Commercial 

Airplanes 777

Service Bulletin

ALERT

Number: 777-52A0050

Original Issue: June 18, 2013

ATA System: 5211

SUBJECT: DOORS - Passenger Entry Doors - Girt Bar Floor Fitting - Spring Pin 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 © 2013 Boeing.

Unpublished Work. All Rights Reserved.

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

Boeing Company.

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BLANK PAGE
Table of Contents

Summary ...................................................... 5

1. PLANNING INFORMATION ........................................ 9

A. Effectivity ................................................ 9

1. Airplanes ............................................. 9

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

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

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

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

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 17

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 20

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 21

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

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

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

FIGURE 1: PASSENGER ENTRY DOOR - GIRT BAR FLOOR FITTING - SPRING PIN REPLACEMENT

[Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

FIGURE 2: PASSENGER ENTRY DOOR - GIRT BAR FLOOR FITTING - SPRING PIN REPLACEMENT

[Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

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BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

ALERT

Summary Number: 777-52A0050

Original Issue: June 18, 2013

ATA System: 5211

SUBJECT: DOORS - Passenger Entry Doors - Girt Bar Floor Fitting - Spring Pin Replacement

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

This service bulletin gives instructions to replace the existing girt bar floor fitting spring pins at the passenger

entry doors with new spring pins that have improved resistance to stress corrosion cracking. If the work given

in this service bulletin is not done, the existing girt bar floor fitting spring pins could develop stress corrosion

cracks and eventually migrate or break. Broken or migrated girt bar floor fitting spring pins could prevent one or

more passenger entry door escape slides from deploying properly during an emergency. If escape slides do not

deploy properly during an emergency, delayed evacuation and serious injury to cabin occupants could occur.

Four operators have reported a total of 23 corroded, migrated, or broken girt bar floor fitting spring pins on nine

different airplanes. One of the operators reported that a broken girt bar floor fitting spring pin prevented a door

escape slide from deploying during a maintenance test.

Boeing has completed analysis on three broken spring pins and has determined that the spring pins failed due

to stress corrosion cracking.

Accomplishment of this service bulletin will ensure that the girt bar floor fitting spring pins are free of stress

corrosion cracking that could prevent proper escape slide deployment during an emergency. The new spring

pin material has demonstrated sufficient service life when used in similar applications on other Boeing model

airplanes.

Boeing Fleet Team Digest (FTD) article 777 FTD 52-12002 is related to this service bulletin.

Boeing Service Related Problem (SRP) 777-SRP-52-0102 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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Planning Data Affected Reference

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

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

Weight and Balance Change No Paragraph 1.H., Weight and Balance Changes

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

Publications Affected No 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 Parts/Material No

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

ACTION (PRR 62777-90S)

At each of the passenger entry doors on the airplane, remove the girt bar floor fitting spring pins. Install new girt

bar floor fitting spring pins that have improved resistance to stress corrosion cracking. Accomplish all actions in

accordance with Paragraph 1.E., Compliance.

EFFECTIVITY

777-200, 777-200LR, 777-300, 777-300ER, and 777F airplanes. Refer to Paragraph 1.A.1., Airplanes, for the

list of affected airplanes.

COMPLIANCE

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 available for airplanes in warranty as of March 14, 2012. Please refer to Paragraph

2.B., Industry Support Information. The warranty remedies will expire eight years from the original issue date of

this service bulletin.

MANPOWER

Airplanes Total Task Hours Elapsed Hours

Group 1 10.00 2.50

Group 2 2.50 1.25

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MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

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BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

ALERT

Number: 777-52A0050

Original Issue: June 18, 2013

ATA System: 5211

SUBJECT: DOORS - Passenger Entry Doors - Girt Bar Floor Fitting - Spring Pin Replacement

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

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

Serial Number data.

This service bulletin is for the airplane(s) shown below. An equivalent change is on subsequent

production airplanes. Refer to PRR 62777-90S for data about this change.

GROUP CONFIGURATION DESCRIPTION

777-200, 777-200LR, 777-300, and 777-300ER airplanes, line

numbers 1 through 1134.

1 -

2 - 777F airplanes, line numbers 1 through 1134.

Airplane Models:

777-200, 777-200LR, 777-300, 777-300ER, 777F

Variable Number Group

WA001 - WA017 1

WA076 - WA080 1

WA086 - WA093 1

WA101 - WA104 1

WA116 - WA119 1

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Variable Number Group

WA131 - WA137 1

WA171 - WA175 1

WA196 - WA198 1

WA206 - WA212 1

WA221 - WA223 1

WA231 - WA232 1

WA241 - WA250 1

WA261 - WA266 1

WA281 - WA283 1

WA301 - WA304 1

WB001 - WB021 1

WB031 - WB046 1

WB051 - WB088 1

WB101 - WB106 1

WB121 - WB125 1

WB131 - WB148 1

WB151 - WB155 1

WB161 - WB177 1

WB181 - WB194 1

WB201 - WB215 1

WB231 - WB247 1

WB271 - WB273 1

WB276 - WB286 1

WB291 - WB302 1

WB306 - WB307 1

WB311 - WB337 1

WB341 - WB342 1

WB366 - WB368 1

WB371 - WB388 1

WB406 1

WB411 - WB413 1

WB416 - WB439 1

WB446 - WB453 1

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Variable Number Group

WB476 1

WB481 - WB484 1

WB501 - WB512 1

WB531 - WB537 1

WB551 - WB554 1

WB591 - WB597 1

WB601 - WB606 1

WB611 - WB622 1

WB631 - WB638 1

WB646 - WB649 1

WC051 - WC073 1

WC101 - WC104 1

WC111 - WC120 1

WC221 - WC224 1

WC241 - WC243 1

WC281 - WC290 1

WC301 - WC308 1

WC361 - WC364 1

WC371 - WC374 1

WC381 - WC395 1

WC441 1

WC446 - WC449 1

WC456 - WC459 1

WC486 - WC493 1

WC506 - WC508 1

WC521 - WC522 1

WC531 - WC536 1

WC546 - WC548 1

WC556 1

WC566 - WC567 1

WC571 - WC574 1

WC581 1

WC586 - WC587 1

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Variable Number Group

WC591 - WC595 1

WD001 - WD002 1

WD011 - WD018 1

WD031 - WD036 1

WD046 - WD055 1

WD066 - WD075 1

WD081 - WD089 1

WD091 1

WD096 1

WD101 - WD106 1

WD111 1

WD116 - WD117 1

WD501 - WD513 1

WD521 - WD541 1

WD546 - WD554 1

WD561 - WD573 1

WD581 - WD599 1

WD606 - WD609 1

WD621 - WD632 1

WD651 - WD665 1

WD671 - WD677 1

WD691 - WD709 1

WD741 - WD752 1

WD761 - WD771 1

WD786 - WD788 1

WD796 - WD821 1

WD826 - WD837 1

WD846 - WD867 1

WD871 - WD892 1

WD911 - WD918 1

WD921 - WD929 1

WD936 - WD957 1

WD966 - WD970 1

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Variable Number Group

WD981 - WD982 1

WD986 - WD987 1

WD991 - WD993 1

WD996 1

WE001 - WE004 1

WE011 - WE012 1

WE021 - WE026 1

WE031 - WE034 1

WE051 - WE055 1

WE071 - WE072 1

WE081 - WE084 1

WE091 - WE094 1

WE126 - WE137 1

WE141 - WE142 1

WE151 - WE166 1

WE176 - WE177 1

WE186 - WE209 1

WE216 - WE217 1

WE226 - WE231 1

WE236 - WE243 1

WE251 - WE253 1

WE261 - WE265 1

WE271 - WE277 1

WE291 1

WE301 - WE309 1

WE331 - WE334 1

WE351 - WE352 1

WE416 - WE417 1

WF001 - WF004 2

WF016 - WF023 2

WF031 - WF038 2

WF046 - WF065 2

WF075 - WF077 2

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Variable Number Group

WF081 - WF088 2

WF096 - WF101 2

WF106 - WF109 2

WF111 - WF115 2

WF121 - WF124 2

WF131 - WF133 2

WF136 - WF138 2

WF146 - WF147 2

WF151 - WF152 2

2. Spares Affected

Examine your spares supply for the parts or components identified below. If any parts or components

are found, refer to Paragraph 3.B., Work Instructions for the recommended action.

Part Number

MS39086-261

MS16562-252

131W1830-1107

131W1830-1108

131W1830-1109

131W1830-1110

131W1830-1111

131W1830-1112

131W1830-1113

131W1830-1114

131W1830-1115

131W1830-1116

131W1830-1117

131W1830-1118

B. Concurrent Requirements

None.

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C. Reason

This service bulletin gives instructions to replace the existing girt bar floor fitting spring pins at the

passenger entry doors with new spring pins that have improved resistance to stress corrosion cracking.

If the work given in this service bulletin is not done, the existing girt bar floor fitting spring pins could

develop stress corrosion cracks and eventually migrate or break. Broken or migrated girt bar floor fitting

spring pins could prevent one or more passenger entry door escape slides from deploying properly

during an emergency. If escape slides do not deploy properly during an emergency, delayed evacuation

and serious injury to cabin occupants could occur.

Four operators have reported a total of 23 corroded, migrated, or broken girt bar floor fitting spring pins

on nine different airplanes. One of the operators reported that a broken girt bar floor fitting spring pin

prevented a door escape slide from deploying during a maintenance test.

Boeing has completed analysis on three broken spring pins and has determined that the spring pins

failed due to stress corrosion cracking.

Accomplishment of this service bulletin will ensure that the girt bar floor fitting spring pins are free of

stress corrosion cracking that could prevent proper escape slide deployment during an emergency.

The new spring pin material has demonstrated sufficient service life when used in similar applications

on other Boeing model airplanes.

Boeing Fleet Team Digest (FTD) article 777 FTD 52-12002 is related to this service bulletin.

Boeing Service Related Problem (SRP) 777-SRP-52-0102 is related to this service bulletin.

D. Description

At each of the passenger entry doors on the airplane, remove the girt bar floor fitting spring pins. Install

new girt bar floor fitting spring pins that have improved resistance to stress corrosion cracking.

Accomplish all actions in accordance with Paragraph 1.E., Compliance.

The work in this service bulletin is done in the maintenance zones given below.

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

Group 1:

Affected Maintenance Zones

Model Zone

777-200, 777-200LR, 777-300, 831, 832, 834, 835, 841, 842, 844, 845

777-300ER

Group 2:

Affected Maintenance Zones

Model Zone

777F 831, 841

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E. Compliance

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.

Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.

Table 1: Passenger Entry Door - Girt Bar Floor Fitting - Spring Pin Replacement

Condition Action Compliance Time

Within 1175 days after the Original

Issue date of this service bulletin.

At each passenger entry door location, replace the spring pin at both

girt bar floor fittings in accordance

with Paragraph 3.B., Work Instructions. (a)

All airplanes.

(a) Accomplishment of spring pin replacement at all girt bar floor fitting locations is terminating action for this

service bulletin.

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.

G. Manpower

The table below shows an estimate of the task hours necessary to do this change for each passenger

entry door location. This estimate is for direct labor only, done by an experienced crew. Adjust the

estimate with operator task hour data if necessary. The estimate does not include lost time. These are

some examples of lost time:

• Time to adjust to the workplace

• Time to schedule the work

• Time to inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools.

Group 1:

Task Number of Persons Task Hours Elapsed Hours

Figure 1 4 10.00 2.50

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Group 1:

Task Number of Persons Task Hours Elapsed Hours

TOTAL FOR EACH AIRPLANE 10.00 2.50

Group 2:

Task Number of Persons Task Hours Elapsed Hours

Figure 2 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 2.50 1.25

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Engineering Change Memo PRR 62777-90S

b. Boeing Service Related Problem (SRP) 777-SRP-52-0102

c. Service Bulletin Index D624W001

d. Standard Overhaul Practices Manual (SOPM) 20-50-01

e. 777 Aircraft Maintenance Manual (AMM) 52-11-00, 52-11-18

f. 777 Fleet Team Digest (FTD) 52-12002

2. Data Supplied with this Service Bulletin:

None.

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

Drawing Number Title

131W1800 Emergency System Installation - Passenger Entry Doors

The table above lists applicable drawings used to prepare this service bulletin. The drawings are

not necessary to make the specified changes, and are not supplied with this service bulletin. The

drawings may not be applicable to all airplane configurations or operators.

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ALERT ALERT
K. Publications Affected

1. Publications:

Publication Chapter-Section

777 Illustrated Parts Catalog 52-11

Component Maintenance Manual 52-12-80

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 does not affect FCS, therefore DTIs are not necessary.

L. Interchangeability and Intermixability of Parts

Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability

information.

M. Software Accomplishment Summary

Not affected.

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ALERT ALERT
2. MATERIAL INFORMATION

A. Material - Price and Availability

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

date of this Service Bulletin (US

Dollars)

ROLT as of the

Original Issue

date of this Service Bulletin (Calendar Days)

Part Number Name Date QTY

BACP18BE16N1000U Spring Pin (a) 1500 141 0.97

(a) Boeing expects replacement spring pins to be available immediately after release of the Original Issue of

this service bulletin.

B. Industry Support Information

Boeing warranty remedies are available for 777 airplanes in warranty as of March 14, 2012. For task

hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Warranty

& Product Assurance Contracts. The parts for airplanes in warranty as of that date will be supplied at

no charge. Send a purchase order for the parts to Boeing Material Management. Please refer to this

service bulletin number and reference the airplane variable number(s) in your purchase order. The

warranty remedies will expire eight years from the original issue date of 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.

NOTE: The parts shown below and the items shown in Paragraph 2.C.2., Parts and Materials

Supplied by the Operator, are necessary for each passenger entry door location on the

airplane.

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Existing Part Notes

Number

New Part Number QTY Name

(a) (b)

(c) (d)

MS39086-261

or

BACP18BE16N1000U 2 Spring Pin

MS16562-252

(a) The quantity shown is the quantity required to make the change at each passenger entry door.

(b) Discard the existing part.

(c) The new part is used in production. The new part is required to terminate the

required actions in this service bulletin.

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

2. Parts and Materials Supplied by the Operator

The following parts or materials are necessary to do the change in this service bulletin. Parts and

materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine

operator part and material supply to make sure all necessary parts and materials are available.

Part Number / QTY Name Notes

Specification

1 Grease (a)

ounce

BMS 3-33

(a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)

for supplier data.

3. Parts Modified and Reidentified

Existing Part QTY Name New Part Number Notes

Number

Passenger Entry Door - (b) (c)

- Girt Bar Mechanism -

Floor Fitting Assy

131W1830-( ) 2 (a)

(a) Two parts are changed at each passenger entry door location.

(b) Make the change in accordance with this service bulletin.

(c) There is no equivalent Boeing part number for the changed part. Identify on the part that

the change done in accordance with this service bulletin was made.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

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

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Part Number Name QTY

BACP18BE16N1000U Spring Pin 1 (a)

(a) One part is necessary for each 131W1830-( ) Passenger Entry Door -

Girt Bar Mechanism - Floor Fitting Assy found in operators inventory.

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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ALERT ALERT

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

definition of the acronyms.

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

3. 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

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

SRM Chapter 51.

5. 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. Refer to SOPM 20-50-01 for alternate

full threaded fasteners (screws) needed for installation in this service bulletin.

6. 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.

7. 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.

8. 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.

9. Shaded areas in Figures are to separate the non-critical and non-authoritative

information from the critical and authoritative information.

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10. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS

are in Paragraph 1.E., Compliance.

B. WORK INSTRUCTIONS

1. Open each of the passenger entry doors. Refer to 777 AMM 52-11-00 as an accepted procedure.

2. Group 1:

At each passenger entry door location, replace the spring pin at both girt bar floor fittings in

accordance with FIGURE 1.

NOTE: Overwing exit doors on 777-300 and 777-300ER airplanes do not have girt bar floor

fittings and do not require the change given in this service bulletin.

3. Group 2:

At each passenger entry door location, replace the spring pin at both girt bar floor fittings in

accordance with FIGURE 2.

4. Do a check of the girt bar floor fittings and correct any discrepancies found. Refer to 777 AMM

52-11-18 as an accepted procedure.

5. Close each of the passenger entry doors. Refer to 777 AMM 52-11-00 as an accepted procedure.

6. Put the airplane back to a serviceable condition.

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This Figure applies only to: Group 1.

FIGURE 1: PASSENGER ENTRY DOOR - GIRT BAR FLOOR FITTING - SPRING PIN REPLACEMENT

(SHEET 1 OF 3)

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FIGURE 1: PASSENGER ENTRY DOOR - GIRT BAR FLOOR FITTING - SPRING PIN REPLACEMENT

(SHEET 2 OF 3)

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ALERT ALERT
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 passenger entry door location.

Step Task Name Identification Qty More Data

MS39086-261 OR 1 (a)

MS16562-252

1 Remove Existing Spring Pin

Remove / Keep Pawl 131W1832-( ) 1 (a)

Remove / Keep Spring 131W1836-( ) 1 (a)

2 Install (Kept) Spring 131W1836-( ) 1 (a) (b) (c)

Install (Kept) Pawl 131W1832-( ) 1 (a) (c)

Install (New) Spring Pin BACP18BE16N1000U 1 (a) (c)

(a) Do this step at each passenger entry door location and each girt bar floor fitting. For Group 1 airplanes,

a total quantity of 16 spring pins should be replaced on each airplane.

(b) Make sure the spring is oriented as shown. The two free legs of the spring should be nested inside the

pawl. The looped end of the spring should sit on the surface of the floor fitting.

(c) Apply BMS 3-33 grease to the hole of the pawl and the entire spring pin prior to installation of the spring

pin. After spring pin installation, apply a light coating of BMS 3-33 grease to all accessible areas of the

spring pin and the spring under the pawl.

FIGURE 1: PASSENGER ENTRY DOOR - GIRT BAR FLOOR FITTING - SPRING PIN REPLACEMENT

(SHEET 3 OF 3)

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This Figure applies only to: Group 2.

FIGURE 2: PASSENGER ENTRY DOOR - GIRT BAR FLOOR FITTING - SPRING PIN REPLACEMENT

(SHEET 1 OF 3)

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FIGURE 2: PASSENGER ENTRY DOOR - GIRT BAR FLOOR FITTING - SPRING PIN REPLACEMENT

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 777-52A0050

ALERT ALERT
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 passenger entry door girt bar floor fitting

location.

Step Task Name Identification Qty More Data

MS39086-261 OR 1 (a)

MS16562-252

1 Remove Existing Spring Pin

Remove / Keep Pawl 131W1832-( ) 1 (a)

Remove / Keep Spring 131W1836-( ) 1 (a)

2 Install (Kept) Spring 131W1836-( ) 1 (a) (b) (c)

Install (Kept) Pawl 131W1832-( ) 1 (a) (c)

Install (New) Spring Pin BACP18BE16N1000U 1 (a) (c)

(a) Do this step at each passenger entry door location and each girt bar floor fitting. For Group 2 airplanes,

a total quantity of 4 spring pins should be replaced on each airplane.

(b) Make sure the spring is oriented as shown. The two free legs of the spring should be nested inside the

pawl. The looped end of the spring should sit on the surface of the floor fitting.

(c) Apply BMS 3-33 grease to the hole of the pawl and the entire spring pin prior to installation of the spring

pin. After spring pin installation, apply a light coating of BMS 3-33 grease to all accessible areas of the

spring pin and the spring under the pawl.

FIGURE 2: PASSENGER ENTRY DOOR - GIRT BAR FLOOR FITTING - SPRING PIN REPLACEMENT

(SHEET 3 OF 3)

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