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Commercial

Airplane

Group 767

Service Bulletin

Number: 767-27-0187

Date: June 25, 2007

ATA System: 2731

SUBJECT: FLIGHT CONTROLS - Elevator - Elevator Power Control Actuator Bellcrank 

Replacement

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET

Copyright © 2007 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Unpublished Work - All Rights Reserved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 

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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, BBJ, DC-8, DC-9, 

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BOEING SERVICE BULLETIN 767-27-0187

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 Table of Contents

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BOEING SERVICE BULLETIN 767-27-0187

Table of Contents

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . 13

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . 13

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 13

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: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 17

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

FIGURE 1: Left Elevator PCA Bellcrank Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

FIGURE 2: Right Elevator PCA Bellcrank Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . 24

FIGURE 3: PCA Bellcrank Rework . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
 Table of Contents

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BOEING SERVICE BULLETIN 767-27-0187

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Commercial

Airplane

Group 767

Service Bulletin

Number: 767-27-0187 Summary

Date: June 25, 2007

ATA System: 2731

SUBJECT: FLIGHT CONTROLS - Elevator - Elevator Power Control Actuator Bellcrank 

Replacement

CONCURRENT REQUIREMENTS

None.

BACKGROUND

This service bulletin gives instructions to replace or rework elevator Power Control Actuator (PCA) bellcranks. 

As an alternative to Boeing Alert Service Bulletin 767-27A0169, the incorporation of this service bulletin 

combined with the repetitive check of the elevator PCA input rod assemblies recommended in Boeing Service 

Bulletin 767-27-0201 and the repetitive check of the elevator PCA rigging recommended in Boeing Service 

Bulletin 767-27-0203 will prevent continued operation with yielded or failed shear rivets in a bellcrank assembly 

for the elevator PCA and will also allow for longer inspection intervals. Operators are currently required by the 

Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2001-04-09 to do the 400 flight-hour 

repetitive check recommended in Boeing Alert Service Bulletin 767-27A0169.

One operator reported the left elevator drooping during a preflight check. Examination of the elevator control 

system found sheared rivets in the left-inboard and center PCA bellcrank assemblies. The elevator single 

hydraulic system check required by a Certification Maintenance Requirement (CMR) may not detect yielded or 

failed shear rivets in the bellcrank assemblies for the elevator PCA. As a result, the FAA issued AD 2000-17-05 

to mandate the accomplishment of the actions specified in Boeing Alert Service Bulletin 767-27A0166, dated 

August 17, 2000.

Since the issuance of AD 2000-17-05, the FAA has received reports that several 767-200, 767-300, and 767-

300F airplanes failed the one-time functional check of the shear rivets required by the AD. As a result, the FAA 

issued AD 2001-04-09 to mandate the accomplishment of the actions specified in Boeing Alert Service Bulletin 

767-27A0169, dated November 21, 2000.

A detailed design review found that the override device incorporated into the elevator PCA input rod assembly 

provides protection against malfunctions and non-normal PCA operation. This design review also found that the 

shear rivets are not needed. The incorporation of this service bulletin combined with the repetitive check of the 

elevator PCA input rod assemblies recommended in Boeing Service Bulletin 767-27-0201 and the repetitive 

check of the elevator PCA rigging recommended in Boeing Service Bulletin 767-27-0203 is an alternative to the 

400 flight-hour repetitive check recommended in Boeing Alert Service Bulletin 767-27A0169.

Boeing Service Related Problem (SRP) 767-SRP-27-0128 is related to this service bulletin.
 

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BOEING SERVICE BULLETIN 767-27-0187

ACTION (PRR B12901-35S)

Do a general visual inspection for the three PCA bellcranks assemblies on each elevator. If a bellcrank assembly 

has shear rivets, replace it with a solid one-piece bellcrank assembly or rework the bellcrank assembly. Do a 

pogo check for each elevator PCA input rod assembly. Do a mis-rig check for each elevator.

EFFECTIVITY

767-400ER Airplanes. Refer to Paragraph 1.A.1 Airplanes, for the list of affected airplanes.

COMPLIANCE

Boeing recommends the instructions in this service bulletin be done within six years after the date on this service 

bulletin.

The 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.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

MANPOWER

MATERIAL INFORMATION

Operator Supplied Parts/Materials.

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

Total Task Hours Elapsed Hours

29.0 18.0
 

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LEFT SIDE SHOWN

INDEX

DO A MIS-RIG CHECK

(2 LOCATIONS)

PLATE

ELEVATOR

EDGE

TRAILING

ELEVATOR PCAS

(LEFT SIDE SHOWN)

DO A POGO CHECK

(6 LOCATIONS)

ASSEMBLY

THE BELLCRANK

REPLACE OR REWORK

SHOWN DISASSEMBLED FOR CLARITY

BELLCRANK ASSEMBLY (TYPICAL) FWD

B

FWD

SEE A

SEE A

SEE A

SEE B

A

W31123
 

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BOEING SERVICE BULLETIN 767-27-0187

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Commercial

Airplane

Group 767

Service Bulletin

Number: 767-27-0187

Date: June 25, 2007

ATA System: 2731

SUBJECT: FLIGHT CONTROLS - Elevator - Elevator Power Control Actuator Bellcrank 

Replacement

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

Refer to Service Bulletin Index Document D624T001 Part 3 for Airplane Variable Number, Line 

Number, and Serial Number data.

This service bulletin is for the airplanes shown below. An equivalent change is on subsequent 

production airplanes. Refer to PRR B12901-35S for data about this change.

Airplane models:

767-400ER

IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER

CONTINENTAL AIRLINES (CAL)

1 VQ071–VQ086

DELTA AIR LINES (DAL)

1 VQ001–VQ021

IDENTIFICATION BY VARIABLE NUMBER

GROUP CONFIGURATION DESCRIPTION

1 - 767-400ER airplanes line numbers 1-901.

Variable Group

VQ001–VQ021 1

VQ071–VQ086 1
 

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BOEING SERVICE BULLETIN 767-27-0187

2. Spares Affected

Examine your spares supply for the parts or components identified in Paragraph 2.C., Parts 

Necessary for Each Airplane. If any parts or components are found, refer to Paragraph 2.C. for 

the recommended use.

B. Concurrent Requirements

None.

C. Reason

This service bulletin gives instructions to replace or rework elevator Power Control Actuator (PCA) 

bellcranks. As an alternative to Boeing Alert Service Bulletin 767-27A0169, the incorporation of this 

service bulletin combined with the repetitive check of the elevator PCA input rod assemblies 

recommended in Boeing Service Bulletin 767-27-0201 and the repetitive check of the elevator PCA 

rigging recommended in Boeing Service Bulletin 767-27-0203 will prevent continued operation with 

yielded or failed shear rivets in a bellcrank assembly for the elevator PCA and will also allow for longer 

inspection intervals. Operators are currently required by the Federal Aviation Administration (FAA) 

Airworthiness Directive (AD) 2001-04-09 to do the 400 flight-hour repetitive check recommended in 

Boeing Alert Service Bulletin 767-27A0169.

One operator reported the left elevator drooping during a preflight check. Examination of the elevator 

control system found sheared rivets in the left-inboard and center PCA bellcrank assemblies. The 

elevator single hydraulic system check required by a Certification Maintenance Requirement (CMR) 

may not detect yielded or failed shear rivets in the bellcrank assemblies for the elevator PCA. As a 

result, the FAA issued AD 2000-17-05 to mandate the accomplishment of the actions specified in 

Boeing Alert Service Bulletin 767-27A0166, dated August 17, 2000.

Since the issuance of AD 2000-17-05, the FAA has received reports that several 767-200, 767-300, 

and 767-300F airplanes failed the one-time functional check of the shear rivets required by the AD. 

As a result, the FAA issued AD 2001-04-09 to mandate the accomplishment of the actions specified 

in Boeing Alert Service Bulletin 767-27A0169, dated November 21, 2000.

A detailed design review found that the override device incorporated into the elevator PCA input rod 

assembly provides protection against malfunctions and non-normal PCA operation. This design 

review also found that the shear rivets are not needed. The incorporation of this service bulletin 

combined with the repetitive check of the elevator PCA input rod assemblies recommended in Boeing 

Service Bulletin 767-27-0201 and the repetitive check of the elevator PCA rigging recommended in 

Boeing Service Bulletin 767-27-0203 is an alternative to the 400 flight-hour repetitive check 

recommended in Boeing Alert Service Bulletin 767-27A0169.

Boeing Service Related Problem (SRP) 767-SRP-27-0128 is related to this service bulletin.

D. Description

Do a general visual inspection for the three PCA bellcranks assemblies on each elevator. If a bellcrank 

assembly has shear rivets, replace it with a solid one-piece bellcrank assembly or rework the bellcrank 

assembly. Do a pogo check for each elevator PCA input rod assembly. Do a mis-rig check for each 

elevator.
 

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BOEING SERVICE BULLETIN 767-27-0187

E. Compliance

Boeing recommends the instructions in this service bulletin be done within six years after the date on 

this service bulletin.

The 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.

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.

This service bulletin has been approved by the FAA. In addition, the Manager of the FAA Seattle 

Aircraft Certification Office approves the action (i.e. inspection or modification) defined in this service 

bulletin combined with the actions defined in Boeing Service Bulletins 767-27-0201 and 767-27-0203 

as an alternative method of compliance to the requirements of paragraph (a) of AD 2001-04-09. All 

provisions of AD 2001-04-09 that are not specifically referenced in the above statement remain fully 

applicable and must be complied with.

G. Manpower

The table below shows an estimate of the task-hours necessary to do this change for each airplane. 

This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator 

task-hour data if necessary. The estimate does not include lost time. These are some examples of lost 

time:

— Time to adjust to the workplace

— Time to schedule the work

— Time to examine the work

— Time to cure the materials

— Time to make the parts

— Time to find the tools.
 

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BOEING SERVICE BULLETIN 767-27-0187

Work Package 1 can be done at the same time as Work Package 2.

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Engineering Change Memo PRR B12901-35S

b. Service Related Problem (SRP) 767-SRP-27-0128

c. 767 Aircraft Maintenance Manual (AMM) 27-31-00, 27-31-06

d. 767 Structural Repair Manual (SRM) Chapter 51

e. Boeing Standard Overhaul Practices Manual (BSOPM) 20-43-03, 20-50-10

f. Component Maintenance Manual (CMM) 27-31-64, 27-31-66

Work Package 

Number Task

Number of 

Persons Task-Hours Elapsed Hours

1 Remove PCA Input Linkage 2 3.0 1.5

Figure 1 1 0.5 0.5

Figure 3 1 3.0 3.0

Test Input Rod Assemblies 

(Pogo Check)

2 4.0 2.0

Install PCA Input Linkage 2 3.0 1.5

Mis-Rig Test 2 1.0 0.5

TOTAL FOR WORK PACKAGE 1 14.5 9.0

2 Remove PCA Input Linkage 2 3.0 1.5

Figure 2 1 0.5 0.5

Figure 3 1 3.0 3.0

Test Input Rod Assemblies 

(Pogo Check)

2 4.0 2.0

Install PCA Input Linkage 2 3.0 1.5

Mis-Rig Test 2 1.0 0.5

TOTAL FOR WORK PACKAGE 2 14.5 9.0

TOTAL FOR EACH AIRPLANE 29.0 18.0
 

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BOEING SERVICE BULLETIN 767-27-0187

g. Boeing Service Bulletin 767-27A0166

h. Boeing Service Bulletin 767-27A0169

i. Boeing Service Bulletin 767-27-0201

j. Boeing Service Bulletin 767-27-0203

k. FAA Airworthiness Directive 2000-17-05

l. FAA Airworthiness Directive 2001-04-09

m. Boeing Drawing 012W6100.

2. Data supplied with this Service Bulletin:

None.

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

None.

K. Publications Affected

L. Interchangeability and Intermixability of Parts

Refer to Paragraph 2.C., Parts Necessary For Each Airplane, for interchangeability and intermixability 

information.

Publication Chapter-Section

767 Illustrated Parts Catalog 27-31

Component Maintenance Manual 27-31
 

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BOEING SERVICE BULLETIN 767-27-0187

2. MATERIAL INFORMATION

A. Material - Price and Availability

The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary For Each 

Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service 

bulletin does not show the Boeing price and supply data.

B. Industry Support Information

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

C. Parts Necessary For Each Airplane

1. Kits/Parts:

None.
 

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BOEING SERVICE BULLETIN 767-27-0187

2. Parts and Materials Supplied by the Operator:

3. Parts Modified and Reidentified:

The parts shown below are changed as shown in this service bulletin. The quantity (QTY) is the 

number of parts changed on each airplane.

4. Parts Removed and Not Replaced:

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

Part Number / 

Specification QTY Name Existing Part Number Notes

252T2118-6 (a) 6 PCA Bellcrank 

Assembly

252T2118-1 or 

252T2118-2 or 

256T2118-3

BACR15FT6KE9C 

(b)

12 Rivet 252T3139-3 or 

BACR15BB5AD9C

BMS 3-24 1 pint Grease - (c)

BMS 10-11, Type 1 8 

ounces

Primer - (c)

Alodine 600 or 

1200

8 

ounces

Chemical 

Conversion 

Coating

- (d)

(a) This part is required if bellcranks are being replaced.

(b) This part is required if existing bellcranks are being reworked.

(c) See the Qualified Products List at the end of the Boeing Material Specification (BMS) 

for supplier data.

(d) Refer to BSOPM 20-43-03 for applicable suppliers.

Existing Part 

Number QTY Name New Part Number Notes

252T2118-1 6 Bellcrank Assembly 252T2118-4 (a), (b), (c)

252T2118-2 or 

252T2118-3

6 Bellcrank Assembly 252T2118-5 (a), (b), (c)

(a) This is the part number after the change given in this service bulletin, if the existing 

bellcranks are being reworked.

(b) Do not use the existing part to replace the new or changed part.

(c) This part is not used in production. The equivalent production part number is 

252T2118-6.
 

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BOEING SERVICE BULLETIN 767-27-0187

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 767-27-0187

3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

WARNING: DO NOT SUPPLY HYDRAULIC POWER DURING THE REMOVAL /INSTALLATION

OF THE PCA BELLCRANK ASSEMBLY. INJURY TO PERSONS OR DAMAGE TO

EQUIPMENT CAN OCCUR.

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. The work instructions are divided into work packages. Task-Hours and Elapsed-Hours 

for each package are given in Paragraph 1.G., Manpower. The work instructions for the 

left and right elevators are the same and both work packages need to be completed 

before the plane is returned to service.

4. 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

— Hole dimensions for standard solid rivets are given in 767 Structural Repair 

Manual, Chapter 51

5. For approved fastener and process material substitutions, refer to 767 Structural Repair 

Manual, Chapter 51, Alternate fasteners are given in 767 Structural Repair Manual 

Chapter 51 and Boeing Drawing 012W6100.

6. If the length of fasteners specified in this service bulletin do not meet the installation 

standards, fasteners of the same specification, or an approved substitute, one grip 

length longer or shorter may be used.

7. A General Visual Inspection is defined as: A visual examination of an interior or exterior 

area, installation or assembly to detect obvious damage, failure or irregularity. This level 

of inspection is made from within touching distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to all surfaces in the inspection area. This 

level of inspection is made under normal available lighting conditions such as daylight, 

hangar lighting, flashlight or drop-light and may require removal or opening of access 

panels or doors. Stands, ladders or platforms may be required to gain proximity to the 

area being checked.

8. These work instructions refer to procedures included on other Boeing documents. 

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

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BOEING SERVICE BULLETIN 767-27-0187

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

in" are included in the instruction, the procedure in the Boeing document must be used.

B. WORK INSTRUCTIONS

WORK PACKAGE 1 - LEFT ELEVATOR

1. Remove elevator Power Control Actuator (PCA) input linkage. Refer to 767 AMM 27-31-06 as an 

accepted procedure. 

2. Do a general visual inspection of the three PCA bellcrank assemblies as given in Figure 1.

a. If the bellcrank assembly has solid rivets and part number 252T2118-4 or 252T2118-5, no 

more action is required for the bellcrank.

b. If the bellcrank is a solid one-piece bellcrank (no rivets), no more action is required for the 

bellcrank.

c. If the bellcrank assembly has shear rivets and part number 252T2118-1, 252T2118-2, or 

252T2118-3, do one of the two following steps:

(1) At operator’s discretion, rework the existing bellcrank to replace the shear rivets with 

solid rivets as given in Figure 3. After rework, the 252T2118-2 or 252T2118-3 bellcrank 

assembly is changed to 252T2118-5 and the 252T2118-1 bellcrank assembly is 

changed to 252T2118-4. 

(2) Obtain new solid one-piece (no rivets) bellcrank assembly 252T2118-6. Use this new 

bellcrank assembly in step 4.

3. Do the following functional test (pogo check) on each of the three elevator PCA input rod 

assemblies.

a. Make sure that the load is 42-62 lbs for initial breakout in the extending and collapsing 

directions.

b. Make sure that the load is 67-97 lbs for travel 0.005 to 0.020 inches from the fully 

compressed or extended position.

c. Make sure that the defection is 1.15-1.35 inches in both fully compressed or extended 

position at full travel of the elevator PCA input rod assembly.

d. Make sure that all operations are smooth and free from binding.

e. Replace or overhaul the elevator PCA input rod assembly if it fails to meet any requirement 

above. Refer to CMM 27-31-64 as an accepted procedure.

4. Install elevator PCA input linkage. Refer to 767 AMM 27-31-06 as an accepted procedure.

5. Do the elevator PCA Mis-Rig test. Refer to 767 AMM 27-31-00 as an accepted procedure.

6. Put the airplane back to a serviceable condition.
 

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BOEING SERVICE BULLETIN 767-27-0187

WORK PACKAGE 2 - RIGHT ELEVATOR

1. Remove elevator PCA input linkage. Refer to 767 AMM 27-31-06 as an accepted procedure. 

2. Do a general visual inspection of the three PCA bellcrank assemblies as given in Figure 2.

a. If the bellcrank assembly has solid rivets and part number 252T2118-4 or 252T2118-5, no 

more action is required for the bellcrank.

b. If the bellcrank is a solid one-piece bellcrank (no rivets), no more action is required for the 

bellcrank.

c. If the bellcrank assembly has shear rivets and part number 252T2118-1, 252T2118-2, or 

252T2118-3, do one of the two following steps:

(1) At operator’s discretion, the existing bellcrank can be reworked to replace the shear 

rivets with solid rivets as given in Figure 3. After rework, the 252T2118-2 or 252T2118-

3 bellcrank assembly is changed to 252T2118-5 and the 252T2118-1 bellcrank 

assembly is changed to 252T2118-4. 

(2) Obtain new solid one-piece (no rivets) bellcrank assembly 252T2118-6. Use this new 

bellcrank assembly in step 4.

3. Do the following functional test (pogo check) on each of the three elevator PCA input rod 

assemblies.

a. Make sure that the load is 42-62 lbs for initial breakout in the extending and collapsing 

directions.

b. Make sure that the load is 67-97 lbs for travel 0.005 to 0.020 inches from the fully 

compressed or extended position.

c. Make sure that the defection is 1.15-1.35 inches in both fully compressed or extended 

position at full travel of the elevator PCA input rod assembly.

d. Make sure that all operations are smooth and free from binding.

e. Replace or overhaul the elevator PCA input rod assembly if it fails to meet any requirement 

above. Refer to CMM 27-31-64 as an accepted procedure.

4. Install elevator PCA input linkage. Refer to 767 AMM 27-31-06 as an accepted procedure.

5. Do the elevator PCA Mis-Rig test. Refer to 767 AMM 27-31-00 as an accepted procedure.

6. Put the airplane back to a serviceable condition.
 FIGURE 1: Left Elevator PCA Bellcrank Inspection

June 25, 2007

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BOEING SERVICE BULLETIN 767-27-0187

FIGURE 1: Left Elevator PCA Bellcrank Inspection

BELLCRANK ASSEMBLY

(TYPICAL)

FOR CLARITY)

(SHOWN DISASSEMBLED

(SOLID ONE-PIECE)

BELLCRANK ASSEMBLY

ELEVATOR PCAs

BELLCRANK ASSEMBLY

(SOLID RIVETS)

BELLCRANK ASSEMBLY

(SHEAR RIVETS)

REQUIRED

NO INSPECTION

NO RIVETS

IN THE MIDDLE

NO INSPECTION HOLE

SOLID RIVETS WITH

THE MIDDLE

INSPECTION HOLE IN

0.070 INCH (1.77 mm)

SHEAR RIVETS WITH

CENTER

OUTBOARD

INBOARD

FWD

A

E

1

2

C D E

B

SEE B

SEE B

SEE A

SEE B

SEE C D

W31128

(SHEET 1 OF 2)
 FIGURE 1: Left Elevator PCA Bellcrank Inspection

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BOEING SERVICE BULLETIN 767-27-0187

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. 

STEP TASK NAME PART NUMBER QTY MORE DATA

1 Inspect Bellcrank Assembly - 3 Do a general visual inspection of 

rivets at locations shown. Note type 

of rivets.

2 Inspect Bellcrank Assembly - 3 Do a general visual inspection for 

part number

(SHEET 2 OF 2)
 FIGURE 2: Right Elevator PCA Bellcrank Inspection

June 25, 2007

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BOEING SERVICE BULLETIN 767-27-0187

FIGURE 2: Right Elevator PCA Bellcrank Inspection

ELEVATOR PCAs

SOLID RIVETS WITH

NO INSPECTION HOLE

IN THE MIDDLE

NO RIVETS

NO INSPECTION

REQUIRED

BELLCRANK ASSEMBLY

(SOLID RIVETS) (SOLID ONE-PIECE)

BELLCRANK ASSEMBLY

(SHOWN DISASSEMBLED

FOR CLARITY)

(TYPICAL)

BELLCRANK ASSEMBLY

INBOARD

OUTBOARD

CENTER

THE MIDDLE

SHEAR RIVETS WITH

0.070 INCH (1.77 mm)

INSPECTION HOLE IN

(SHEAR RIVETS)

BELLCRANK ASSEMBLY

FWD

A

1

SEE B

SEE B

SEE B

D E

2

SEE C E D

B

SEE A

C

W31124

(SHEET 1 OF 2)
 FIGURE 2: Right Elevator PCA Bellcrank Inspection

June 25, 2007

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BOEING SERVICE BULLETIN 767-27-0187

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. 

STEP TASK NAME PART NUMBER QTY MORE DATA

1 Inspect Bellcrank Assembly - 3 Do a general visual inspection of 

rivets at locations shown. Note type 

of rivets.

2 Inspect Bellcrank Assembly - 3 Do a general visual inspection for 

part number

(SHEET 2 OF 2)
 FIGURE 3: PCA Bellcrank Rework

June 25, 2007

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BOEING SERVICE BULLETIN 767-27-0187

FIGURE 3: PCA Bellcrank Rework

66.30°

66.80°

LOWER ARM

RIVET

SHOWN DISASSEMBLED FOR CLARITY

BELLCRANK ASSEMBLY (TYPICAL)

ARM ASSEMBLY

LOWER ARM

B-B

0.35

0.33

ASSEMBLY

ARM

DIA THRU

0.202

0.191

C/L

SYMM

A-A

B

B

A

A

1 9

8

14

14

4

12

6 10

13

2 5 11

3

7

8

9

W31132

(SHEET 1 OF 3)
 FIGURE 3: PCA Bellcrank Rework

June 25, 2007

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BOEING SERVICE BULLETIN 767-27-0187

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 bellcrank.

STEP TASK NAME PART NUMBER QTY NOTES

1 Remove /

Discard

Shear Rivet 252T3139-3 or 

BACR15BB5AD9C

2 If rivets are damaged, position 

bellcrank arms as required so rivet 

pieces are in alignment.

2 Remove /Keep Lower Arm 252T2174-( ) (a) 1 Remove lower arm from arm 

assembly. 

3 Remove /DiscardMarker BAC27TCT0114 1

4 Clean Lower Arm and 

Arm Assembly

252T2174-( ) and 

252T2173-( ) 

(a)(b)

2 Clean the mating surfaces of each 

part. If damage is found refer to CMM 

27-31-66 to repair parts. 

5 Install Lower Arm 252T2174-( ) (a) 1 Attach to arm assembly. 

6 Inspect Lower Arm and 

Arm Assembly

252T2174-( ) and 

252T2173-( ) 

(a)(b)

- Make sure that the lower arm turns 

freely on the shaft of the arm 

assembly. Hold lower arm in vertical 

position and place arm assembly in 

horizontal position. Release arm 

assembly and make sure it rotates 

freely to vertical position. 

7 Ream Lower Arm 

Hole

- 1 If necessary, to increase diameter of 

hole to the minimum dimension 

(1.1255-1.1260 inch) that lets the part 

turn freely. Repeat with inspection until 

part turns freely with no binding.

8 Rotate Lower Arm and 

Arm Assembly

252T2174-( ) and 

252T2173-( ) 

(a)(b)

1 To put bellcrank arms in the position 

shown. Use clamps to hold the 

bellcrank arms in position shown. 

9 Drill / Ream Rivet holes - 2 Increase the diameter of the rivet holes 

to dimension shown (0.191-0.202 inch) 

while keeping bellcrank arms in 

position. Make sure to put a temporary 

cover on the bearing in the arm 

assembly. Metal particles can cause 

damage to the bearing.

10 Disassemble / 

Clean

Lower Arm and 

Arm Assembly

252T2174-( ) and 

252T2173-( ) 

(a)(b)

- Make sure to remove all particles and 

burrs from the mating surfaces of each 

part. Remove the cover from the 

bearing. 

11 Install Lower Arm 252T2174-( ) (a) - Apply grease to the mating surfaces of 

the lower arm and the arm assembly. 

Use a temporary clamp to hold the 

bellcrank arms in the position shown. 

Use Grease BMS 3-24 -

12 Install Rivets BACR15FT6KE9C 2 Apply grease to all surfaces of each 

rivet. Use Grease BMS 3-24 -

(SHEET 2 OF 3)
 FIGURE 3: PCA Bellcrank Rework

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BOEING SERVICE BULLETIN 767-27-0187

13 Part Mark Bellcrank 

Assembly

- 1 Rubber stamp new bellcrank assembly 

part number 252T2118-5 on arm 

assembly for reworked bellcrank 

252T2118-2 and 252T2118-3. Rubber 

stamp new bellcrank assembly part 

number 252T2118-4 on arm assembly 

for reworked bellcrank 252T2118-1. 

Refer to BSOPM 20-50-10.

14 Apply Chemical 

Conversion 

Coating

Alodine 600 or 

1200 

- To any bare surfaces on lower arm and 

arm assembly. Refer to CMM 27-31-

66.

Primer BMS 10-11, Type 1 -

(a) Lower arm 252T2174 -( ) part numbers are 252T2174-1, 252T2174-3, 252T2174-5 and 252T2174-6

(b) Arm assembly 252T2173-( ) part numbers are 252T2173 -1 and 252T2173 -5

STEP TASK NAME PART NUMBER QTY NOTES

(SHEET 3 OF 3)