# 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 circuitboard 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 prev ent 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. TriumphAerostructures 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 NECESSA RY 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 pub lication. No part may be reproduced, stored in any retrieval syst em, or transmitted in any part or form or by any means, electronic, photocopying, micr ofilm, microfiche, mechanical, or otherwise, without prior written permission of Gu lfstream Aerospace.

This technical data is controlled under the Ex port Administration Regulations by General License TSU. It may not be transferre d 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 Gulfstre am Aerospace Corporation (GAC) GV aircraft and only G500/G550 aircraft 5001 thru 5340 (Triumph Aer ostructures - 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 instruct ions for the Fuel Boost Pump (1159SCP500-5).

D. Compliance: This Service Bulletin has a 48-month compliance req uirement and will be managed by Gulfstream's Program Office Retrofit Management Team. After completion of this service bulletin, the 1159 SCP500-7 Fuel Boost Pumps will be inspected every scheduled “A” check as given in GV/G500/G550 AMM pr ocedure Fuel Boost Pump - Fuel Leak Check, 28-26-01, Inspection / Check.

E. Approval: This Service Bulletin and Related Engineering Drawi ngs 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 har dware (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 basi c tools required.

I. Warranty: This Service Bulletin will be accomplished at no ch arge 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 (C MM) 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 proc edure for the removal and installation of all four GV and GV-SP Fuel Boost Pumps. The instructions are p rovided to expedite the removal and replacement of the fuel pumps. Unless specifically referenced, th ese 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 a nd AMM instruction where applicable.

A. General: Fuel boost pumps are located on the rear spar in th e 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 pump s 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) ................................................. G SE5100721 or equivalent Container, 1 - 1.5 quarts (0.946 - 1.41 liters), ap proved 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, Maint enance Practices

• External Electrical Power Application, 20-20-10, M aintenance Practices

• Fuel Boost Pump Control System - Operational Check , 28-26-01, Adjustment / Test or Code 282011

• Fuel Boost Pump Electromagnetic Interference Filte r - 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 Practi ces. (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 f ire handle for pump being removed.
NOTE: This closes engine fuel shut-off valve.
WARNING: BEFORE WORKING IN ANY WHEEL WELL, ENSURE ALL LANDIN G 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. Ref er 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 1159SC P500-5 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 (Le ft 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: 07 4S1P1, Left Alt: 074S3P1; Right Main: 074S2P1, Right Alt: 074S4P1) from pump pressure swi tch (8G1566 or 8G1594). (c) Remove 4 bolts (NAS6404A13) and 4 washers (NAS1149C 0416R) attaching boost pump to rear spar. Retain bolts and washers for install ation of 1159SCP500-7 boost pump. WARNING: TO PREVENT FIRE HAZARD FROM FUEL SPILL, DO NOT DISCONNECT

VAPOR RETURN LINE UNTIL PUMP IS PARTIALLY REMOVED F ROM 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. Re fer 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: 132122D 0104-180; 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 fue l. (h) Pour fuel from boost pump into container, then rota te 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 inboa rd 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 pr ocedure Fuel Boost Pump Electromagnetic Interference Filter - Functional Check, 28-26-03, I nspection / Check.
NOTE: Do not perform the capacitance check. The capacita nce check is to be performed only

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

E. Prepare removed fuel boost pump (GAC Part Number 11 59SCP500-5) for shipment. (1) Remove pressure switch (8G1566 or 8G1594) from boos t 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 o n new boost pump (1159SCP500-7). (4) Return removed fuel boost pumps (1159SCP500-5) to G ulfstream 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 a nd 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 N umber 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 ne w 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 installati on. (3) Install new O-rings (MS29513-121, MS29513-125) on p ump suction and discharge ports as given in Figure 1, Sheet 2.

G. Install new replacement fuel boost pump (GAC Part N umber 1159SCP500-7) as follows: (1) Inspect for presence of foreign objects.
NOTE: Installation of all four boost pumps must be perfo rmed 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 requ ired 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: 132122D010 4-180; 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 (NAS1149 C0416R). Torque bolts to 50 - 70 inch-pounds (5.65 - 7.91 Nm).
NOTE: Bolts and washers are to be reused from the 1159SC P500-5 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 swit ch (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 breaker s 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 FL OW switch is depressed. (5) Remove safety clips, tags and depress circuit break ers 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 fu ll 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 - Operationa l 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 c urrent 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”-Driv e 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 7/1 6” 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 2GE 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 Aviatio n 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 give n 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 w hole or in part.
Copyright (2011)

DCN (EAR) These commodities, software, or technology were exported from the United States in accordance with the Export Administration Re gulations. Transfer of this data by any means to a non-U.S. person, whethe r in the United States or abroad, without an export license or o ther approval from the U.S. Government, is strictly prohibited. ECCN# 9E 991 Export Authorization: NLR 

# SERVICE BULLETIN,

Fuel Boost Pump, GE Part No. 31760-1

Gulfstream GV, G500/G550

GE Document Numb er 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: 4N72731760-28-100 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 info rmation and is disclosed in confidence. I t 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 Avia tion Systems LLC
, including, but without limitation, it is not to be used in t he creation, manufacture, development, or derivation of any repairs , modifications, spare parts, design, or configuration c hanges or to obtain FAA or any other governm ent or regulatory approval to do so. If cons ent 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 r eproduction in whole or in part. The information contained in this document may also be c ontrolled by U.S. export control laws. Unauthorized export or re-export is prohibited. Destination Control Statement These commodities, technology or software were exported from the United States in accordance with the Export Administration Reg ulations. Diversion contrary to US Law is prohibit ed.” 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 AN Y INSTRUCTION GIVEN HERE, AS AMENDED FROM TIME TO TIME BY GE AVIATION, MAY ENDANGER H EALTH OR SAFETY. A. Effectivity:

Aircraft: Gulfstream GV, G500/G5 50 (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 issu ed to facilitate the exchange of al l 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 num ber 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 ch anges 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 reco mmended 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

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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 acco mplish 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 Aero space 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 AerostructuresService Bulletin SBTAGV/GVSP-28-JG0XXX. SERVICE BULLETIN. Part Number 31760-1

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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.