Commercial 

Airplanes 777

Service Bulletin

SPECIAL ATTENTION

Number: 777-27-0115

Original Issue: May 22, 2013

ATA System: 2731

SUBJECT: FLIGHT CONTROLS - Elevator Control System - Pitch Rate Sensor (PRS) 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 © 2013 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Unpublished Work.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

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BLANK PAGE
Table of Contents

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

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

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

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 . . . . . . . . . . . . . . . . . . . . . . . . 19

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 20

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

FIGURE 1: FORWARD CARGO COMPARTMENT - PITCH RATE SENSOR (PRS) INSPECTION . . 23

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BOEING SERVICE BULLETIN 777-27-0115

BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

SPECIAL ATTENTION

Summary Number: 777-27-0115

Original Issue: May 22, 2013

ATA System: 2731

SUBJECT: FLIGHT CONTROLS - Elevator Control System - Pitch Rate Sensor (PRS) Inspection

And Replacement

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

This service bulletin gives instructions to inspect maintenance records, and replace the existing flight control

system Pitch Rate Sensors (PRS) if the inspection finds it necessary. One of two possible part numbers of PRS

can produce erroneous output. If two PRS on one side of the airplane produce erroneous output, this could

cause an automatic disengagement of the autopilot and autoland at low altitude.

Boeing has received two reports of automatic autopilot disengagement. An investigation found that this was

caused by erroneous output by two existing PRS on one side of the airplane. The four (4) PRS each measure

the pitch rate of the airplane. If one PRS starts producing an erroneous output, the Primary Flight Control System

(PFCS) flags it as faulty and removes it from any control laws. If two PRS on the same side of an aircraft are

each flagged as faulty, this causes the PFCS to change from normal mode to secondary mode. The latest PRS

design was introduced in production in March 2012. Boeing has determined that the latest PRS design may be

less reliable than its preceding design.

Accomplishment of this service bulletin will make sure that the PRS version that was used in production before

March 2012 is installed in each of the four PRS locations on the airplane. Four (4) PRS are located behind the

endwall in the aft end of the forward cargo compartment, with two (2) each on the left and right hand sides. The

replacement PRS was produced by a different supplier, has a better service record, and is expected to decrease

the chance of automatic autopilot disengagement.

Boeing Service Related Problem (SRP) 777-SRP-27-0226 is related to this service bulletin.

Boeing Fleet Team Digest (FTD) 777 FTD 27-12001 is related to this service bulletin.

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

information.

Planning Data Affected Reference

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

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Planning Data Affected Reference

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 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 No Paragraph 2.C.1., Kits/Parts

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

by the Operator

Operator Supplied Parts/Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

ACTION

Group 1:

Check maintenance records to find if PRS part number 402875-03-01 is installed in all four (4) PRS locations.

If the maintenance records check does not find that PRS part number 402875-03-01 is installed in all four (4)

PRS locations: Open access to each of the four (4) PRS and inspect for the part number of each PRS in

accordance with PART 1. Replace each existing PRS part number 402875-05-01 with part number 402875-03-01

in accordance with PART 2. If records show no PRS part number 402875-05-01 have been installed, then no

further action is required.

Group 2:

Open access to each of the four (4) PRS and inspect for the part number of each PRS in accordance with PART

1. Replace each existing PRS part number 402875-05-01 with part number 402875-03-01 in accordance with

PART 2.

EFFECTIVITY

777-200LR/F/300/300ER 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 not available for the configuration changes given in this service bulletin.

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BOEING SERVICE BULLETIN 777-27-0115
MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Operator Supplied Parts/Materials.

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

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BOEING SERVICE BULLETIN 777-27-0115
Commercial 

Airplanes 777

Service Bulletin

SPECIAL ATTENTION

Number: 777-27-0115

Original Issue: May 22, 2013

ATA System: 2731

SUBJECT: FLIGHT CONTROLS - Elevator Control System - Pitch Rate Sensor (PRS) Inspection

And Replacement

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

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 airplanes shown below.

GROUP CONFIGURATION DESCRIPTION

777-200LR/F/300/300ER Airplanes L/N 94-998 and 1050-1110, that

had Pitch Rate Sensors 402875-03-01 installed in production, but

may have replaced one or more units with a 402875-05-01 in-service

1 -

777-200LR/F/300ER Airplanes L/N 999-1049, that had Pitch Rate

Sensors 402875-05-01 installed in production

2 -

Airplane Models:

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

Variable Number Group

WB501 - WB512 1

WB531 - WB537 1

WB551 - WB554 1

WB591 - WB597 1

WB601 - WB606 1

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Variable Number Group

WB611 - WB622 1

WB631 - WB638 1

WB646 - WB649 1

WD001 - WD002 1

WD011 - WD018 1

WD031 - WD036 1

WD046 - WD055 1

WD066 - WD075 1

WD081 - WD089 1

WD091 1

WD096 1

WD101 - WD105 1

WD111 1

WD116 1

WD117 2

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 - WD819 1

WD826 - WD837 1

WD846 - WD867 1

WD871 - WD887 1

WD888 2

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BOEING SERVICE BULLETIN 777-27-0115
Variable Number Group

WD889 - WD892 1

WD911 - WD915 1

WD916 - WD917 2

WD918 1

WD921 - WD922 1

WD923 2

WD924 - WD929 1

WD936 - WD939 1

WD940 - WD941 2

WD942 - WD943 1

WD946 - WD954 1

WD955 2

WD956 - WD957 1

WD966 - WD970 1

WD981 - WD982 1

WD986 - WD987 1

WD991 2

WD992 - 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 - WE093 1

WE126 - WE137 1

WE141 1

WE151 - WE155 1

WE156 - WE159 2

WE160 - WE163 1

WE176 - WE177 1

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BOEING SERVICE BULLETIN 777-27-0115
Variable Number Group

WE186 - WE192 1

WE193 - WE204 2

WE205 - WE207 1

WE216 - WE217 1

WE226 - WE228 1

WE229 - WE230 2

WE231 1

WE236 1

WE237 - WE240 2

WE241 - WE243 1

WE251 - WE253 2

WE261 2

WE262 - WE265 1

WE271 - WE272 2

WE273 - WE275 1

WE301 - WE307 1

WE331 - WE334 1

WE351 1

WE416 1

WF001 - WF004 1

WF016 - WF021 1

WF031 - WF034 1

WF035 2

WF036 - WF038 1

WF046 - WF059 1

WF060 - WF063 2

WF064 1

WF075 - WF077 1

WF081 - WF088 1

WF096 - WF101 1

WF106 - WF107 1

WF108 - WF109 2

WF111 - WF113 1

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BOEING SERVICE BULLETIN 777-27-0115
Variable Number Group

WF114 2

WF115 1

WF121 - WF124 1

WF131 - WF133 1

WF136 1

WF137 2

WF138 1

WF146 2

WF147 1

WF151 2

WF152 1

2. Spares Affected

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

are found, refer to Paragraph 2.C., Parts Necessary for Each Airplane, for the recommended

action.

Part Number

402875-05-01

B. Concurrent Requirements

None.

C. Reason

This service bulletin gives instructions to inspect maintenance records, and replace the existing flight

control system Pitch Rate Sensors (PRS) if the inspection finds it necessary. One of two possible part

numbers of PRS can produce erroneous output. If two PRS on one side of the airplane produce

erroneous output, this could cause an automatic disengagement of the autopilot and autoland at low

altitude.

Boeing has received two reports of automatic autopilot disengagement. An investigation found that this

was caused by erroneous output by two existing PRS on one side of the airplane. The four (4) PRS

each measure the pitch rate of the airplane. If one PRS starts producing an erroneous output, the

Primary Flight Control System (PFCS) flags it as faulty and removes it from any control laws. If two

PRS on the same side of an aircraft are each flagged as faulty, this causes the PFCS to change from

normal mode to secondary mode. The latest PRS design was introduced in production in March 2012.

Boeing has determined that the latest PRS design may be less reliable than its preceding design.

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BOEING SERVICE BULLETIN 777-27-0115
Accomplishment of this service bulletin will make sure that the PRS version that was used in production

before March 2012 is installed in each of the four PRS locations on the airplane. Four (4) PRS are

located behind the endwall in the aft end of the forward cargo compartment, with two (2) each on the

left and right hand sides. The replacement PRS was produced by a different supplier, has a better

service record, and is expected to decrease the chance of automatic autopilot disengagement.

Boeing Service Related Problem (SRP) 777-SRP-27-0226 is related to this service bulletin.

Boeing Fleet Team Digest (FTD) 777 FTD 27-12001 is related to this service bulletin.

D. Description

Group 1:

Check maintenance records to find if PRS part number 402875-03-01 is installed in all four (4) PRS

locations. If the maintenance records check does not find that PRS part number 402875-03-01 is

installed in all four (4) PRS locations: Open access to each of the four (4) PRS and inspect for the part

number of each PRS in accordance with PART 1. Replace each existing PRS part number 402875-05-01

with part number 402875-03-01 in accordance with PART 2. If records show no PRS part number

402875-05-01 have been installed, then no further action is required.

Group 2:

Open access to each of the four (4) PRS and inspect for the part number of each PRS in accordance

with PART 1. Replace each existing PRS part number 402875-05-01 with part number 402875-03-01

in accordance with PART 2.

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

Group 1:

Affected Maintenance Zones

Model Zone

777-200LR, 777-300, 777- 125, 126

300ER, 777F

Group 2:

Affected Maintenance Zones

Model Zone

777-200LR, 777-300ER, 777F 125, 126

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.

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BOEING SERVICE BULLETIN 777-27-0115
Group 1:

Table 1: Pitch Rate Sensor (PRS) - Inspection and Replacement

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 60 months -

after the original issue date of this

service bulletin.

Do a check of maintenance records to find if

PRS part number

402875-03-01 is installed

in all four (4) PRS locations.

All Airplanes

Within 60 months -

after the original issue date of this

service bulletin.

Do PART 1: PRS PART

NUMBER INSPECTION.

CONDITION 1:

THE MAINTENANCE

RECORDS CHECK DOES

NOT FIND THAT PRS

PART NUMBER 402875-

03-01 IS INSTALLED IN

ALL FOUR (4) PRS LOCATIONS

No further action is re- - -

quired.

CONDITION 2:

PRS PART NUMBER

402875-03-01 IS INSTALLED IN ALL FOUR

(4) PRS LOCATIONS

Do PART 2: REPLACE- Before further flight -

MENT OF PRS PART

NUMBER 402875-05-01

WITH 402875-03-01.

CONDITION 3:

ONE OR MORE OF THE

FOUR (4) PRS WITH

PART NUMBER 402875-

05-01 IS FOUND

No further action is re- - -

quired.

CONDITION 4:

PRS PART NUMBER

402875-03-01 IS FOUND

IN ALL FOUR (4) PRS LOCATIONS

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

Group 2:

Table 1: Pitch Rate Sensor (PRS) - Inspection and Replacement

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 60 months -

after the original issue date of this

service bulletin.

Do PART 1: PRS PART

NUMBER INSPECTION.

All Airplanes

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BOEING SERVICE BULLETIN 777-27-0115
Group 2:

Table 1: Pitch Rate Sensor (PRS) - Inspection and Replacement

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Do PART 2: REPLACE- Before further flight -

MENT OF PRS PART

NUMBER 402875-05-01

WITH 402875-03-01.

CONDITION 3:

ONE OR MORE OF THE

FOUR (4) PRS WITH

PART NUMBER 402875-

05-01 IS FOUND

No further action is re- - -

quired

CONDITION 4:

PRS PART NUMBER

402875-03-01 IS FOUND

IN ALL FOUR (4) PRS LOCATIONS

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 airplane.

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.

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 0.75 0.75

Figure 1 1 0.20 0.20

Replace (a) 1 0.65 0.65

Test (a) 1 0.35 0.35

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BOEING SERVICE BULLETIN 777-27-0115
Task Number of Persons Task Hours Elapsed Hours

Close Access 1 0.75 0.75

TOTAL FOR EACH AIRPLANE 1.70 1.70

(a) Estimates given for these tasks are for each PRS that requires replacement

and are not included in total shown. Multiply the number of PRS units requiring

replacement by the estimates shown and add to the totals given to calculate

the revised total.

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Boeing Service Related Problem (SRP) 777-SRP-27-0226

b. Service Bulletin Index D624W001

c. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19

d. 777 Aircraft Maintenance Manual (AMM) 25-52-17, 27-31-11

e. 777 Fleet Team Digest (FTD) 27-12001

2. Data Supplied with this Service Bulletin:

None.

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

None.

K. Publications Affected

1. Publications:

Publication Chapter-Section

777 Wiring Diagram Manual Equipment list

777 Illustrated Parts Catalog 27-31

2. Damage Tolerance Based Structural Inspections:

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BOEING SERVICE BULLETIN 777-27-0115
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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BOEING SERVICE BULLETIN 777-27-0115
2. MATERIAL INFORMATION

A. Material - Price and Availability

The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each

Airplane . As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin

does not show the Boeing price and supply data.

B. Industry Support Information

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

C. Parts Necessary for Each Airplane

1. Kits/Parts

None.

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 Existing Part Number Notes

Specification

402875-03-01 4 PITCH RATE SENSOR 402875-05-01 (a) (b)

(a) This part is used in production.

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

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.

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BOEING SERVICE BULLETIN 777-27-0115
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 777-27-0115
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. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,

and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.

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

information from the critical and authoritative information.

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

are in Paragraph 1.E., Compliance.

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BOEING SERVICE BULLETIN 777-27-0115
B. WORK INSTRUCTIONS

1. Group 1:

Do a check of maintenance records to find if PRS part number 402875-03-01 is installed in all four

(4) PRS locations.

CONDITION 1: THE MAINTENANCE RECORDS CHECK DOES NOT FIND THAT PRS PART

NUMBER 402875-03-01 IS INSTALLED IN ALL FOUR (4) PRS LOCATIONS

a. Do PART 1: PRS PART NUMBER INSPECTION.

CONDITION 2: PRS PART NUMBER 402875-03-01 IS INSTALLED IN ALL FOUR (4) PRS

LOCATIONS

a. No further action is required.

2. Group 2:

Do PART 1: PRS PART NUMBER INSPECTION.

PART 1: PRS PART NUMBER INSPECTION

1. Remove the aft end wall of forward cargo compartment. Refer to 777 AMM 25-52-17 as an accepted

procedure.

2. Inspect for the part number of each PRS, in accordance with FIGURE 1.

CONDITION 3: ONE OR MORE OF THE FOUR (4) PRS WITH PART NUMBER 402875-05-01

IS FOUND

a. Do PART 2: REPLACEMENT OF PRS PART NUMBER 402875-05-01 WITH 402875-03-01.

CONDITION 4: PRS PART NUMBER 402875-03-01 IS FOUND IN ALL FOUR (4) PRS

LOCATIONS

a. Close the aft end wall of forward cargo compartment. Refer to 777 AMM 25-52-17 as an

accepted procedure.

b. Put the airplane back to a serviceable condition.

PART 2: REPLACEMENT OF PRS PART NUMBER 402875-05-01 WITH 402875-03-01

1. Replace each existing PRS part number 402875-05-01 with part number 402875-03-01. Refer to

777 AMM 27-31-11 as an accepted procedure.

2. Do the PRS system test. Refer to 777 AMM 27-31-11 as an accepted procedure.

3. Close the aft end wall of forward cargo compartment. Refer to 777 AMM 25-52-17 as an accepted

procedure.

4. Put the airplane back to a serviceable condition.

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FIGURE 1: FORWARD CARGO COMPARTMENT - PITCH RATE SENSOR (PRS) INSPECTION

(SHEET 1 OF 2)

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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 this figure.

Step Task Name Identification Qty More Data

1 Inspect PITCH RATE SENSOR - 4 (a)

(a) Record the part number of each PRS.

FIGURE 1: FORWARD CARGO COMPARTMENT - PITCH RATE SENSOR (PRS) INSPECTION

(SHEET 2 OF 2)

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