### Commercial **Airplanes** 

# MD11 Service Bulletin **SPECIAL ATTENTION Number: MD11-55-027**  Original Issue: March 17, 2011 ATA System: 5510 **SUBJECT:** STABILIZERS - Horizontal Stabilizer - Change Rub Strips of Tail Fuel Tank Center Box Front Spar Access Doors Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). 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## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2011 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. 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, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 17, 2011 MD11-55-027 1 of 18 3.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 17, 2011 MD11-55-027 2 of 18 **BOEING SERVICE BULLETIN MD11-55-027**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION ........................................ 7 A. Effectivity................................................ 7 1. Airplanes ............................................. 7 2. Spares Affected ......................................... 7 B. Concurrent Requirements....................................... 7 C. Reason................................................. 8 D. Description ............................................... 8 E. Compliance .............................................. 8 F. Approval ................................................ 8 G. Manpower ............................................... 8 H. Weight and Balance Changes .................................... 9 I. Electrical Load Data.......................................... 9 J. References .............................................. 9 1. Existing Data .......................................... 9 2. Data supplied with this Service Bulletin ............................ 9 3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 9 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 12 3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 12 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 FIGURE 1: CHANGE RUB STRIPS OF TAIL FUEL TANK CENTER BOX FRONT SPAR ACCESS DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 17, 2011 MD11-55-027 3 of 18 **BOEING SERVICE BULLETIN MD11-55-027**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 17, 2011 MD11-55-027 4 of 18 **BOEING SERVICE BULLETIN MD11-55-027**

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### Commercial **Airplanes** 

# MD11 Service Bulletin **SPECIAL ATTENTION Summary**  **Number: MD11-55-027** Original Issue: March 17, 2011 ATA System: 5510 **SUBJECT:** STABILIZERS - Horizontal Stabilizer - Change Rub Strips of Tail Fuel Tank Center Box Front Spar Access Doors BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. **CONCURRENT REQUIREMENTS** None. **BACKGROUND** An investigation by Boeing revealed that the rub strips of tail fuel tank center box front spar access doors were manufactured improperly. Tail center box fuel tank front spar access door rub strips were inadvertently anodized (electrically non-conductive) instead of alodined (electrically conductive) as prescribed in design drawings. Anodization of the rub strips may prevent adequate electrical bonding between the rub strips and the doors. Replacing anodized rub strips with alodined rub strips will provide adequate electrical bonding between the rub strips and the fuel access doors. If not corrected, inadequate electrical bonding can contribute to possible ignition of flammable fuel vapor in the tail fuel tank as a result of a lightning strike. **ACTION** This service bulletin provides instructions to change the rub strips of the tail fuel tank center box front spar access doors. **EFFECTIVITY** MD-11 and MD-11F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. **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. Boeing recommends that the rub strips of the tail fuel tank center box front spar access doors be changed within 60 months after the original issue date on this service bulletin. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are available for airplanes in warranty as of July 21, 2010. Please refer to Paragraph 2.B., Industry Support Information.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 17, 2011 MD11-55-027 5 of 18**MANPOWER Elapsed Hours**  **Total Task Hours Airplanes**  16.0 32.0 MD-11, MD-11F
**MATERIAL INFORMATION** Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 17, 2011 MD11-55-027 6 of 18 **BOEING SERVICE BULLETIN MD11-55-027**

### Commercial **Airplanes** 

# MD11 Service Bulletin **SPECIAL ATTENTION Number: MD11-55-027**  Original Issue: March 17, 2011 ATA System: 5510 **SUBJECT:** STABILIZERS - Horizontal Stabilizer - Change Rub Strips of Tail Fuel Tank Center Box Front Spar Access Doors BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. **1. PLANNING INFORMATION A. Effectivity**  1. Airplanes This service bulletin is for the airplanes shown below.

**DESCRIPTION CONFIGURATION**  **GROUP** Change Rub Strips of Tail Fuel Tank Center Box Front Spar Access Doors for Fuselage Number 447 - 613 - 1

Airplane Models: MD-11, MD-11F **Group Fuselage Num-**  **ber** 1 447 - 613 2. Spares Affected None. **B. Concurrent Requirements** None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 17, 2011 MD11-55-027 7 of 18**C. Reason** An investigation by Boeing revealed that the rub strips of tail fuel tank center box front spar access doors were manufactured improperly. Tail center box fuel tank front spar access door rub strips were inadvertently anodized (electrically non-conductive) instead of alodined (electrically conductive) as prescribed in design drawings. Anodization of the rub strips may prevent adequate electrical bonding between the rub strips and the doors. Replacing anodized rub strips with alodined rub strips will provide adequate electrical bonding between the rub strips and the fuel access doors. If not corrected, inadequate electrical bonding can contribute to possible ignition of flammable fuel vapor in the tail fuel tank as a result of a lightning strike. **D. Description** This service bulletin provides instructions to change the rub strips of the tail fuel tank center box front spar access doors. The work in this service bulletin is done in the maintenance zone(s) given below.
**Affected Maintenance Zones Zone**  **Model** 189 MD-11, MD-11F **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. Boeing recommends that the rub strips of the tail fuel tank center box front spar access doors be changed within 60 months after the original issue date on this service bulletin. **F. Approval** This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. **G. Manpower** The table below shows an estimate of the task hours necessary to do this change 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:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 17, 2011 MD11-55-027 8 of 18 **BOEING SERVICE BULLETIN MD11-55-027**• 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.

**Elapsed Hours Task Hours**  **Number of Persons Task**  5.0 10.0 2 Defuel and Purge 1.0 2.0 2 Remove Fuel Tank Access Doors 7.5 15.0 2 Change Rub Strips 1.0 2.0 2 Install Fuel Tank Ac- cess Doors 1.5 3.0 2 Leak Check 16.0 32.0 TOTAL FOR EACH AIRPLANE **H. Weight and Balance Changes** None. **I. Electrical Load Data** Not changed. **J. References** 1. Existing Data a. MD-11, MD-11F Aircraft Maintenance Manual (AMM) 52-57-19. b. MD-11, MD-11F Structural Repair Manual (SRM) 51-42-07. 2. Data supplied with this Service Bulletin None. 3. Installation Drawings Used in the Preparation of this Service Bulletin **Change Title**  **Document Number** Z, AEO AA SPAR ASSY - CONSTANT HORIZ STAB, FORWARD ALC8020

This drawing was used to prepare this service bulletin. This drawing is not necessary to make the specified changes, and is not supplied with this service bulletin. This drawing may not be applicable to all airplane configurations or operators.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 17, 2011 MD11-55-027 9 of 18 **BOEING SERVICE BULLETIN MD11-55-027 K. Publications Affected**  1. Publications: **Chapter-Section Publication**  51-42-07 Structural Repair Manual 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 does not affect FCS, therefore DTIs are not necessary. **L. Interchangeability and Intermixability of Parts** Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability information.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 17, 2011 MD11-55-027 10 of 18 **BOEING SERVICE BULLETIN MD11-55-027 2. MATERIAL INFORMATION**  **A. Material - Price and Availability** Boeing can supply the parts shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The parts are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145 **REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION**  **ROLT as of the original issue date of this Service**  **Bulletin (Calendar Days) QTY**  **Name Part Number** 

60 2 RUB STRIP ALC8028-1 60 36 RIVET BACR15BA3AD8C **B. Industry Support Information** Boeing warranty remedies are available for MD-11 airplanes in warranty as of July 21, 2010. For task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Commercial Airplanes Group - Warranties. The parts for airplanes in warranty as of that date will be supplied at no charge. Send a purchase order for the parts to Boeing Spares. Please refer to this service bulletin number and reference the airplane fuselage number in your purchase order. Boeing Commercial Airplanes Group - Warranties P.O. Box 3707 M/C 2L-46 Seattle, Washington 98124-2207 USA (Service Bulletin MD11-55-027) **C. Parts Necessary For Each Airplane** 1. Kits/Parts To get the parts shown below, refer to Paragraph 2.A., Material - Price and Availability. **NOTE:** The parts shown below and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 17, 2011 MD11-55-027 11 of 18 **BOEING SERVICE BULLETIN MD11-55-027 Notes**  **Existing Part Name**  **QTY New Part Number**  (a) ALC8028-1 RUB STRIP 2 ALC8028-1 (b) MS20426AD3 RIVET 36 BACR15BA3AD8C (a) Alodined rub strip, part number ALC8028-1 replaces existing anodized rub strip part number ALC8028-1. (b) Alodined rivet, part number BACR15BA3AD8C replaces existing rivet, part number MS20426AD3. 2. Parts and Materials Supplied by the Operator
**Notes Name**  **QTY Part Number /**  **Specification** (a) Sealing Compound, Integral Fuel Tanks and Fuel Cell Cavities 1 Quart PR-1422 B-2 (DMS 2082 B-2) or Equivalent
CAGE PRC-DeSoto International, Incorporation (a) Can be purchased from: 83574 24811 Avenue Rockefeller Valencia, California 91355-3468

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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 17, 2011 MD11-55-027 12 of 18 **BOEING SERVICE BULLETIN MD11-55-027 3. ACCOMPLISHMENT INSTRUCTIONS**  **A. GENERAL INFORMATION WARNING:**  WHILE YOU DO WORK IN THE TAILCONE AREA, MAKE SURE THAT YOU OBEY ALL SAFETY PRECAUTIONS. IF YOU DO NOT OBEY THE PRECAUTIONS, DEATH OR INJURY TO PERSONS CAN OCCUR. **WARNING:** IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE CAN OCCUR. **CAUTION:** ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE TO THE AIRPLANE OR EQUIPMENT. **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. The instructions identified in Paragraph 3.B., Work Instructions, and the Figure(s) give the recommended sequence of steps. The sequence of steps to do this service bulletin can be changed. 2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 3. Equivalent parts are listed in the AEPL, Drawing 7595071. 4. Use the approved fastener and process material substitutions, in accordance with Structural Repair Manual MD-11, MD11F SRM 51. 5. If the length of any fastener specified in this service bulletin does not meet installation standards given in MD-11, MD-11F SRM 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in MD-11, MD-11F SRM 51 may be used. In addition, washers may be installed for fastener grip length in accordance with MD-11, MD-11F SRM 51. 6. A 1/8-inch thick stack of the same type washers called for in this service bulletin is the maximum thickness which may be used under fastener head or nut to counteract accumulation of tolerances. EXCEPTION: When the available fastener length increments are greater than 1/16-inch, a 3/16-inch thick stack of the same type washers may be used. 7. 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 17, 2011 MD11-55-027 13 of 18 **BOEING SERVICE BULLETIN MD11-55-027**– Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets are in Structural Repair Manual MD-11, MD-11F SRM 51 – Torque limits to tighten nuts and bolts are in MD-11, MD-11F SRM 51. 8. 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. 9. 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. The removed part can be discarded if a new or serviceable part is installed. 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. **B. WORK INSTRUCTIONS** 1. Remove and keep tail fuel tank center box front spar access doors 352AZ and 352BZ. Refer to MD-11, MD-11F AMM 52-57-19 as an accepted procedure. 2. Change rub strips in accordance with Figure 1 and MD-11, MD-11F SRM 51-42-07. **NOTE:** Proper installation of the rub strips prevents fuel leaks and sparking during a lightning strike to the airplane. 3. Install kept tail fuel tank center box front spar access doors 352AZ and 352BZ. Refer to MD-11, MD-11F AMM 52-57-19 as an accepted procedure. 4. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 17, 2011 MD11-55-027 14 of 18 **BOEING SERVICE BULLETIN MD11-55-027 FIGURE 1: CHANGE RUB STRIPS OF TAIL FUEL TANK CENTER BOX FRONT SPAR ACCESS DOOR**  **(SHEET 1 OF 4)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 17, 2011 MD11-55-027 15 of 18 **BOEING SERVICE BULLETIN MD11-55-027 FIGURE 1: CHANGE RUB STRIPS OF TAIL FUEL TANK CENTER BOX FRONT SPAR ACCESS DOOR**  **(SHEET 2 OF 4)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 17, 2011 MD11-55-027 16 of 18 **BOEING SERVICE BULLETIN MD11-55-027 FIGURE 1: CHANGE RUB STRIPS OF TAIL FUEL TANK CENTER BOX FRONT SPAR ACCESS DOOR**  **(SHEET 3 OF 4)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 17, 2011 MD11-55-027 17 of 18 **BOEING SERVICE BULLETIN MD11-55-027**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for the figure.
**MORE DATA QTY**  **IDENTIFICA- TION**  **NAME TASK**  **STEP** (a) 36 MS20426AD3 Rivet Remove (Dis- card) 1

2 ALC8028-1 Rub Strip Remove (Dis- card) 2 3D0292-1 Gang Channel Remove (Keep)

- PR-1422 B-2 Sealant Remove (Dis- card) (DMS 2082 B-2)

- PR-1422 B-2 Sealant Apply (New) 2 (DMS 2082 B-2) 2 ALC8028-1 Rub Strip Install (New) 2 ALC8028-1 Rub Strip Drill 2 3D0292-1 Gang Channel Install (Kept) 36 BACR15BA3AD8C Rivet Install (New) (a) In accordance with MD-11, MD-11F SRM 51-42-07.

**FIGURE 1: CHANGE RUB STRIPS OF TAIL FUEL TANK CENTER BOX FRONT SPAR ACCESS DOOR (SHEET 4 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 17, 2011 MD11-55-027 18 of 18 **BOEING SERVICE BULLETIN MD11-55-027**