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

8/9/2019 TM 11-5826-302-12 Integrated Inertial Navigation System an ASN-132 1987

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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 3

FEBRUARY 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 SOMEONE

IS THE VICTIM OF ELECTRICAL SHOCK

DO NOT TRY TO PULL OR GRAB THE INDIVIDUAL

IF POSSIBLE, TURN OFF THE ELECTRICAL POWER

IF YOU CANNOT TURN OFF THE ELECTRICAL

POWER, PULL, PUSH, OR LIFT THE PERSON TO

SAFETY USING A DRY WOODEN POLE OR A DRY

ROPE OR SOME OTHER INSULATING MATERIAL

SEND FOR HELP AS SOON AS POSSIBLE

AFTER THE INJURED PERSON IS FREE OF

CONTACT WITH THE SOURCE OF ELECTRICAL

SHOCK, MOVE THE PERSON A SHORT DISTANCEAWAY AND IMMEDIATELY START ARTIFICIAL

RESUSCITATION


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

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

injury to personnel, allow SDC to cool or wear protective hand covering prior toremoving the SDC.

B


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TECHNICAL MANUAL

No. 11-5826-302-12

TM 11-5826-302-12

HEADQUARTERS

DEPARTMENT OF THE ARMY

Washington, DC, 1 December 1987

OPERATOR’ S AND AVIATION UNITMAINTENANCE MANUAL

INTEGRATED INERTIAL NAVIGATION

SYSTEM 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 o r 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 : C o mm an de r, U S A rm y Co mm un ic at i on s- El ec t ro ni cs C om ma nd an d Fo rtMonmouth, 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

III

IV

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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Equ ipment Descr ip t ion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Pr i nci p le s of Ope rat ion . . . . . . . . . . l. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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

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

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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 Expendable Suppl i es and Mate r 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

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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 of unusual 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 the

c. A chapter on operator maintenance instructions. manual is at the front of the manual.

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

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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 and

which 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 of this 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

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Electrical Equipment TACAN MountMounting BaseMT4915/A

1-6 REPORTING EQUIPMENT IMPROVEMENT

RECOMMENDATIONS (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 material

or 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 and

path 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 and

ease 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 MAJOR

COMPONENTS.

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 of electronic 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 with

extreme care to prevent damage to precision electronicequipment. The equipment is designed and constructed

so 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 of the units (except the NPU) in the vehicle can be accom-plished by one person using standard tools. Two personsare required to lift the NPU.

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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

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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

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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.

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LOCATION AND DESCRIPTION OF MAJOR INS MOUNT COMPONENTS

1-8


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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,

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LOCATION AND DESCRIPTION OF MAJOR NPU COMPONENTS

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1

and9.

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.

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LOCATION AND DESCRIPTION OF MAJOR NPU MOUNT COMPONENTS

1. GUIDE PIN. Ensures proper positioning and attachment of NPU.

2. SHOCK MOUNT. Provides shock and vibration protection for the NPU.

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

4. NPU SELF-LOCKING HOLDDOWN RETAINER Secures NPU to mount.

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LOCATION AND DESCRIPTION OF MAJOR CDU COMPONENTS

1.

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.

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LOCATION AND DESCRIPTION OF MAJOR SDC COMPONENTS

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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

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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

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1

and

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

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

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

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.

13

and14, 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

NPUWeight

Length

Width

Height

NPU Mount

Weight

Length

Width

Height

CDU

Weight

Length

Width

Height

SDC

Weight

Length

WidthHeight

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), 16.0

to 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 side

mounted 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 a

general-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 magnetic

course from the coordinates of the position at whichthe selected magnetic course steering mode was se-lected.

1-14.3 The NPU provides computer processing and

input /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. The

NPU contains a central processor unit (CPU) thatdirectly addresses 64K 16-bit words of core memory for

instructions 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 for

communications with other units over the multiplex

data buses.

1-14.4 The CDU displays data and controls the oper-

ating modes of the IINS. The CDU is capable of

entering, changing, and recalling data from the NPU,INS, and TACAN RT; receiving data from the aircraft

altimeter encoder. This data is encoded and displayedon the CDU CRT as navigational and operational status

information. In addition, the CDU provides mode con-trol to the INS and TACAN RT. Electrical power to

the INS and TACAN RT is also controlled by the CDU.

The CDU also acts as backup bus controller for the

multiplex data buses in the event of an NPU failure.

1-14.5 The SDC performs data processing to convert

the TACAN RT Aeronautical Radio Incorporated

(ARINC) inputs and outputs to corresponding serial

data formats for transmission over the multiplex 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 data

bus at a time, it can monitor both buses continuously to

determine over which bus valid data communications

are taking place. Redundant portions of the SDC 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. The

IINS 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 of bearing and distance for updating the inertial systeminformation. The TACAN RT outputs are processed by

the SDC for compatibility with the multiplex data

buses. 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 pages

provide navigation information for the operator during

preflight and flight. Each page consists of eight lines

with up to 19 characters on each line. In most cases

each line is divided into the left side and right side.

Each side contains information pertinent to the opera-

tion of the IINS. On both sides of lines 1, 3, 5, and 7

there are line select keys which perform functions as

defined by the line legend adjacent to the line select

key. Table 2-1 describes the function of the line select

keys. Following are typical illustrations and descriptions

of each CDU data display page.

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Figure 2-1. Controls and Indicators

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Control or

Key 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 key

adjacent to “MAC will change the display to MAC Heading (MH)and MAG VAR (MV)

3. legend ( T/R). If the arrow points up, the legend 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 the

entire entryControls 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. When

pressed, . 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 was

just 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 RT

annunciation; UPDT annunciator in NAV; NAVRDY; last mark designation

4. STR. Provides selected course; range, bearing and time to steerpoint;present position; UTM or L/L selection; cardinal heading/distance;failed RT annunciator; NAVRDY annunciator in aline; UPDT 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; channel

selection and selection of auto or manual mode

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Table 2-1. CDU Controls and Indicators - Continued

Control or

Key Indicator Function

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 FAST

mode. 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 of operation. 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 of the 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

Control orKey Indicator Function

14 STR switch Three position toggle switch used to increment/decrement selectedsteerpoint. The number of the selected steerpoint appears on line 1 of the 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

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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.

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2.

3.

4.

5.

6.

7.

8.

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1. LINE 1. The left side displays the page label. The right side displays true beading (TH). Entered true heading 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 off

after 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.

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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.

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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 during

the 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,

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NOTETo select this page, set CDU page select switch to INS.

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1.

2.

3.

4.

5.

6.

7.

8.

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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.

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ZEROIZE PAGE

NOTE

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

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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.



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TESTS PAGE

NOTE

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

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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 the

word 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.

6. LINE 6. The left side is reserved for annunciations described later. The right side displays that the INS page can

be selected by pressing the CDU page slew switch down.



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

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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.

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.

7. LINE 7. The left side displays INS miscellaneous data addresses. Addresses that can be entered should be in

decimal format with a range of 0 to 65,535. The right side displays the contents of the addressed 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.

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NOTE

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

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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,

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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 not

used at the operator or aviation unit level.

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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<

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NOTE

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

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1. LINE 1. This line displays the page label.

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

3

and4. 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.


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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.

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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 on

all 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 is

calculated assuming a flat earth.

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

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


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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.

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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.

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TACAN CONTROL PACE

NOTE

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

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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 to

the 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 of stations 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.

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TACAN STATION PAGE

NOTE

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

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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.


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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,

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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.

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NOTETo select this page, set CDU mode select switch to UPDT. When this page is

selected, TACAN updating is deleted,

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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.



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ACCEPT/REJECT PAGE

NOTE

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

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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 and

nautical miles in L/L mode. The right side displays bearing (BRG) from true north, to the selected destination,

4. LINE 4, The left side displays time-to-go (TTG) to the selected destination. If TTG is greater than 2 minutes, it 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 is

calculated assuming a flat earth,

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

7. LINE 7. The left side displays ACCEPT. If the adjacent line select key is pressed, the update is accepted and 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.


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ANNUNCIATIONS

System status messages appear on line 2 (2) and the left side of line 6 (6) regardless of selected page (except NPU data

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

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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.

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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 for

aircraft preoperational procedures.

CHECKS AND SERVICES (PMCS)

Section III. OPERATION UNDER USUAL CONDITIONS

During oper

Documents

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