# General Electric Alert Service Bulletin CF6-80C2: No revision named

- Rights: © General Electric Company. Filed by the FAA in regulations.gov docket FAA-2020-0371, the docket of AD 2021-03-02. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [General Electric Alert Service Bulletin CF6-80C2](https://openairdocs.org/service-documents/ge/cf6-80c2.md)
- Title as filed: cf6-80c2-sb-72-1577-r01
- Pages: 13
- PDF: https://openairdocs.org/files/sha256/51/22/5122354d3d18f8bfeaa0efca0dbb2a9722cd675a849b870245dbd715c9346908
- Page: https://openairdocs.org/service-documents/ge/cf6-80c2/file/5122354d3d18

## Text

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### Page 1

CF6-80C2 Airbus Service Bulletins (SBs)
SB 72-1577 R01 ENGINE - Fuel Manifold and Drains (72-65-00) - HMU/MEC Idler Adapter
Inspection
Date Printed:
2019/09/18
GE PROPRIETARY INFORMATION - Not to be used, disclosed to
others or reproduced without the express written consent of
GE. Technical data is considered ITAR and/or EAR controlled;
transfer of this data to a Non-US Person, without USG
authorization, is strictly prohibited.
Page
1 of 13
CF6-80C2 SERVICE BULLETIN - 72-1577 R01 Revised:08/16/2019
SB 72-1577 R01 ENGINE - FUEL MANIFOLD AND DRAINS
(72-65-00) - HMU/MEC IDLER ADAPTER INSPECTION
Issued:
10/31/2018
GE Designated: -CONFIDENTIAL-
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 part.
This technical data is considered subject to the Export Administration
Regulations (EAR) pursuant to 15 CFR Parts 730-774. Transfer of this
data by any means to a Non-U.S. 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 (2019) General Electric Company, U.S.A.
TRANSMITTAL INFORMATION
REVISION 1 TO SERVICE BULLETIN 72-1577
Revision 1 is issued to update paragraphs 1., , 2.,PLANNING INFORMATION
, and 3., .MATERIAL INFORMATION ACCOMPLISHMENT INSTRUCTIONS
The original was issued October 31, 2018. Revision bars in the left
margin identify changes.
1. PLANNING INFORMATION
A. Effectivity
* * * CF6-80C2A1/A2/A3/A5/A8/B1/B2/B4/B6
* * * CF6-80C2A5F/B1F/B2F/B4F/B5F/B6F/B6FA/B7F/B8F/D1F
This Service Bulletin is not applicable to these CF6-80C2
engines:
*CF6-80C2 engines, serial numbers 707-417 and up are not affected by this
Service Bulletin.
*CF6-80C2 engines, which have not had a shop visit prior to November 1, 2018.
These serial numbers are the best available data.
The accessory gearbox (AGB) adapters [hydromechanical unit
(HMU)/main engine control (MEC) idler adapters] P/N ,9395M78G01
P/N , P/N , P/N , P/N ,9395M78G02 9395M78G04 9395M78G05 9395M78G08
and P/N  are affected by this Service Bulletin.9395M78G10

### Page 2

CF6-80C2 Airbus Service Bulletins (SBs)
SB 72-1577 R01 ENGINE - Fuel Manifold and Drains (72-65-00) - HMU/MEC Idler Adapter
Inspection
Date Printed:
2019/09/18
GE PROPRIETARY INFORMATION - Not to be used, disclosed to
others or reproduced without the express written consent of
GE. Technical data is considered ITAR and/or EAR controlled;
transfer of this data to a Non-US Person, without USG
authorization, is strictly prohibited.
Page
2 of 13
This Service Bulletin is applicable only for AGB adapters with
Tap-Lok inserts.
B. Description
This Service Bulletin provides instructions to do an inspection
of the inserts on the HMU/MEC idler adapter and a pull check.
C. Compliance
Category 2
GE recommends that you do this Service Bulletin as soon as
possible without effect on revenue service but no later than
1,200 flight hours from Service Bulletin issuance date with
repeat inspections not to exceed 1,200 flight hours between
inspections. Terminating action to be completed no later than
next shop visit.
Impact B
This recommendation is to address a condition that may result in
an Increased Rate of In-Flight Shutdowns (IFSD), Take-Off Aborts
(TOA), Air Turn Backs (ATB) or Diversions (DIV).
NOTE:This Service Bulletin can be done 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
operator's fleet.
D. Concurrent Requirements
None.
E. Reason
(1) Objective:
To improve reliability and reduce significant events.
To prevent a fuel leak and possible undercowl fire events in the CF6-80C2
engines.
(2) Condition:
A threaded insert in the HMU/MEC idler adapter flange pulled-out, causing a
fuel leak.
(3) Cause:
The repair of the insert was done incorrectly.
(4) Inspection:
The inspection will detect if the inserts are installed correctly.
(5) Substantiation:
Substantiation is by comparative analysis and fleet experience.
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 AGB assembly, you will need 1
man-hour to do the shim check. If the assembly passes the shim
check, no additional manpower is required. If the assembly fails
the shim check, 4 additional man-hours will be needed to do the
protrusion and pull-out test of the inserts.
H. Weight and Balance
Weight and balance are not changed.

### Page 3

CF6-80C2 Airbus Service Bulletins (SBs)
SB 72-1577 R01 ENGINE - Fuel Manifold and Drains (72-65-00) - HMU/MEC Idler Adapter
Inspection
Date Printed:
2019/09/18
GE PROPRIETARY INFORMATION - Not to be used, disclosed to
others or reproduced without the express written consent of
GE. Technical data is considered ITAR and/or EAR controlled;
transfer of this data to a Non-US Person, without USG
authorization, is strictly prohibited.
Page
3 of 13
I. References (Use the latest version of these documents)
Airbus A300-600 Aircraft Maintenance Manual (AMM)
Airbus A310 Aircraft Maintenance Manual (AMM)
Boeing 747-200/300 Aircraft Maintenance Manual (AMM)
Boeing 747-400 Aircraft Maintenance Manual (AMM)
Boeing 767 Aircraft Maintenance Manual (AMM)
McDonnell Douglas MD-11 Aircraft Maintenance Manual (AMM)
GEK 9250, Commercial Engine Standard Practices Manual (SPM)
GEK 92451, CF6-80C2 Engine Manual (EM)
GEK 92452-1, CF6-80C2A (PMC) Illustrated Parts Catalog (IPC)
GEK 92452-2, CF6-80C2B (PMC) Illustrated Parts Catalog (IPC)
GEK 92452-3, CF6-80C2D (FADEC) Illustrated Parts Catalog (IPC)
GEK 92452-4, CF6-80C2B (FADEC) Illustrated Parts Catalog (IPC)
GEK 92452-5, CF6-80C2A (FADEC) Illustrated Parts Catalog (IPC)
J. Publications Affected
None.
K. Interchangeability
Not applicable.
L. Software Accomplishment Summary
Not applicable.
2. MATERIAL INFORMATION
A. Material - Price and Availability
(1) Parts necessary to do this Service Bulletin:
None.
(2) Other Spare Parts:
Part Number
Qty/
Eng Part Name
Unit ($)
Price 
Pkg
Qty
Lead Time
Days
1453M60P04 (AR) Gasket, Seal 28.00 (10) 5
9117M58P07 (AR) Insert, Oversize
Screw (Second
Oversize)
Thread-Self-Tapping
50.25 (1) Quote
9117M35P08 (AR) Insert, Oversize
Screw (Third
Oversize)
Thread-Self-Tapping
72.50 (10) 5
NOTE:Prices are provided for planning purposes and are subject to change.
(3) Consumables:
Code Number Description
C03-001 Primer, Zinc Chromate
C04-035 Solvent, General (isopropyl alcohol)
C10-067 Tape, Platers (tape) (or equivalent)
C10-182 Cloth, Cleaning for Aircraft Structural (clean cloth)
B. Industry Support Information
None.
C. Configuration Chart
None.
D. Parts Disposition
Remove and replace inserts if a failure of the pull-out test
occurs.

### Page 4

CF6-80C2 Airbus Service Bulletins (SBs)
SB 72-1577 R01 ENGINE - Fuel Manifold and Drains (72-65-00) - HMU/MEC Idler Adapter
Inspection
Date Printed:
2019/09/18
GE PROPRIETARY INFORMATION - Not to be used, disclosed to
others or reproduced without the express written consent of
GE. Technical data is considered ITAR and/or EAR controlled;
transfer of this data to a Non-US Person, without USG
authorization, is strictly prohibited.
Page
4 of 13
E. Tooling - Price and Availability
Description Refer To
Locally Manufactured Pull-Out
Test Tool
Figure 2 
Tool Number Description
-- Screw Extractor [for use in a 0.250 inch (6.35 mm)
hole]
-- High Speed Hand Drill
-- Appropriate Size Uncoated, Straight Flute or Twist
Drill Bit with a Point Angle of 115 to 140 Degrees
-- 1/4-28 Tap-Lok Insertion Driver Tool
3. ACCOMPLISHMENT INSTRUCTIONS
A. General
NOTE:This Service Bulletin contains two options.
(1) Option 1 - repetitive shim check, to be performed within 1,200 flight hours
with repeat inspections not to exceed 1,200 flight hours between
inspections. Refer to paragraph 3.B., .Option 1 - Containment Action
(2) Option 2 - one-time pull check of the installed inserts on the HMU/MEC
idler adapter to be performed no later than next engine shop visit. Refer
to paragraph 3.C., .Option 2 - Terminating Action
B. Option 1 - Containment Action
(1) Do a shim check at the eight bolt locations as follows:
NOTE:Removal of the bracket is optional. The shim check can be done with and
without the bracket installed.
(a) Optional Procedure. Remove the bracket. Refer to  Item 3Figure 1,
(Bolt) and Item 4 (Bracket).
1 Remove the three bolts that attach the bracket.
2 Remove the bracket.
3 Install the bolts again and torque the bolts to 110 to 140 lb in.
(12.4 to 15.8 Nm).
(b) Do the shim check with a shim stock of 0.004 inch (0.10 mm) on the
adapter flange-gasket interface. Refer to  and do as follows:Figure 1
1 Insert a shim of 0.004 inch (0.10 mm) between the gasket and the
HMU/MEC idler adapter flange at each of the eight bolt locations and
as follows:
a If you cannot insert the shim of 0.004 inch (0.10 mm) between
the gasket and the flange for each of the eight bolt locations,
this is considered a PASS.
1) Install the bracket back if you removed it. The installation
of the bracket, as specified in step 3.B.(1)(b) , is1b
necessary to complete this inspection.
b Install the bracket again. Refer to  Item 3 (Bolt) andFigure 1,
Item 4 (Bracket) and do as follows:
1) Remove the three bolts at the bracket location.
2) Install the bracket with the three bolts.
3) Torque the three bolts to 110 to 140 lb in. (12.4 to 15.8
Nm).
c If you can insert the shim of 0.004 inch (0.10 mm) between the
gasket and the flange at any of the eight bolt locations more
than 0.100 inch (2.54 mm) in depth, this is considered a FAIL.
Complete the shim check at each of the remaining bolt locations.
Note locations which fail and continue with step 3.B.(1)(c).
(c) If the shim check fails, torque the bolt again to 110 to 140 lb in.
(12.4 to 15.8 Nm) at each bolt locations that failed the shim check. Do
the shim check again with a shim of 0.004 inch (0.10 mm) on the adapter
flange-gasket interface.
(d) If the shim check fails once more after you torque the bolt again, do

### Page 5

CF6-80C2 Airbus Service Bulletins (SBs)
SB 72-1577 R01 ENGINE - Fuel Manifold and Drains (72-65-00) - HMU/MEC Idler Adapter
Inspection
Date Printed:
2019/09/18
GE PROPRIETARY INFORMATION - Not to be used, disclosed to
others or reproduced without the express written consent of
GE. Technical data is considered ITAR and/or EAR controlled;
transfer of this data to a Non-US Person, without USG
authorization, is strictly prohibited.
Page
5 of 13
paragraph 3.C., .Option 2 - Terminating Action
C. Option 2 - Terminating Action
(1) Remove the fuel pump tube and fuel tube. Refer to  Item 1 (FuelFigure 1,
Pump Tube) and Item 2 (Fuel Tube) and Table 1 for applicable AMM removal
instructions.
NOTE:The rigid fuel pump tube and fuel tube that are installed in the HMU/MEC
idler adapter pads are connected to the fuel pump (bypass and discharge).
The fuel pump tube and fuel tube must be removed from the two sides to
get access to the AGB pads.
Table 1. Fuel Pump Tube, Fuel Tube Removal, and Installation Reference
Table
AMM Procedure Reference
Boeing
747-400 AMM
(FADEC)
1. Remove the bypass tube form the
hydromechanical unit (HMU) adapter on the
AGB and remove the discharge tube from the
HMU adapter on the AGB.
Refer to the Boeing 747-400
AMM, 73-11-01, TASK
73-11-01-004-001-J00,
Subtask
73-11-01-034-008-J00,
paragraphs (2)(b) and
(2)(c).
2. Install the bypass tube in the HMU
adapter on the AGB and install the
discharge tube in the HMU adapter on the
AGB.
Refer to the Boeing 747-400
AMM, 73-11-01, TASK
73-11-01-404-016-J00,
Subtasks
73-11-01-224-046-J00,
73-11-01-224-041-J00, and
73-11-01-434-027-J00.
Boeing
747-200/300
AMM
(PMC)
1. Remove the bypass tube from the main
engine control (MEC) adapter on the AGB and
remove the discharge tube from the MEC
adapter on the AGB.
Refer to the Boeing
747-200/300 AMM, 73-11-01,
paragraphs 4.C.(3) and (4).
2. Install the bypass tube in the MEC
adapter on the AGB and install the
discharge tube in the MEC adapter on the
AGB.
Refer to the Boeing
747-200/300 AMM, 73-11-01,
paragraphs J.(1), (2), and
(3).
Boeing 767
AMM
(PMC)
1. Remove the bypass tube from the MEC
adapter on the AGB and remove the discharge
tube from the MEC adapter on the AGB.
Refer to the Boeing 767 AMM,
73-11-01, TASK
73-11-01-004-001-H00,
Subtask
73-11-01-034-010-H00,
paragraphs (2)(b) and
(2)(c).
2. Install the bypass tube in the MEC
adapter on the AGB and install the
discharge tube in the MEC adapter on the
AGB.
Refer to the Boeing 767 AMM,
73-11-01, TASK
73-11-01-404-039-H00,
Subtasks
73-11-01-224-027-H00,
73-11-01-224-028-H00, and
73-11-01-434-029-H00.
Boeing 767
AMM
(FADEC)
1. Remove the bypass tube from the HMU
adapter on the AGB and remove the discharge
tube from the HMU adapter on the AGB.
Refer to the Boeing 767 AMM,
73-11-01, TASK
73-11-01-004-001-H03,
Subtask
73-11-01-034-008-H03,
paragraphs (2)(c) and
(2)(d).
2. Install the bypass tube in the HMU
adapter on the AGB and install the
discharge tube in the HMU adapter on the
AGB.
Refer to the Boeing 767 AMM,
73-11-01, TASK
73-11-01-404-018-H03,
Subtasks

### Page 6

CF6-80C2 Airbus Service Bulletins (SBs)
SB 72-1577 R01 ENGINE - Fuel Manifold and Drains (72-65-00) - HMU/MEC Idler Adapter
Inspection
Date Printed:
2019/09/18
GE PROPRIETARY INFORMATION - Not to be used, disclosed to
others or reproduced without the express written consent of
GE. Technical data is considered ITAR and/or EAR controlled;
transfer of this data to a Non-US Person, without USG
authorization, is strictly prohibited.
Page
6 of 13
73-11-01-224-028-H03,
73-11-01-224-029-H03, and
73-11-01-434-032-H03.
McDonnell
Douglas
MD-11 AMM
(FADEC)
1. Remove the return fuel tube and the
control fuel tube from the fuel pump and
the AGB.
Refer to the McDonnell
Douglas MD-11 AMM, 73-12-01,
TASK 73-12-01-000-801,
Subtask 73-12-01-030-001.
2. Install the return fuel tube and the
control fuel tube in the fuel pump and the
AGB.
Refer to the McDonnell
Douglas MD-11 AMM, 73-12-01,
TASK 73-12-01-400-801,
Subtask 73-12-01-820-020,
paragraphs (7)(c), (7)(d),
and (7)(e) and Subtask
73-12-01-430-001, paragraphs
(9), (10), and (11).
Airbus
A300-600
(FADEC)
1. Remove the fuel pump discharge tube and
the fuel return tube attached to the fuel
pump and the HMU adapter.
Refer to the Airbus A300-600
AMM, 73-12-01, TASK
73-12-01, Page 401,
paragraphs 2.B.(3) and (4).
2. Install the fuel pump discharge tube and
the fuel return tube attached to the fuel
pump and the HMU adapter.
Refer to the Airbus A300-600
AMM, 73-12-01, TASK
73-12-01, paragraphs
2.C.(9), (10), and (11).
Airbus
A300-600
(PMC)
1. Remove the fuel pump discharge tube and
the fuel return tube attached to the fuel
pump and the MEC adapter.
Refer to the Airbus A300-600
AMM, 73-12-01, TASK
73-12-01, paragraphs 2.B.(3)
and (4).
2. Install the fuel pump discharge tube and
the fuel return tube attached to the fuel
pump and the MEC adapter.
Refer to the Airbus A300-600
AMM, 73-12-01, TASK
73-12-01, paragraphs
2.C.(9), (10), and (11).
Airbus A310
(PMC)
1. Remove the fuel pump discharge tube and
the fuel return tube attached to the fuel
pump and the MEC adapter.
Refer to the Airbus A310
AMM, 73-12-01, TASK
73-12-01, paragraphs 2.B.(3)
and (4).
2. Install the fuel pump discharge tube and
the fuel return tube attached to the fuel
pump and the MEC adapter.
Refer to the Airbus A310
AMM, 73-12-01, TASK
73-12-01, paragraphs
2.C.(9), (10), and (11).
(2) Do a standard insert inspection. Refer to the CF6-80C2 EM, 72-65-02,
INSPECTION.
(3) Do a protrusion check at all eight bolt locations as follows:
(a) Do an inspection of the eight inserts to make sure that they do not
protrude above the idler adapter flange face as follows:
1 Put a straight edge across the surface. If the insert is below the
bottom of the straight edge, the insert is correct.
2 If you find protruded insert(s), replace the protruded insert(s).
Refer to paragraph 3.C.(5).
(b) Do a check for insert looseness. Refer to  Item 3 (Bolt) andFigure 1,
do as follows:
1 Insert the bolt and do a check for insert movement. If you find
movement, replace the insert. Refer to paragraph 3.C.(5).
(c) If you do not find protrusion or movement, continue with the pull-out
test. Refer to paragraph 3.C.(4).
(4) Do a pull-out test at all eight bolt locations as follows:
(a) Use the locally manufactured pull-out test tool. Refer to  andFigure 2
do as follows:
1 Insert a 1/4-28 bolt and torque to 190 to 210 lb in. (21.4 to 23.7

### Page 7

CF6-80C2 Airbus Service Bulletins (SBs)
SB 72-1577 R01 ENGINE - Fuel Manifold and Drains (72-65-00) - HMU/MEC Idler Adapter
Inspection
Date Printed:
2019/09/18
GE PROPRIETARY INFORMATION - Not to be used, disclosed to
others or reproduced without the express written consent of
GE. Technical data is considered ITAR and/or EAR controlled;
transfer of this data to a Non-US Person, without USG
authorization, is strictly prohibited.
Page
7 of 13
Nm).
2 Loosen and remove the 1/4-28 bolt.
(b) Do a check of the insert again for protrusion. Refer to paragraph
3.C.(3) and do as follows:
1 If you find protruded insert(s), replace the protruded insert(s).
Refer to paragraph 3.C.(5).
2 If you do not find protrusion, install the removed fuel pump tube
and fuel tube. Refer to  Item 1 (Fuel Pump Tube) and ItemFigure 1,
2 (Fuel Tube), Table 1 for applicable AMM installation instructions,
and do as follows:
a Put a mark 72-1577 on the HMU/MEC idler adapter to show
compliance with this Service Bulletin. Use a light vibro-peen on
the area showed on  Refer to the SPM, 70-16-04,Figure 3.
VIBRO-PEEN MARKING.
(5) Do the insert replacement as follows:
WARNING:REFER TO THE PRODUCT LABEL AND THE MANUFACTURER'S (MATERIAL) SAFETY
DATA SHEET FOR INSTRUCTIONS ON THE HAZARDS, STORAGE, SAFE HANDLING
AND PROPER USE OF THIS PRODUCT.
(a) Use a clean cloth (C10-182) to clean the flange surface with isopropyl
alcohol (C04-035) and remove the fuel residue.
CAUTION:THE FOREIGN MATERIAL INTO THE ENGINE FUEL SYSTEM CAN CAUSE
OPERATIONAL ISSUES THAT INCLUDE THE LOSS OF THRUST CONTROL AND
IN-FLIGHT SHUTDOWNS (IFSD).
(b) Cover all open ports to make sure that no foreign material enters into
the engine hardware. You can use an approved tape (C10-067) for this
purpose.
(c) Use a screw extractor to unscrew the damaged threaded insert and remove
it.
(d) Refer to the SPM, 70-48-03, TAP-LOK INSERTS, Table 2 for recommended
drill/hole size and TAP-LOK insert for second or third TAP-LOK insert
replacement.
NOTE:For insert replacement, only a second or third TAP-LOK insert
replacement applies. First replacement is not applicable.
(e) Hold the drill perpendicular to the flange face.
(f) Center the drill bit in the insert hole.
(g) With a high speed drill and a light feed force, drill the hole to size.
The hole will go through the flange to the back side.
NOTE:The use of a cutting fluid is not necessary.
(h) Deburr the hole to remove burrs or high metal on the two sides of the
flange. You can introduce a chamfer of up to 0.010 inch (0.25 mm) to
remove burrs.
WARNING:REFER TO THE PRODUCT LABEL AND THE MANUFACTURER'S (MATERIAL) SAFETY
DATA SHEET (SDS) FOR INSTRUCTIONS ON THE HAZARDS, STORAGE, SAFE
HANDLING AND PROPER USE OF THIS PRODUCT.
(i) Coat the surface of the hole and the insert threads with zinc chromate
primer (C03-001).
(j) Use the 1/4-28 Tap-Lok insertion driver tool to drive the insert to
0.005-0.040 inch (0.13-1.02 mm) below the flange surface.
(k) Thoroughly clean the area to remove all chips and debris.
(l) Wipe the flange surface with a clean cloth (C10-182) to remove all fine
particles.
(m) Put a mark 72-1577 on the HMU/MEC idler adapter to show compliance with
this Service Bulletin. Use a light vibro-peen next to the idler adapter
part number. Refer to the SPM, 70-16-04, VIBRO-PEEN MARKING.
(n) Remove the protective covers used to close the open ports.
WARNING:REFER TO THE PRODUCT LABEL AND THE MANUFACTURER'S (MATERIAL) SAFETY
DATA SHEET FOR INSTRUCTIONS ON THE HAZARDS, STORAGE, SAFE HANDLING
AND PROPER USE OF THIS PRODUCT.
(o) Use a clean cloth (C10-182) with isopropyl alcohol (C04-035) to wipe
the flange surface and remove fine particles and tape (C10-067) residue

### Page 8 (OCR)

CF6-80C2 Airbus Service Bulletins (SBS)
SB 72-1577 R01 ENGINE - Fuel Manifold and Drains (72-65-00) - HMU/MEC Idler Adapter
Inspection
if used.
(6) Do an inspection of the fuel pump tube/fuel tube and adapter flange-gasket.
Refer to the CF6-80C2 EM, 72-00-05, INSPECTION/CHECK.
(7) Install back the fuel pump tube and fuel tube. Refer to Figure 1, Item 1
(Fuel Pump Tube) and Item 2 (Fuel Tube) and Table 1 for applicable AMM
installation instructions.
AGB
FWD
ACCESSORY  HMU/MEC
GEARBOX
FUEL PUMP
(BYPASS)
2
(DISCHARGE)
LEGEND:
1. FUEL PUMP TUBE
2. FUEL TUBE  5059736-00
Location of the HMU/MEC Fuel Control Idler Adapter
Figure 1 (Sheet 1)
GE PROPRIETARY INFORMATION - Not to be used, disclosed to
Date Printed:  others or reproduced without the express written consent of  Page
2019/09/18  GE. Technical data is considered ITAR and/or EAR controlled;  8 of 13
transfer of this data to a Non-US Person, without USG
authorization, is strictly prohibited.

### Page 9 (OCR)

CF6-80C2 Airbus Service Bulletins (SBS)
SB 72-1577 RO1 ENGINE - Fuel Manifold and Drains (72-65-00) - HMU/MEC Idler Adapter
Inspection
SHIM CHECK
(8 BOLT LOCATIONS)
1 (REF)
2 (REF)
LEGEND
3. BOLT (QTY-8)
4. BRACKET  5060049-00
Location of the HMU/MEC Fuel Control Idler Adapter
Figure 1 (Sheet 2)
GE PROPRIETARY INFORMATION - Not to be used, disclosed to
Date Printed:  others or reproduced without the express written consent of  Page
2019/09/18  GE. Technical data is considered ITAR and/or EAR controlled;  9 of 13
transfer of this data to a Non-US  Person, without USG
authorization, is strictly prohibited.

### Page 10 (OCR)

CF6-80C2 Airbus Service Bulletins (SBs)
SB 72-1577 R01 ENGINE - Fuel Manifold and Drains (72-65-00) - HMU/MEC Idler Adapter
Inspection
OPTIONAL SPOT WELDS
FLANGE.
INSERT
3
LOCALLY MANUFACTURED WASHER STACK
LEGEND:
1. 1/4-28 BOLT P/N MS9566-XX
2. WASHER (QTY-AR)
INNER DIAMETER 0.25 (6.4)
3. WASHER
MINIMUM INNER DIAMETER 0.625 (15.88)
MINIMUM THICKNESS 0.050 (1.27)
NOTE:
1. DIMENSIONS ARE IN INCHES WITH
MILLIMETERS IN PARENTHESES.
2. BOLT LENGTH NEEDED=INSERT DEPTH 0.480 (12.19)+WASHER STACK.  5059738-00
Pull-Out Test Tool
Figure 2 (Sheet 1)
GE PROPRIETARY INFORMATION - Not to be used, disclosed to
Date Printed:  others or reproduced without the express written consent of  Page
2019/09/18  GE. Technical data is considered ITAR and/or EAR controlled;  10 of 13
transfer of this data to a Non-US Person, without USG
authorization, is strictly prohibited.

### Page 11 (OCR)

CF6-80C2 Airbus Service Bulletins (SBS)
SB 72-1577 RO1 ENGINE - Fuel Manifold and Drains (72-65-00) - HMU/MEC Idler Adapter
Inspection
TOOLING REQUIRED
LOCALLY MANUFACTURED OR PROCURED TOOLING - PLATE
2 (REF)
OPTIONAL
WELDS
1.812
(46.02)
1.812
(46.02)
INSERT  FLANGE
0.625 MIN
(15.88)  1 (REF)
HOLE
(4 PLACES)
LOCALLY MANUFACTURED PLATE
LEGEND:
4. PLATE
MINIMUM THICKNESS 0.050 (1.27)
NOTE:
1. DIMENSIONS ARE IN INCHES WITH
MILLIMETERS IN PARENTHESES.
2. BOLT LENGTH NEEDED-INSERT DEPTH 0.480 (12.19)+PLATE AND WASHER STACK.  5060044-01
Pull-Out Test Tool
Figure 2 (Sheet 2)
GE PROPRIETARY INFORMATION - Not to be used, disclosed to
Date Printed:  others or reproduced without the express written consent of  Page
2019/09/18  GE. Technical data is considered ITAR and/or EAR controlled;  11 of 13
transfer of this data to a Non-US Person, without USG
authorization, is strictly prohibited.

### Page 12 (OCR)

CF6-80C2 Airbus Service Bulletins (SBS)
SB 72-1577 RO1 ENGINE - Fuel Manifold and Drains (72-65-00) - HMU/MEC Idler Adapter
Inspection
AGB
LiO
MARKING LOCATION*
FORWARD LOOKING AFT
NOTE:
*THE MARK MUST BE DONE IN ONE OF THESE AREAS.  6001211-00
Marking Areas
Figure 3
4. APPENDIX A - Inspection Criteria Flow Down Chart
GE PROPRIETARY INFORMATION - Not to be used, disclosed to
Date Printed:  others or reproduced without the express written consent of  Page
2019/09/18  GE. Technical data is considered ITAR and/or EAR controlled;  12 of 13
transfer of this data to a Non-US Person, without USG
authorization, is strictly prohibited.

### Page 13 (OCR)

CF6-80C2 Airbus Service Bulletins (SBS)
SB 72-1577 RO1 ENGINE - Fuel Manifold and Drains (72-65-00) - HMU/MEC Idler Adapter
Inspection
NO ACTION
ENGINE LESS THAN  NO
ESN 707-417  REQUIRED
YES
DID ENGINE HAVE
FIRST SHOP VISIT  NO
BEFORE  PUT A MARK 72-1577
NOVEMBER 1, 2018?  ON THE ADAPTER TO
SHOW COMPLIANCE
YES  WITH THIS SERVICE
BULLETIN
OPTIONS
COMPLETE
OPTION 1  OPTION 2
CONTAINMENT ACTION  TERMINATING ACTION
* DO A STANDARD INSERT INSPECTION.
PASS  DO A SHIM CHECK ON  THE ADAPTER FLANGE-GASKET  INSPECTION.  REFER TO THE CF6-80C2 EM, 72-65-02,
INTERFACE AT LETTER  CHECK (ON-WING)  ° DO A CHECK FOR INSERT PROTRUSION.  * DO A PULL-OUT TEST OF  PASS
200 LB. IN. (22.5 NM) AT 8 BOLT LOCATIONS.
* DO A FUEL PUMP TUBE/FUEL TUBE AND
ADAPTER FLANGE-GASKET CHECK.
DO A CHECK OF THE BOLT  REFER TO THE CF6-80C2 EM, 72-00-05,
TORQUE AND TORQUE AGAIN  FAIL  INSPECTION/CHECK.
TO 110 to 140 LB. IN.
(12.4 TO 15.8 NM)  FAIL
PASS
REPLACE INSERT WITH
DO A SHIM CHECK ON THE  SECOND OR THIRD
ADAPTER FLANGE-GASKET  OVERSIZE INSERT
INTERFACE (ON-WING)
5060046-00
Criteria Flow Down Chart
Figure 4
GE Designated: - CONFIDENTIAL Subject to the restrictions on the media
GE PROPRIETARY INFORMATION - Not to be used, disclosed to
2019/09/18  Date Printed:  others or reproduced without the express written consent of  GE. Technical data is considered ITAR and/or EAR controlled;  13 of 13  Page
transfer of this data to a Non-US Person, without USG
authorization, is strictly prohibited.

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