CUSTOMER BULLETIN

SUBJECT

NUMBER 122 

FUEL (ATA 28) 

REPLACEMENT – FUEL BOOST PUMPS, 

P/N 1159SCP500-5 

APRIL 11, 2012 
Gulfstream G550 Customer Bulletin No. 122 

“April 11, 2012” 

Page 1 of 3 

Fuel (ATA 28), Replacement – Fuel Boost Pumps, P/N 1159SCP500-5 

I. Planning Information:

A. Effectivity: 

Aircraft serial numbers 5001 through 5340 

B. Reason: 

A Gulfstream V operator experienced failure of a fuel boost pump, Gulfstream part 

number 1159SCP500-5 (supplier part number 31760-1). Overheat damage was evident 

on the internal components as well as the external housing. Subsequent investigation 

identified inadequate clearance between the internal capacitor and a printed circuit 

board as the root cause of the failure. Additionally, on other components, a damaged oring between the "wet" and "dry" cavities of the boost pump resulted in fuel ingress into 

the "dry" area. Product improvements have been incorporated into the boost pumps to 

modify the capacitor installation to prevent external shorting and incorporate an 

inspection port to allow for inspection of the "dry" cavity. Incorporation of these 

modifications is required to preclude the potential for a wheel well fire. Triumph 

Aerostructures and GE Aviation Systems have issued Service Bulletins (SB) SBTAGV/GVSP-28-JG0162 and 31760-28-100, respectively, to incorporate these product 

enhancements by replacing all P/N 1159SCP500-5 fuel boost pumps with P/N 

1159SCP500-7 (supplier part number 31760-3) pumps. 

C. Description: 

This customer bulletin is a one-time action to replace all P/N 1159SCP500-5 fuel boost 

pumps with P/N 1159SCP500-7 pumps in order to incorporate modifications provided by 

the above listed service bulletins. 

Note: All SB references in this document are intended to be inclusive of any 

amendments or revisions unless otherwise stated. 

D. Compliance: 

Compliance with this customer bulletin is required within 42 months of the release date. 

This customer bulletin is a managed program and should be accomplished at a 

Gulfstream Aerospace authorized warranty repair facility. Due to a limited number of 

spares being available at any one time, this customer bulletin must be coordinated 

through the Program Office and Gulfstream Scheduling at 800-810-GULF (4853), or 

912-965-4178. Program Office will manage a limited component exchange pool. 

Operators having this customer bulletin performed at a Gulfstream G550 Authorized 

Warranty Repair Facility may elect to utilize the exchange inventory pool or have their 

original components repaired. If not scheduled, down times could increase significantly. 
Gulfstream G550 Customer Bulletin No. 122 

“April 11, 2012” 

Page 2 of 3 

E. Approval: 

This customer bulletin has been FAA approved as this issue is the subject of FAA 

Airworthiness action. It requires compliance with Triumph Aerostructures SBTAGV/GVSP-28-JG0162 and GE Aviation Systems SB 31760-28-100, which contain all 

other applicable regulatory agency approval information.

F. Manpower: 

Replace fuel boost pumps - 23.5 man-hours

G. Material: 

Refer to Triumph SB-TAGV/GVSP-28-JG0162. 

Note: Return all removed P/N 1159SCP500-5 boost pumps for modification to 

1159SCP500-7 configuration. Refer to GE Aviation Systems SB 31760-28-100. 

H. References: 

 G550 Aircraft Maintenance Manual (AMM), Chapters 20 and 28 

 Triumph SB-TAGV/GVSP-28-JG0162 (attached)

 GE Aviation Systems SB 31760-28-100 (attached) 

I. Tooling/Equipment: 

Refer to Triumph SB-TAGV/GVSP-28-JG0162. 

J. Opportunity for No Charge Compliance:

The labor and material to comply with this customer bulletin will be provided at no 

charge if performed at a Gulfstream G550 Authorized Warranty Repair Facility within the 

recommended compliance time stated in this document. 

Note: Additional labor hours incurred due to aircraft configuration or mechanical 

difficulties must be charged on a separate work order and submitted for warranty 

consideration. 

K. Weight and Balance: 

N/A 
Gulfstream G550 Customer Bulletin No. 122 

“April 11, 2012” 

Page 3 of 3 

II. Accomplishment Instructions:

CAUTION: PROTECT WIRE BUNDLES, CONNECTORS AND SURROUNDING 

STRUCTURE DURING ANY MAINTENANCE PROCEDURE FROM SHAVINGS, 

DEBRIS AND CONTAMINATION. MAINTAIN A PROPERLY CLEANED WORK 

AREA THROUGHOUT THE PROCEDURE TO ENSURE THE INTEGRITY OF 

THE AFFECTED COMPONENT / SYSTEM. VISUALLY INSPECT WORK AREA 

USING ADDITIONAL LIGHT AS NECESSARY TO VERIFY ABSENCE OF ANY 

DEBRIS PRIOR TO COMPLETION OF PROCEDURE. FAILURE TO COMPLY 

MAY RESULT IN DAMAGE TO COMPONENTS AND / OR SYSTEMS.

A. Prepare the aircraft for safe maintenance. Refer to AMM, Safe Ground Maintenance 

Procedure, Chapter 20.

WARNING: BEFORE WORKING IN ANY WHEEL WELL, ENSURE ALL LANDING 

GEAR AND LANDING GEAR DOOR SAFETY DEVICES ARE 

INSTALLED.

B. Gain access to the left and right main landing gear wheel wells. 

C. RC- Inspect fuel boost pumps for part number. Any P/N 1159SCP500-7 fuel boost 

pumps that are installed will remain in service and require no further action. 

D. RC – Replace any fuel boost pumps with a part number P/N 1159SCP500- 5 or prior 

and install fuel boost pumps with a part number P/N 1159SCP500- 7 or later. This action 

is required to address the condition described in Step I.C. Description, which is the 

subject of FAA Airworthiness action. 

Note: Refer to Triumph SB-TAGV/GVSP-28-JG0162 and GE Aviation Systems SB 

31760-28-100 for accomplishment instructions. 

E. Ensure work area is clean and clear of foreign objects (FOD). 

F. Record compliance with this customer bulletin in the aircraft’s permanent maintenance 

records and return aircraft to flight status. 

G. Report compliance with this customer bulletin to Gulfstream Computerized Maintenance 

Program (CMP) via electronic transmittal or fill out and fax the attached service reply 

card. 

Note: Some steps in the accomplishment instructions are identified as Required for 

Compliance (RC). If this CB is mandated by an airworthiness directive (AD), the 

steps identified as RC must be done to comply with the AD. Steps not identified 

with RC are recommended and may be deviated from, done as part of other 

actions, or done with accepted methods different from those given in the CB, if 

the RC steps can be done and the aircraft can be put back in service in a 

serviceable condition. 

If technical assistance is required, contact your area Gulfstream Field Service Representative or call 

Gulfstream Customer Support at 800-810-GULF (4853) or 912-965-4178 (fax 912-965-4184). 
Gulfstream G550 Customer Bulletin No. 122 

“April 11, 2012” 

Customer Bulletin prepared by Gulfstream Aerospace, 500 Gulfstream Road, P.O. Box 2206, Savannah, Georgia 31402-2206, USA. 

© 2012 Gulfstream Aerospace 

All rights reserved, including the right to reproduce this publication. No part may be reproduced, stored in any retrieval system, or transmitted in any part or form or 

by any means, electronic, photocopying, microfilm, microfiche, mechanical, or otherwise, without prior written permission of Gulfstream Aerospace. 

This technical data is controlled under the Export Administration Regulations by General License TSU. It may not be transferred to a third party 

without the prior written approval of the U.S. Department of Commerce.

GA 611A 2/97 

Service Reply Card 

Please fax this page to Gulfstream CMP at 800-944-1775 or 912-963-0265. 

The following Customer Bulletin (CB) has been addressed: 

CB Number A/C A/C Type Compliance Date 

981220 G550 

Aircraft Hours 

Aircraft Landings 

This Customer Bulletin is not applicable because: 

Serial Number not affected 

Appliance not installed 

______Previously complied with (annotate method of compliance below) 

 

Signature Title/Certificate Number Company 

Comments / Suggestions: 
GULFSTREAM GV & GV-SP SERVICE BULLETIN

SB-TAGV/GVSP-28-JG0162 

Page 1 of 12 

Revision: NEW August 30, 2011 

FUEL BOOST PUMP REPLACEMENT

SB-TAGV/GVSP-28-JG0162

1. PLANNING: 

A. Effectivity: 

This Service Bulletin is applicable to all Gulfstream Aerospace Corporation (GAC) GV aircraft and 

only G500/G550 aircraft 5001 thru 5340 (Triumph Aerostructures - Vought Integrated Products 

Division wings 501 thru 1035) (GE Aviation Systems fuel boost pump S/N Range 0001 thru 2223). 

B. Reason: 

This service bulletin is being issued to facilitate the exchange of new or refurbished 1159SCP500-7 

(GE Aviation Systems P/N 31760-3) fuel boost pumps. The 1159SCP500-7 pumps incorporate a new 

leak detection port. 

C. Description: 

This Service Bulletin provides replacement instructions for the Fuel Boost Pump (1159SCP500-5). 

D. Compliance: 

This Service Bulletin has a 48-month compliance requirement and will be managed by Gulfstream's 

Program Office Retrofit Management Team.

After completion of this service bulletin, the 1159SCP500-7 Fuel Boost Pumps will be inspected every 

scheduled “A” check as given in GV/G500/G550 AMM procedure Fuel Boost Pump - Fuel Leak 

Check, 28-26-01, Inspection / Check. 

E. Approval: 

This Service Bulletin and Related Engineering Drawings contained in Paragraph 1.L are FAA 

approved. 

F. Manpower: 

Refer to corresponding Gulfstream Customer Bulletin. Modification of fuel boost pump from 

1159SCP500-5 to the 1159SCP500-7 configuration will be performed by GE Aviation Systems and 

modification instructions are not provided as part of this service bulletin. 

G. Material - Cost and Availability: 

Triumph Aerostructures shall supply all sealing hardware (O-rings) at no cost to Gulfstream for the 

fuel boost pump replacement. This will not include installation tools or sealant. Refer to Paragraph 3, 

Table 3 - Parts Required. Hardware will be provided to GAC in bulk quantities. No hardware will be 

provided with the packaged pump. 

H. Tooling Requirements: 

Refer to Table 6, Standard Tools for a list of basic tools required. 

I. Warranty: 

This Service Bulletin will be accomplished at no charge to operator. 

J. Weight and Balance: 

Not affected. 
GULFSTREAM GV & GV-SP SERVICE BULLETIN

SB-TAGV/GVSP-28-JG0162 

Page 2 of 12 

Revision: NEW August 30, 2011

K. References: 

GE Aviation Systems Service Bulletin 31760-28-100 

GE Aviation Systems Component Maintenance Manual (CMM) 28-26-01 

GV/G500/G550 Aircraft Maintenance Manual (AMM) 

GV/G500/G550 Illustrated Parts Catalog (IPC) 

L. Related Engineering Drawings: 

1159P52019 - Fuel System Instl Wing, Hopper 

1159SCP500 - Fuel System Boost Pump and EMI Filter 

M. Other Publications Affected: 

None 
GULFSTREAM GV & GV-SP SERVICE BULLETIN

SB-TAGV/GVSP-28-JG0162 

Page 3 of 12 

Revision: NEW August 30, 2011 

2. ACCOMPLISHMENT INSTRUCTIONS: 

The following instructions provide a condensed procedure for the removal and installation of all four GV 

and GV-SP Fuel Boost Pumps. The instructions are provided to expedite the removal and replacement of 

the fuel pumps. Unless specifically referenced, these instructions are to be performed independent of the 

GAC CMP and AMM procedure and in some instance may provide conflicting instructions. The procedure 

outline herein should take precedent over GAC CMP and AMM instruction where applicable.

A. General: 

Fuel boost pumps are located on the rear spar in the main wheel wells as follows: 

• Left (L) Main Wheel Well 

- L main boost pump (074A1): Inboard 

- L alt boost pump (074A3): Outboard 

• Right (R) Main Wheel Well 

- R main boost pump (074A2): Inboard 

- R alt boost pump (074A4): Outboard 

It is recommended that all four (4) fuel boost pumps be replaced as a set. If one or more 

1159SCP500-7 fuel boost pumps are installed, it is not necessary to replace the installed 

1159SCP500-7 pumps. 

B. Prepare Aircraft for Maintenance: 

SPECIAL TOOLS AND TEST EQUIPMENT

Circuit breaker safety clips ........................................................................................ GSE2400984 or equivalent 

Torque wrench, 40 - 200 inch-pounds (0 - 16.95 Nm) ................................................. GSE5100721 or equivalent 

Container, 1 - 1.5 quarts (0.946 - 1.41 liters), approved for fuel ..................................................... Standard 

CONSUMABLES

Safety wire, 0.032” .......................................................................................................................... MS20995C32 

Safety wire, 0.040” .......................................................................................................................... MS20995C40 

Lubricant, O-ring (Braycoat-236) ....................................................................... VV-P-236A or equivalent 

Zip ties ...............................................................................................................................Standard 

(1) GV/G500/G550 AMM References 

• Safe Ground Maintenance Procedure, 20-00-00, Maintenance Practices

• External Electrical Power Application, 20-20-10, Maintenance Practices

• Fuel Boost Pump Control System - Operational Check, 28-26-01, Adjustment / Test or Code 

282011

• Fuel Boost Pump Electromagnetic Interference Filter - Functional Check, 28-26-03, 

Inspection / Check

(2) Aircraft Preparation 

(a) Prepare aircraft for safe ground maintenance. Refer to AMM procedure Safe Ground 

Maintenance Procedure, 20-00-00, Maintenance Practices. 

(b) Pull, tag and install safety clips on the following Circuit Breakers (CB): 

TYPE CB NAME CB PANEL CB LOCATION 

GV CLASSIC FIRE EXT SHOT #1 LEER B12

GV CLASSIC FIRE EXT SHOT #2 REER B12
GULFSTREAM GV & GV-SP SERVICE BULLETIN

SB-TAGV/GVSP-28-JG0162 

Page 4 of 12 

Revision: NEW August 30, 2011

TYPE CB NAME CB PANEL CB LOCATION 

G500/G550 FIRE EXT SHOT #1 LEER ENGINE SYS / CTLS

G500/G550 FIRE EXT SHOT #2 REER ENGINE SYS / CTLS

(c) Apply external electrical power to aircraft. Refer to AMM procedure External Electrical 

Power Application, 20-20-10, Maintenance Practices.

(d) On pedestal, pull and tag appropriate L / R DISCH fire handle for pump being removed. 

NOTE: This closes engine fuel shut-off valve. 

WARNING: BEFORE WORKING IN ANY WHEEL WELL, ENSURE ALL LANDING GEAR 

AND LANDING GEAR DOOR SAFETY DEVICES ARE INSTALLED.

(e) Open left and right main landing gear door. 

(f) Remove external electrical power from aircraft. Refer to AMM procedure External 

Electrical Power Application, 20-20-10, Maintenance Practices. 

(g) Pull, tag and install safety clip on the following applicable Circuit Breakers (CB): 

TYPE CB NAME CB PANEL CB LOCATION 

GV CLASSIC L FUEL S/O LEER B3 

GV CLASSIC R FUEL S/O REER B14 

TYPE CB NAME CB PANEL CB LOCATION 

G500/G550 L FUEL S/O LEER FUEL

G500/G550 R FUEL S/O REER FUEL

C. Remove fuel boost pump (GAC Part Number 1159SCP500-5) as follows: 

NOTE: Make sure boost pumps to be removed are the 1159SCP500-5 configuration. The 

1159SCP500-7 configuration boost pumps do not need to be replaced. Removal of all 

four boost pumps must be performed in the following order: 

(1) L/H Main Fuel Boost Pump (Inboard) 

(2) L/H Alternate Fuel Boost Pump (Outboard) 

(3) R/H Alternate Fuel Boost Pump (Outboard) 

(4) R/H Main Fuel Boost Pump (Inboard) 

(1) Remove boost pump as follows: 

(a) Disconnect boost pump electrical connector plug (Left Main: 074FL1P2, Left Alt: 

074FL1P3; Right Main: 074FL2P2, Right Alt: 074FL2P3) from Electromagnetic 

Interference (EMI) filter. 
GULFSTREAM GV & GV-SP SERVICE BULLETIN

SB-TAGV/GVSP-28-JG0162 

Page 5 of 12 

Revision: NEW August 30, 2011 

(b) Disconnect electrical connector plug (Left Main: 074S1P1, Left Alt: 074S3P1; Right Main: 

074S2P1, Right Alt: 074S4P1) from pump pressure switch (8G1566 or 8G1594). 

(c) Remove 4 bolts (NAS6404A13) and 4 washers (NAS1149C0416R) attaching boost pump 

to rear spar. Retain bolts and washers for installation of 1159SCP500-7 boost pump. 

WARNING: TO PREVENT FIRE HAZARD FROM FUEL SPILL, DO NOT DISCONNECT 

VAPOR RETURN LINE UNTIL PUMP IS PARTIALLY REMOVED FROM 

REAR SPAR.

(d) Slowly pull boost pump straight out until first set of O-rings (MS29513-121, MS29513-

125) on suction and discharge ports can be seen. Refer to Figure 1 Sheet 3. 

WARNING: TO PREVENT FIRE HAZARD, ENSURE AN APPROVED CONTAINER IS 

AVAILABLE TO CATCH REMAINING FUEL FROM VAPOR RETURN LINE 

BEFORE DISCONNECTING LINE. 

(e) Disconnect vapor return line (Inboard pump: 132122D0104-180; Outboard pump: 

132122D0123-180) from fuel boost pump to allow pump suction check valve to close. 

(f) Place fuel rags under boost pump. Catch remaining fuel from vapor return line in 

container. 

(g) Remove fuel boost pump from manifold on rear spar. 

NOTE: Boost pump contains approximately 1⁄2 - 1 cup of fuel. 

(h) Pour fuel from boost pump into container, then rotate pump to allow remaining fuel to 

drain from pump ports. 

(i) Place boost pump on work bench. 

(j) Tag removed boost pump (1159SCP500-5). 

(2) Repeat Steps C.(1)(a) thru C.(1)(i) to remove the L/H wing outboard boost pump. 

(3) Repeat Steps C.(1) thru C.(2) to remove the R/H wing outboard and then the inboard boost 

pumps. 

D. EMI Filter test: 

CAUTION: TO PREVENT DAMAGE TO PUMP, EMI FILTER TEST MUST BE PERFORMED. 

(1) Perform boost pump EMI filter test. Refer to AMM procedure Fuel Boost Pump Electromagnetic 

Interference Filter - Functional Check, 28-26-03, Inspection / Check. 

NOTE: Do not perform the capacitance check. The capacitance check is to be performed only 

if multiple boost pumps in the same position have failed or if EMI filter is suspect. 

E. Prepare removed fuel boost pump (GAC Part Number 1159SCP500-5) for shipment.

(1) Remove pressure switch (8G1566 or 8G1594) from boost pump. Discard O-ring (MS29512-04). 

(2) Remove union (AN815-D6) from vapor return line port from boost pump. Discard O-ring 

(MS29512-06). 

(3) Retain pressure switch and union for installation on new boost pump (1159SCP500-7). 

(4) Return removed fuel boost pumps (1159SCP500-5) to Gulfstream Aerospace Corporation for 

shipment to GE Aviation Systems for modification to the 1159SCP500-7 configuration. Refer to 

GE Aviation Systems Service Bulletin 31760-28-100 and CMM 28-26-01 for packaging and 

shipping instructions. 
GULFSTREAM GV & GV-SP SERVICE BULLETIN

SB-TAGV/GVSP-28-JG0162 

Page 6 of 12 

Revision: NEW August 30, 2011

F. Prepare new replacement fuel boost pump (GAC Part Number 1159SCP500-7) for installation.

(1) Install union (AN815-D6) using new O-ring (MS29512-06) in vapor return line port of the 

1159SCP500-7 boost pump. Torque union to 120 - 150 inch-pounds (13.56 - 16.95 Nm). 

(2) Install pressure switch (8G1566 or 8G1594) using new O-ring (MS29512-04) in pressure port. 

Torque switch to 90 inch-pounds (10.17 Nm). Safety wire pressure switch to boost pump. 

NOTE: Make sure to lubricate o-rings prior to installation. 

(3) Install new O-rings (MS29513-121, MS29513-125) on pump suction and discharge ports as 

given in Figure 1, Sheet 2. 

G. Install new replacement fuel boost pump (GAC Part Number 1159SCP500-7) as follows: 

(1) Inspect for presence of foreign objects. 

NOTE: Installation of all four boost pumps must be performed in the following order: 

(1) L/H Alternate Fuel Boost Pump (Outboard) 

(2) L/H Main Fuel Boost Pump (Inboard) 

(3) R/H Main Fuel Boost Pump (Inboard) 

(4) R/H Alternate Fuel Boost Pump (Outboard) 

(2) Install boost pump as follows: 

NOTE: The fuel boost pump is self-priming. It is not required to add fuel to pump before 

installation. 

(a) Position fuel boost pump into fuel pump manifold on rear spar up to first set of o-rings. 

Do not fully insert fuel pump into fuel manifold at this time. Refer to Figure 1 Sheet 3. 

(b) Connect vapor return line (Inboard pump: 132122D0104-180; Outboard pump: 

132122D0123-180) to union (AN815-D6). Torque line to 120 - 150 inch-pounds (13.56 - 

16.95 Nm). 

(c) Push fuel boost pump (1159SCP500-7) fully into rear spar (manifold). 

(d) Install 4 bolts (NAS6404A13) and 4 washers (NAS1149C0416R). Torque bolts to 50 - 70 

inch-pounds (5.65 - 7.91 Nm). 

NOTE: Bolts and washers are to be reused from the 1159SCP500-5 boost pump removal. 

(3) Repeat Steps E.(2)(a) thru E.(2)(g) to install the L/H wing inboard boost pump. 

(4) Repeat Steps E.(2) thru E.(3) to install the R/H wing inboard and then outboard boost pumps. 

(5) Verify position, then connect and safety wire boost pump electrical connector (Left Main: 

074FL1P2, Left Alt: 074FL1P3; Right Main: 074FL2P2, Right Alt: 074FL2P3) to EMI filter. 

(6) Connect and safety wire electrical connector (Left Main: 074S1P1, Left Alt: 074S3P1; Right 

Main: 074S2P1, Right Alt: 074S4P1) to pressure switch (8G1566 or 8G1594). 

H. Follow-On Actions / Return to Service: 

(1) Inspect for presence of foreign objects around work area. 

(2) Remove safety clip, tag and depress circuit breakers pulled in Step 2.B.(2)(f). 

(3) Apply external electrical power to aircraft. Refer to AMM procedure External Electrical Power 

Application, 20-20-10, Maintenance Practices. 
GULFSTREAM GV & GV-SP SERVICE BULLETIN

SB-TAGV/GVSP-28-JG0162 

Page 7 of 12 

Revision: NEW August 30, 2011 

(4) On FUEL SYSTEMS Cockpit Overhead Panel, ensure X FLOW switch is depressed. 

(5) Remove safety clips, tags and depress circuit breakers pulled in Step 2.B.(2)(b). 

(6) Remove tag from L / R DISCH fire handle, then push in handle. 

(7) Visually verify both fuel shut-off valves are in full OPEN position. See Figure 2. 

NOTE: The valves are located on the rear wing spar above each pair of fuel boost pumps. 

(8) Perform Fuel Boost Pump Control System - Operational Check, 28-26-01, Adjustment / Test or 

Code 282011. 

(9) Close left and right main landing gear door. 

(10) Record all maintenance actions in accordance with current governing authority. 

(a) Update the following CMP cards with new fuel boost pump part number and serial 

number information: 

• CMP Code 282001 

• CMP Code 282002 

• CMP Code 282003 

• CMP Code 282004 

3. MATERIAL INFORMATION: 

A. Parts Required (Per Aircraft): 

Part Number Nomenclature Qty 

1159SCP500-7 Fuel Boost Pump 4 

MS29512-06 O-ring 4 

MS29513-121 O-ring 8 

MS29513-125 O-ring 8 

MS29512-04 O-ring 4 

Table 3 - PARTS REQUIRED 

B. Consumables Required: 

Material Code Material Specification Nomenclature 

- - - MS20995C32 Safety wire, 0.032” 

- - - MS20995C40 Safety wire, 0.040” 

Braycoat-236 VV-P-236A O-ring lubricant 

- - - - - - Zip ties 

Table 4 - CONSUMABLES REQUIRED 
GULFSTREAM GV & GV-SP SERVICE BULLETIN

SB-TAGV/GVSP-28-JG0162 

Page 8 of 12 

Revision: NEW August 30, 2011

C. Parts Removed: 

Part Number Nomenclature Disposition 

1159SCP500-5 Fuel Boost Pump Tag, Return to GAC 

MS29512-06 O-ring Discard 

MS29513-121 O-ring Discard 

MS29513-125 O-ring Discard 

MS29512-04 O-ring Discard 

Table 5 - PARTS REMOVED 

D. Standard Tools: 

● Diagonal cutter ● 1⁄4”-Drive 7/16” socket ● 1⁄4”-Drive 6” extension 

● Duckbill pliers ● 1⁄4”-Drive 7/16” socket - swivel ● 1⁄4”-Drive 12” extension 

● Safety wire pliers ● 3⁄8”-Drive open crows foot 7/16” socket ● 3⁄8”-Drive 2” extension 

● Cannon plug pliers ● 3⁄8”-Drive open crows foot 11/16” socket ● 7/16” Open-end wrench 

● 1⁄4”-Drive ratchet ● 3⁄8”-Drive open crows foot 13/16” socket ● 11/16” Open-end wrench 

● 3⁄8”-Drive ratchet ● 3⁄8”-Drive to 1⁄4”-drive adapter ● 13/16” Open-end wrench 

Table 6 - STANDARD TOOLS 
GULFSTREAM GV & GV-SP SERVICE BULLETIN

SB-TAGV/GVSP-28-JG0162 

Page 9 of 12 

Revision: NEW August 30, 2011 

Fuel Boost Pump 

Figure 1 (Sheet 1 of 3) 
GULFSTREAM GV & GV-SP SERVICE BULLETIN

SB-TAGV/GVSP-28-JG0162 

Page 10 of 12 

Revision: NEW August 30, 2011

Fuel Boost Pump 

Figure 1 (Sheet 2 of 3) 
GULFSTREAM GV & GV-SP SERVICE BULLETIN

SB-TAGV/GVSP-28-JG0162 

Page 11 of 12 

Revision: NEW August 30, 2011 

Fuel Boost Pump 

Figure 1 (Sheet 3 of 3) 
GULFSTREAM GV & GV-SP SERVICE BULLETIN

SB-TAGV/GVSP-28-JG0162 

Page 12 of 12 

Revision: NEW August 30, 2011

Fuel Shut-off Valve 

Figure 2 
GE AVIATION SYSTEMS LLC PROPRIETARY INFORMATION 

The information contained in this document is GE Aviation Systems LLC proprietary information and is disclosed in confidence. It is the property of GE 

Aviation Systems LLC and shall not be used, disclosed to others or reproduced without the express written consent of GE Aviation Systems LLC, 

including, but without limitation, it is not to be used in the creation, manufacture, development, or derivation of any repairs, modifications, spare parts, 

designs, or configuration changes or to obtain FAA or any other government or regulatory approval to do so. If consent is given for reproduction in 

whole or in part, this notice and the notice set forth on each page of this document shall appear in any such reproduction in whole or in part. 

Copyright (2011) 

DCN (EAR) 

These commodities, software, or technology were exported from the United States in accordance with the Export Administration Regulations. 

Transfer of this data by any means to a non-U.S. person, whether in the United States or abroad, without an export license or other approval from the 

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SERVICE BULLETIN, 

Fuel Boost Pump, 

GE Part No. 31760-1 

Gulfstream GV, G500/G550 

GE Document Number 31760-28-100 

Issue Date: 04 March 2011

Revision: -

Revision Date:

Prepared by: Date: 

Mike Bailey, Engr. Support Specialist 

Checked by: Date: 

Sherrie Lundgren, Configuration Management 

& Tech Pubs Leader 

Approved by: Date: 

Pete Walker, Sustaining Engineering Leader 

 

CAGE Code: 4N727 
31760-28-100

PAGE 2 

REVISION - 

Use or disclosure of data contained on this sheet is subject to the restrictions on the cover or first page.

RECORD OF REVISIONS

Revision 

No. Description Initial Date 

 

- Initial Release Prepared 

 Checked 

 Approved 

 
GEK 118,728

CAGE CODE: 4N727 

For Europe, Africa, India and 

Middle East contact:

GE Aviation Systems Ltd 

Customer & Product Support 

Bishops Cleeve, Cheltenham, 

Glos. GL52 8SF, 

United Kingdom 

T: + 44 (0)1242 673355 

F: + 44 (0)1242 669180

For Asia, Australasia and the Pacific 

contact:

GE Aviation Systems Australia Pty Ltd 

Customer & Product Support 

3 Hakea Street, 

Brisbane Airport, QLD4007, 

Australia 

T: + 61 7 3860 0700 

F: + 61 7 3860 0701

For the Americas 

contact:

GE Aviation Systems LLC 

Customer & Product Support 

14200 Roosevelt Blvd 

Clearwater, 

Florida 33762 

United States of America 

T: + 1 (727) 539 1631

Global Contact: systems.support@ge.com

Manual Ref: 28-26-01 

SERVICE BULLETIN 

Copyright (2011), GE Aviation Systems LLC, U.S.A. 

The information contained in this document is GE Aviation Systems LLC proprietary information and is disclosed in confidence. It is the property of 

GE Aviation Systems LLC and shall not be used, disclosed to others or reproduced without the express written consent of GE Aviation Systems 

LLC, including, but without limitation, it is not to be used in the creation, manufacture, development, or derivation of any repairs, modifications, 

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reproduction in whole or in part, this notice and the notice set forth on each page of this document shall appear in any such reproduction in whole or 

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prohibited. 

Destination Control Statement 

These commodities, technology or software were exported from the United States in accordance with the Export Administration Regulations. 

Diversion contrary to US Law is prohibited.” ECCN: 9E991, License Exception: NLR. 

Feb 15/11 31760-28-100

Revision – Feb 15/11 PAGE 1 OF 4 

FUEL BOOST PUMP, P/N 31760-1

Modification to P/N 31760-3

I. PLANNING INFORMATION

WARNING: FAILURE TO CORRECTLY IMPLEMENT ANY INSTRUCTION GIVEN HERE, AS AMENDED 

FROM TIME TO TIME BY GE AVIATION, MAY ENDANGER HEALTH OR SAFETY. 

A. Effectivity:

Aircraft: Gulfstream GV, G500/G550 (Aircraft 5001 through 5346) 

Unit: Fuel Boost Pump 

Part Number: GE Aviation Part Number 31760-1 

Serial Number: S/N 0001 through S/N 2231. 

B. Concurrent Requirements

(1) Not applicable. 

C. Reason:

(1) This Service Bulletin is being issued to facilitate the exchange of all in-service GE Aviation part number 

31760-1 Fuel Boost Pumps (Gulfstream part number 1159SCP500-5) for modified GE Aviation part 
. SERVICE BULLETIN. 

Part Number 31760-1 

Feb 15/11 31760-28-100

Revision – Feb 15/11 PAGE 2 OF 4 

GE Proprietary Information – subject to the restrictions on the cover or first page 

number 31760-3 configuration pumps (Gulfstream part number 1159SCP500-7). The new GE Aviation 

part number 31760-3 pumps incorporate product improvement changes to ensure the continuous and 

safe operation of the fuel boost pumps. 

(2) A new end cover that adds an inspection port has been incorporated as part of the new Fuel Boost 

Pump part number 31760-3 design. The inspection port allows for scheduled inspection of the pump’s 

dry electronic cavity for the presence of fuel. 

(3) Previously incorporated changes to the part number 31760-1 pumps, the addition of a nomex barrier 

(MOD B) and the requirement for clearance gap check between the barrier and capacitors (MOD A and 

MOD C), have also been carried forward into the design of the part number 31760-3 pump. 

D. Description:

(1) This Service Bulletin, in combination with GE’s CMM 28-26-01, modifies fuel boost pumps 31760-1, 

MOD NONE through MOD C, by incorporating the changes shown in C(2) and C(3) above. A modified 

31760-1 pump will be re-identified as a 31760-3 pump once all modifications have been incorporated. 

E. Compliance:

(1) Incorporation of this Service Bulletin is recommended to be accomplished to prevent significant 

operational disruption. 

(2) P/N 31760-1 Fuel Boost Pumps should be returned through the Gulfstream Aerospace Program 

Management Warehouse/Product Support Receiving to GE. GE Aviation is the only party authorized to 

perform this Service Bulletin. 

(3) GE Aviation recommends incorporation of this Service Bulletin at the next convenient maintenance 

opportunity. This Service Bulletin is part of a Gulfstream retrofit managed program. 

F. Approval:

(1) The FAA has approved the technical contents of this Service Bulletin. 

G. Weight and Balance:

(1) No Change. 

H. Electrical Load Data:

(1) Not affected. 

I. Software Accomplishment Summary

(1) Not applicable. 

J. References

(1) GE Aviation Component Maintenance Manual, 28-26-01. 
. SERVICE BULLETIN. 

Part Number 31760-1 

Feb 15/11 31760-28-100

Revision – Feb 15/11 PAGE 3 OF 4 

GE Proprietary Information – subject to the restrictions on the cover or first page 

K. Publications Affected

(1) GE Aviation Component Maintenance Manual, 28-26-01. 

L. Materials-Cost and Availability

(1) Not applicable for this Service Bulletin. 

M. Tooling

(1) No special tools are required. 

II. MATERIAL INFORMATION 

A. Material – Price and Availability

(1) There are no additional materials required to accomplish the instructions contained in this Service 

Bulletin. 

(2) Fuel Boost Pumps submitted to Gulfstream Aerospace Corporation for modification will have a 

turnaround time of 5 business days, depending upon parts availability. 

(3) Operators must contact Gulfstream Aerospace Corporation no later than 30 days prior to returning a 

unit, for parts planning and availability that will ensure retrofit turnaround times as stated in paragraph 

A.(2) above. 

(4) Return Fuel Boost Pumps to Gulfstream Aerospace Corporation. Price available upon request. 

(5) Operators must return Fuel Boost Pumps to Gulfstream Aerospace Corporation. 

(6) Upon completion of the upgrade, the 31760-3 pump will be returned with installation hardware kit per Gulfstream 

part number GAC P/N 1159SB50143-1. 

B. Industry Support Information

(1) Not applicable. 

C. Material Necessary for Each Component

(1) Not applicable. 

D. Tooling Price and Availability

NEW PART 

NUMBER KEYWORD OLD PART 

NUMBER QTY SPECIAL INSTRUCTIONS/ 

DISPOSITION 

GE P/N 

31760-3 FUEL BOOST PUMP 31760-1 1 

Return P/N 31760-1 units to 

GAC for modification to P/N 

31760-3 configuration. 

GAC P/N 

1159SB50143-1 Installation Hardware Kit N/A 1 

See Triumph Aerostructures 

Service Bulletin SBTAGV/GVSP-28-JG0XXX 
. SERVICE BULLETIN. 

Part Number 31760-1 

Feb 15/11 31760-28-100

Revision – Feb 15/11 PAGE 4 OF 4 

GE Proprietary Information – subject to the restrictions on the cover or first page 

(1) Not applicable. 

III. ACCOMPLISHMENT INSTRUCTIONS 

A. General

(1) Return P/N 31760-1 Fuel Boost Pumps to Gulfstream Aerospace Corporation for modification to the 

31760-3 configuration.