Commercial 

Airplanes 757

Service Bulletin

Number: 757-28-0136

Original Issue: June 05, 2014

ATA System: 2841

SUBJECT: FUEL - Fuel Quantity Indicating System - Built-In Test Equipment Test/Procedure

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ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET

Copyright © 2014 Boeing.

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BLANK PAGE
Table of Contents

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 14

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 15

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 15

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

FIGURE 1: MAIN EQUIPMENT CENTER - FUEL QUANTITY PROCESSOR UNIT - INSPECT . . . . 20

APPENDIX A: HONEYWELL FUEL QUANTITY BITE TEST . . . . . . . . . . . . . . . . . . . . . . . . . 22

APPENDIX B: HONEYWELL FUEL QUANTITY BITE - NON-DISPATCHABLE FAULT CODES . . . . . 24

APPENDIX C: SIMMONDS/GOODRICH FUEL QUANTITY BITE PROCEDURE . . . . . . . . . . . . . . 25

APPENDIX D: SIMMONDS/GOODRICH FUEL QUANTITY BITE - NON-DISPATCHABLE FAULT MESSAGES

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

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BLANK PAGE
Commercial 

Airplanes 757

Service Bulletin

Summary Number: 757-28-0136

Original Issue: June 05, 2014

ATA System: 2841

SUBJECT: FUEL - Fuel Quantity Indicating System - Built-In Test Equipment Test/Procedure

CONCURRENT REQUIREMENTS

Refer to Paragraph 1.B., Concurrent Requirements.

BACKGROUND

This service bulletin gives instructions to identify fault code(s) or fault message(s) that are non-dispatchable

fault(s) for the 757 freighters. There is a potential that certain latent failures of the Fuel Quantity Indicating System

(FQIS) inside the tank and a hot short failure outside the tank may introduce an ignition source inside the Center

Wing Tank (CWT). Doing the tests in this service bulletin will minimize fault(s) in the CWT FQIS that could affect

tank safety.

Based on the Fuel Tank Flammability Reduction Rule requirements, 757 passenger airplanes are required to

have the Nitrogen Generation System (NGS) installed in order to reduce the Center Wing Tank (CWT) flammability

exposure. The freighters are not required to have the NGS installed. There is a potential that certain latent

failures of the FQIS inside the tank combined with a hot short failure outside the tank may introduce an ignition

source in the Center Wing Tank. To reduce the probability of latent failures for the 757 airplanes without the

NGS system installed, the Fuel Quantity Processor Unit (FQPU) Built-In Test Equipment (BITE) Test/Procedure

should be performed at regular intervals.

Boeing Service Related Problem (SRP) 757-SRP-28-0148 is related to this service bulletin.

NOTE: 757 freighter airplanes are exempt from installing the Nitrogen Generation System.

This service bulletin is the result of the safety assessments conducted by Boeing under a Special Federal Aviation

Regulation (SFAR) 88, Fuel Tank System Fault Tolerance Evaluation Requirements.

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

information.

Planning Data Affected Reference

Spares Affected No Paragraph 1.A.2., Spares Affected

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related No

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

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

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Planning Data Affected Reference

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 No 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

Get access to the Main Equipment Center at the E3-4 electronics shelf to find if the FQPU is Honeywell or

Simmonds/Goodrich. Do the Fuel Quantity BITE Test/Procedure. Record the fault code(s) if any are shown

during the Fuel Quantity BITE Test/Procedure. Compare the fault code(s) with APPENDIX B or APPENDIX D

and do repair.

EFFECTIVITY

757-200/200PF Freighter Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).

COMPLIANCE

Refer to Paragraph 1.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.

INDUSTRY SUPPORT INFORMATION

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

service bulletin.

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

None.

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BLANK PAGE
Commercial 

Airplanes 757

Service Bulletin

Number: 757-28-0136

Original Issue: June 05, 2014

ATA System: 2841

SUBJECT: FUEL - Fuel Quantity Indicating System - Built-In Test Equipment Test/Procedure

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is applicable to 757-200, 757-200PF Freighter Airplanes.

Refer to Service Bulletin Index D624N001 Part 3 for Airplane Variable Number, Line Number, and

Serial Number data.

GROUP CONFIGURATION DESCRIPTION

1 - BITE Test - for 757 Freighter Airplanes.

1 Honeywell Fuel Quantity BITE Test.

2 Simmonds/Goodrich Fuel Quantity BITE Procedure.

Airplane Models:

757-200, 757-200PF

Variable Number Group

NA201 - NA204 1

NA206 - NA213 1

NA215 - NA236 1

NC901 - NC951 1

NC971 1

NC973 - NC974 1

NS601 - NS616 1

NT001 - NT009 1

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2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

This service bulletin gives instructions to identify fault code(s) or fault message(s) that are

non-dispatchable fault(s) for the 757 freighters. There is a potential that certain latent failures of the

Fuel Quantity Indicating System (FQIS) inside the tank and a hot short failure outside the tank may

introduce an ignition source inside the Center Wing Tank (CWT). Doing the tests in this service bulletin

will minimize fault(s) in the CWT FQIS that could affect tank safety.

Based on the Fuel Tank Flammability Reduction Rule requirements, 757 passenger airplanes are

required to have the Nitrogen Generation System (NGS) installed in order to reduce the Center Wing

Tank (CWT) flammability exposure. The freighters are not required to have the NGS installed. There

is a potential that certain latent failures of the FQIS inside the tank combined with a hot short failure

outside the tank may introduce an ignition source in the Center Wing Tank. To reduce the probability

of latent failures for the 757 airplanes without the NGS system installed, the Fuel Quantity Processor

Unit (FQPU) Built-In Test Equipment (BITE) Test/Procedure should be performed at regular intervals.

NOTE: 757 freighters are exempt from installing the Nitrogen Generating System.

This service bulletin is the result of the safety assessments conducted by Boeing under a Special

Federal Aviation Regulation (SFAR) 88, Fuel Tank System Fault Tolerance Evaluation Requirements.

Boeing Service Related Problem (SRP) 757-SRP-28-0148 is related to this service bulletin.

D. Description

Get access to the Main Equipment Center at the E3-4 electronics shelf to find if the FQPU is Honeywell

or Simmonds/Goodrich. Do the Fuel Quantity BITE Test/Procedure. Record the fault code(s) if any are

shown during the Fuel Quantity BITE Test/Procedure. Compare the fault code(s) with APPENDIX B

or APPENDIX D and do repair.

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

Affected Maintenance Zones

Model Zone

757-200, 757-200PF 119

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 757-28-0136
Table 1: INSPECTION TO DETERMINE FQPU

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 6 months 750 flight hours.

after the original issue date of the

Service Bulletin.

Inspect for part number

on the FQPU to determine if the FQPU is Honeywell or Simmonds/Goodrich.

757 Freighter airplanes.

At the times in Ta- -

ble 2.

757 Freighter airplanes Do the actions in Table 2.

with Honeywell FQPU.

At the times in Ta- -

ble 3.

757 Freighter airplanes Do the actions in Table 3.

with Simmonds/Goodrich

FQPU.

Group 1, Configuration 1:

Table 2: BUILT-IN TEST EQUIPMENT TEST HONEYWELL FQPU

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 6 months 750 flight hours.

after the original issue date of the

Service Bulletin.

Do FUEL QUANTITY

BITE Test and record

fault code(s).

Compare the fault

code(s).

757 Freighter airplanes

with Honeywell FQPU.

For fault code(s) recorded - -

that are not in APPENDIX

B, use operator's procedure for disposition.

CONDITION 1: NO FAULT

CODE(S) DISPLAYED

THAT ARE LISTED IN APPENDIX B.

No further action required.

Before further -

flight.

In APPENDIX B, use the

FIM TASK in the row of

the Fault Code(s) recorded, to determine the necessary repair and do repair.

CONDITION 2: FAULT

CODE(S) DISPLAYED

ARE LISTED IN APPENDIX B.

Repeat Fuel Quantity

BITE Test and record

fault code(s) and Compare the fault code(s) until CONDITION 1 occurs.

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Group 1, Configuration 2:

Table 3: BUILT-IN TEST EQUIPMENT - SIMMONDS/GOODRICH FQPU

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 6 months 750 flight hours.

after the original issue date of this

service bulletin.

Do FUEL QUANTITY

BITE Procedure and

record fault message(s).

Compare the fault message(s).

757 Freighter airplanes

with Simmonds/Goodrich

FQPU.

For fault code(s) recorded - -

that are not in APPENDIX

D, use operator's procedure for disposition.

CONDITION 3: NO FAULT

MESSAGE(S) DISPLAYED

THAT ARE LISTED IN APPENDIX D.

No further action required.

Before further -

flight.

In APPENDIX D, use the

FIM TASK in the row of

the Fault Message(s)

recorded, to determine

the necessary repair and

do repair.

CONDITION 4: FAULT

MESSAGE(S) DISPLAYED

ARE LISTED IN APPENDIX D.

Repeat Fuel Quantity

BITE Test and record

fault message(s) and

Compare the fault message(s) until CONDITION

3 occurs.

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 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

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BOEING SERVICE BULLETIN 757-28-0136
• Time to inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools.

Group 1, Configuration 1:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 0.50 0.50

Figure 1 1 0.10 0.10

Test 1 0.25 0.25

Close Access 1 0.50 0.50

TOTAL FOR EACH AIRPLANE 1.35 1.35

The time to make the change to get CONDITION 1 results in accordance with Fault Isolation Manual

is not included.

Group 1, Configuration 2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 0.50 0.50

Figure 1 1 0.10 0.10

Test 1 0.25 0.25

Close Access 1 0.50 0.50

TOTAL FOR EACH AIRPLANE 1.35 1.35

The time to make the change to get CONDITION 3 results in accordance with Fault Isolation Manual

is not included.

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Boeing Service Related Problem (SRP) 757-SRP-28-0148

b. Service Bulletin Index D624N001

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BOEING SERVICE BULLETIN 757-28-0136
c. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-15, 20-10-19, 20-20-00

d. 757 Aircraft Maintenance Manual (AMM) 06-41-00, 06-44-00, 24-22-00

e. 757 Fault Isolation Manual (FIM) 28-41

f. 757 Wiring Diagram Manual (WDM) 28-21-11

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:

None.

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

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

M. Software Accomplishment Summary

Not affected.

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2. MATERIAL INFORMATION

A. Material - Price and Availability

None.

B. Industry Support Information

Boeing warranty remedies are not available for the configuration changes and/or repair procedures

given in this service bulletin.

C. Parts Necessary for Each Airplane

1. Kits/Parts

None.

2. Parts and Materials Supplied by the Operator

None.

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

None.

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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 Values:

— Values for structural fasteners are given in 757 Structural Repair Manual,

Chapter 51.

— Values for airframe maintenance tasks are included in Chapter 20 of Airplane

Maintenance Manual (AMM).

— Values for electrical maintenance tasks are included in Chapter 20 of

Standard Wiring Practices Manual (SWPM).

— Values for engine maintenance tasks are included in Chapter 70 of 757

Airplane Maintenance Manual (AMM).

— Non-standard torque values for maintenance tasks are included in the

applicable installation step.

4. 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.

5. 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.

6. Refer to APPENDIX A for HONEYWELL FUEL QUANTITY BITE TEST and

APPENDIX B for HONEYWELL FUEL QUANTITY BITE - NON-DISPATCHABLE

FAULT CODES.

7. Refer to APPENDIX C for SIMMONDS/GOODRICH FUEL QUANTITY BITE

PROCEDURE and APPENDIX D for SIMMONDS/GOODRICH FUEL QUANTITY

BITE - NON-DISPATCHABLE FAULT MESSAGES.

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BOEING SERVICE BULLETIN 757-28-0136
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. This service bulletin includes functional test procedures for the systems changed by

this service bulletin. More functional tests can possibly be necessary in accordance

with standard maintenance practices because of interruption to other airplane systems.

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

are in Paragraph 1.E., Compliance.

11. Some steps in the Work Instructions are identified as Required for Compliance (RC).

If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps

identified as RC must be done to comply with the AD. Alternative procedures for

steps not identified with RC can be used if the RC steps can still be done as specified,

and the airplane can be put back in a serviceable condition. An Alternative Method

of Compliance (AMOC) is not necessary for deviations to steps that are not identified

as RC.

B. WORK INSTRUCTIONS

1. Supply electrical power to the airplane. Refer to 757 AMM 24-22-00 as an accepted procedure.

2. Open the Main Equipment Center (MEC) door to get access to the E3-4 electronics shelf. Refer

to 757 AMM 06-41-00.

3. RC - At E3-4 electronics shelf, inspect for part number on Fault Quantity Processor Unit (FQPU)

in accordance with FIGURE 1 determine if the FQPU is Honeywell or Simmonds/Goodrich and

follow the applicable procedure.

FUEL QUANTITY PROCESSOR UNIT APPLICABLE PROCEDURE

HONEYWELL GROUP 1, CONFIGURATION 1

SIMMONDS/GOODRICH GROUP 1, CONFIGURATION 2

4. Group 1, Configuration 1:

Honeywell procedure.

a. RC - Do Fuel Quantity BITE Test and record fault code(s) in accordance with APPENDIX A.

b. RC - Compare the fault code(s) recorded during the Fuel Quantity BITE Test with faults code(s)

listed in APPENDIX B.

(1) CONDITION 1: NO FAULT CODE(S) DISPLAYED THAT ARE LISTED IN APPENDIX

B.

(a) For fault code(s) recorded that are not in APPENDIX B, use operator's procedure

for disposition.

(b) No further action required.

(c) Close MEC access door. Refer to 757 AMM 06-41-00.

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(d) Put the airplane back to a serviceable condition.

(2) CONDITION 2: FAULT CODE(S) DISPLAYED ARE LISTED IN APPENDIX B.

(a) RC - In APPENDIX B, use the FIM TASK in the row of the Fault Code(s) recorded,

to determine the necessary repair and do the repair. Refer to SWPM 20-10-15 and

SWPM 20-20-00 as accepted procedures for wire repairs.

(b) Repeat work instruction 4a and 4b until CONDITION 1: NO FAULT CODE(S)

DISPLAYED THAT ARE LISTED IN APPENDIX B occurs.

5. Group 1, Configuration 2:

Simmonds/Goodrich procedure.

a. RC - Do Fuel Quantity BITE Procedure and record fault message(s) in accordance with

APPENDIX C.

b. RC - Compare the fault message(s) recorded during the Fuel Quantity BITE Procedure with

faults codes listed in APPENDIX D.

(1) CONDITION 3: NO FAULT MESSAGE(S) DISPLAYED THAT ARE LISTED IN APPENDIX

D.

(a) For fault code(s) recorded that are not in APPENDIX D, use operator's procedure

for disposition.

(b) No further action required.

(c) Close MEC access door. Refer to 757 AMM 06-41-00.

(d) Put the airplane back to a serviceable condition.

(2) CONDITION 4: FAULT MESSAGE(S) DISPLAYED ARE LISTED IN APPENDIX D.

(a) RC - In APPENDIX D, use the SHEET in the row of the Fault Message(s) recorded,

to determine the necessary repair and do the repair. Refer to SWPM 20-10-15 and

SWPM 20-20-00 as accepted procedures for wire repairs.

(b) Repeat work instruction 5a and 5b until CONDITION 3: NO FAULTS DISPLAYED

THAT ARE LISTED IN APPENDIX D occurs.

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FIGURE 1: MAIN EQUIPMENT CENTER - FUEL QUANTITY PROCESSOR UNIT - INSPECT

(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 each airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Honeywell FQPU. Use Group

1 1, Configuration 1 instructions.

S345T002-( )

(HG1064AA( ))

FUEL QUANTITY

PROCESSOR UNIT

1 INSPECT

(a)

Simmonds/Goodrich FQPU.

Use Group 1, Configuration 2

instructions. 1

S345N001-( )

(3007-( ))

FUEL QUANTITY

PROCESSOR UNIT

2 INSPECT

(a)

(a) Inspect for part number.

FIGURE 1: MAIN EQUIPMENT CENTER - FUEL QUANTITY PROCESSOR UNIT - INSPECT

(SHEET 2 OF 2)

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HONEYWELL FUEL QUANTITY BITE TEST

(1) Make sure the system is in this configuration: Electrical Power On. Refer to 757 AMM 24-22-00 as an accepted

procedure.

(2) Close this access panel, 621GB. The fueling station door must be closed for this test. Refer to 757 AMM

06-44-00 for the location of fueling station door.

(3) Open this access panel, 119BL. Refer to 757 AMM 06-41-00 for the location of the electrical equipment door.

(4) Go into the main equipment center.

(5) PRESS TEST Procedure.

– (a) On the FQPU, push and hold the PRESS TEST switch for a minimum of one second and a maximum

of seven seconds.

– (b) Make sure the FQPU display shows the number 88.

– (c) Release the PRESS TEST Switch.

– (d) Make sure the FQPU display goes off.

(6) RESET Procedure.

NOTE: Performing the "RESET" function erases all fault codes in the processor memory.

– (a) Push the RESET Switch for one second and release.

– (b) Make sure the FQPU Display shows the status code F1. (Reset in progress)

– (c) After approximately 22 seconds, make sure the FQPU display shows the status code F2. (Reset

successful)

– 1) If the FQPU display shows the status code F3, (Reset fail), wait 45 seconds and do the RESET

procedure again.

NOTE: The FQPU display must show the status code F2 before you do the VERIFY procedure.

(7) VERIFY Procedure

– (a) Push the VERIFY switch for 1 second and release it.

– (b) Make sure the processor display shows the status code F4 (Verify in progress).

– (c) If the processor display shows the status code F5 (Verify no faults) after 40 seconds, then the system

is OK.

– (d) If the processor display shows F6 (Verify faults exist) after 40 seconds, do these steps:

– 1) Push the VERIFY switch for 1 second and release it to cause the processor display to go off.

– 2) Push the BIT switch for 1 second and release it.

– 3) Make a written record of the fault code(s) shown.

– 4) Continue to push and release the BIT switch while you make a written record of all the fault codes

shown.

– (e) When the status codes 00, F8, or F9 shows on the processor display, all the fault codes are shown.

– (f) Push the BIT switch for 1 second and release it.

– (g) Make sure the processor display goes off.

APPENDIX A: HONEYWELL FUEL QUANTITY BITE TEST

(SHEET 1 OF 2)

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NOTE: If necessary wait for 45 seconds before you can do this procedure again.

APPENDIX A: HONEYWELL FUEL QUANTITY BITE TEST

(SHEET 2 OF 2)

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HONEYWELL FQIS BITE - NON-DISPATCHABLE FAULT CODES

Fault Most Probable Fault FIM TASK

Code

21 Left Center Tank Unit no.1 (Resistance Low) 28-41 Task 876 - Table 125

22 Left Center Tank Unit no.2 (Resistance Low) 28-41 Task 876 - Table 125

23 Left Center Tank Unit no.3 (Resistance Low) 28-41 Task 876 - Table 125

24 Left Center Tank Unit no.4 (Resistance Low) 28-41 Task 876 - Table 125

25 Left Center Tank Unit no.5 (Resistance Low) 28-41 Task 876 - Table 125

26 Right Center Tank Unit no.6 (Resistance Low) 28-41 Task 876 - Table 125

27 Right Center Tank Unit no.7 (Resistance Low) 28-41 Task 876 - Table 125

28 Right Center Tank Unit no.8 (Resistance Low) 28-41 Task 876 - Table 125

29 Right Center Tank Unit no.9 (Resistance Low) 28-41 Task 876 - Table 125

71 Left Center Tank Unit Wiring No.1 28-41 Task 879 - Table 128

72 Left Center Tank Unit Wiring No.2 28-41 Task 879 - Table 128

73 Left Center Tank Unit Wiring No.3 28-41 Task 879 - Table 128

74 Left Center Tank Unit Wiring No.4 28-41 Task 879 - Table 128

75 Left Center Tank Unit Wiring No.5 28-41 Task 879 - Table 128

76 Right Center Tank Unit Wiring No.6 28-41 Task 880 - Table 129

77 Right Center Tank Unit Wiring No.7 28-41 Task 880 - Table 129

78 Right Center Tank Unit Wiring No.8 28-41 Task 880 - Table 129

79 Right Center Tank Unit Wiring No.9 28-41 Task 880 - Table 129

C2 Center Tank Compensator (Resistance Low) 28-41 Task 853 - Table 105

C5 Center Tank Compensator Wiring 28-41 Task 855 - Table 107

APPENDIX B: HONEYWELL FUEL QUANTITY BITE - NON-DISPATCHABLE FAULT CODES

(SHEET 1 OF 1)

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SIMMONDS/GOODRICH FUEL QUANTITY BITE PROCEDURE

(1) Make sure the system is in this configuration: Electrical Power On. Refer to 757 AMM 24-22-00 as an accepted

procedure.

NOTE: The BITE Display Board on the processor will come on during airplane power-up. The menu will be

inactive when you push the ON button on the front panel of the processor during the power-up condition

for approximately 90 seconds.

(2) Close this access panel, 621GB. The fueling station door must be closed for this test. Refer to 757 AMM

06-44-00 for the location of fueling station door.

(3) Open this access panel, 119BL. Refer to 757 AMM 06-41-00 for the location of the electrical equipment door.

(4) Go into the main equipment center.

(5) FQIS "SELF TEST ?" procedure

– (a) On the fuel quantity processor unit (FQPU), press and hold the "ON/OFF" button for a minimum of one

second.

NOTE: If the processor BITE display is not ON after you push the "ON/OFF" button more than once, make

sure power is supplied to the processor (757 WDM 28-21-11)

– (b) Make sure the processor display shows "PRESENT_FAULTS_?".

– (c) Push and release the "NO" button until the "SELF_TEST_?" message shows.

– (d) Push and release the "YES" button.

– (e) When the message "BEGIN_SELF_TEST_?" shows, push and release the "YES" button.

NOTE: The self test will use 90 seconds, and the message "TEST_IN_PROGRESS" will show.

– (f) If "TEST_COMPLETE_SELF_TEST_PASS" shows on the display. System OK.

– (g) If "TEST_COMPLETE_LIST_FAULTS_?" shows on the display, push and release the "YES" button first

and the "DOWN" button next to see the faults. Continue to push and release the "DOWN" button until all

the fault messages are shown. Make a written record of the fault messages shown.

– (h) Push and release the "DOWN" button.

– (i) When the message "END_OF_SELF_TEST_FAULTS" shows on the display, all the self test faults

messages are shown.

– (j) Push and release the "MENU" button to take you back to "SELF TEST ?" or the "ON/OFF" button to turn

OFF the processor display.

APPENDIX C: SIMMONDS/GOODRICH FUEL QUANTITY BITE PROCEDURE

(SHEET 1 OF 1)

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SIMMONDS/GOODRICH FQIS BITE - NON-DISPATCHABLE FAULT MESSAGES

SHEET

(Refer to 757 FIM 28-41 FAULT

TREE 847 Fig.108 as an accepted procedure)

Fault Message

CT TU ## OPEN LOZ OR HIZ WIRE Sheet 2

CT TU ## SHORTED TO GROUND Sheet 6

CT TU ?? SHORTED TO GROUND Sheet 36

CT COMP OPEN LOZ OR HIZ WIRE Sheet 7

CT COMP SHORTED TO GROUND Sheet 10

CT HIZ WIRE OPEN AT PROCESSOR Sheet 13

CT HIZ WIRE LOW RESISTANCE Sheet 15

CT HIZ SHIELD SHORT TO GND Sheet 17

The ## Tank Unit Number From 1 to 9.

The ?? = Can not determine the unit.

APPENDIX D: SIMMONDS/GOODRICH FUEL QUANTITY BITE - NON-DISPATCHABLE FAULT MESSAGES

(SHEET 1 OF 1)

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