### Commercial **Airplanes** 

# 777 Service Bulletin **ALERT Number: 777-53A0068**  Original Issue: June 12, 2013 ATA System: 5345 5365 2315 **SUBJECT:** FUSELAGE - Sections 44 and 46 - Crown Skin Panel - Corrosion and Crack on Fuselage Skin Below SATCOM Antenna Adapter Plate - Inspection 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 © 2013 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 Unpublished Work.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, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, 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.

Original Issue: June 12, 2013 777-53A0068 1 of 76 6.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 2 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Effectivity. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 42 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 43 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 43 M. Software Accomplishment Summary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 C. Parts Necessary for Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 45 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 45 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48 FIGURE 1: SECTION 46 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - MARK AND LOCATE FASTENER COMMON TO BONDING JUMPER AND ADAPTER PLATE [Group 1-2] . . . 53 FIGURE 2: SECTION 46 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - INTERNAL INSPECTION [Group 1-2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55 FIGURE 3: SECTION 46 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - EXTERNAL INSPECTION [Group 1-2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 58 FIGURE 4: SECTION 44 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - MARK AND LOCATE FASTENER COMMON TO BONDING JUMPER AND ADAPTER PLATE [Group 2]. . . . 61 FIGURE 5: SECTION 44 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - INTERNAL INSPECTION [Group 2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 63 FIGURE 6: SECTION 44 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - EXTERNAL INSPECTION [Group 2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 3 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**FIGURE 7: SECTION 46 - 2-BAY SATCOM ANTENNA - FUSELAGE SKIN - MARK AND LOCATE FASTENER COMMON TO BONDING JUMPER AND ADAPTER PLATE [Group 3-4; Group 5, Configuration 3-4]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 69 FIGURE 8: SECTION 46 - 2-BAY SATCOM ANTENNA - FUSELAGE SKIN - INTERNAL INSPECTION [Group 3-4; Group 5, Configuration 3-4]. . . . . . . . . . . . . . . . . . . . . . . . . . . . 71 FIGURE 9: SECTION 46 - 2-BAY SATCOM ANTENNA - FUSELAGE SKIN - EXTERNAL INSPECTION [Group 3-4; Group 5, Configuration 3-4]. . . . . . . . . . . . . . . . . . . . . . . . . . . . 74

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 4 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**

### Commercial **Airplanes** 

# 777 Service Bulletin **ALERT Summary**  **Number: 777-53A0068** Original Issue: June 12, 2013 ATA System: 5345 5365 2315 **SUBJECT:** FUSELAGE - Sections 44 and 46 - Crown Skin Panel - Corrosion and Crack on Fuselage Skin Below SATCOM Antenna Adapter Plate - Inspection
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. **CONCURRENT REQUIREMENTS**
None. **BACKGROUND** This service bulletin gives instructions to inspect for corrosion and cracks in the crown fuselage skin under 2-bay and 3-bay satellite communication (SATCOM) antenna adapter plates located in Sections 44 and 46. There could be fretting and damage to the fuselage skin finish due to a contact between the adapter plate bonding jumper and fuselage skin. Removal of finish in the fuselage skin results in exposure to corrosion, which can lead to cracks. Cracks in the fuselage skin that are not found and repaired can propagate to the point where the fuselage skin structure cannot sustain limit load. When the fuselage skin cannot sustain limit load, this can results in possible rapid decompression and loss of structural integrity. One operator reported a 16 inch crack under the 3-bay SATCOM antenna adapter plate in the crown skin of the fuselage between STA 1601 and STA 1622 (Section 46), and S-1L and S-2L on an airplane that was 14 years old with approximately 14,000 total flight cycles. This crack was found while doing Maintenance Planning Data (MPD) inspection, 777 MPD Section 2, 53-598-00, which requires fuselage skin inspection between STA 1434 and STA 1832. As a part of the MPD inspection, removal of antennas and adapter plates are necessary to access the entire fuselage skin. Subsequent to this crack finding, the same operator inspected 42 other airplanes that are between 6 and 16 years old and found some local corrosion, but no other cracking. Boeing has performed metallurgical fracture analysis of the section of the fuselage skin with the 16 inch crack, which was sent in by the operator. The damaged fuselage skin showed that the braided section of the bonding jumper cable was contacting the skin. The contact between the bonding jumper and fuselage skin results in fretting and removal of the fuselage skin finish. The removal of finish results in exposure to corrosion. The damaged skin panel showed severe exfoliation corrosion in the area where the braided section of the bonding jumper contacted the skin. The fracture analysis showed that primary crack initiated at the area of the exfoliation corrosion. The analysis also showed that cracking progressed by intergranular stress corrosion partially through thickness for 13.5 inches along the interior surface of the skin. Further propagation of the crack through to the exterior surface occurred by fatigue.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 5 of 76In addition, Boeing has performed an analysis of SATCOM antenna installations. The installation drawing for 3-bay SATCOM antenna in Section 46 show no clearance between the fuselage skin and the fastener attaching the SATCOM lug adapter plate to the bonding jumper. Due to the lack of clearance, the fastener may come in contact with the fuselage skin. Furthermore, the fastener is located between stringers where the fastener can have a contact with the fuselage due to pillowing out effect when the fuselage is pressurized. The fastener contact with the fuselage skin results in fretting that causes removal of the fuselage skin finish, which results in exposure to corrosion. Boeing has also determined that there are 2-bay and 3-bay SATCOM antennas that are installed at two locations. The "2-bay" and "3-bay" terminologies are used to describe the length of the antenna in terms of frame bays. The 2-bay SATCOM antennas are 2 frame bays long and are installed in Section 46. The 3-bay SATCOM antennas are 3 frame bays long and are installed in Section 44 or Section 46, or both. Airplanes can be delivered with either 2-bay or 3-bay SATCOM antenna in Section 46 as a primary option. If a SATCOM antenna is installed in Section 46, additional 3-bay SATCOM antenna in Section 44 can be installed as a dual option. The analysis showed that both 2-bay and 3-bay SATCOM antennas in Sections 44 and 46 can have similar issues related to bonding jumper and the fastener contacting the skin that results in fretting and removal of fuselage skin finish. The fretting and presence of corrosion are factors that can lead to fuselage skin cracking. This service bulletin gives instructions to inspect for corrosion and cracks in the crown fuselage skin under 2-bay and 3-bay SATCOM antenna adapter plates located in Sections 44 and 46 of the airplane. Boeing Service Related Problem (SRP) 777-SRP-53-0418 is related to this service bulletin. A future service bulletin will be issued to give a terminating action for the continued inspections given in this service bulletin.
**NOTE:** There has been a production change to the bonding jumper installation for 3-bay SATCOM antennas in Section 44 at line number 1068 and on, and in Section 46 at line number 1077 and on. There has not been a production change to the bonding jumper installation for 2-bay SATCOM antennas. Boeing Fleet Team Digest (FTD) 777 FTD 53-12001 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 Paragraph 1.E., Compliance and Paragraph 1.F., Approval Yes 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 No Operator Supplied Material

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 6 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Reference**  **Affected Planning Data**  Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin No Special Tooling Required

**ACTION Group 5, Configuration 1-2, 5:**  No action is necessary in accordance with this service bulletin. **Group 1-4; Group 5, Configuration 3-4:** Get internal and external access to SATCOM antenna(s). Do repetitive internal and external detailed and surface high frequency eddy current (HFEC) inspections of the visible fuselage skin and doubler, if installed. If any corrosion or crack is found, do a repair in accordance with 777 SRM or contact Boeing for repair instructions and do the repair. If an indication is found that shows a contact of the fastener attaching the SATCOM lug adapter plate to the bonding jumper, contact Boeing for repair instructions and do the repair. After the repair, repeat the inspections in accordance with this service bulletin. Put the airplane back to a serviceable condition. **EFFECTIVITY** 777-200, 777-200LR, 777-300, 777-300ER, and 777F 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. **Group 5, Configuration 1-2, 5:** None. No action is necessary in accordance with this service bulletin. **Group 1-4; Group 5, Configuration 3-4:** Refer to Paragraph 1.E., Compliance. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are available for airplanes in warranty as of June 25, 2012. Please refer to Paragraph 2.B., Industry Support Information. The warranty remedies will expire eight years from the original issue date of this service bulletin. **MANPOWER Group 5, Configuration 1-2, 5:**  None. No action is necessary in accordance with this service bulletin.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 7 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 1:**  **Elapsed Hours Total Task Hours**  **Airplanes** 13.40 17.60 Group 1: Section 46 - 3- Bay SATCOMAntenna - Fuselage Skin Inspection **Group 2: Elapsed Hours**  **Total Task Hours Airplanes**  26.80 35.20 Group 2: Sections 44 and46 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection **Group 3-4; Group 5, Configuration 3-4: Elapsed Hours**  **Total Task Hours Airplanes**  13.40 17.60 Group 3-4; 5, Configuration 3- 4: Section 46 - 2- Bay SATCOMAntenna - Fuselage Skin Inspection
**MATERIAL INFORMATION**
None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 8 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 9 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 10 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**

BLANK PAGE

### Commercial **Airplanes** 

# 777 Service Bulletin **ALERT Number: 777-53A0068**  Original Issue: June 12, 2013 ATA System: 5345 5365 2315 **SUBJECT:** FUSELAGE - Sections 44 and 46 - Crown Skin Panel - Corrosion and Crack on Fuselage Skin Below SATCOM Antenna Adapter Plate - Inspection
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER.
**1. PLANNING INFORMATION A. Effectivity**  1. Airplanes Refer to Service Bulletin Index D624W001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplane(s) shown below.

**NOTE:** This service bulletin is for the airplanes identified in the Group Configuration table. The effectivity list shown below includes airplanes up to line number 1202. Some airplanes before line number 1202 may be affected by this service bulletin but not included in the effectivity list because they are being delivered out of sequence. At least one airplane, either before or after line number 1202 or both, is affected by this service bulletin and these airplanes are in Group(s) 5. These airplanes will be added to the service bulletin's MyBoeingFleet.com (MBF) "get effectivity" result when they are added to the MBF Fleet Profile Page.
**DESCRIPTION CONFIGURATION**  **GROUP** Airplanes line number 1 through 1076 with 3-bay SATCOM antenna in Section 46. These airplanes do not have SATCOM antenna in Section 44. - 1

Airplanes line number 1 through 1067 with 3-bay SATCOM antenna in Sections 44 and 46. - 2

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 11 of 76**DESCRIPTION CONFIGURATION**  **GROUP** Airplanes line number 1 through 1123 with 2-bay SATCOM antenna in Section 46. These airplanes do not have SATCOM antenna in Section 44. - 3

Airplanes line number 1068 through 1123 with 3-bay SATCOM antenna in Section 44 and 2-bay SATCOM antenna in Section 46. - 4

Airplanes not delivered at the original issue date of this service bulletin and the SATCOM antenna configuration is unknown. - 5

Airplanes with 3-bay SATCOM antenna in Section 46. These airplanes have a production change to the bonding jumper installation for 3-bay SATCOM antenna in Section 46. These airplanes do not have SATCOM antenna in Section 44. 1

Airplanes with 3-bay SATCOM antenna in Sections 44 and 46. These airplanes have a production change to the bonding jumper installation for 3-bay SATCOM antenna in Sections 44 and 46. 2

Airplanes with 2-bay SATCOM antenna in Section 46. These airplanes do not have a production change to the bonding jumper installation for 2-bay SATCOM antenna in Section 46. These airplanes do not have SATCOM antenna in Section 44. 3

Airplanes with 3-bay SATCOM antenna in Section 44 and 2-bay SATCOM antenna in Section 46. These airplanes have a production change to the bonding jumper installation for 3-bay SATCOM antenna in Section 44. These airplanes do not have a production change to the bonding jumper installation for 2-bay SATCOM antenna in Section 46. 4

Airplanes with no SATCOM antenna. 5

Airplane Models: 777-200, 777-200LR, 777-300, 777-300ER, 777F **Group Variable Number**  1 WB105 - WB106 1 WB140 - WB148 1 WB151 - WB155 1 WB176 - WB177 1 WB181 - WB194 1 WB201 - WB215

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 12 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group**  **Variable Number** 1 WB231 - WB247 2 WB271 - WB273 2 WB276 - WB286 2 WB291 - WB302 1 WB311 - WB337 1 WB341 - WB342 1 WB366 - WB368 1 WB371 - WB388 2 WB406 1 WB416 - WB439 1 WB446 - WB453 2 WB476 1 WB501 - WB512 1 WB611 - WB622 1 WB631 - WB638 1 WB646 - WB649 1 WC051 - WC073 1 WC101 - WC104 1 WC116 - WC120 1 WC221 - WC224 1 WC241 - WC243 1 WC281 - WC290 1 WC301 - WC308 1 WC361 - WC364 1 WC371 - WC374 1 WC381 - WC395 1 WC441 1 WC446 - WC449 1 WC456 - WC459 1 WC486 - WC493 1 WC506 - WC508 1 WC521 - WC522 1 WC531 - WC536

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 13 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group**  **Variable Number** 1 WC546 - WC548 1 WC556 1 WC566 - WC567 3 WC571 - WC574 1 WC581 1 WC586 1 WD001 - WD002 2 WD011 - WD018 1 WD031 - WD036 1 WD046 - WD051 3 WD052 - WD055 1 WD066 - WD075 3 WD081 - WD089 3 WD091 3 WD096 3 WD101 - WD106 3 WD111 1 WD116 - WD117 5 WD121 1 WD501 - WD513 1 WD521 - WD541 1 WD546 - WD554 1 WD561 - WD573 1 WD581 - WD594 3 WD595 - WD599 1 WD606 - WD609 1 WD621 - WD632 1 WD651 - WD665 1 WD671 - WD675 3 WD676 1 WD677 1 WD691 - WD709 1 WD741 - WD752

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 14 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group**  **Variable Number** 1 WD761 - WD771 1 WD786 - WD788 1 WD796 - WD819 5 WD820 - WD824 1 WD826 - WD837 1 WD846 - WD850 3 WD851 - WD867 3 WD871 - WD892 5 WD893 - WD894 3 WD911 - WD918 3 WD921 - WD929 1 WD936 - WD939 3 WD940 - WD944 5 WD945 3 WD946 - WD957 3 WD966 - WD970 1 WD981 - WD982 1 WD986 - WD987 1 WD991 - WD992 5 WD994 1 WD996 1 WE001 - WE004 1 WE011 - WE012 3 WE021 - WE026 1 WE031 - WE034 3 WE051 - WE055 3 WE071 - WE072 5 WE073 - WE075 3 WE081 - WE084 1 WE091 - WE093 5 WE095 3 WE126 - WE137 3 WE141 - WE142

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 15 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group**  **Variable Number** 5 WE143 - WE144 3 WE151 - WE165 5 WE166 - WE167 1 WE176 - WE177 3 WE186 - WE208 5 WE209 - WE211 1 WE216 - WE217 5 WE218 1 WE226 - WE231 1 WE236 - WE240 5 WE244 1 WE251 - WE253 1 WE261 - WE263 5 WE266 3 WE271 - WE276 5 WE277 - WE278 5 WE291 - WE292 3 WE301 - WE309 5 WE310 - WE311 4 WE331 - WE334 5 WE335 - WE336 5 WE352 - WE356 5 WE376 - WE377 5 WE386 - WE387 5 WE396 5 WE417 - WE420 5 WE426 5 WE436 5 WE441 3 WF001 - WF004 3 WF016 - WF022 5 WF023 3 WF031 - WF038

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 16 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group**  **Variable Number** 5 WF039 - WF040 3 WF046 - WF064 5 WF065 - WF066 3 WF075 - WF077 3 WF081 - WF088 3 WF096 - WF101 3 WF106 - WF109 3 WF111 - WF115 3 WF121 - WF124 3 WF131 - WF133 3 WF136 - WF138 5 WF139 3 WF146 - WF147 3 WF151 - WF152 5 WF156 - WF157 5 WF166 2. Spares Affected
None. **B. Concurrent Requirements**
None. **C. Reason** This service bulletin gives instructions to inspect for corrosion and cracks in the crown fuselage skin under 2-bay and 3-bay satellite communication (SATCOM) antenna adapter plates located in Sections 44 and 46. There could be fretting and damage to the fuselage skin finish due to a contact between the adapter plate bonding jumper and fuselage skin. Removal of finish in the fuselage skin results in exposure to corrosion, which can lead to cracks. Cracks in the fuselage skin that are not found and repaired can propagate to the point where the fuselage skin structure cannot sustain limit load. When the fuselage skin cannot sustain limit load, this can results in possible rapid decompression and loss of structural integrity.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 17 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**One operator reported a 16 inch crack under the 3-bay SATCOM antenna adapter plate in the crown skin of the fuselage between STA 1601 and STA 1622 (Section 46), and S-1L and S-2L on an airplane that was 14 years old with approximately 14,000 total flight cycles. This crack was found while doing Maintenance Planning Data (MPD) inspection, 777 MPD Section 2, 53-598-00, which requires fuselage skin inspection between STA 1434 and STA 1832. As a part of the MPD inspection, removal of antennas and adapter plates are necessary to access the entire fuselage skin. Subsequent to this crack finding, the same operator inspected 42 other airplanes that are between 6 and 16 years old and found some local corrosion, but no other cracking. Boeing has performed metallurgical fracture analysis of the section of the fuselage skin with the 16 inch crack, which was sent in by the operator. The damaged fuselage skin showed that the braided section of the bonding jumper cable was contacting the skin. The contact between the bonding jumper and fuselage skin results in fretting and removal of the fuselage skin finish. The removal of finish results in exposure to corrosion. The damaged skin panel showed severe exfoliation corrosion in the area where the braided section of the bonding jumper contacted the skin. The fracture analysis showed that primary crack initiated at the area of the exfoliation corrosion. The analysis also showed that cracking progressed by intergranular stress corrosion partially through thickness for 13.5 inches along the interior surface of the skin. Further propagation of the crack through to the exterior surface occurred by fatigue. In addition, Boeing has performed an analysis of SATCOM antenna installations. The installation drawing for 3-bay SATCOM antenna in Section 46 show no clearance between the fuselage skin and the fastener attaching the SATCOM lug adapter plate to the bonding jumper. Due to the lack of clearance, the fastener may come in contact with the fuselage skin. Furthermore, the fastener is located between stringers where the fastener can have a contact with the fuselage due to pillowing out effect when the fuselage is pressurized. The fastener contact with the fuselage skin results in fretting that causes removal of the fuselage skin finish, which results in exposure to corrosion. Boeing has also determined that there are 2-bay and 3-bay SATCOM antennas that are installed at two locations. The "2-bay" and "3-bay" terminologies are used to describe the length of the antenna in terms of frame bays. The 2-bay SATCOM antennas are 2 frame bays long and are installed in Section 46. The 3-bay SATCOM antennas are 3 frame bays long and are installed in Section 44 or Section 46, or both. Airplanes can be delivered with either 2-bay or 3-bay SATCOM antenna in Section 46 as a primary option. If a SATCOM antenna is installed in Section 46, additional 3-bay SATCOM antenna in Section 44 can be installed as a dual option. The analysis showed that both 2-bay and 3-bay SATCOM antennas in Sections 44 and 46 can have similar issues related to bonding jumper and the fastener contacting the skin that results in fretting and removal of fuselage skin finish. The fretting and presence of corrosion are factors that can lead to fuselage skin cracking. This service bulletin gives instructions to inspect for corrosion and cracks in the crown fuselage skin under 2-bay and 3-bay SATCOM antenna adapter plates located in Sections 44 and 46 of the airplane. Boeing Service Related Problem (SRP) 777-SRP-53-0418 is related to this service bulletin. A future service bulletin will be issued to give a terminating action for the continued inspections given in this service bulletin. **NOTE:** There has been a production change to the bonding jumper installation for 3-bay SATCOM antennas in Section 44 at line number 1068 and on, and in Section 46 at line number 1077 and on. There has not been a production change to the bonding jumper installation for 2-bay SATCOM antennas. Boeing Fleet Team Digest (FTD) 777 FTD 53-12001 is related to this service bulletin.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 18 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT D. Description**  **Group 5, Configuration 1-2, 5:** No action is necessary in accordance with this service bulletin. **Group 1-4; Group 5, Configuration 3-4:** Get internal and external access to SATCOM antenna(s). Do repetitive internal and external detailed and surface high frequency eddy current (HFEC) inspections of the visible fuselage skin and doubler, if installed. If any corrosion or crack is found, do a repair in accordance with 777 SRM or contact Boeing for repair instructions and do the repair. If an indication is found that shows a contact of the fastener attaching the SATCOM lug adapter plate to the bonding jumper, contact Boeing for repair instructions and do the repair. After the repair, repeat the inspections in accordance with this service bulletin. Put the airplane back to a serviceable condition. The work in this service bulletin is done in the maintenance zone(s) given below. **Group 1:**
**Affected Maintenance Zones Zone**  **Model** 253, 254 777-200, 777-200LR, 777-300, 777-300ER **Group 2:**
**Affected Maintenance Zones Zone**  **Model** 243, 244, 253, 254 777-200, 777-200LR **Group 3:**
**Affected Maintenance Zones Zone**  **Model** 253, 254 777-200, 777-200LR, 777- 300ER, 777F **Group 4:**
**Affected Maintenance Zones Zone**  **Model** 253, 254 777-300ER

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 19 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 5:** 
**Affected Maintenance Zones Zone**  **Model** 253, 254 777-200, 777-200LR, 777-300, 777-300ER, 777F **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 5, Configuration 1-2, 5:** None. No action is necessary in accordance with this service bulletin. **Group 5, Configuration 3-4:** Refer to Table 13 for the Compliance Information for Section 46 - 2-Bay SATCOM Antenna. **Group 1-4:** Use the Compliance Information Index tables to find the applicable Fuselage Skin Inspection compliance table for each affected SATCOM antenna. Refer to the following table for the Compliance Information Index tables. **Group 1-4: NOTE:**  In the compliance table titles, the compliance information in terms of "Days" refers to the time since the date of issuance of the original certificate of airworthiness or the original export certificate of airworthiness. **Group 1-4: Group 4**  **Group 3 Group 2**  **Group 1 Compliance Infor-** **mation Index Ta ble**  **SATCOM Antenna Location/Description** 

- - X X Table 1 Section 46 - 3-Bay SATCOM Antenna

- - X

- Table 5 Section 44 - 3-Bay SATCOM Antenna X X

- - Table 9 Section 46 - 2-Bay SATCOM Antenna **Group 1-2: Table 1: Section 46 - 3-Bay SATCOM Antenna - Compliance Information Index** 

**Action Condition Questionnaire**  If No, go to the next question. If Yes, go to Table 2. 1. Does the airplane have more than or equal to 14,000 total flight cycles at the time of the original issue date of this service bulletin?

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 20 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 1-2:**  **Table 1: Section 46 - 3-Bay SATCOM Antenna - Compliance Information Index**

**Action Condition Questionnaire**  If No, go to the next question. If Yes, go to Table 2. 2. For the airplane, at the time of the original issue date of this service bulletin, has the time been morethan or equal to 5,250 days since the date of issuance of the original certificate of airworthiness or the original export certificate of airworthiness? If No, go to the next question. If Yes, go to Table 3. 3. Does the airplane have more than or equal to 12,000 total flight cycles and less than 14,000 total flight cycles at the time of the original issue date of this service bulletin? If No, go to Table 4.(a) If Yes, go to Table 3. 4. For the airplane, at the time of the original issue date of this service bulletin, has the time been more than or equal to 4,500 days and less than 5,250 days since the date of issuance of the original certificate of airworthiness or the original export certificate of airworthiness? (a) At the time of the original issue date of this service bulletin, the airplane has less than 12,000 total flightcycles and has been less than 4,500 days since the date of issuance of the original certificate of airworthiness or the original export certificate of airworthiness. **Group 1-2: Table 2: Section 46 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with More than or**  **Equal to 14,000 Total Flight Cycles or 5,250 Days Repeat Interval**  **(Not to Exceed) Compliance Time**  **Action Condition**  1,500 flight cycles or 750 days, whichever occurs first.(a) Within 120 days after the originalissue date of this service bulletin.(a) Do internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2.(a) All airplanes.

(b) Before further flight. Do a 777 SRM repair inaccordance with Paragraph 3.B., Work Instructions, Part 2, or contactBoeing for repair instructions and do the repair. Any corrosion found or Any crack found.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 21 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 1-2:**  **Table 2: Section 46 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with More than or Equal to 14,000 Total Flight Cycles or 5,250 Days**  **Repeat Interval (Not to Exceed)**  **Compliance Time Action**  **Condition**

- Before further flight. Contact Boeing for repair instructions and do the repair. Any indication found thatshows a contact of the fastener attaching the SATCOM lug adapter plate to the bonding jumper given in Paragraph 3.B., Work Instructions, Part 2. and 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2. 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2.Any blend repair accomplished within AllowableDamage 1 limits in accordance with 777 SRM 53- 00-01 given in Paragraph 3.B., Work Instructions, Part 2. 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler in accordance with Paragraph 3.B., Work Instructions, Part 2. Any fuselage skin repairdoubler installed in accordance with 777 SRM 53- 00-01 given in Paragraph 3.B., Work Instructions, Part 2. (a) Previous accomplishment of internal or external detailed inspection of the fuselage skin from STA 1601 to STA 1622 and from S-1L to S-1R meets the requirements of the initial internal and external detailedand surface HFEC inspection of the visible fuselage skin in accordance with Paragraph 3.B., Work Instructions, Part 2. Refer to 777 MPD Section 2, 53-598-00, Boeing Multi-Operator Message (MOM-MOM-12-0466-01B), and 777 FTD 53-12001 for additional information related to this service bulletin issue. (b) For airplanes on which any blend repair is accomplished within allowable damage 1 limits in accordancewith 777 SRM 53-00-01 and for airplanes on which any fuselage skin repair doubler is installed in accordance 777 SRM 53-00-01 given in Paragraph 3.B., Work Instructions, Part 2, refer to the applicable rows in this table for additional inspections.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 22 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 1-2:**  **Table 3: Section 46 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Except for Airplanes Identified in Table 2; Airplanes with More than or Equal to 12,000 and Less than 14,000 Total Flight Cycles; or**  **More than or Equal to 4,500 and Less than 5,250 Days Repeat Interval**  **(Not to Exceed) Compliance Time**  **(Whichever Occurs First) Action**  **Condition** 1,500 flight cycles or 750 days, whichever occurs first.(a) Within 750 flight cycles or 375 days after the original issuedate of this service bulletin,whichever occurs first.(a) Within 120 days after reachingone of the following (whichever occurs first): – 14,000 totalflight cycles. – 5,250 days from thedate of issuance of the original certificateof airworthiness or theoriginal export certificate of airworthiness whichever occurs first. (a) Do internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2.(a) All airplanes.

(b) Before further flight. Do a 777 SRM repair inaccordance with Paragraph 3.B., Work Instructions, Part 2, or contactBoeing for repair instructions and do the repair. Any corrosion found or Any crack found.

- Before further flight. Contact Boeing for repair instructions and do the repair. Any indication found thatshows a contact of the fastener attaching the SATCOM lug adapter plate to the bonding jumper given in Paragraph 3.B., Work Instructions, Part 2. and 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 23 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 1-2:**  **Table 3: Section 46 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Except for Airplanes Identified in Table 2; Airplanes with More than or Equal to 12,000 and Less than 14,000 Total Flight Cycles; or**  **More than or Equal to 4,500 and Less than 5,250 Days Repeat Interval**  **(Not to Exceed) Compliance Time**  **(Whichever Occurs First) Action**  **Condition** 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2.Any blend repair accomplished within AllowableDamage 1 limits in accordance with 777 SRM 53- 00-01 given in Paragraph 3.B., Work Instructions, Part 2. 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler in accordance with Paragraph 3.B., Work Instructions, Part 2. Any fuselage skin repairdoubler installed in accordance with 777 SRM 53- 00-01 given in Paragraph 3.B., Work Instructions, Part 2. (a) Previous accomplishment of internal or external detailed inspection of the fuselage skin from STA 1601 to STA 1622 and from S-1L to S-1R meets the requirements of the initial internal and external detailedand surface HFEC inspection of the visible fuselage skin in accordance with Paragraph 3.B., Work Instructions, Part 2. Refer to 777 MPD Section 2, 53-598-00, Boeing Multi-Operator Message (MOM-MOM-12-0466-01B), and 777 FTD 53-12001 for additional information related to this service bulletin issue. (b) For airplanes on which any blend repair is accomplished within allowable damage 1 limits in accordancewith 777 SRM 53-00-01 and for airplanes on which any fuselage skin repair doubler is installed in accordance 777 SRM 53-00-01 given in Paragraph 3.B., Work Instructions, Part 2, refer to the applicable rows in this table for additional inspections.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 24 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 1-2:**  **Table 4: Section 46 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with Less than 12,000 Total Flight Cycles and 4,500 Days**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition**  1,500 flight cycles or 750 days, whichever occurs first.(a) Within 750 flight cycles or 375 days after the original issuedate of this service bulletin,whichever occurs first.(a) Before 12,000 total flight cycles or within 4,500 days from the date of issuance of the originalcertificate of airworthiness orthe original export certificate of airworthiness,whichever occurs first.(a) Do internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2.(a) All airplanes.

(b) Before further flight. Do a 777 SRM repair inaccordance with Paragraph 3.B., Work Instructions, Part 2, or contactBoeing for repair instructions and do the repair. Any corrosion found or Any crack found.

- Before further flight. Contact Boeing for repair instructions and do the repair. Any indication found thatshows a contact of the fastener attaching the SATCOM lug adapter plate to the bonding jumper given in Paragraph 3.B., Work Instructions, Part 2. and 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2. 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2.Any blend repair accomplished within AllowableDamage 1 limits in accordance with 777 SRM 53- 00-01 given in Paragraph 3.B., Work Instructions, Part 2.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 25 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 1-2:**  **Table 4: Section 46 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with Less than 12,000 Total Flight Cycles and 4,500 Days**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition**  1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler in accordance with Paragraph 3.B., Work Instructions, Part 2. Any fuselage skin repairdoubler installed in accordance with 777 SRM 53- 00-01 given in Paragraph 3.B., Work Instructions, Part 2. (a) Previous accomplishment of internal or external detailed inspection of the fuselage skin from STA 1601 to STA 1622 and from S-1L to S-1R meets the requirements of the initial internal and external detailedand surface HFEC inspection of the visible fuselage skin in accordance with Paragraph 3.B., Work Instructions, Part 2. Refer to 777 MPD Section 2, 53-598-00, Boeing Multi-Operator Message (MOM-MOM-12-0466-01B), and 777 FTD 53-12001 for additional information related to this service bulletin issue. (b) For airplanes on which any blend repair is accomplished within allowable damage 1 limits in accordancewith 777 SRM 53-00-01 and for airplanes on which any fuselage skin repair doubler is installed in accordance 777 SRM 53-00-01 given in Paragraph 3.B., Work Instructions, Part 2, refer to the applicable rows in this table for additional inspections. **Group 2: Table 5: Section 44 - 3-Bay SATCOM Antenna - Compliance Information Index** 

**Action Condition Questionnaire**  If No, go to the next question. If Yes, go to Table 6. 1. Does the airplane have more than or equal to 14,000 total flight cycles at the time of the original issue date of this service bulletin? If No, go to the next question. If Yes, go to Table 6. 2. For the airplane, at the time of the original issue date of this service bulletin, has the time been morethan or equal to 5,250 days since the date of issuance of the original certificate of airworthiness or the original export certificate of airworthiness? If No, go to the next question. If Yes, go to Table 7. 3. Does the airplane have more than or equal to 12,000 total flight cycles and less than 14,000 total flight cycles at the time of the original issue date of this service bulletin? If No, go to Table 8.(a) If Yes, go to Table 7. 4. For the airplane, at the time of the original issue date of this service bulletin, has the time been more than or equal to 4,500 days and less than 5,250 days since the date of issuance of the original certificate of airworthiness or the original export certificate of airworthiness?

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 26 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 2:**  **Table 5: Section 44 - 3-Bay SATCOM Antenna - Compliance Information Index**

**Action Condition Questionnaire**  (a) At the time of the original issue date of this service bulletin, the airplane has less than 12,000 total flightcycles and has been less than 4,500 days since the date of issuance of the original certificate of airworthiness or the original export certificate of airworthiness. **Group 2: Table 6: Section 44 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with More than or**  **Equal to 14,000 Total Flight Cycles or 5,250 Days Repeat Interval**  **(Not to Exceed) Compliance Time**  **Action Condition**  1,500 flight cycles or 750 days, whichever occurs first.(a) Within 120 days after the originalissue date of this service bulletin.(a) Do internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2.(a) All airplanes.

(b) Before further flight. Do a 777 SRM repair inaccordance with Paragraph 3.B., Work Instructions, Part 2, or contactBoeing for repair instructions and do the repair. Any corrosion found or Any crack found.

- Before further flight. Contact Boeing for repair instructions and do the repair. Any indication found thatshows a contact of the fastener attaching the SATCOM lug adapter plate to the bonding jumper given in Paragraph 3.B., Work Instructions, Part 2. and 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2. 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2.Any blend repair accomplished within AllowableDamage 1 limits in accordance with 777 SRM 53- 00-01 given in Paragraph 3.B., Work Instructions, Part 2.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 27 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 2:**  **Table 6: Section 44 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with More than or Equal to 14,000 Total Flight Cycles or 5,250 Days**  **Repeat Interval (Not to Exceed)**  **Compliance Time Action**  **Condition** 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler in accordance with Paragraph 3.B., Work Instructions, Part 2. Any fuselage skin repairdoubler installed in accordance with 777 SRM 53- 00-01 given in Paragraph 3.B., Work Instructions, Part 2. (a) Previous accomplishment of internal or external detailed inspection of the fuselage skin from STA 1077 to STA 1098 and from S-1L to S-1R meets the requirements of the initial internal and external detailedand surface HFEC inspection of the visible fuselage skin in accordance with Paragraph 3.B., Work Instructions, Part 2. Refer to 777 MPD Section 2, 53-598-00, Boeing Multi-Operator Message (MOM-MOM-12-0466-01B), and 777 FTD 53-12001 for additional information related to this service bulletin issue. (b) For airplanes on which any blend repair is accomplished within allowable damage 1 limits in accordancewith 777 SRM 53-00-01 and for airplanes on which any fuselage skin repair doubler is installed in accordance 777 SRM 53-00-01 given in Paragraph 3.B., Work Instructions, Part 2, refer to the applicable rows in this table for additional inspections.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 28 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 2:**  **Table 7: Section 44 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Except for Airplanes Identified in Table 6; Airplanes with More than or Equal to 12,000 and Less than 14,000 Total Flight Cycles; or**  **More than or Equal to 4,500 and Less than 5,250 Days Repeat Interval**  **(Not to Exceed) Compliance Time**  **(Whichever Occurs First) Action**  **Condition** 1,500 flight cycles or 750 days, whichever occurs first.(a) Within 750 flight cycles or 375 days after the original issuedate of this service bulletin,whichever occurs first.(a) Within 120 days after reachingone of the following (whichever occurs first): – 14,000 totalflight cycles. – 5,250 days from thedate of issuance of the original certificateof airworthiness or theoriginal export certificate of airworthiness whichever occurs first. (a) Do internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2.(a) All airplanes.

(b) Before further flight. Do a 777 SRM repair inaccordance with Paragraph 3.B., Work Instructions, Part 2, or contactBoeing for repair instructions and do the repair. Any corrosion found or Any crack found.

- Before further flight. Contact Boeing for repair instructions and do the repair. Any indication found thatshows a contact of the fastener attaching the SATCOM lug adapter plate to the bonding jumper given in Paragraph 3.B., Work Instructions, Part 2. and 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 29 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 2:**  **Table 7: Section 44 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Except for Airplanes Identified in Table 6; Airplanes with More than or Equal to 12,000 and Less than 14,000 Total Flight Cycles; or**  **More than or Equal to 4,500 and Less than 5,250 Days Repeat Interval**  **(Not to Exceed) Compliance Time**  **(Whichever Occurs First) Action**  **Condition** 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2.Any blend repair accomplished within AllowableDamage 1 limits in accordance with 777 SRM 53- 00-01 given in Paragraph 3.B., Work Instructions, Part 2. 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler in accordance with Paragraph 3.B., Work Instructions, Part 2. Any fuselage skin repairdoubler installed in accordance with 777 SRM 53- 00-01 given in Paragraph 3.B., Work Instructions, Part 2. (a) Previous accomplishment of internal or external detailed inspection of the fuselage skin from STA 1077 to STA 1098 and from S-1L to S-1R meets the requirements of the initial internal and external detailedand surface HFEC inspection of the visible fuselage skin in accordance with Paragraph 3.B., Work Instructions, Part 2. Refer to 777 MPD Section 2, 53-598-00, Boeing Multi-Operator Message (MOM-MOM-12-0466-01B), and 777 FTD 53-12001 for additional information related to this service bulletin issue. (b) For airplanes on which any blend repair is accomplished within allowable damage 1 limits in accordancewith 777 SRM 53-00-01 and for airplanes on which any fuselage skin repair doubler is installed in accordance 777 SRM 53-00-01 given in Paragraph 3.B., Work Instructions, Part 2, refer to the applicable rows in this table for additional inspections.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 30 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 2:**  **Table 8: Section 44 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with Less than 12,000 Total Flight Cycles and 4,500 Days**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition**  1,500 flight cycles or 750 days, whichever occurs first.(a) Within 750 flight cycles or 375 days after the original issuedate of this service bulletin,whichever occurs first.(a) Before 12,000 total flight cycles or within 4,500 days from the date of issuance of the originalcertificate of airworthiness orthe original export certificate of airworthiness,whichever occurs first.(a) Do internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2.(a) All airplanes.

(b) Before further flight. Do a 777 SRM repair inaccordance with Paragraph 3.B., Work Instructions, Part 2, or contactBoeing for repair instructions and do the repair. Any corrosion found or Any crack found.

- Before further flight. Contact Boeing for repair instructions and do the repair. Any indication found thatshows a contact of the fastener attaching the SATCOM lug adapter plate to the bonding jumper given in Paragraph 3.B., Work Instructions, Part 2. and 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2. 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2.Any blend repair accomplished within AllowableDamage 1 limits in accordance with 777 SRM 53- 00-01 given in Paragraph 3.B., Work Instructions, Part 2.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 31 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 2:**  **Table 8: Section 44 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with Less than 12,000 Total Flight Cycles and 4,500 Days**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition**  1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler in accordance with Paragraph 3.B., Work Instructions, Part 2. Any fuselage skin repairdoubler installed in accordance with 777 SRM 53- 00-01 given in Paragraph 3.B., Work Instructions, Part 2. (a) Previous accomplishment of internal or external detailed inspection of the fuselage skin from STA 1077 to STA 1098 and from S-1L to S-1R meets the requirements of the initial internal and external detailedand surface HFEC inspection of the visible fuselage skin in accordance with Paragraph 3.B., Work Instructions, Part 2. Refer to 777 MPD Section 2, 53-598-00, Boeing Multi-Operator Message (MOM-MOM-12-0466-01B), and 777 FTD 53-12001 for additional information related to this service bulletin issue. (b) For airplanes on which any blend repair is accomplished within allowable damage 1 limits in accordancewith 777 SRM 53-00-01 and for airplanes on which any fuselage skin repair doubler is installed in accordance 777 SRM 53-00-01 given in Paragraph 3.B., Work Instructions, Part 2, refer to the applicable rows in this table for additional inspections. **Group 3-4: Table 9: Section 46 - 2-Bay SATCOM Antenna - Compliance Information Index** 

**Action Condition Questionnaire**  If No, go to the next question. If Yes, go to Table 10. 1. Does the airplane have more than or equal to 14,000 total flight cycles at the time of the original issue date of this service bulletin? If No, go to the next question. If Yes, go to Table 10. 2. For the airplane, at the time of the original issue date of this service bulletin, has the time been morethan or equal to 5,250 days since the date of issuance of the original certificate of airworthiness or the original export certificate of airworthiness? If No, go to the next question. If Yes, go to Table 11. 3. Does the airplane have more than or equal to 12,000 total flight cycles and less than 14,000 total flight cycles at the time of the original issue date of this service bulletin? If No, go to Table 12.(a) If Yes, go to Table 11. 4. For the airplane, at the time of the original issue date of this service bulletin, has the time been more than or equal to 4,500 days and less than 5,250 days since the date of issuance of the original certificate of airworthiness or the original export certificate of airworthiness?

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 32 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 3-4:**  **Table 9: Section 46 - 2-Bay SATCOM Antenna - Compliance Information Index**

**Action Condition Questionnaire**  (a) At the time of the original issue date of this service bulletin, the airplane has less than 12,000 total flightcycles and has been less than 4,500 days since the date of issuance of the original certificate of airworthiness or the original export certificate of airworthiness. **Group 3-4: Table 10: Section 46 - 2-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with More than**  **or Equal to 14,000 Total Flight Cycles or 5,250 Days Repeat Interval**  **(Not to Exceed) Compliance Time**  **Action Condition**  1,500 flight cycles or 750 days, whichever occurs first.(a) Within 120 days after the originalissue date of this service bulletin.(a) Do internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2.(a) All airplanes.

(b) Before further flight. Do a 777 SRM repair inaccordance with Paragraph 3.B., Work Instructions, Part 2, or contactBoeing for repair instructions and do the repair. Any corrosion found or Any crack found.

- Before further flight. Contact Boeing for repair instructions and do the repair. Any indication found thatshows a contact of the fastener attaching the SATCOM lug adapter plate to the bonding jumper given in Paragraph 3.B., Work Instructions, Part 2. and 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2. 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2.Any blend repair accomplished within AllowableDamage 1 limits in accordance with 777 SRM 53- 00-01 given in Paragraph 3.B., Work Instructions, Part 2.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 33 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 3-4:**  **Table 10: Section 46 - 2-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with More than or Equal to 14,000 Total Flight Cycles or 5,250 Days**  **Repeat Interval (Not to Exceed)**  **Compliance Time Action**  **Condition** 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler in accordance with Paragraph 3.B., Work Instructions, Part 2. Any fuselage skin repairdoubler installed in accordance with 777 SRM 53- 00-01 given in Paragraph 3.B., Work Instructions, Part 2. (a) Previous accomplishment of internal or external detailed inspection of the fuselage skin from STA 1601 to STA 1622 and from S-1L to S-1R meets the requirements of the initial internal and external detailedand surface HFEC inspection of the visible fuselage skin in accordance with Paragraph 3.B., Work Instructions, Part 2. Refer to 777 MPD Section 2, 53-598-00, Boeing Multi-Operator Message (MOM-MOM-12-0466-01B), and 777 FTD 53-12001 for additional information related to this service bulletin issue. (b) For airplanes on which any blend repair is accomplished within allowable damage 1 limits in accordancewith 777 SRM 53-00-01 and for airplanes on which any fuselage skin repair doubler is installed in accordance 777 SRM 53-00-01 given in Paragraph 3.B., Work Instructions, Part 2, refer to the applicable rows in this table for additional inspections.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 34 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 3-4:**  **Table 11: Section 46 - 2-Bay SATCOM Antenna - Fuselage Skin Inspection - Except for Airplanes Identified in Table 10; Airplanes with More than or Equal to 12,000 and Less than 14,000 Total Flight Cycles; or**  **More than or Equal to 4,500 and Less than 5,250 Days Repeat Interval**  **(Not to Exceed) Compliance Time**  **(Whichever Occurs First) Action**  **Condition** 1,500 flight cycles or 750 days, whichever occurs first.(a) Within 750 flight cycles or 375 days after the original issuedate of this service bulletin,whichever occurs first.(a) Within 120 days after reachingone of the following (whichever occurs first): – 14,000 totalflight cycles. – 5,250 days from thedate of issuance of the original certificateof airworthiness or theoriginal export certificate of airworthiness whichever occurs first. (a) Do internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2.(a) All airplanes.

(b) Before further flight. Do a 777 SRM repair inaccordance with Paragraph 3.B., Work Instructions, Part 2, or contactBoeing for repair instructions and do the repair. Any corrosion found or Any crack found.

- Before further flight. Contact Boeing for repair instructions and do the repair. Any indication found thatshows a contact of the fastener attaching the SATCOM lug adapter plate to the bonding jumper given in Paragraph 3.B., Work Instructions, Part 2. and 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 35 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 3-4:**  **Table 11: Section 46 - 2-Bay SATCOM Antenna - Fuselage Skin Inspection - Except for Airplanes Identified in Table 10; Airplanes with More than or Equal to 12,000 and Less than 14,000 Total Flight Cycles; or**  **More than or Equal to 4,500 and Less than 5,250 Days Repeat Interval**  **(Not to Exceed) Compliance Time**  **(Whichever Occurs First) Action**  **Condition** 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2.Any blend repair accomplished within AllowableDamage 1 limits in accordance with 777 SRM 53- 00-01 given in Paragraph 3.B., Work Instructions, Part 2. 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler in accordance with Paragraph 3.B., Work Instructions, Part 2. Any fuselage skin repairdoubler installed in accordance with 777 SRM 53- 00-01 given in Paragraph 3.B., Work Instructions, Part 2. (a) Previous accomplishment of internal or external detailed inspection of the fuselage skin from STA 1601 to STA 1622 and from S-1L to S-1R meets the requirements of the initial internal and external detailedand surface HFEC inspection of the visible fuselage skin in accordance with Paragraph 3.B., Work Instructions, Part 2. Refer to 777 MPD Section 2, 53-598-00, Boeing Multi-Operator Message (MOM-MOM-12-0466-01B), and 777 FTD 53-12001 for additional information related to this service bulletin issue. (b) For airplanes on which any blend repair is accomplished within allowable damage 1 limits in accordancewith 777 SRM 53-00-01 and for airplanes on which any fuselage skin repair doubler is installed in accordance 777 SRM 53-00-01 given in Paragraph 3.B., Work Instructions, Part 2, refer to the applicable rows in this table for additional inspections.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 36 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 3-4:**  **Table 12: Section 46 - 2-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with Less than 12,000 Total Flight Cycles and 4,500 Days**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition**  1,500 flight cycles or 750 days, whichever occurs first.(a) Within 750 flight cycles or 375 days after the original issuedate of this service bulletin,whichever occurs first.(a) Before 12,000 total flight cycles or within 4,500 days from the date of issuance of the originalcertificate of airworthiness orthe original export certificate of airworthiness,whichever occurs first.(a) Do internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2.(a) All airplanes.

(b) Before further flight. Do a 777 SRM repair inaccordance with Paragraph 3.B., Work Instructions, Part 2, or contactBoeing for repair instructions and do the repair. Any corrosion found or Any crack found.

- Before further flight. Contact Boeing for repair instructions and do the repair. Any indication found thatshows a contact of the fastener attaching the SATCOM lug adapter plate to the bonding jumper given in Paragraph 3.B., Work Instructions, Part 2. and 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2. 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2.Any blend repair accomplished within AllowableDamage 1 limits in accordance with 777 SRM 53- 00-01 given in Paragraph 3.B., Work Instructions, Part 2.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 37 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 3-4:**  **Table 12: Section 46 - 2-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with Less than 12,000 Total Flight Cycles and 4,500 Days**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition**  1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler in accordance with Paragraph 3.B., Work Instructions, Part 2. Any fuselage skin repairdoubler installed in accordance with 777 SRM 53- 00-01 given in Paragraph 3.B., Work Instructions, Part 2. (a) Previous accomplishment of internal or external detailed inspection of the fuselage skin from STA 1601 to STA 1622 and from S-1L to S-1R meets the requirements of the initial internal and external detailedand surface HFEC inspection of the visible fuselage skin in accordance with Paragraph 3.B., Work Instructions, Part 2. Refer to 777 MPD Section 2, 53-598-00, Boeing Multi-Operator Message (MOM-MOM-12-0466-01B), and 777 FTD 53-12001 for additional information related to this service bulletin issue. (b) For airplanes on which any blend repair is accomplished within allowable damage 1 limits in accordancewith 777 SRM 53-00-01 and for airplanes on which any fuselage skin repair doubler is installed in accordance 777 SRM 53-00-01 given in Paragraph 3.B., Work Instructions, Part 2, refer to the applicable rows in this table for additional inspections. **Group 5, Configuration 3-4: Table 13: Section 46 - 2-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes Not Yet Delivered**  **at the Original Issue Date of this Service Bulletin Repeat Interval**  **(Not to Exceed) Compliance Time**  **Action Condition**  1,500 flight cycles or 750 days, whichever occurs first. Before 12,000 total flight cycles or within 4,500 days from the date of issuance of the original certificateof airworthiness or the original export certificate of airworthiness, whichever occurs first. Do internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2. All airplanes.

(a) Before further flight. Do a 777 SRM repair inaccordance with Paragraph 3.B., Work Instructions, Part 2, or contactBoeing for repair instructions and do the repair. Any corrosion found or Any crack found.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 38 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 5, Configuration 3-4:**  **Table 13: Section 46 - 2-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes Not Yet Delivered at the Original Issue Date of this Service Bulletin**  **Repeat Interval (Not to Exceed)**  **Compliance Time Action**  **Condition**

- Before further flight. Contact Boeing for repair instructions and do the repair. Any indication found thatshows a contact of the fastener attaching the SATCOM lug adapter plate to the bonding jumper given in Paragraph 3.B., Work Instructions, Part 2. and 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2. 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler, if installed, inaccordance with Paragraph 3.B., Work Instructions, Part 2.Any blend repair accomplished within AllowableDamage 1 limits in accordance with 777 SRM 53- 00-01 given in Paragraph 3.B., Work Instructions, Part 2. 1,500 flight cycles or 750 days, whichever occurs first. Within 1,500 flight cycles or 750 days after the repair, whichever occurs first.Repeat internal and external detailed and surface HFEC inspections of the visible fuselage skin and doubler in accordance with Paragraph 3.B., Work Instructions, Part 2. Any fuselage skin repairdoubler installed in accordance with 777 SRM 53- 00-01 given in Paragraph 3.B., Work Instructions, Part 2. (a) For airplanes on which any blend repair is accomplished within allowable damage 1 limits in accordancewith 777 SRM 53-00-01 and for airplanes on which any fuselage skin repair doubler is installed in accordance 777 SRM 53-00-01 given in Paragraph 3.B., Work Instructions, Part 2, refer to the applicable rows in this table for additional 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 39 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**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 tables below show an estimate of the task hours necessary to do this inspection for each 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 5, Configuration 1-2, 5:** None. No action is necessary in accordance with this service bulletin. **Group 1: Table 1: Section 46 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection**  **Elapsed Hours Task Hours**  **Number of Persons Task**  2.00 2.00 1 Open Access - Inter- nal 2.10 4.20 2 Open Access - Exter- nal 0.20 0.20 1 FIGURE 1 3.00 3.00 1 FIGURE 2 2.00 2.00 1 FIGURE 3 2.00 2.00 1 Close Access - Inter- nal 2.10 4.20 2 Close Access - Exter- nal 13.40 17.60 TOTAL FOR EACH AIRPLANE **Group 2: Table 2: Sections 44 and 46 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection**  **Elapsed Hours Task Hours**  **Number of Persons Task**  Section 44 - 3-Bay SATCOM Antenna 2.00 2.00 1 Open Access - Inter- nal

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 40 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 2:**  **Table 2: Sections 44 and 46 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection Elapsed Hours**  **Task Hours Number of Persons**  **Task** 2.10 4.20 2 Open Access - Exter- nal 0.20 0.20 1 FIGURE 4 3.00 3.00 1 FIGURE 5 2.00 2.00 1 FIGURE 6 2.00 2.00 1 Close Access - Inter- nal 2.10 4.20 2 Close Access - Exter- nal Section 46 - 3-Bay SATCOM Antenna 2.00 2.00 1 Open Access - Inter- nal 2.10 4.20 2 Open Access - Exter- nal 0.20 0.20 1 FIGURE 1 3.00 3.00 1 FIGURE 2 2.00 2.00 1 FIGURE 3 2.00 2.00 1 Close Access - Inter- nal 2.10 4.20 2 Close Access - Exter- nal 26.80 35.20 TOTAL FOR EACH AIRPLANE **Group 3-4; Group 5, Configuration 3-4: Table 3: Section 46 - 2-Bay SATCOM Antenna - Fuselage Skin Inspection**  **Elapsed Hours Task Hours**  **Number of Persons Task**  2.00 2.00 1 Open Access - Inter- nal 2.10 4.20 2 Open Access - Exter- nal 0.20 0.20 1 FIGURE 7 3.00 3.00 1 FIGURE 8 2.00 2.00 1 FIGURE 9 2.00 2.00 1 Close Access - Inter- nal

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 41 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT Group 3-4; Group 5, Configuration 3-4:**  **Table 3: Section 46 - 2-Bay SATCOM Antenna - Fuselage Skin Inspection Elapsed Hours**  **Task Hours Number of Persons**  **Task** 2.10 4.20 2 Close Access - Exter- nal 13.40 17.60 TOTAL FOR EACH AIRPLANE **H. Weight and Balance Changes**
None. **I. Electrical Load Data** Not changed. **J. References** 1. Existing Data: a. Boeing Service Letter 777-SL-51-013 b. Boeing Service Related Problem (SRP) 777-SRP-53-0418 c. Service Bulletin Index D624W001 d. Standard Overhaul Practices Manual (SOPM) 20-50-19 e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19, 20-20-10 f. 777 Aircraft Maintenance Manual (AMM) 23-15-08, 23-15-23, 25-80-00, 53-61-51 g. 777 Fleet Team Digest (FTD) 53-12001 h. 777 Maintenance Planning Data (MPD) Section 2, 53-598-00 i. 777 Non-Destructive Testing (NDT) Manual Part 6, 51-00-01 j. 777-200 Structural Repair Manual (SRM) 51-10-02, 53-00-01 k. 777-300 Structural Repair Manual (SRM) 51-10-02, 53-00-01 l. 777F Structural Repair Manual (SRM) 51-10-02, 53-00-01 2. Data Supplied with this Service Bulletin:
None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 42 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**3. Installation Drawings Used in the Preparation of this Service Bulletin:

**Title Drawing Number**  SUPPORT INSTL - SATCOM, HIGH GAIN TOP MOUNT 144W0026 SUPPORT INSTL - SATCOM, HIGH GAIN TOP MOUNT 146W0027 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. **K. 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 but no new DTIs are necessary. **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: June 12, 2013 777-53A0068 43 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 44 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**

BLANK PAGE**2. MATERIAL INFORMATION A. Material - Price and Availability** 
None. **B. Industry Support Information** Boeing warranty remedies are available for 777 airplanes in warranty as of June 25, 2012. For inspection labor task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Warranty & Product Assurance Contracts. If the condition described in this service bulletin is found during the inspection for airplanes in warranty as of that date and additional task hours are required, send a warranty claim to Boeing Warranty & Product Assurance Contracts. Please refer to this service bulletin number and reference the airplane variable number(s) in your purchase order. The warranty remedies will expire eight years from the original issue date of this service bulletin. **C. Parts Necessary for Each Airplane** 1. Kits/Parts
None. 2. Parts and Materials Supplied by the Operator
None. 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: June 12, 2013 777-53A0068 45 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 46 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**

BLANK PAGE**3. 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 – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – 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. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures, and SWPM 20-10-19 for the wire separation requirements, as accepted procedures. 6. A Detailed Inspection is defined as: An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required. 7. 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. 8. Boeing Service Letter 777-SL-51-013, 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 47 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**9. 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. 10. 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. 11. 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. 12. Shaded areas in Figures are to separate the non-critical and non-authoritative information from the critical and authoritative information. 13. The satellite communication (SATCOM) antenna is also referred to as Top Mount High Gain Antenna (TMHGA). For this service bulletin, "SATCOM antenna" is used to refer to the antenna. **B. WORK INSTRUCTIONS Group 5, Configuration 1-2, 5:**  No action is necessary in accordance with this service bulletin. These airplanes either have a production change to the bonding jumper installation for 3-bay SATCOM antenna or do not have any SATCOM antennas installed. **Group 1-4; Group 5, Configuration 3-4: Part 1 - Access** 
1. **Group 1-2:** Section 46 - 3-Bay SATCOM Antenna - Internal Access: a. Open the circuit breaker to the SATCOM antenna and remove interior furnishings. Refer to 777 AMM 23-15-08 as an accepted procedure. b. Remove insulation blankets. Refer to 777 AMM 25-80-00 as an accepted procedure.
2. **Group 2:** Section 44 - 3-Bay SATCOM Antenna - Internal Access: a. Open the circuit breaker to the SATCOM antenna and remove interior furnishings. Refer to 777 AMM 23-15-08 as an accepted procedure. b. Remove insulation blankets. Refer to 777 AMM 25-80-00 as an accepted procedure.
3. **Group 3-4; Group 5, Configuration 3-4:** Section 46 - 2-Bay SATCOM Antenna - Internal Access: a. Open the circuit breaker to the SATCOM antenna and remove interior furnishings. Refer to 777 AMM 23-15-08 as an accepted procedure. b. Remove insulation blankets. Refer to 777 AMM 25-80-00 as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 48 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**4. **Group 1-2:** Section 46 - 3-Bay SATCOM Antenna - External Access: a. Remove the SATCOM antenna. Refer to 777 AMM 23-15-23 as an accepted procedure. b. Remove the adapter plate. Refer to 777 AMM 53-61-51 as an accepted procedure. During the removal of the adapter plate, locate and mark the location of the fastener common to the adapter plate and bonding jumper on the fuselage skin or doubler, if installed, in accordance with FIGURE 1.
5. **Group 2:** Section 44 - 3-Bay SATCOM Antenna - External Access: a. Remove the SATCOM antenna. Refer to 777 AMM 23-15-23 as an accepted procedure. b. Remove the adapter plate. Refer to 777 AMM 53-61-51 as an accepted procedure. During the removal of the adapter plate, locate and mark the location of the fastener common to the adapter plate and bonding jumper on the fuselage skin or doubler, if installed, in accordance with FIGURE 4.
6. **Group 3-4; Group 5, Configuration 3-4:** Section 46 - 2-Bay SATCOM Antenna - External Access: a. Remove the SATCOM antenna. Refer to 777 AMM 23-15-23 as an accepted procedure. b. Remove the adapter plate. Refer to 777 AMM 53-61-51 as an accepted procedure. During the removal of the adapter plate, locate and mark the location of the fastener common to the adapter plate and bonding jumper on the fuselage skin or doubler, if installed, in accordance with FIGURE 7. **Group 1-4; Group 5, Configuration 3-4: Part 2 - Inspection** 
1. **Group 1-2:** Section 46 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection: Do internal detailed and surface high frequency eddy current (HFEC) inspections of the visible fuselage skin in accordance with FIGURE 2. If a fuselage skin repair doubler is installed, do detailed and surface HFEC inspections of the visible doubler in the specified inspection area in accordance with the figure. Do external detailed and surface HFEC inspections of the visible fuselage skin in accordance with FIGURE 3. If a fuselage skin repair doubler is installed, do detailed and surface HFEC inspections of the visible doubler in the specified inspection area in accordance with the figure.
**NOTE:** Previous accomplishment of internal or external detailed inspection of the fuselage skin from STA 1601 to STA 1622 and from S-1L to S-1R meets the intent of the initial internal and external detailed and surface HFEC inspection of the visible fuselage skin. a. If any corrosion is found, do a repair in accordance with 777-200 SRM 53-00-01 or 777-300 SRM 53-00-01; or contact Boeing for repair instructions and do the repair. General corrosion damage removal procedure and inspection is specified in 777-200 SRM 51-10-02 or 777-300 SRM 51-10-02.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 49 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**(1) If a blend repair was accomplished within Allowable Damage 1 limits in accordance with 777-200 SRM 53-00-01 or 777-300 SRM 53-00-01, repeat the internal and external detailed and surface HFEC inspections at the time given in Paragraph 1.E., Compliance. (2) If external repair doubler is necessary in accordance with 777 SRM, contact Boeing for repair instructions and do the repair to make sure that there is sufficient clearance between the fuselage skin or doubler, and fastener attaching the SATCOM lug adapter plate to the bonding jumper. If a fuselage skin repair doubler was installed, repeat the internal and external detailed and surface HFEC inspections at the time given in Paragraph 1.E., Compliance. b. If any crack is found, do a repair in accordance with 777-200 SRM 53-00-01 or 777-300 SRM 53-00-01; or contact Boeing for repair instructions and do the repair. (1) If external repair doubler is necessary in accordance with 777 SRM, contact Boeing for repair instructions and do the repair to make sure that there is sufficient clearance between the fuselage skin or doubler, and fastener attaching the SATCOM lug adapter plate to the bonding jumper. (2) If a fuselage skin repair doubler was installed, repeat the internal and external detailed and surface HFEC inspections at the time given in Paragraph 1.E., Compliance. c. If any indication is found that shows a contact of the fastener attaching the SATCOM lug adapter plate to the bonding jumper, contact Boeing for repair instructions and do the repair. Indications of the fastener contact include imprint, gouge, rubbing, and scratch. After the repair, repeat the internal and external detailed and surface HFEC inspections at the time given in Paragraph 1.E., Compliance.
2. **Group 2:** Section 44 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection: Do internal detailed and surface HFEC inspections of the visible fuselage skin in accordance with FIGURE 5. If a fuselage skin repair doubler is installed, do detailed and surface HFEC inspections of the visible doubler in the specified inspection area in accordance with the figure. Do external detailed and surface HFEC inspections of the visible fuselage skin in accordance with FIGURE 6. If a fuselage skin repair doubler is installed, do detailed and surface HFEC inspections of the visible doubler in the specified inspection area in accordance with the figure.
**NOTE:** Previous accomplishment of internal or external detailed inspection of the fuselage skin from STA 1077 to STA 1098 and from S-1L to S-1R meets the intent of the initial internal and external detailed and surface HFEC inspection of the visible fuselage skin. a. If any corrosion is found, do a repair in accordance with 777-200 SRM 53-00-01 or 777-300 SRM 53-00-01; or contact Boeing for repair instructions and do the repair. General corrosion damage removal procedure and inspection is specified in 777-200 SRM 51-10-02 or 777-300 SRM 51-10-02. (1) If a blend repair was accomplished within Allowable Damage 1 limits in accordance with 777-200 SRM 53-00-01 or 777-300 SRM 53-00-01, repeat the internal and external detailed and surface HFEC inspections at the time given in Paragraph 1.E., Compliance.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 50 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**(2) If external repair doubler is necessary in accordance with 777 SRM, contact Boeing for repair instructions and do the repair to make sure that there is sufficient clearance between the fuselage skin or doubler, and fastener attaching the SATCOM lug adapter plate to the bonding jumper. If a fuselage skin repair doubler was installed, repeat the internal and external detailed and surface HFEC inspections at the time given in Paragraph 1.E., Compliance. b. If any crack is found, do a repair in accordance with 777-200 SRM 53-00-01 or 777-300 SRM 53-00-01; or contact Boeing for repair instructions and do the repair. (1) If external repair doubler is necessary in accordance with 777 SRM, contact Boeing for repair instructions and do the repair to make sure that there is sufficient clearance between the fuselage skin or doubler, and fastener attaching the SATCOM lug adapter plate to the bonding jumper. (2) If a fuselage skin repair doubler was installed, repeat the internal and external detailed and surface HFEC inspections at the time given in Paragraph 1.E., Compliance. c. If any indication is found that shows a contact of the fastener attaching the SATCOM lug adapter plate to the bonding jumper, contact Boeing for repair instructions and do the repair. Indications of the fastener contact include imprint, gouge, rubbing, and scratch. After the repair, repeat the internal and external detailed and surface HFEC inspections at the time given in Paragraph 1.E., Compliance.
3. **Group 3-4; Group 5, Configuration 3-4:** Section 46 - 2-Bay SATCOM Antenna - Fuselage Skin Inspection: Do internal detailed and surface HFEC inspections of the visible fuselage skin in accordance with FIGURE 8. If a fuselage skin repair doubler is installed, do detailed and surface HFEC inspections of the visible doubler in the specified inspection area in accordance with the figure. Do external detailed and surface HFEC inspections of the visible fuselage skin in accordance with FIGURE 9. If a fuselage skin repair doubler is installed, do detailed and surface HFEC inspections of the visible doubler in the specified inspection area in accordance with the figure.
**NOTE:** Previous accomplishment of internal or external detailed inspection of the fuselage skin from STA 1601 to STA 1622 and from S-1L to S-1R meets the intent of the initial internal and external detailed and surface HFEC inspection of the visible fuselage skin. a. If any corrosion is found, do a repair in accordance with 777-200 SRM 53-00-01, 777-300 SRM 53-00-01, or 777F SRM 53-00-01; or contact Boeing for repair instructions and do the repair. General corrosion damage removal procedure and inspection is specified in 777-200 SRM 51-10-02, 777-300 SRM 51-10-02, or 777F SRM 51-10-02. (1) If a blend repair was accomplished within Allowable Damage 1 limits in accordance with 777-200 SRM 53-00-01, 777-300 SRM 53-00-01, or 777F SRM 53-00-01, repeat the internal and external detailed and surface HFEC inspections at the time given in Paragraph 1.E., Compliance.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 51 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**(2) If external repair doubler is necessary in accordance with 777 SRM, contact Boeing for repair instructions and do the repair to make sure that there is sufficient clearance between the fuselage skin or doubler, and fastener attaching the SATCOM lug adapter plate to the bonding jumper. If a fuselage skin repair doubler was installed, repeat the internal and external detailed and surface HFEC inspections at the time given in Paragraph 1.E., Compliance. b. If any crack is found, do a repair in accordance with 777-200 SRM 53-00-01, 777-300 SRM 53-00-01, or 777F SRM 53-00-01; or contact Boeing for repair instructions and do the repair. (1) If external repair doubler is necessary in accordance with 777 SRM, contact Boeing for repair instructions and do the repair to make sure that there is sufficient clearance between the fuselage skin or doubler, and fastener attaching the SATCOM lug adapter plate to the bonding jumper. (2) If a fuselage skin repair doubler was installed, repeat the internal and external detailed and surface HFEC inspections at the time given in Paragraph 1.E., Compliance. c. If any indication is found that shows a contact of the fastener attaching the SATCOM lug adapter plate to the bonding jumper, contact Boeing for repair instructions and do the repair. Indications of the fastener contact include imprint, gouge, rubbing, and scratch. After the repair, repeat the internal and external detailed and surface HFEC inspections at the time given in Paragraph 1.E., Compliance. **Group 1-4; Group 5, Configuration 3-4: Part 3 - Restoration** 
1. Internal Restoration a. Install insulation blankets. Refer to 777 AMM 25-80-00 as an accepted procedure. b. Install interior furnishings. Refer to 777 AMM 23-15-08 as an accepted procedure.
2. External Restoration a. Install the adapter plate. Refer to 777 AMM 53-61-51 as an accepted procedure for installing the adapter plate. Refer to SWPM 20-20-10 as an accepted procedure for installing the bonding jumper. After the installation of the fastener attaching the adapter plate to the bonding jumper, encapsulate the fastener, washer, nut, and periphery of the bonding jumper with BMS 5-95. Refer to SOPM 20-50-19 as an accepted procedure. Make sure there is no contact between the sealant of the cap sealed fastener and fuselage skin or doubler, if installed. Use of a boroscope or feeler gauge is an acceptable method to ensure there is no contact. 3. Install the SATCOM antenna. Refer to 777 AMM 23-15-23 as an accepted procedure. Close the circuit breaker to the SATCOM antenna. Refer to AMM 23-15-08 or 23-15-23 as an accepted procedure. 4. Put the airplane back to a serviceable condition.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 52 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT This Figure applies only to: Group 1-2.** 

**FIGURE 1: SECTION 46 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - MARK AND LOCATE FASTENER COMMON TO BONDING JUMPER AND ADAPTER PLATE**  **(SHEET 1 OF 2)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 53 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

**More Data Qty**  **Identification Name**  **Task Step**  (a)

- - FUSELAGE SKIN/DOUBLER Locate 1 (a) Directly under the fastener common to the adapter plate and bonding jumper, locate and mark the location of the fastener on the fuselage skin or doubler, if installed, within 0.25 inch using a felt tip marker. The location of the mark will be used to identify the inspection area in FIGURE 3.

**FIGURE 1: SECTION 46 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - MARK AND LOCATE FASTENER COMMON TO BONDING JUMPER AND ADAPTER PLATE**  **(SHEET 2 OF 2)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 54 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT This Figure applies only to: Group 1-2.** 

**FIGURE 2: SECTION 46 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - INTERNAL INSPECTION (SHEET 1 OF 3)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 55 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT FIGURE 2: SECTION 46 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - INTERNAL INSPECTION**  **(SHEET 2 OF 3)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 56 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

**More Data Qty**  **Identification Name**  **Task Step**  (a)

- - FUSELAGE SKIN/DOUBLER Inspect 1 (b)

- - FUSELAGE SKIN/DOUBLER Inspect 2 (a) Do a detailed inspection of the visible fuselage skin for cracks. Do the inspection in the area between STA 1567.5 and STA 1643, and S-2L and S-2R. If a fuselage skin repair doubler is installed, do a detailed inspection of the visible doubler in the specified inspection area. (b) Do a surface HFEC inspection of the visible fuselage skin for cracks in accordance with 777 NDT Manual Part 6, 51-00-01. If a fuselage skin repair doubler is installed, do a surface HFEC inspection of the visible doubler in the specified inspection area.

**FIGURE 2: SECTION 46 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - INTERNAL INSPECTION (SHEET 3 OF 3)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 57 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT This Figure applies only to: Group 1-2.** 

**FIGURE 3: SECTION 46 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - EXTERNAL INSPECTION (SHEET 1 OF 3)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 58 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT FIGURE 3: SECTION 46 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - EXTERNAL INSPECTION**  **(SHEET 2 OF 3)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 59 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

**More Data Qty**  **Identification Name**  **Task Step**  (a)

- - FUSELAGE SKIN/DOUBLER Inspect 1 (b)

- - FUSELAGE SKIN/DOUBLER Inspect 2 (c)

- - FUSELAGE SKIN/DOUBLER Inspect 3 (a) Do a detailed inspection of the visible fuselage skin for corrosion and cracks, and for any indication that shows a contact of the fastener attaching the SATCOM lug adapter plate to the bonding jumper. Do the inspection in the area between STA 1567.5 and STA 1643, and S-2L and S-2R. Indications of the fastener contact include imprint, gouge, rubbing, and scratch. If a fuselage skin repair doubler is installed, do a detailed inspection of the visible doubler in the specified inspection area. (b) Do a surface HFEC inspection of the visible fuselage skin for cracks in accordance with 777 NDT Manual Part 6, 51-00-01. The marked location on the fuselage was accomplished in FIGURE 1. If a fuselage skin repair doubler is installed, do a surface HFEC inspection of the visible doubler in the specified inspection area. (c) Do a surface HFEC inspection of the fuselage skin around the edge of the bonding jumper for cracks in accordance with 777 NDT Manual Part 6, 51-00-01. If a fuselage skin repair doubler is installed, do a surface HFEC inspection of the doubler in the specified inspection area.

**FIGURE 3: SECTION 46 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - EXTERNAL INSPECTION (SHEET 3 OF 3)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 60 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT This Figure applies only to: Group 2.** 

**FIGURE 4: SECTION 44 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - MARK AND LOCATE FASTENER COMMON TO BONDING JUMPER AND ADAPTER PLATE**  **(SHEET 1 OF 2)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 61 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

**More Data Qty**  **Identification Name**  **Task Step**  (a)

- - FUSELAGE SKIN/DOUBLER Locate 1 (a) Directly under the fastener common to the adapter plate and bonding jumper, locate and mark the location of the fastener on the fuselage skin or doubler, if installed, within 0.25 inch using a felt tip marker. The location of the mark will be used to identify the inspection area in FIGURE 6.

**FIGURE 4: SECTION 44 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - MARK AND LOCATE FASTENER COMMON TO BONDING JUMPER AND ADAPTER PLATE**  **(SHEET 2 OF 2)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 62 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT This Figure applies only to: Group 2.** 

**FIGURE 5: SECTION 44 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - INTERNAL INSPECTION (SHEET 1 OF 3)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 63 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT FIGURE 5: SECTION 44 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - INTERNAL INSPECTION**  **(SHEET 2 OF 3)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 64 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

**More Data Qty**  **Identification Name**  **Task Step**  (a)

- - FUSELAGE SKIN/DOUBLER Inspect 1 (b)

- - FUSELAGE SKIN/DOUBLER Inspect 2 (a) Do a detailed inspection of the visible fuselage skin for cracks. Do the inspection in the area between STA 1035 and STA 1119, and S-2L and S-2R. If a fuselage skin repair doubler is installed, do a detailed inspection of the visible doubler in the specified inspection area. (b) Do a surface HFEC inspection of the visible fuselage skin for cracks in accordance with 777 NDT Manual Part 6, 51-00-01. If a fuselage skin repair doubler is installed, do a surface HFEC inspection of the visible doubler in the specified inspection area.

**FIGURE 5: SECTION 44 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - INTERNAL INSPECTION (SHEET 3 OF 3)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 65 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT This Figure applies only to: Group 2.** 

**FIGURE 6: SECTION 44 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - EXTERNAL INSPECTION (SHEET 1 OF 3)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 66 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT FIGURE 6: SECTION 44 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - EXTERNAL INSPECTION**  **(SHEET 2 OF 3)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 67 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

**More Data Qty**  **Identification Name**  **Task Step**  (a)

- - FUSELAGE SKIN/DOUBLER Inspect 1 (b)

- - FUSELAGE SKIN/DOUBLER Inspect 2 (c)

- - FUSELAGE SKIN/DOUBLER Inspect 3 (a) Do a detailed inspection of the visible fuselage skin for corrosion and cracks, and for any indication that shows a contact of the fastener attaching the SATCOM lug adapter plate to the bonding jumper. Do the inspection in the area between STA 1567.5 and STA 1643, and S-2L and S-2R. Indications of the fastener contact include imprint, gouge, rubbing, and scratch. If a fuselage skin repair doubler is installed, do a detailed inspection of the visible doubler in the specified inspection area. (b) Do a surface HFEC inspection of the visible fuselage skin for cracks in accordance with 777 NDT Manual Part 6, 51-00-01. The marked location on the fuselage was accomplished in FIGURE 4. If a fuselage skin repair doubler is installed, do a surface HFEC inspection of the visible doubler in the specified inspection area. (c) Do a surface HFEC inspection of the fuselage skin around the edge of the bonding jumper for cracks in accordance with 777 NDT Manual Part 6, 51-00-01. If a fuselage skin repair doubler is installed, do a surface HFEC inspection of the doubler in the specified inspection area.

**FIGURE 6: SECTION 44 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - EXTERNAL INSPECTION (SHEET 3 OF 3)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 68 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT This Figure applies only to: Group 3-4; Group 5, Configuration 3-4.** 

**FIGURE 7: SECTION 46 - 2-BAY SATCOM ANTENNA - FUSELAGE SKIN - MARK AND LOCATE FASTENER COMMON TO BONDING JUMPER AND ADAPTER PLATE**  **(SHEET 1 OF 2)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 69 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

**More Data Qty**  **Identification Name**  **Task Step**  (a)

- - FUSELAGE SKIN/DOUBLER Locate 1 (a) Directly under the fastener common to the adapter plate and bonding jumper, locate and mark the location of the fastener on the fuselage skin or doubler, if installed, within 0.25 inch using a felt tip marker. The location of the mark will be used to identify the inspection area in FIGURE 9.

**FIGURE 7: SECTION 46 - 2-BAY SATCOM ANTENNA - FUSELAGE SKIN - MARK AND LOCATE FASTENER COMMON TO BONDING JUMPER AND ADAPTER PLATE**  **(SHEET 2 OF 2)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 70 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT This Figure applies only to: Group 3-4; Group 5, Configuration 3-4.** 

**FIGURE 8: SECTION 46 - 2-BAY SATCOM ANTENNA - FUSELAGE SKIN - INTERNAL INSPECTION (SHEET 1 OF 3)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 71 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT FIGURE 8: SECTION 46 - 2-BAY SATCOM ANTENNA - FUSELAGE SKIN - INTERNAL INSPECTION**  **(SHEET 2 OF 3)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 72 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

**More Data Qty**  **Identification Name**  **Task Step**  (a)

- - FUSELAGE SKIN/DOUBLER Inspect 1 (b)

- - FUSELAGE SKIN/DOUBLER Inspect 2 (a) Do a detailed inspection of the visible fuselage skin for cracks. Do the inspection in the area between STA 1580 and STA 1643, and S-2L and S-2R. If a fuselage skin repair doubler is installed, do a detailed inspection of the visible doubler in the specified inspection area. (b) Do a surface HFEC inspection of the visible fuselage skin for cracks in accordance with 777 NDT Manual Part 6, 51-00-01. If a fuselage skin repair doubler is installed, do a surface HFEC inspection of the visible doubler in the specified inspection area.

**FIGURE 8: SECTION 46 - 2-BAY SATCOM ANTENNA - FUSELAGE SKIN - INTERNAL INSPECTION (SHEET 3 OF 3)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 73 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT This Figure applies only to: Group 3-4; Group 5, Configuration 3-4.** 

**FIGURE 9: SECTION 46 - 2-BAY SATCOM ANTENNA - FUSELAGE SKIN - EXTERNAL INSPECTION (SHEET 1 OF 3)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 74 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT FIGURE 9: SECTION 46 - 2-BAY SATCOM ANTENNA - FUSELAGE SKIN - EXTERNAL INSPECTION**  **(SHEET 2 OF 3)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 75 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

**More Data Qty**  **Identification Name**  **Task Step**  (a)

- - FUSELAGE SKIN/DOUBLER Inspect 1 (b)

- - FUSELAGE SKIN/DOUBLER Inspect 2 (c)

- - FUSELAGE SKIN/DOUBLER Inspect 3 (a) Do a detailed inspection of the visible fuselage skin for corrosion and cracks, and for any indication that shows a contact of the fastener attaching the SATCOM lug adapter plate to the bonding jumper. Do the inspection in the area between STA 1580 and STA 1643, and S-2L and S-2R. Indications of the fastener contact include imprint, gouge, rubbing, and scratch. If a fuselage skin repair doubler is installed, do a detailed inspection of the visible doubler in the specified inspection area. (b) Do a surface HFEC inspection of the visible fuselage skin for cracks in accordance with 777 NDT Manual Part 6, 51-00-01. The marked location on the fuselage was accomplished in FIGURE 7. If a fuselage skin repair doubler is installed, do a surface HFEC inspection of the visible doubler in the specified inspection area. (c) Do a surface HFEC inspection of the fuselage skin around the edge of the bonding jumper for cracks in accordance with 777 NDT Manual Part 6, 51-00-01. If a fuselage skin repair doubler is installed, do a surface HFEC inspection of the doubler in the specified inspection area.

**FIGURE 9: SECTION 46 - 2-BAY SATCOM ANTENNA - FUSELAGE SKIN - EXTERNAL INSPECTION (SHEET 3 OF 3)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2013 777-53A0068 76 of 76 **BOEING SERVICE BULLETIN 777-53A0068 ALERT**  **ALERT**