### Commercial **Airplanes** 

# DC10 Service Bulletin **Number: DC10-53-182** Original Issue: June 28, 2013 ATA System: 5300 **SUBJECT:** FUSELAGE - Fuselage - Inspect/Change Left and Right Forward Cargo Compartment Frame to Cargo Liner Attachment Holes 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 Unpublished Work.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Original Issue: June 28, 2013 DC10-53-182 1 of 26 2.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 28, 2013 DC10-53-182 2 of 26 **BOEING SERVICE BULLETIN DC10-53-182**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION ........................................ 7 A. Effectivity................................................ 7 1. Airplanes............................................. 7 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 14 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 14 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 14 M. Software Accomplishment Summary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 C. Parts Necessary for Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 16 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 17 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 FIGURE 1: REMOVE CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT FASTENERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 FIGURE 2: INSPECT CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT HOLES . 23 FIGURE 3: CHANGE CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT HOLES . 25

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 28, 2013 DC10-53-182 3 of 26 **BOEING SERVICE BULLETIN DC10-53-182**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 28, 2013 DC10-53-182 4 of 26 **BOEING SERVICE BULLETIN DC10-53-182**

BLANK PAGE

### Commercial **Airplanes** 

# DC10 Service Bulletin **Summary Number: DC10-53-182**  Original Issue: June 28, 2013 ATA System: 5300 **SUBJECT:** FUSELAGE - Fuselage - Inspect/Change Left and Right Forward Cargo Compartment Frame to Cargo Liner Attachment Holes **CONCURRENT REQUIREMENTS** None. **BACKGROUND** Federal Aviation Administration (FAA) requirement 14 Code of Federal Regulations (CFR) Part 26.21, Amendment 26-6 with effective date May 24/2012, requires the establishment of a binding schedule for the release of new service actions (Service Bulletins) to support Widespread Fatigue Damage (WFD) rules Limit of Validity (LOV) from current regulatory limits, refer to 14 CFR Part 121.1115. To extend the LOV for airplanes in Paragraph 1.A.1, Effectivity, beyond the FAA published dates in Table 1 of 14 CFR Part 121.1115, new service actions have been identified. Inspecting and changing the frame fastener holes in the forward cargo compartment will extend the LOV. If the inspection and modification is not completed, there may be undetected cracks in the fastener holes which could result in the loss of fail safe structural integrity. The left and right forward cargo compartment frames have been determined to be structure that is susceptible to Widespread Fatigue Damage (WFD). **ACTION** This service bulletin provides instructions to do as follows: 1. Remove fasteners in the left and right hand sides of the forward cargo compartment. 2. Do an Eddy Current High Frequency (ETHF) inspection of the open fastener holes for cracks. Based on inspection findings do what follows: Condition 1 - No Crack Detected a. Install Hi-Loks. Condition 2 - Crack Detected in Any Hole a. Contact Boeing to get instructions for the repair for this service bulletin, and do the work instructed by Boeing. **EFFECTIVITY** DC-10-10, DC-10-10F, DC-10-30, DC-10-30F, DC-10-40, MD-10-10F, and MD-10-30F Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 28, 2013 DC10-53-182 5 of 26**COMPLIANCE** The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Refer to Paragraph 1.E., Compliance. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the inspection and/or repair procedures given in this service bulletin. **MANPOWER** Refer to Paragraph 1.G., Manpower. **MATERIAL INFORMATION** Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 28, 2013 DC10-53-182 6 of 26 **BOEING SERVICE BULLETIN DC10-53-182**

### Commercial **Airplanes** 

# DC10 Service Bulletin **Number: DC10-53-182** Original Issue: June 28, 2013 ATA System: 5300 **SUBJECT:** FUSELAGE - Fuselage - Inspect/Change Left and Right Forward Cargo Compartment Frame to Cargo Liner Attachment Holes
**1. PLANNING INFORMATION A. Effectivity**  1. Airplanes

**DESCRIPTION CONFIGURATION**  **GROUP** Airplanes with regular size forward cargo door.

- 1 Airplanes with oversize forward cargo door.

- 2

Airplane Models: DC-10-10, DC-10-10F, DC-10-30, DC-10-30F, DC-10-40, MD-10-10F, MD-10-30F **Group Fuselage Num-**  **ber** 1 1 1 2 1 3 1 4 1 5 1 6 1 7 1 8 1 9 1 10 1 11 1 12

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 28, 2013 DC10-53-182 7 of 26**Group Fuselage Num-**  **ber** 1 13 1 14 1 15 1 16 1 17 1 18 1 19 1 20 1 21 1 22 1 23 1 24 1 25 1 26 1 27 2 28 1 29 1 30 1 31 1 32 1 33 2 34 1 35 2 36 1 37 1 38 1 39 2 40 2 41 1 42 2 43 2 44

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 28, 2013 DC10-53-182 8 of 26 **BOEING SERVICE BULLETIN DC10-53-182 Group**  **Fuselage Num- ber**  1 45 2 46 1 47 1 48 1 49 1 50 1 51 1 52 2 53 1 54 1 55 1 56 2 57 1 58 1 59 2 60 1 61 1 62 2 63 1 64 1 65 2 66 1 67 1 68 2 69 1 70 2 71 1 72 2 73 1 74 2 75 1 76

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 28, 2013 DC10-53-182 9 of 26 **BOEING SERVICE BULLETIN DC10-53-182 Group**  **Fuselage Num- ber**  2 77 1 78 2 79 1 80 1 81 2 82 1 83 2 84 2 85 1 86 2 87 2 88 1 89 2 90 2 91 2 92 2 93 2 94 1 95 1 96 2 97 2 98 2 99 2 100 - 102 1 103 2. Spares Affected None. **B. Concurrent Requirements** None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 28, 2013 DC10-53-182 10 of 26 **BOEING SERVICE BULLETIN DC10-53-182 C. Reason**  Federal Aviation Administration (FAA) requirement 14 Code of Federal Regulations (CFR) Part 26.21, Amendment 26-6 with effective date May 24/2012, requires the establishment of a binding schedule for the release of new service actions (Service Bulletins) to support Widespread Fatigue Damage (WFD) rules Limit of Validity (LOV) from current regulatory limits, refer to 14 CFR Part 121.1115. To extend the LOV for airplanes in Paragraph 1.A.1, Effectivity, beyond the FAA published dates in Table 1 of 14 CFR Part 121.1115, new service actions have been identified. Inspecting and changing the frame fastener holes in the forward cargo compartment will extend the LOV. If the inspection and modification is not completed, there may be undetected cracks in the fastener holes which could result in the loss of fail safe structural integrity. The left and right forward cargo compartment frames have been determined to be structure that is susceptible to Widespread Fatigue Damage (WFD). **D. Description** This service bulletin provides instructions to do as follows: 1. Remove fasteners in the left and right hand sides of the forward cargo compartment. 2. Do an Eddy Current High Frequency (ETHF) inspection of the open fastener holes for cracks. Based on inspection findings do what follows: Condition 1 - No Crack Detected a. Install Hi-Loks. Condition 2 - Crack Detected in Any Hole a. Contact Boeing to get instructions for the repair for this service bulletin, and do the work instructed by Boeing. The work in this service bulletin is done in the maintenance zone(s) given below. **Group 1:**
**Affected Maintenance Zones Zone**  **Model** 125, 126 DC-10-10, DC-10-10F, DC-10- 30F, MD-10-10F, MD-10-30F **Group 2:**
**Affected Maintenance Zones Zone**  **Model** 125, 126 DC-10-10, DC-10-10F, DC-10- 30, DC-10-40

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 28, 2013 DC10-53-182 11 of 26 **BOEING SERVICE BULLETIN DC10-53-182 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. Do the required actions in accordance with Paragraph 3. Accomplishment Instructions. **Table 1: High Frequency Eddy Current Inspection for Cracks in Fuselage Frame Holes Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition**

- Within 72 months after the original issuedate of this service bulletin. Before 30,000total flight cycles. Do an Eddy Current HighFrequency (ETHF) inspection of left and right forward cargo compartmentframe to cargo liner attachment holes for cracks and do the work of the applicable condition that follows. All Airplanes

- - Before further flight. Install Hi-Loks. Condition 1 - No Crack De- tected.

- - Before further flight.Contact Boeing to get instructions for the repair for this service bulletinand do the work instructed by Boeing.Condition 2 - Crack Detected in Any Hole.

**F. Approval** For DC-10 Series Airplanes: 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. For MD-10 Series Airplanes: 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. 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 28, 2013 DC10-53-182 12 of 26 **BOEING SERVICE BULLETIN DC10-53-182**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 inspection/modification 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 1: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 2.0 2.0 1 FIGURE 1 16.0 16.0 1 FIGURE 2 5.0 5.0 1 FIGURE 3 23.0 23.0 TOTAL FOR EACH AIRPLANE
**NOTE:** Task hours for the repair of crack damage, if any, are not listed. **Group 2: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 2.5 2.5 1 FIGURE 1 16.5 16.5 1 FIGURE 2 5.5 5.5 1 FIGURE 3 24.5 24.5 TOTAL FOR EACH AIRPLANE
**NOTE:** Task hours for the repair of crack damage, if any, are not listed. **H. Weight and Balance Changes**
**Moment Change (MEW) IN.-LBS**  **Mfr's Empty Weight (MEW)**  **LBS Approximate Sta**  **tion (Inches) Kit SB10530182**  +255.0 +0.3 +1010.6 -3 +299.1 +0.3 +997.0 -5

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 28, 2013 DC10-53-182 13 of 26 **BOEING SERVICE BULLETIN DC10-53-182 I. Electrical Load Data**  Not changed. **J. References** 1. Existing Data: a. Nondestructive Testing Standard Practice Manual (NDTSPM) (Publication MDC 93K0393), Part 06 Eddy Current b. DC-10, MD-10 Structural Repair Manual (SRM) Chapter 51 c. DC-10 Widespread Fatigue Damage / Limit of Validity (WFD/LOV) Document MDC 12K1003 2. Data Supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: **Change Title**  **Document Number** NEW FWD CARGO FRAME - INSPEC- TION AND MOD SR10530096
The table above lists the applicable drawing used to prepare this service bulletin. The drawing is not necessary to make the specified changes, and is not supplied with this service bulletin. The drawing 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 28, 2013 DC10-53-182 14 of 26 **BOEING SERVICE BULLETIN DC10-53-182 2. MATERIAL INFORMATION**  **A. Material - Price and Availability** Boeing can supply the kits 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 kits 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** 
**Unit Price as of the original issue** **date of this Ser vice Bulletin (US**  **Dollars) ROLT as of the**  **original issue date of this Ser** **vice Bulletin (Cal endar Days)**  **Name Kit Number** 

$762.00 60 days FWD CARGO FRAME - INSPECTION AND MOD SB10530182-3 $801.00 60 days FWD CARGO FRAME - INSPECTION AND MOD SB10530182-5

**B. Industry Support Information** Boeing warranty remedies are not available for the inspection and/or repair procedures given in this service bulletin. **C. Parts Necessary for Each Airplane** 1. Kits/Parts To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. **NOTE:** One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. **Group 1:**
**Kit SB10530182 Notes**  **Existing Part Number**  **Name QTY**  **New Part Number -3** 

- - - - SB10530182-3

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 28, 2013 DC10-53-182 15 of 26 **BOEING SERVICE BULLETIN DC10-53-182 Group 1:** 
**Kit SB10530182 Notes**  **Existing Part Number**  **Name QTY**  **New Part Number -3**  (a) (b) MS20470AD5 PIN-OVERSIZE 76 HLT426-6-2

- - NUT 76 MS21042L3

- - WASHER 76 NAS1252-10L (a) Discard the existing part. (b) May be purchased from: Hi-Shear Corporation, 2600 Skypark Drive Torrance, California 90505; CAGE 73197 **Group 2:**
**Kit SB10530182 Notes**  **Existing Part Number**  **Name QTY**  **New Part Number -5** 

- - - - SB10530182-5 (a) (b) MS20470AD5 PIN-OVERSIZE 80 HLT426-6-2

- - NUT 80 MS21042L3

- - WASHER 80 NAS1252-10L (a) Discard the existing part. (b) May be purchased from: Hi-Shear Corporation, 2600 Skypark Drive Torrance, California 90505; CAGE 73197 2. Parts and Materials Supplied by the Operator The following parts or materials are necessary to do the change in this service bulletin. Parts and materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine operator part and material supply to make sure all necessary parts and materials are available.
**Notes Name**  **QTY Part Number /**  **Specification** (a) Sealant, Low Viscosity 3 Pt. P/S 870 C-12/20 (DMS 2013 Type 1Class A) or Equivalent) (a) Can be purchased from: PRC-DeSoto International 12780 San Fernando Road, Sylmar, CA. 91342; CAGE 92108.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 28, 2013 DC10-53-182 16 of 26 **BOEING SERVICE BULLETIN DC10-53-182**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 28, 2013 DC10-53-182 17 of 26 **BOEING SERVICE BULLETIN DC10-53-182**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 28, 2013 DC10-53-182 18 of 26 **BOEING SERVICE BULLETIN DC10-53-182**

BLANK PAGE**3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION**  **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. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Equivalent parts are listed in the AEPL, Drawing 7595071. 3. Use the approved fastener, process material substitutions, and installation in accordance with DC-10, MD-10 SRM Chapter 51. 4. If the length of any fastener specified in this service bulletin does not meet installation standards given in Structural Repair Manual (SRM) Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. 5. 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. 6. 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 are in DC-10, MD-10 SRM Chapter 51. – Torque limits to tighten nuts and bolts are in DC-10, MD-10 SRM Chapter 51. 7. Obey all of the warnings and cautions given in the specified manual sections.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 28, 2013 DC10-53-182 19 of 26 **BOEING SERVICE BULLETIN DC10-53-182**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. 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. 10. Shaded areas in Figures are reference only. Shaded areas in Figures may look different than your airplane. 11. When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION numbers for that CONDITION number or OPTION number. 12. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS are in Paragraph 1.E., Compliance. **B. WORK INSTRUCTIONS** 1. Remove fasteners in accordance with FIGURE 1. 2. Do an Eddy Current High Frequency (ETHF) inspection of the frame open fastener holes in accordance with FIGURE 2, based on inspection findings do as follows: Condition 1 - No Crack Detected a. Install Hi-Loks in accordance with FIGURE 3. b. Return airplane to serviceable condition. Condition 2 - Crack Detected in Any Hole a. Contact Boeing to get instructions for the repair for this service bulletin, and do the work instructed by Boeing. b. Return airplane to serviceable condition.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 28, 2013 DC10-53-182 20 of 26 **BOEING SERVICE BULLETIN DC10-53-182 FIGURE 1: REMOVE CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT FASTENERS**  **(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 28, 2013 DC10-53-182 21 of 26 **BOEING SERVICE BULLETIN DC10-53-182**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
**More Data Qty**  **Identification Name**  **Task Step** 

- MS20470AD5 RIVET Remove 1

**FIGURE 1: REMOVE CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT FASTENERS (SHEET 2 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 28, 2013 DC10-53-182 22 of 26 **BOEING SERVICE BULLETIN DC10-53-182 FIGURE 2: INSPECT CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT HOLES**  **(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 28, 2013 DC10-53-182 23 of 26 **BOEING SERVICE BULLETIN DC10-53-182**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) 4
- HOLE Inspect 1 (a) Refer to Nondestructive Testing Standard Practice Manual NDTSPM Part 06 Eddy Current, Procedure 3, 06-10-01.003 as an accepted procedure.

**FIGURE 2: INSPECT CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT HOLES (SHEET 2 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 28, 2013 DC10-53-182 24 of 26 **BOEING SERVICE BULLETIN DC10-53-182 FIGURE 3: CHANGE CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT HOLES**  **(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 28, 2013 DC10-53-182 25 of 26 **BOEING SERVICE BULLETIN DC10-53-182**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 each frame.
**More Data Qty**  **Identification Name**  **Task Step**  (a) (b) (c) 4 HLT426-6-2 PIN-OVERSIZE Install (New) 1 (b) 4 MS21042L3 NUT Install (New) (b) 4 NAS1252-10L WASHER Install (New) (a) Hole diameter 0.1981-0.2011 (b) Refer to DC-10, MD-10 SRM Chapter 51 as an accepted procedure. (c) Install fasteners with DMS 2013 Type 1 Class A or equivalent sealant. Refer to DC-10, MD-10 SRM Chapter 51 as an accepted procedure.

**FIGURE 3: CHANGE CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT HOLES (SHEET 2 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 28, 2013 DC10-53-182 26 of 26 **BOEING SERVICE BULLETIN DC10-53-182**