### Commercial Airplanes 

# 757 Service Bulletin SPECIAL ATTENTION Number: 757-57-0071 Original Issue: September 12, 2012 ATA System: 5750 SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Inboard Flap, Inboard Track - Forward Support Fitting Inspection and Replacement Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2012 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, DreamlinerTM, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing. BOEING is a trademark of Boeing Management Company.

Original Issue: September 12, 2012 757-57-0071 1 of 69 4.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 2 of 69 BOEING SERVICE BULLETIN 757-57-0071

BLANK PAGETable of Contents Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 1. PLANNING INFORMATION........................................ 9 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 1. Airplanes............................................. 9 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 24 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 24 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 25 M. Software Accomplishment Summary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 C. Parts Necessary for Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 27 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 28 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 FIGURE 1: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY INSPECTION [Group 1]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34 FIGURE 2: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY INSPECTION [Group 2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 FIGURE 3: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT [Group 1]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 FIGURE 4: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT [Group 2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46 FIGURE 5: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY INSPECTION [Group 1]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52 FIGURE 6: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY INSPECTION [Group 2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 3 of 69 BOEING SERVICE BULLETIN 757-57-0071FIGURE 7: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT [Group 1]. . . . . . . . . . . . . . . . . . . . . . . . . . . 58 FIGURE 8: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT [Group 2]. . . . . . . . . . . . . . . . . . . . . . . . . . . 64

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 4 of 69 BOEING SERVICE BULLETIN 757-57-0071

### Commercial Airplanes 

# 757 Service Bulletin SPECIAL ATTENTION Summary Number: 757-57-0071 Original Issue: September 12, 2012 ATA System: 5750 SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Inboard Flap, Inboard Track - Forward Support Fitting Inspection and Replacement BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. CONCURRENT REQUIREMENTS None. BACKGROUND This service bulletin gives instructions to inspect and if necessary replace the forward support fitting assembly at the inboard flap, inboard track. The forward support fitting assembly consists of two back-to-back machined components that attach the forward end of the inboard track of the inboard flap to the Main Landing Gear (MLG) beam. If the work in this service bulletin is not done, a broken forward support fitting could lead to loss of inboard flap control and subsequent inability to fly the airplane safely. One operator reported a broken forward support fitting assembly at the inboard flap, inboard track. During a post flight taxi, the pilots noticed a FLAP TE DISAGREE message on the Engine Indication and Crew Alerting System (EICAS). On examination, the ground maintenance personnel discovered that both components of the forward support fitting assembly had broken causing the inboard track and transmission to drop about eight inches into the wheel well. The incident occurred at 22,328 flight cycles and is the only reported incident of this type. Metallurgical analysis determined that cracks had initiated at a compound radius in each component flange common to the MLG beam. Each crack propagated by fatigue and was followed by final ductile rupture. Accomplishment of the work in this service bulletin will make sure that any cracked forward support fitting assembly at the inboard flap, inboard track is found and replaced. Boeing Service Related Problem (SRP) 757-SRP-57-0245 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 757 FTD 57-10004 is related to this service bulletin. This table is provided to operators for planning purposes only. Refer to the applicable sections for more information.
Reference Affected Planning Data Paragraph 1.A.2., Spares Affected No Spares Affected

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 5 of 69Reference Affected Planning Data Paragraph 1.E., Compliance No AD Related Paragraph 1.H., Weight and Balance Changes No Weight and Balance Change Paragraph 1.I., Electrical Load Data No Electrical Load Changed Paragraph 1.K., Publications Affected No Publications Affected Paragraph 1.K., Publications Affected No Airplane Flight Operations Affected (Flight CrewOperations Manual and/or FAA Approved Airplane Flight Manual) Paragraph 2.C.1., Kits/Parts No Kits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator Yes Operator Supplied Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin No Special Tooling Required

ACTION Get access to the inboard flap, inboard track of the left wing and the right wing. Do a High Frequency Eddy Current (HFEC) inspection for cracking in the flanges of the forward support fitting assembly common to the MLG beam. If any crack is found, replace the forward support fitting assembly in accordance with this service bulletin. If no cracking is found, do repeat inspections at the interval given in Paragraph 1.E., Compliance. EFFECTIVITY All 757 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s). COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Refer to Paragraph 1.E., Compliance. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspection and/or replacement given in this service bulletin. MANPOWER Refer to Paragraph 1.G., Manpower. Elapsed Hours Total Task Hours Airplanes 5.80 (a) 10.20 (a) All Groups (a) This estimate is for inspection only.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 6 of 69 BOEING SERVICE BULLETIN 757-57-0071MATERIAL INFORMATION Operator Supplied Parts/Materials. Refer to Paragraph 2.A., Material - Price and Availability.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 7 of 69 BOEING SERVICE BULLETIN 757-57-0071Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 8 of 69 BOEING SERVICE BULLETIN 757-57-0071

BLANK PAGE

### Commercial Airplanes 

# 757 Service Bulletin SPECIAL ATTENTION Number: 757-57-0071 Original Issue: September 12, 2012 ATA System: 5750 SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Inboard Flap, Inboard Track - Forward Support Fitting Inspection and Replacement BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. 1. PLANNING INFORMATION A. Effectivity 1. Airplanes This service bulletin is for the airplanes shown below. Refer to Service Bulletin Index D624N001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data.
DESCRIPTION CONFIGURATION GROUP All 757-300 airplanes.

- 1 All 757-200, -200CB, 200PF airplanes.

- 2

Airplane Models: 757-200, 757-200CB, 757-200PF, 757-300Group Variable Number2 NA001 - NA028 2 NA191 - NA199 2 NA201 - NA239 2 NA301 - NA305 2 NA341 - NA352 2 NA391 - NA399 2 NA401 - NA408

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 9 of 69Group Variable Number2 NA441 - NA447 2 NA501 - NA586 2 NB001 - NB004 2 NB021 - NB023 2 NB036 - NB041 2 NB051 - NB053 2 NB061 - NB073 2 NB079 2 NB131 - NB148 2 NB161 - NB162 2 NB166 - NB168 2 NB201 - NB204 2 NB221 - NB228 2 NB230 2 NB236 2 NB239 2 NB261 - NB267 2 NB291 - NB299 2 NB301 - NB302 2 NB311 - NB312 2 NB321 - NB331 2 NB421 - NB438 2 NB446 2 NB451 - NB454 2 NB501 - NB523 2 NB561 2 NB571 2 NB581 - NB583 2 NC001 - NC033 2 NC041 - NC042 2 NC051 - NC052 2 NC056 - NC062 2 NC066 - NC084

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 10 of 69 BOEING SERVICE BULLETIN 757-57-0071Group Variable Number2 NC091 - NC094 2 NC151 2 NC161 2 NC901 - NC951 2 NC971 - NC974 2 ND001 - ND007 2 ND011 - ND059 2 ND111 - ND113 2 ND161 - ND199 2 ND201 - ND203 2 ND221 - ND225 2 ND241 - ND248 2 ND301 - ND322 2 ND401 2 ND891 2 ND895 2 NE001 - NE008 2 NE011 - NE088 2 NE091 - NE094 2 NE141 - NE150 2 NE161 - NE177 2 NE201 - NE204 2 NE301 - NE302 2 NE311 - NE325 2 NJ001 - NJ004 2 NJ031 - NJ032 2 NJ551 - NJ555 1 NL001 - NL002 1 NL006 - NL017 1 NL101 - NL109 1 NL141 1 NL601 - NL616 2 NN001 - NN002

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 11 of 69 BOEING SERVICE BULLETIN 757-57-0071Group Variable Number2 NN051 - NN052 2 NP901 - NP904 2 NS601 - NS616 2 NT001 - NT009 2 NT201 - NT202 2 NT231 - NT234 2 NT237 - NT240 2 NT242 2 NT245 - NT248 2 NT281 - NT289 2 NT341 - NT347 2 NT351 - NT360 2 NT371 - NT373 2 NT375 - NT379 2 NT381 - NT386 2 NT401 - NT409 2 NT411 - NT412 2 NT426 - NT427 2 NT431 - NT432 2 NT436 - NT438 2 NT441 - NT442 2 NT446 2 NT701 - NT769 2 NT791 - NT796 2 NT861 - NT862 2 NT881 - NT885 2 NT901 - NT916 2 NT971 - NT985 2 NU031 - NU038 1 NU701 - NU705 1 NU721 - NU728 1 NU731 - NU732

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 12 of 69 BOEING SERVICE BULLETIN 757-57-00712. Spares Affected None. B. Concurrent Requirements None. C. Reason This service bulletin gives instructions to inspect and if necessary replace the forward support fitting assembly at the inboard flap, inboard track. The forward support fitting assembly consists of two back-to-back machined components that attach the forward end of the inboard track of the inboard flap to the Main Landing Gear (MLG) beam. If the work in this service bulletin is not done, a broken forward support fitting could lead to loss of inboard flap control and subsequent inability to fly the airplane safely. One operator reported a broken forward support fitting assembly at the inboard flap, inboard track. During a post flight taxi, the pilots noticed a FLAP TE DISAGREE message on the Engine Indication and Crew Alerting System (EICAS). On examination, the ground maintenance personnel discovered that both components of the forward support fitting assembly had broken causing the inboard track and transmission to drop about eight inches into the wheel well. The incident occurred at 22,328 flight cycles and is the only reported incident of this type. Metallurgical analysis determined that cracks had initiated at a compound radius in each component flange common to the MLG beam. Each crack propagated by fatigue and was followed by final ductile rupture. Accomplishment of the work in this service bulletin will make sure that any cracked forward support fitting assembly at the inboard flap, inboard track is found and replaced. Boeing Service Related Problem (SRP) 757-SRP-57-0245 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 757 FTD 57-10004 is related to this service bulletin. D. Description Get access to the inboard flap, inboard track of the left wing and the right wing. Do a High Frequency Eddy Current (HFEC) inspection for cracking in the flanges of the forward support fitting assembly common to the MLG beam. If any crack is found, replace the forward support fitting assembly in accordance with this service bulletin. If no cracking is found, do repeat inspections at the interval given in Paragraph 1.E., Compliance. The work in this service bulletin is done in the maintenance zone(s) given below. Group 1:
Affected Maintenance ZonesZone Model 143, 144 757-300

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 13 of 69 BOEING SERVICE BULLETIN 757-57-0071Group 2:
Affected Maintenance ZonesZone Model 143, 144 757-200, 757-200CB, 757- 200PF E. Compliance The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Group 1: Table 1: Left Wing - Inboard Flap, Inboard Track - Forward Support Fitting Assembly Inspection and Replacement Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) Action Condition 6,000 flight cycles. (a) - Before 15,000total flight cycles.Do a High Frequency Eddy Current (HFEC) inspection for cracking in theforward support fitting assembly of the left wing inboard flap, inboard trackin accordance with Accomplishment Instructions paragraph 3.B.2.a.(1) Airplanes with less than 12,000 total flight cycles at the original issue date of this service bulletin and (1) have not replaced theforward support fitting assembly on the left wing OR(2) have replaced the forward support fitting assembly on the left wing but theforward support fitting assembly flight cycles are unknown. 6,000 flight cycles. (a) Within 36 months from the original issuedate of this service bulletin. Within 3,000 flight cycles from the original issue date ofthis service bulletin. Do a HFEC inspection for cracking in the forward support fitting assembly of the left wing inboardflap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.a.(1) Airplanes with 12,000 or more total flight cycles at the original issue date of this service bulletin and (1) have not replaced theforward support fitting assembly on the left wing OR(2) have replaced the forward support fitting assembly on the left wing but theforward support fitting assembly flight cycles are unknown.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 14 of 69 BOEING SERVICE BULLETIN 757-57-0071Group 1: Table 1: Left Wing - Inboard Flap, Inboard Track - Forward Support Fitting Assembly Inspection and Replacement Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) Action Condition 6,000 flight cycles. (a) Within 48 months from the original issuedate of this service bulletin. Within 15,000 flight cyclesfrom the replacement of the left wing forward support fitting assembly. Do a HFEC inspection for cracking in the forward support fitting assembly of the left wing inboardflap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.a.(1)Airplanes that have replaced the forward support fitting assembly on the leftwing and the forward support fitting assembly flight cycles are less than 12,000 at the original issue date of this service bulletin. 6,000 flight cycles. (a) Within 36 months from the original issuedate of this service bulletin. Within 3,000 flight cycles from the original issue date ofthis service bulletin. Do a HFEC inspection for cracking in the forward support fitting assembly of the left wing inboardflap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.a.(1)Airplanes that have replaced the forward support fitting assembly on the leftwing and the forward support fitting assembly flight cycles are 12,000 or more at the original issue date of this service bulletin. 6,000 flight cycles. (a) - Within 15,000 flight cyclesfrom the replacement of the forward support fitting assembly on the left wing. Do a HFEC inspection for cracking in the forward support fitting assembly of the left wing inboardflap, inboard track in accordance with the Accomplishment Instructions Paragraph 3.B.2.a.(1).Airplanes that have replaced the forward support fitting assembly on the leftwing as a result of any inspection accomplished by this service bulletin.

- - Before further flight.Replace the forward support fitting assembly at the left wing inboard flap,inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.a.(1)(a). Any crack found in the left wing forward support fitting assembly.

(a) Replacement of the forward support fitting assembly at the left wing inboard flap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.a.(1)(a) terminates the 6,000 flight cycle repeat inspections for the fitting that was removed. After the replacement of the forward support fitting assembly, refer to the applicable description in the Condition column for the appropriate compliance time and repeat inspections.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 15 of 69 BOEING SERVICE BULLETIN 757-57-0071Group 1: Table 2: Right Wing - Inboard Flap, Inboard Track - Forward Support Fitting Assembly Inspection and Replacement Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) Action Condition 6,000 flight cycles. (a) - Before 15,000total flight cycles.Do a High Frequency Eddy Current (HFEC) inspection for cracking in theforward support fitting assembly of the right wing inboard flap, inboard track in accordance withAccomplishment Instructions paragraph 3.B.2.a.(2). Airplanes with less than 12,000 total flight cycles at the original issue date of this service bulletin and (1) have not replaced theforward support fitting assembly on the right wing OR(2) have replaced the forward support fitting assembly on the right wing but theforward support fitting assembly flight cycles are unknown. 6,000 flight cycles. (a) Within 36 months from the original issuedate of this service bulletin. Within 3,000 flight cycles from the original issue date ofthis service bulletin. Do a HFEC inspection for cracking in the forward support fitting assembly of the right wing inboardflap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.a.(2). Airplanes with 12,000 or more total flight cycles at the original issue date of this service bulletin and (1) have not replaced theforward support fitting assembly on the right wing OR(2) have replaced the forward support fitting assembly on the right wing but theforward support fitting assembly flight cycles are unknown. 6,000 flight cycles. (a) Within 48 months from the original issuedate of this service bulletin. Within 15,000 flight cyclesfrom the replacement of the right wing forward support fitting assembly. Do a HFEC inspection for cracking in the forward support fitting assembly of the right wing inboardflap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.a.(2).Airplanes that have replaced the forward support fitting assembly on the rightwing and the forward support fitting assembly flight cycles are less than 12,000 at the original issue date of this service bulletin. 6,000 flight cycles. (a) Within 36 months from the original issuedate of this service bulletin. Within 3,000 flight cycles from the original issue date ofthis service bulletin. Do a HFEC inspection for cracking in the forward support fitting assembly of the right wing inboardflap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.a.(2).Airplanes that have replaced the forward support fitting assembly on the rightwing and the forward support fitting assembly flight cycles are 12,000 or more at the original issue date of this service bulletin.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 16 of 69 BOEING SERVICE BULLETIN 757-57-0071Group 1: Table 2: Right Wing - Inboard Flap, Inboard Track - Forward Support Fitting Assembly Inspection and Replacement Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) Action Condition 6,000 flight cycles. (a) - Within 15,000 flight cyclesfrom the replacement of the forward support fitting assembly on the right wing. Do a HFEC inspection for cracking in the forward support fitting assembly of the right wing inboardflap, inboard track in accordance with the Accomplishment Instructions Paragraph 3.B.2.a.(2).Airplanes that have replaced the forward support fitting assembly on the rightwing as a result of any inspection accomplished by this service bulletin.

- - Before further flight.Replace the forward support fitting assembly at the right wing inboardflap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.a.(2)(a). Any crack found in the right wing forward support fitting assembly.

(a) Replacement of the forward support fitting assembly at the right wing inboard flap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.a.(2)(a) terminates the 6,000 flight cycle repeat inspections for the fitting that was removed. After the replacement of the forward support fitting assembly, refer to the applicable description in the Condition column for the appropriate compliance time and repeat inspections. Group 2: Table 3: Left Wing - Inboard Flap, Inboard Track - Forward Support Fitting Assembly Inspection and Replacement Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) Action Condition 6,000 flight cycles. (a) - Before 18,000total flight cycles.Do a High Frequency Eddy Current (HFEC) inspection for cracking in theforward support fitting assembly of the left wing inboard flap, inboard trackin accordance with Accomplishment Instructions paragraph 3.B.2.b.(1) Airplanes with less than 15,000 total flight cycles at the original issue date of this service bulletin and (1) have not replaced theforward support fitting assembly on the left wing OR(2) have replaced the forward support fitting assembly on the left wing but theforward support fitting assembly flight cycles are unknown.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 17 of 69 BOEING SERVICE BULLETIN 757-57-0071Group 2: Table 3: Left Wing - Inboard Flap, Inboard Track - Forward Support Fitting Assembly Inspection and Replacement Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) Action Condition 6,000 flight cycles. (a) Within 36 months from the original issuedate of this service bulletin. Within 3,000 flight cycles from the original issue date ofthis service bulletin. Do a HFEC inspection for cracking in the forward support fitting assembly of the left wing inboardflap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.b.(1) Airplanes with 15,000 or more total flight cycles and 30,000 or less total flight cycles at the original issue date of this service bulletin and (1) have not replaced theforward support fitting assembly on the left wing OR(2) have replaced the forward support fitting assembly on the left wing but theforward support fitting assembly flight cycles are unknown. 6,000 flight cycles. (a) Within 12 months from the original issuedate of this service bulletin. Within 1,000 flight cycles from the original issue date ofthis service bulletin. Do a HFEC inspection for cracking in the forward support fitting assembly of the left wing inboardflap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.b.(1) Airplanes with more than 30,000 total flight cycles at the original issue date of this service bulletin and (1) have not replaced theforward support fitting assembly on the left wing OR(2) have replaced the forward support fitting assembly on the left wing but theforward support fitting assembly flight cycles are unknown. 6,000 flight cycles. (a) Within 48 months from the original issuedate of this service bulletin. Within 18,000 flight cyclesfrom the replacement of the left wing forward support fitting assembly. Do a HFEC inspection for cracking in the forward support fitting assembly of the left wing inboardflap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.b.(1)Airplanes that have replaced the forward support fitting assembly on the leftwing and the forward support fitting assembly flight cycles are less than 15,000 at the original issue date of this service bulletin.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 18 of 69 BOEING SERVICE BULLETIN 757-57-0071Group 2: Table 3: Left Wing - Inboard Flap, Inboard Track - Forward Support Fitting Assembly Inspection and Replacement Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) Action Condition 6,000 flight cycles. (a) Within 36 months from the original issuedate of this service bulletin. Within 3,000 flight cycles from the original issue date ofthis service bulletin. Do a HFEC inspection for cracking in the forward support fitting assembly of the left wing inboardflap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.b.(1)Airplanes that have replaced the forward support fitting assembly on the leftwing and the forward support fitting assembly flight cycles are 15,000 or more and 30,000 or less at the original issue date of this service bulletin. 6,000 flight cycles. (a) Within 12 months from the original issuedate of this service bulletin. Within 1,000 flight cycles from the original issue date ofthis service bulletin. Do a HFEC inspection for cracking in the forward support fitting assembly of the left wing inboardflap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.b.(1)Airplanes that have replaced the forward support fitting assembly on the leftwing and the forward support fitting assembly flight cycles are more than 30,000 at the original issue date of this service bulletin. 6,000 flight cycles. (a) - Within 18,000 flight cyclesfrom the replacement of the forward support fitting assembly on the left wing. Do a HFEC inspection for cracking in the forward support fitting assembly of the left wing inboardflap, inboard track in accordance with the Accomplishment Instructions Paragraph 3.B.2.b.(1).Airplanes that have replaced the forward support fitting assembly on the leftwing as a result of any inspection accomplished by this service bulletin.

- - Before further flight.Replace the forward support fitting assembly at the left wing inboard flap,inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.b.(1)(a). Any crack found in the left wing forward support fitting assembly.

(a) Replacement of the forward support fitting assembly at the left wing inboard flap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.b.(1)(a) terminates the 6,000 flight cycle repeat inspections for the fitting that was removed. After the replacement of the forward support fitting assembly, refer to the applicable description in the Condition column for the appropriate compliance time and repeat inspections.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 19 of 69 BOEING SERVICE BULLETIN 757-57-0071Group 2: Table 4: Right Wing - Inboard Flap, Inboard Track - Forward Support Fitting Assembly Inspection and Replacement Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) Action Condition 6,000 flight cycles. (a) - Before 18,000total flight cycles.Do a High Frequency Eddy Current (HFEC) inspection for cracking in theforward support fitting assembly of the right wing inboard flap, inboard track in accordance withAccomplishment Instructions paragraph 3.B.2.b.(2). Airplanes with less than 15,000 total flight cycles at the original issue date of this service bulletin and (1) have not replaced theforward support fitting assembly on the right wing OR(2) have replaced the forward support fitting assembly on the right wing but theforward support fitting assembly flight cycles are unknown. 6,000 flight cycles. (a) Within 36 months from the original issuedate of this service bulletin. Within 3,000 flight cycles from the original issue date ofthis service bulletin. Do a HFEC inspection for cracking in the forward support fitting assembly of the right wing inboardflap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.b.(2). Airplanes with 15,000 or more total flight cycles and 30,000 or less total flight cycles at the original issue date of this service bulletin and (1) have not replaced theforward support fitting assembly on the right wing OR(2) have replaced the forward support fitting assembly on the right wing but theforward support fitting assembly flight cycles are unknown. 6,000 flight cycles. (a) Within 12 months from the original issuedate of this service bulletin. Within 1,000 flight cycles from the original issue date ofthis service bulletin. Do a HFEC inspection for cracking in the forward support fitting assembly of the right wing inboardflap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.b.(2). Airplanes with more than 30,000 total flight cycles at the original issue date of this service bulletin and (1) have not replaced theforward support fitting assembly on the right wing OR(2) have replaced the forward support fitting assembly on the right wing but theforward support fitting assembly flight cycles are unknown.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 20 of 69 BOEING SERVICE BULLETIN 757-57-0071Group 2: Table 4: Right Wing - Inboard Flap, Inboard Track - Forward Support Fitting Assembly Inspection and Replacement Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) Action Condition 6,000 flight cycles. (a) Within 48 months from the original issuedate of this service bulletin. Within 18,000 flight cyclesfrom the replacement of the right wing forward support fitting assembly. Do a HFEC inspection for cracking in the forward support fitting assembly of the right wing inboardflap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.b.(2).Airplanes that have replaced the forward support fitting assembly on the rightwing and the forward support fitting assembly flight cycles are less than 15,000 at the original issue date of this service bulletin. 6,000 flight cycles. (a) Within 36 months from the original issuedate of this service bulletin. Within 3,000 flight cycles from the original issue date ofthis service bulletin. Do a HFEC inspection for cracking in the forward support fitting assembly of the right wing inboardflap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.b.(2).Airplanes that have replaced the forward support fitting assembly on the rightwing and the forward support fitting assembly flight cycles are 15,000 or more and 30,000 or less at the original issue date of this service bulletin. 6,000 flight cycles. (a) Within 12 months from the original issuedate of this service bulletin. Within 1,000 flight cycles from the original issue date ofthis service bulletin. Do a HFEC inspection for cracking in the forward support fitting assembly of the right wing inboardflap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.b.(2).Airplanes that have replaced the forward support fitting assembly on the rightwing and the forward support fitting assembly flight cycles are more than 30,000 at the original issue date of this service bulletin. 6,000 flight cycles. (a) - Within 18,000 flight cyclesfrom the replacement of the forward support fitting assembly on the right wing. Do a HFEC inspection for cracking in the forward support fitting assembly of the right wing inboardflap, inboard track in accordance with the Accomplishment Instructions Paragraph 3.B.2.b.(2).Airplanes that have replaced the forward support fitting assembly on the rightwing as a result of any inspection accomplished by this service bulletin.

- - Before further flight.Replace the forward support fitting assembly at the right wing inboardflap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.b.(2)(a). Any crack found in the right wing forward support fitting assembly.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 21 of 69 BOEING SERVICE BULLETIN 757-57-0071Group 2: Table 4: Right Wing - Inboard Flap, Inboard Track - Forward Support Fitting Assembly Inspection and Replacement Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) Action Condition(a) Replacement of the forward support fitting assembly at the right wing inboard flap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.b.(2)(a) terminates the 6,000 flight cycle repeat inspections for the fitting that was removed. After the replacement of the forward support fitting assembly, refer to the applicable description in the Condition column for the appropriate compliance time and repeat inspections. F. Approval This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. G. Manpower The table below shows an estimate of the task hours necessary to do this service bulletin for each side of the airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time: • Time to adjust to the workplace • Time to schedule the work • Time to inspect the work • Time to cure the materials • Time to make the parts • Time to find the tools. Group 1: LEFT WING Elapsed Hours Task Hours Number of Persons Task 1.10 2.20 2 Open Access and Preparation 0.70 0.70 1 FIGURE 1 2.25 2.25 1 FIGURE 3 1.10 2.20 2 Close Access and Restoration

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 22 of 69 BOEING SERVICE BULLETIN 757-57-0071Group 1: LEFT WING Elapsed Hours Task Hours Number of Persons Task 2.90 5.10 TOTAL - INSPECTION ONLY, LEFT WING 5.15 7.35 TOTAL - INSPECTION AND REPLACE- MENT, LEFT WING Group 1: RIGHT WING Elapsed Hours Task Hours Number of Persons Task 1.10 2.20 2 Open Access and Preparation 0.70 0.70 1 FIGURE 5 2.25 2.25 1 FIGURE 7 1.10 2.20 2 Close Access and Restoration 2.90 5.10 TOTAL - INSPECTION ONLY, RIGHT WING 5.15 7.35 TOTAL - INSPECTION AND REPLACE- MENT, RIGHT WING Group 2: LEFT WING Elapsed Hours Task Hours Number of Persons Task 1.10 2.20 2 Open Access and Preparation 0.70 0.70 1 FIGURE 2 2.10 2.10 1 FIGURE 4 1.10 2.20 2 Close Access and Restoration 2.90 5.10 TOTAL - INSPECTION ONLY, LEFT WING 5.00 7.20 TOTAL - INSPECTION AND REPLACE- MENT, LEFT WING Group 2: RIGHT WING Elapsed Hours Task Hours Number of Persons Task 1.10 2.20 2 Open Access and Preparation

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 23 of 69 BOEING SERVICE BULLETIN 757-57-0071Group 2: RIGHT WING Elapsed Hours Task Hours Number of Persons Task 0.70 0.70 1 FIGURE 6 2.10 2.10 1 FIGURE 8 1.10 2.20 2 Close Access and Restoration 2.90 5.10 TOTAL - INSPECTION ONLY, RIGHT WING 5.00 7.20 TOTAL - INSPECTION AND REPLACE- MENT, RIGHT WING H. Weight and Balance Changes None. I. Electrical Load Data Not changed. J. References 1. Existing Data: a. Boeing Service Related Problem (SRP) 757-SRP-57-0245. b. Service Bulletin Index D624N001. c. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-41-02, 20-43-03, 20-50-19. d. 757 Aircraft Maintenance Manual (AMM) 27-51-02, 27-51-03, 29-11-00, 32-00-15, 32-00-20. e. 757 Fleet Team Digest (FTD) 57-10004. f. 757 Non-Destructive Testing (NDT) Manual Part 6, 51-00-01, Part 6, 51-00-19. 2. Data Supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin:
Title Drawing NumberSupport Instl - Inbd Track, Inbd Main Flap 113N1201 The table above lists applicable drawings used to prepare this service bulletin. The drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. The drawings may not be applicable to all airplane configurations or operators.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 24 of 69 BOEING SERVICE BULLETIN 757-57-0071K. Publications Affected 1. Publications: None. 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin affects FCS. DTI requirements for the structure affected are contained in Paragraph 1.E., Compliance of this service bulletin. L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. M. Software Accomplishment Summary Not affected.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 25 of 69 BOEING SERVICE BULLETIN 757-57-0071Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 26 of 69 BOEING SERVICE BULLETIN 757-57-0071

BLANK PAGE2. MATERIAL INFORMATION A. Material - Price and Availability The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin does not show the Boeing price and supply data. B. Industry Support Information Boeing warranty remedies are not available for the inspection and replacement procedures given in this service bulletin. C. Parts Necessary for Each Airplane 1. Kits/Parts None. 2. Parts and Materials Supplied by the Operator Group 1:
Notes Name QTY Part Number / Speci- fication Left wing. (a) Fwd Support Fitting Assy 1 113N1242-7 Right wing. (a) Fwd Support Fitting Assy 1 113N1242-8 (b) Bolt 12 BACB30US5K19 (b) Nut 12 BACN10HR5CS (b) Washer 12 BACW10BP5APU (b) Washer 12 BACW10BP5CD (c) Chemical Conversion Coating 2 Oz TYPE 2, CLASS A (d) Primer 2 Oz BMS 10-11, TYPE I (d) Sealant 2 Oz BMS 5-95, TYPE 1, CLASS B-1/2 (d) Grease 3 Oz BMS 3-33 (a) Required only if the forward support fitting assembly is cracked. (b) Required only if the removed part is unserviceable or is different to the one required for installation in accordance with this service bulletin. (c) Refer to SOPM 20-43-03 for material sources. (d) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 27 of 69 BOEING SERVICE BULLETIN 757-57-0071Group 2:
Notes Name QTY Part Number / Speci- fication Left wing. (a) Fwd Support Fitting Assy 1 654N0244-697 Right wing. (a) Fwd Support Fitting Assy 1 654N0244-698 (b) Bolt 12 BACB30US5K19 (b) Nut 12 BACN10HR5CS (b) Washer 12 BACW10BP5APU (b) Washer 12 BACW10BP5CD (c) Chemical Conversion Coating 2 Oz TYPE 2, CLASS A (d) Primer 2 Oz BMS 10-11, TYPE I (d) Sealant 2 Oz BMS 5-95, TYPE 1, CLASS B-1/2 (d) Grease 3 Oz BMS 3-33 (a) Required only if the forward support fitting assembly is cracked. (b) Required only if the removed part is unserviceable or is different to the one required for installation in accordance with this service bulletin. (c) Refer to SOPM 20-43-03 for material sources. (d) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data.
3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None. D. Parts Necessary to Change Spares None. E. Special Tooling - Price and Availability None. F. Special Tooling Necessary to do this Service Bulletin No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 28 of 69 BOEING SERVICE BULLETIN 757-57-00713. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION CAUTION:KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. NOTE:1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch – Hole dimensions for standard solid rivets and fasteners are in Structural Repair Manual (SRM) Chapter 51 – Torque limits to tighten nuts and bolts are in SRM Chapter 51 4. Use the approved fastener and process material substitutions in accordance with SRM Chapter 51. 5. If the length of any fastener specified in this service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. 6. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. 7. Boeing Service Letter 757-SL-51-022, Damage Reporting and Repair Plan/Design Guidelines, is an acceptable procedure to request information from Boeing for additional structural repair instructions. The Service Letter describes what information must be provided to Boeing before a structural repair can be provided. 8. The instructions in Paragraph 3.B., Work Instructions and the figures can include operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing Index contain data on versions of the tools or test equipment that you can use. It is permitted to use replaced tools. It is not permitted to use superseded tools. 9. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 29 of 69 BOEING SERVICE BULLETIN 757-57-007110. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part. 11. Shaded areas in Figures are reference only. Shaded areas in Figures may look different than your airplane. B. WORK INSTRUCTIONS 1. ACCESS AND PREPARATION a. Put the flaps in the fully down position and install a DO-NOT-OPERATE tag on the flap control lever. b. Make sure the main and nose gear downlocks are installed on the nose and Main Landing Gear (MLG). Refer to 757 AMM 32-00-20 as an accepted procedure. c. Open the doors for the landing gear and install the door locks. Refer to 757 AMM 32-00-15 as an accepted procedure. d. Remove the power from the left hydraulic system. Refer to 757 AMM 29-11-00 as an accepted procedure. e. Open the following circuit breakers and install safety tags: Main Power Distribution Panel, P6
Name Number Column Row ALTN SLAT PWR C03014 20 D ALTN FLAP PWR C00323 23 D Overhead Circuit Breaker Panel, P11
Name Number Column Row WARN ELEX B C00566 18 B HYDRAULICS PTU CONT C04054 31 D FLAP LOAD RELIEF C01022 10 H FLAP/SLAT ALTN DR ARM C04212 23 H WARN ELEX A C00565 33 J f. Install a trailing edge flap power drive lock on the trailing edge flap Power Drive Unit (PDU). Refer to 757 AMM 27-51-03 as an accepted procedure. 2. FORWARD SUPPORT FITTING ASSEMBLY INSPECTION AND REPLACEMENT

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 30 of 69 BOEING SERVICE BULLETIN 757-57-0071a.Group 1: (1) Do a High Frequency Eddy Current (HFEC) inspection for cracking in the forward support fitting assembly of the left wing inboard flap, inboard track in accordance with FIGURE 1. (a) If any crack is found, do the following: 1) Support the left wing inboard flap. Refer to 757 AMM 27-51-02 as an accepted procedure. 2) Replace the forward support fitting assembly at the left wing inboard flap, inboard track in accordance with FIGURE 3. 3) Remove the support equipment from the left wing inboard flap. Refer to 757 AMM 27-51-02 as an accepted procedure. 4) Do repeat inspections at the interval given in Paragraph 1.E., Compliance. (b) If no cracking is found, do repeat inspections at the interval given in Paragraph 1.E., Compliance. (2) Do a HFEC inspection for cracking in the forward support fitting assembly of the right wing inboard flap, inboard track in accordance with FIGURE 5. (a) If any crack is found, do the following: 1) Support the right wing inboard flap. Refer to 757 AMM 27-51-02 as an accepted procedure. 2) Replace the forward support fitting assembly at the right wing inboard flap, inboard track in accordance with FIGURE 7. 3) Remove the support equipment from the right wing inboard flap. Refer to 757 AMM 27-51-02 as an accepted procedure. 4) Do repeat inspections at the interval given in Paragraph 1.E., Compliance. (b) If no cracking is found, do repeat inspections at the interval given in Paragraph 1.E., Compliance. b.Group 2: (1) Do a High Frequency Eddy Current (HFEC) inspection for cracking in the forward support fitting assembly of the left wing inboard flap, inboard track in accordance with FIGURE 2. (a) If any crack is found, do the following: 1) Support the left wing inboard flap. Refer to 757 AMM 27-51-02 as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 31 of 69 BOEING SERVICE BULLETIN 757-57-00712) Replace the forward support fitting assembly at the left wing inboard flap, inboard track in accordance with FIGURE 4. 3) Remove the support equipment from the left wing inboard flap. Refer to 757 AMM 27-51-02 as an accepted procedure. 4) Do repeat inspections at the interval given in Paragraph 1.E., Compliance. (b) If no cracking is found, do repeat inspections at the interval given in Paragraph 1.E., Compliance. (2) Do a HFEC inspection for cracking in the forward support fitting assembly of the right wing inboard flap, inboard track in accordance with FIGURE 6. (a) If any crack is found, do the following: 1) Support the right wing inboard flap. Refer to 757 AMM 27-51-02 as an accepted procedure. 2) Replace the forward support fitting assembly at the right wing inboard flap, inboard track in accordance with FIGURE 8. 3) Remove the support equipment from the right wing inboard flap. Refer to 757 AMM 27-51-02 as an accepted procedure. 4) Do repeat inspections at the interval given in Paragraph 1.E., Compliance. (b) If no cracking is found, do repeat inspections at the interval given in Paragraph 1.E., Compliance. 3. CLOSE ACCESS AND RESTORATION a. Remove the trailing edge flap power drive lock from the trailing edge flap PDU. Refer to 757 AMM 27-51-03 as an accepted procedure. b. Remove safety tags and close the following circuit breakers: Main Power Distribution Panel, P6
Name Number Column Row ALTN SLAT PWR C03014 20 D ALTN FLAP PWR C00323 23 D Overhead Circuit Breaker Panel, P11
Name Number Column Row WARN ELEX B C00566 18 B HYDRAULICS PTU CONT C04054 31 D FLAP LOAD RELIEF C01022 10 H

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 32 of 69 BOEING SERVICE BULLETIN 757-57-0071Overhead Circuit Breaker Panel, P11
Name Number Column Row FLAP/SLAT ALTN DR ARM C04212 23 H WARN ELEX A C00565 33 J c. Restore power to the left hydraulic system. Refer to 757 AMM 29-11-00 as an accepted procedure. d. Remove the door locks and close the doors for the landing gear. Refer to 757 AMM 32-00-15 as an accepted procedure. e. Remove the main and nose gear downlocks from the nose and MLG. Refer to 757 AMM 32-00-20 as an accepted procedure. f. Retract the flaps to the fully up position. g. Put the airplane back to a serviceable condition.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 33 of 69 BOEING SERVICE BULLETIN 757-57-0071This Figure applies only to: Group 1.

FIGURE 1: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY INSPECTION (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 34 of 69 BOEING SERVICE BULLETIN 757-57-0071FIGURE 1: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY INSPECTION (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 35 of 69 BOEING SERVICE BULLETIN 757-57-0071The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for one side of the airplane.
More Data Qty Identification Name Task Step (a) 1
- Fwd Support Fitting Assy Inspect 1 (a) Do a High Frequency Eddy Current (HFEC) inspection for cracking in the forward support fitting assembly in accordance with 757 NDT Part 6, 51-00-01 or 757 NDT Part 6, 51-00-19.

FIGURE 1: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY INSPECTION (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 36 of 69 BOEING SERVICE BULLETIN 757-57-0071This Figure applies only to: Group 2.

FIGURE 2: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY INSPECTION (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 37 of 69 BOEING SERVICE BULLETIN 757-57-0071FIGURE 2: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY INSPECTION (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 38 of 69 BOEING SERVICE BULLETIN 757-57-0071The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for one side of the airplane.
More Data Qty Identification Name Task Step (a) 1
- Fwd Support Fitting Assy Inspect 1 (a) Do a High Frequency Eddy Current (HFEC) inspection for cracking in the forward support fitting assembly in accordance with 757 NDT Part 6, 51-00-01 or 757 NDT Part 6, 51-00-19.

FIGURE 2: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY INSPECTION (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 39 of 69 BOEING SERVICE BULLETIN 757-57-0071This Figure applies only to: Group 1.

FIGURE 3: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 1 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 40 of 69 BOEING SERVICE BULLETIN 757-57-0071FIGURE 3: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 2 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 41 of 69 BOEING SERVICE BULLETIN 757-57-0071The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for one side of the airplane.
More Data Qty Identification Name Task Step

- 1
- Nut Remove / Keep 1

- 1
- Bolt Remove / Keep

- 1
- Washer Remove / Keep

- 2
- Bolt Retainer Remove / Keep

- 1
- Nut Remove / Keep 2

- 1
- Bolt Remove / Keep

- 2
- Washer Remove / Keep

- 1 BACB28AK08-064 Bushing Remove / Keep 3

- 6
- Bolt Remove / Keep 4

- 6
- Nut Remove / Keep

- 12
- Washer Remove / Keep

- 1
- Fwd Support Fitting As- sy Remove 5 (a) 5
- Hole Inspect 6 (b) 1
- Hole Inspect 7 (c) (d) 5
- Hole Drill / Ream 8 (c) (e) 1
- Hole Drill / Ream 9 (f)

- - Main Landing Gear Beam Clean 10 (g)

- BMS 5-95, TYPE 1, CLASS B-1/2 Sealant Apply 11

- 1 113N1242-7 Fwd Support Fitting As- sy Install (New) 12 (h) Refer to the fastener table. 5
- Fastener Install (New) 13
Refer to the fastener table. 5
- Nut Torque 14 (i)

- BMS 5-95, TYPE 1, CLASS B-1/2 Sealant Apply (h) Refer to the fastener table. 1
- Fastener Install (New) 15

FIGURE 3: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 3 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 42 of 69 BOEING SERVICE BULLETIN 757-57-0071More Data Qty Identification Name Task Step Refer to the fastener table. 1
- Nut Torque 16 (i)

- BMS 5-95, TYPE 1, CLASS B-1/2 Sealant Apply (j) 1 BACB28AK08-064 Bushing Install (Kept) 17 (k) 1
- Bolt Install (Kept) 18 One under the bolt head and one under the nut. 2
- Washer Install (Kept)

Finger tight. 1
- Nut Install (Kept) Torque the nut to 375 - 450 in-lb. 1
- Nut Torque 19

- 2
- Bolt Retainer Install (Kept) 20

- 1
- Bolt Install (Kept)

- 1
- Washer Install (Kept)

- 1
- Nut Install (Kept) (a) Inspect the holes in the main landing gear beam to make sure that they are round and undamaged. Forany hole which is distorted or damaged, ream that hole in 1/64 inch increments until it is round and undamaged. Maximum diameter is 0.354 inches. Minimum edge margin is 0.530 (b) Inspect the holes in the main landing gear beam to make sure that they are round and undamaged. Forany hole which is distorted or damaged, ream that hole in 1/64 inch increments until it is round and undamaged. Maximum diameter is 0.316 inches. Minimum edge margin is 0.530 inches (c) Locate and hold the new forward support fitting assembly where the old one was located. (d) Match-drill holes in the forward support fitting assembly through the existing holes in the Main Landing Gear (MLG) beam. Maximum hole diameter is 0.354 inches. Minimum edge margin in forward support fitting assembly is 0.470 inches. Break sharp edges. (e) Match-drill hole in the forward support fitting assembly through the existing hole in the MLG beam. Maximum hole diameter is 0.316 inches. Minimum edge margin in forward support fitting assembly is 0.470 inches. Break sharp edges. (f) Clean the mating surface of the MLG beam. Refer to SOPM 20-30-03 as an accepted procedure. (g) Apply a fay seal to the mating surfaces of the forward support fitting and the MLG beam. Refer to SOPM 20-50-19 as an accepted procedure. (h) Install wet with BMS 5-95, Type 1, Class B-1/2 sealant. Refer to SOPM 20-50-19 as an accepted procedure. (i) Fillet seal the nuts with BMS 5-95, Type 1, Class B-1/2 sealant. Refer to SOPM 20-50-19 as an accepted procedure. (j) Install the bushing with BMS 3-33 grease. Apply the grease on the outside diameter and inside diameter of the bushing.

FIGURE 3: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 4 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 43 of 69 BOEING SERVICE BULLETIN 757-57-0071More Data Qty Identification Name Task Step (k) Install the bolt with BMS 3-33 grease. Apply the grease on the outside diameter of the bolt. Remove excess grease from the threads prior to nut installation.

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure.
More Data Hole Dia Qty Identification Name Code (a) (b) 0.250 - 0.254 1 BACB30US4K19 Bolt A (a) Torque the nut to 90 - 125 in-lb. - 1 BACN10HR4CS Nut (a) Install under the nut.

- 1 BACW10BP4APU Washer (a) Install under the bolt head. - 1 BACW10BP4CD Washer (a) (c) 0.312 - 0.316 1 BACB30US5K19 Bolt A (Optional) (a) Torque the nut to 180 - 250 in-lb. - 1 BACN10HR5CS Nut (a) Install under the nut.

- 1 BACW10BP5APU Washer (a) Install under the bolt head. - 1 BACW10BP5CD Washer

FIGURE 3: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 5 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 44 of 69 BOEING SERVICE BULLETIN 757-57-0071More Data Hole Dia Qty Identification Name Code (a) (b) 0.279 - .291 5 BACB30US4K19 Bolt B (a) Torque the nut to 90 - 125 in-lb. - 5 BACN10HR4CS Nut (a) Install under the nut.

- 5 BACW10BP4APU Washer (a) Install under the bolt head. - 5 BACW10BP4CD Washer (a) (c) 0.342 - 0.354 5 BACB30US5K19 Bolt B (Optional) (a) Torque the nut to 180 - 250 in-lb. - 5 BACN10HR5CS Nut (a) Install under the nut.

- 5 BACW10BP5APU Washer (a) Install under the bolt head. - 5 BACW10BP5CD Washer (a) It is acceptable to install serviceable parts that were previously removed if they meet the requirements in this table. (b) For the hole sizes that are between the final diameter shown, ream to the appropriate oversize hole as required. Refer to 757-300 SRM 51-40-05 as an accepted procedure. Use oversize bolt BACB30US4K19X or BACB30US4K19Y as required. (c) For the hole sizes that are between the final diameter shown, ream to the appropriate oversize hole as required. Refer to 757-300 SRM 51-40-05 as an accepted procedure. Use oversize bolt BACB30US5K19X or BACB30US5K19Y as required.

FIGURE 3: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 6 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 45 of 69 BOEING SERVICE BULLETIN 757-57-0071This Figure applies only to: Group 2.

FIGURE 4: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 1 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 46 of 69 BOEING SERVICE BULLETIN 757-57-0071FIGURE 4: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 2 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 47 of 69 BOEING SERVICE BULLETIN 757-57-0071The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for one side of the airplane.
More Data Qty Identification Name Task Step

- 1
- Nut Remove / Keep 1

- 1
- Bolt Remove / Keep

- 1
- Washer Remove / Keep

- 2
- Bolt Retainer Remove / Keep

- 1
- Nut Remove / Keep 2

- 1
- Bolt Remove / Keep

- 2
- Washer Remove / Keep

- 1 BACB28AK08-064 Bushing Remove / Keep 3

- 6
- Bolt Remove / Keep 4

- 6
- Nut Remove / Keep

- 12
- Washer Remove / Keep

- 1
- Fwd Support Fitting As- sy Remove 5 (a) 5
- Hole Inspect 6 (b) 1
- Hole Inspect 7 (c) (d) 5
- Hole Drill / Ream 8 (c) (e) 1
- Hole Drill / Ream 9 (f)

- - Main Landing Gear Beam Clean 10 (g)

- BMS 5-95, TYPE 1, CLASS B-1/2 Sealant Apply 11

- 1 654N0244-697 Fwd Support Fitting As- sy Install (New) 12 (h) Refer to the fastener table. 5
- Fastener Install (New) 13
Refer to the fastener table. 5
- Nut Torque 14 (i)

- BMS 5-95, TYPE 1, CLASS B-1/2 Sealant Apply (h) Refer to the fastener table. 1
- Fastener Install (New) 15

FIGURE 4: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 3 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 48 of 69 BOEING SERVICE BULLETIN 757-57-0071More Data Qty Identification Name Task Step Refer to the fastener table. 1
- Nut Torque 16 (i)

- BMS 5-95, TYPE 1, CLASS B-1/2 Sealant Apply (j) 1 BACB28AK08-064 Bushing Install (Kept) 17 (k) 1
- Bolt Install (Kept) 18 One under the bolt head and one under the nut. 2
- Washer Install (Kept)

Finger tight. 1
- Nut Install (Kept) Torque the nut to 375 - 450 in-lb. 1
- Nut Torque 19

- 2
- Bolt Retainer Install (Kept) 20

- 1
- Bolt Install (Kept)

- 1
- Washer Install (Kept)

- 1
- Nut Install (Kept) (a) Inspect the holes in the main landing gear beam to make sure that they are round and undamaged. Forany hole which is distorted or damaged, ream that hole in 1/64 inch increments until it is round and undamaged. Maximum diameter is 0.354 inches. Minimum edge margin is 0.530 (b) Inspect the holes in the main landing gear beam to make sure that they are round and undamaged. Forany hole which is distorted or damaged, ream that hole in 1/64 inch increments until it is round and undamaged. Maximum diameter is 0.316 inches. Minimum edge margin is 0.530 inches (c) Locate and hold the new forward support fitting assembly where the old one was located. (d) Match-drill holes in the forward support fitting assembly through the existing holes in the Main Landing Gear (MLG) beam. Maximum hole diameter is 0.354 inches. Minimum edge margin in forward support fitting assembly is 0.470 inches. Break sharp edges. (e) Match-drill hole in the forward support fitting assembly through the existing hole in the MLG beam. Maximum hole diameter is 0.316 inches. Minimum edge margin in forward support fitting assembly is 0.470 inches. Break sharp edges. (f) Clean the mating surface of the MLG beam. Refer to SOPM 20-30-03 as an accepted procedure. (g) Apply a fay seal to the mating surfaces of the forward support fitting and the MLG beam. Refer to SOPM 20-50-19 as an accepted procedure. (h) Install wet with BMS 5-95, Type 1, Class B-1/2 sealant. Refer to SOPM 20-50-19 as an accepted procedure. (i) Fillet seal the nuts with BMS 5-95, Type 1, Class B-1/2 sealant. Refer to SOPM 20-50-19 as an accepted procedure. (j) Install the bushing with BMS 3-33 grease. Apply the grease on the outside diameter and inside diameter of the bushing.

FIGURE 4: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 4 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 49 of 69 BOEING SERVICE BULLETIN 757-57-0071More Data Qty Identification Name Task Step (k) Install the bolt with BMS 3-33 grease. Apply the grease on the outside diameter of the bolt. Remove excess grease from the threads prior to nut installation.

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure.
More Data Hole Dia Qty Identification Name Code (a) (b) 0.250 - 0.254 1 BACB30US4K19 Bolt A (a) Torque the nut to 90 - 125 in-lb. - 1 BACN10HR4CS Nut (a) Install under the nut.

- 1 BACW10BP4APU Washer (a) Install under the bolt head. - 1 BACW10BP4CD Washer (a) (c) 0.312 - 0.316 1 BACB30US5K19 Bolt A (Optional) (a) Torque the nut to 180 - 250 in-lb. - 1 BACN10HR5CS Nut (a) Install under the nut.

- 1 BACW10BP5APU Washer (a) Install under the bolt head. - 1 BACW10BP5CD Washer

FIGURE 4: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 5 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 50 of 69 BOEING SERVICE BULLETIN 757-57-0071More Data Hole Dia Qty Identification Name Code (a) (b) 0.279 - .291 5 BACB30US4K19 Bolt B (a) Torque the nut to 90 - 125 in-lb. - 5 BACN10HR4CS Nut (a) Install under the nut.

- 5 BACW10BP4APU Washer (a) Install under the bolt head. - 5 BACW10BP4CD Washer (a) (c) 0.342 - 0.354 5 BACB30US5K19 Bolt B (Optional) (a) Torque the nut to 180 - 250 in-lb. - 5 BACN10HR5CS Nut (a) Install under the nut.

- 5 BACW10BP5APU Washer (a) Install under the bolt head. - 5 BACW10BP5CD Washer (a) It is acceptable to install serviceable parts that were previously removed if they meet the requirements in this table. (b) For the hole sizes that are between the final diameter shown, ream to the appropriate oversize hole as required. Refer to 757-300 SRM 51-40-05 as an accepted procedure. Use oversize bolt BACB30US4K19X or BACB30US4K19Y as required. (c) For the hole sizes that are between the final diameter shown, ream to the appropriate oversize hole as required. Refer to 757-300 SRM 51-40-05 as an accepted procedure. Use oversize bolt BACB30US5K19X or BACB30US5K19Y as required.

FIGURE 4: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 6 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 51 of 69 BOEING SERVICE BULLETIN 757-57-0071This Figure applies only to: Group 1.

FIGURE 5: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY INSPECTION (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 52 of 69 BOEING SERVICE BULLETIN 757-57-0071FIGURE 5: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY INSPECTION (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 53 of 69 BOEING SERVICE BULLETIN 757-57-0071The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for one side of the airplane.
More Data Qty Identification Name Task Step (a) 1
- Fwd Support Fitting Assy Inspect 1 (a) Do a High Frequency Eddy Current (HFEC) inspection for cracking in the forward support fitting assembly in accordance with 757 NDT Part 6, 51-00-01 or 757 NDT Part 6, 51-00-19.

FIGURE 5: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY INSPECTION (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 54 of 69 BOEING SERVICE BULLETIN 757-57-0071This Figure applies only to: Group 2.

FIGURE 6: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY INSPECTION (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 55 of 69 BOEING SERVICE BULLETIN 757-57-0071FIGURE 6: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY INSPECTION (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 56 of 69 BOEING SERVICE BULLETIN 757-57-0071The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for one side of the airplane.
More Data Qty Identification Name Task Step (a) 1
- Fwd Support Fitting Assy Inspect 1 (a) Do a High Frequency Eddy Current (HFEC) inspection for cracking in the forward support fitting assembly in accordance with 757 NDT Part 6, 51-00-01 or 757 NDT Part 6, 51-00-19.

FIGURE 6: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY INSPECTION (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 57 of 69 BOEING SERVICE BULLETIN 757-57-0071This Figure applies only to: Group 1.

FIGURE 7: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 1 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 58 of 69 BOEING SERVICE BULLETIN 757-57-0071FIGURE 7: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 2 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 59 of 69 BOEING SERVICE BULLETIN 757-57-0071The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for one side of the airplane.
More Data Qty Identification Name Task Step

- 1
- Nut Remove / Keep 1

- 1
- Bolt Remove / Keep

- 1
- Washer Remove / Keep

- 2
- Bolt Retainer Remove / Keep

- 1
- Nut Remove / Keep 2

- 1
- Bolt Remove / Keep

- 2
- Washer Remove / Keep

- 1 BACB28AK08-064 Bushing Remove / Keep 3

- 6
- Bolt Remove / Keep 4

- 6
- Nut Remove / Keep

- 12
- Washer Remove / Keep

- 1
- Fwd Support Fitting As- sy Remove 5 (a) 5
- Hole Inspect 6 (b) 1
- Hole Inspect 7 (c) (d) 5
- Hole Drill / Ream 8 (c) (e) 1
- Hole Drill / Ream 9 (f)

- - Main Landing Gear Beam Clean 10 (g)

- BMS 5-95, TYPE 1, CLASS B-1/2 Sealant Apply 11

- 1 113N1242-8 Fwd Support Fitting As- sy Install (New) 12 (h) Refer to the fastener table. 5
- Fastener Install (New) 13
Refer to the fastener table. 5
- Nut Torque 14 (i)

- BMS 5-95, TYPE 1, CLASS B-1/2 Sealant Apply (h) Refer to the fastener table. 1
- Fastener Install (New) 15

FIGURE 7: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 3 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 60 of 69 BOEING SERVICE BULLETIN 757-57-0071More Data Qty Identification Name Task Step Refer to the fastener table. 1
- Nut Torque 16 (i)

- BMS 5-95, TYPE 1, CLASS B-1/2 Sealant Apply (j) 1 BACB28AK08-064 Bushing Install (Kept) 17 (k) 1
- Bolt Install (Kept) 18 One under the bolt head and one under the nut. 2
- Washer Install (Kept)

Finger tight. 1
- Nut Install (Kept) Torque the nut to 375 - 450 in-lb. 1
- Nut Torque 19

- 2
- Bolt Retainer Install (Kept) 20

- 1
- Bolt Install (Kept)

- 1
- Washer Install (Kept)

- 1
- Nut Install (Kept) (a) Inspect the holes in the main landing gear beam to make sure that they are round and undamaged. Forany hole which is distorted or damaged, ream that hole in 1/64 inch increments until it is round and undamaged. Maximum diameter is 0.354 inches. Minimum edge margin is 0.530 (b) Inspect the holes in the main landing gear beam to make sure that they are round and undamaged. Forany hole which is distorted or damaged, ream that hole in 1/64 inch increments until it is round and undamaged. Maximum diameter is 0.316 inches. Minimum edge margin is 0.530 inches (c) Locate and hold the new forward support fitting assembly where the old one was located. (d) Match-drill holes in the forward support fitting assembly through the existing holes in the Main Landing Gear (MLG) beam. Maximum hole diameter is 0.354 inches. Minimum edge margin in forward support fitting assembly is 0.470 inches. Break sharp edges. (e) Match-drill hole in the forward support fitting assembly through the existing hole in the MLG beam. Maximum hole diameter is 0.316 inches. Minimum edge margin in forward support fitting assembly is 0.470 inches. Break sharp edges. (f) Clean the mating surface of the MLG beam. Refer to SOPM 20-30-03 as an accepted procedure. (g) Apply a fay seal to the mating surfaces of the forward support fitting and the MLG beam. Refer to SOPM 20-50-19 as an accepted procedure. (h) Install wet with BMS 5-95, Type 1, Class B-1/2 sealant. Refer to SOPM 20-50-19 as an accepted procedure. (i) Fillet seal the nuts with BMS 5-95, Type 1, Class B-1/2 sealant. Refer to SOPM 20-50-19 as an accepted procedure. (j) Install the bushing with BMS 3-33 grease. Apply the grease on the outside diameter and inside diameter of the bushing.

FIGURE 7: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 4 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 61 of 69 BOEING SERVICE BULLETIN 757-57-0071More Data Qty Identification Name Task Step (k) Install the bolt with BMS 3-33 grease. Apply the grease on the outside diameter of the bolt. Remove excess grease from the threads prior to nut installation.

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure.
More Data Hole Dia Qty Identification Name Code (a) (b) 0.250 - 0.254 1 BACB30US4K19 Bolt A (a) Torque the nut to 90 - 125 in-lb. - 1 BACN10HR4CS Nut (a) Install under the nut.

- 1 BACW10BP4APU Washer (a) Install under the bolt head. - 1 BACW10BP4CD Washer (a) (c) 0.312 - 0.316 1 BACB30US5K19 Bolt A (Optional) (a) Torque the nut to 180 - 250 in-lb. - 1 BACN10HR5CS Nut (a) Install under the nut.

- 1 BACW10BP5APU Washer (a) Install under the bolt head. - 1 BACW10BP5CD Washer

FIGURE 7: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 5 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 62 of 69 BOEING SERVICE BULLETIN 757-57-0071More Data Hole Dia Qty Identification Name Code (a) (b) 0.279 - .291 5 BACB30US4K19 Bolt B (a) Torque the nut to 90 - 125 in-lb. - 5 BACN10HR4CS Nut (a) Install under the nut.

- 5 BACW10BP4APU Washer (a) Install under the bolt head. - 5 BACW10BP4CD Washer (a) (c) 0.342 - 0.354 5 BACB30US5K19 Bolt B (Optional) (a) Torque the nut to 180 - 250 in-lb. - 5 BACN10HR5CS Nut (a) Install under the nut.

- 5 BACW10BP5APU Washer (a) Install under the bolt head. - 5 BACW10BP5CD Washer (a) It is acceptable to install serviceable parts that were previously removed if they meet the requirements in this table. (b) For the hole sizes that are between the final diameter shown, ream to the appropriate oversize hole as required. Refer to 757-300 SRM 51-40-05 as an accepted procedure. Use oversize bolt BACB30US4K19X or BACB30US4K19Y as required. (c) For the hole sizes that are between the final diameter shown, ream to the appropriate oversize hole as required. Refer to 757-300 SRM 51-40-05 as an accepted procedure. Use oversize bolt BACB30US5K19X or BACB30US5K19Y as required.

FIGURE 7: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 6 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 63 of 69 BOEING SERVICE BULLETIN 757-57-0071This Figure applies only to: Group 2.

FIGURE 8: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 1 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 64 of 69 BOEING SERVICE BULLETIN 757-57-0071FIGURE 8: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 2 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 65 of 69 BOEING SERVICE BULLETIN 757-57-0071The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for one side of the airplane.
More Data Qty Identification Name Task Step

- 1
- Nut Remove / Keep 1

- 1
- Bolt Remove / Keep

- 1
- Washer Remove / Keep

- 2
- Bolt Retainer Remove / Keep

- 1
- Nut Remove / Keep 2

- 1
- Bolt Remove / Keep

- 2
- Washer Remove / Keep

- 1 BACB28AK08-064 Bushing Remove / Keep 3

- 6
- Bolt Remove / Keep 4

- 6
- Nut Remove / Keep

- 12
- Washer Remove / Keep

- 1
- Fwd Support Fitting As- sy Remove 5 (a) 5
- Hole Inspect 6 (b) 1
- Hole Inspect 7 (c) (d) 5
- Hole Drill / Ream 8 (c) (e) 1
- Hole Drill / Ream 9 (f)

- - Main Landing Gear Beam Clean 10 (g)

- BMS 5-95, TYPE 1, CLASS B-1/2 Sealant Apply 11

- 1 654N0244-698 Fwd Support Fitting As- sy Install (New) 12 (h) Refer to the fastener table. 5
- Fastener Install (New) 13
Refer to the fastener table. 5
- Nut Torque 14 (i)

- BMS 5-95, TYPE 1, CLASS B-1/2 Sealant Apply (h) Refer to the fastener table. 1
- Fastener Install (New) 15

FIGURE 8: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 3 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 66 of 69 BOEING SERVICE BULLETIN 757-57-0071More Data Qty Identification Name Task Step Refer to the fastener table. 1
- Nut Torque 16 (i)

- BMS 5-95, TYPE 1, CLASS B-1/2 Sealant Apply (j) 1 BACB28AK08-064 Bushing Install (Kept) 17 (k) 1
- Bolt Install (Kept) 18 One under the bolt head and one under the nut. 2
- Washer Install (Kept)

Finger tight. 1
- Nut Install (Kept) Torque the nut to 375 - 450 in-lb. 1
- Nut Torque 19

- 2
- Bolt Retainer Install (Kept) 20

- 1
- Bolt Install (Kept)

- 1
- Washer Install (Kept)

- 1
- Nut Install (Kept) (a) Inspect the holes in the main landing gear beam to make sure that they are round and undamaged. Forany hole which is distorted or damaged, ream that hole in 1/64 inch increments until it is round and undamaged. Maximum diameter is 0.354 inches. Minimum edge margin is 0.530 (b) Inspect the holes in the main landing gear beam to make sure that they are round and undamaged. Forany hole which is distorted or damaged, ream that hole in 1/64 inch increments until it is round and undamaged. Maximum diameter is 0.316 inches. Minimum edge margin is 0.530 inches (c) Locate and hold the new forward support fitting assembly where the old one was located. (d) Match-drill holes in the forward support fitting assembly through the existing holes in the Main Landing Gear (MLG) beam. Maximum hole diameter is 0.354 inches. Minimum edge margin in forward support fitting assembly is 0.470 inches. Break sharp edges. (e) Match-drill hole in the forward support fitting assembly through the existing hole in the MLG beam. Maximum hole diameter is 0.316 inches. Minimum edge margin in forward support fitting assembly is 0.470 inches. Break sharp edges. (f) Clean the mating surface of the MLG beam. Refer to SOPM 20-30-03 as an accepted procedure. (g) Apply a fay seal to the mating surfaces of the forward support fitting and the MLG beam. Refer to SOPM 20-50-19 as an accepted procedure. (h) Install wet with BMS 5-95, Type 1, Class B-1/2 sealant. Refer to SOPM 20-50-19 as an accepted procedure. (i) Fillet seal the nuts with BMS 5-95, Type 1, Class B-1/2 sealant. Refer to SOPM 20-50-19 as an accepted procedure. (j) Install the bushing with BMS 3-33 grease. Apply the grease on the outside diameter and inside diameter of the bushing.

FIGURE 8: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 4 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 67 of 69 BOEING SERVICE BULLETIN 757-57-0071More Data Qty Identification Name Task Step (k) Install the bolt with BMS 3-33 grease. Apply the grease on the outside diameter of the bolt. Remove excess grease from the threads prior to nut installation.

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure.
More Data Hole Dia Qty Identification Name Code (a) (b) 0.250 - 0.254 1 BACB30US4K19 Bolt A (a) Torque the nut to 90 - 125 in-lb. - 1 BACN10HR4CS Nut (a) Install under the nut.

- 1 BACW10BP4APU Washer (a) Install under the bolt head. - 1 BACW10BP4CD Washer (a) (c) 0.312 - 0.316 1 BACB30US5K19 Bolt A (Optional) (a) Torque the nut to 180 - 250 in-lb. - 1 BACN10HR5CS Nut (a) Install under the nut.

- 1 BACW10BP5APU Washer (a) Install under the bolt head. - 1 BACW10BP5CD Washer

FIGURE 8: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 5 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 68 of 69 BOEING SERVICE BULLETIN 757-57-0071More Data Hole Dia Qty Identification Name Code (a) (b) 0.279 - .291 5 BACB30US4K19 Bolt B (a) Torque the nut to 90 - 125 in-lb. - 5 BACN10HR4CS Nut (a) Install under the nut.

- 5 BACW10BP4APU Washer (a) Install under the bolt head. - 5 BACW10BP4CD Washer (a) (c) 0.342 - 0.354 5 BACB30US5K19 Bolt B (Optional) (a) Torque the nut to 180 - 250 in-lb. - 5 BACN10HR5CS Nut (a) Install under the nut.

- 5 BACW10BP5APU Washer (a) Install under the bolt head. - 5 BACW10BP5CD Washer (a) It is acceptable to install serviceable parts that were previously removed if they meet the requirements in this table. (b) For the hole sizes that are between the final diameter shown, ream to the appropriate oversize hole as required. Refer to 757-300 SRM 51-40-05 as an accepted procedure. Use oversize bolt BACB30US4K19X or BACB30US4K19Y as required. (c) For the hole sizes that are between the final diameter shown, ream to the appropriate oversize hole as required. Refer to 757-300 SRM 51-40-05 as an accepted procedure. Use oversize bolt BACB30US5K19X or BACB30US5K19Y as required.

FIGURE 8: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY REPLACEMENT (SHEET 6 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2012 757-57-0071 69 of 69 BOEING SERVICE BULLETIN 757-57-0071