GE PROPRIETARY INFORMATION
The information contained in this document is GE proprietary information and is disclosed in confidence. It is the property of GE and shall not be used, disclosed to others or reproduced without the express written consent of GE, 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.
This technical data is considered EAR controlled pursuant to 15 CFR Parts 730-774 respectively. Transfer of this data by any means to a Non-US Person, whether in the United States or abroad, without the proper U.S. Government authorization (e.g., License, exemption, NLR, etc.), is strictly prohibited.
Copyright (2017) General Electric Company, U.S.A.
TRANSMITTAL INFORMATION
REVISION 3 TO SERVICE BULLETIN 73-0031
Revision 3 is issued to update paragraphs 1., PLANNING INFORMATION, 2., MATERIAL INFORMATION, and 3., ACCOMPLISHMENT INSTRUCTIONS.
Revision 2 was issued June 24, 2016. Revision 1 was issued March 23, 2015. The original was issued July 29, 2014. Revision bars in the left margin identify changes.
1.PLANNING INFORMATION
A.Effectivity
* * * FOR GEnx-1B64, -1B64/P1, -1B64/P2, -1B67, -1B67/P1, -1B67/P2, -1B70, -1B70/P1, -1B70C/P1, -1B70C/P2, -1B70/P2, -1B70/75/P1, -1B70/75/P2, -1B74/75/P1, -1B74/75/P2, -1B76A/P2
Deleted.
This Service Bulletin has been introduced in production to these GEnx-1B engines:
 •
GEnx-1B engines, serial numbers 956-955 and up.
These serial numbers are the best available data.
 The W13 harness electrical bracket (support bracket) P/N 2583M26G01 and attaching hardware are affected by this Service Bulletin.
B.Description
This Service Bulletin releases a new W13 harness electrical bracket (support bracket) P/N 2735M32G01.
 Also, two cushion loop clamps P/N AS62505 and two bolts P/N MS9556-06 are introduced by this Service Bulletin for both the replacement and rework options to allow better clamping of the W13 branches P133 and P135, with the difference of one additional nut P/N AS62505 for the rework option.
 The same objective can be achieved in the field by replacing the affected support bracket with the new P/N 2735M32G01 configuration or by rework of the affected support bracket to the P/N 2681M62G01 reworked configuration.
  NOTE:
Having any of the two field configuration options (replacement or rework) specified in paragraph 1.K., Interchangeability is allowed to comply with this Service Bulletin.
C.Compliance
Category 4
GE recommends that you do this Service Bulletin to introduce the new support bracket when the area is exposed.
NOTE:
This Service Bulletin can be accomplished on wing or in shop.
This Service Bulletin is offered to improve the reliability or performance of your GE product, or to help prevent the occurrence of the event or condition described in this Service Bulletin. If the operator elects not to participate in the bulletin, that decision will be taken into consideration by GE in evaluating future product performance issues that may arise in the operators fleet.
D.Concurrent Requirements
None.
E.Reason
(1)Objective:
To introduce new parts and improve reliability.
(2)Condition:
The flexible W13 harness has a potential for an over flexure condition on branches and potential undesirable riding of the flexible W13 harness.
(3)Cause:
The flexible W13 harness on branch P133 and P135 showed 16.0 inches (406 mm) and 18.0 inches (457 mm) respectively of unsupported length from the last clamping point to the connector.
(4)Improvement:
The new support bracket assures the route and clearances of the W13 harness to maintain it without affecting the structural integrity of the surrounding hardware.
The field rework of the support bracket P/N 2583M26G01 to P/N 2681M62G01 ensures a better clamping method and prevents chafing of the P133 and P135 branches of the W13 harness.
 The purpose of the revision 3 of this Service Bulletin is to ensure that engines coming out of production and in the field only have the cushioned loop clamps P/N AS62505 supporting both P133 and P135 branches to prevent branch chafing caused by other types of clamps or by the metal clip.
(5)Substantiation:
Substantiation is by analysis and comparative analysis.
F.Approval
 This Service Bulletin contains no modification information that revises the approved configuration and therefore does not require FAA or regulatory approval.
G.Manpower
After you get access to the fuel main inlet tube hose, you will need approximately 0.5 man-hour for each engine or component.
H.Weight and Balance
The complete compliance with this Service Bulletin increases weight by 0.3 lb (0.1 kg).
I.References (Use the latest version of this document)
GEK 9250, Commercial Engine Standard Practices Manual (SPM)
GEK 112851, GEnx-1B Engine Manual (EM)
GEK 112862, GEnx-1B Cleaning, Inspection, and Repair Manual (CIR)
GEK 112864, GEnx-1B Engine Illustrated Parts Catalog (EIPC)
GEnx-1B Boeing 787 Aircraft Maintenance Manual (AMM)
  NOTE:
The reference documents listed below are for the engine manufacturer's internal use only:
 
CID: 575130, 575570, 575708, 575879
 
BPP: 12-72-00-12
J.Publications Affected
GEK 112851, GEnx-1B Engine Manual (EM)
GEK 112864, GEnx-1B Engine Illustrated Parts Catalog (EIPC)
GEnx-1B Boeing 787 Aircraft Maintenance Manual (AMM)
K.Interchangeability
Qualified interchangeability.
Production configuration:
 The new support bracket P/N 2735M32G01, cushion loop clamps P/N AS62505, and double hexagon head machine bolts (bolts) P/N AS9556-06 or P/N MS9556-06 must be introduced in a complete engine set.
Field configuration:
 Two different possibilities are allowed in the field:
 (1)The support bracket P/N 2583M26G01, two cushion loop clamps P/N AS62505, nut P/N J1092P03, and bolts P/N AS9556-06 or P/N MS9556-06 must be introduced in a complete engine set.
 NOTE:
The support bracket P/N 2583M26G01 should be reworked to the P/N 2681M62G01 per the instructions included in this Service Bulletin paragraph 3.C., Rework.
 (2)The new support bracket P/N 2735M32G01, two cushion loop clamps P/N AS62505, and two bolts P/N MS9556-06 must be introduced in a complete engine set.
L.Software Accomplishment Summary
Not applicable.
2.MATERIAL INFORMATION
A.Material - Price and Availability
(1)Parts necessary to do this Service Bulletin:
 
Part Number
Qty/ Eng
Part Name
Unit ($) Price
Pkg Qty
Lead Time Days
 
1355-1349*
(1)
Packing, Preformed
NP
(-)
--
 
1391-0050*
(2)
Packing, Preformed
NP
(-)
--
 
1391-0052*
(1)
Packing, Preformed
NP
(-)
--
 
Deleted
 
For Field Replacement Option:
 
2735M32G01
(1)
Bracket, W13 Harness Electrical
175.00
(1)
Quote
 
AS62505
(1)
Clamp, Cushion Loop
NP
(-)
--
 
MS9556-06
(2)
Bolt, Double Hexagon Head Machine
NP
(-)
--
 
For Field Rework Option:
 
AS62505
(2)
Clamp, Cushion Loop
NP
(-)
--
 
MS9556-06
(2)
Bolt, Double Hexagon Head Machine
NP
(-)
--
 
J1092P03
(1)
Nut, Self-Locking
8.25
(50)
5
NP = Not Provisioned
 
*Part not supplied by GE Engine Services Distribution L.L.C. To procure parts, contact the following:
Woodward Governor Co.
5001 North Second Street
P.O. Box 7001
Rockford, Illinois 61125-7001
U.S.A.
NOTE:
Prices are provided for planning purposes and are subject to change.
(2)Other Spare Parts:
 
Part Number
Qty/ Eng
Part Name
Unit ($) Price
Pkg Qty
Lead Time Days
 
J1215P32**
(1)
Gasket, Flange Seal
263.25
(1)
5
 **Refer to paragraph 3., ACCOMPLISHMENT INSTRUCTIONS, step 3.A.(3).
NOTE:
Prices are provided for planning purposes and are subject to change.
(3)Consumables:
 
Code Number
Description
 
C02-019
Oil, Engine Lubricating
(engine oil)
 
C02-058
Compound, Thread Lubricating
(lubricant)
 
C10-182
Cloth, Cleaning for Aircraft Structural
(cleaning cloth)
B.Industry Support Information
 None.
C.Configuration Chart
 
New Part Number
Qty/ Eng
Part Name
Old Part Number/ IPC Location
Qty/ Eng
Op Code
Chg/ Sprt Code
 
(PRODUCTION ONLY)
 
2447M20G01/
G02/G03/G04
(X)
Assembly, Propulsor Module
2447M20G01
G02/G03/G04
(X)
RM
-/-
 
2376M20G02/
G03/G04/G05/
G06/G07/G08/
G09
(X)
Assembly, Propulsor Module
2376M20G02/
G03/G04/G05/
G06/G07/G08/
G09
(X)
RM
-/-
 
.2735M32G01
01-140A, 73-11-40
(1)
Bracket, W13 Harness Electrical
(Old Name)
Bracket, W13 Harness Support
(New Name)
(SIN 6741N)
.2583M26G01
01-140, 73-11-40
(1)
RE
5/-
 
.AS62505
01-180, 73-11-40
(2)
Clamp, Cushion Loop
(SIN 6708E)
.J1432P05
55-060, 73-21-65
(1)
RE/QTC
5/E
 
.MS9556-06
55-050A, 73-21-65
(2)
Bolt, Double Hexagon Head Machine
(SIN 6702A)
.MS9556-06
55-050A, 73-21-65
(1)
QTC
5/-
 
(FIELD REPLACEMENT OPTION)
 
2376M20G05/
G06/G07/G08/
G09
(X)
Assembly, Propulsor Module
2376M20G05/
G06/G07/G08/
G09
(X)
RM
-/-
 
2447M20G01/
G02/G03
(X)
Assembly, Propulsor Module
2447M20G01/
G02/G03
(X)
RM
-/-
 
.2735M32G01
01-140A, 73-11-40
(1)
Bracket, W13 Harness Electrical
(Old Name)
Bracket, W13 Harness Support
(New Name)
(SIN 6741N)
.2583M26G01
01-140, 73-11-40
(1)
RE
5/-
 
.AS62505
01-180, 73-11-40
(1)
Clamp, Cushion Loop
(SIN 6708E)
.J1432P05
55-060, 73-21-65
(1)
RE
5/E
 
.AS9556-06
55-050, 73-21-65
(1)
Bolt, Double Hexagon Head Machine
(SIN 6702A)
.AS9556-06*
55-050, 73-21-65
(1)
RM
-/-
 
OR
 
.MS9556-06
55-050A, 73-21-65
(1)
Bolt, Double Hexagon Head Machine
(SIN 6702A)
.MS9556-06*
55-050A, 73-21-65
(1)
RM
-/-
 
.AS62505
01-180, 73-11-40
(1)
Clamp, Cushion Loop
(SIN 6708E)
--
(-)
AD
5/-
 
.MS9556-06
01-150, 73-11-40
(1)
Bolt, Double Hexagon Head Machine
(SIN 67429)
--
(-)
AD
5/-
 
*GEnx-1B EIPC shows both configurations as possible existing bolts installed. If the bolt P/N MS9556-06 or P/N AS9556-06 is already installed, it should be kept as part of the new Revision 3 configuration intent of this Service Bulletin.
 
 
(FIELD REWORK OPTION)
 
2376M20G05/
G06/G07/G08/
G09
(X)
Assembly, Propulsor Module
2376M20G05/
G06/G07/G08/
G09
(X)
RM
-/-
 
2447M20G01/
G02/G03/G04
(X)
Assembly, Propulsor Module
2447M20G01/
G02/G03/G04
(X)
RM
-/-
 
.2681M62G01
01-141, 73-11-40
(1)
Bracket, W13 Harness Electrical
(SIN 6741N)
.2583M26G01
01-140, 73-11-40
(1)
RW
5/-
 
.AS62505
01-180, 73-11-40
(1)
Clamp, Cushion Loop
(SIN 6708E)
.J1432P05
55-060, 73-21-65
(1)
RE
5/E
 
.AS9556-06
55-050, 73-21-65
(1)
Bolt, Double Hexagon Head Machine
(SIN 6702A)
.AS9556-06*
55-050, 73-21-65
(1)
RM
-/-
 
OR
 
.MS9556-06
55-050A, 73-21-65
(1)
Bolt, Double Hexagon Head Machine
(SIN 6702A)
.MS9556-06*
55-050A, 73-21-65
(1)
RM
-/-
 
.AS62505
01-180, 73-11-40
(1)
Clamp, Cushion Loop
(SIN 6708E)
--
(-)
AD
5/-
 
.MS9556-06
01-150, 73-11-40
(1)
Bolt, Double Hexagon Head Machine
(SIN 67429)
--
(-)
AD
5/-
 
.J1092P03
01-160, 73-11-40
(1)
Nut, Self-Locking
(SIN 67441)
--
(-)
AD
5/-
 
*GEnx-1B EIPC shows both configurations as possible existing bolts installed. If the bolt P/N MS9556-06 or P/N AS9556-06 is already installed, it should be kept as part of the new Revision 3 configuration intent of this Service Bulletin.
  NOTE:
Deleted.
 Operation Codes
AD=Add
QTC=Quantity Change RE=Replace RM=Remains RW=Rework
Change Codes
5=Qualified interchangeability. Refer to paragraph 1.K., Interchangeability.
 Support Codes
A=Old parts will no longer be supplied. E=Old parts will be supplied, and can be used at other engine locations.
D.Parts Disposition
Old part is being reworked under some certain condition.
E.Tooling - Price and Availability
 
Tool Number
Description
 
--
Mechanics Hand-Tools
 
--
Hand Drill
 
--
Vibropeen Marker, Pneumatic or Electromagnetic
3.ACCOMPLISHMENT INSTRUCTIONS
A.Disassembly
WARNING:
DO NOT EAT, DRINK, BREATHE, OR LET THIS AVIATION TURBINE FUEL (JET FUEL) TOUCH YOU. IT IS POISONOUS AND POSSIBLY CARCINOGENIC. DO NOT USE THIS MATERIAL NEAR SPARKS, FLAMES, WELDING, HOT SURFACES OR IGNITION SOURCES. DO NOT SMOKE NEAR THIS MATERIAL. THIS CAN POSSIBLY CAUSE THE MATERIAL TO BURN. USE CORRECT PROTECTION EQUIPMENT APPROVED BY YOUR SAFETY OFFICE WHEN YOU TOUCH OR USE THIS MATERIAL.
CAUTION:
A LARGE VOLUME OF FUEL WILL DRAIN FROM THE FUEL SUPPLY SYSTEM. TO PREVENT A FUEL SPILL, YOU MUST USE A MINIMUM OF TWO 5 GAL (19 L) FUEL RESISTANT CONTAINERS TO DRAIN THE FUEL SYSTEM.
 (1)Drain the filter bowl (01-015, 73-11-01) on the main fuel pump (MFP) (6, Figure 2 or Figure 3) as follows:
 NOTE:
Figure 2 is for the Field Replacement option and Figure 3 is for the Field Rework option.
(a)Put a 5 gal (19 l) fuel resistant container, STD-201, below the filter bowl (01-015).
(b)Remove the drain plug (01-072) from the filter bowl (01-015) and let the fuel drain into the fuel resistant container.
(c)Remove and discard the preformed packing (01-070) from the drain plug (01-072).
WARNING:
REFER TO THE PRODUCT LABEL AND THE MANUFACTURERS (MATERIAL) SAFETY DATA SHEET FOR INSTRUCTIONS ON THE HAZARDS, STORAGE, SAFE HANDLING AND PROPER USE OF THIS PRODUCT.
CAUTION:
PUT A NEW PREFORMED PACKING (01-070) ON THE DRAIN PLUG (01-072). A USED PREFORMED PACKING (01-070) WILL NOT SEAL CORRECTLY. IF THE PREFORMED PACKING (01-070) DOES NOT SEAL, DAMAGE TO THE EQUIPMENT CAN OCCUR.
(d)Lubricate the new preformed packing (01-070) with C02-019 engine oil.
(e)Install the new preformed packing (01-070) on the drain plug (01-072).
(f)Install the drain plug (01-072) in the filter bowl (01-015).
(g)Torque the drain plug (01-072) to 105-115 lb in. (11.9-13.0 Nm).
WARNING:
DO NOT EAT, DRINK, BREATHE, OR LET THIS AVIATION TURBINE FUEL (JET FUEL) TOUCH YOU. IT IS POISONOUS AND POSSIBLY CARCINOGENIC. DO NOT USE THIS MATERIAL NEAR SPARKS, FLAMES, WELDING, HOT SURFACES OR IGNITION SOURCES. DO NOT SMOKE NEAR THIS MATERIAL. THIS CAN POSSIBLY CAUSE THE MATERIAL TO BURN. USE CORRECT PROTECTION EQUIPMENT APPROVED BY YOUR SAFETY OFFICE WHEN YOU TOUCH OR USE THIS MATERIAL.
CAUTION:
A LARGE VOLUME OF FUEL WILL DRAIN FROM THE FUEL SUPPLY SYSTEM. TO PREVENT A FUEL SPILL, YOU MUST USE A MINIMUM OF TWO 5 GAL (19 L) FUEL RESISTANT CONTAINERS TO DRAIN THE FUEL SYSTEM.
 (2)Drain the fuel at the MFP (6, Figure 2 or Figure 3) as follows:
 NOTE:
Figure 2 is for the Field Replacement option and Figure 3 is for the Field Rework option.
(a)Put a 5 gal (19 l) fuel resistant container, STD-201, below the MFP (6).
 (b)Remove the two machine plugs (01-035, 73-11-00) and machine plug (01-025) from the MFP (6, Figure 2 or Figure 3) and let the fuel drain into the fuel resistant container.
(c)Remove and discard the two preformed packings (01-030) and preformed packing (01-020) from the two machine plugs (01-035) and machine plug (01-025).
(d)Reinstall the two machine plugs (01-035) and machine plug (01-025) as follows:
WARNING:
REFER TO THE PRODUCT LABEL AND THE MANUFACTURERS (MATERIAL) SAFETY DATA SHEET FOR INSTRUCTIONS ON THE HAZARDS, STORAGE, SAFE HANDLING AND PROPER USE OF THIS PRODUCT.
CAUTION:
PUT NEW PREFORMED PACKINGS (01-030) AND PREFORMED PACKING (01-020) ON THE MACHINE PLUGS (01-035) AND MACHINE PLUG (01-025). FAILURE OF THE PREFORMED PACKINGS CAN CAUSE DAMAGE TO EQUIPMENT.
1Lubricate the new preformed packings (01-030) and preformed packing (01-020) with C02-019 engine oil.
2Put the new preformed packings (01-030) on the machine plugs (01-035) and new preformed packing (01-020) on the machine plug (01-025).
 3Install the machine plug (01-025) in the MFP (6, Figure 2 or Figure 3).
4Torque the machine plug (01-025) to 35-45 lb in. (4.0-5.1 Nm).
 5Install the machine plugs (01-035) in the MFP (6, Figure 2 or Figure 3).
6Torque the machine plugs (01-035) to 70-80 lb in. (7.9-9.0 Nm).
 (3)Remove the machine bolts (3, Figure 2 or Figure 3), fuel main inlet tube hose (4), and flange seal gasket (5) from the MFP (6).
 NOTE:
Figure 2 is for the Field Replacement option and Figure 3 is for the Field Rework option.
NOTE:
The flange seal gasket (5) is reusable, subject to an inspection. For in-shop, refer to the GEnx-1B CIR, 72-09-99, INSPECTION 001, Subtask 72-09-99-220-025. For on-wing, refer to the GEnx-1B Boeing 787 AMM, B787-A-G70-00-04-02A-520A-A, Gasket Seal with Imbedded Flexible Seal Material - Removal.
B.Assembly
WARNING:
REFER TO THE PRODUCT LABEL AND THE MANUFACTURERS (MATERIAL) SAFETY DATA SHEET FOR INSTRUCTIONS ON THE HAZARDS, STORAGE, SAFE HANDLING AND PROPER USE OF THIS PRODUCT.
(1)Lubricate the threads and washer faces of bolts with C02-058 lubricant before installation. After installation, remove unwanted C02-058 lubricant with C10-182 cleaning cloth.
 (2)Install the new support bracket (7, Figure 2) or the reworked support bracket (7, Figure 3) as follows:
(a)Install a flange seal gasket (5) on the MFP (6).
(b)Install the fuel main inlet tube hose (4) on the MFP (6).
(c)Attach the support bracket (7) and the fuel main inlet tube hose (4) with machine bolts (3).
(d)Torque the machine bolts (3) to 235 to 275 lb in. (26.6 to 31.1 Nm).
 (3)Install the W13 harness (1) as follows:
 (a)For the new support bracket (7, Figure 2), attach the W13 harness (1) to the support bracket (7) with two cushion loop clamps (8) and two bolts (9).
 (b)For the reworked support bracket (7, Figure 3), do as follows:
 1Attach the P135 branch of the W13 harness (1, Figure 1) to the reworked support bracket (7) with the new cushion loop clamp (8), bolt (9), and nut (10).
 2Attach the P133 branch of the W13 harness (1) to the support bracket (7) with the new cushion loop clamp (8) and bolt (9).
(c)Torque the bolts (9) to 32 to 38 lb in. (3.6 to 4.3 Nm).
C.Rework
 (1)Rework the support bracket (7, Figure 3) to the new configuration as follows:
 NOTE:
This rework procedure makes the installation of the P135 branch of the W13 harness (1) easier. At the same time, it introduces a new cushion loop clamp (8) to prevent chafing in the P133 and P135 branches of the W13 harness (1).
 (a)Find and put a mark that better suits the dimensions of the P135 branch to install the new cushion loop clamp (8). Refer to the tolerances specified in Figure 4, Sheet 1.
  NOTE:
Step 3.C.(1)(a) is necessary only if the P135 branch (Figure 1) of the W13 harness does not attach correctly in the clip, of the support bracket (1, Figure 1). If the dimension of the P135 branch fits correctly in the metal clip, this same location can be used. Continue with step 3.C.(1)(b).
 (b)Remove the current clip of the support bracket (7) by drilling out the two rivets that hold the clip to the support bracket (7). Refer to the SPM, 70-13-00, RIVETED JOINTS.
 (c)Make a hole in the support bracket (7, Figure 3) in the location marked in step 3.C.(2). Use a drill bit of the size specified in Figure 4, Sheet 1.
(d)Reidentify the support bracket (7, Figure 3) as follows:
1Find the part number marking location of support of bracket (7). Refer to Figure 4, Sheet 2.
2Cross out the existing part number 2583M26G01 of support bracket (7, Figure 1). Make sure to keep the old part number legible. Refer to the SPM, 70-16-04, VIBRO-PEEN MARKING.
3Identify the reworked support bracket (7, Figure 1) with part number 2681M62G01. Refer to the SPM, 70-16-04, VIBRO-PEEN MARKING.
 (2)Refer to Figure 5 for final post-GEnx-1B S/B 73-0031, Revision 3 configuration.
D.Post-Maintenance Operational Check
(1)Do a dry-motor-leak test (Test No. 1). Refer to the GEnx-1B Boeing 787 AMM, DMC-B787-A-G71-00-00-48A-364A-A.
Support Bracket Location
Figure 1  
Support Bracket Location
Figure 2  
Support Bracket Location
Figure 3  
Rework of the Support Bracket
Figure 4   (Sheet 1)
Rework of the Support Bracket
Figure 4   (Sheet 1)
Final post-GEnx-1B S/B 73-0031 Revision 3 Configuration
Figure 5