUTLET. Allows cooling air to exhaust through the sides of the INS.

LATCH RELEASE. Provides lock release when latch assembly is in locked position.

LATCH LOCK. Maintains the latch assembly locking mechanism in the locked position.

ELAPSED TIME INDICATOR. Displays total INS operating time in hours.

LATCH ASSEMBLY. Provides unit to mount locking mechanism,

FAULT INDICATORS. Provides fault detection and isolation information.

TEST CONNECTOR. Provides testing interface for intermediate level maintenance.

GYRO BIAS DECAL. Provides gyro bias data determined during alinement or test,

CALIBRATION DECAL. Provides calibration data determined during alinement or test,

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

1.

2.

3.

4.

5.

6.

7.

8.

9.

10.

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

NAMEPLATE. Provides mount identification information.

COOLING AIR INLET. Provides mount heat exchanger interface with aircraft cooling air supply.

POWER CONNECTOR LOCATION. Provides mounting area for aircraft wiring connector,

ROUND GUIDE PIN. Ensures proper positioning and attachment of INS.

GASKET, Provides an air seal between the mount and the INS.

FLAPPER GUIDE. Provides flapper alinement with INS air intakes.

DIAMOND GUIDE PIN, Ensures proper positioning and attachment of INS.

KEEPER ASSEMBLY. Provides latch points for the INS latch assembly.

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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1and9.

2.

3.

4.

5.

6.

7.

8.

10.

11.

12.

13.

14.

15.

16.

HANDLES. Provides lifting and transportability aids for maintenance personnel.

WARRANTY SEAL. Provides cover seals to preclude unauthorized entry into unit.

HEAT EXCHANGER. Provides airfIow to remove heat from the chassis.

RUN /RESET SWITCH-INDICATOR, Provides NPU program run indication and reset control.

IDENTIFICATION DECAL. Provides NPU nomenclature, part number, and serial number.

MOUNTING HOOK. Provides mounting point for NPU mount holddown retainers.

, CONSOLE LOCK. Locks out the Virtual Console Port and causes the NPU to begin processing the operationalflight program at power-up.

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

POWER CONNECTOR. Provides main power inputs to the NPU.

ELAPSED TIME METER. Displays total NPU operating time in hours.

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

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

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

GROUND LUG. Provides NPU chassis to aircraft wiring ground connection.

FUSES. Provides 10 amp NPU circuit protection.

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.

1-12

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LOCATION AND DESCRIPTION OF MAJOR CDU COMPONENTS

1.

2.

3.

4.

5.

IDENTIFICATION DECAL. Provides CDU nomenclature, part number, and serial number.

ELAPSED TIME METER. Displays total CDU operating time in hours.

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

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

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

1-13

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LOCATION AND DESCRIPTION OF MAJOR SDC COMPONENTS

1-14

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1.

2.

3.

4.

5.

6.

7.

8.

9.

10.

11.

12.

13.

14.

15.

COOLING FINS. Provides cooling by natural convection to side mounted fins.

POWER/SIGNAL 1/0 CONNECTOR, Provides input power and signal interface connection to aircraft wiring.

MOUNTING HOOK. Provides mounting point for TACAN mount holddown retainer.

WARRANTY SEAL. Provides seals to preclude unauthorized entry into the unit.

INSTRUMENT 1/0 CONNECTOR. Provides interface for Aeronautical Radioinstruments buses.

BK DATA BUS CONNECTOR. Provides interface for backup serial data bus B.

PRI DATA BUS CONNECTOR. Provides interface for primary serial data bus A.

PS1 FAIL INDICATOR. Provides power supply card fault detection display.

A2 FAIL INDICATOR. Provides ARINC processor card fault detection display.

Al FAIL INDICATOR. Provides AMUX card fault detection display.

BRACKET. Provides for securing the SDC to the TACAN.

ELAPSED TIME METER. Displays total SDC operating time in hours.

IDENTIFICATION DECAL. Provides SDC nomenclature, part number, and serial

WARRANTY DECAL. Provides warranty information and instructions.

Incorporated (ARINC) flight

number,

INSTALLATION /REMOVAL DECAL. Provides SDC/aircraft installation history data.

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LOCATION AND DESCRIPTION OF MAJOR TACAN RT COMPONENTS

1-16

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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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1and

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.

5and

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.

8and11. 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.

13and14, GUIDE PINS. Ensures proper positioning and attachment of TACAN RT.

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Table 1-5. IINS

Item Value

WEIGHTS AND DIMENSIONS

INS

Weight

Length

Width

Height

INS Mount

Weight

Length

Width

Height

NPU

Weight

Length

Width

Height

NPU Mount

Weight

Length

Width

Height

CDU

Weight

Length

Width

Height

SDC

Weight

Length

Width

Height

TACAN RT

Weight

Length

Width

18.73 kg (41.20 lb)

459.486 mm (18.09 in.)

191.008 mm (7.52 in.)

193.548 mm (7.62 in.)

2.54 kg (5.60 lb)

372.11 mm (14.65 in.)

251.96 mm (9,92 in.)

35.56 mm (1.40 in. )

40.82 kg (90.00 lb)

614.426 mm (24.19 in. )

337.82 mm (13.30 in.)

193,548 mm (7.62 in.)

2.27 kg (5.00 lb)

567.944 mm (22.36 in.)

279.4 mm (11.00 in.)

48.26 mm (1.90 in. )

4.54 kg (10.00 lb)

165.1 mm (6.50 in.)

146.05 mm (5.75 in.)

180.975 mm (7. 125 in. )

4.54 kg (10.00 lb)

373.38 mm (14.70 in. )

70.86 mm (2.79 in. )

204.47 mm (8.05 in. )

13,61 kg (30.00 lb)

369.316 mm (14.54 in.)

171.196 mm (6.74 in. )

Equipment Data

Item Value

Height 172.466 mm (6.79 in. )

TACAN Mount

Weight

Length

Width

Height

IINS

INS

NPU

CDU

SDC

0.90 kg (2.00 lb)

439,4 mm (17,30 in.)

266.7 mm (10.50 in.)

212.3 mm (8.36 in.)

POWER REQUIREMENTS

Total system AC power re-quirements, 2500 volt am-peres (VA) maximum

Total system DC power re-quirements, 359 watts maxi-mum

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

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

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

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

Backup power (battery), 16.0to 30.0 VDC, 240 wattsmaximum

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

24.0 to 32.0 VDC

0 to 5V, 380 to 420 Hz, 10VA maximum

24.0 to 28.5 VDC, 50 wattsmaximum

24.0 to 28.5 VDC. 50 wattsmaximum

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

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Table 1-5. IINS Equipment Data - Continued

Item Value Item Value

ENVIRONMENTAL SDC

INS Temperature:

Temperature: Operating

Operating -40”C (-40”F) to +71°C(+ 160”F)” Non-operating

Non-operating -54”c (-65”F) to +95”c(+203”F) Altitude

‘Provided proper cooling air requirements are met. —Cooling air

Altitude:

Steady-state

Intermittent(2 min max)

Cooling air

NPU

Temperature:

Operating

Non-operating

Altitude

CDU

Temperature:

Operating

Non-operating

Altitude

Cooling air

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

TACAN RT

Temperature:+ 18,288 m ( + 60,000 ft) to

+24,384 m (+80,000 ft) Operating

3.6 pounds per minute maxi-mum

Non-operating

-55”c (-67°F) to +71°c Altitude

(+160°F)Cooling air-62°C (-79°) to +95°C

-54°c (-65°F) to +55°c(+131°F)

-62°C (-79°F) to +85°C(+185°F)

+ 9144 m (30,000 ft) maxi-mum

Natural convection to sidemounted cooling fins

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

Intermittent and 0.5-hour in-tervals: + 95°C ( + 203°F)

-62°C (-80°F) to +95°C( + 2 0 3 ° F )

+21,336 m (70,000 ft) maxi-mum

internal blower

(+202°F)

+24,384 m ( +80,000 ft) max-imum

Natural conduction to sidemounted heat exchanger.Heat exchanger fan draws40 cubic feet per minute

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

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

-64°C (-83°F) to +71°C(+160°F)

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

Natural convection and con-duction to mounting panel

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Section III. PRINCIPLES OF OPERATION

1-14 PRINCIPLES OF OPERATION.

1-14.1 The IINS provides accurate knowledge of air-craft navigation parameters including present position,velocity, altitude, and heading information. The IINS iscapable of short- and/or long-range missions and can beupdated wherever TACAN navigation facilities exist ormanually without TACAN data. A serial data bus isemployed for data exchange within the IINS and theexternal avionic systems. The multiplex data bus systemconsists of two separate buses (A and B). Only one busis active at any given time, with the other bus in astandby mode for redundancy purposes. As shown infigure 1-2, the multiplex data buses provide a path fordata flow between the INS, SDC, NPU, CDU, and theexternal mission systems. Data to and from the TACANRT is first processed by the SDC before it is applied tothe multiplex data buses.

1-14.2 The INS provides inertial reference for theIINS which includes aircraft velocity, altitude, positionheading, and attitude. The INS operates by sensingaircraft accelerations from a gyro-stabilized, four-gim-bal, all-attitude platform. Output functions of the INSinclude accurate present-position and velocity data,

course-line computations, steering commands, and an-gular pitch, roll, and heading information. The naviga-tion and guidance computations are performed by ageneral-purpose digital computer using a semiconduc-tor memory. The computer steering commands arereferenced either to great-circle route to the desireddestination coordinates, or to a selected magneticcourse from the coordinates of the position at whichthe selected magnetic course steering mode was se-lected.

1-14.3 The NPU provides computer processing andinput /output operation for the IINS. System level com-putations are performed by the NPU to implement thefollowing IINS integration functions: system executiveand master schedular; TACAN RT/inertial updating;TACAN RT automatic tuning; primary bus controller;system level built-in test; NPU built-in self-test; backupmode logic/control (other than NPU failure); and alti-tude data processing/slant range compensation. TheNPU contains a central processor unit (CPU) thatdirectly addresses 64K 16-bit words of core memory forinstructions and data. The CPU is microprogrammedand decodes the operands and performs the required

Figure 1-2. IINS Block Diagram

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arithmetic, logic and control functions. The CPU con-trols the operation of the 1/0 section of the NPU forcommunications with other units over the multiplexdata buses.

1-14.4 The CDU displays data and controls the oper-ating modes of the IINS. The CDU is capable ofentering, changing, and recalling data from the NPU,INS, and TACAN RT; receiving data from the aircraftaltimeter encoder. This data is encoded and displayedon the CDU CRT as navigational and operational statusinformation. In addition, the CDU provides mode con-trol to the INS and TACAN RT. Electrical power tothe INS and TACAN RT is also controlled by the CDU.The CDU also acts as backup bus controller for themultiplex data buses in the event of an NPU failure.

1-14.5 The SDC performs data processing to convertthe TACAN RT Aeronautical Radio Incorporated(ARINC) inputs and outputs to corresponding serialdata formats for transmission over the multiplex databuses to the NPU and CDU. The SDC can communi-cate via one of the two multiplex data buses, Althoughthe SDC communicates over only one multiplex databus at a time, it can monitor both buses continuously todetermine over which bus valid data communicationsare taking place. Redundant portions of the SDC circui-try are isolated to ensure that a failure of one bus doesnot degrade performance of the remaining bus. The

SDC also provides ARINC characteristic digital param-eters to the aircraft flight instruments.

1-14.6 The position error of an inertial navigationsystem increases with time, therefore, a position refer-ence sensor is used to update the inertial data, andthereby bound the time-growing position error. TheIINS derives position updates from the TACAN RTrange and bearing measurements. The TACAN RTdetermines the relative bearing of the aircraft from aselected TACAN ground station and determines thedistance or range of the station. The TACAN RToperates within 390 nautical miles of a TACAN groundstation. Since the TACAN system operating limit is lineof sight, the actual operating range is dependent onaircraft altitude. The TACAN system operates on aselected channel from 252 available channels. The 252channels are equally divided into 126 x-channels and126 y-channels with both x- and y-channels spaced at 1MHz intervals. Upon being interrogated by the TACANRT, the ground station beacon transmits a signal. Fromthis signal the TACAN RT computes the values ofbearing and distance for updating the inertial systeminformation. The TACAN RT outputs are processed bythe SDC for compatibility with the multiplex databuses. The TACAN RT also produces and transmitsdistance information when interrogated in the air-to-airoperation by another TACAN-equipped aircraft, how-ever, this air-to-air mode precludes using the TACANinformation to update the IINS.

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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 arecontained on the CDU. The CDU controls and indica-tors are illustrated in figure 2-1 and listed, with func-tional descriptions, in table 2-1.

2-2 CDU DATA DISPLAY PAGE DESCRIPTIONS.

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

preflight and flight. Each page consists of eight lineswith up to 19 characters on each line. In most caseseach line is divided into the left side and right side.Each side contains information pertinent to the opera-tion of the IINS. On both sides of lines 1, 3, 5, and 7there are line select keys which perform functions asdefined by the line legend adjacent to the line selectkey. Table 2-1 describes the function of the line selectkeys. Following are typical illustrations and descriptionsof each CDU data display page.

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Figure 2-1. Controls and Indicators

2-2

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Control orKey Indicator

Table 2-1. CDU Controls and Indicators

Function

1 Data display

2 Line selectkeys

3

4

5

6

Alphanumerickeys

CLR key

BRT control

0 key

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

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

1. legend (TH 358.3 ). If the arrow points toward the legend anumeric entry (entered into the scratch pad on line 8) is allowed bypressing 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 de-scribed by the legend. For example, pressing the line select keyadjacent 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 indicatescurrent mode status and pressing the adjacent line select key willchange the mode. If no arrow appears next to a legend then that lineselect key performs no operation

4. Up or down pointing arrows on the sixth line of the data displayallows operator to slew display one page up or down by pressing pageslew toggle switch up or down

Alphanumeric entries are made by pressing one of the ten character keyson the keyboard and will appear first in the scratch pad (line 8), Eachactuation of a key will cause a character to be displayed from left toright 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 successiveactuations of the KLM /5 key. The 0-9 and . keys shall enter therespective number or decimal point unless the keyboard is in the lettermode. When the LTR/USE key is pressed, LTR is annunciated to theright of the scratch pad, and the next keystroke will enter an alphacharacter. When the desired data appears in the scratch pad, it will beentered by pressing the line select key adjacent to the data beingupdated, When the line select key is pressed, the scratch pad contentswill be checked for proper range and format. If the entry is valid, itwill be transferred to the IINS, read back, and displayed adjacent tothe line select key. Completion of this cycle will clear the scratch pad

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

Controls brightness of the data display from full on to full 05

Used to enter number 0 into the scratch pad

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Table 2-1. CDU Controls and indicators - Continued

Control orKey Indicator Function

8

9

10

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

LTR/USE key When pressed, allows letters to be entered into the scratch pad. Whenpressed a second time, signals the CDU to use the character that wasjust entered, and deletes LTR entry mode

FACK key When pressed, signals the system that an annunciated failure has beenrecognized by the operator, and causes the flashing annunciation to goto a steady annunciation

Page select Selects the type of information to be displayed. The following fiveswitch categories of display pages can be selected:

1. POS. Provides provisions for entering present position; universaltransverse mercator (UTM) or latitude/longitude (L/L) selection.Provides provisions for entering magnetic variation, true and mag-netic; ground track; and ground speed. TTG and TO/FROM annunci-ators; failed RT annunciation; NAV RDY in aline mode; UPDT inNAV mode

2. INS. Provides inertial alinement status; barometric pressure; altitude;data zeroize; and access to system data and unit tests; time in alinemode; steering and destination number selected; failed RT; UPDT inNAV; TTG and TO/FROM NAV RDY in aline annunciations

3. DEST. Provides selected course entry; destination coordinates; UTMor L/L selection; range, bearing, and time to destination; cardinalheading/distance; steering and destination number selected; failed RTannunciation; UPDT annunciator in NAV; NAVRDY; last markdesignation

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 inNAV; TTG and TO/FROM annunciators

5. TCN. Provides both TACAN control and station data. The TACANcontrol page provides power control; mode selection; slant range andbearing to station; update enable; and access to station pages. TheTACAN station pages provide station number magnetic variationentry; coordinates, channel entry; slant range/bearing entry; andelevation entry. Number of selected station and number of stationupdating. Failed RT numbers; NAVRDY; UPDT; TO/FROM; channelselection and selection of auto or manual mode

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Table 2-1. CDU Controls and Indicators - Continued


NOTE

All five pages above provide scratchpadfor entering data.

11 Mode selectswitch

12

13

DEST switch

BIT indicator

Selects eight different modes of operation for theIINS. The mode selectswitch selects the following IINS modes of operation:

1.

2.

3.

4.

5.

6.

7.

8.

OFF. Turns off the IINS (removes power from TACAN RT, INS, andCDU)

FAST. In this position the INS either performs a stored headingalinement or best available true heading (BATH) alinement. If aBATH alinement is performed, true or magnetic heading informationmust be entered not later than 1 minute after selecting the FASTmode. If magnetic heading information is not entered, system willassume a stored heading. After heading information is entered, presentposition may be entered if desired

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

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

UPDT. In this position the NPU freezes present position data for alater manual position update by overflying a known position desig-nated by a mark

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

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

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

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

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

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Table 2-1. CDU Controls and Indicators – Continued


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

Used to signal the INS to note the current present position and use it forone of two of the following purposes:

15 MRK key

1. Store as a markpoint (destination A thru F) when the mode selectswitch is in the NAV position

2. Store present position relative to selected destination for possibleupdating when mode select switch is in the UPDT position

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

2-6

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 lineselect keys as required to obtain the above display.

(2-7 blank)/2-8

2.

3.

4.

5.

6.

7.

8.

TM 11-5826-302-12

1. LINE 1. The left side displays the page label. The right side displays true beading (TH). Entered true heading willbe accepted only during the first 80 seconds of a fast alinement. Arrow indication goes off after navigation mode isselected.

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

LINE 3. The left side displays magnetic variation (MV). At power turon, the INS computed variation isindicated. If a magnetic variation is entered, the entered value will be displayed and used by the INS, An equalsign 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 indicationgoes off after the navigation mode is selected.

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.

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

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

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. Arrowindication goes off after navigation mode is selected. The right side displays that the UTM coordinates aredisplayed on lines 5 and 7, If adjacent line select key is pressed, the latitude and longitude (L/L) coordinates aredisplayed on lines 5 and 7, respectively. Latitude and longitude are displayed in degrees/minutes/seconds.

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

2-9

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POSITION PAGE (L/L)

NOTE

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

2-10

TM 11-5826-302-12

1. LINE 1. The left side displays the page label. The right side displays true heading (TH). Entered true heading willbe accepted only during the first 60 seconds of a fast alinement. Arrow indication goes off after navigation mode isselected.

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 thefirst 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 duringthe first 2 minutes of gyrocompass or BATH alinement. Arrow indication goes off after navigation mode isselected. The right side displays that latitude and longitude (L/L) coordinates are indicated. If adjacent line selectkey 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 isentered 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.

2-12

1.

2.

3.

4.

5.

6.

7.

8.

TM 11-5826-302-12

LINE 1. The left side displays the page label and selected destination and steerpoint. The right side displays thatthe zeroize page can be selected by pressing the adjacent line select key.

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

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

LINE 4. Not used.

LINE 5. The left side displays barometric pressure (BARO), Barometric pressureor FAST alinement. Arrow indication goes off after navigation mode is selected.DATA page can be selected by pressing the adjacent line select key.

. .

must be entered during NORMThe right side displays that the

LINE 6. The left side is reserved for annunciations described later. The right side displays the destination locationin which the last mark was stored.

LINE 7, The left side displays INS alinement time and goes from 0.0 (INS turn on) to a maximum of 99,9minutes. 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).

LINE 8. This line is the scratch pad. Data entered from the CDU keyboard first appears on this line before it isentered 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.


3. LINE 3. The left side displays that sensitive data can be zeroized by pressing the adjacent line select key. Theright 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 thatthe 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 canbe selected by pressing the CDU page slew switch down.



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. Afterthe line select key is pressed, the word GO will be replaced with a blank. After completion of the test, the theword GO or FAIL will be displayed. The right side displays the status of the NPU. Either GO or FAIL will becontinuously 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 theline select key is pressed, the word GO will be replaced with a blank, After completion of the test, the word GOor 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.




2-17

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NOTEThis 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.


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 adjacentline select key.


5. LINE 5. The left side displays that the I06 data page can be selected by pressing the adjacent line select key. Theright side displays that the I07 data page can be selected by pressing the adjacent line select key.


7. LINE 7. The left side displays INS miscellaneous data addresses. Addresses that can be entered should be indecimal format with a range of 0 to 65,535. The right side displays the contents of the addressed memorylocation. 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 isentered 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

1.

2.

3.

4.

5.

6.

7.

8.

TM 11-5826-202-12

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

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

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


LINE 5. The left side displays an address. The arrow pointing down on the right side indicates that the contentsof the addressed memory location is displayed on line 6.


LINE 7. This line displays that the DATA page can be selected by pressing the CDU page slew switch down.

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

2-21

TM 11-5826-302-12

NOTE

These pages are selected from the DATA page by pressing line 5 left or right lineselect 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 notused at the operator or aviation unit level.

2-22

TM 11-5826-302-12

1,3,5,

and7. 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.


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 afourth time will reset back to displaying set one.

8. LINE 8. Not used<

2-23

TM 11-5826-302-12

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.

3and4. 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 pagecan be selected by pressing the CDU page slew switch down.

7. LINE 7. This line displays roll in units of degrees/minutes.


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 lineselect 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 destinationmay be selected by pressing the CDU DEST switch up or down to increment or decrement the selecteddestination by one. The right side displays desired course (true) to destination. When the system is first turned onall courses to destination will default to previously entered data.


3. LINE 3. The left side displays current range (RNG) to the selected destination in kilometers. The right sidedisplays 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 isdisplayed 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 selecteddestination. 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) gridzone 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 iscalculated 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 UTMcoordinates 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.


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 lineselect key as required to obtain the above display.

2-28

TM 11-5826-302-12

1.

2.

3.

4.

5.

6.

7.

8.

LINE 1. The left side displays the page label and selected destination (D2) and steerpoint (S3). A new steerpointmay be selected by pressing the CDU STR switch up or down to increment or decrement the selected steerpointby one provided the steer points have been entered as destinations. The right side displays desired selected truecourse to the selected steerpoint. If a course to destination has not been previously entered, the CDU willcommand the INS to use zero degrees as the desired course.

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

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

LINE 4. The left side displays time-to-go (TTG) to the selected steerpoint. If TTG is greater than 2 minutes, it isdisplayed 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 selectedsteerpoint. The distance is calculated assuming a flat earth.

LINE 5. The left side displays the universal transverse mercator (UTM) steerpoint grid zone and spheroid. Theright 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.

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

LINE 7. The left side displays steerpoint area casting, and northing. The right side indicates that the UTMcoordinates 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.

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.

2.

3.

4.

5.

6.

7

8.

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

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

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

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

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 andprovide automatic updates to the INS, Also, when in UPDT mode, numbers will appear to indicate the number ofstations updating out of the number of active stations.

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

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

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

2-31

TM 11-3826-302-12

TACAN STATION PAGE

NOTE

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

2-32

TM 11-5824-302-12

1. LINE 1. The left side displays the age label and TACAN station number. The right side displays whether aTACAN 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.


3. LINE 3. The left side displays magnetic variation (MV) which must be entered for each TACAN station. Systemwill 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 tunedTACAN station. The right side displays bearing (BRG) from magnetic north to the currently tuned TACANstation.

5. LINE 5. The left side displays the universal transverse mercator (UTM) TACAN station grid zone and spheroid orlatitude, The right side displays TACAN station elevation (thousands of feet). Resolution is provided to thenearest 10 feet.

6. LINE 6. The left side is reserved for annunciations described later. The right side displays that additional TACANstation (STA) pages can be selected by pressing the CDU page slew switch up or down to increment or decrementthe station number displayed.

7. LINE 7. The left side displays TACAN station area, casting, and northing or longitude. The right side indicatesthat the UTM coordinates are displayed on lines 5 and 7. If adjacent line select key is pressed, the latitude andlongitude (L/L) coordinates are displayed on lines 5 and 7, respectively. Latitude and longitude are displayed indegrees/minutes/seconds.


2-33

TM 11-5826-302-12

MARK OPERATION PAGE

NOTE

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

2-34

TM 11-5826-302-12

1.

2.

3.

4.

5.

6.

7.

8.

LINE 1. The left side displays the page label and selected destination (D2) and steerpoint (S3). A new steerpointmay be selected by pressing the CDU STR switch up or down to increment or decrement the selected steerpointby one provided the steer points have been entered as destinations. The right side displays current desired truecourse to the selected steerpoint. If a course to destination has not been previously entered, the CDU willcommand the INS to use zero degrees as the desired course.

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

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

LINE 4. The left side displays time-to-go (TTG) to the selected steerpoint. If TTG is greater than 2 minutes, it isdisplayed 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 selectedsteerpoint. The distance is calculated assuming a flat earth.

LINE 5. The left side displays the universal transverse mercator (UTM) steerpoint grid zone and spheroid. Theright 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,

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

LINE 7. The left side displays steerpoint area, easting, and northing. The right side indicates that the UTMcoordinates 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.

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 thescratch 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 isselected, TACAN updating is deleted,

2-36

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.


3. LINE 3. The left side displays current range (RNG) to the selected destination in kilometers in UTM mode andnautical 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 isdisplayed 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 atrue 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 andnautical miles in L/L mode, to a true north/south line intersecting the selected destination. The distance iscalculated assuming a flat earth.

6. LINE 6. The left side is reserved for annunciations described later. The right side is not used.



2-37

TM 11-5826-302-12

ACCEPT/REJECT PAGE

NOTE

To select this page, set CDU mode select switch to UPDT and press MRK key toobtain 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.


3. LINE 3, The left side displays current range (RNG) to the selected destination in kilometers in UTM mode andnautical 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 isdisplayed 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 atrue east /west line intersecting the selected destination. The right side displays the north/south correction thatwill be sent to the NPU to correct the system present position if that update is accepted. The distance iscalculated 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 andnautical miles in L/L mode, to a true north/south line intersecting the selected destination. This distance will beapplied as the east/west correction to the system present position if the update is accepted. The distance iscalculated 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 thedata 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 directlyover the entered destination at the time of MARK and that the proper destination isdisplayed at the top of the page. Verification that the cardinal distances on lines 4and 5 are reasonable (within a few tenths of a kilometer if manual position updatinghas been performed or within current system error indications if position updatingwas not performed) is an approved method of this verification.


2--39

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 datapage). Data appearing on lines 1 (l), 3 (3), 4 (4), 5 (5), 7 (7), and 8 (8) will be whatever is applicable to the pageselected. The following is a summary of messages that are presented and the failures /condition they represent:

2 - 4 0

TM 11-5826-302-12

Message Failure/Condition Line

MSC

NPU

INU

ADC

TCN

PFM

TTG(flashing)

TO

FROM

Scu

NAVRDY(steady)

NAVRDY(flashing)

ATTD

DEGRD

UPDT

DEGUPD

Mission system computer interface has failed

NPU has failed

INS navigation processing has failed. Attitude may bevalid

Air data (altimeter) is invalid

TACAN RT has failed or is turned off

Post flight maintenance is required

Aircraft is within 2 minutes of selected steerpoint

Distance to steerpoint is decreasing

Distance to steerpoint is increasing

Signal data converter has failed or ARINC bus has failed

During alinement. INS attitude data and degradednavigation performance are available

During alinement. Full INS navigation performance isavailable

The INS is in attitude mode due to:

a. Operator selection

b. INS failure

c. DATA bus failure. Attitude data are valid

The INS is in navigate mode and a degraded performancealinement, not a full performance alinement, wasperformed

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

Degraded navigation mode updated by TACAN RT

NOTE

2

2

2

2

2

2

2

2

2

2

6

6

6

6

6

6

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

2-41

TM 11-5826-302-12

Section Il. OPERATOR PREVENTIVE MAINTENANCE

2-3 GENERAL.

2-3.1 There are no operator PMCS procedures. Referto aircraft technical manual TM 55-1520-237-10CL foraircraft preoperational procedures.

CHECKS AND SERVICES (PMCS)

Section III. OPERATION UNDER USUAL CONDITIONS

During operation no combination ofCDU control settings will cause damageto the equipment or create a hazard topersonnel, however, if the aircraft INSpower circuit breakers were disengagedwithin 10 seconds after setting the CDUto OFF mode, equipment damage willoccur.

2-4 ASSEMBLY AND PREPARATION FOR USE.

2-4.1 There is no assembly of the IINS at the operatorlevel, The equipment is installed in the aircraft byaviation unit level maintenance personnel. There is nospecial switch settings required before the equipment isput into operation.

2-5 INITIAL ADJUSTMENTS AND SELF TEST.

2-5.1 Initial Adjustments. There are no initial adjust-ments for the IINS.

2-5.2 Self Test. Self test procedures are performed byaviation unit level personnel.

2-6 OPERATING PROCEDURE.

2-6.1 The operating procedure for the IINS consists ofa description of each type of data that can be enteredfrom the CDU into the system, typical data entry,preoperational, inflight, and shutdown procedures.

2-6.2 Data Entry Description. The following para-graphs describe each type of data that can be enteredinto the IINS.

2-6.2.1 Alphanumeric Entry. Alphanumeric entries aremade by pressing one of the ten character keys on thekeyboard. The character first appears on the data dis-play scratch pad (line 8). Actuation of a key causes acharacter to be displayed from left to right on the

scratch pad. The numbered and decimal keys enter therespective number or decimal point unless the keyboardis in the letter mode. When the LTR/USE key ispressed, LTR will be indicated on the right side of thescratch pad, and the next key pressed will enter analpha character. In the UTM mode, pressing keys withalpha characters above them will put the first alphacharacter associated with that key on the scratch pad.Successive actuations of the key will cause the secondand third characters to appear. When the desired char-acter is displayed, pressing the LTR/USE key a secondtime signals the CDU to use that character. When theCDU is signaled to use the character displayed, itautomatically reverts back to the numeric mode, In thecase where successive alpha characters appear, theLTR/USE key must be pressed twice to use the charac-ter previously entered, and enter the alpha mode for thenext character. When the position, destination, andTACAN pages are displayed and latitude/longitudeformat is selected, actuation of ABC/N2, GHJ/W4,NPQ/E6, and UVW/S8 keys will enter N, W, E, and Srespectively. These are the only letters that can beentered in this mode. In all other circumstances when inthe alpha mode, the alphas above the key pressed willappear. Once the desired data appears on the scratchpad, it is entered by pressing the line select key adjacentto the data being updated. When the line select key ispressed, the scratch pad contents will be checked forproper range and format. If the entry is valid, it will betransferred to the IINS, read back, and displayed adja-cent to the line select key. Completion of this cycleclears the scratch pad.

2-6.2.2 Error Checking. Several checks are performedon entered data before it appears on the line and thescratch pad is cleared. Failure to pass these checks willcause one of three of the following messages to bedisplayed alternately with the unused entry inscratch pad:

ENTRY ERROR - indicatesnot passed range and formatCDU (e.g., course of 3700).

that the entered datachecks performed by

the

hasthe

2-42

TM 11-5826-302-12

2 - 4 3

TM 11-5826-302-12

ILLEGAL ENTRY - indicates that the entered data isinconsistent with IINS operation (e.g., entry of trueheading in navigation mode).

ENTRY IGNORED – IINS has neither accepted norrejected entered data. Entry status is undetermined.

2-6.2.3 Magnetic Heading or True Heading Entry.Magnetic heading or true heading may be enteredduring the first 60 seconds of a best available trueheading (BATH) alinement. Scratch pad entries may beup to four numeric digits including an optional decimalpoint. If no decimal point is entered, whole degrees areassumed. Leading zeros are optional.

2-6.2.4 Present Position Entry. Present position mayhe entered only during the first 2 minutes of normalalinement, or first 2 minutes of a BATH alinement aftermagnetic or true heading has been entered. Arrowsadjacent to present position coordinates cue the opera-tor when entry is permitted. Either latitude/longitudeor universal transverse mercator (UTM) coordinatesmay be entered. Coordinate selection is provided ondata display line 7 right.

2-6,2.4.1 Latitude Entry. Scratch pad entries may be2, 3, 4, 5, or 6 numeric digits preceded by an optionalN or S. The first two digits are degrees, the third andfourth are minutes, and the fifth and sixth are seconds.If any digits are not entered, zeroes will be assumed. Ifthe N or S is not entered, the previously displayed valuewill be assumed. If the entered latitude is less than 10°,a leading zero must be entered. If a leading zero is notentered, an error message will flash.

2-6.2.4.2 Longitude Entry. Scratch pad entries may be3, 4, 5, 6, or 7 numeric digits preceded by an optional Eor W. The first three digits are degrees, the fourth andfifth are minutes, and the sixth and seventh are seconds.If any digits are not entered, zeroes will be assumed. Ifthe E or W is not entered, the previously displayedvalue will be assumed. If the entered longitude is lessthan 100°, a leading zero (two leading zeros if less than10°) must be entered. If a leading two zeros are notentered, an error message will flash.

2-6.2.4.3 Spheroid and Grid Zone Entry. Scratch padentries may be made for spheroid and grid zone, justspheroid or just grid zone. Spheroids are numeric entryand alpha indicationfor spheroid models:

Code

according to the following codes

Spheroid Abbrevi-Model ation

0 International INT

2-44

1 Clark 1866 CL6

2 Clark 1880 CL0

3 Everest EVR

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

Grid zone entries consist of one or two numbers and analpha character. Spheroid entries consist of code num-bers 0 thru 10.

2-6.2.4.4 Area/Eastings/Northings Entry. Scratch padentries may be made for area and eastings/northings,just area, or just eastings/northings. Entries for areamust consist of two alpha characters. Entries for east-ings/northings must be 2, 4, 6, 8 or 10 digits. Any datanot entered, the system will presume all previous en-tries are valid. Digits will be evenly split betweencastings and northings with trailing zeros inserted.Although entries may be made and sent to the INS to aresolution of 2 meters, the display will round to thenearest 10 meters.

2-6.2.5 Magnetic Variation Entry. Scratch pad entriesconsist of an E or w and up to four numeric digitsincluding decimal point. If no-decimal point is entered,whole degrees are assumed. The range of entries is O.OO

to E 179.9° or W 180.0°.

2-6.2.6 Manually Entered Field Altitude. Field alti-tude must be entered to the nearest 100 feet (mean sealevel) during alinement. The range of valid entries isfrom -1000 to +65,520 feet in increments of 100 feet.

2-6.2.7 Barometric Pressure Entry, Barometric pres-sure must be entered to the nearest 0.01 inches Hgduring alinement.

2-6.2.8 Destination Coordinate Entry. Destination co-ordinates may be entered during any phase of themission. Either latitude/longitude or UTM coordinatesmay be entered. The operator can enter up to 16destinations. These destinations can be used for steer-points or overfly fixes. When a destination is selected asa steerpoint, steering information (range, bearing, timeto go, course deviation) is computed for the CDU andaircraft instruments. An overfly fix requires that theflyover point be entered as a destination. When a markis performed the stored coordinates in destinations A

TM 11-5826-302-12

thru F are replaced with markpoint position data. Themark locations are used in sequence (A, B, C, D, E, F,A, B, etc.). Entry of destination coordinates is identicalto entry of present position coordinates as described inparagraph 2-6.2.4,

2-6.2.9 Course to Destination Entry. The desired truecourse to destination may be entered for each destina-tion during any phase of the mission. Scratch pad entryrequirements are the same as for magnetic or trueheading as described in paragraph 2-6.2.3, Up to fournumeric digits may be entered with an optional decimalpoint. If no decimal point is entered, whole degrees areassumed.

2-6.2.10 TACAN Station Magnetic Variation Entry.TACAN station magnetic variation can be enteredduring any phase of the mission and entry is the same asmagnetic variation entry described in paragraph 2-6.2.5.

2-6.2.11 TACAN Station Position Entry. TACAN sta-tion position entry can be made during any phase of themission. Station position entry is performed the same aspresent position coordinates as described in paragraph2-6.2.4. Either latitude/longitude or UTM coordinatesmay be entered.

2-6.2.12 TACAN Station Channel Entry. TACAN sta-tion channel entry can be made during any phase of themission. The TACAN station pages provide the capabil-ity to enter station channel for each of the 16 stations.A total of 252 channels are possible (126 X channelsand 126 Y channels). Unless otherwise specified, it isassumed an X channel has been entered.

2-6.3 Typical Data Entry. Data entry onto the CDUscratch pad and into the system is basically the same forall datathat can be entered. For any particular datathat is required to be entered, the correct CDU datadisplay page must be selected, the mode select switchmust be in the applicable position, and the correctkeyboard and line select keys pressed.

2-6.4 Preoperational Procedures. The preoperationalprocedures consist of NPU loading, alinement, destina-tion/steering data entry, and TACAN data entry proce-dures. The NPU loading and alinement procedures mustbe performed on the ground before the IINS can be

placed in the navigation mode of operation and theaircraft can be moved, Entry of destination and TA-CAN data can be performed during alinement, afteralinement, or during any phase of the mission if desired.Refer to paragraphs 2-6.2.8 thru 2-6.2.12 for a descrip-tion of destination and TACAN data that can be en-tered.

2-6.4.1 NPU Loading Procedure. Refer to technicalmanual TM 11-6625-3099-13 for the NPU loading pro-cedure.

NOTE

TACAN and destination data (except de-sired course) will be retained in memoryfrom turnon to turnon unless zeroized.

2-6.4.2 Alinement Procedures. Alinement proceduresare performed on the ground when the IINS is firstturned on. The alinement procedures consist of a nor-mal or fast alinement. Fast alinement consists of twotypes of stored alinements and a best available trueheading (BATH) alinement. A stored alinement (provid-ing limited degraded system accuracies) can be per-formed if the aircraft has not been moved since lastnormal alinement (and the mode switch not set toNAV) and turnoff. A second stored alinement (provid-ing degraded systems accuracies as indicated in table1-1) can be performed if the aircraft has not beenmoved since the last normal alinement (and the modeswitch set to NAV) and turnoff. BATH alinement isperformed if the aircraft has been moved since lastnormal alinement and turnoff.

2-6.4.3 Destination/Steering Data Entry Procedure.Destination/steering data entry procedures can be per-formed during alinement, afteralinement, or during anyphase of the mission. The following procedure is per-formed after alinement with the system in the NAVmode.

2-6.4.4 TACAN Data Entry Procedure, TACAN dataentry procedures can be performed during alinement,after alinement, or during any phase of the mission. Thefollowing procedure is performed after alinement withthe system in the NAV mode.

2-45

TM 11-5826-302-12

NORMAL ALINEMENT

2-46

TM 11-5826-302-12

NORMAL ALINEMENT

1.

2.

3.

4.adjacent

5.

NOTE

CDU display will remain blank for 30 seconds after turnon. Present position must beentered within 2 minutes of turnon. Barometric pressure and altitude must beentered during alinement.

During alinement, data display line 6 left (6) may have a steady indication ofNAVRDY. Alinement will be complete when NAVRDY begins to flash.

Ensure that aircraft power is applied to the system.

NOTE

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

Set mode select switch (28) to NORM,

Set page select switch (30) to POS.

Observe that data display line 7 right (7) displays L/L T. If data display line 7 right (7) displays UTM pressline select key (12).

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

NOTE

Present position data must be entered for each normal alinement. The followingsteps are examples of entering present position data. Substitute your own presentposition data when performing these steps.

When making keyboard entries, if an incorrect key is pressed, press CLR key (22), asrequired, 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°1030.

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. Observethat data display line 8 (8) displays W 1183530.

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9. Press data display line 7 left (7) line select key (35). Observe that data display line 7 left (7) displaysW118°35 30.

10. Set page select switch (30) to INS.

NOTE

When entering position altitude, altitude must entered to the nearest 100feet (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), andNPQ/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 -AALT8.6.

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 -BARO29.01.

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 storedalinement (with limited degraded accuracies) is to be performed following thenormal 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 pressuremust be entered during alinement.

Alinement will be complete when data display line 6 (6) displays a flashing NAVRDYif a normal alinement was performed and the mode select switch was not set toNAV.

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 If data display line 7 right (7) displays UTM pressadjacent line select key (12).

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

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 yourown barometric pressure when performing these steps. Enter local barometricpressure to the nearest 0,01 inches Hg.

When making keyboard entries, if an incorrect key is pressed press CLR key (22) asrequired, 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.


10. Observe that data display line 7 (7) displays alinement time and status. Data display line 6 left (6) displays aflashing 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 magneticheading must be entered during the first 60 seconds of turnon. Present position mustbe entered within 2 minutes of turnon. Barometric pressure and altitudeentered 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.

must be

4. Observe that data display line 7 right (7) displays L/L If data display line 7 right (7) displays UTM , pressadjacent line select key (12).

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

NOTE

The following steps are examples of entering present position data. Substitute yourown present position and heading data when performing these steps. Either trueheading or magnetic heading can be entered. Magnetic heading is entered bypressing line select key (10). The following example uses true heading.

When making keyboard entries, if an incorrect key is pressed, press CLR key (22) asrequired, 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) displaysTH = 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 thatdata 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°1030.

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) displaysW118°35 30.

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

NOTE

When entering present position altitude, altitude must be entered to the nearest 100feet (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 8,600feet.

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.


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 thealpha mode.

NOTE

When making keyboard entries, if an incorrect key is pressed, press CLR key (22), asrequired, 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 datadisplay 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 UTMadjacent 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 - 18TCL6.

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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 thealpha 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 datadisplay 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 -UV23456780.

19. Set mode select switch (28) to OFF.

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TACAN DATA ENTRY

(2-59 blank) /2-60

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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) displaysTACAN ON.

4. Observe that data display line 3 left (3) displays T/R. If it does not, press data display line 3 left (3) lineselect key (37).

NOTE

Allow 90 seconds for TACAN warmup, X in the following steps represents somenumber.

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 , pressadjacent line select key (12).

NOTE

When making keyboard entries, if an incorrect key is pressed, press CLR key (22) asrequired, 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 -MVW79.9.

11. If data display line 8 right (8) does not display LTR, press LTR/USE key (26) to place the keyboard in thealpha 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 datadisplay 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) lineselect 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 CH10X.

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 EL0.00.

21. Press data display line 7 right (7) line select key (12). Observe that entered station latitude and longitudecoordinates change to UTM coordinates.

22. Press data display line 1 left (1) line select key (38). Observe that data display line 1 left (1) displaysTACAN OFF.

23, Set mode select switch (28) to OFF.

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2-6.5 Inflight Procedures. Inflight procedures consistsof selecting various data diplay pages for viewing

following procedures explain mark opertion, manual(overfly) position updating, and selecting steerpoints.

navigation data, entering destination and TACAN data Refer to paragraphs 2-6.2.8 thru 2-6.2.12 for a descrip-selecting steerpoints, selecting the update mode, mark tion of destination and TACAN data that can be en-opertion, and manual (overfly) position updating. The tered.

MARK OPERATION

NOTE

Current aircraft position may be stored in one of the markpoint locations (destina-tions A thru F) by pressing the MRK key. The mark indication will appear in line 8on any page selected. The following procedure uses the steer page, The marklocations 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 latestmark is stored is displayed in the scratch pad; such as MARK A.

(2-63 blank)/2-64

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MARK OPERATION

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MANUAL (OVERFLY) POSITION UPDATING

2 - 6 6

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MANUAL (OVERFLY) POSITION UPDATING

NOTE

An overfy update represents a manual position update technique which the pilotoverflies his selected destination and signals the INS by pressing the MRK key, andsubsequently 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) displaysdisplay line 7 right (7) displays REJECT

3. If the update data is acceptable, press line select key (35) that is adjacent to data displaydisplayed 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 REJECT-displayed 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

2 - 6 8

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SELECTING STEERPOINTS

NOTE

The operator can enter up to 16 destinations. These destinations can be used forsteerpoints during an phase of the mission. When a destination is selected as asteering information range, bearing, time to go, course deviation) is computed forthe CDU and aircraft instruments. If a mark(s) has been performed during themission, the stored coordinates in destinations A thru F have been replaced withmarkpoint 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 bedisengaged for at least 10 seconds afterselecting the OFF mode.

2-6.6 Shutdown Procedure. Shutting down the IINSconsists of setting the CDU mode select switch to OFF.

2-7 OPERATION OF AUXILIARY EQUIPMENT.

2-7.1 There is no auxiliary equipment supplied withthe IINS. For operation of interfacing avionics equip-ment, 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 theaircraft is capable of flying in.

2-9 EMERGENCY PROCEDURES,

2-9.1 In the event of loss of any subsystem, the IINSwill provide backup mode capability to the maximumfeasible extent. If there is an NPU failure, the CDUassumes the data bus control functions, and IINS navi-gational performance will be as specified for free iner-tial performance. If an INS failure should occur, TA-CAN-derived position will be available if the NPU and

interface functions remain operational. The degradedmodes of performance are listed in table 2-2.

2-1O JAMMING AND ECM PROCEDURES.

2-10.1 The only piece of equipment subject to jam-ming or electronic countermeasures (ECM) would bethe TACAN. If the TACAN signal is interfered with,the TACAN can be shut down and the system canprovide inertial navigation without the aid of the TA-CAN, however, updating can be accomplished manu-ally.

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Table 2-2.

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Table 2-2.

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CHAPTER 3

OPERATOR MAINTENANCE

There are no operator maintenance procedures. Referto aircraft technical manual TM 55-1520-237-10CL foraircraft preoperational procedures.

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CHAPTER 4

AVIATION UNIT MAINTENANCE

Section 1. LUBRICATION

4-1 GENERAL.

4-1.1 There are no lubrication instructions for theIINS.

Section Il. IINS

4-2 SERVICE UPON RECEIPT OF MATERIEL.

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

4-3 UNPACKING INSTRUCTIONS.

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

4-4 CHECKING UNPACKED EQUIPMENT.

4-4.1 IINS units are inspected for damage incurredduring shipment, checked for complete shipment, andequipment modifications by AVIM personnel. Equip-ment checking bypersonnel consiststable 4-1.

Aviation Unit Maintenance (AVUM)of performing the actions listed in

INSTRUCTIONS

UPON RECEIPT

4-5 DEPROCESSING UNPACKED EQUIPMENT.

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

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

4-6.1 No special tools, special test equipment, ormaterials are required to install the INS, NPU, CDU,SDC, or the TACAN RT. The CDU is installed with a9/32 in. flat-tip screwdriver.

4-7 INSTALLATION OF INS, NPU, AND TACANMOUNTS.

4-7.1 Refer to aircraft technical manual TM 11-1520-237-23 for installation of the INS, NPU, and TACANmounts.

4-8 INSTALLATION OF INS.

4-8.1 Perform INS installation as follows:

4-1

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Table 4-1. IINS Service Upon Receipt Inspection Data

Location Item Action Remarks

14

2.

3.

4.

5.

6.

INS and INS mount,NPU and NPU mount,CDU, SDC, and TA-CAN RT and TACANmount

INS, NPU, CDU,SIX, and TACAN RT

INS, NPU, CDU,SDC, and TACAN RTand TACAN mount

INS and INS mount,NPU and NPU mount,CDU, SDC, and TA-CAN RT and TACANmount

NPU, CDU, and TA-CAN mount

CDU

Control surfaces a. Inspect for dents and scratchesand covers b. Reject control surfaces and cov-

Controls and a.indicators

b.

Connector a.

b.

Mounting a.hardware b.

Lamps and a.fuses

b.

Knobs a.

b.

ers if damage prevents themfrom functioning properly

Inspect for broken, bent, orscratched parts

Reject control or indicator

(1) . .

(2)

(3)

(4)

If damage prevents themfrom functioning properly

If control cannot be rotatedthrough its complete rangewithout any binding orscraping

If toggle and pushbuttonswitches cannot operatesmoothly

If glass surfaced indicatorscannot be cleaned properly

Inspect for bent, burned or bro-ken pins

Reject connectors

Inspect for bent or broken parts

Reject mounting hardware ifdamage prevents it from func-tioning properly

Inspect for broken or burnedparts

Reject lamps or fuses

Inspect for broken parts

Reject knobs

—

Process to Avia-tion IntermediateMaintenance (AVIM)

—

Process to AVIM

—

Process to AVIM

---

Process to AVIM

Refer to section Vfor replacement

- .

Refer to section Vfor replacement

4-2

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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 electronicequipment,

When handling the INS, do not lift or carry by the latch assembly.

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

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

3. Check that mount gasket is in proper position and isnot deformed or damaged.

4. Remove plastic protective dust covers from INSconnectors.

5. Press two latch releases (1) to release latch assembly 6. Place latch assembly (2) in open position. Hold the(2). INS (3) by the latch assembly and support it from the

bottom. Place INS on mount (4) and slide inwardengaging 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 assem-bly has engaged keeper assembly (6) and is in lockposition. Verify the latch assembly has latched bypulling 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 beforeinstalling NPU. Refer to aircraft technical manual TM 11-1520-237-23 for NPUpower removal procedure.

The NPU weighs approximately 90 pounds. Use at least two persons to lift and moveit,

When handling the NPU, use extreme care to prevent damage to precision elec-tronic equipment.

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

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

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

3. Remove plastic protective dust covers from NPUconnectors.

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

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6. For NPU interconnecting cable information refer toaircraft technical manual TM 11-1520-237-23. Con-nect aircraft cables to connectors (5, typical) of NPU(l).

7. Ensure that console lock (6) is connected to connec-tor 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 CDUinstalling CDU.

interconnecting

When handling the CDU, use extreme care to preventelectronic equipment.

1. Remove plastic protective dust covers from CDU 3. Carefully pushconnectors.

damage

cables before

to precision

CDU (3) into aircraft panel (4).

2. For CDU interconnecting cable information, refer toaircraft technical manual TM 11-1520-237-23. Con-nect 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 intercon-necting cables before installing SIX.

When handling the SIX, use extreme care to prevent damage to precision electronicequipment.

L Ensure that TACAN mount is installed in accordancewith paragraph 4-7.

2. Remove plastic protective dust covers from SDCconnectors.

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

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

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5. For SDC interconnecting cable information refer toaircraft technical manual TM 11-1520-237-23. Con-nect aircraft cables to connectors (5, 6, and 7) ofSDC (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 RTinterconnecting cables before installing TACAN RT.

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

1. Ensure that TACAN mount is installed in accordancewith 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 inplace with two knurled screws (4).

2. Remove plastic protective dust covers from TACANRT connectors.

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

4-11

TM 11-5826-302-12

4-13 INTERCONNECTIONS.

4-13.1 The IINS units are interconnected to aircraftavionics by aircraft cabling. Refer to aircraft technicalmanual TM 11-1520-237-23 for cabling diagrams.

4-14 PRELIMINARY SERVICING AND ADJUST-MENT OF EQUIPMENT.

4-14.1 No prelimimary servicing or adjustment of theequipment is required at the organizational level, how-ever when replacing an INS, ensure that unit is incurrent calibration.

5. For TACAN RT interconnecting cable information,refer to aircraft technical manual TM 11-1520-237-23. Connect aircraft cables to connectors (7, 8, and 9)of TACAN RT (l).

6. Position bracket (3) over TACAN RT (1) handle andsecure with two knurled screws (4).

4-12

Section Ill. AVIATION UNIT PREVENTIVE

4-15 PMCS PROCEDURES.

MAINTENANCE

Table 4-2.

TM 11-5826-302-12

CHECKS AND SERVICES (PMCS)

Aviation Unit Preventive MaintenanceChecks and Services

4-15.1 The PMCS procedures are contained in table4-2. Progressive phase maintenance concepts permit Item Item To Bemaintenance intervals to be determined by the mainte- No. Proceduresnance office.

1

2

3

4

5

6

7

8

9

10

11

12

13

14

Faultindicators

Airflow

Surfaces andcovers

Mountingsurfaces

Mount guidepins

Controls andindicators

Connectors

Mountinghardware

Lamp andfuse covers

Lamps andfuses

Knobs

Panelnomenclature

CDU CRTsurface

Equipment ingeneral

Check for fault indicatorbeing set (all white)

Check that airflow is notblocked to rack mountedunits

Check for scratches anddents. Cheek that coversare secure

Check that mounting sur-faces on mounts do nothave dents or scratches

Check that mount guidepins are not bent

Check for broken, bent, orscratched parts

Check for bent, burned, orbroken pins

Check for bent or brokenparts

Check for broken or miss-ing parts

Check for broken or miss-ing parts

Check for broken orcracked parts

Check for illegible or oblit-erated markings

Check for excessive accu-mulation of dirt

Check for excessive accu-mulation of dirt and de-bris

4-13

TM 11-5826-302-12

Section IV. IINS TROUBLESHOOTING PROCEDURES

4-16 GENERAL. at any time during the mission, a bus failure has occur-

4-16.1 Organizational troubleshooting of the IINS red, refer to aircraft technical manual TM 11-1520-237-

consists of performing the INS/NPU, CDU, and TA- 23 for corrective action. All IINS units must be in-

CAN RT/SDC self test procedures in the sequence stalled in the aircraft during troubleshooting. Refer to

given. Whenever a corrective action is required, refer aircraft technical manual TM 11-1520-237-23 for cover-

to section V and replace the defective unit then rerun age of the INS, NPU, and TACAN mounts.

the required self test procedure to verify the repair. Ifthe CDU indicates a PFM system status message on line 4-17 INS/NPU SELF TEST PROCEDURE.

2, regardless of selected page (except NPU data page), 4-17.1 Perform INS self test procedure as follows:

INS/NPU SELF TEST PROCEDURE

NOTE

This test takes approximately 14 minutes. Ifmately 14 minutes, the system will perform an


allowed to continue beyond approxi-aline gyro bias.

2. Set CDU mode select switch (28) to TEST, data display screen illuminates after 30 seconds. Adjust BRTcontrol for desired illumination.


4. Observe that data display line 7 (7) displays elapsed time. After approximately 14 minutes the timer willreset 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 accessthe 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 breakerswithin 10 seconds after setting CDU to OFF mode.

9. Set CDU mode select switch (28) to OFF.

4-14

TM 11-5826-302-12

4 - 1 5

TM 11-5826-302-12

4-18 CDU SELF TEST PROCEDURE.

4-18.1 Perform CDU self test procedure as follows:

CDU SELF TEST PROCEDURE


2. Set CDU mode select switch (28) to NORM, data display screen illuminates after 30 seconds. Adjust BRTcontrol for desired illumination.


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 CDUFAIL 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.



4-16

TM 11-5826-302-12

4-17

TM 11-5826-302-12

4-19 TACAN RT/SDC SELF TEST PROCEDURE.

4-19.1 Perform TACAN/RT SDC self test procedureas follows:

TACAN RT/SDC SELF TEST PROCEDURE


2. Set CDU mode select switch (28) to NORM, data display screen illuminates after 30 seconds. Adjust BRTcontrol for desired illumination.


4. Press data display line 1 left line select key (38). Observe data display line 1 left (1) displays TACAN ON.

5. Observe that data display line 3 left (3) displays 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 TCNFAIL 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, iffuse is good, replace the TACAN RT.


13. Press data display line 1 left (1) line select key (38). Observe data display line 1 left (1) displays TACANOFF.



4-18

TM 11-5826-302-12

4-19

TM 11-5826-302-12

4-20. CALIBRATION (GYRO BIAS). complete. The gyro bias factors are automatically up-

4-20.1 The calibration mode is used during ground data and corrected when a flashing NAVRDY is &-

maintenance for the purpose of automatically comput- played. If deemed necessary by degraded navigation

ing gyro bias correction for all three platform axes. performance, the gyro bias function is accomplished as

Gyro bias mode requires approximately 90 minutes to follows:

CALIBRATION (GYRO BIAS)


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 If data display line 7 right (7) displays UTM pressadjacent line select key (12).

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

NOTE

Present position data must be entered for calibration. The following steps areexamples of entering present data. Substitute your own present position data whenperforming these steps.

When making keyboard entries, if an incorrect key is pressed, press CLR key (22), asrequired, 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 N341030.

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. Observethat data display line 8 (8) displays W1183530.

4-20

TM 11-5826-302-12

4-21

TM 11-5826-302-12

10. Press data display line 7 left (7) line select key (35). Observe that data display line 7 left (7) displays W1183530.

NOTE

The calibrate mode requires approximately 90 minutes to accomplish. Successfulcompletion is indicated by a flashing NAVRDY. The gyro bias information will beautomatically stored in memory. Turning the system off prior to issuance of theflashing 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 breakerswithin 10 seconds after CDU to OFF mode.


4-22

TM 11-5826-302-12

4-21 GENERAL.

4-21.1 IINS unit maintenance includes repair of theIINS by replacement of NPU fuses, CDU lamps andknobs, TACAN mount fuse, and replacement of INS,NPU, CDU, SDC, and TACAN RT units. Failed unitsare forwarded to AVIM.

4-21.2 The normal test procedure is to perform theoperational check to verify the malfunction. The mal-function symptoms should be furnished by the aircrew/operator but can be obtained or verified by mainte-nance personnel performing the IINS troubleshootingprocedures in section IV.

4-21.3 Repairs are verified by repeating the opera-tional check.

4-21.4 Refer to TM 1l-5826-302-20P for repair partsand special tools list.

4-22 IINS OPERATIONAL CHECK.

4-22.1 The operational check of the IINS consists ofperforming the STD INS/NPU, CDU, and TACANRT/SDC self test procedures in paragraphs 4-17, 4-18,and 4-19.

4−23 4−23 REMOVAL AND INSTALLATION OF NPUFUSES.

4-23.1 Perform NPU fuses removal and installation asfollows:

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 removalprocedure.

NOTE

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

4-23

TM 11-5826-302-12

1. Unscrew and remove each fuseholder cap (1) fromNPU (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.

INSTALLATION ,

1. Install fuse (4) into fuseholder (3) and install fuse-holder into NPU.

2. Screw fuseholder (3) to NPU (2).

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

4-24

TM 11-5826-302-12

4-24 REMOVAL AND INSTALLATION OF CDULAMPS.

4-24.1 Perform CDU lamps removal and installationas follows:

REMOVING/INSTALLING CDU LAMPS

TOOLS: None

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

REMOVAL:

To prevent damage to caps, do not usetools to remove caps from front panelassembly.

1. Carefully pull each cap (1 and 2) out of CDU frontpanel assembly (3).

INSTALLATION :

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

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

2. Remove lamp (4) from cap (1).

4-25

TM 11-5826-302-12

4-25 REMOVAL AND INSTALLATION OF CDUKNOBS.

4-25.1 Perform CDU knobs removal and installationas 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/installingknobs.

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

4-26

TM 11-5826-302-12

REMOVAL:

1. Using 5/64 in. hex head wrench, loosen two set-

2,

3.

screws (1) on each knob (2 and 3) securing knobs toCDU front panel assembly (4).

Remove knobs (2 and 3) from CDU front panelassembly (4).

Using .035 in. hex head wrench, loosen two set-screws (5) securing knob (6) to CDU front panelassembly (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 panelassembly (4).

3.

4.

Install knobs (2 and 3) to CDU front panel assembly(4).

Using 5/64 in. hex head wrench, tighten two set-screws (1) on each knob (2 and 3) securing knobs toCDU front panel assembly (4).

4-27

TM 11-5826-302-12

4-26 REMOVAL AND INSTALLATION OF TACANMOUNT FUSE.

4-26.1 Perform TACAN mount fuse removal and in-stallation as follows:

REMOVING/INSTALLING TACAN MOUNT FUSE

TOOLS: None

Ensure that aircraft power is removedinstalling fuse.

from the TACAN mount before removing/

REMOVAL:

1. Remove TACAN RT as described in paragraph 4-32to gain access to TACAN mount fuse.

2. Unscrew fuseholder (1) from TACAN mount (2).

3. Remove fuseholder (1) from TACAN mount (2) andseparate fuse (3) from fuseholder by pulling one fromthe other.

INSTALLATION:

1. Install fuse (3) into fuseholder (1) and install fuse-holder into TACAN mount (2).

2. Screw fuseholder (1) to TACAN mount (2).

3. Install TACAN RT as described in paragraph 4-32.

4-28

TM 11-5826-302-12

4-27 REMOVAL AND INSTALLATION OF INS, 4-28 REMOVAL AND INSTALLATION OF INS.NPU, AND TACAN MOUNTS. 4-28.1 Perform INS removal and installation as fol-

4-27.1 Refer to aircraft technical manual TM 11-1520- lows:237-23 for installation of the INS, NPU, and TACANmounts.

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 electronicequipment,

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 theINS.

4-29

TM 11-5826-302-12

REMOVAL:

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

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

3. Install plastic protective dust covers on INS connec-tors.

INSTALLATION,

1. Remove plasticconnectors.

protective dust covers from INS

2. With latch assembly (2) in the open position, holdthe INS (3) by the latch assembly and support it fromthe bottom. Place INS on mount (4) and slide inwardengaging guide pins and the connectors.

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

4-30

TM 11-5826-302-12

4-29 REMOVAL AND INSTALLATION OF NPU.

4-29.1 Perform NPU removal and installation as fol-lows:

REMOVING/INSTALLING NPU

TOOLS: None

Ensure that aircraftremoving/installing

power is removed from the NPU interconnecting cables beforeNPU. 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 moveit.

When handling the NPU, use extreme care to prevent damage to precision elec-tronic equipment.

NOTE

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

4-31

TM 11-2826-202-12

REMOVAL:

1. DiSConneCt aircraft cables from connectors (1, typi-cal) of NPU (2).

2. Loosen and release two self-locking holddown retain-ers (3) from two mounting hooks (4).

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 NPUconnectors.

2. Place NPU (2) on mount (5) and slide inward engag-ing the guide pins.

3. Position two self-locking holddown retainers (3) on

4.

5.

two mounting hooks (4) and tighten self-lockingholddown retainers securing NPU to mount.

For NPU interconnecting cable information, refer toaircraft technical manual TM 11-1520-237-23. Con-nect aircraft cables to connectors (1, typical) of NPU(2).

Ensure that console lock (6) is connected to connec-tor J11.

4-32

TM 11-5826-302-12

4-30 REMOVAL AND INSTALLATION OF CDU.

4-30.1 Perform CDU removal and installation as fol-lows:

REMOVING/INSTALLING CDU

TOOLS: 9/32 in. flat-tip screwdriver

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

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

4-33

TM 11-5826-302-12

REMOVAL:

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

2. Carefully pull CDU (2) out of aircraft panel (3).

3. Disconnect two aircraft cable connectors (4) fromCDU (2).

4. Install plastic protective dust covers on CDU connec-tors.

INSTALLATION:

1. Remove plastic protective dust covers from CDUconnectors.

2. For CDU interconnecting cable information refer toaircraft technical manual TM 11-1520-237-23. Con-nect two aircraft cable connectors (4) to CDU (2).

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

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

4-24

TM 11-5826-302-12

4-31 REMOVAL AND INSTALLATION OF SDC.

4-31.1 Perform SDC removal and installation as fol-lows:

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 shortperiod of time after a flight (even if the equipment was never turned on). To preventinjury to personnel, allow SDC to cool or wear protective hand covering prior toremoving the SDC.

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

4-36

TM 11-5826-302-12

REMOVAL:

1. Disconnect aircraft cables from connectors (1, 2, and3) of SDC (4).

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 connec-tors .

INSTALLATION:

1.

2.

3.

4.

Remove plastic protective dust covers from SDCconnectors.

Place SDC (4) on mount (9) and slide inward engag-ing the connector.

Position self-locking holddown retainer (5) on mount-ing hook (6) and tighten self-locking holddown re-tainer securing SDC to mount. Position bracket (8)over TACAN RT handle and tighten two knurledscrews (7).

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

4-38

TM 11-5826-302-12

432 REMOVAL AND INSTALLATION OF TACANRT.

4-32.1 Perform TACAN RT removal and installationas 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 precisionelectronic equipment.

4-37

TM 11-5826-302-12

REMOVAL:1. Disconnect aircraft cables from connectors (1, 2, and

3) of TACAN RT (4).

2. Loosen and release two self-locking holddown retain-ers (5) from two mounting hooks (6), Loosen twoknurled screws (7) and lift bracket (8). Retighten twoknurled 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 RTConnectors.

INSTALLATION:

1. Remove plastic protective dust covers from TACANRT connectors.

2. Place TACAN RT (4) on mount (9) and slide inwardengaging the guide pins.

3. Position two self-locking holddown retainers (5) on

4.

two mounting hooks (6) and tighten self-lockingholddown retainers securing TACAN RT to mount.Position bracket (8) over TACAN RT (4) handle andtighten two knurled screws (7).

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

4-38

4-33 PLACING IINS IN SERVICE.

4-33.1 Refer to paragraph 422 and perform the IINSoperational check to verify repairs and complete lidchecks.

434 CDU CLEANING.

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

Do not use sharp tools or volatile sol-vents. Avoid excessive pressure on glass.Failure to comply may result in damageto 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.

Section VI. IINS PREPARATION

b.

c.

d.

e.

f.

TM 11-5826-302-12

NOTE

If glass cannot be cleaned thoroughlywith a dry lint-free clod proceed withsteps b thru f.

Prepare a cleaning solution of water and mildliquid detergent.

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

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

Wipe dry with clean, lint-free cloth.

Inspect glass surface for cleanliness making cer-tain that no residue is present. If further cleaningis required, repeat steps b thru f.

FOR STORAGE OR SHIPMENT

4-35 PREPARING IINS FOR STORAGE OR SHIP-MENT.

4-35.1 The IINS is not packaged in a single container.IINS units are prepared for storage or shipment byAVIM 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 2408-16Component Removal and Repair/Overhaul Record . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DA Form 2410Discrepancy in Shipment Report . . . . ......... . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . SF 361Quality Deficiency Report . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . ......... ...... SF 368

Recommended Changes to Publications and Blank Forms . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DA Form 2028

Recommended Changes to Equipment Technical Publications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DA Form 2028-2Report of Discrepancy.................. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SF 364

A-3 TECHNICAL MANUALS.

Administrative Storage of Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Aviation Unit and Intermediate Maintenance Manual, EH-60A

Helicopter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Intermediate Maintenance Manual, Inertial Navigation SetAN/ASN-141 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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

Operators Manual, EH-60A Helicopter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Operator’s, Organizational, and Direct Support Maintenance Manual,Test Set Group OQ-329/U . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Organizational Maintenance Manual, TACAN Navigational SetAN/ARN-118 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Procedures for Destruction of Electronics Materiel to PreventEnemy Use (Electronics Command) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Repair Parts and Special Tools List for Integrated InertiaINavigation System AN/ASN-132(V) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

TM 740-90-1

TM 11-1520-237-23Series

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

TM 11-7021-202Series

TM 55-1520-237-10CL

TM 11-6625-3099-13

NAVAIR 16-30 ARN118-2

TM 750-244-2

TM 11-5826-302-20PThe 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/ResponseMultiplex Data Bus . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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

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

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

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

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

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

Functional Users Manual for the Army MaintenanceManagement System-Aviation (TAMMS-A) . . . . . . . . . . . . . . . . . . . . . . .

MIL-STD-1553

AR 750-50

CTA 8-100

DA Pam 25-30

SB 11-654

AR 55-38

CTA 50-970

DA Pam 738-751

A-2

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) as-signs maintenance functions in accordance with theThree Levels of Maintenance concept for Army avia-tion. These maintenance levels (categories) - AviationUnit Maintenance (AVUM), Aviation IntermediateMaintenance (AVIM), and Depot Maintenance - aredepicted on the MAC as:

AVWM, which corresponds to an O Code in the RepairParts and Special Tools List (RPSTL)

AVIM, which corresponds to an F Code in the RepairParts and Special Tools List (RPSTL)

DEPOT, which corresponds to a D Code in the RepairParts and Special Tools List (RPSTL)

B-1.2 The maintenance to be performed below depotand in the field is described as follows:

B-1.2.1 Aviation Unit Maintenance (AWM) activitieswill be staffed and equipped to perform high frequency“On-Aircraft” maintenance tasks required to retain orreturn aircraft systems to a serviceable condition. Themaintenance capability of the AWUM will be governedby the Maintenance Allocation Chart (MAC) and lim-ited by the amount and complexity of ground supportequipment (CSE), facilities required, authorized man-ning strength and critical skills available. The rangeand quantity of authorized spare modules/componentswill be consistent with the mobility requirements dic-tated by the air mobility concept. (Assignments ofmaintenance tasks to divisional company size aviationunits will consider the overall maintenance capability ofthe division, the requirement to conserve personnel andequipment resources, and air mobility requirements.)

B-1.2.1.1 Company Size Aviation Units: Performthose tasks which consist primarily of preventive main-tenance and maintenance repair and replacement func-tions associated with sustaining a high level of aircraftoperational readiness. Perform maintenance inspectionsand servicing to include preflight, daily, intermediate,periodic (or phased), and special inspections as autho-rized by the MAC or higher headquarters, Identify the

cause of equipment/system malfunctions using applica-ble technical manual troubleshooting instructions, built-in test equipment (BITE), installed aircraft instruments,or test, measurement, and diagnostic equipment(TMDE). Replace worn or damaged modules/compo-nents that do not require complex adjustments or sys-tern alinement and which can be removed/installedwith available skills, tools, and ground support equip-ment. Perform operational and continuity checks andmake minor repair to the electrical system. Inspect,service and make operational, capacity, and pressurechecks to hydraulic systems. Perform servicing, func-tional adjustments, and minor repair/replacement tothe flight control, propulsion, power train, and fuelsystems. Accomplish air frame repair that does notrequire extensive disassembly, jigging, or alinement.The manufacture of air frame parts will be limited tothose items which can be fabricated with tools andequipment found in current air mobile tool and shopsets. Evacuate unserviceable modules/components andend items beyond the repair capability of AVUM to thesupporting AVIM.

B-1.2.1.2 Less than Company Size Aviation Units:Aviation elements organic to brigade, group, battalionheadquarter, and detachment size units are normallysmall and have less than ten aircraft assigned. Mainte-nance tasks performed by these units will be thosewhich can be accomplished by the aircraft crew chief orassigned aircraft repairman and will normally be limitedto preventive maintenance, inspections, servicing, spotpainting, stop drilling, application of nonstress patches,minor adjustments, module/component fault diagnosis,and replacement of selected modules/components. Re-pair functions will normally be accomplished by thesupporting AVIM unit.

B-1.2.2 Aviation Intermediate Maintenance (AVIM)provides mobile, responsive “One-Stop” maintenancesupport. (Maintenance functions which are not condu-cive to sustaining air mobility will be assigned to depotmaintenance). AVIM may perform all maintenancefunctions authorized to be done at A WM. Repair ofequipment for return to user will emphasize support or

B-1

TM 11-5826-302-12

operational readiness requirements. Authorized mainte-nance includes replacement and repair of modules/components and end items which can be accomplishedefficiently with available skills, tools, and equipment.AVIM establishes the Direct Exchange (DX) programfor AWM units by repairing selected items for returnto stock when such repairs cannot be accomplished atthe AVUM level. The AVIM level inspects, trou-bleshoots, performs diagnostic tests, repairs, adjusts,calibrates, and alines aircraft system modules/compo-nents. AVIM units will have capability to determine theserviceability of specified modules/components re-moved prior to the expiration of the Time BetweenOverhaul (TBO) or finite life. Module/component disas-sembly and repair will support the DX program andwill normally be limited to tasks requiring cleaning andthe replacement of seals, fittings, and items of commonhardware. Air frame repair and fabrication of parts willbe limited to those maintenance tasks which can beperformed with available tools and test equipment.Unserviceable reparable modules/components and enditems which are beyond the capability of AVIM torepair will be evacuated to Depot Maintenance. AVIMwill perform aircraft weight and balance inspectionsand other special inspections which exceed AWMcapability. provides quick response maintenance sup-port, including aircraft recovery and air evacuation, on-the-job training, and technical assistance through theuse of mobile maintenance contact teams. Maintainsauthorized operational readiness float aircraft. Providescollection and classification services for serviceable/unserviceable material. Operates a cannibalization ac-tivity in accordance with AR 750-50. (The aircraftmaintenance company within the maintenance battalionof a division will perform AVIM functions consistentwith air mobility requirements and conservation ofpersonnel and equipment resources. Additional interme-diate maintenance support will be provided by thesupporting nondivisional AVIM unit.)

B-2 USE OF THE MAINTENANCE ALLOCATIONCHART (Section II),

B-2.1 The Maintenance Allocation Chart assigns main-tenance functions to the lowest category of mainte-nance based on past experience and the following con-siderations:

B-2.1.1 Skills Available,

B-2.2 Only the lowest category of maintenance autho-rized to perform a maintenance function is indicated, Ifthe lowest maintenance category cannot perform alltasks of any single maintenance function (e.g., test,repair), then the higher maintenance level(s) that canaccomplish additional tasks will also be indicated.

B-2.3 A maintenance function assigned to a mainte-nance category will automatically be authorized to beperformed at any higher maintenance category.

B-2.4 A maintenance function that cannot be per-formed at the assigned category of maintenance for anyreason may be evacuated to the next higher mainte-nance category. Higher maintenance categories willperform the maintenance functions of lower mainte-nance categories when required or directed by thecommander that has the authority to direct such task-ing.

B-2.5 The assignment of a maintenance function will“not be construed as authorization to carry the relatedrepair parts or spares in stock. Information to requisi-tion or otherwise secure the necessary repair parts willbe as specified in the associated Repair Parts and Spe-cial Tools List (RPSTL).

B-2.6 Normally there will be no deviation from theassigned level of maintenance. In cases of operationalnecessity, maintenance functions assigned to a mainte-nance level may, on a one-time basis and at the requestof the lower maintenance level, be specifically autho-rized by the maintenance officer of the level of mainte-nance to which the function is assigned. The specialtools, equipment, etc. required by the lower level ofmaintenance to perform this function will be furnishedby the maintenance level to which the function isassigned. This transfer of a maintenance function to alower maintenance level does not relieve the highermaintenance level of the responsibility for the function.The higher level of maintenance will provide technicalsupervision and inspection of the function being per-formed at the lower level.

B-2.7 Changes to the Maintenance Allocation Chartwill be based on continuing evaluation and analysis byresponsible technical personnel and on reports receivedfrom field activities.

B-3 MAINTENANCE FUNCTIONS.

B-3.1 Maintenance functions will be limited to anddefined as follows:

B-2.1.2 Work time required. B-3.2 Inspect. To determine the serviceability of anitem by comparing its physical, mechanical, and/or

B-2.1.3 Tools and test equipment required and/or electrical characteristics with established standardsavailable. through examination (e.g., by sight, sound, or feel).

B-2

TM 11-5826-302-12

B-3.3 Test. To verify serviceability by measuring themechanical, pneumatic, hydraulic, or electrical charac-teristics of an item and comparing those characteristicswith prescribed standards.

B-3.4 Service. Operations required periodically tokeep an in proper operating condition, i.e., toclean (includes decontaminate, when required), to pre-serve, to drain to paint, or to replenish fuel, lubricants,chemical fluids, or gases.

B-3.5 Adjust. To maintain or regulate, within pre-scribed limits, by bringing into proper or exact position,or by setting the operating characteristics to specifiedparameters.

B-3.6 Aline. To adjust specified variable elements ofan item to bring about optimum or desired perform-ance,

B-3.7 Calibrate, To determine and cause correctionsto be made or to be adjusted on instruments or test,measuring, and diagnostic equipments used in precisionmeasurement. Consists of comparisons of two instru-ments, one of which is a certified standard of knownaccuracy, to detect and adjust any discrepancy in theaccuracy of the instrument being compared.

B-3.8 Remove/Install. To remove and install the sameitem when required to perform service or other mainte-nance functions. Install may be the act of emplacing,seating, or fixing into position a spare, repair part, ormodule (component or assembly) in a manner to allowthe proper functioning of an equipment or system.

B-3.9 Replace. To remove an unserviceable item andinstall a serviceable counterpart in its place. “Replace”is authorized by the MAC and is shown as the 3dposition code of the SMR code.

B-3.10 Repair. The application of maintenance serv-ices 1

, including fault location/troubleshooting2, re-moval/installation, and disassembly/assembl~ proce-dures, and maintenance actions4 to identify troubles andrestore serviceability to an item by correcting specificdamage, fault, malfunction, or failure in a part, subas-sembly, module (component or assembly), end item, orsystem,

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

2 Fault locate/troubleshoot - the process of inves-tigating and detecting the cause of equipment malfunc-tioning the act of isolating a fault within a system orunit under test (UUT).

B.3.11 Overhaul. That maintenance effort (service/action) prescribed to restore an item to a completelysereviceable/operational condition as required by main-tenance standards in appropriate technical publications(i.e., DMWR). Overhaul is normally the highest degreeof maintenance performed by the Army. Overhaul doesnot normally return an item to like new condition.

B-3.12 Rebuild. Consists of those services/actions nec-essary for the restoration of unserviceable equipment toa like new condition in accordance with original manu-facturing standards. Rebuild is the highest degree ofmateriel maintenance applied to Army equipment. Therebuild operation includes the act of returning to zerothose age measurements (hours/miles, etc.) consideredin classifying Army equipment/components,

B-4 FUNCTIONAL GROUPS (Columns 1 and 2).

B-4.1 The functional groupings shown in the samplebelow identify maintenance significant components,assemblies, subassemblies, and modules with the nexthigher assembly.

GroupNumber

04

0401

0402

0403

Description

POWER PLANT

ENGINE GENERAL

Servicing, handling, inspection require-ments, lubrication charts, overhauland retirement schedules. Externallines & hoses. (As applicable,)

COMPRESSOR SECTION(COLD SECTION MODULE)

Rotor, blades, vanes, impeller, stators,inlet guide vanes, main frame, parti-cle separator, bleed valve, bearings,seals, external lines & hoses.

COMBUSTION SECTION(HOT SECTION MODULE)

Liners, nozzles, stators, rotor, seals, cou-plings, blades.

3 Disassemble/assemble - encompasses the step-by-step taking apart (or breakdown) of a spare/func-tional group coded item to the level of its least compo-nency identified as maintenance significant (i.e., assignedan SMR code) for the category of maintenance underconsideration.

4 Actions - welding, grinding, riveting, straighten-ing, facing, remachining and/or resurfacing.

B-3

TM 11-5826-202-12

0404

0405

0406

0407

0408

0409

0410

POWER-TURBINE(POWER TURBINE MODULE)Nozzles, rotors, blades, exit guide vanes,

exhaust frame, drift shaft, bearings,seals, external lines and hoses.

ACCESSORY GEAR BOX(ACCESSORY SECTION MODULE)

input and output gears, seals, chip de-tector, housing drive shaft, bearings,seals.

FUEL SYSTEM

Fuel control, fuel boost pump, gover-nors, fuel filter assembly, sequencevalve, fuel manifold, fuel nozzle, ex-ternal lines and hoses.

ELECTRICAL SYSTEM

Electrical control units, exciters, ther-mocoupler, ignition harness, electri-cal cables, history record, torqueoverspeed sensor, Np sensor, alternatestator, blowers.

OIL SYSTEM

Tanks, oil filter, oil cooler, lube andscavenge pumps, oil filter bypass sen-sors, external lines and hoses.

DRIVE SYSTEM

Reduction gear assembly, output shaft,seal, bearing.

MISCELLANEOUS EQUIPMENT

(As applicable).

B-5 MAINTENANCE FUNCTION (Column 3).

B-5.1 Column 3 lists the functions to be performed onthe items listed in column 2.

B-6 MAINTENANCE CATEGORIES AND WORKTIMES (Column 4).

B-6.1 The maintenance categories (levels) AVUM,AVIM, and DEPOT are listed on the MaintenanceAllocation Chart with individual columns that include

the work times for maintenance functions at each main-tenance level. Work time presentations such as “0.1“indicate the average time it requires a maintenancelevel to perform a specified maintenance function. If awork time has not been established, the columnarpresentation shall indicate “ “. Maintenancelevels higher than the level of maintenance indicatedare authorized to perform the indicated function.

B-7 TOOLS AND TEST EQUIPMENT (Column 5and Section III).

B-7.1 Common tool sets (not individual tools), specialtools, test, and support equipment required to performmaintenance functions are listed alphabetically in Sec-tion III with a reference number to permit cross--referencing to column 5 in the MAC. In addition themaintenance category authorized to use the device islisted along with the item National Stock Number(NSN) and if applicable, the tool number to aid inidentifying the tool/device.

B-8 REMARKS (Column 6 and Section IV).

B-8.1 Remarks (identified by an alphabetic code incolumn 6) and other notes (identitfied by a number inparentheses in the applicable column) are listed inSection IV to provide a ready reference to the definitionof the remark/note.

B-4

TM 11-5826-302-12

Section II. MAINTENANCE ALLOCATION CHART

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

B-5

TM 11-5826-202-12

Section Il. MAINTENANCE ALLOCATION CHART - Continued

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

B-6

TM 11-5826-302-12

Tool or TestEquipmentReference

Code

1

2

3

4

5

Section III. TOOL AND TEST EQUIPMENT REQUIREMENTS


MaintenanceLevel

DEPOT

AVUM/DEPOT

AVUM/AVIM

DEPOT

DEPOT

Nomenclature

Bag, Anti-Static

Multimeter, DigitalAN/PSM-45

Tool Kit, ElectronicEquipment TK-101/G

Tool Kit, ElectronicEquipment TK-105/G

Work Station, Static

National/NATOStock Number

8105-01-120-3377

6625-01-139-2512

5180-00-064-5178

5180-00-610-8177

4940-01-087-3458

ToolNumber

B-7

TM 11-5826-302-12

Section IV. REMARKS


ReferenceCode Remarks/Notes

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

B Calibration (gyro bias) is performed on a powered-up aircraft when performanceexceeds the circular error for one hour flight (CEP) per technical manual, TM 11-5826-302-12.

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

D Built-in-test (BIT), automatic and switch activated, at the installed system level isperformed to verify system operational status. In the event of a malfunction thefailed 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 Antenna is provisioned as part of the aircraft, see TM 11-1520-237-23-3.

K INS Mount requires special precision alinement relative to the airframe. Removal ofINS mount is performed at AVIM level. Refer to reference code I above.

B-8

TM 11-5826-302-12

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 andbasic issue items for the IINS to help you inventoryitems required for safe and efficient operation.

C-2 GENERAL.

C-2.1 The Components of End Item and Basic IssueItems Lists are divided into the following sections:

C-2.2 Section II. Components of End Item. This list-ing is for informational purposes only, and is not au-thority to requisition replacements. These items arepart of the end item, but are removed and separatelypackaged for transportation or shipment. AS part of theend item, these items must be with the end item when-ever it is issued or transferred between property ac-counts. Illustrations are furnished to assist you in identi-fying the items.

C-2.3 Section 111, Basic Issue Items. There are noadditional items required to place the IINS in opera-tion, to operate it, and to perform emergency repairs.

C-3 EXPLANATION OF COLUMNS.

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

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

C-3.3 Column (2) - National Stock Number. Indi-cates the National Stock Number assigned to the itemand will be used for requisitioning purposes

C-3.4 Column (3) - Description. Indicates the Federalitem name and, if required a minimum description toidentify and locate the item, The last line for each itemindicates the Federal Supply Code for Manufacturer(FSCM) (in parentheses) followed by the part number.(Enter portions of next two sentences, only if applica-ble.) If item needed differs for different models of thisequipment, 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-3.5 Column (4) - Units of Measure (U/M). Indi-cates the measure used in performing the actual opera-tional/maintenance function. This measure is expressedby a two-character alphabetical abbreviation (e.g., ea,in, pr).

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

C-1

TM 11-5826-202-12

Section II. COMPONENTS OF END ITEM

C-2

TM 11-5826-302-12

(1)Illus

Number

1

2

3

4

5

6

7

8

Section Il. COMPONENTS OF END ITEM - Continued

(2)National Stock

Number

6605-01-135-6328

5826-01-012-1938

5826-01-142-3059

5826-01-041-2044

7035-01-166-7857

6605-01-107-2380

6605-01-206-8954

(3)Description Usable

FSCM and Part Number On Code

Control Display)

Unit C-l1097/ASN-132(V) (57045 622-6143-001

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

Signal Data Converter CV-3739/ASN-132(V) (06481) 886510-1

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

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

Navigation Processor Unit Mount (14345)105794

Inertial Navigation Set Mount (06481)880100-1

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

(4)

U/M

EA

EA

EA

EA

EA

EA

EA

EA

(5)QtyRqr

1

1

1

1

1

1

1

1

C-3/(C-4blank)

TM 11-5826-302-12

APPENDIX D

EXPENDABLE SUPPLIES AND MATERIALS LIST

Section 1. INTRODUCTION

D-1 SCOPE.

D-1.1 This appendix lists expendable supplies andmaterials you will need to operate and maintain theIINS. This listing is for informational purposes only andis not authority to requisition the listed items. Theseitems are authorized to you by CTA 50-970, Expend-able/Durable Items (Except Medical, Class V, RepairParts; and Heraldic Items), or CTA 8-100, Army Medi-cal Department Expendable/Durable Items.

D-2 EXPLANATION OF COLUMNS,

D-2.1 Column (1) – Item Number. This number isassigned to the entry in the listing and is referenced inthe narrative instructions to identify the material (e.g.,“Use cleaning compound, item 5, App. D“).

D-2.2 Column (2) - Level. This column identifies thelowest level of maintenance that requires the listeditem.

(Enter as applicable)

AVUM - Aviation Unit Maintenance

AVIM - Aviation Intermediate Maintenance

DEPOT - Depot Maintenance

D-2.3 Column (3) - National Stock Number. This isthe National Stock Number assigned to the item; use itto request or requisition the item.

D-2.4 Column (4) - Description. Indicates the Federalitem name and, if required, a description to identify theitem. The last line for each item indicates the FederalSupply Code for Manufacturer (FSCM) in parenthesesfollowed by the part number.

D-2.5 Column (5) – Unit of Measure (U/M). Indicatesthe measure used in performing the actual maintenancefunction. This measure is expressed by a two-characteralphabetical abbreviation (e.g., ea, in, pr). If the unit ofmeasure differs from the unit of issue, requisition thelowest unit of issue that will satisfy your requirements.

D-1

TM 11-5826-302-12

Section II. EXPENDABLE SUPPLIES AND MATERIALS LIST

(1) (2) (3) (4) (5)Item National Stock

Number Level Number Description U/M

1 AVUM 7920-00-044-9291 Cloth, Lint-Free BX

D-2

TM 11-5826-302-12

GLOSSARY

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

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

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

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

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

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

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

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

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

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

ATTD.. . . . . . . . . . . . . . . . . . . .

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

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

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

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

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

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

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

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

CEP . . . . . . . . . . . . . . . . . . . . . . . . . . .

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

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

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

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

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

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

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

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

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

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

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

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

FSCM . . . . . . . . . . . . . . . . . . . . . . . .

Section L

Altimeter altitude

Active

Aviation intermediatemaintenance

Aviation unit maintenance

Air-to-air receive

Air-to-air transmit/receive

Accept/reject

Air data computer

Altitude and heading

Aeronautical radioincorporated

Attitude

Barometric pressure

Best available true heading

Built-in test

Built-in test equipment

Bearing

Brightness

Calibrate

Control display unit

Circular error probability

Convergence factor

Channel

Central processor unit

Degraded

Degraded mode update byTACAN

Destination

Discrepancy in shipmentreport

Depot maintenanceinterservice supportagreement

Direct exchange

Electronic countermeasures

Equipment improvementrecommendation

Fault acknowledge

Federal supply code formanufacturer

ABBREVIATIONS

GS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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

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

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

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

INIT . . . . . . . . . . . . . . . . . . . . . . . . . .

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

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

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

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

L/L . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

Pod . . . . . . . . . . . . . . . . . . . .....

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

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

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

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

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

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

Ground speed

Ground support equipment

Ground track

Horizontal situationindicator

Inertial altitude

Initialize

Integrated inertial navigationsystem

Inactive

Inertial navigation set

Input/output

Latitude/longitude

Line replaceable unit

Maintenance allocation chart

Manually entered altitude

Military grid referencesystem

Magnetic heading

Mark

Mission system computer

Modified table oforganization and equipment

Magnetic variation

Navigate

Navigate ready

Normal

Navigation processor unit

National stock number

Post flight maintenancerequired

Preventive maintenancechecks and services

Position

Pitch, roll, and velocity

Receive

Range

Report of discrepancy

Repair parts and specialtools list

Receiver-transmitter

Glossary 1

TM 11-5826-302-12

Section 1. ABBREVIATIONS - Continued

SCU . . . . . . . . . . . . . . . . . . . . . . . . . . . . Signal converter unit

SDC . . . . . . . . . . . . . . . . . . . . . . . . . . . Signal data converter

SRNG . . . . . . . . . . . . . . . . . . . . . . . . Slant range

STA . . . . . . . . . . . . . . . . . . . . . . . . . . . . Station

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

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

TACAN . . . . . . . . . . . . . . . . . . . . . Tactical air navigation

TAMES . . . . . . . . . . . . . . . . . . . . . The Army maintenancemanagement system

TBO . . . . . . . . . . . . . . . . . . . . . . . . . . . Time between overhaul

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

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

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

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

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

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

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

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

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

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

True heading

TACAN input/output

Test measurement diagnosticequipment

Transmit/receive

Time-to-go

Update

Universal transversemercator

Section II. DEFINITIONS OF UNUSUAL TERMS

Unit under test

Volt amperes

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

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

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

Spheroid - An earth spheroid model used for comput-ing geodetic positions. Different models are used invarious parts of the world, IINS can accommodate thefollowing spheroid models:

Abbrevi-Spheroid Model ation

International INT

Clark 1866

Clark 1880

Everest

Bessel

Australian National

AiryHough

South American

Modified Everest

WGS-72

CL6

CL0

EVR

BSL

AUS

ARY

HGH

SAM

MEV

WGS

Universal Transverse Mercator (UTM) - A rectangularcoordinate system.

Glossary 2

TM 11-5826-302-12

ALPHABETICAL INDEX

Subject, Para Subject, Para

A

Adjustment of equipment, preliminary, 4-14

Alinement procedures, 2-6.4.2

Alphanumeric entry, 2-6.2.1

Area entry, 2-6.2.4.4

Assembly and preparation for use, 2-4

B

Barometric pressure entry, 2-6.2.7

c

Calibration (gyro bias), 4-20

Capabilities and features, IINS, 1-9

CDU

Cleaning, 4-34

Controls and indicators, 2-1

Installation, 4-10, 4-30

Page descriptions, 2-2

Removal, 4-30

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

Course to destination entry, 2-6.2.9

D

Data entry description, 2-6.2

Alphanumeric, 2-6.2.1

Area, 2-6.2.4.4

Barometric pressure, 2-6,2.7

Course to destination, 2-6.2.9

Destination coordinate, 2-6.2.8

Eastings, 2-6.2.4.4

Error checking, 2-6.2.2

Field altitude, 2-6.2.6

Grid zone, 2-6.2.4.3

Latitude, 2-6.2.4.1

Longitude, 2-6.2.4.2

Magnetic heading, 2-6.2.3

Magnetic variation, 2-6.2.5

Northings, 2-6.2.4.4

Present position, 2-6.2.4

Spheroid, 2-6.2.4.3

TACAN station channel, 2-6.2.12

TACAN station magnetic variation, 2-6.2.10

TACAN station position, 2-6.2.11

True heading, 2-6.2.3

Data processing set, see NPU

Reprocessing unpacked equipment, 4-5

Destination coordinate entry, 2-6.2.8

Destination/steering data entry procedure, 2-6.4.3

Destruction of Army electronics materiel, 1-3

Differences between models, 1-11

E

Eastings entry, 2-6.2.4.4

Emergency procedures, 2-9

Equipment data, 1-12

Equipment, purpose, 1-1.4

Error checking, 2-6.2.2

F

G

Grid zone entry, 2-6.2.4.3

H

I

IINS

Capabilities and features, 1-9

Operational check, 4-22

Purpose, 1-8

Semite, placing in, 4-33

Shipment, preparation for, 4-35

Storage, preparation for, 4-35

Index 1

TM 11-5826-302-12

ALPHABETICAL

Subject, Para

INDEX - Continued

Subject, Para

Unpacking instruction 4-3

Inflight procedures, 2-6.5

Initial adjustments, 2-5.1

Initial adjustments and self test 2-5

Initial adjustments, 2-5.1

Self test, 2-5.2

INS

Installation 4-8,4-28

Removal, 4-28

self test, 4-17

Installation

CDU, 4-10,4-30

CDU knobs, 4-25

CDU lamps, 4-24

INS, 4-8,4-28

Materials required,

Mounts, 4-7,4-27

NPU, 4-9,4-29

NPU fuses, 4-23

SDC, 4-11,4-31

4-6

TACAN mount fuse, 4-26

TACAN RT, 4-12,4-32

Test equipment required, 4-6

Tools required, 4-6

Integrated inertial navigation system, see IINS

Interconnections, 4-13

J

Jamming and ECM procedures, 2-10

K

L

Latitude entry, 2-6.2.4.1

Location and description of major components,1-10

Longitude entry, 2-6.2.4.2

Index 2

M

Magnetic heading entry, 2-6.2.3

Magnetic variation entry, 2-6.2.5

Maintenance forms, records, and reports, 1-2

Manual

scope, 1-1

Type, 1-1.2

Manually entered field altitude, 2-6.2.6

Model number and equipment name, 1-1.3

Mounts


Removal, 4-27

N

Navigation processor unit, see NPU

Northings entry, 2-6.2.4.4

NPU


Loading procedure, 2-6.4.1

Removal, 4-29

Self test, 4-17

0

Official nomenclature, common names, and desig-nations, 1-5

Operating procedure, 2-6

Operation in unusual weather, 2-8

Operation of auxiliary equipment, 2-7

Operational check, IINS, 4-22

Operator’s controls and indicators, 2-1

P

Placing IINS in service, 4-33

PMCS procedures, 4-15

Preoperational procedures, 2-6.4

Preparation for storage or shipment, 1-4

Present position entry, 2-6.2.4

Principles of operation, 1-14

TM 11-5826-302-12

ALPHABETICAL INDEX - Continued

Subject, Para Subject, Para

Purpose of equipment, 1-1.4 Signal data converter, see SDCpurpose of IINS, 1-8 Spheroid entry, 2-6.2.4.3

Q Shipment, preparation for, I-4

Storage, preparation for, 1-4R

TRemoval

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

INS, 4-28

Mounts, 4-27

NPU, 4-29

NPU fuses, 4-23

SDC, 4-31

TACAN mount fuse, 4-26

TACAN RT, 4-32

Reporting equipment improvement recommenda-tions, 1-6

s

Safety, care, and handling, 1-13

Care, 1-13.2

TACAN station magnetic variation entry, 2-6.2.10

TACAN station position entry, 2-6.2.11

TACAN RT


Removal, 4-32

Self test, 4-19Tools, test equipment, and materials required for

installation, 4-6

True heading entry, 2-6.2.3

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 wScope, 1-1

SDC


Warranty information, 1-7

x

YRemoval, 4-31

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. VUONOGeneral, United States Army

Chief of Staff

R.L. DILWORTHBrigadier General, United States Army

The Adjutant General

DISTRIBUTION:To be distr ibuted in accordance with DA Form 12-31A li terature

requirements for EEC EH-60A.

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

PIN: 063193-000

TM 11-5826-302-12 (1987_1201) OMM & AVUM, AN_ASN-132(V) IINS

Documents

Transcript of TM 11-5826-302-12 (1987_1201) OMM & AVUM, AN_ASN-132(V) IINS