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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
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.
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.
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
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
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
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
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.
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.
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.
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.
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.