Commercial 

Airplanes 727

Service Bulletin

SPECIAL ATTENTION

Number: 727-55-0095

Original Issue: September 24, 2012

ATA System: 5500

SUBJECT: STABILIZERS - Vertical Stabilizer - Fin Closure Rib - Chord Inspection

Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15

CFR 300-774). An export license may be required before it is used for development, production or use by foreign

persons from specific countries. The controller of this data has the individual responsibility to abide by all export

laws.

ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET

Copyright © 2012 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Unpublished Work.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, DreamlinerTM,

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 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. BOEING is a trademark of Boeing Management

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BLANK PAGE
Table of Contents

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

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

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 16

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 19

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 20

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

FIGURE 1: VERTICAL STABILIZER - LEFT SIDE FIN CLOSURE RIB CHORD INSPECTION . . . . 24

FIGURE 2: VERTICAL STABILIZER - RIGHT SIDE FIN CLOSURE RIB CHORD INSPECTION . . . 26

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BLANK PAGE
Commercial 

Airplanes 727

Service Bulletin

SPECIAL ATTENTION

Summary Number: 727-55-0095

Original Issue: September 24, 2012

ATA System: 5500

SUBJECT: STABILIZERS - Vertical Stabilizer - Fin Closure Rib - Chord Inspection

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

This service bulletin gives instructions to inspect the left side and right side chords of the fin closure rib for

cracking or corrosion. The fin closure rib is located at the top of the vertical fin structure. The chords of the fin

closure rib support the horizontal stabilizer hinge fittings. If the work in this service bulletin is not done, widespread

cracking in the chords may weaken the fin closure rib structure which could result in loss of airplane control due

to lack of horizontal stabilizer support.

One operator reported finding a crack on the left side chord of the fin closure rib during a routine maintenance

inspection. The crack measured a maximum of 2.4 inches long and it ran along the length of the chord. The

airplane had accumulated 5,303 flight cycles and 11,669 flight hours when the crack was found. Cracking at

this location is the result of intergranular stress corrosion caused by the material properties of 2024-T351

extrusion from which the closure rib chord is made. This material becomes vulnerable after the surface finishes

begin to break down as a result of normal in-service aging.

A fleet history search revealed that this occurrence is the first report of intergranular cracking of the chords. The

Corrosion Prevention and Control Program (CPCP) and Maintenance Planning Data (MPD) documentation for

727 airplanes both contain visual inspections of the chords, but no NDT inspections. Accomplishment of the

NDT and visual inspections in this service bulletin will make sure that any crack or corrosion in the left side or

right side chords of the fin closure rib is detected.

Boeing Service Related Problem (SRP) 727-SRP-55-0050 is related to this service bulletin.

Boeing Fleet Team Digest (FTD) 727 FTD 55-10001 is related to this service bulletin.

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

information.

Planning Data Affected Reference

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

AD Related No Paragraph 1.E., Compliance

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Planning Data Affected Reference

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 (Flight Crew No Paragraph 1.K., Publications Affected

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

Get access to the left side and right side chords of the fin closure rib by opening access panels at the fin closure

rib. Do a detailed inspection for any crack or corrosion and High Frequency Eddy Current (HFEC) inspections

for any crack in the left side and right side chords. If any crack or corrosion is found, contact Boeing for repair

or replacement instructions and do the work instructed by Boeing. Do repeat inspections at the interval 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.

MANPOWER

Refer to Paragraph 1.G., Manpower.

Airplanes Total Task Hours Elapsed Hours

Group 1 17.00 11.00

MATERIAL INFORMATION

Operator Supplied Parts/Materials.

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

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BLANK PAGE
Commercial 

Airplanes 727

Service Bulletin

SPECIAL ATTENTION

Number: 727-55-0095

Original Issue: September 24, 2012

ATA System: 5500

SUBJECT: STABILIZERS - Vertical Stabilizer - Fin Closure Rib - Chord Inspection

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

Refer to Service Bulletin Index D6-9825 Part 3 for Airplane Variable Number, Line Number, and

Serial Number data.

This service bulletin is for the airplane(s) shown below.

GROUP CONFIGURATION DESCRIPTION

1 - All 727, 727-100, 727-100C, 727-200, 727-200F, 727C airplanes.

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 - E3523 1

E3551 - E3553 1

E3571 - E3578 1

E3601 - E3604 1

E3621 - E3622 1

E3651 - E3655 1

E3677 1

E3681 - E3684 1

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

E5251 - E5252 1

E5271 - E5281 1

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BOEING SERVICE BULLETIN 727-55-0095
Variable Number Group

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 - QA046 1

QA051 - QA099 1

QA101 - QA199 1

QA201 - QA225 1

QA301 - QA349 1

QA351 - QA376 1

QA378 1

QA401 - QA499 1

QA501 - QA537 1

QA551 - QA579 1

QA581 - QA585 1

QA601 - QA688 1

QA701 - QA753 1

QA801 - QA805 1

QA851 - QA899 1

QA901 - QA946 1

QA949 1

QB001 - QB002 1

QB031 - QB049 1

QB051 - QB068 1

QB101 - QB110 1

QB114 - QB119 1

QB121 - QB149 1

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Variable Number Group

QB151 - QB158 1

QB201 - QB220 1

QB301 - QB316 1

QB351 - QB352 1

QB401 - QB407 1

QB451 - QB458 1

QB501 - QB575 1

QB601 - QB629 1

QB651 1

QB701 - QB705 1

QB801 - QB810 1

QB901 - QB904 1

QD001 - QD012 1

QD031 - QD046 1

QD085 - QD088 1

QD101 - QD105 1

QD121 - QD127 1

QD141 - QD149 1

QD161 - QD164 1

QD191 - QD192 1

QD201 - QD239 1

QD281 - QD284 1

QD301 - QD305 1

QD321 - QD330 1

QD351 1

QD401 - QD403 1

QD407 1

QD410 1

QD421 - QD427 1

QD441 - QD453 1

QD471 - QD475 1

QD501 - QD518 1

QD551 - QD558 1

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Variable Number Group

QD571 - QD572 1

QD581 - QD583 1

QD601 - QD607 1

QD621 - QD624 1

QD641 1

QD661 - QD663 1

QD681 - QD685 1

QD691 - QD692 1

QD701 - QD702 1

QD711 - QD717 1

QD741 1

QD761 - QD769 1

QD781 - QD782 1

QD791 1

QD801 - QD804 1

QD821 - QD828 1

QD901 - QD910 1

QD931 - QD932 1

QD951 - QD954 1

QD971 - QD973 1

QD991 - QD992 1

QE001 - QE002 1

QL001 - QL008 1

QL031 - QL032 1

QL081 1

QL501 - QL515 1

2. Spares Affected

None.

B. Concurrent Requirements

None.

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BOEING SERVICE BULLETIN 727-55-0095
C. Reason

This service bulletin gives instructions to inspect the left side and right side chords of the fin closure

rib for cracking or corrosion. The fin closure rib is located at the top of the vertical fin structure. The

chords of the fin closure rib support the horizontal stabilizer hinge fittings. If the work in this service

bulletin is not done, widespread cracking in the chords may weaken the fin closure rib structure which

could result in loss of airplane control due to lack of horizontal stabilizer support.

One operator reported finding a crack on the left side chord of the fin closure rib during a routine

maintenance inspection. The crack measured a maximum of 2.4 inches long and it ran along the length

of the chord. The airplane had accumulated 5,303 flight cycles and 11,669 flight hours when the crack

was found. Cracking at this location is the result of intergranular stress corrosion caused by the material

properties of 2024-T351 extrusion from which the closure rib chord is made. This material becomes

vulnerable after the surface finishes begin to break down as a result of normal in-service aging.

A fleet history search revealed that this occurrence is the first report of intergranular cracking of the

chords. The Corrosion Prevention and Control Program (CPCP) and Maintenance Planning Data (MPD)

documentation for 727 airplanes both contain visual inspections of the chords, but no NDT inspections.

Accomplishment of the NDT and visual inspections in this service bulletin will make sure that any crack

or corrosion in the left side or right side chords of the fin closure rib is detected.

Boeing Service Related Problem (SRP) 727-SRP-55-0050 is related to this service bulletin.

Boeing Fleet Team Digest (FTD) 727 FTD 55-10001 is related to this service bulletin.

D. Description

Get access to the left side and right side chords of the fin closure rib by opening access panels at the

fin closure rib. Do a detailed inspection for any crack or corrosion and High Frequency Eddy Current

(HFEC) inspections for any crack in the left side and right side chords. If any crack or corrosion is found,

contact Boeing for repair or replacement instructions and do the work instructed by Boeing. Do repeat

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

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

Affected Maintenance Zones

Model Zone

727, 727-100, 727-100C, 727- 3-97

200, 727-200F, 727C

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BOEING SERVICE BULLETIN 727-55-0095
E. Compliance

Table 1: Vertical Stabilizer - Fin Closure Rib Chord Inspection

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 24 months 26 months.

after the original issue date of this

service bulletin.

Do a detailed inspection for

any crack or corrosion and

High Frequency Eddy Current

(HFEC) inspections for any

crack in the left side and right

side chords of the fin closure

rib in accordance with Accomplishment Instructions paragraph 3.B. Part 2.

All airplanes

Before further -

flight.

Contact Boeing for repair or

replacement instructions and

do the work instructed by

Boeing.

Any crack 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.

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.

Task Number of Persons Task Hours Elapsed Hours

Preparation 1 1.00 1.00

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Task Number of Persons Task Hours Elapsed Hours

Open Access 1 1.50 1.50

FIGURE 1 2 6.00 3.00

FIGURE 2 2 6.00 3.00

Restoration 1 1.00 1.00

Close Access 1 1.50 1.50

TOTAL FOR EACH AIRPLANE 17.00 11.00

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not applicable.

J. References

1. Existing Data:

a. Boeing Service Related Problem (SRP) 727-SRP-55-0050

b. Standard Overhaul Practices Manual (SOPM) 20-41-05

c. 727 Aircraft Maintenance Manual (AMM) 12-30-05, 27-30-00

d. 727 Fleet Team Digest (FTD) 55-10001

e. 727 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00, Figure 4, Figure 23.

f. Boeing Service Letter 727-SL-51-041.

2. Data Supplied with this Service Bulletin:

None.

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

None.

K. Publications Affected

1. Publications:

None.

2. Damage Tolerance Based Structural Inspections:

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BOEING SERVICE BULLETIN 727-55-0095
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 727-55-0095

BLANK PAGE
2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the kits/parts shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators

are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.

The kits/parts are subject to the terms and conditions of the Boeing standard purchase order

acknowledgment. Prices are in United States Dollars. Terms: Net 30 days.

Reference this service bulletin and submit your purchase order by one of these methods:

1. Order on-line via ATA Spec 2000 or The Boeing PART Page

2. Fax to (206) 662-7145

REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER

AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION

Unit Price as of

the date of this

Service Bulletin

(US Dollars)

ROLT as of the

date of this Service Bulletin (Calendar Days)

Number Name

65-16804-1 Chord LH - 49,066.00

65-16804-2 Chord RH - 49,066.00

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

Part Number / Speci- QTY Name Notes

fication

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

65-16804-1 1 Chord LH -

65-16804-2 1 Chord RH -

(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.

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BOEING SERVICE BULLETIN 727-55-0095
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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BOEING SERVICE BULLETIN 727-55-0095
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

– Hole dimensions for standard solid rivets and fasteners are in Structural Repair

Manual (SRM) Chapter 51

– Torque limits to tighten nuts and bolts are in SRM Chapter 51

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

SRM Chapter 51.

5. 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.

9. Shaded areas in Figures are reference only. Shaded areas in Figures may look

different than your airplane.

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BOEING SERVICE BULLETIN 727-55-0095
B. WORK INSTRUCTIONS

1. PART 1 - PREPARATION AND ACCESS

a. Place the horizontal stabilizer leading edge in the full down position.

b. Position the horizontal stabilizer trim cutout switches to CUTOUT.

c. Depressurize the elevator hydraulic systems A and B. Refer to 727 AMM 27-30-00 as an

accepted procedure.

d. Open all autopilot circuit breakers on the P18 panel and install DO-NOT-CLOSE identifiers.

e. Get access to the fin upper closure rib by removing access panels 9705, 9706, 9710, 9711,

9777 and 9778. Refer to 727 AMM 12-30-05 as an accepted procedure.

2. PART 2 - INSPECTION

a. Prepare the area for safe work. Refer to Part 1 as an accepted procedure.

b. Do a detailed inspection for any crack or corrosion and High Frequency Eddy Current (HFEC)

inspections for any crack in the left side chord of the fin closure rib in accordance with FIGURE

1.

(1) If any crack or corrosion is found, do one of the options that follow:

(a) Contact Boeing for replacement instructions and replace the left side chord with a

new or serviceable left side chord, part number 65-16804-1, in accordance with the

instructions provided by Boeing.

(b) Contact Boeing for repair instructions and do the work instructed by Boeing.

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

1.E., Compliance.

c. Do a detailed inspection for any crack or corrosion and HFEC inspections for any crack in the

right side chord of the fin closure rib in accordance with FIGURE 2.

(1) If any crack or corrosion is found, do one of the options that follow:

(a) Contact Boeing for replacement instructions and replace the right side chord with a

new or serviceable right side chord, part number 65-16804-2, in accordance with the

instructions provided by Boeing.

(b) Contact Boeing for repair instructions and do the work instructed by Boeing.

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

1.E., Compliance.

d. Apply BMS 3-23, Type 2 Corrosion Inhibiting Compound to exposed areas of the fin closure

rib. Refer to SOPM 20-41-05 as an accepted procedure.

e. Put the airplane back to a serviceable condition. Refer to Part 3 as an accepted procedure.

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BOEING SERVICE BULLETIN 727-55-0095
3. PART 3 - RESTORATION AND CLOSE ACCESS

a. Close access panels 9705, 9706, 9710, 9711, 9777 and 9778. Refer to 727 AMM 12-30-05

as an accepted procedure.

b. Close all autopilot circuit breakers on the P18 panel and remove DO-NOT-CLOSE identifiers.

c. Pressurize the elevator hydraulic systems A and B. Refer to 727 AMM 27-30-00 as an accepted

procedure.

d. Position the horizontal stabilizer trim cutout switches to NORMAL.

e. Put the airplane back to a serviceable condition.

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BOEING SERVICE BULLETIN 727-55-0095
FIGURE 1: VERTICAL STABILIZER - LEFT SIDE FIN CLOSURE RIB CHORD INSPECTION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 727-55-0095
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 one side of the airplane.

Step Task Name Identification Qty More Data

1 Inspect Left Side Chord 65-16804-1 1 (a)

2 Inspect Left Side Chord 65-16804-1 1 (b) (f)

3 Inspect Left Side Chord 65-16804-1 1 (c) (g)

4 Inspect Left Side Chord 65-16804-1 1 (d)

5 Inspect Left Side Chord 65-16804-1 1 (e)

(a) Do a detailed inspection for any crack or corrosion in the left side chord of the fin closure rib.

(b) Do a detailed inspection for any crack or corrosion in the internal surfaces of the left side chord of the fin

closure rib. A borescope can be used for the inspection of the internal surfaces of the chord. Access to

internal surfaces can be achieved through the two access holes in the fin closure rib web.

(c) Do a High Frequency Eddy Current (HFEC) transverse scan inspection for any crack in the chord lower

radii in accordance with 727 NDT Part 6, 51-00-00, Figure 4 or Figure 23. Access to internal surfaces can

be achieved through the two access holes in the fin closure rib web. A flexible shaft pencil probe and visual aids such as borescope and flashlight can be used as necessary to assist with the inspection of internal surfaces. At any location where the radius cannot be scanned because it is covered by structure,

no HFEC inspection is required.

(d) Do a HFEC parallel scan inspection for any crack in the chord upper radius in accordance with 727 NDT

Part 6, 51-00-00, Figure 4 or Figure 23. At any location where the upper radius cannot be scanned because

it is covered by structure, no HFEC inspection is required.

(e) Do a HFEC inspection for any crack in the upper edge of the chord in accordance with 727 NDT Part 6,

51-00-00, Figure 4 or Figure 23. At any location where the upper edge cannot be scanned because it is

covered by structure, no HFEC inspection is required.

(f) For the borescope or video probe inspection of the forward 10 inches of the chord, it is necessary to attach

a dowel rod to the borescope or video probe if a flexible borescope or video probe is used. A sleeve (tube)

for the flexible borescope or video probe can be used instead of a dowel rod to make the flexible borescope

or video probe rigid.

(g) A 90 degree pencil probe with a minimum shaft length of 8 inches is required to reach the forward most

inspection area on the chord. Alternatively, a shorter 90 degree probe can be used with a dowel rod attached to the handle. A shorter 90 degree probe can be used for the remaining inspection areas.

FIGURE 1: VERTICAL STABILIZER - LEFT SIDE FIN CLOSURE RIB CHORD INSPECTION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 727-55-0095
FIGURE 2: VERTICAL STABILIZER - RIGHT SIDE FIN CLOSURE RIB CHORD INSPECTION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 727-55-0095
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 one side of the airplane.

Step Task Name Identification Qty More Data

1 Inspect Right Side Chord 65-16804-2 1 (a)

2 Inspect Right Side Chord 65-16804-2 1 (b) (f)

3 Inspect Right Side Chord 65-16804-2 1 (c) (g)

4 Inspect Right Side Chord 65-16804-2 1 (d)

5 Inspect Right Side Chord 65-16804-2 1 (e)

(a) Do a detailed inspection for any crack or corrosion in the right side chord of the fin closure rib.

(b) Do a detailed inspection for any crack or corrosion in the internal surfaces of the right side chord of the

fin closure rib. A borescope can be used for the inspection of the internal surfaces of the chord. Access

to internal surfaces can be achieved through the two access holes in the fin closure rib web.

(c) Do a High Frequency Eddy Current (HFEC) transverse scan inspection for any crack in the chord lower

radii in accordance with 727 NDT Part 6, 51-00-00, Figure 4 or Figure 23. Access to internal surfaces can

be achieved through the two access holes in the fin closure rib web. A flexible shaft pencil probe and visual aids such as borescope and flashlight can be used as necessary to assist with the inspection of internal surfaces. At any location where the radius cannot be scanned because it is covered by structure,

no HFEC inspection is required.

(d) Do a HFEC parallel scan inspection for any crack in the chord upper radius in accordance with 727 NDT

Part 6, 51-00-00, Figure 4 or Figure 23. At any location where the upper radius cannot be scanned because

it is covered by structure, no HFEC inspection is required.

(e) Do a HFEC inspection for any crack in the upper edge of the chord in accordance with 727 NDT Part 6,

51-00-00, Figure 4 or Figure 23. At any location where the upper edge cannot be scanned because it is

covered by structure, no HFEC inspection is required.

(f) For the borescope or video probe inspection of the forward 10 inches of the chord, it is necessary to attach

a dowel rod to the borescope or video probe if a flexible borescope or video probe is used. A sleeve (tube)

for the flexible borescope or video probe can be used instead of a dowel rod to make the flexible borescope

or video probe rigid.

(g) A 90 degree pencil probe with a minimum shaft length of 8 inches is required to reach the forward most

inspection area on the chord. Alternatively, a shorter 90 degree probe can be used with a dowel rod attached to the handle. A shorter 90 degree probe can be used for the remaining inspection areas.

FIGURE 2: VERTICAL STABILIZER - RIGHT SIDE FIN CLOSURE RIB CHORD INSPECTION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 727-55-0095