### 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 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. 9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2014 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

Original Issue: June 05, 2014 757-28-0136 1 of 26 4.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 2 of 26 **BOEING SERVICE BULLETIN 757-28-0136**

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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 3 of 26 **BOEING SERVICE BULLETIN 757-28-0136**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 4 of 26 **BOEING SERVICE BULLETIN 757-28-0136**

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.
**Reference Affected**  **Planning Data** Paragraph 1.A.2., Spares Affected No Spares Affected Paragraph 1.E., Compliance and Paragraph 1.F., Approval No AD Related Paragraph 1.H., Weight and Balance Changes No Weight and Balance Change Paragraph 1.I., Electrical Load Data No Electrical Load Changed

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 5 of 26**Reference Affected**  **Planning Data** Paragraph 1.K., Publications Affected No Publications Affected Paragraph 1.K., Publications Affected No Airplane Flight Operations Affected (Flight CrewOperations Manual and/or FAA Approved Airplane Flight Manual) Paragraph 2.C.1., Kits/Parts No Kits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator No Operator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin No Special Tooling Required

**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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 6 of 26 **BOEING SERVICE BULLETIN 757-28-0136**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 7 of 26 **BOEING SERVICE BULLETIN 757-28-0136**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 8 of 26 **BOEING SERVICE BULLETIN 757-28-0136**

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.
**DESCRIPTION CONFIGURATION**  **GROUP** BITE Test - for 757 Freighter Airplanes.

- 1 Honeywell Fuel Quantity BITE Test. 1 Simmonds/Goodrich Fuel Quantity BITE Procedure. 2

Airplane Models: 757-200, 757-200PF **Group Variable Number**  1 NA201 - NA204 1 NA206 - NA213 1 NA215 - NA236 1 NC901 - NC951 1 NC971 1 NC973 - NC974 1 NS601 - NS616 1 NT001 - NT009

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 9 of 262. 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 Zone**  **Model** 119 757-200, 757-200PF **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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 10 of 26 **BOEING SERVICE BULLETIN 757-28-0136 Table 1: INSPECTION TO DETERMINE FQPU**  **Repeat Interval (Not to Exceed)**  **Compliance Time Action**  **Condition** 750 flight hours. Within 6 monthsafter the original issue date of the Service Bulletin. Inspect for part numberon the FQPU to determine if the FQPU is Honeywell or Simmonds/Goodrich. 757 Freighter airplanes.

- At the times in Ta- ble 2. Do the actions in Table 2. 757 Freighter airplanes with Honeywell FQPU.

- At the times in Ta- ble 3. Do the actions in Table 3. 757 Freighter airplanes with Simmonds/Goodrich FQPU. **Group 1, Configuration 1: Table 2: BUILT-IN TEST EQUIPMENT TEST HONEYWELL FQPU**  **Repeat Interval (Not to Exceed)**  **Compliance Time Action**  **Condition** 750 flight hours. Within 6 monthsafter 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 APPENDIXB, use operator's procedure for disposition. CONDITION 1: NO FAULT CODE(S) DISPLAYEDTHAT ARE LISTED IN APPENDIX B. No further action required.

- Before further flight. In APPENDIX B, use the FIM TASK in the row ofthe Fault Code(s) recorded, to determine the necessary repair and do repair. CONDITION 2: FAULT CODE(S) DISPLAYEDARE LISTED IN APPENDIX B.
Repeat Fuel Quantity BITE Test and recordfault code(s) and Compare the fault code(s) until CONDITION 1 occurs.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 11 of 26 **BOEING SERVICE BULLETIN 757-28-0136 Group 1, Configuration 2:**  **Table 3: BUILT-IN TEST EQUIPMENT - SIMMONDS/GOODRICH FQPU Repeat Interval**  **(Not to Exceed) Compliance Time**  **Action Condition**  750 flight hours. Within 6 monthsafter 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 APPENDIXD, use operator's procedure for disposition. CONDITION 3: NO FAULT MESSAGE(S) DISPLAYEDTHAT 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) DISPLAYEDARE LISTED IN APPENDIX D.
Repeat Fuel Quantity BITE Test and record fault message(s) andCompare 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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 12 of 26 **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: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.50 0.50 1 Open Access 0.10 0.10 1 Figure 1 0.25 0.25 1 Test 0.50 0.50 1 Close Access 1.35 1.35 TOTAL FOR EACH AIRPLANE The time to make the change to get CONDITION 1 results in accordance with Fault Isolation Manual is not included.
**Group 1, Configuration 2: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.50 0.50 1 Open Access 0.10 0.10 1 Figure 1 0.25 0.25 1 Test 0.50 0.50 1 Close Access 1.35 1.35 TOTAL FOR EACH AIRPLANE 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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 13 of 26 **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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 14 of 26 **BOEING SERVICE BULLETIN 757-28-0136 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 15 of 26 **BOEING SERVICE BULLETIN 757-28-0136**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 16 of 26 **BOEING SERVICE BULLETIN 757-28-0136**

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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 17 of 26 **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.
**APPLICABLE PROCEDURE FUEL QUANTITY PROCESSOR UNIT**  GROUP 1, CONFIGURATION 1 HONEYWELL GROUP 1, CONFIGURATION 2 SIMMONDS/GOODRICH
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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 18 of 26 **BOEING SERVICE BULLETIN 757-28-0136**(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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 19 of 26 **BOEING SERVICE BULLETIN 757-28-0136 FIGURE 1: MAIN EQUIPMENT CENTER - FUEL QUANTITY PROCESSOR UNIT - INSPECT**  **(SHEET 1 OF 2)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 20 of 26 **BOEING SERVICE BULLETIN 757-28-0136**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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Honeywell FQPU. Use Group 1, Configuration 1 instructions. 1 S345T002-( ) (HG1064AA( )) FUEL QUANTITY PROCESSOR UNIT INSPECT 1 (a) Simmonds/Goodrich FQPU. Use Group 1, Configuration 2 instructions. 1 S345N001-( ) (3007-( )) FUEL QUANTITY PROCESSOR UNIT INSPECT 2
(a) (a) Inspect for part number.

**FIGURE 1: MAIN EQUIPMENT CENTER - FUEL QUANTITY PROCESSOR UNIT - INSPECT (SHEET 2 OF 2)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 21 of 26 **BOEING SERVICE BULLETIN 757-28-0136**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)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 22 of 26 **BOEING SERVICE BULLETIN 757-28-0136 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)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 23 of 26 **BOEING SERVICE BULLETIN 757-28-0136 HONEYWELL FQIS BITE - NON-DISPATCHABLE FAULT CODES**  **FIM TASK Most Probable Fault**  **Fault Code**  28-41 Task 876 - Table 125 Left Center Tank Unit no.1 (Resistance Low) 21 28-41 Task 876 - Table 125 Left Center Tank Unit no.2 (Resistance Low) 22 28-41 Task 876 - Table 125 Left Center Tank Unit no.3 (Resistance Low) 23 28-41 Task 876 - Table 125 Left Center Tank Unit no.4 (Resistance Low) 24 28-41 Task 876 - Table 125 Left Center Tank Unit no.5 (Resistance Low) 25 28-41 Task 876 - Table 125 Right Center Tank Unit no.6 (Resistance Low) 26 28-41 Task 876 - Table 125 Right Center Tank Unit no.7 (Resistance Low) 27 28-41 Task 876 - Table 125 Right Center Tank Unit no.8 (Resistance Low) 28 28-41 Task 876 - Table 125 Right Center Tank Unit no.9 (Resistance Low) 29 28-41 Task 879 - Table 128 Left Center Tank Unit Wiring No.1 71 28-41 Task 879 - Table 128 Left Center Tank Unit Wiring No.2 72 28-41 Task 879 - Table 128 Left Center Tank Unit Wiring No.3 73 28-41 Task 879 - Table 128 Left Center Tank Unit Wiring No.4 74 28-41 Task 879 - Table 128 Left Center Tank Unit Wiring No.5 75 28-41 Task 880 - Table 129 Right Center Tank Unit Wiring No.6 76 28-41 Task 880 - Table 129 Right Center Tank Unit Wiring No.7 77 28-41 Task 880 - Table 129 Right Center Tank Unit Wiring No.8 78 28-41 Task 880 - Table 129 Right Center Tank Unit Wiring No.9 79 28-41 Task 853 - Table 105 Center Tank Compensator (Resistance Low) C2 28-41 Task 855 - Table 107 Center Tank Compensator Wiring C5

**APPENDIX B: HONEYWELL FUEL QUANTITY BITE - NON-DISPATCHABLE FAULT CODES (SHEET 1 OF 1)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 24 of 26 **BOEING SERVICE BULLETIN 757-28-0136**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)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 25 of 26 **BOEING SERVICE BULLETIN 757-28-0136 SIMMONDS/GOODRICH FQIS BITE - NON-DISPATCHABLE FAULT MESSAGES**  **SHEET (Refer to 757 FIM 28-41 FAULT** 

**TREE 847 Fig.108 as an ac cepted procedure)**  **Fault Message**

Sheet 2 CT TU ## OPEN LOZ OR HIZ WIRE Sheet 6 CT TU ## SHORTED TO GROUND Sheet 36 CT TU ?? SHORTED TO GROUND Sheet 7 CT COMP OPEN LOZ OR HIZ WIRE Sheet 10 CT COMP SHORTED TO GROUND Sheet 13 CT HIZ WIRE OPEN AT PROCESSOR Sheet 15 CT HIZ WIRE LOW RESISTANCE Sheet 17 CT HIZ SHIELD SHORT TO GND
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)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 05, 2014 757-28-0136 26 of 26 **BOEING SERVICE BULLETIN 757-28-0136**