Commercial 

Airplanes 727

Service Bulletin

SPECIAL ATTENTION

Number: 727-57-0187

Original Issue: March 08, 2012

ATA System: 5714

SUBJECT: WINGS - Wing Center Box - Upper Skin and Rear Spar Upper Chord Inspection

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.

ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET

Copyright © 2012 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Unpublished Work - All Rights Reserved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

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3.0
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BOEING SERVICE BULLETIN 727-57-0187

BLANK PAGE
Table of Contents

Summary ...................................................... 5

1. PLANNING INFORMATION ........................................ 9

A. Effectivity ................................................ 9

1. Airplanes ............................................. 9

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

1. Existing Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

2. Data supplied with this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

3. Installation Drawings Used in the Preparation of this Service Bulletin . . . . . . . . . . . . 22

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 25

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 26

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

FIGURE 1: WINGS - WING CENTER BOX - INTERNAL FUEL TANK INSPECTION OF THE REAR SPAR

UPPER CHORD HORIZONTAL FLANGE . . . . . . . . . . . . . . . . . . . . . . . . . . 32

FIGURE 2: WINGS - WING CENTER BOX - INTERNAL FUEL TANK INSPECTION OF THE REAR SPAR

UPPER CHORD RADIUS [Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

FIGURE 3: WINGS - WING CENTER BOX - INTERNAL FUEL TANK INSPECTION OF THE REAR SPAR

UPPER CHORD RADIUS REQUIRING SEALANT REMOVAL [Group 2] . . . . . . . . . . 38

FIGURE 4: WINGS - WING CENTER BOX - INTERNAL FUEL TANK INSPECTION OF THE REAR SPAR

UPPER CHORD RADIUS WITHOUT SEALANT REMOVAL . . . . . . . . . . . . . . . . 41

FIGURE 5: WINGS - WING CENTER BOX - EXTERNAL FUEL TANK INSPECTION OF THE UPPER SKIN

AND PRESSURE SEAL AT STA 870 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44

FIGURE 6: WINGS - WING CENTER SECTION - REAR SPAR UPPER CHORD - INTERNAL FUEL TANK

SEALANT APPLICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47

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BOEING SERVICE BULLETIN 727-57-0187

BLANK PAGE
Commercial 

Airplanes 727

Service Bulletin

SPECIAL ATTENTION

Summary Number: 727-57-0187

Original Issue: March 08, 2012

ATA System: 5714

SUBJECT: WINGS - Wing Center Box - Upper Skin and Rear Spar Upper Chord Inspection

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

This service bulletin gives instructions to inspect the upper skin and the rear spar upper chord of the wing center

box, at Body Station (STA) 870 for cracking or corrosion. The upper skin and the rear spar upper chord of the

wing center box are classified as principal structural elements. If the work in this service bulletin is not done,

undetected cracking or corrosion in this area could severely limit the load carrying capabilities of the structure

which could result in the inability of the remaining structure to carry limit load which would preclude the continued

safe flight of the airplane.

Several operators have reported spanwise cracks and corrosion in the upper skin and rear spar upper chord

between Left Buttock Line (LBL) 70.50 and Right Buttock Line (RBL) 70.50, at STA 870. The crack sizes ranged

from 0.125 inches to 12 inches. The airplanes had accumulated between 31, 679 and 61,359 total flight hours

and between 17,754 and 58,796 total flight cycles. Analysis has shown that the cracks are a result of stress

corrosion which is a common problem in the 7178-T651 and 7178-T6511 aluminum from which the wing center

box upper skin and some rear spar upper chords are manufactured. All 727-100/-200 airplanes were delivered

with 7178-T651 aluminum plate upper skin panels and therefore all these airplanes are affected.

Corrosion occurrences in the wing center section are known issues. Boeing Service Bulletin 727-57-0170 was

issued for inspections and application of a corrosion inhibitor for external portions of the wing center section.

Additionally, multiple Structural Item Interim Advisories (SIIA) were issued for corrosion incidences to wing center

section stiffeners, webs, upper skins and chords at the rear spar. However, none of these documents resolves

the issue of cracking or corrosion at the wing center box upper skin and rear spar. Accomplishment of this service

bulletin will make sure that cracking or corrosion at the upper skin and the rear spar upper chord at the wing

center box, STA 870 are detected.

Boeing Service Related Problem (SRP) 727-SRP-52-0228 is related to this service bulletin.

Boeing Fleet Team Digest (FTD) 727 FTD 57-08003 is related to this service bulletin.

This table is provided to operators for planning purposes only. Refer to the applicable sections for more

information.

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Planning Data Affected Reference

Spares Affected No Paragraph 1.A.2., Spares Affected

AD Related No Paragraph 1.E., Compliance

Weight and Balance Change No Paragraph 1.H., Weight and Balance Changes

Electrical Load Changed No Paragraph 1.I., Electrical Load Data

Publications Affected No Paragraph 1.K., Publications Affected

Airplane Flight Operations Affected No Paragraph 1.K., Publications Affected

(Flight Crew Operations Manual and/or

FAA Approved Airplane Flight Manual)

Kits/Parts Required No Paragraph 2.C.1., Kits/Parts

Paragraph 2.C.2., Parts and Materials Supplied

by the Operator

Operator Supplied Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

ACTION

Defuel all tanks. Get access to the lower surface of the wing center box upper skin near the aft rear spar through

the center fuel tank. Between LBL 70.50 and RBL 70.50, at STA 870, do the following inspections: Do a High

Frequency Eddy Current (HFEC) inspection or a detailed inspection for cracking around the forward fastener

row in the rear spar upper chord horizontal flange. Do a Low Frequency Eddy Current (LFEC) inspection around

the aft fastener row in the rear spar upper chord horizontal flange for cracking in the upper skin and the rear

spar upper chord horizontal flange. Do a HFEC inspection or a detailed inspection for cracking in the rear spar

upper chord radius. If any crack is found, contact Boeing for repair instructions and do the repair. If no cracking

is found, do the repeat inspections at the intervals given in Paragraph 1.E., Compliance.

Get access to the upper surface of the wing center box upper skin near the rear spar by removing floor panels

at the wing center box. Between LBL 70.50 and RBL 70.50, at STA 870, do the following inspections: Do a

detailed inspection or a HFEC inspection for cracking in the upper skin around the forward fastener row common

to the rear spar upper chord horizontal flange. Do a detailed inspection for any damage, cracking or corrosion

in the pressure seal. If any damage, cracking or corrosion is found, contact Boeing for repair instructions and

do the repair. If no cracking is found, do the repeat inspections at the intervals given in Paragraph 1.E.,

Compliance.

EFFECTIVITY

All 727, 727-100, 727-100C, 727-200, 727-200F, 727C Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the

list of affected airplanes.

COMPLIANCE

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the inspection procedures given in this service bulletin.

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BOEING SERVICE BULLETIN 727-57-0187
MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Operator Supplied Parts/Materials.

Refer to Paragraph 2.A., Material - Price and Availability.

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BOEING SERVICE BULLETIN 727-57-0187
Commercial 

Airplanes 727

Service Bulletin

SPECIAL ATTENTION

Number: 727-57-0187

Original Issue: March 08, 2012

ATA System: 5714

SUBJECT: WINGS - Wing Center Box - Upper Skin and Rear Spar Upper Chord Inspection

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

GROUP CONFIGURATION DESCRIPTION

727, 727C, 727-100, 727-100C, and 727-200 airplanes with bladder

fuel cells at the wing center section.

1 -

727, 727-100 and 727-200, 727-200F airplanes with an integral fuel

tank at the wing center section.

2 -

Airplane Models:

727, 727-100, 727-100C, 727-200, 727-200F, 727C

Variable Number Group

E0001 - E0042 1

E0101 - E0140 1

E0201 - E0216 1

E0301 - E0351 1

E0401 - E0423 1

E3001 - E3006 1

E3011 - E3014 1

E3021 - E3040 1

E3059 1

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Variable Number Group

E3061 - E3077 1

E3101 - E3103 1

E3111 - E3118 1

E3141 - E3152 1

E3171 - E3177 1

E3201 - E3206 1

E3221 - E3224 1

E3241 - E3290 1

E3341 - E3350 1

E3401 - E3421 1

E3451 - E3452 1

E3471 - E3474 1

E3501 - E3513 1

E3516 - E3522 1

E3523 2

E3551 - E3553 1

E3571 - E3578 1

E3601 - E3604 1

E3621 - E3622 1

E3651 - E3655 1

E3677 1

E3681 - E3682 1

E3683 - E3684 2

E3701 - E3704 1

E3751 - E3755 1

E3781 - E3784 1

E5001 - E5011 1

E5031 - E5068 1

E5101 - E5116 1

E5141 - E5143 1

E5161 - E5164 1

E5201 - E5203 1

E5221 - E5245 1

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BOEING SERVICE BULLETIN 727-57-0187
Variable Number Group

E5251 - E5252 1

E5271 - E5281 1

E5301 - E5306 1

E5351 - E5353 1

E5381 - E5382 1

E5401 - E5424 1

E5426 - E5429 1

E5433 1

E5435 1

E5451 - E5455 1

E5481 - E5483 1

E5501 - E5502 1

QA001 - QA021 1

QA022 - QA023 2

QA024 - QA025 1

QA026 - QA046 2

QA051 - QA058 1

QA059 - QA099 2

QA101 - QA141 1

QA142 - QA199 2

QA201 - QA225 1

QA301 - QA316 1

QA317 - QA324 2

QA325 - QA329 1

QA330 - QA349 2

QA351 - QA368 1

QA369 - QA376 2

QA378 2

QA401 - QA428 1

QA429 - QA499 2

QA501 - QA532 1

QA533 - QA537 2

QA551 - QA567 1

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BOEING SERVICE BULLETIN 727-57-0187
Variable Number Group

QA568 - QA573 2

QA574 - QA575 1

QA576 2

QA577 - QA578 1

QA579 2

QA581 - QA585 2

QA601 - QA626 1

QA627 - QA688 2

QA701 - QA724 1

QA725 - QA753 2

QA801 - QA805 1

QA851 - QA853 1

QA854 - QA899 2

QA901 - QA906 1

QA907 - QA946 2

QA949 2

QB001 - QB002 1

QB031 - QB033 1

QB034 - QB049 2

QB051 - QB068 2

QB101 - QB102 1

QB103 - QB110 2

QB114 - QB119 2

QB121 - QB149 2

QB151 - QB158 2

QB201 - QB220 2

QB301 - QB316 2

QB351 - QB352 2

QB401 - QB407 2

QB451 - QB458 2

QB501 - QB575 2

QB601 - QB629 2

QB651 2

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BOEING SERVICE BULLETIN 727-57-0187
Variable Number Group

QB701 - QB705 2

QB801 - QB810 2

QB901 - QB904 2

QD001 - QD012 2

QD031 - QD046 2

QD085 - QD088 2

QD101 - QD105 2

QD121 - QD127 2

QD141 - QD149 2

QD161 - QD164 2

QD191 - QD192 2

QD201 - QD239 2

QD281 - QD284 2

QD301 - QD305 2

QD321 - QD330 2

QD351 2

QD401 - QD403 2

QD407 2

QD410 2

QD421 - QD427 2

QD441 - QD453 2

QD471 - QD475 2

QD501 - QD518 2

QD551 - QD558 2

QD571 - QD572 2

QD581 - QD583 2

QD601 - QD607 2

QD621 - QD624 2

QD641 2

QD661 - QD663 2

QD681 - QD685 2

QD691 - QD692 2

QD701 - QD702 2

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BOEING SERVICE BULLETIN 727-57-0187
Variable Number Group

QD711 - QD717 2

QD741 2

QD761 - QD769 2

QD781 - QD782 2

QD791 2

QD801 - QD804 2

QD821 - QD828 2

QD901 - QD910 2

QD931 - QD932 2

QD951 - QD954 2

QD971 - QD973 2

QD991 - QD992 2

QE001 - QE002 2

QL001 - QL008 2

QL031 - QL032 2

QL081 2

QL501 - QL515 2

2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

This service bulletin gives instructions to inspect the upper skin and the rear spar upper chord of the

wing center box, at Body Station (STA) 870 for cracking or corrosion. The upper skin and the rear spar

upper chord of the wing center box are classified as principal structural elements. If the work in this

service bulletin is not done, undetected cracking or corrosion in this area could severely limit the load

carrying capabilities of the structure which could result in the inability of the remaining structure to carry

limit load which would preclude the continued safe flight of the airplane.

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BOEING SERVICE BULLETIN 727-57-0187
Several operators have reported spanwise cracks and corrosion in the upper skin and rear spar upper

chord between Left Buttock Line (LBL) 70.50 and Right Buttock Line (RBL) 70.50, at STA 870. The

crack sizes ranged from 0.125 inches to 12 inches. The airplanes had accumulated between 31, 679

and 61,359 total flight hours and between 17,754 and 58,796 total flight cycles. Analysis has shown

that the cracks are a result of stress corrosion which is a common problem in the 7178-T651 and

7178-T6511 aluminum from which the wing center box upper skin and some rear spar upper chords

are manufactured. All 727-100/-200 airplanes were delivered with 7178-T651 aluminum plate upper

skin panels and therefore all these airplanes are affected.

Corrosion occurrences in the wing center section are known issues. Boeing Service Bulletin 727-57-0170

was issued for inspections and application of a corrosion inhibitor for external portions of the wing

center section. Additionally, multiple Structural Item Interim Advisories (SIIA) were issued for corrosion

incidences to wing center section stiffeners, webs, upper skins and chords at the rear spar. However,

none of these documents resolves the issue of cracking or corrosion at the wing center box upper skin

and rear spar. Accomplishment of this service bulletin will make sure that cracking or corrosion at the

upper skin and the rear spar upper chord at the wing center box, STA 870 are detected.

Boeing Service Related Problem (SRP) 727-SRP-52-0228 is related to this service bulletin.

Boeing Fleet Team Digest (FTD) 727 FTD 57-08003 is related to this service bulletin.

D. Description

Defuel all tanks. Get access to the lower surface of the wing center box upper skin near the aft rear

spar through the center fuel tank. Between LBL 70.50 and RBL 70.50, at STA 870, do the following

inspections: Do a High Frequency Eddy Current (HFEC) inspection or a detailed inspection for cracking

around the forward fastener row in the rear spar upper chord horizontal flange. Do a Low Frequency

Eddy Current (LFEC) inspection around the aft fastener row in the rear spar upper chord horizontal

flange for cracking in the upper skin and the rear spar upper chord horizontal flange. Do a HFEC

inspection or a detailed inspection for cracking in the rear spar upper chord radius. If any crack is found,

contact Boeing for repair instructions and do the repair. If no cracking is found, do the repeat inspections

at the intervals given in Paragraph 1.E., Compliance.

Get access to the upper surface of the wing center box upper skin near the rear spar by removing floor

panels at the wing center box. Between LBL 70.50 and RBL 70.50, at STA 870, do the following

inspections: Do a detailed inspection or a HFEC inspection for cracking in the upper skin around the

forward fastener row common to the rear spar upper chord horizontal flange. Do a detailed inspection

for any damage, cracking or corrosion in the pressure seal. If any damage, cracking or corrosion is

found, contact Boeing for repair instructions and do the repair. If no cracking is found, do the repeat

inspections at the intervals given in Paragraph 1.E., Compliance.

The work in this service bulletin is done in the maintenance zone(s) given below.

Group 1:

Affected Maintenance Zones

Model Zone

727, 727-100, 727-100C, 727- 1-74

200, 727C

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BOEING SERVICE BULLETIN 727-57-0187
Group 2:

Affected Maintenance Zones

Model Zone

727, 727-100, 727-200, 727- 1-74

200F

E. Compliance

Group 1:

Table 1: Wing Center Box - Internal Fuel Tank Inspection of the Upper Skin and Rear Spar Upper

Chord

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Do an inspection for cracking - -

around the forward fastener row

in the rear spar upper chord horizontal flange between Left Buttock Line (LBL) 70.50 and Right

Buttock Line (RBL) 70.50, at Body

Station (STA) 870, using one of

the following options:

All Airplanes.

Within 3 years af- 6 years.

ter the original issue date of this

service bulletin.

OPTION 1: Do a High Frequency

Eddy Current (HFEC) inspection

in accordance with Accomplishment Instructions paragraph

3.B.2.a.(1)(a).

OR

Within 3 years af- 3 years.

ter the original issue date of this

service bulletin.

OPTION 2: Do a detailed inspection in accordance with Accomplishment Instructions paragraph

3.B.2.a.(1)(b).

Before further -

flight.

Contact Boeing for repair instructions and do the repair instructed

by Boeing.

Any crack found.

Within 3 years af- 6 years.

ter the original issue date of this

service bulletin.

Do a Low Frequency Eddy Current (LFEC) inspection around the

aft fastener row in the rear spar

upper chord horizontal flange for

cracking in the upper skin and the

rear spar upper chord horizontal

flange between LBL 70.50 and

RBL 70.50, at STA 870, in accordance with Accomplishment Instructions paragraph 3.B.2.a.(2).

All Airplanes.

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BOEING SERVICE BULLETIN 727-57-0187
Group 1:

Table 1: Wing Center Box - Internal Fuel Tank Inspection of the Upper Skin and Rear Spar Upper

Chord

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Before further -

flight.

Contact Boeing for repair instructions and do the repair instructed

by Boeing.

Any crack found.

Do an inspection for cracking in - -

the rear spar upper chord radius

between LBL 70.50 and RBL

70.50, at STA 870, using one of

the following options:

All Airplanes.

Within 3 years af- 3 years.

ter the original issue date of this

service bulletin.

OPTION 1: Do a detailed inspection in accordance with Accomplishment Instructions paragraph

3.B.2.a.(3)(a).

OR

Within 3 years af- 6 years.

ter the original issue date of this

service bulletin.

OPTION 2: Do a HFEC inspection

in accordance with Accomplishment Instructions paragraph

3.B.2.a.(3)(b).

Before further -

flight.

Contact Boeing for repair instructions and do the repair instructed

by Boeing.

Any crack found.

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BOEING SERVICE BULLETIN 727-57-0187
Group 2:

Table 2: Wing Center Box - Internal Fuel Tank Inspection of the Upper Skin and Rear Spar Upper

Chord

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Do an inspection for cracking - -

around the forward fastener row

in the rear spar upper chord horizontal flange between Left Buttock Line (LBL) 70.50 and Right

Buttock Line (RBL) 70.50, at Body

Station (STA) 870, using one of

the following options:

All Airplanes.

Within 3 years af- 6 years.

ter the original issue date of this

service bulletin.

OPTION 1: Do a High Frequency

Eddy Current (HFEC) inspection

in accordance with Accomplishment Instructions paragraph

3.B.2.a.(1)(a).

OR

Within 3 years af- 3 years.

ter the original issue date of this

service bulletin.

OPTION 2: Do a detailed inspection in accordance with Accomplishment Instructions paragraph

3.B.2.a.(1)(b).

Before further -

flight.

Contact Boeing for repair instructions and do the repair instructed

by Boeing.

Any crack found.

Within 3 years af- 6 years.

ter the original issue date of this

service bulletin.

Do a Low Frequency Eddy Current (LFEC) inspection around the

aft fastener row in the rear spar

upper chord horizontal flange for

cracking in the upper skin and the

rear spar upper chord horizontal

flange between LBL 70.50 and

RBL 70.50, at STA 870, in accordance with Accomplishment Instructions paragraph 3.B.2.a.(2).

All Airplanes.

Before further -

flight.

Contact Boeing for repair instructions and do the repair instructed

by Boeing.

Any crack found.

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BOEING SERVICE BULLETIN 727-57-0187
Group 2:

Table 2: Wing Center Box - Internal Fuel Tank Inspection of the Upper Skin and Rear Spar Upper

Chord

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Do an inspection for cracking in - -

the rear spar upper chord radius

between LBL 70.50 and RBL

70.50, at STA 870, using one of

the following options:

All Airplanes.

Within 3 years af- 3 years.

ter the original issue date of this

service bulletin.

OPTION 1: Do a detailed inspection in accordance with Accomplishment Instructions paragraph

3.B.2.a.(4)(a).

OR

Within 3 years af- 6 years.

ter the original issue date of this

service bulletin.

OPTION 2: Do a HFEC inspection

in accordance with Accomplishment Instructions paragraph

3.B.2.a.(4)(b).

OR

Within 3 years af- 6 years.

ter the original issue date of this

service bulletin.

OPTION 3: Do a HFEC inspection

in accordance with Accomplishment Instructions paragraph

3.B.2.a.(4)(c).

NOTE: Removal of sealant from

the rear spar upper chord radius

is not required for Option 3 inspection.

Before further -

flight.

Contact Boeing for repair instructions and do the repair instructed

by Boeing.

Any crack found.

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BOEING SERVICE BULLETIN 727-57-0187
All Groups:

Table 3: Wing Center Box - External Fuel Tank Inspection of the Upper Skin and Pressure Seal

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Do an inspection for cracking in - -

the upper skin around the forward

fastener row common to the rear

spar upper chord horizontal flange

between LBL 70.50 and RBL

70.50, at STA 870, using one of

the following options:

All Airplanes.

Within 3 years af- 3 years.

ter the original issue date of this

service bulletin.

OPTION 1: Do a detailed inspection in accordance with Accomplishment Instructions paragraph

3.B.2.b.(1)(a).

OR

Within 3 years af- 6 years.

ter the original issue date of this

service bulletin.

OPTION 2: Do a HFEC inspection

in accordance with Accomplishment Instructions paragraph

3.B.2.b.(1)(b).

Before further -

flight.

Contact Boeing for repair instructions and do the repair instructed

by Boeing.

Any crack found.

Within 3 years af- 3 years.

ter the original issue date of this

service bulletin.

Do a detailed inspection for damage, cracking or corrosion in the

pressure seal between LBL 70.50

and RBL 70.50, at STA 870, in

accordance with Accomplishment

Instructions paragraph 3.B.2.b.(2).

All Airplanes.

Before further -

flight.

Contact Boeing for repair instructions and do the repair instructed

by Boeing.

Any damage,

cracking or corrosion found.

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.

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BOEING SERVICE BULLETIN 727-57-0187
G. Manpower

The table below shows an estimate of the task hours necessary to do this service bulletin 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

Preparation 4 8.00 2.00

Open Access 4 9.30 2.33

FIGURE 1, OPTION 1 2 10.00 5.00

FIGURE 1, OPTION 2 2 8.00 4.00

FIGURE 2, OPTION 1 2 3.00 1.50

FIGURE 2, OPTION 2 2 5.00 2.50

FIGURE 5, OPTION 1 2 6.00 3.00

FIGURE 5, OPTION 2 2 8.00 4.00

Restoration 4 8.00 2.00

Close Access 2 17.30 8.65

TOTAL FOR EACH AIRPLANE (a) (a)

(a) The total task hours and total elapsed hours for each airplane depend on which inspection

options are accomplished. Operators should add the hours for each applicable task to

calculate the total hours for each airplane.

Group 2:

Task Number of Persons Task Hours Elapsed Hours

Preparation 4 8.00 2.00

Open Access 4 17.30 4.33

FIGURE 1, OPTION 1 2 10.00 5.00

FIGURE 1, OPTION 2 2 8.00 4.00

FIGURE 3, OPTION 1 2 14.20 7.10

FIGURE 3, OPTION 2 2 16.30 8.15

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BOEING SERVICE BULLETIN 727-57-0187
Group 2:

Task Number of Persons Task Hours Elapsed Hours

FIGURE 4, OPTION 3 2 5.00 2.50

FIGURE 5, OPTION 1 2 6.00 3.00

FIGURE 5, OPTION 2 2 8.00 4.00

FIGURE 6 2 15.50 7.75

Restoration 4 8.00 2.00

Close Access 4 17.30 4.33

TOTAL FOR EACH AIRPLANE (a) (a)

(a) The total task hours and total elapsed hours for each airplane depend on which inspection

options are accomplished. Operators should add the hours for each applicable task to

calculate the total hours for each airplane.

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not applicable.

J. References

1. Existing Data

a. Boeing Service Bulletin 727-57-0170.

b. Boeing Service Related Problem (SRP) 727-SRP-52-0228.

c. Standard Overhaul Practices Manual (SOPM) 20-30-93, 20-41-05, 20-50-19.

d. 727 Aircraft Maintenance Manual (AMM) 12-30-03, 28-10-00, 28-11-21, 28-12-01, 28-12-11,

28-23-00, 51-31-00, 53-20-11.

e. 727 Fleet Team Digest (FTD) 57-08003.

f. 727 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00, Part 6, 51-00-27, Part 6, 57-10-28.

2. Data supplied with this Service Bulletin

None.

3. Installation Drawings Used in the Preparation of this Service Bulletin

Drawing Number Title

65-16202 REAR SPAR INSTALLATION - WING CENTER SECTION

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BOEING SERVICE BULLETIN 727-57-0187
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 does not affect FCS, therefore DTIs are not necessary.

L. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

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BOEING SERVICE BULLETIN 727-57-0187
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BOEING SERVICE BULLETIN 727-57-0187

BLANK PAGE
2. MATERIAL INFORMATION

A. Material - Price and Availability

None.

B. Industry Support Information

Boeing warranty remedies are not available for the inspection procedures given in this service bulletin.

C. Parts Necessary For Each Airplane

1. Kits/Parts

None.

2. Parts and Materials Supplied by the Operator

Group 1:

Part Number / Speci- QTY Name Notes

fication

BMS 3-23, Type 2 5 oz Corrosion Inhibiting Compound (a)

(a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)

for supplier data.

Group 2:

Part Number / Speci- QTY Name Notes

fication

BMS 3-23, Type 2 5 oz Corrosion Inhibiting Compound (a)

BMS 5-45, Class B 5 oz Sealant, Integral Fuel Tank (a)

(a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)

for supplier data.

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None.

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BOEING SERVICE BULLETIN 727-57-0187
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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BOEING SERVICE BULLETIN 727-57-0187
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

4. Use the approved fastener and process material substitutions in accordance with

SRM Chapter 51.

5. 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.

6. These work instructions refer to procedures included in other Boeing documents.

When the words "refer to" are used and the operator has an accepted alternative

procedure, the accepted alternative procedure can be used. When the words "in

accordance with" are included in the instruction, the procedure in the Boeing document

must be used.

7. Boeing Service Letter 727-SL-51-041, Damage Reporting and Repair Plan/Design

Guidelines, is an acceptable procedure to request information from Boeing for

additional structural repair instructions. The Service Letter describes what information

must be provided to Boeing before a structural repair can be provided.

8. 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. PREPARATION AND ACCESS

a. Defuel all tanks. Refer to 727 AMM 28-23-00 as an accepted procedure.

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BOEING SERVICE BULLETIN 727-57-0187
b. Group 1:

(1) Open the wing center fuel cell access panel. Refer to 727 AMM 28-12-11 as an accepted

procedure.

(2) Remove the wing center section fuel tank bladder cells. Refer to 727 AMM 28-12-01 as

an accepted procedure.

c. Group 2:

(1) Open the wing center section fuel tank access panel. Refer to 727 AMM 28-11-21 as an

accepted procedure.

(2) Purge the wing center section fuel tank. Refer to 727 AMM 28-10-00 as an accepted

procedure.

d. Open floor panels 3355, 3356, 3455 and 3456 to get access to the upper surface of the wing

center section upper skin. Refer to 727 AMM 12-30-03 and 727 AMM 53-20-11 as accepted

procedures.

2. INSPECTION

a. Internal Fuel Tank Inspection

(1) Do an inspection for cracking around the forward fastener row in the rear spar upper

chord horizontal flange between Left Buttock Line (LBL) 70.50 and Right Buttock Line

(RBL) 70.50, at Body Station (STA) 870, using one of the following options:

(a) OPTION 1: Do a High Frequency Eddy Current (HFEC) inspection in accordance

with FIGURE 1.

1) If any crack is found, contact Boeing for repair instructions and do the repair

instructed by Boeing.

2) If no cracking is found, do the repeat inspections at the interval given in

Paragraph 1.E., Compliance.

(b) OPTION 2: Do a detailed inspection in accordance with FIGURE 1.

1) If any crack is found, contact Boeing for repair instructions and do the repair

instructed by Boeing.

2) If no cracking is found, do the repeat inspections at the interval given in

Paragraph 1.E., Compliance.

(2) Do a Low Frequency Eddy Current (LFEC) inspection around the aft fastener row in the

rear spar upper chord horizontal flange for cracking in the upper skin and the rear spar

upper chord horizontal flange between LBL 70.50 and RBL 70.50, at STA 870, in

accordance with FIGURE 1.

(a) If any crack is found, contact Boeing for repair instructions and do the repair instructed

by Boeing.

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BOEING SERVICE BULLETIN 727-57-0187
(b) If no cracking is found, do the repeat inspections at the interval given in Paragraph

1.E., Compliance.

(3) Group 1:

Do an inspection for cracking in the rear spar upper chord radius between LBL 70.50 and

RBL 70.50, at STA 870, using one of the following options:

(a) OPTION 1: Do a detailed inspection in accordance with FIGURE 2.

1) If any crack is found, contact Boeing for repair instructions and do the repair

instructed by Boeing.

2) If no cracking is found, do the repeat inspections at the interval given in

Paragraph 1.E., Compliance.

(b) OPTION 2: Do a HFEC inspection in accordance with FIGURE 2.

1) If any crack is found, contact Boeing for repair instructions and do the repair

instructed by Boeing.

2) If no cracking is found, do the repeat inspections at the interval given in

Paragraph 1.E., Compliance.

(4) Group 2:

Do an inspection for cracking in the rear spar upper chord radius between LBL 70.50 and

RBL 70.50, at STA 870, using one of the following options:

(a) OPTION 1: Remove the sealant from the rear spar upper chord radius and do a

detailed inspection in accordance with FIGURE 3.

1) If any crack is found, contact Boeing for repair instructions and do the repair

instructed by Boeing.

2) If no cracking is found, apply sealant to the rear spar upper chord radius in

accordance with FIGURE 6 and do the repeat inspections at the interval given

in Paragraph 1.E., Compliance.

(b) OPTION 2: Remove the sealant from the rear spar upper chord radius and do a

HFEC inspection in accordance with FIGURE 3.

1) If any crack is found, contact Boeing for repair instructions and do the repair

instructed by Boeing.

2) If no cracking is found, apply sealant to the rear spar upper chord radius in

accordance with FIGURE 6 and do the repeat inspections at the interval given

in Paragraph 1.E., Compliance.

(c) OPTION 3: Do a HFEC inspection in accordance with FIGURE 4.

NOTE: Removal of sealant from the rear spar upper chord radius is not required

for Option 3 inspection.

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1) If any crack is found, contact Boeing for repair instructions and do the repair

instructed by Boeing.

2) If no cracking is found, do the repeat inspections at the interval given in

Paragraph 1.E., Compliance.

b. External Fuel Tank Inspection

(1) Do an inspection for cracking in the upper skin around the forward fastener row common

to the rear spar upper chord horizontal flange between LBL 70.50 and RBL 70.50, at STA

870, using one of the following options:

(a) OPTION 1: Do a detailed inspection in accordance with FIGURE 5.

1) If any crack is found, contact Boeing for repair instructions and do the repair

instructed by Boeing.

2) If no cracking is found, do the repeat inspections at the interval given in

Paragraph 1.E., Compliance.

(b) OPTION 2: Do a HFEC inspection in accordance with FIGURE 5.

1) If any crack is found, contact Boeing for repair instructions and do the repair

instructed by Boeing.

2) If no cracking is found, do the repeat inspections at the interval given in

Paragraph 1.E., Compliance.

(2) Do a detailed inspection for damage, cracking or corrosion in the pressure seal between

LBL 70.50 and RBL 70.50, at STA 870, in accordance with FIGURE 5.

(a) If any damage, cracking or corrosion is found, contact Boeing for repair instructions

and do the repair instructed by Boeing.

(b) If no damage, cracking or corrosion is found, do the repeat inspections at the interval

given in Paragraph 1.E., Compliance.

3. RESTORATION AND CLOSE ACCESS

a. Apply BMS 3-23, Type 2 Corrosion Inhibiting Compound to the upper surface of the wing

center box upper skin near the rear spar. Refer to SOPM 20-41-05 as an accepted procedure.

b. Close floor panels 3355, 3356, 3455 and 3456. Refer to 727 AMM 12-30-03 and 727 AMM

53-20-11 as accepted procedures.

c. Group 1:

(1) Apply BMS 3-23, Type 2 Corrosion Inhibiting Compound to the inside of the wing center

section where inspection was done. Refer to SOPM 20-41-05 as an accepted procedure.

(2) Install the wing center section fuel tank bladder cells. Refer 727 AMM 28-12-01 to as an

accepted procedure.

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BOEING SERVICE BULLETIN 727-57-0187
(3) Close the wing center fuel cell access panel. Refer to 727 AMM 28-12-11 as an accepted

procedure.

d. Group 2:

(1) Close the wing center section fuel tank access panel. Refer to 727 AMM 28-11-21 as an

accepted procedure.

e. Put the airplane back to a serviceable condition.

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BOEING SERVICE BULLETIN 727-57-0187
FIGURE 1: WINGS - WING CENTER BOX - INTERNAL FUEL TANK INSPECTION OF THE REAR SPAR

UPPER CHORD HORIZONTAL FLANGE

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 727-57-0187
FIGURE 1: WINGS - WING CENTER BOX - INTERNAL FUEL TANK INSPECTION OF THE REAR SPAR

UPPER CHORD HORIZONTAL FLANGE

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 727-57-0187
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 airplane.

Step Task Name Identification Qty More Data

1 Inspect Rear Spar Upper Chord - 1 (a)

Upper Skin and Rear - - (b)

Spar Upper Chord

2 Inspect

(a) OPTION 1: Do a High Frequency Eddy Current (HFEC) inspection for cracking around the forward fastener

row in the rear spar upper chord horizonal flange between Left Buttock Line (LBL) 70.50 and Right Buttock

Line (RBL) 70.50 in accordance with 727 NDT Part 6, 57-10-28. OPTION 2: Do a detailed inspection for

cracking around the forward fastener row in the rear spar upper chord horizontal flange between LBL

70.50 and RBL 70.50.

(b) Do a Low Frequency Eddy Current (LFEC) inspection around the aft fastener row in the rear spar upper

chord horizontal flange for cracking in the upper skin and the rear spar upper chord horizontal flange between LBL 70.50 and RBL 70.50 in accordance with 727 NDT Part 6, 57-10-28.

FIGURE 1: WINGS - WING CENTER BOX - INTERNAL FUEL TANK INSPECTION OF THE REAR SPAR

UPPER CHORD HORIZONTAL FLANGE

(SHEET 3 OF 3)

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This Figure applies only to: Group 1.

FIGURE 2: WINGS - WING CENTER BOX - INTERNAL FUEL TANK INSPECTION OF THE REAR SPAR

UPPER CHORD RADIUS

(SHEET 1 OF 3)

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FIGURE 2: WINGS - WING CENTER BOX - INTERNAL FUEL TANK INSPECTION OF THE REAR SPAR

UPPER CHORD RADIUS

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 727-57-0187
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 airplane.

Step Task Name Identification Qty More Data

Rear Spar Upper Chord - - (a)

Radius

1 Inspect

(a) OPTION 1: Do a detailed inspection for cracking in the rear spar upper chord radius between LBL 70.50

and RBL 70.50. OPTION 2: Do a High Frequency Eddy Current (HFEC) inspection for cracking in the

rear spar upper chord radius between LBL 70.50 and RBL 70.50 in accordance with 727 NDT Part 6, 51-

00-00 Figure 23. Scan the probe in a manner to detect span wise cracks.

FIGURE 2: WINGS - WING CENTER BOX - INTERNAL FUEL TANK INSPECTION OF THE REAR SPAR

UPPER CHORD RADIUS

(SHEET 3 OF 3)

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This Figure applies only to: Group 2.

FIGURE 3: WINGS - WING CENTER BOX - INTERNAL FUEL TANK INSPECTION OF THE REAR SPAR

UPPER CHORD RADIUS REQUIRING SEALANT REMOVAL

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 727-57-0187
FIGURE 3: WINGS - WING CENTER BOX - INTERNAL FUEL TANK INSPECTION OF THE REAR SPAR

UPPER CHORD RADIUS REQUIRING SEALANT REMOVAL

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 727-57-0187
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 airplane.

Step Task Name Identification Qty More Data

1 Remove Sealant - - (a)

Rear Spar Upper Chord - - (b)

Radius

2 Inspect

(a) Remove all the sealant from the rear spar upper chord radius between Left Buttock Line (LBL) 70.50 and

Right Buttock Line (RBL) 70.50. Refer to SOPM 20-50-19 as an accepted procedure.

(b) OPTION 1: Do a detailed inspection for cracking in the rear spar upper chord radius between LBL 70.50

and RBL 70.50. OPTION 2: Do a High Frequency Eddy Current (HFEC) inspection for cracking in the

rear spar upper chord radius between LBL 70.50 and RBL 70.50 in accordance with 727 NDT Part 6, 51-

00-00 Figure 23. Scan the probe in a manner to detect span wise cracks.

FIGURE 3: WINGS - WING CENTER BOX - INTERNAL FUEL TANK INSPECTION OF THE REAR SPAR

UPPER CHORD RADIUS REQUIRING SEALANT REMOVAL

(SHEET 3 OF 3)

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FIGURE 4: WINGS - WING CENTER BOX - INTERNAL FUEL TANK INSPECTION OF THE REAR SPAR

UPPER CHORD RADIUS WITHOUT SEALANT REMOVAL

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 727-57-0187
FIGURE 4: WINGS - WING CENTER BOX - INTERNAL FUEL TANK INSPECTION OF THE REAR SPAR

UPPER CHORD RADIUS WITHOUT SEALANT REMOVAL

(SHEET 2 OF 3)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 08, 2012

727-57-0187

42 of 49

BOEING SERVICE BULLETIN 727-57-0187
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 airplane.

Step Task Name Identification Qty More Data

Rear Spar Upper Chord - - (a)

Radius

1 Inspect

(a) Do a High Frequency Eddy Current (HFEC) inspection for cracking in the rear spar upper chord radius

between Left Buttock Line (LBL) 70.50 and Right Buttock Line (RBL) 70.50 in accordance with 727 NDT

Part 6, 51-00-27. Scan the probe in a manner to detect spanwise cracks. Make sure to calibrate the instrument for the sealant thickness that is in the radius. The maximum thickness of the sealant allowed

for this procedure is defined in 727 NDT Part 6, 51-00-27.

FIGURE 4: WINGS - WING CENTER BOX - INTERNAL FUEL TANK INSPECTION OF THE REAR SPAR

UPPER CHORD RADIUS WITHOUT SEALANT REMOVAL

(SHEET 3 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 08, 2012

727-57-0187

43 of 49

BOEING SERVICE BULLETIN 727-57-0187
FIGURE 5: WINGS - WING CENTER BOX - EXTERNAL FUEL TANK INSPECTION OF THE UPPER SKIN

AND PRESSURE SEAL AT STA 870

(SHEET 1 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 08, 2012

727-57-0187

44 of 49

BOEING SERVICE BULLETIN 727-57-0187
FIGURE 5: WINGS - WING CENTER BOX - EXTERNAL FUEL TANK INSPECTION OF THE UPPER SKIN

AND PRESSURE SEAL AT STA 870

(SHEET 2 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 08, 2012

727-57-0187

45 of 49

BOEING SERVICE BULLETIN 727-57-0187
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 airplane.

Step Task Name Identification Qty More Data

1 Inspect Upper Skin - - (a)

2 Inspect Pressure Seal - - (b)

(a) OPTION 1: Do a detailed inspection for cracking in the upper skin around the forward fastener row common

to the rear spar upper chord horizontal flange between Left Buttock Line (LBL) 70.50 and Right Buttock

Line (RBL) 70.50. OPTION 2: Do a High Frequency Eddy Current (HFEC) inspection for cracking in the

upper skin around the forward fastener row common to the rear spar upper chord horizontal flange between

LBL 70.50 and RBL 70.50 in accordance with 727 NDT Part 6, 57-10-28.

(b) Do a detailed inspection of the pressure seal between LBL 70.50 and RBL 70.50 for damage, cracking

or corrosion. Examples of damage are missing, flaking, or blistering in the paint, primer, sealant, or corrosion

inhibiting compound.

FIGURE 5: WINGS - WING CENTER BOX - EXTERNAL FUEL TANK INSPECTION OF THE UPPER SKIN

AND PRESSURE SEAL AT STA 870

(SHEET 3 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 08, 2012

727-57-0187

46 of 49

BOEING SERVICE BULLETIN 727-57-0187
FIGURE 6: WINGS - WING CENTER SECTION - REAR SPAR UPPER CHORD - INTERNAL FUEL TANK

SEALANT APPLICATION

(SHEET 1 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 08, 2012

727-57-0187

47 of 49

BOEING SERVICE BULLETIN 727-57-0187
FIGURE 6: WINGS - WING CENTER SECTION - REAR SPAR UPPER CHORD - INTERNAL FUEL TANK

SEALANT APPLICATION

(SHEET 2 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 08, 2012

727-57-0187

48 of 49

BOEING SERVICE BULLETIN 727-57-0187
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 airplane.

Step Task Name Identification Qty More Data

Rear Spar Upper Chord - - (a)

Radius and Web

1 Clean

Sealant, Integral Fuel BMS 5-45, CLASS B - (b)

Tank

2 Apply

(a) Clean the rear spar upper chord radius and the upper edge of the rear spar web between Left Buttock

Line (LBL) 70.50 and Right Buttock Line (RBL) 70.50. Refer to SOPM 20-30-93 as an accepted procedure.

(b) Apply a fillet seal common to the upper edge of the rear spar web and radius of the rear spar upper chord

LBL 70.50 to RBL 70.50. Refer to 727 AMM 51-31-00 or SOPM 20-50-19 as an accepted procedure.

FIGURE 6: WINGS - WING CENTER SECTION - REAR SPAR UPPER CHORD - INTERNAL FUEL TANK

SEALANT APPLICATION

(SHEET 3 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 08, 2012

727-57-0187

49 of 49

BOEING SERVICE BULLETIN 727-57-0187