Commercial 

Airplanes 777

Service Bulletin

SPECIAL ATTENTION

Number: 777-32-0083

Original Issue: February 05, 2009

Revision 2: May 02, 2013

ATA System: 3211

SUBJECT: LANDING GEAR - Main Landing Gear - Retract Actuator Fuse Pin Inspection and

Replacement

Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15

CFR 300-774). An export license may be required before it is used for development, production or use by foreign

persons from specific countries. The controller of this data has the individual responsibility to abide by all export

laws.

ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET

Copyright © 2009 Boeing.

Unpublished Work. All Rights Reserved.

Treatment of this document and its content is governed by contract with Boeing. Rights to use this document

are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The

Boeing Company.

Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,

BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and

Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in

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4.0
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BOEING SERVICE BULLETIN 777-32-0083

BLANK PAGE
Table of Contents

Revision Transmittal Sheet ............................................ 5

Summary ...................................................... 7

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 18

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 22

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 22

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

FIGURE 1: LEFT MLG RETRACT ACTUATOR FUSE PIN INSPECTION . . . . . . . . . . . . . . . . 25

FIGURE 2: RIGHT MLG RETRACT ACTUATOR FUSE PIN INSPECTION . . . . . . . . . . . . . . . 27

FIGURE 3: LEFT MLG RETRACT ACTUATOR FUSE PIN REPLACEMENT . . . . . . . . . . . . . . 29

FIGURE 4: RIGHT MLG RETRACT ACTUATOR FUSE PIN REPLACEMENT . . . . . . . . . . . . . 32

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BOEING SERVICE BULLETIN 777-32-0083
Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 777-32-0083

BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

SPECIAL ATTENTION

Revision Transmittal Sheet Number: 777-32-0083

Original Issue: February 05, 2009

Revision 2: May 02, 2013

ATA System: 3211

SUBJECT: LANDING GEAR - Main Landing Gear - Retract Actuator Fuse Pin Inspection and

Replacement

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-12-08 is related to this service bulletin.

Group 1 only: No more work is necessary on the airplane(s) that have replaced 112W1769-1 Retract Actuator

Fuse Pins with 112W1769-3 Retract Actuator Fuse Pins in accordance with the Original Issue or Revision 1 of

this service bulletin and have not replaced 112W1769-3 Retract Actuator Fuse Pins with 112W1769-1 Retract

Actuator Fuse Pins.

Group 2 airplanes, 777-200 and 777-300 airplanes line number 164 through 1027, are added to this service

bulletin effectivity. Due to an interchangeability error in the Illustrated Parts Catalog (IPC), it is possible that

112W1769-1 Retract Actuator Fuse Pins were installed on 777-200 and 777-300 airplanes line number 164

through 1027.

REASON FOR REVISION

This revision is sent to update compliance time information for inspection and replacement of the 112W1769-1

fuse pin. This revision also added Group 2 airplanes.

These sections were changed:

1. In Summary, Background, added information about the addition of Group 2 airplanes.

2. In Summary, Background, added Summary Evaluation Table.

3. In Summary, Effectivity, added spares affected reference.

4. In Summary, Compliance, added FAA AD reference.

5. In Summary, Compliance, added information related to the future release of Airworthiness Directive.

6. In Paragraph 1.A.1, Airplanes, added 777-200 and 777-300 airplanes line number 164 through 1027

to Group 2.

7. In Paragraph 1.A.2, Spares Affected, added affected spares.

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5 of 34
8. In Paragraph 1.C., Reason, added information about the addition of Group 2 airplanes.

9. In Paragraph 1.E., Compliance, added FAA AD reference.

10. In Paragraph 1.E., Compliance, added information related to the future release of Airworthiness Directive.

11. In Paragraph 1.E., Compliance, updated compliance table description.

12. In Paragraph 1.E., Compliance, added effective date of Airworthiness Directive.

13. In Paragraph 1.E., Compliance added description for evaluating conditions and actions.

14. In Paragraph 1.E., Compliance, updated compliance time for All Airplanes condition.

15. In Paragraph 1.E., Compliance, updated compliance time for Condition 2A.

16. In Paragraph 1.E., Compliance, updated compliance time for Condition 2B.

17. In Paragraph 1.E., Compliance, updated compliance time for Condition 2C.

18. In Paragraph 1.E., Compliance, added Table 2 for Group 2 airplanes.

19. In Paragraph 1.F., Approval, added alternative method of compliance information for Group 1 airplanes.

20. In Paragraph 1.J.1., Existing Data, added FAA AD reference.

21. In Paragraph 1.K., Publications Affected, added Damage Tolerance Based Structural Inspections

statement.

22. In Paragraph 2.A., Material - Price and Availability, updated ROLT and Unit Price information.

23. In Paragraph 3.A., General Information, deleted note 1.

24. In Paragraph 3.B., Work Instructions, Part 2, added Retract Actuator Fuse Pin part number.

25. FIGURE 1, 2, 3, and 4, added Step Table description paragraph.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location

of important changes.

Pages with no vertical lines have no important changes.

REVISION HISTORY

Original Issue: February 05, 2009

Revision 1: February 17, 2011

Revision 2: May 02, 2013

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BOEING SERVICE BULLETIN 777-32-0083
Commercial 

Airplanes 777

Service Bulletin

SPECIAL ATTENTION

Summary Number: 777-32-0083

Original Issue: February 05, 2009

Revision 2: May 02, 2013

ATA System: 3211

SUBJECT: LANDING GEAR - Main Landing Gear - Retract Actuator Fuse Pin Inspection and

Replacement

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

Accomplishment of this service bulletin will find and replace 112W1769-1 Retract Actuator Fuse Pins. The

112W1769-1 Retract Actuator Fuse Pins have been found to crack and fail earlier than the previously determined

safe life limit of the pins. A fractured Retract Actuator Fuse Pin can cause the main landing gear (MLG) to extend

without restriction and attempt to lock into position under high dynamic loads. Unrestricted MLG extension could

cause structural damage to the side and drag brace lock assemblies, leading to unlocked drag and/or side

braces which could result in landing gear collapse during touchdown, rollout or taxi.

One operator reported that a right MLG 112W1769-1 pin sheared during normal flight operations. The failure

occurred on a pin with 10,874 flight cycles. The left MLG pin was also inspected and was found to be cracked.

Examination of the sheared pin concluded that the cracking was due to fatigue. Three other pins that were

reported to have cracks had between 10,000 and 11,000 flight cycles.

Subsequent to the release of Revision 1 of this service bulletin, it was found that the Illustrated Parts Catalog

(IPC) allowed interchangeability of 112W1769-1 Retract Actuator Fuse Pins with 112W1769-3 Retract Actuator

Fuse Pins on 777-200 and 777-300 airplanes line number 164 through 1027.

This service bulletin provides instructions to inspect the left and right MLG for 112W1769-1 Retract Actuator

Fuse Pins and to replace the affected pins with 112W1769-3 pins.

Boeing Service Related Problem (SRP) 777-SRP-57-0226 is related to this service bulletin.

Boeing Service Letter (SL) 777-SL-57-011 is related to this service bulletin.

Boeing Fleet Team Digest Article (FTD) 777 FTD 57-08005 is related to this service bulletin.

This table is provided to operators for planning purposes only. Refer to the applicable sections for more

information.

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7 of 34
Planning Data Affected Reference

Spares Affected Yes Paragraph 1.A.2., Spares Affected

AD Related Yes Paragraph 1.E., Compliance

Weight and Balance Change Yes Paragraph 1.H., Weight and Balance Changes

Electrical Load Changed No Paragraph 1.I., Electrical Load Data

Publications Affected Yes Paragraph 1.K., Publications Affected

Airplane Flight Operations Affected (Flight Crew No Paragraph 1.K., Publications Affected

Operations Manual and/or FAA Approved Airplane Flight Manual)

Kits/Parts Required Yes Paragraph 2.C.1., Kits/Parts

Paragraph 2.C.2., Parts and Materials Supplied

by the Operator

Operator Supplied Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

ACTION

Get access to the left and right MLG Retract Actuator Fuse Pins. Do an inspection of the Retract Actuator Fuse

Pins to identify the part number. If an affected pin is found, replace the pin. If an affected pin is not found, no

further action is required at that pin location.

EFFECTIVITY

777-200 and -300 Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.

Refer to Paragraph 1.A.2., Spares Affected for the list of affected components.

COMPLIANCE

Group 1:

Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-12-08 is related to this service bulletin.

Group 2:

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service

bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin

mandatory.

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the inspection, and/or repair procedures given in this service

bulletin.

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BOEING SERVICE BULLETIN 777-32-0083
MANPOWER

Airplanes Total Task Hours Elapsed Hours

All 4.50 3.00

MATERIAL INFORMATION

Boeing and Operator Supplied Parts/Materials.

Refer to Paragraph 2.A., Material - Price and Availability.

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BOEING SERVICE BULLETIN 777-32-0083
Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 777-32-0083
Commercial 

Airplanes 777

Service Bulletin

SPECIAL ATTENTION

Number: 777-32-0083

Original Issue: February 05, 2009

Revision 2: May 02, 2013

ATA System: 3211

SUBJECT: LANDING GEAR - Main Landing Gear - Retract Actuator Fuse Pin Inspection and

Replacement

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is for the airplanes shown below.

Refer to Service Bulletin Index Document D624W001 Part 3 for Airplane Variable Number, Line

Number, and Serial Number data.

GROUP CONFIGURATION DESCRIPTION

1 - 777-200 and 777-300 Airplanes with line numbers 1 through 163.

2 - 777-200 and 777-300 Airplanes with line numbers 164 through 1027.

Airplane Models:

777-200, 777-300

Variable Number Group

WA001 - WA017 1

WA076 - WA080 1

WA086 - WA093 1

WA101 - WA104 1

WA116 - WA119 1

WA131 - WA137 1

WA171 - WA175 1

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Variable Number Group

WA196 - WA198 1

WA206 - WA211 1

WA212 2

WA221 - WA223 1

WA231 - WA232 1

WA241 - WA250 2

WA261 - WA266 2

WA281 - WA283 2

WA301 - WA304 2

WB001 - WB014 1

WB015 - WB021 2

WB031 - WB046 2

WB051 - WB068 1

WB069 - WB088 2

WB101 - WB104 1

WB105 - WB106 2

WB121 - WB125 1

WB131 - WB133 1

WB134 - WB148 2

WB151 - WB153 1

WB154 - WB155 2

WB161 - WB169 1

WB170 - WB177 2

WB181 - WB186 1

WB187 - WB194 2

WB201 - WB215 2

WB231 - WB234 1

WB235 - WB247 2

WB271 - WB272 1

WB273 2

WB276 - WB286 1

WB291 - WB302 2

WB306 - WB307 1

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BOEING SERVICE BULLETIN 777-32-0083
Variable Number Group

WB311 - WB313 1

WB314 - WB335 2

WB336 1

WB337 2

WB341 - WB342 2

WB366 - WB368 2

WB371 1

WB372 - WB388 2

WB406 2

WB411 - WB413 2

WB416 - WB439 2

WB446 - WB453 2

WB476 2

WB481 - WB484 2

WB501 - WB504 1

WB505 - WB512 2

WB531 - WB534 1

WB535 - WB537 2

WB551 - WB552 1

WB553 - WB554 2

WB591 - WB592 1

WB593 - WB597 2

WB601 1

WB602 - WB606 2

WB611 - WB622 2

WB631 - WB638 2

WB646 - WB649 2

WC051 - WC073 2

WC101 - WC104 2

WC111 - WC120 2

WC221 - WC224 2

WC241 - WC243 2

WC281 - WC290 2

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BOEING SERVICE BULLETIN 777-32-0083
Variable Number Group

WC301 - WC308 2

WC361 - WC364 2

WC371 - WC374 2

WC381 - WC395 2

WC441 2

WC446 - WC449 2

WC456 - WC459 2

WC486 - WC493 2

WC506 - WC508 2

WC521 - WC522 2

WC531 - WC536 2

WC546 - WC548 2

WC556 2

WC566 - WC567 2

WC571 - WC574 2

WC581 2

WC586 2

WC591 - WC592 2

2. Spares Affected

Examine your spares supply for the part identified below. If the part is found, it is recommended

to remove the part from your spares supply.

Part Number

112W1769-1

B. Concurrent Requirements

None.

C. Reason

Accomplishment of this service bulletin will find and replace 112W1769-1 Retract Actuator Fuse Pins.

The 112W1769-1 Retract Actuator Fuse Pins have been found to crack and fail earlier than the previously

determined safe life limit of the pins. A fractured Retract Actuator Fuse Pin can cause the main landing

gear (MLG) to extend without restriction and attempt to lock into position under high dynamic loads.

Unrestricted MLG extension could cause structural damage to the side and drag brace lock assemblies,

leading to unlocked drag and/or side braces which could result in landing gear collapse during

touchdown, rollout or taxi.

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BOEING SERVICE BULLETIN 777-32-0083
One operator reported that a right MLG 112W1769-1 pin sheared during normal flight operations. The

failure occurred on a pin with 10,874 flight cycles. The left MLG pin was also inspected and was found

to be cracked. Examination of the sheared pin concluded that the cracking was due to fatigue. Three

other pins that were reported to have cracks had between 10,000 and 11,000 flight cycles.

Subsequent to the release of Revision 1 of this service bulletin, it was found that the Illustrated Parts

Catalog (IPC) allowed interchangeability of 112W1769-1 Retract Actuator Fuse Pins with 112W1769-3

Retract Actuator Fuse Pins on 777-200 and 777-300 airplanes line number 164 through 1027.

This service bulletin provides instructions to inspect the left and right MLG for 112W1769-1 Retract

Actuator Fuse Pins and to replace the affected pins with 112W1769-3 pins.

Boeing Service Related Problem (SRP) 777-SRP-57-0226 is related to this service bulletin.

Boeing Service Letter (SL) 777-SL-57-011 is related to this service bulletin.

Boeing Fleet Team Digest Article (FTD) 777 FTD 57-08005 is related to this service bulletin.

Revision 2 is sent to update compliance time information for inspection and replacement of the

112W1769-1 fuse pin. This revision also added Group 2 airplanes.

D. Description

Get access to the left and right MLG Retract Actuator Fuse Pins. Do an inspection of the Retract

Actuator Fuse Pins to identify the part number. If an affected pin is found, replace the pin. If an affected

pin is not found, no further action is required at that pin location.

Group 1:

Revision 2 - No more work is necessary on the airplane(s) that have replaced 112W1769-1 Retract

Actuator Fuse Pins with 112W1769-3 Retract Actuator Fuse Pins in accordance with the Original Issue

or Revision 1 of this service bulletin and have not replaced 112W1769-3 Retract Actuator Fuse Pins

with 112W1769-1 Retract Actuator Fuse Pins.

Group 2:

Revision 2 - Group 2 airplanes, 777-200 and 777-300 airplanes line number 164 through 1027, are

added to this service bulletin effectivity. Due to an interchangeability error in the Illustrated Parts Catalog

(IPC), it is possible that 112W1769-1 Retract Actuator Fuse Pins were installed on 777-200 and 777-300

airplanes line number 164 through 1027.

The work in this service bulletin is done in the maintenance zone(s) given below.

Affected Maintenance Zones

Model Zone

777-200, 777-300 731, 741

E. Compliance

Group 1:

Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-12-08 is related to this service

bulletin.

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BOEING SERVICE BULLETIN 777-32-0083
Group 2:

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to

this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this

service bulletin mandatory.

Accomplish Part 1 and Part 2 as required in Table 1 below in accordance with Paragraph 3.,

Accomplishment Instructions. Part 2 only affects airplanes with any 112W1769-1 MLG Retract Actuator

Fuse Pin installed.

NOTE: 1. The conditions, actions and compliance times below are based on flight cycles on each pin

since new, not flight cycles of the airplane on which the pin is installed.

2. The effective date of AD 2012-12-08 is July 30, 2012.

Evaluate the conditions and actions for the left and right Main Landing Gear (MLG) Retract Actuator

Fuse Pin separately.

Group 1:

Table 1: Inspection and Replacement of Retract Actuator Fuse Pin

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 18 months after the effec- -

tive date of AD 2012-12-08.

Inspect the pin in accordance with Part 1 - MLG

Retract Actuator Fuse Pin

Part Number Inspection.

All Airplanes

No further action is re- - -

quired for that fuse pin

location. (a)

Condition 1: 112W1769-3

MLG Retract Actuator Fuse

Pin Installed.

Within 18 months after the effec- -

tive date of AD 2012-12-08.

Replace the pin in accordance with Part 2 - MLG

Retract Actuator Fuse Pin

Replacement. (a)

Condition 2A: 112W1769-

1 MLG Retract Actuator

Fuse Pin installed with

greater than 10,000 flight

cycles (FC).

Within 18 -

months after the

effective date of

AD 2012-12-08.

Before 10,000

total flight-cycles on the pin.

Replace the pin in accordance with Part 2 - MLG

Retract Actuator Fuse Pin

Replacement. (a)

Condition 2B: 112W1769-

1 MLG Retract Actuator

Fuse Pin installed with

8,000 to 10,000 FC.

Within 24 -

months after the

effective date of

AD 2012-12-08.

Before 8,000 total flight-cycles

on the pin.

Replace the pin in accordance with Part 2 - MLG

Retract Actuator Fuse Pin

Replacement. (a)

Condition 2C: 112W1769-

1 MLG Retract Actuator

Fuse Pin installed with less

than 8,000 FC.

(a) The 112W1769-3 MLG Retract Actuator Fuse Pin is a safe life limited part. Refer to 777 MPD Section 9

for the safe life limits.

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BOEING SERVICE BULLETIN 777-32-0083
Group 2:

Table 2: Inspection and Replacement of Retract Actuator Fuse Pin

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 18 months after the Revi- -

sion 2 date of this service bulletin.

Inspect the pin in accordance with Part 1 - MLG

Retract Actuator Fuse Pin

Part Number Inspection.

All Airplanes

No further action is re- - -

quired for that fuse pin

location. (a)

Condition 1: 112W1769-3

MLG Retract Actuator Fuse

Pin Installed.

Within 18 months after the Revi- -

sion 2 date of this service bulletin.

Replace the pin in accordance with Part 2 - MLG

Retract Actuator Fuse Pin

Replacement. (a)

Condition 2A: 112W1769-

1 MLG Retract Actuator

Fuse Pin installed with

greater than 10,000 flight

cycles (FC).

Within 18 -

months after the

Revision 2 date

of this service

bulletin.

Before 10,000

total flight-cycles on the pin.

Replace the pin in accordance with Part 2 - MLG

Retract Actuator Fuse Pin

Replacement. (a)

Condition 2B: 112W1769-

1 MLG Retract Actuator

Fuse Pin installed with

8,000 to 10,000 FC.

Within 24 -

months after the

Revision 2 date

of this service

bulletin.

Before 8,000 total flight-cycles

on the pin.

Replace the pin in accordance with Part 2 - MLG

Retract Actuator Fuse Pin

Replacement. (a)

Condition 2C: 112W1769-

1 MLG Retract Actuator

Fuse Pin installed with less

than 8,000 FC.

(a) The 112W1769-3 MLG Retract Actuator Fuse Pin is a safe life limited part. Refer to 777 MPD Section 9

for the safe life limits.

F. Approval

This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified

in this service bulletin comply with the applicable regulations and are FAA approved, as well as European

Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved

airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on

the airplane in its original Boeing delivery configuration or as modified by other approved Boeing

changes.

If an airplane has a non-Boeing modification or repair that affects a component or system also affected

by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval

before incorporating this service bulletin.

Group 1:

In addition, the Manager of the FAA Seattle Aircraft Certification Office approves accomplishment of

the inspection and replacement defined in this service bulletin as an alternative method of compliance

to the inspection and replacement requirements of paragraph (g) of AD 2012-12-08. All provisions of

AD 2012-12-08 that are not specifically referenced in the above statement remain fully applicable and

must be complied with accordingly.

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BOEING SERVICE BULLETIN 777-32-0083
G. Manpower

Number of Per- Task Hours Elapsed Hours

sons

Task

Open Access 2 1.50 0.75

FIGURE 1 1 0.25 0.25

FIGURE 2 1 0.25 0.25

FIGURE 3 1 0.50 0.50

FIGURE 4 1 0.50 0.50

Close Access 2 1.50 0.75

TOTAL FOR EACH AIRPLANE 4.50 3.00

H. Weight and Balance Changes

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

All - 2.7 - 3628.0

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Boeing Service Letter 777-SL-57-011

b. Boeing Service Related Problem (SRP) 777-SRP-57-0226

c. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2012-12-08

d. 777 Aircraft Maintenance Manual (AMM) 06-44-00, 32-00-15, 32-00-30, 32-11-01

e. 777 Fleet Team Digest (FTD) 57-08005

f. 777 Maintenance Planning Data (MPD) Section 9

2. Data Supplied with this Service Bulletin:

None.

3. Installation Drawings Used in the Preparation of this Service Bulletin:

Drawing Number Title

161W0000 Installation - Main Landing Gear

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BOEING SERVICE BULLETIN 777-32-0083
This drawing was used to prepare this service bulletin. This drawing is not necessary to make the

specified changes, and is not supplied with this service bulletin. This drawing may not be applicable

to all airplane configurations or operators.

K. Publications Affected

1. Publications:

Publication Chapter-Section

777 Illustrated Parts Catalog 32-11

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue

Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the

Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary.

L. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

M. Software Accomplishment Summary

Not affected.

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BOEING SERVICE BULLETIN 777-32-0083
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BOEING SERVICE BULLETIN 777-32-0083

BLANK PAGE
2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the parts shown in Paragraph 2.C., Parts Necessary for Each Airplane as shown

below. Operators are encouraged to share schedule requirements with Boeing for incorporation of the

service bulletin. The parts are subject to the terms and conditions of the Boeing standard purchase

order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days.

Reference this service bulletin and submit your purchase order by one of these methods:

1. Order on-line via ATA Spec 2000 or The Boeing PART Page

2. Fax to (206) 662-7145

REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER

AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION

Unit Price as of the

Revision 2 date of

this Service Bulletin (US Dollars)

ROLT as of the Revision 2 date of this

Service Bulletin

(Calendar Days)

Part Number Name

112W1769-3 MLG Retract Actuator Fuse Pin 561 $700.00

B. Industry Support Information

Boeing warranty remedies are not available for the inspection, and/or repair procedures given in this

service bulletin.

C. Parts Necessary for Each Airplane

1. Kits/Parts

To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.

Existing Part Notes

Number

New Part Number QTY Name

(a) (b)

(c)

MLG Retract Actua- 112W1769-1

tor Fuse Pin

112W1769-3 2

(a) Discard the existing part.

(b) This part is used in production.

(c) You cannot use the existing part to replace the new or changed part.

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BOEING SERVICE BULLETIN 777-32-0083
2. Parts and Materials Supplied by the Operator

Part Number / QTY Name Notes

Specification

BMS3-27 (BMS3- - Corrosion Inhibiting Material (a)

38 Optional)

BACP18BC03A12P 2 Pin, Cotter

(a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for

supplier data.

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

F. Special Tooling Necessary to do this Service Bulletin

No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance

and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine

operator tool supply to make sure all necessary tools are available.

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BOEING SERVICE BULLETIN 777-32-0083
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR

OTHER ELECTRICAL DAMAGE.

NOTE: 1. This note has been deleted.

2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms.

3. Obey all of the warnings and cautions given in the specified manual sections.

4. Unless shown differently, these dimensions and tolerances are used:

– Linear dimensions are in inches

– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus

or minus 0.03 inch

– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch

– Angular tolerance is plus or minus 2 degrees

– Hole dimensions for standard solid rivets and fasteners are in Structural Repair

Manual (SRM) Chapter 51

– Torque limits to tighten nuts and bolts are in SRM Chapter 51

5. Use the approved fastener and process material substitutions in accordance with

SRM Chapter 51.

6. If the length of any fastener specified in this service bulletin does not meet installation

standards given in SRM Chapter 51, then a fastener of the same specification, or

an approved substitute, with a length which meets the installation standards given

in SRM Chapter 51 may be used. In addition, washers may be installed for fastener

grip length in accordance with SRM Chapter 51.

7. These work instructions refer to procedures included in other Boeing documents.

When the words "refer to" are used and the operator has an accepted alternative

procedure, the accepted alternative procedure can be used. When the words "in

accordance with" are included in the instruction, the procedure in the Boeing document

must be used.

8. If it is necessary to remove more parts for access, you can remove those parts. If

you can get access without removing identified parts, it is not necessary to remove

all of the identified parts. Jacking and shoring limitations must be observed.

9. Where the work instructions include installation of a kept part, a new or serviceable

part with the same part number can be installed as an alternative to the kept part.

The removed part can be discarded if a new or serviceable part is installed.

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BOEING SERVICE BULLETIN 777-32-0083
B. WORK INSTRUCTIONS

1. Install the Main Landing Gear (MLG) downlock pins. Refer to 777 AMM 32-00-30 as an accepted

procedure.

2. Install the MLG safety pins. Refer to 777 AMM 32-00-15 as an accepted procedure.

3. Open the following access panels on the left and right wing. Refer to 777 AMM 06-44-00 as an

accepted procedure.

– 551DB - Inboard Fixed Trailing Edge Panel

– 651DB - Inboard Fixed Trailing Edge Panel

4. Do Part 1 - MLG Retract Actuator Fuse Pin Part Number Inspection.

a. Condition 1: 112W1769-3 MLG Retract Actuator Fuse Pin installed.

(1) No further action is required for that fuse pin location.

b. Condition 2: 112W1769-1 MLG Retract Actuator Fuse Pin installed.

(1) Determine the total flight cycles on the MLG Retract Actuator Fuse Pin since new.

(2) Do Part 2 - MLG Retract Actuator Fuse Pin Replacement within the compliance time in

accordance with Paragraph 1.E., Compliance Condition 2A, 2B or 2C for that fuse pin

location.

(3) No further action is required for that fuse pin location.

5. Close the following access panels on the left and right wing. Refer to 777 AMM 06-44-00 as an

accepted procedure.

– 551DB - Inboard Fixed Trailing Edge Panel

– 651DB - Inboard Fixed Trailing Edge Panel

6. Remove the MLG safety pins. Refer to 777 AMM 32-00-15 as an accepted procedure.

7. Remove the Main Landing Gear (MLG) downlock pins. Refer to 777 AMM 32-00-30 as an accepted

procedure.

8. Put the airplane back to a serviceable condition.

Part 1 - MLG Retract Actuator Fuse Pin Part Number Inspection

1. Inspect the MLG Retract Actuator Fuse Pins to determine the part numbers in accordance with

FIGURE 1 for the left MLG and FIGURE 2 for the right MLG. As an alternative, a review of the

maintenance or delivery records can be used if the part number of the installed MLG Retract

Actuator Fuse Pin can be positively determined.

Part 2 - MLG Retract Actuator Fuse Pin Replacement

1. Replace the 112W1769-1 MLG Retract Actuator Fuse Pin in accordance with FIGURE 3 for the

left MLG and FIGURE 4 for the right MLG.

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BOEING SERVICE BULLETIN 777-32-0083
FIGURE 1: LEFT MLG RETRACT ACTUATOR FUSE PIN INSPECTION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-32-0083
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each component.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

to determine the part

number which is located on the head of

the pin.

Retract Actuator Fuse 112W1769 1

Pin

1 Inspect

FIGURE 1: LEFT MLG RETRACT ACTUATOR FUSE PIN INSPECTION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-32-0083
FIGURE 2: RIGHT MLG RETRACT ACTUATOR FUSE PIN INSPECTION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-32-0083
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each component.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

to determine the part

number which is located on the head of

the pin.

Retract Actuator Fuse 112W1769 1

Pin

1 Inspect

FIGURE 2: RIGHT MLG RETRACT ACTUATOR FUSE PIN INSPECTION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-32-0083
FIGURE 3: LEFT MLG RETRACT ACTUATOR FUSE PIN REPLACEMENT

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 777-32-0083
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each component.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to 777 AMM

32-11-01 as an accepted procedure.

Keep washers and

nut.

Retract Actuator Fuse 112W1769-1 1

Pin

1 Remove

Refer to 777 AMM

32-11-01 as an accepted procedure. A

new or overhauled

pin is acceptable.

Retract Actuator Fuse 112W1769-3 1

Pin

2 Install (New)

FIGURE 3: LEFT MLG RETRACT ACTUATOR FUSE PIN REPLACEMENT

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 777-32-0083
STEP TASK NAME IDENTIFICATION QTY MORE DATA

lightly coating the

thread group of the

pin and the washer

faces.

BMS3-27 (BMS3-38 -

optional)

Corrosion Inhibiting

Material

3 Apply

Tighten nut to 15-25

in-lbs over maximum

run on torque.

4 Install (Kept) Nut - 1

to the nearest

castellation to install

the cotter pin.

5 Loosen Nut - 1

6 Install (New) Cotter Pin BACP18BC03A12P 1

Wipe off all excess

material.

BMS3-27 (BMS3-38 -

optional)

Corrosion Inhibiting

Material

7 Remove

FIGURE 3: LEFT MLG RETRACT ACTUATOR FUSE PIN REPLACEMENT

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 777-32-0083
FIGURE 4: RIGHT MLG RETRACT ACTUATOR FUSE PIN REPLACEMENT

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 777-32-0083
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each component.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to 777 AMM

32-11-01 as an accepted procedure.

Keep washers and

nut.

Retract Actuator Fuse 112W1769-1 1

Pin

1 Remove

Refer to 777 AMM

32-11-01 as an accepted procedure. A

new or overhauled

pin is acceptable.

Retract Actuator Fuse 112W1769-3 1

Pin

2 Install (New)

FIGURE 4: RIGHT MLG RETRACT ACTUATOR FUSE PIN REPLACEMENT

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 777-32-0083
STEP TASK NAME IDENTIFICATION QTY MORE DATA

lightly coating the

thread group of the

pin and the washer

faces.

BMS3-27 (BMS3-38 -

optional)

Corrosion Inhibiting

Material

3 Apply

Tighten nut to 15-25

in-lbs over max run

on torque.

4 Install (Kept) Nut - 1

to the nearest

castellation to install

the cotter pin.

5 Loosen Nut - 1

6 Install (New) Cotter Pin BACP18BC03A12P -

Wipe off all excess

material.

BMS3-27 (BMS3-38 -

optional)

Corrosion Inhibiting

Material

7 Remove

FIGURE 4: RIGHT MLG RETRACT ACTUATOR FUSE PIN REPLACEMENT

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 777-32-0083