Commercial 

Airplanes 777

Service Bulletin

SPECIAL ATTENTION

Number: 777-32-0083

Original Issue: February 05, 2009

Revision 1: February 17, 2011

ATA System: 3211

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

Replacement

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2.0
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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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

1. Existing Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

2. Data supplied with this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

3. Installation Drawings Used in the Preparation of this Service Bulletin . . . . . . . . . . . . 15

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 18

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 18

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

FIGURE 1: LEFT MLG RETRACT ACTUATOR FUSE PIN INSPECTION . . . . . . . . . . . . . . . . 21

FIGURE 2: RIGHT MLG RETRACT ACTUATOR FUSE PIN INSPECTION . . . . . . . . . . . . . . . 23

FIGURE 3: LEFT MLG RETRACT ACTUATOR FUSE PIN REPLACEMENT . . . . . . . . . . . . . . 25

FIGURE 4: RIGHT MLG RETRACT ACTUATOR FUSE PIN REPLACEMENT . . . . . . . . . . . . . 28

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BOEING SERVICE BULLETIN 777-32-0083
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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 1: February 17, 2011

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

No more work is necessary on the airplane(s) changed in accordance with the original issue of this service

bulletin.

REASON FOR REVISION

This revision is sent to add an optional material for the Corrosion Inhibiting Material.

These sections were changed:

1. In Paragraph 2.A., Material - Price and Availability, updated table to current standards.

2. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator, added BMS3-38 as optional to BMS3-27

in Part Number Specification column.

3. In Paragraph 3.A., General Information, added Note 5, 6, 8 and 9 to the note list.

4. In Figure 3, step 3, added BMS3-38 as optional to BMS3-27 in Identification column.

5. In Figure 3, step 7, added BMS3-38 as optional to BMS3-27 in Identification column.

6. In Figure 4, step 3, added BMS3-38 as optional to BMS3-27 in Identification column.

7. In Figure 4, step 7, added BMS3-38 as optional to BMS3-27 in Identification column.

The data given in Information Notice 777-32-0083 IN 01 is included in this revision.

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.

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REVISION HISTORY

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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 1: February 17, 2011

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.

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.

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.

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EFFECTIVITY

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

COMPLIANCE

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.

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
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BOEING SERVICE BULLETIN 777-32-0083

BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

SPECIAL ATTENTION

Number: 777-32-0083

Original Issue: February 05, 2009

Revision 1: February 17, 2011

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 Airplanes with line numbers 1-163.

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

WA221 - WA223 1

WA231 - WA232 1

WB001 - WB014 1

WB051 - WB068 1

WB101 - WB104 1

WB121 - WB125 1

WB131 - WB133 1

WB151 - WB153 1

WB161 - WB169 1

WB181 - WB186 1

WB231 - WB234 1

WB271 - WB272 1

WB276 - WB286 1

WB306 - WB307 1

WB311 - WB313 1

WB336 1

WB371 1

WB501 - WB504 1

WB531 - WB534 1

WB551 - WB552 1

WB591 - WB592 1

WB601 1

2. Spares Affected

None.

B. Concurrent Requirements

None.

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BOEING SERVICE BULLETIN 777-32-0083
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.

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.

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.

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.

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

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

Accomplishment Instructions.

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.

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BOEING SERVICE BULLETIN 777-32-0083
Table 1: Inspection and Replacement of Retract Actuator Fuse Pin

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 6 months -

after the Date of

the Original Issue

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 6 months -

after the Date of

the Original Issue

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).

Before 10,000 FC -

on the pin or within

12 months after the

Date of the Original

Issue of this Service Bulletin,

whichever occurs

later.

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.

Before 8,000 FC -

on the pin or within

24 months after the

Date of the Original

Issue of this Service Bulletin,

whichever occurs

later.

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.

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

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

e. 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

Publication Chapter-Section

777 Illustrated Parts Catalog 32-11

L. Interchangeability and Intermixability of Parts

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

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BOEING SERVICE BULLETIN 777-32-0083
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

orignal issue date

of this Service Bulletin (US Dollars)

ROLT as of

the original

issues date

of this Service Bulletin

(Calendar

Days)

Part Number Name

112W1769-3 MLG Retract Actuator Fuse Pin 588 $769.00

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. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s)

give the recommended sequence of steps. The sequence of steps to do this service

bulletin can be changed.

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 into 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 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
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
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
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
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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29 of 30

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