1F-15C-2-05JG-00-1.pdf

TO 1F-15C-2-05JG-00-1

TECHNICAL MANUAL

JOB GUIDE

AIRCRAFT - GENERAL

MAINTENANCE

S/S/SN 05-00-01 THRU 05-00-07

USAF SERIES

F-15C AND F-15D

AIRCRAFT

McDonnell Douglas Corporation

F33657-77-C-0200

FA8634-19-F-0011

DISTRIBUTION STATEMENT D - Distribution authorized to the Department of Defense and U.S. DoD contractors only (Critical Technology)

(1 August 1990). Other requests shall be referred to AFLCMC/WAQ, 235

Byron Street, Suite 19A, Robins AFB, GA 31098-1670.

WARNING - This document contains technical data whose export is restricted by the Arms Export Control Act (Title 22, U.S.C. Sec 2751, et seq.) or the Export Administration Act of 1979, (Title 50, U.S.C., App.

2401, et seq.), as amended. Violations of these export laws are subject to severe criminal penalties. Dissemination in accordance with provisions of

DoD Directive 5230.25.

HANDLING AND DESTRUCTION NOTICE - Comply with Distribution

Statement and destroy by any method that will prevent disclosure of contents or reconstruction of the document.

Published under authority of the Secretary of the Air Force.

1 JULY 2012

CHANGE 18 - 15 JUNE 2021

BASIC AND ALL UPDATES HAVE BEEN MERGED TO MAKE THIS A COMPLETE PUBLICATION.

LIST OF EFFECTIVE PAGES

Insert latest changed pages; dispose of superseded pages in accordance with applicable regulations.

NOTE: On a changed page, the portion of the text affected by the latest change is indicated by a vertical line in the outer margin of the page. Changes to illustrations are indicated by vertical lines, miniature pointing hands, shaded areas or a major change symbol.

Dates of issue for original and changed pages:

Original .... 0........1 Jul 12

Change...... 1...... 1 Nov 12

Change...... 2.......1 Sep 13

Change...... 3.......1 Jan 14

Change...... 4.....15 Feb 15

Change...... 5.......7 Dec 15

Change...... 6......4 Mar 16

Change...... 7....26 Mar 16

Change...... 8.... 19 Aug 16

Change...... 9.....25 Apr 17

Change.... 10...... 8 Aug 17

Change.... 11.....15 Jun 18

Change.... 12.... 15 Aug 19

Change.... 13..... 15 Oct 19

Change.... 14.....28 Feb 20

Change.... 15.....15 Jun 20

Change.... 16.....15 Jan 21

Change.... 17... 15 May 21

Change.... 18.....15 Jun 21

Total number of pages in this publication is 280 consisting of the following:

Page #Change Page #Change Page #Change

No. No. No. No. No. No.

Title

A

B

C i ii iii iv blank v vi vii viii ix x

1-1

1-2

1-3

1-4

1-5

1-6

1-7

1-8

1-9

1-10

1-11

1-12

1-13

1-14

1-15

1-16

1-17

1-18

1-19

1-20

1-21

1-22

1-23

1-24

1-25

1-26

1-27

1-28

1-29

1-30

1-31

1-32

1-33

1-34

1-35

1-36

1-37

1-38

1-39

1-40

1-41

1-42

1-43

1-44

1-45

1-46

1-47

1-48

1-49

TO 1F-15C-2-05JG-00-1

#Zero in this column indicates an original page.

A Change 18

1-50

1-51

1-52

1-53

1-54

1-55

1-56

1-57

1-58

1-59

1-60

1-61

1-62

1-63

1-64

1-65

1-66 blank

2-1

2-2

2-3

2-4

2-5

2-6

2-7

2-8 blank

3-1

3-2

3-3

3-4

3-5

3-6

3-7

3-8

3-9

3-10 deleted

3-11 deleted

3-12 deleted

3-13 deleted

3-14

3-15

3-16

3-17

3-18

3-19

3-20

3-21

3-22

3-23

3-24

3-25

3-26

3-27

3-28

3-29

3-30

3-31

3-32

3-33

3-34 deleted

3-35 deleted

3-36

3-37

3-38

3-39

3-40

3-41

3-42

3-43

3-44

3-45

3-46

4-1

4-2

4-3

4-4 blank

5-1

5-2

5-3

5-4

5-5

5-6

5-7

5-8

5-9

5-10

5-11

5-12

5-13

5-14

5-15

5-16

5-17

5-18

5-19

5-20

5-21

5-22

5-23

5-24

5-25

5-26

5-27

5-28

5-29

5-30

5-31

5-32

5-33

5-34

5-35

5-36

5-37

5-38

5-39

5-40 deleted

5-41 deleted

5-42 deleted

5-43 deleted

5-44

5-45

5-46 deleted

5-47 deleted

5-48

5-49

5-50

5-51

5-52

5-53

5-54

TO 1F-15C-2-05JG-00-1

Page #Change Page #Change Page #Change

No. No. No. No. No. No.

Change 18 B

5-55

5-56

5-57

5-58

5-59

5-60

5-61 blank

5-62

5-63

5-64

5-65

5-66

5-67

5-68

5-68A

5-68B

5-68C

5-68D

5-68E

5-68F

5-68G

5-68H

5-69

5-70

5-71 deleted

5-72 deleted

5-73

5-74

5-75

5-76

5-77

5-78

5-79

5-80

5-81

5-82

5-83

5-84

5-85

5-86

5-87

5-88

5-89

5-90 deleted

5-91 deleted

5-92 deleted

5-93 deleted

5-94

5-95

5-96 deleted

5-97 deleted

5-98

5-99

5-100

5-101

5-102 blank

6-1 blank

6-2

6-3

6-4

6-5

6-6

6-7

6-8

6-9

6-10

6-11

6-12 blank

7-1

7-2

7-3

7-4

7-5

7-6

7-7

7-8

7-9

7-10

7-11

7-12

7-13

7-14

7-15

7-16

7-17

7-18

7-19

7-20

7-21

7-22

7-23

7-24

7-25

7-26

7-27

7-28

7-29

7-30

7-31

7-32

7-33

7-34

7-35

7-36

7-37

7-38

7-39

7-40

TO 1F-15C-2-05JG-00-1

Page #Change Page #Change Page #Change

No. No. No. No. No. No.

C Change 18

TABLE OF CONTENTS

System/Subsystem/

Function/Paragraph Title Subject Number

TO 1F-15C-2-05JG-00-1

INTRODUCTION

Purpose

Scope

Significant Changes

Ozone Depleting Compounds (ODC)

Applicability Notations

Illustrations

Input Conditions

Function/Task Arrangement

Follow-on Maintenance

Improvement Reports

Glossary

Record of Applicable Time Compliance

Technical Orders

GENERAL MAINTENANCE

Aircraft Safe for Maintenance . . . . . . . . . . . . . 05-00-01

Cockpit Entry, Normal and Alternate

Boarding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-00-02

Canopy Operation, Opening, and Closing . . . 05-00-03

Electrical (Static) Grounding . . . . . . . . . . . . . . 05-00-04

Electrical Power Application and Removal . . 05-00-05

Proximity Switch Control Hookup and

Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-00-06

External Hydraulic Power Application and

Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-00-07 i

TO 1F-15C-2-05JG-00-2

GENERAL MAINTENANCE

External Ground Cooling Air Application and Removal . . . . . . . . . . . . . . . . . . . . . . . . . . 05-00-08

Ground Intercommunications Connecting and Disconnecting . . . . . . . . . . . . . . . . . . . . . 05-00-09

Utility Electrical Power Connector . . . . . . . . . 05-00-10

Radome Opening, Removal, Installation and

Closing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-00-11

Landing Gear Forward Doors Opening and

Closing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-00-12

External Fuel Tanks Preparation, Installation, Checkouts, and Removal . . . . 05-00-15

TO 1F-15C-2-05JG-00-3

GENERAL MAINTENANCE

Main Landing Gear (MLG) Wheel and Tire

Assembly Inspection, Removal, and

Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-00-16

Nose Landing Gear (NLG) Wheel and Tire

Assembly Inspection, Removal, and

Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-00-17

Solo Flight Configuration and Return to

Standard Flight Configuration. . . . . . . . . . . 05-00-18

Joint Oil Analysis Program (JOAP) . . . . . . . . 05-00-19

Electrical Bonding and Sealing . . . . . . . . . . . . 05-00-20

MUX-648A/A, B/A, C/A and D/A Aircraft

Cargo Pod Installation and Removal . . . . . 05-00-22

Airborne Instrumentation System (AIS) and

Global Positioning System (GPS) Pod

Aircraft Preparation, Pod Preparation, Installation, and Removal . . . . . . . . . . . . . . . 05-00-23

TO 1F-15C-2-05JG-00-1

System/Subsystem/

Function/Paragraph Title Subject Number ii

External Fuel Tank(s) Overwing Fuel

Transfer Preparation, Power On

Transfer, Gravity Transfer, and

Checkouts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-00-24

External Fuel Tank(s) Fuel Transfer

Preparation, Transfer, and Checkouts . . . . 05-00-25

Wing External Fuel Tanks Installation, and

Removal Alternate Method, Manual . . . . . 05-00-26

Hydraulic Component External Leakage

Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GV 12-00-00

TO 1F-15C-2-05JG-00-1

System/Subsystem/

Function/Paragraph Title Subject Number iii/(iv blank)

INTRODUCTION

PURPOSE.

This manual provides step-by-step general maintenance information for the F-15C and F-15D aircraft.

SCOPE.

The procedures in this manual are in a function/task arrangement with the number of each step shown on the illustration to locate the applicable hardware. Normally, illustrations and text are on facing pages; except in operational checkout procedures where a foldout illustration may follow several pages of text.

General information for TO 1F-15C-2-05JG series manuals is provided in TO 1F-15C-2-00GV-00-1.

SIGNIFICANT CHANGES.

This revision removes reference to conformal fuel tanks and improves usability.

OZONE DEPLETING COMPOUNDS (ODC).

This Technical Order (TO) has been updated as necessary to remove hazardous materials known as Class I ODC. The alternates for Class I ODC are provided in compliance with existing Federal requirements in effect when the TO was updated. Depending upon location, State and Local requirements may be different than Federal Requirements. In these cases, refer to the local Environmental Management

Directorate for information.

APPLICABILITY NOTATIONS.

Information and instructions contained in this manual unique to one model are identified as F-15C of F-15D. Data applicable to specific aircraft within a series are identified by

USAF serial numbers.

v

Instructions for UHF Anti-Jam (Have Quick) capability in

F-15 aircraft modified by TO 1F-15-704 (Incorporation of

Have Quick in F-15A/B/C/D Aircraft) are not contained in this T.O., refer to TO 1F-15A-2-23GS-00-1-1. Copies of

TO 1F-15A-2-23GS-00-1-1 may be obtained from

ASD/TAFC(T).

ILLUSTRATIONS.

Illustrations show equipment location for each task. Task step numbers and illustration index numbers are identical.

Switches, controls, and indicators are located on illustrations, but may not be shown in position required by test.

INPUT CONDITIONS.

The input conditions at the start of each function contain the information required to prepare the aircraft for maintenance and the recommended number of people to complete the function. The required consumable supplies, support equipment, support data, special tools, and safety precautions are also provided.

FUNCTION/TASK ARRANGEMENT.

A function is made up of a task or series of tasks and illustrations which support a system or component. A function supporting a component gives all tasks required to support that component. Typical tasks are removal, installation, adjustment, rigging, operational checkout, cleaning, and so forth. All steps within a task must be done to complete the task. All tasks within a function must be done to complete the function.

Following the procedures in this technical manual is mandatory. However, when doing Red Ball maintenance, only those steps required to complete the task must be done per approved local procedures. Technicians must be sure the intent of the task has been satisfied.

vi

FOLLOW-ON MAINTENANCE.

All steps listed under follow-on maintenance must be done when the tasks required for a given function have been completed.

IMPROVEMENT REPORTS.

Recommendations for improvements to prescribed requirements and procedures will be submitted through

Enhanced Technical Information Management System

(ETIMS), per TO 00-5-1.

GLOSSARY.

Nonstandard abbreviations and symbols are described below.

All abbreviations and symbols used in the maintenance manual set are described in TO 1F-15C-2-00GV-00-1.

ADCP Advanced Display Core Processor

AMAD Airframe Mounted Accessory Drive

DTM Data Transfer Module

EADI Electronic Attitude Display Indicator

ECS Environmental Control System

HUD Head Up Display

ICMS Internal Countermeasure System

IDB Initialization Data Base

JFS Jet Fuel Starter

LHVI Lower Helmet Vehicle Interface

LRU Line Replaceable Unit

MPD Multipurpose Display

MPCD Multipurpose Color Display

QDC Quick Disconnect

RIU Remote Interface Unit

Change 16 vii viii Change 13

RECORD OF APPLICABLE TIME COMPLIANCE

TECHNICAL ORDERS.

The record of applicable time compliance technical orders is a list of all TCTO which affect the technical content (text or illustration) of this manual. Only current TCTO are listed. A TCTO is deleted from the list when any of the below occurs:

a. The equipment configuration to which the TCTO is applicable is no longer covered in the manual.

b. The TCTO is rescinded.

c. The TCTO is superseded or replaced.

Record of Applicable Time Compliance Technical Orders

TCTO No. Title TCTO Date

1F-15-1361 APG-63(V)1 Radar Installation, F-15C/D MSIP Aircraft

11 Dec 98

1F-15-1503 Modification of F-15C Aircraft to Incorporate APG-63(V)3 Radar

7 Mar 11

1F-15-1551 Incorporation of Long Term Fleet Rewire into F-15C/D Aircraft

11 Sep 09

1F-15-1608 Installation of SATCOM Phase I Increment 1 into F-15C/D Aircraft

30 Sep 11

1F-15-1614 Installation of SATCOM Phase II (Increment 1) into F-15C/D Aircraft

25 Aug 15

Record of Applicable Time Compliance Technical

Orders (Continued)

TCTO No. Title

TCTO

Date

1F-15-1637 Replacement of Navigation

Control Indicator (PN 683320-16)

With Flat Panel Control Indicator

(PN 70M0000050-001)

19 Aug 14

1F-15-1668 Installation of Improved Wheels

(PN 3-1694) and Carbon Brakes

(PN 2-1762) on F-15C/D Aircraft

22 Dec 16

1F-15-1675 Modification of F-15C/D Aircraft to Incorporate Vertical Situation

Display Replacement (VSDR) into Non Advanced Display Core

Processor (ADCP) Equipped

Aircraft

1F-15-1709 Installation of AN/ALE-58A

Countermeasure Dispensing Set

Wiring to Aircraft Wings for

F-15C/D

29 Oct 19

1F-15C-517 Installation of APG-63(V)2 Active

Electronic Scan Array, F-15C

Aircraft

1 Nov 99

1F-15C-531 Modification of F-15C(V)2 Radar

Aircraft to Incorporate

APG-63(V)3 Radar

5 Sep 19

1F-15C-533 Modification of F-15C Aircraft to

Incorporate Advanced Display

Core Processor (ADCP) II

30 Apr 21

Change 18 ix

Record of Applicable Time Compliance Technical

Orders (Continued)

TCTO No. Title

TCTO

Date

1F-15C-542 Installation of Multifunctional

Information Distribution System, Joint Tactical Radio System

(MIDS/JTRS) and Electronic

Horizontal Situation Indicator

(EHSI) into F-15C Aircraft

30 Apr 21

1F-15C-548 Modification of F-15C (V)0

Aircraft to Incorporate

APG-63(V)3 Radar

26 Apr 21 x Change 18

AIRCRAFT SAFE FOR MAINTENANCE.

NOTE

For redball procedures, do Redball Safe For Maintenance.

While maintaining alert status configuration to improve alert posture and satisfy a specific quick reaction commitment, aircraft safe for maintenance is not required to be done on aircraft on alert status when completing the following procedures provided that minimum safety devices for alert aircraft are installed (TO 1F-15A-6WC-3-3) and external power or external hydraulic pressure is not applied to the aircraft.

• Airframe Mounted Accessory Drive (AMAD) Gearbox Routine Oil Servicing (12-10-06).

• Engine Oil Routine Oil Servicing (12-10-15).

• Tire Servicing (12-10-22).

• Power Control (PC 1 and PC 2) Service Inspection and Reservoir Servicing (12-10-23).

• Utility Reservoir Servicing, Service Inspection and

Reservoir Servicing (12-20-24).

• Liquid Oxygen Converter By Replacement Method

(12-10-25).

• Transponder Computer Mode 4 Programing

Procedure (34-50-12).

• Interrogator Computer Mode 4 Programming

Procedure (34-59-13).

• Embedded GPS/INS (EGI) LRU Crypto Key

Loading (34-56-05).

• FDL Crypto Key Loading (34-57-05) and

(34-57-08).

• FDL Battery Replacement (34-57-13).

• MIDS/JTRS Crypto Key Loading (34-54-06).

• MIDS/JTRS Battery Replacement (34-54-13).

• Refueling Without External Electrical Power

(12-10-07).

• Engine Data Download (FI 71-01-00).

• Central Gearbox (CGB)/Jet Fuel Starter (JFS) Oil

Servicing Inspection and Routine Oil Servicing (12-10-08).

• Integrated Drive Generator Inspection and Routine Servicing (12-10-17).

• Obtain Engine Samples (JOAP) (05-00-19).

TO 1F-15C-2-05JG-00-1

05-00-01 Change 16 1-1

1-2 Change 17 05-00-01

INPUT CONDITIONS.

Applicability: All

• Some steps in this function are limited by applicability and are identified by numbered flags as listed:

1 F-15D

Support Equipment:

• Fire extinguisher, halon (preferred)

• Fire extinguisher, CO2/CB (alternate)

• Approved hanger fire suppression system (alternate)

• Maintenance Stand

Support Data:

• 05-10-11

• TO 00-25-172

• TO 1F-15A-33-1-2CL-17

Safety Conditions:

• Establish communications, if other maintenance is in progress.

• Review aircraft records for status of aircraft.

• Ensure proper fall protection methods are used as required.

Reference TO 1F-15E-2-00GV-00-1 for guidance.

Change 12 1-3 05-00-01

To avoid inadvertent armament firing which could result in death, injury, or damage to equipment, make sure safety pins are installed and fully seated. Ground safety pins are inserted correctly when removal cannot be done without pressing the locking pin release button.

If installed, do not remove pins to test for serviceable condition. Make sure pin is fully inserted by pressing locking pin release button and push safety pin into second detent. Release locking pin button and pull out on the handle.

If aircraft has 1000 pounds or more of component weight removed forward of the main landing gear, being cannibalized, or undergoing major maintenance, aircraft must be moored (10-00-02) to prevent tipping.

To prevent the possible introduction of foreign objects into the variable inlets and engine intakes, intake covers must be installed at all times except during engine operation, intake inspection, or intake maintenance and will not be removed until aircrew arrival.

Make sure vari ramp louvers and bypass doors are covered to prevent foreign object intrusion when maintenance is done in this area.

Do not install engine air inlet protectors when ambient temperature is below -20 °F until engines and the air inlets have cooled for at least 2 hours. If installed sooner, condensation will form in the air inlet, and freezing of N1 compressor blades to the case may occur.

To prevent death or injury to personnel, an appropriate maintenance stand must be used to access the top of the aircraft if the canopy is closed.

REDBALL SAFE FOR MAINTENANCE.

WARNING

Do not go near aircraft within the operating engine intake area. If a malfunction exists, shut down the applicable engine(s) and move towards aircraft from that side. If access to door 10L/R is required, make sure the ramp switch is placed to

EMERGENCY or both engines are shut down.

To prevent injury to personnel or damage to equipment, electrical power must be isolated from applicable system before disconnecting or connecting electrical circuits.

1. Make sure serviceable fire extinguisher or approved hanger fire suppression system exists. Refer to

TO 00-25-172.

2. Make sure aircraft chocks are installed.

To prevent damage to aircraft engine(s) as a result of ground cable ingestion, do not install aircraft ground cable forward of aircraft intakes when engine(s) are operating.

3. Make sure static ground cable is installed (05-00-04).

4. Establish communication with aircrew (05-00-09).

5. Safety live ordnance per TO 1F-15A-33-1-2CL-17.

TO 1F-15C-2-05JG-00-1

1-4

Figure 01. Sheet 1

1-5

To prevent death or injury to personnel, extreme caution must be used while working around ejection seat(s). The redundant emergency escape system can be initiated with the canopy open.

Make sure all required cockpit safety devices are correctly installed.

6. If cockpit entry is required, do the below:

NOTE

The steps below are to be done in cockpit and rear cockpit as required.

6.1. Install safety pin in canopy jettison handle.

6.2. Install cockpit safety pin in canopy actuated

initiator.

6.3. Install canopy ground safety lock (05-10-03).

TO 1F-15C-2-05JG-00-1

1-6

Figure 01. Sheet 2

1-7

6.4. Position ejection controls safety lever to

EJECTION CONTROLS LOCKED.

6.5. Install ejection seat ground safety pin in

EJECTION CONTROL HANDLE.

6.6. Install ejection seat ground safety pin in

EMERGENCY MANUAL CHUTE HANDLE.

TO 1F-15C-2-05JG-00-1

1-8

Figure 01. Sheet 3

1-9

EXTERIOR INSPECTION.

1. Make sure serviceable fire extinguisher or approved hanger fire suppression system exists. Refer to

TO 00-25-172.

2. Static ground cable is installed (05-00-04).

3. If required, moor aircraft (10-00-02).

4. Nose landing gear ground safety pin is installed.

5. Be sure M61A1 internal gun armament ground safety pin installed through door 40.

6. Open door 42 and be sure clearing sector tool/download pin assembly is installed.

TO 1F-15C-2-05JG-00-1

1-10

Figure 01. Sheet 4

1-11

7. If right Chaff/Flare magazines are loaded, make sure armament ground safety pin is installed.

TO 1F-15C-2-05JG-00-1

1-12

Figure 01. Sheet 5

1-13

8. Open door 45.

9. ROUNDS LIMITER switch set to LIMIT position.

10. Rounds preset knob set to 900 rounds.

11. Close door 45.

TO 1F-15C-2-05JG-00-1

1-14

Figure 01. Sheet 6

1-15

12. If right LAU-106 launchers have stores installed, open doors 49R and/or 100R and be sure armament ground safety pin is installed in LAU-106 launcher.

TO 1F-15C-2-05JG-00-1

1-16

Figure 01. Sheet 7

1-17

13. (AIM-120) arm firing device indicator (AFD) for safe indication, white S on green background.

14. Deleted.

TO 1F-15C-2-05JG-00-1

1-18 Change 1

Figure 01. Sheet 8

Change 1 1-19

1-20 Change 5 05-00-01

15. Right main landing gear ground safety pin is installed.

NOTE

See TO 1F-15C-2-00GV-00-1 for chock style variations approved for use.

16. Right main landing gear wheel chock(s) installed.

Figure 01. Sheet 9

1-21

17. If right inboard pylon is installed, be sure safety devices listed below are installed:

To prevent damage to equipment, make sure armament ground safety pins are fully seated past the second detent.

17.1. Armament ground safety pin in SUU-59( ) pylon

ejection breech.

17.2. If stores are loaded, armament ground safety pin

in MAU-12( ) bomb rack.

TO 1F-15C-2-05JG-00-1

1-22

Figure 01. Sheet 10

1-23

18. If right inboard missile launchers are installed and loaded, be sure safety devices listed below are installed or positioned:

18.1. (LAU-128) in-flight lock indicator (IFL) is locked.

18.2. (AIM-9L/M) safe/arm handle positioned to SAFE and safety pin installed.

18.3. (AIM-9X) make sure SAFE/ARM selector handle is set to SAFE.

18.4. (AIM-9( )) dome and fuze cover installed.

TO 1F-15C-2-05JG-00-1

1-24

Figure 01. Sheet 11

1-25

18.5. (AIM-120) arm firing device indicator (AFD) for safe indication, white S on green background.

18.6. Deleted.

TO 1F-15C-2-05JG-00-1

1-26 Change 1

Figure 01. Sheet 12

Change 1 1-27

19. If SUU-20B/A dispenser is installed on right inboard pylon, and loaded, be sure safety devices listed below are installed:

19.1. Circuit disconnect safety spring.

19.2. Ejector gun safety pins.

19.3. Intervalometer switch set to SAFE.

TO 1F-15C-2-05JG-00-1

1-28

Figure 01. Sheet 13

1-29

20. Arresting hook uplock ground safety pin installed, if arresting hook is up.

21. Arresting hook downlock ground safety pin installed, if arresting hook is down.

22. If maintenance is to be done on the vertical stabilizer, cover the surface below with a locally manufactured protective pad to prevent damage by dropped objects.

TO 1F-15C-2-05JG-00-1

1-30

Figure 01. Sheet 14

1-31

23. If centerline pylon is installed, be sure safety devices listed below are installed:

To prevent damage to equipment, make sure armament ground safety pins are fully seated past the second detent.

23.1. Armament ground safety pin in SUU-60( ) pylon

ejection breech.

23.2. If stores are loaded, armament ground safety pin

in MAU-12( ) bomb rack.

24. If left inboard pylon is installed, be sure safety devices listed below are installed:

To prevent damage to equipment, make sure armament ground safety pins are fully seated past the second detent.

24.1. Armament ground safety pin in SUU-59( ) pylon

ejection breech.

24.2. If stores are loaded, armament ground safety pin

in MAU-12( ) bomb rack.

TO 1F-15C-2-05JG-00-1

1-32

Figure 01. Sheet 15

1-33

25. If left inboard missile launchers are installed and loaded, be sure safety devices listed below are installed or positioned:

25.1. (LAU-128) in-flight lock indicator (IFL) is locked.

25.2. (AIM-9L/M) safe/arm handle positioned to SAFE and safety pin installed.

25.3. (AIM-9X) make sure SAFE/ARM selector handle is set to SAFE.

25.4. (AIM-9( )) dome and fuze cover installed.

TO 1F-15C-2-05JG-00-1

1-34

Figure 01. Sheet 16

1-35

25.5. (AIM-120) arm firing device (AFD) indicator for safe indication, white S on green background.

25.6. Deleted.

TO 1F-15C-2-05JG-00-1

1-36 Change 1

Figure 01. Sheet 17

Change 1 1-37

26. If SUU-20B/A dispenser is installed on left inboard and/or centerline pylon, and loaded, be sure safety devices listed below are installed:

26.1. Circuit disconnect safety spring.

26.2. Ejector gun safety pins.

26.3. Intervalometer switch set to SAFE.

TO 1F-15C-2-05JG-00-1

1-38

Figure 01. Sheet 18

1-39

27. If A/A 37U-36 Aerial Gunnery Target System

(AGTS-36) is installed inspect for the following:

27.1. Towreel piston safety blocks - installed.

27.2. Visual augmentor bag ties - not installed in cutter.

27.3. Turbine inlet cover - installed.

TO 1F-15C-2-05JG-00-1

1-40

Figure 01. Sheet 19

1-41

28. If left LAU-106 launchers have stores installed, open doors 49L and/or 100L and be sure armament ground safety pin is installed in LAU-106 launcher.

TO 1F-15C-2-05JG-00-1

1-42

Figure 01. Sheet 20

1-43

29. (AIM-120) arm firing device indicator (AFD) for safe indication, white S on green background.

30. Deleted.

TO 1F-15C-2-05JG-00-1

1-44 Change 1

Figure 01. Sheet 21

Change 1 1-45

31. Left main landing gear ground safety pin is installed.

32. Left main landing gear wheel chock(s) installed.

33. If left Chaff/Flare magazines are loaded make sure armament ground safety pin is installed.

TO 1F-15C-2-05JG-00-1

1-46

Figure 01. Sheet 22

1-47

COCKPIT/REAR COCKPIT INSPECTION.

If maintenance procedure does not require cockpit entry, Cockpit/Rear Cockpit Inspection may be omitted from safe for maintenance procedure. If added maintenance functions are done concurrently and cockpit entry is required, to prevent injury to personnel or damage to equipment Safe for Maintenance with

Cockpit/Rear Cockpit Inspection must be done.

1. Do cockpit entry normal and alternate boarding

(05-00-02).

WARNING

To prevent death or injury to personnel, extreme caution must be used while working around the ejection seat(s). The redundant emergency escape system can be initiated with the canopy open.

Make sure all cockpit safety pins are correctly installed.

To prevent death or injury to personnel canopy actuated initiator safety pin must be installed.

2. Make sure cockpit safety pin is installed in canopy actuated initiator (05-10-11).

3. Make sure safety pin is installed in canopy emergency jettison handle and Ñ1 rear emergency jettison handle.

TO 1F-15C-2-05JG-00-1

1-48

Figure 01. Sheet 23

1-49

4. Canopy ground safety lock installed.

1-50

Figure 01. Sheet 24

1-51

5. ACES II ejection seat safety devices listed below installed or set:

NOTE

The steps below are to be done in cockpit and rear cockpit as required.

5.1. Ejection controls safety lever is set to EJECTION

CONTROLS LOCKED.

5.2. Ejection seat ground safety pin in EJECTION

CONTROL HANDLE.

5.3. Ejection seat ground safety pin in EMERGENCY

MANUAL CHUTE HANDLE.

TO 1F-15C-2-05JG-00-1

1-52

Figure 01. Sheet 25

1-53

1-54 Change 5 05-00-01

To prevent damage to seat, lap belts must be connected together and survival kit straps on top of seat pan cover.

To prevent damage to canopy, recovery parachute, or UWARS equipment, parachute riser straps must be positioned against the backrest pad.

5.4. Make sure parachute riser straps are positioned against the backrest pad.

5.5. Lap belts connected together and survival kit connector

straps on top of seat pan cover.

5.6. Ejection seat pitot covers installed.

Figure 01. Sheet 26

1-55

5.7. If ejection seat is raised in the maintenance

position, be sure vernier rocket motor sear safety pin is installed in vernier rocket motor sear.

TO 1F-15C-2-05JG-00-1

1-56

Figure 01. Sheet 27

1-57

1-58 Change 5 05-00-01

6. If CRU-94/P type oxygen mask connector is installed, make sure vest port plug is correctly installed and secure.

To prevent damage to components, make sure emergency oxygen hose is connected to CRU-( ) oxygen mask connector.

To prevent damage to CRU-94/P oxygen mask connector (if installed), make sure it is stowed using the top outlet only.

7. Make sure emergency oxygen hose is connected to oxygen mask connector and oxygen mask connector is correctly stowed in stowage plug on right console.

Figure 01. Sheet 28

1-59

8. Make sure MASTER switch on Multipurpose Color

Display is set to SAFE.

9. Make sure SEL JETT knob on Multipurpose Color

Display is set to OFF.

10. Make sure weapon/mode selector switch on right throttle is set to gun (aft position).

11. Make sure EMERG JETT switch pushbutton is out, yellow not showing

TO 1F-15C-2-05JG-00-1

1-60

Figure 01. Sheet 29

Change 15 1-61

1-62 Change 17 05-00-01

12. On the ENGINE control panel, make sure JFS STARTER ON/OFF switch and L/R ENG MASTER switches are set to

OFF.

13. On CMD control panel, set switches as listed below:

13.1. MODE switch - OFF

13.2. DISP SEL switch - CHAFF

13.3. FLARE switch - NORM

13A. On SENSOR control panel, set switches as listed below:

13A.1. POD PWR switch- OFF

13A.2. LASER ARM switch- SAFE

Change 17 1-63

Figure 01. Sheet 30

1-64 Change 7 05-00-01

To prevent injury to personnel or damage to equipment, the lower helmet vehicle interface (LHVI) quick disconnect (QDC) must be securely stowed in the stowage receptacle.

14. Make sure LHVI QDC is securely stowed in the stowage receptacle.

Figure 01. Sheet 31

Change 15 1-65/(1-66 blank)

COCKPIT ENTRY, NORMAL AND ALTERNATE

BOARDING.

INPUT CONDITIONS.

Applicability: All

• Some steps in this function are limited by applicability and are identified by numbered flags as listed:

Ñ1 F-15C Ñ2 F-15D

Required Conditions:

• Aircraft safe for maintenance (05-00-01)

Support Equipment:

NOTE

Access ladder is only used in alternate boarding.

• Ladder, access

Safety Conditions:

Use caution when in cockpit to prevent damage to electrical components on throttle grips.

TO 1F-15C-2-05JG-00-1

05-00-02 2-1

NORMAL BOARDING.

Stand clear of retractable steps before pushing release button. Free-fall of steps could cause injury to personnel.

1. Push button located on retractable step door, and lower retractable steps by hand.

WARNING

To prevent injury to personnel or damage to equipment, handgrip must not be used as a step during normal boarding procedures.

2. Open canopy (05-00-03).

3. Inspect canopy actuated initiator fired warning indicator on bulkhead to left of front seat for normal (unfired) condition. If red coil is extended escape system components must be replaced (Ñ1 GS 95-10-00 or

Ñ2 GS 95-11-00).

4. Retract steps into aircraft by pushing up steps until steps lock flush with moldline of aircraft.

5. Make sure access steps are latched, stowed correctly and button is flush.

TO 1F-15C-2-05JG-00-1

2-2

Figure 02. Sheet 1

2-3

ALTERNATE BOARDING.

1. Open canopy (05-00-03).

To prevent damage to aircraft do not position ladder forward against windshield arch.

2. When using ladder for cockpit access, lift ladder vertically and hook upper end of ladder over cockpit sill.

3. Inspect canopy actuated fired warning indicator on bulkhead to left front seat for normal (unfired) condition. If red coil is extended escape system components must be replaced (Ñ1 GS 95-10-00 or

Ñ2 GS 95-11-00).

TO 1F-15C-2-05JG-00-1

2-4

Figure 02. Sheet 2

2-5

4. For rear cockpit/no. 5 equipment compartment access, position ladder against forward part of second canopy roller support and against side of fuselage.

TO 1F-15C-2-05JG-00-1

2-6

Figure 02. Sheet 3

2-7/(2-8 blank)

Change 7 3-1 05-00-03

CANOPY OPERATION, OPENING, AND CLOSING.

INPUT CONDITIONS.

Applicability: All

• Some steps in this function are limited by applicability and are identified by numbered flags as listed:

1F-15C 2F-15D

3DELETED

4DELETED

Required Conditions:

• Aircraft safe for maintenance (05-00-01)

Support Equipment:

• Power source, external electrical

• Power source, external hydraulic

• Maintenance stand

• Pump handle, JFS accumulator

• Filler and pressurization unit

• Cover, NLG wheel and tire

Support Data:

• 05-00-12

• 05-10-03

• TO 4T-1-3

3-2 Change 7 05-00-03

Supplies (Consumables):

Personal Safety Equipment:

• Gloves, protective

• Face shield or goggles

NOMENCLATURE

PART NUMBER

(CAGE) QTY

Cloth, flannel CCC-C-458,TYPE 3, CLASS 2

(81348)

AR

Lockwire MS20995NC41 (96906)

AR

Rymplecloth 301-100 (97327)

AR

Change 7 3-3 05-00-03

Safety Conditions:

To prevent damage to canopy and/or injury to personnel, canopy must be closed and locked if canopy safety lock or adjustable canopy braces are not installed.

To prevent damage to canopy from excessive wind loads, canopy must not be operated and must be closed and locked in winds greater than 60 knots. Canopy should be manually restrained to prevent damage from excessive opening forces if canopy hydraulic system is suspected of containing air and wind is gusting above 15 knots.

To prevent damage to canopy aft fairings, panels 153 L/R, and underlying structures, make sure panels 153 L/R are completely removed or completely installed before opening canopy.

NOTE

If canopy fails to open using both internal and external procedures, refer to TO 1F-15C-3-4.

OPENING (EXTERNAL).

To prevent water damage to electronic equipment, remove any snow or ice from canopy before opening.

Be careful to avoid scratching transparency.

1. If canopy is covered with snow, do the below:

1.1. Position maintenance stand next to aircraft.

1.2. Wipe snow from canopy with rymplecloth or clean

flannel cloth.

2. If canopy is frozen or covered with ice, deice canopy before opening (12-10-04).

3. Remove maintenance stand.

NOTE

Canopy is normally opened by canopy accumulator hydraulic pressure.

4. Open canopy by doing below:

4.1. Press release button to extend external CANOPY

CONTROL HANDLE.

TO 1F-15C-2-05JG-00-1

05-00-03 3-4

Figure 03. Sheet 1

3-5

To prevent damage to canopy external control cables, do not exceed Ñ1 45 pounds force or Ñ2 90 pounds force when manually operating external handle.

4.2. Move external CANOPY CONTROL HANDLE to

UP.

RESULT: Canopy raises.

4.3. Install canopy ground safety lock (05-10-03).

4.4. Move external CANOPY CONTROL HANDLE to

HOLD then stow handle.

4.5. Do cockpit/rear cockpit inspection (05-00-01).

5. Ñ1 If canopy does not open hydraulically, do the below:

5.1. Make sure external CANOPY CONTROL

HANDLE is set to UP.

To prevent damage to canopy locking actuator and/or shear bolts, do not exceed 130 foot pounds when unlocking and 180 foot pounds when locking the canopy using canopy external manual unlock shaft.

5.2. Insert 1/2-inch drive tool into external manual

CANOPY UNLOCK shaft and rotate full clockwise.

TO 1F-15C-2-05JG-00-1

3-6

Figure 03. Sheet 2

3-7

5.3. Position maintenance stand on left side of aircraft.

To prevent injury to personnel or damage to canopy, two personnel are required if the canopy does not raise hydraulically.

To prevent damage to aircraft, canopy must be full aft (about 1.5 inches) before manually opening canopy.

5.4. Manually raise canopy to full up position and

manually hold.

5.5. Install canopy ground safety lock (05-10-03).

5.6. Move external CANOPY CONTROL HANDLE to

HOLD and stow handle.

5.7. Do cockpit/rear cockpit inspection (05-00-01).

5.8. Remove 1/2-inch drive tool.

5.9. Remove maintenance stand.

TO 1F-15C-2-05JG-00-1

3-8

Figure 03. Sheet 3

3-9

3-14 Change 12 05-00-03

All data on pages 3-10 thru 3-13 including figure 3, sheets 4 and 5 deleted.

6. Deleted.

7.2If canopy does not open hydraulically, do the below:

Hydraulic fluid may cause skin irritation. Avoid contact with skin and clothing. Wash thoroughly after handling.

To prevent injury to personnel from possible hydraulic fluid spray, gloves and eye protection should be worn while using hydraulic filler and pressurization unit.

7.1. Make sure external CANOPY CONTROL

HANDLE is set to UP. If canopy is not unlocked, refer to Fault Code 9521B3ZZ.

7.2. Open NLG forward door (05-00-12).

Change 12 3-15

Figure 03. Sheet 6

3-16 Change 10 05-00-03

7.3. Install cover on NLG wheel and tire. Refer to TO 4T-1-3.

7.4. On filler and pressurization unit, close bleed valve.

7.5. Remove safety wire and dust cap.

7.6. Remove hose dust plug.

7.7. Connect hose assembly from filler unit to hand pump quick disconnect.

7.8. Tighten coupling nut clockwise until nut can not be

tightened any more by hand.

7.9. Install hose dust plug in hand pump dust cap.

Change 12 3-17

Figure 03. Sheet 7

To prevent damage to hydraulic systems, opening/closing pressure must not exceed 3000

PSIG.

7.10. Operate pump handle until canopy is fully open.

7.11. Move external CANOPY CONTROL HANDLE to

HOLD and stow handle.

TO 1F-15C-2-05JG-00-1

3-18

Change 12 3-19

Figure 03. Sheet 8

3-20 Change 12 05-00-03

7.12. Install canopy ground safety lock (05-10-03).

7.13. Open bleed valve.

7.14. Disconnect hose assembly from hand pump quick

disconnect.

7.15. Remove hose dust plug from hand pump dust cap.

7.16. Install hose dust plug on hose assembly.

7.17. Install hand pump dust cap.

To prevent damage to equipment and possible injury to personnel, lockwire must be installed in a way to prevent dust cap from being removed without cutting the lockwire and dust cap lanyard must be removed.

7.18. To prevent dust cap from loosening, safety dust

cap to coupling half with lockwire connecting together any two opposite mounting flange holes, the dust cap groove and hydraulic tee.

7.19. Move hydraulic filler and pressurization unit from

vicinity of aircraft.

7.20. Remove cover from NLG wheel and tire. Refer to

TO 4T-1-3.

7.21. Inspect for foreign objects and close NLG forward

door (05-00-12).

Change 12 3-21

Figure 03. Sheet 9

OPENING (INTERNAL).

Canopy is normally opened by canopy hydraulic accumulator pressure.

1. Open canopy by doing below:

To prevent damage to canopy internal control cables, do not exceed Ñ1 30 pounds force or Ñ2 60 pounds force when manually operating internal CANOPY CONTROL handle.

1.1. Move internal CANOPY CONTROL handle to UP.

RESULT: Canopy raises.

1.2. Install canopy ground safety lock (05-10-03).

2. Ñ1 If canopy does not open hydraulically, do the below:

2.1. Make sure internal CANOPY CONTROL

HANDLE is set to UP.

2.2. Remove quick release pin from canopy internal

manual unlock handle.

2.3. Pull canopy internal manual unlock handle full aft.

RESULT: Canopy moves about 0.8 inch aft.

TO 1F-15C-2-05JG-00-1

3-22

Figure 03. Sheet 10

3-23

Operation of canopy internal manual unlock handle opens canopy slightly. To prevent shearing of canopy control cams attach bolts, canopy must be full aft (about 1.5 inches) before manually opening canopy.

2.4. Pull canopy full aft.

2.5. Raise canopy manually.

2.6. Move internal CANOPY CONTROL handle to

HOLD.

2.7. Install canopy ground safety lock (05-10-03).

2.8. Push canopy internal manual unlock handle full

forward.

2.9. Install quick release pin.

2.10. Move internal CANOPY CONTROL or external

CANOPY CONTROL HANDLE to UP.

TO 1F-15C-2-05JG-00-1

3-24

Figure 03. Sheet 11

3-25

3-26 Change 12 05-00-03

NOTE

When manually opening canopy, canopy locking hook must be rotated aft.

3.1To manually rotate canopy locking hook aft, do the below:

3.1. Insert 1/2-inch drive tool into external manual

CANOPY UNLOCK shaft and rotate full clockwise.

3.2. Move internal CANOPY CONTROL or external

CANOPY CONTROL HANDLE to HOLD.

4.1To hydraulically rotate hook aft, do the below:

4.1. Apply external electrical power (05-00-05).

4.2. Apply external hydraulic power (05-00-07).

4.3. Move internal CANOPY CONTROL or external

CANOPY CONTROL HANDLE to UP, then back to HOLD.

4.4. Stow external CANOPY CONTROL HANDLE by

pushing in until retaining latch is engaged.

5.1Install canopy ground safety lock (05-10-03).

6.2If internal controls do not open canopy, it must be opened externally. See EXTERNAL OPENING.

Change 12 3-27

Figure 03. Sheet 12

CLOSING (EXTERNAL).

Canopy is normally closed using canopy hydraulic accumulator pressure.

1. Close canopy by doing below:

1.1. Remove canopy ground safety lock (05-10-03).

1.2. Visually inspect canopy sills for foreign objects.

1.3. Press release button to extend external CANOPY

CONTROL HANDLE.

To prevent damage to canopy external control cables, do not exceed Ñ1 45 pounds force or Ñ2 90 pounds force when operating external

CANOPY CONTROL HANDLE.

1.4. Move external CANOPY CONTROL HANDLE to

DOWN.

RESULT: Canopy lowers and closes against windshield.

TO 1F-15C-2-05JG-00-1

3-28

Figure 03. Sheet 13

3-29

To be sure canopy is fully closed and locked, a 10 second delay must be observed after canopy is closed before moving external CANOPY

CONTROL HANDLE from DOWN to LOCK.

1.5. Move external CANOPY CONTROL HANDLE to

LOCK.

1.6. Stow external CANOPY CONTROL HANDLE by

pushing in until retaining latch is engaged.

TO 1F-15C-2-05JG-00-1

3-30

Figure 03. Sheet 14

3-31

3-32 Change 12 05-00-03

2.1If canopy does not close hydraulically, do the below:

2.1. Insert 1/2-inch drive tool into external manual

CANOPY UNLOCK shaft.

2.2. Rotate 1/2-inch drive tool clockwise to the

unlocked position.

2.3. Visually inspect canopy locking hooks, making sure

hooks are in the full aft position (unlocked).

2.4. Make sure external CANOPY CONTROL

HANDLE is set to DOWN.

2.5. Deleted.

NOTE

Locking action can be detected by a pop sound as locking mechanism moves overcenter.

2.6. Rotate 1/2-inch drive tool counterclockwise to close

and lock canopy.

2.7. Remove 1/2-inch drive tool.

2.8. Move external CANOPY CONTROL HANDLE to

LOCK.

2.9. Stow external CANOPY CONTROL HANDLE by

pushing in until retaining latch is engaged.

Change 12 3-33

Figure 03. Sheet 15

3-36 Change 12 05-00-03

3. Deleted.

4.2If canopy does not close hydraulically, do the below:

Hydraulic fluid may cause skin irritation. Avoid contact with skin and clothing. Wash thoroughly after handling.

To prevent injury to personnel from possible hydraulic fluid spray, gloves and eye protection should be worn while using hydraulic filler and pressurization unit.

4.1. Open NLG forward door (05-00-12).

4.2. Make sure external CANOPY CONTROL

HANDLE is set to DOWN.

All data on pages 3-34 and 3-35 including figure 3, sheet 16 deleted.

Change 12 3-37

Figure 03. Sheet 17

3-38 Change 10 05-00-03

NOTE

Make sure hydraulic filler and pressurization unit is positioned so that the canopy can be observed as it closes.

4.3. Install cover on NLG wheel and tire. Refer to TO 4T-1-3.

4.4. On filler and pressurization unit, close bleed valve.

4.5. Remove safety wire and hand pump dust cap.

4.6. Remove hose dust plug.

4.7. Connect hose assembly from filler unit to hand pump quick disconnect.

4.8. Tighten coupling nut clockwise until nut can not be

tightened any more by hand.

4.9. Install hose dust plug in hand pump dust cap.

Change 12 3-39

Figure 03. Sheet 18

To prevent damage to hydraulic systems, opening/closing pressure must not exceed 3000

PSIG.

4.10. Operate pump handle until canopy closes against

windshield.

4.11. Move external CANOPY CONTROL HANDLE to

LOCK and stow handle.

TO 1F-15C-2-05JG-00-1

3-40

Change 12 3-41

Figure 03. Sheet 19

3-42 Change 12 05-00-03

4.12. Open bleed valve.

4.13. Disconnect hose assembly from hand pump quick

disconnect.

4.14. Remove hose dust plug from hand pump dust cap.

4.15. Install hose dust plug on hose assembly.

To prevent injury to personnel or damage to equipment, lockwire must be installed in a way that prevents dust cap from being removed without cutting lockwire and dust cap lanyard must be removed.

4.16. Install hand pump dust cap.

4.17. To prevent dust cap from loosening, safety dust

cap to coupling half with lockwire connecting together any two opposite mounting flange holes, the dust cap groove and hydraulic tee.

4.18. Move hydraulic filler pressurization unit from

vicinity of aircraft.

4.19. Remove cover from NLG wheel and tire. Refer to

TO 4T-1-3.

4.20. Inspect for foreign objects and close NLG forward

door (05-00-12).

Change 12 3-43

Figure 03. Sheet 20

CLOSING (INTERNAL).

Canopy is normally closed using canopy hydraulic accumulator pressure.

1. Close canopy by doing the below:

1.1. Remove canopy ground safety lock (05-10-03).

1.2. Visually inspect canopy sills for foreign objects.

To prevent damage to canopy internal control cables, do not exceed Ñ1 30 pounds force or Ñ2 60 pounds force when operating internal

CANOPY CONTROL handle.

1.3. Move internal CANOPY CONTROL handle to

DOWN.

RESULT: Canopy lowers and closes against windshield.

NOTE

To be sure canopy is fully closed and locked, a 10 second delay must be observed after canopy is closed before moving internal handle from DN to

LOCKED.

1.4. Move internal CANOPY CONTROL handle to

LOCKED.

TO 1F-15C-2-05JG-00-1

3-44

Figure 03. Sheet 21

3-45

If internal controls do not close canopy, it can be manually closed or closed using external power.

2. To close canopy manually, see EXTERNAL CLOSING.

3. To close canopy using external power, do the below:

3.1. Apply external electrical power (05-00-05).

3.2. Apply external hydraulic power (05-00-07).

3.3. Close canopy internally. See INTERNAL

CLOSING.

TO 1F-15C-2-05JG-00-1

3-46

ELECTRICAL (STATIC) GROUNDING.

INPUT CONDITIONS.

Applicability: All

Support Equipment:

• Grounding cable, aircraft

Safety Conditions:

Grounding receptacles shall be secure to prevent danger of electrical spark from static potential.

To prevent damage to aircraft engine(s) as a result of ground cable ingestion, do not install aircraft ground cable forward of aircraft intakes when engine(s) are operating.

TO 1F-15C-2-05JG-00-1

05-00-04 4-1

PROCEDURE.

Grounding receptacle used, is determined by the mechanic.

1. Determine grounding receptacle required for maintenance function.

WARNING

To prevent a dangerous shock, ground wire must be connected to an approved static ground before connecting to aircraft

2. Install grounding clip to approved static ground.

3. Install connector in grounding receptacle. Connector shall be snug.

4. If required, replace damaged static ground receptacle as listed:

4.1. Engine area (24-70-10).

4.2. Left air intake duct (24-70-11).

4.3. Left and Right MLG wheelwell (24-70-12).

4.4. Nose area (24-70-13).

4.5. Pylon area, TO 16W6-25-12.

TO 1F-15C-2-05JG-00-1

4-2

Figure 04. Sheet 1

4-3/(4-4 blank)

ELECTRICAL POWER APPLICATION AND

REMOVAL.

INPUT CONDITIONS.

Applicability: All

• Some steps in this function are limited by applicability and are identified by numbered flags as listed:

Ñ1 F-15C Ñ2 F-15D

Ñ3 F-15C 78-0468 THRU 85-0125, F-15D 78-0561

THRU 85-0134

Ñ4 F-15C 85-0126 AND UP, F-15D 86-0181 AND

UP

Ñ5 F-15C AND F-15D AFTER TO 1F-15-1361

Ñ6 F-15C 78-0468 THRU 83-0043

Ñ7 F-15C 84-0001 AND UP

Ñ8 BEFORE TO 1F-15C-517

Ñ9 AFTER TO 1F-15C-517 AND BEFORE

TO 1F-15C-531

Ñ10 F-15C AND F-15D BEFORE TO 1F-15-1361

Ñ11 F-15C AFTER TO 1F-15C-533

Ñ12 DELETED

Ñ13 WITHOUT HPWS INSTALLED

Ñ14 WITH HPWS INSTALLED

Ñ15 BEFORE TO 1F-15-1551

Ñ16 AFTER TO 1F-15-1551

Ñ17 BEFORE TO 1F-15-1503, TO 1F-15C-531,

AND TO 1F-15C-548

Ñ18 AFTER TO 1F-15-1503, TO 1F-15C-531, OR

TO 1F-15C-548

Ñ19 AFTER TO 1F-15-1709

Ñ20 BEFORE TO 1F-15-1637

Ñ21 AFTER TO 1F-15-1637

Ñ22 BEFORE TO 1F-15-1614

Ñ23 AFTER TO 1F-15-1614

Ñ24 DELETED

TO 1F-15C-2-05JG-00-1

05-00-05 Change 18 5-1

Ñ25 IF USING A/M32A-60 SERIES

GENERATORS

Ñ26 BEFORE TO 1F-15C-533 AND

TO 1F-15-1675

Ñ27 AFTER TO 1F-15C-533 OR

TO 1F-15-1675

Ñ28 BEFORE TO 1F-15C-542

Ñ29 AFTER TO 1F-15C-542

Required Conditions:

• Aircraft safe for maintenance (05-00-01)

NOTE

To improve alert posture and satisfy a specific quick reaction commitment, local commanders may direct external power-on fuel and LOX amount tests, KY-58 recording, and external lighting operational tests without disconnecting all store (missiles and pods) umbilicals. This selection will require the gun, CMD, and all pylon and launcher safety pins to be installed and applies to aircraft on alert status only.

Support Equipment:

• Ñ25 Generator set, gas turbine, A/M32A-60

Generator set, diesel engine, A/M32A-86D, B809 series, Motor Generator MD-2,3,4, Frequency

Converter EPU-6, 10050SSFC64-50 (or equivalent)

• Air source, external cooling, when required

• Proximity switch control, when required

• Safety clip assemblies, circuit breaker

Support Data:

• Ñ1 05-10-11

TO 1F-15C-2-05JG-00-1

5-2 Change 18

Safety Precautions:

Failure to set circuit breakers and switches as specified may energize aircraft systems and result in injury to personnel or damage to equipment.

To prevent injury to personnel or damage to equipment, electrical power must be shut off before connecting or disconnecting electrical connections.

To prevent injury to personnel or damage to equipment, the GROUND CHECK PANEL must be installed before applying external ground power. The fuel boost pumps will operate with the GROUND CHECK PANEL removed from the aircraft and external ground power applied.

To prevent damage to electrical and electronic systems, cooling air is required when switches or controls are set differently than specified.

To prevent damage to equipment, remove external electrical power if ECS caution light comes on during operational checkout. Refer to

Avionics Temperature Control Malfunction -

Fault Code Ñ13 2163B or Ñ14 2166B.

GND PWR control panel switches are manually set and electromagnetically held. If external power is interrupted, switches must be reset.

TO 1F-15C-2-05JG-00-1

5-3

APPLICATION.

Left wing shown, right wing opposite.

Repeated application of external electrical power will not require inspection of wing areas for fuel leakage as long as reapplication is during one task.

1. Inspect left and right wing areas for signs of fuel leakage as listed below:

1.1. Complete upper and lower wing surface specially

all drain holes and leak prone areas.

1.2. Anti-collision light in area of drain hole, if no drain

hole exists inspect lens and light periphery.

1.3. Fuel leakage into engine vent scoop.

1.4. If leakage exists, refer to Integral Wing Tank Leak

Classification (GS 28-10-00).

TO 1F-15C-2-05JG-00-1

5-4

Figure 05. Sheet 1

5-5

5-6 Change 17 05-00-05

To prevent injury to personnel or damage to equipment, all stores umbilicals connected to the LAU-106 and LAU-128 launchers shall be isolated before application of electrical power except training missile, Air Combat Maneuvering Instrumentation (ACMI) or other instrumentation pods provided the GND PWR panel, position switches 4 and :CC, or ;ADCP/RIU or Armament Override switches are maintained in the off position at all times except when inventorying the memory or loading stores memory to match mission requirements.

2. If LAU-106 launchers have stores installed, isolate umbilicals (05-10-09).

3. If LAU-128 launchers have stores installed, isolate umbilicals (05-10-49).

Figure 05. Sheet 2

5-7

To prevent injury to personnel or damage to equipment, CMD circuit breakers must be open before application of electrical power if chaff and/or flares are loaded.

4. Open door 6L.

5. On ESSENTIAL BUS CIRCUIT BREAKER PANEL, make sure circuit breakers listed below are open if chaff and/or flares are loaded:

NAME REFDEZ ZONE

CMD DSA FWD 70CBC007 Ñ15 R3

Ñ16 P5

CMD DSA AFT 70CBC009 Ñ15 R4

Ñ16 Q2

CMD PRGMR 70CBC011 Ñ15 R5

Ñ16 P2

6. Install safety clip assemblies.

7. Inspect area for foreign objects and close door 6L.

TO 1F-15C-2-05JG-00-1

5-8

Figure 05. Sheet 3

5-9

Ñ19 To prevent injury to personnel or damage to equipment, ALE-58 circuit breakers must be open before application of electrical power if chaff and/or flares are loaded.

8. Ñ19 Open door 10R.

9. Ñ19 On RIGHT BUS CIRCUIT BREAKER

PANEL NO. 1, open circuit breakers listed below:

NAME REFDEZ ZONE

AN/ALE-58 DC PWR 70CBF053 K6

AN/ALE-58 2A/2B PWR 70CBF051 Ñ15 B3

Ñ16 C3

AN/ALE-58 8A/8B PWR 70CBF052 Ñ15 D3

Ñ16 E3

10. Ñ19 Install safety clip assemblies.

11. Ñ19 Inspect area for foreign objects and close door 10R.

TO 1F-15C-2-05JG-00-1

5-10

Figure 05. Sheet 4

5-11

A/M 32A or MD-4 generator sets may be used as alternates to supply the electrical power requirements only. A/M 32A must be used if external ground cooling air is to be applied.

This task…