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

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ECCN: 9E991

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Unpublished Work. All Rights Reserved.

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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

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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).

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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.

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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

GROUP CONFIGURATION DESCRIPTION

1 - Airplanes with regular size forward cargo door.

2 - Airplanes with oversize forward cargo door.

Airplane Models:

DC-10-10, DC-10-10F, DC-10-30, DC-10-30F, DC-10-40, MD-10-10F, MD-10-30F

Fuselage Num- Group

ber

1 1

2 1

3 1

4 1

5 1

6 1

7 1

8 1

9 1

10 1

11 1

12 1

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Fuselage Num- Group

ber

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 1

28 2

29 1

30 1

31 1

32 1

33 1

34 2

35 1

36 2

37 1

38 1

39 1

40 2

41 2

42 1

43 2

44 2

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Fuselage Num- Group

ber

45 1

46 2

47 1

48 1

49 1

50 1

51 1

52 1

53 2

54 1

55 1

56 1

57 2

58 1

59 1

60 2

61 1

62 1

63 2

64 1

65 1

66 2

67 1

68 1

69 2

70 1

71 2

72 1

73 2

74 1

75 2

76 1

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Fuselage Num- Group

ber

77 2

78 1

79 2

80 1

81 1

82 2

83 1

84 2

85 2

86 1

87 2

88 2

89 1

90 2

91 2

92 2

93 2

94 2

95 1

96 1

97 2

98 2

99 2

100 - 102 2

103 1

2. Spares Affected

None.

B. Concurrent Requirements

None.

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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

Model Zone

DC-10-10, DC-10-10F, DC-10- 125, 126

30F, MD-10-10F, MD-10-30F

Group 2:

Affected Maintenance Zones

Model Zone

DC-10-10, DC-10-10F, DC-10- 125, 126

30, DC-10-40

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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)

Condition Action

Within 72 -

months after the

original issue

date of this service bulletin.

Before 30,000

total flight cycles.

Do an Eddy Current High

Frequency (ETHF) inspection of left and right forward cargo compartment

frame to cargo liner attachment holes for cracks

and do the work of the

applicable condition that

follows.

All Airplanes

Before further - -

flight.

Condition 1 - No Crack De- Install Hi-Loks.

tected.

Before further - -

flight.

Contact Boeing to get instructions for the repair

for this service bulletin

and 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.

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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:

Task Number of Persons Task Hours Elapsed Hours

FIGURE 1 1 2.0 2.0

FIGURE 2 1 16.0 16.0

FIGURE 3 1 5.0 5.0

TOTAL FOR EACH AIRPLANE 23.0 23.0

NOTE: Task hours for the repair of crack damage, if any, are not listed.

Group 2:

Task Number of Persons Task Hours Elapsed Hours

FIGURE 1 1 2.5 2.5

FIGURE 2 1 16.5 16.5

FIGURE 3 1 5.5 5.5

TOTAL FOR EACH AIRPLANE 24.5 24.5

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 StaKit SB10530182 tion (Inches)

-3 +1010.6 +0.3 +255.0

-5 +997.0 +0.3 +299.1

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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:

Document Number Title Change

FWD CARGO FRAME - INSPEC- NEW

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.

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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 Service Bulletin (US

Dollars)

ROLT as of the

original issue

date of this Service Bulletin (Calendar Days)

Kit Number Name

FWD CARGO FRAME - INSPECTION AND 60 days $762.00

MOD

SB10530182-3

FWD CARGO FRAME - INSPECTION AND 60 days $801.00

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

Existing Part Notes

Number

New Part Number QTY Name

-3

SB10530182-3 - - - -

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BOEING SERVICE BULLETIN DC10-53-182
Group 1:

Kit SB10530182

Existing Part Notes

Number

New Part Number QTY Name

-3

HLT426-6-2 76 PIN-OVERSIZE MS20470AD5 (a) (b)

MS21042L3 76 NUT - -

NAS1252-10L 76 WASHER - -

(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

Existing Part Notes

Number

New Part Number QTY Name

-5

SB10530182-5 - - - -

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

MS21042L3 80 NUT - -

NAS1252-10L 80 WASHER - -

(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.

Part Number / QTY Name Notes

Specification

P/S 870 C-12/20 3 Pt. Sealant, Low Viscosity (a)

(DMS 2013 Type 1

Class A) or Equivalent)

(a) Can be purchased from: PRC-DeSoto International 12780 San Fernando Road, Sylmar,

CA. 91342; CAGE 92108.

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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.

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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.

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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.

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BOEING SERVICE BULLETIN DC10-53-182
FIGURE 1: REMOVE CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT FASTENERS

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN DC10-53-182
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

Step Task Name Identification Qty More Data

1 Remove RIVET MS20470AD5 -

FIGURE 1: REMOVE CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT FASTENERS

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN DC10-53-182
FIGURE 2: INSPECT CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT HOLES

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN DC10-53-182
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

Step Task Name Identification Qty More Data

1 Inspect HOLE - 4 (a)

(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)

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BOEING SERVICE BULLETIN DC10-53-182
FIGURE 3: CHANGE CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT HOLES

(SHEET 1 OF 2)

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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.

Step Task Name Identification Qty More Data

1 Install (New) PIN-OVERSIZE HLT426-6-2 4 (a) (b) (c)

Install (New) NUT MS21042L3 4 (b)

Install (New) WASHER NAS1252-10L 4 (b)

(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)

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BOEING SERVICE BULLETIN DC10-53-182