Commercial 

Airplanes 767

Service Bulletin

ALERT

Number: 767-27A0227

Original Issue: February 12, 2013

ATA System: 2751

SUBJECT: FLIGHT CONTROLS - Flaps - Outboard Flap Actuator Crank Arm Mechanism - Flap

Positions 1, 2, 7 and 8 Bearing Inspection/Replacement

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

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

laws.

ECCN: 9E991

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ALERT ALERT

BLANK PAGE
Table of Contents

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

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

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

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

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

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

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

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 29

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 32

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 35

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

FIGURE 1: INSPECT THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT

RIB ASSEMBLY IN FLAP POSITIONS 1, 2, 7, AND 8, OUTBOARD SIDE [Group 1-3,

Configuration 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52

FIGURE 2: INSPECT THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT

RIB ASSEMBLY IN FLAP POSITIONS 1, 2, 7, AND 8, INBOARD SIDE [Group 1-3, Configuration

2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55

FIGURE 3: RESTORE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT

RIB ASSEMBLY IN FLAP POSITIONS 1, 2, 7, AND 8, OUTBOARD SIDE [Group 1-3,

Configuration 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 58

FIGURE 4: RESTORE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT

RIB ASSEMBLY IN FLAP POSITIONS 1, 2, 7, AND 8, INBOARD SIDE [Group 1-3, Configuration

2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 61

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
FIGURE 5: REPLACE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT

RIB ASSEMBLY IN FLAP POSITION 1 [Group 1-3, Configuration 2] . . . . . . . . . . . . 63

FIGURE 6: REPLACE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT

RIB ASSEMBLY IN FLAP POSITION 2 [Group 1-3, Configuration 2] . . . . . . . . . . . . 66

FIGURE 7: REPLACE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT

RIB ASSEMBLY IN FLAP POSITION 7 [Group 1-3, Configuration 2] . . . . . . . . . . . . 69

FIGURE 8: REPLACE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT

RIB ASSEMBLY IN FLAP POSITION 8 [Group 1-3, Configuration 2] . . . . . . . . . . . . 72

FIGURE 9: RE-IDENTIFY THE TRAILING EDGE (TE) FLAP SUPPORT RIB ASSEMBLY FOR APPLICABLE

FLAP POSITIONS WITH CORRECT NEW PART NUMBERS [Group 1, 3, Configuration 1] . 75

APPENDIX A: BEARING DAMAGE DEFINITIONS AND SUGGESTED WORKSHEET TO RECORD THE

CONDITION OF THE REMOVED BEARINGS [Group 1-3, Configuration 2] . . . . . . . . 76

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Commercial 

Airplanes 767

Service Bulletin

ALERT

Summary Number: 767-27A0227

Original Issue: February 12, 2013

ATA System: 2751

SUBJECT: FLIGHT CONTROLS - Flaps - Outboard Flap Actuator Crank Arm Mechanism - Flap

Positions 1, 2, 7 and 8 Bearing Inspection/Replacement

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

Accomplishment of this service bulletin will replace the Trailing Edge (TE) Flap support bearings without a roller

retention feature at the TE Flap support rib assembly in Flap Positions 1, 2, 7, and 8 with new bearings with a

roller retention feature. The TE Flap support bearings are integral components of the TE Flap support rib

assemblies. The TE Flap rotary actuators and position transmitters are attached to the TE support rib assemblies

along the rear spar. Not replacing the TE Flap support bearings can, in the event of an undetected bearing

failure, lead to damage to the TE rotary actuators and other TE Flap support rib parts, which could result in a

dual Flap drive system disconnect in both TE Flap rotary actuators, and a possible Flaps blowback with loss of

controllability of the airplane.

There have been several cases of varying degrees of TE Flap support bearings damage at the TE Flap support

rib assemblies in Flap Positions 1, 2, 4, 5, 7, and 8. An operator reported "TE FLAP ASYM" and "TE SHUT

DOWN" messages at Flap 5 during a landing approach. Bearing damage was found at the Outboard E Flap

support rib assembly in Flap Positions 1, 2, 7, and 8, and at the Inboard TE Flap support rib assembly in Positions

4 and 5. The inspection of a second airplane revealed similar TE Flap support bearing damage, but no EICAS

messages were experienced in that case. A third airplane was inspected by another operator, and similar damage

to the TE Flap support bearings was found, but no EICAS messages were experienced in that case either.

Another operator found a broken position transmitter gearbox on a fourth airplane after receiving a Flap skew

message. This airplane also had TE Flap support bearing damage in the TE Flap support rib assembly at various

TE Flap Positions. Bearing damage in the TE Flaps support rib assembly is caused by the use of dead-blow

mallets during the installation of the shaft on the TE Flap support rib assembly when TE Flap support bearings

without a roller retention feature are installed. This method of installation may compromise bearings without a

roller retention feature. The TE Flap support bearings in TE Flap Positions 3 and 6 are not affected.

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This service bulletin replaces Boeing service bulletin 767-27A0222, Original Issue. More work is necessary for

Group 1, Configuration 1 airplanes (airplanes that accomplished the terminating action given in Boeing service

bulletin 767-27A0222, Original Issue) to maintain part number configuration control of the flap support rib

assemblies. For these airplanes, the new part numbers for TE Flap support rib assembly in Flap Positions 1

and 8 were incorrect in 767-27A0222, Original Issue. The TE Flap support rib assembly part numbers should

be changed to the correct part number on the affected airplanes in this group/configuration. No more work is

necessary for Group 2, Configuration 1 airplanes. For this airplane, the new part numbers for TE Flap support

rib assembly in Flap Positions 1 and 8 were correct in 767-27A0222, Original Issue.

This service bulletin does not provide instructions to inspect/replace the TE Flap support bearings and the rotary

actuators at Flap Positions 4 and 5. The TE Flap support bearings and TE rotary actuators at these Flap Positions

are covered by service bulletin 767-27-0223. The TE Flap support bearings and TE rotary actuators at Flap

Positions 3 and 6 are not affected by the condition addressed in this service bulletin

Boeing Service Related Problem (SRP) 767-SRP-57-0235 and SRP 767-SRP-57-0255 are 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 Yes Paragraph 1.A.2., Spares Affected

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

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

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

Publications Affected Yes Paragraph 1.K., Publications Affected

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

Operations Manual or FAA Approved Airplane

Flight Manual)

Kits/Parts Required Yes Paragraph 2.C.1., Kits/Parts

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

by the Operator

Operator Supplied Parts/Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

ACTION

Group 1, 3, Configuration 1:

RE-IDENTIFY THE TRAILING EDGE (TE) FLAP SUPPORT RIB ASSEMBLY FOR APPLICABLE FLAP

POSITIONS WITH CORRECT NEW PART NUMBERS

1. Do PART 3 to reidentify the TE Flap support rib assembly at the applicable Flap Positions with the

correct new part numbers.

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Group 2, Configuration 1:

1. No action required.

Group 1-3, Configuration 2:

INSPECT THE TE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB ASSEMBLY IN FLAP

POSITIONS 1, 2, 7, AND 8:

1. Do PART 1A to do a General Visual Inspection (GVI) of the TE Flap support bearings at the TE Flap

support rib assembly in Flap Positions 1, 2, 7, and 8 to identify the type of bearing installed.

a. PART 1A, STEP 7, CONDITION 1: Two bearings with a roller retention feature are installed at the

TE Flap support rib assembly in Flap Positions 1, 2, 7, and 8.

– No bearing replacement is required. Put the airplane back to a serviceable condition in

accordance with Accomplishment Instructions PART 1B.

a. PART 1A, STEP 7, CONDITION 2: At least one bearing without a roller retention feature is installed

at the TE Flap support rib assembly in Flap Position1, 2, 7, or 8.

– Replace the two bearings at each applicable TE Flap support rib in accordance with

Accomplishment Instructions PART 2.

– Do a General Visual Inspection (GVI) of each pair of bearings removed in accordance with

Accomplishment Instructions PART 2, Step 1.d.

Group 1-3, Configuration 2:

REPLACE THE TRAILING EDGE (TE) FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITIONS 1, 2, 7, or 8:

1. Do PART 2 to replace the applicable TE Flap support bearings at the TE Flap support rib assembly in

Flap Positions 1, 2, 7, or 8 after bearing the inspection in PART 1A if one or more bearings, at any of

the applicable TE Flap Positions, do not have a roller retention feature.

2. Do a GVI of the removed TE Flap support bearings and record the damage / type bearing combination.

Use the data to find if the TE rotary actuators at Flap Positions 1, 2, 7, or 8 are serviceable or if they

need to be overhauled or replaced.

a. PART 2, STEP 1.f, 2.f, 3.f, or 4.f., CONDITION 1: Both TE Flap support bearings at TE Flap support

rib assembly in Flap Position 1 have at least one face each that meets the definitions of good or

slightly damaged bearing face.

– PART 2, Step 1.f, CONDITION 1, Step 1: The TE rotary actuator is acceptable and may be

used as-is in the applicable Flap Position(s).

b. PART 2, STEP 1.f, 2.f, 3.f, or 4.f., CONDITION 2: Only one TE Flap support bearing at the TE

Flap support rib assembly in Flap Position 1 has at least one face that meets the definition of good

or slightly damaged bearing face. The other bearing at the same TE Flap support rib assembly

has faces that meet the definitions of moderately damaged or fractured bearing face.

– PART 2, Step 1.f, CONDITION 2, Step 1: Overhaul or replace the TE rotary actuator at the

TE Flap support rib assembly in the applicable Flap Position(s).

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
c. PART 2, STEP 1.f, 2.f, 3.f, or 4.f., CONDITION 3: Both bearings at the TE Flap support rib assembly

in Flap Position 1 have all faces that meet the definitions of moderately damaged or fractured

bearing face.

– PART 2, Step 1.f, CONDITION 3, Step 1: Replace the TE rotary actuator at the TE Flap

support rib assembly in the applicable Flap Position(s).

Group 1-3, Configuration 2:

FUNCTIONAL TEST AFTER BEARING REPLACEMENT:

1. Do the functional test after the TE Flap rib support bearings have been replaced at Flap Position 1, 2,

7 or 8.

EFFECTIVITY

767-200/-300/-300F/-400ER Airplanes that have bearings without a roller retention feature installed at the Trailing

Edge (TE) Flap support ribs. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.

COMPLIANCE

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service

bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin

mandatory.

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of July 15, 2009. Please refer to Paragraph

2.B., Industry Support Information.

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

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BLANK PAGE
Commercial 

Airplanes 767

Service Bulletin

ALERT

Number: 767-27A0227

Original Issue: February 12, 2013

ATA System: 2751

SUBJECT: FLIGHT CONTROLS - Flaps - Outboard Flap Actuator Crank Arm Mechanism - Flap

Positions 1, 2, 7 and 8 Bearing Inspection/Replacement

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

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

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

Serial Number data.

GROUP CONFIGURATION DESCRIPTION

1 - 767-200/300/300F/400ER Airplanes Line Number 949 - 981

Airplanes that accomplished the terminating action in Boeing service

bulletin 767-27A0222, Original Issue, but need to repart mark the TE

Flap support rib assembly in Flap Positions 1 and 8

1

Airplanes that did not accomplish the terminating action in Boeing

service bulletin 767-27A0222, Original Issue

2

2 - 767-300F Airplane Line Number 982

Airplanes that accomplished the terminating action in Boeing service

bulletin 767-27A0222, Original Issue

1

Airplanes that did not accomplished the terminating action in Boeing

service bulletin 767-27A0222, Original Issue

2

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GROUP CONFIGURATION DESCRIPTION

3 - 767-300/300F/400ER Airplanes Line Number 740-810

Airplanes that replaced the Trailing Edge Flap support bearings with

bearings with a retention feature, but need to repart mark the TE Flap

support rib assembly in Flap Positions 1, 2, 7 and 8

1

Airplanes that have not inspected/replaced the Trailing Edge Flap

support bearings with bearings with a retention feature

2

Airplane Models:

767-200, 767-300, 767-300F, 767-400ER

Variable Number Group

VQ001 - VQ009 3

VQ071 - VQ073 3

VQ111 1

VR089 1

VR108 - VR109 1

VR207 - VR209 3

VR256 - VR257 3

VR266 1

VR422 3

VR441 3

VR472 3

VS055 - VS056 3

VS076 - VS078 3

VS095 - VS102 3

VS112 - VS113 3

VS137 3

VS201 - VS203 3

VS208 3

VS216 - VS217 3

VS270 - VS274 3

VS291 3

VS302 3

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Variable Number Group

VS307 3

VS316 3

VS321 - VS324 3

VS366 - VS367 3

VS381 - VS382 3

VS391 - VS392 3

VS401 3

VS466 - VS470 3

VS486 3

VS496 3

VS506 - VS507 3

VS716 - VS720 1

VS733 - VS736 1

VS904 - VS910 1

VS912 1

VS916 1

VS921 - VS922 1

VS931 - VS933 1

VT531 - VT533 1

VT541 - VT542 1

VT543 2

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.

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
C. Reason

Accomplishment of this service bulletin will replace the Trailing Edge (TE) Flap support bearings without

a roller retention feature at the TE Flap support rib assembly in Flap Positions 1, 2, 7, and 8 with new

bearings with a roller retention feature. The TE Flap support bearings are integral components of the

TE Flap support rib assemblies. The TE Flap rotary actuators and position transmitters are attached

to the TE support rib assemblies along the rear spar. Not replacing the TE Flap support bearings can,

in the event of an undetected bearing failure, lead to damage to the TE rotary actuators and other TE

Flap support rib parts, which could result in a dual Flap drive system disconnect in both TE Flap rotary

actuators, and a possible Flaps blowback with loss of controllability of the airplane.

There have been several cases of varying degrees of TE Flap support bearings damage at the TE Flap

support rib assemblies in Flap Positions 1, 2, 4, 5, 7, and 8. An operator reported "TE FLAP ASYM"

and "TE SHUT DOWN" messages at Flap 5 during a landing approach. Bearing damage was found

at the Outboard E Flap support rib assembly in Flap Positions 1, 2, 7, and 8, and at the Inboard TE

Flap support rib assembly in Positions 4 and 5. The inspection of a second airplane revealed similar

TE Flap support bearing damage, but no EICAS messages were experienced in that case. A third

airplane was inspected by another operator, and similar damage to the TE Flap support bearings was

found, but no EICAS messages were experienced in that case either. Another operator found a broken

position transmitter gearbox on a fourth airplane after receiving a Flap skew message. This airplane

also had TE Flap support bearing damage in the TE Flap support rib assembly at various TE Flap

Positions. Bearing damage in the TE Flaps support rib assembly is caused by the use of dead-blow

mallets during the installation of the shaft on the TE Flap support rib assembly when TE Flap support

bearings without a roller retention feature are installed. This method of installation may compromise

bearings without a roller retention feature. The TE Flap support bearings in TE Flap Positions 3 and 6

are not affected.

This service bulletin replaces Boeing service bulletin 767-27A0222, Original Issue. More work is

necessary for Group 1, Configuration 1 airplanes (airplanes that accomplished the terminating action

given in Boeing service bulletin 767-27A0222, Original Issue) to maintain part number configuration

control of the flap support rib assemblies. For these airplanes, the new part numbers for TE Flap support

rib assembly in Flap Positions 1 and 8 were incorrect in 767-27A0222, Original Issue. The TE Flap

support rib assembly part numbers should be changed to the correct part number on the affected

airplanes in this group/configuration. No more work is necessary for Group 2, Configuration 1 airplanes.

For this airplane, the new part numbers for TE Flap support rib assembly in Flap Positions 1 and 8

were correct in 767-27A0222, Original Issue.

This service bulletin does not provide instructions to inspect/replace the TE Flap support bearings and

the rotary actuators at Flap Positions 4 and 5. The TE Flap support bearings and TE rotary actuators

at these Flap Positions are covered by service bulletin 767-27-0223. The TE Flap support bearings

and TE rotary actuators at Flap Positions 3 and 6 are not affected by the condition addressed in this

service bulletin

Boeing Service Related Problem (SRP) 767-SRP-57-0235 and SRP 767-SRP-57-0255 are related to

this service bulletin.

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
D. Description

Group 1, 3, Configuration 1:

RE-IDENTIFY THE TRAILING EDGE (TE) FLAP SUPPORT RIB ASSEMBLY FOR APPLICABLE

FLAP POSITIONS WITH CORRECT NEW PART NUMBERS

1. Do PART 3 to reidentify the TE Flap support rib assembly at the applicable Flap Positions with

the correct new part numbers.

Group 2, Configuration 1:

1. No action required.

Group 1-3, Configuration 2:

INSPECT THE TE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB ASSEMBLY IN

FLAP POSITIONS 1, 2, 7, AND 8:

1. Do PART 1A to do a General Visual Inspection (GVI) of the TE Flap support bearings at the TE

Flap support rib assembly in Flap Positions 1, 2, 7, and 8 to identify the type of bearing installed.

a. PART 1A, STEP 7, CONDITION 1: Two bearings with a roller retention feature are installed

at the TE Flap support rib assembly in Flap Positions 1, 2, 7, and 8.

– No bearing replacement is required. Put the airplane back to a serviceable condition in

accordance with Accomplishment Instructions PART 1B.

a. PART 1A, STEP 7, CONDITION 2: At least one bearing without a roller retention feature is

installed at the TE Flap support rib assembly in Flap Position1, 2, 7, or 8.

– Replace the two bearings at each applicable TE Flap support rib in accordance with

Accomplishment Instructions PART 2.

– Do a General Visual Inspection (GVI) of each pair of bearings removed in accordance

with Accomplishment Instructions PART 2, Step 1.d.

Group 1-3, Configuration 2:

REPLACE THE TRAILING EDGE (TE) FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT

RIB ASSEMBLY IN FLAP POSITIONS 1, 2, 7, or 8:

1. Do PART 2 to replace the applicable TE Flap support bearings at the TE Flap support rib assembly

in Flap Positions 1, 2, 7, or 8 after bearing the inspection in PART 1A if one or more bearings, at

any of the applicable TE Flap Positions, do not have a roller retention feature.

2. Do a GVI of the removed TE Flap support bearings and record the damage / type bearing

combination. Use the data to find if the TE rotary actuators at Flap Positions 1, 2, 7, or 8 are

serviceable or if they need to be overhauled or replaced.

a. PART 2, STEP 1.f, 2.f, 3.f, or 4.f., CONDITION 1: Both TE Flap support bearings at TE Flap

support rib assembly in Flap Position 1 have at least one face each that meets the definitions

of good or slightly damaged bearing face.

– PART 2, Step 1.f, CONDITION 1, Step 1: The TE rotary actuator is acceptable and may

be used as-is in the applicable Flap Position(s).

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
b. PART 2, STEP 1.f, 2.f, 3.f, or 4.f., CONDITION 2: Only one TE Flap support bearing at the

TE Flap support rib assembly in Flap Position 1 has at least one face that meets the definition

of good or slightly damaged bearing face. The other bearing at the same TE Flap support rib

assembly has faces that meet the definitions of moderately damaged or fractured bearing

face.

– PART 2, Step 1.f, CONDITION 2, Step 1: Overhaul or replace the TE rotary actuator at

the TE Flap support rib assembly in the applicable Flap Position(s).

c. PART 2, STEP 1.f, 2.f, 3.f, or 4.f., CONDITION 3: Both bearings at the TE Flap support rib

assembly in Flap Position 1 have all faces that meet the definitions of moderately damaged

or fractured bearing face.

– PART 2, Step 1.f, CONDITION 3, Step 1: Replace the TE rotary actuator at the TE Flap

support rib assembly in the applicable Flap Position(s).

Group 1-3, Configuration 2:

FUNCTIONAL TEST AFTER BEARING REPLACEMENT:

1. Do the functional test after the TE Flap rib support bearings have been replaced at Flap Position

1, 2, 7 or 8.

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

Group 1:

Affected Maintenance Zones

Model Zone

767-200, 767-300, 767-300F, 566, 666

767-400ER

Group 2:

Affected Maintenance Zones

Model Zone

767-300F 566, 666

Group 3:

Affected Maintenance Zones

Model Zone

767-300, 767-300F, 767-400ER 566, 666

E. Compliance

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to

this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this

service bulletin mandatory.

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Group 1, 3, Configuration 1:

No compliance time given.

Group 2, Configuration 1:

No further action required.

Group 1-2, Configuration 2:

Table 1: Inspect and Replace the TE Flap Support Rib Bearings at the Flap Support Rib Assembly in

Flap Positions 1, 2, 7 and 8.

Repeat Interval (Not to Exceed)Compliance Time (Whichever

Occurs Later)

Condition Action

Within 500 flight -

cycles after the

original issue

date of this Service Bulletin

Before 6,000 total flight cyclesDo a General Visual Inspection (GVI) of both

bearings at the TE flap

support rib assembly in

Flap Positions 1, 2, 7, and

8 to determine if the bearings have a roller retention

feature in accordance with

Accomplishment Instructions PART 1A

All airplanes

No bearing replacement is - -

required. Put the airplane

back to a serviceable condition in accordance with

Accomplishment Instructions PART 1B

PART 1A, STEP 4, CONDITION 1 - Two bearings

with a roller retention feature are installed at the TE

Flap support rib assembly

in Flap Positions 1, 2, 7,

and 8

- Replace the two bearings Before further flight -

at each applicable TE Flap

support rib in accordance

with Accomplishment Instructions PART 2

PART 1A, STEP 4, CONDITION 2 - At least one

bearing without a roller retention feature is installed

at the TE Flap support rib

assembly in Flap Position

1, 2, 7, or 8

- Do a General Visual Inspection (GVI) of each pair

of bearings removed in accordance with Accomplishment Instructions PART 2,

Step 1.d.

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Group 1-2, Configuration 2:

Table 1: Inspect and Replace the TE Flap Support Rib Bearings at the Flap Support Rib Assembly in

Flap Positions 1, 2, 7 and 8.

Repeat Interval (Not to Exceed)Compliance Time (Whichever

Occurs Later)

Condition Action

The TE rotary actuator is - -

acceptable and may be

used as-is in the applicable

Flap Position(s) where

CONDITION 1 is found:

PART 2, STEP 1.e, CONDITION 1 - Both TE Flap

support bearings at TE

Flap support rib assembly

in Flap Position 1 have at

least one face each that

meets the definitions of

good or slightly damaged

bearing face

- Flap Position 1 - In accordance with Accomplishment Instructions PART 2,

Step 1.e, CONDITION 1,

Or Step 1

- Flap Position 2 - In accordance with Accomplishment Instructions PART 2,

Step 2.e, CONDITION 1,

Step 1

PART 2, STEP 2.e, CONDITION 1 - Both TE Flap

support bearings at TE

Flap support rib assembly

in Flap Position 2 have at

least one face each that

meets the definitions of

good or slightly damaged

bearing face

- Flap Position 7 - In accordance with Accomplishment Instructions PART 2,

Step 3.e, CONDITION 1,

Or Step 1

- Flap Position 8 - In accordance with Accomplishment Instructions PART 2,

Step 4.e, CONDITION 1,

Step 1

PART 2, STEP 3.e, CONDITION 1 - Both TE Flap

support bearings at TE

Flap support rib assembly

in Flap Position 7 have at

least one face each that

meets the definitions of

good or slightly damaged

bearing face

Or

PART 2, STEP 4.e, CONDITION 1 - Both TE Flap

support bearings at TE

Flap support rib assembly

in Flap Position 8 have at

least one face each that

meets the definitions of

good or slightly damaged

bearing face

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Group 1-2, Configuration 2:

Table 1: Inspect and Replace the TE Flap Support Rib Bearings at the Flap Support Rib Assembly in

Flap Positions 1, 2, 7 and 8.

Repeat Interval (Not to Exceed)Compliance Time (Whichever

Occurs Later)

Condition Action

Overhaul or replace the TE Before further flight -

rotary actuator at the TE

Flap support rib assembly

in the applicable Flap Position(s) where CONDITION

2 is found:

PART 2, STEP 1.e, CONDITION 2 - Only one TE

Flap support bearing at the

TE Flap support rib assembly in Flap Position 1 has

at least one face that

meets the definition of

good or slightly damaged

bearing face. The other

bearing at the same TE

Flap support rib assembly

has faces that meet the

definitions of moderately

damaged or fractured

bearing face

- Flap Position 1 - In accordance with Accomplishment Instructions PART 2,

Step 1.e, CONDITION 2,

Step 1, OPTION 1 or OPTION 2

- Flap Position 2 - In accordance with Accomplishment Instructions PART 2,

Step 2.e, CONDITION 2,

Step 1, OPTION 1 or OPTION 2

Or

PART 2, STEP 2.e, CONDITION 2 - Only one TE

Flap support bearing at the

TE Flap support rib assembly in Flap Position 2 has

at least one face that

meets the definition of

good or slightly damaged

bearing face. The other

bearing at the same TE

Flap support rib assembly

has faces that meet the

definitions of moderately

damaged or fractured

bearing face

- Flap Position 7 - In accordance with Accomplishment Instructions PART 2,

Step 3.e, CONDITION 2,

Step 1, OPTION 1 or OPTION 2

- Flap Position 8 - In accordance with Accomplishment Instructions PART 2,

Step 4.e, CONDITION 2,

Step 1, OPTION 1 or OPTION 2

Or

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Group 1-2, Configuration 2:

Table 1: Inspect and Replace the TE Flap Support Rib Bearings at the Flap Support Rib Assembly in

Flap Positions 1, 2, 7 and 8.

Repeat Interval (Not to Exceed)Compliance Time (Whichever

Occurs Later)

Condition Action

PART 2, STEP 3.e, CONDITION 2 - Only one TE

Flap support bearing at the

TE Flap support rib assembly in Flap Position 7 has

at least one face that

meets the definition of

good or slightly damaged

bearing face. The other

bearing at the same TE

Flap support rib assembly

has faces that meet the

definitions of moderately

damaged or fractured

bearing face

Or

PART 2, STEP 4.e, CONDITION 2 - Only one TE

Flap support bearing at the

TE Flap support rib assembly in Flap Position 8 has

at least one face that

meets the definition of

good or slightly damaged

bearing face. The other

bearing at the same TE

Flap support rib assembly

has faces that meet the

definitions of moderately

damaged or fractured

bearing face

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Group 1-2, Configuration 2:

Table 1: Inspect and Replace the TE Flap Support Rib Bearings at the Flap Support Rib Assembly in

Flap Positions 1, 2, 7 and 8.

Repeat Interval (Not to Exceed)Compliance Time (Whichever

Occurs Later)

Condition Action

Replace the TE rotary actu- Before further flight -

ator at the TE Flap support

rib assembly in the applicable Flap Position(s) where

CONDITION 3 is found:

PART 2, STEP 1.e, CONDITION 3 - Both bearings

at the TE Flap support rib

assembly in Flap Position

1 have all faces that meet

the definitions of moderately damaged or fractured

bearing face

- Flap Position 1 - In accordance with Accomplishment Instructions PART 2,

Step 1.e, CONDITION 3,

Step 1

Or

PART 2, STEP 2.e, CONDITION 3 - Both bearings

at the TE Flap support rib

assembly in Flap Position

2 have all faces that meet

the definitions of moderately damaged or fractured

bearing face

- Flap Position 2 - In accordance with Accomplishment Instructions PART 2,

Step 2.e, CONDITION 3,

Step 1

- Flap Position 7 - In accordance with Accomplishment Instructions PART 2,

Step 3.e, CONDITION 3,

Step 1

Or

PART 2, STEP 3.e, CONDITION 3 - Both bearings

at the TE Flap support rib

assembly in Flap Position

7 have all faces that meet

the definitions of moderately damaged or fractured

bearing face

- Flap Position 8 - In accordance with Accomplishment Instructions PART 2,

Step 4.e, CONDITION 3,

Step 1

Or

PART 2, STEP 4.e, CONDITION 3 - Both bearings

at the TE Flap support rib

assembly in Flap Position

8 have all faces that meet

the definitions of moderately damaged or fractured

bearing face

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Group 3, Configuration 2:

Table 2: Inspect and Replace the TE Flap Support Rib Bearings at the Flap Support Rib Assembly

in Flap Positions 1, 2, 7 and 8.

Repeat Interval

(not to Exceed)

Compliance

Time

Condition Action

Within 5,500 -

flight cycles after

the original issue

date of this service bulletin

Do a General Visual Inspection (GVI) of both

bearings at the TE flap

support rib assembly in

Flap Positions 1, 2, 7, and

8 to determine if the bearings have a roller retention

feature in accordance with

Accomplishment Instructions PART 1A.

All airplanes

No bearing replacement is - -

required. Put the airplane

back to a serviceable condition in accordance with

Accomplishment Instructions PART 1B

PART 1A, STEP 4, CONDITION 1 - Two bearings

with a roller retention feature are installed at the TE

Flap support rib assembly

in Flap Positions 1, 2, 7,

and 8

Before further -

flight

- Replace the two bearings

at each applicable TE Flap

support rib in accordance

with Accomplishment Instructions PART 2

PART 1A, STEP 4, CONDITION 2 - At least one

bearing without a roller retention feature is installed

at the TE Flap support rib

assembly in Flap Position

1, 2, 7, or 8

- Do a General Visual Inspection (GVI) of each pair

of bearings removed in accordance with Accomplishment Instructions PART 2,

Step 1.d.

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Group 3, Configuration 2:

Table 2: Inspect and Replace the TE Flap Support Rib Bearings at the Flap Support Rib Assembly

in Flap Positions 1, 2, 7 and 8.

Repeat Interval

(not to Exceed)

Compliance

Time

Condition Action

The TE rotary actuator is - -

acceptable and may be

used as-is in the applicable

Flap Position(s) where

CONDITION 1 is found:

PART 2, STEP 1.e, CONDITION 1 - Both TE Flap

support bearings at TE

Flap support rib assembly

in Flap Position 1 have at

least one face each that

meets the definitions of

good or slightly damaged

bearing face

- Flap Position 1 - In accordance with Accomplishment Instructions PART 2,

Step 1.e, CONDITION 1,

Or Step 1

- Flap Position 2 - In accordance with Accomplishment Instructions PART 2,

Step 2.e, CONDITION 1,

Step 1

PART 2, STEP 2.e, CONDITION 1 - Both TE Flap

support bearings at TE

Flap support rib assembly

in Flap Position 2 have at

least one face each that

meets the definitions of

good or slightly damaged

bearing face

- Flap Position 7 - In accordance with Accomplishment Instructions PART 2,

Step 3.e, CONDITION 1,

Or Step 1

- Flap Position 8 - In accordance with Accomplishment Instructions PART 2,

Step 4.e, CONDITION 1,

Step 1

PART 2, STEP 3.e, CONDITION 1 - Both TE Flap

support bearings at TE

Flap support rib assembly

in Flap Position 7 have at

least one face each that

meets the definitions of

good or slightly damaged

bearing face

Or

PART 2, STEP 4.e, CONDITION 1 - Both TE Flap

support bearings at TE

Flap support rib assembly

in Flap Position 8 have at

least one face each that

meets the definitions of

good or slightly damaged

bearing face

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Group 3, Configuration 2:

Table 2: Inspect and Replace the TE Flap Support Rib Bearings at the Flap Support Rib Assembly

in Flap Positions 1, 2, 7 and 8.

Repeat Interval

(not to Exceed)

Compliance

Time

Condition Action

Before further -

flight

Overhaul or replace the TE

rotary actuator at the TE

Flap support rib assembly

in the applicable Flap Position(s) where CONDITION

2 is found:

PART 2, STEP 1.e, CONDITION 2 - Only one TE

Flap support bearing at the

TE Flap support rib assembly in Flap Position 1 has

at least one face that

meets the definition of

good or slightly damaged

bearing face. The other

bearing at the same TE

Flap support rib assembly

has faces that meet the

definitions of moderately

damaged or fractured

bearing face

- Flap Position 1 - In accordance with Accomplishment Instructions PART 2,

Step 1.e, CONDITION 2,

Step 1, OPTION 1 or OPTION 2

- Flap Position 2 - In accordance with Accomplishment Instructions PART 2,

Step 2.e, CONDITION 2,

Step 1, OPTION 1 or OPTION 2

Or

PART 2, STEP 2.e, CONDITION 2 - Only one TE

Flap support bearing at the

TE Flap support rib assembly in Flap Position 2 has

at least one face that

meets the definition of

good or slightly damaged

bearing face. The other

bearing at the same TE

Flap support rib assembly

has faces that meet the

definitions of moderately

damaged or fractured

bearing face

- Flap Position 7 - In accordance with Accomplishment Instructions PART 2,

Step 3.e, CONDITION 2,

Step 1, OPTION 1 or OPTION 2

- Flap Position 8 - In accordance with Accomplishment Instructions PART 2,

Step 4.e, CONDITION 2,

Step 1, OPTION 1 or OPTION 2

Or

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Group 3, Configuration 2:

Table 2: Inspect and Replace the TE Flap Support Rib Bearings at the Flap Support Rib Assembly

in Flap Positions 1, 2, 7 and 8.

Repeat Interval

(not to Exceed)

Compliance

Time

Condition Action

PART 2, STEP 3.e, CONDITION 2 - Only one TE

Flap support bearing at the

TE Flap support rib assembly in Flap Position 7 has

at least one face that

meets the definition of

good or slightly damaged

bearing face. The other

bearing at the same TE

Flap support rib assembly

has faces that meet the

definitions of moderately

damaged or fractured

bearing face

Or

PART 2, STEP 4.e, CONDITION 2 - Only one TE

Flap support bearing at the

TE Flap support rib assembly in Flap Position 8 has

at least one face that

meets the definition of

good or slightly damaged

bearing face. The other

bearing at the same TE

Flap support rib assembly

has faces that meet the

definitions of moderately

damaged or fractured

bearing face

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Group 3, Configuration 2:

Table 2: Inspect and Replace the TE Flap Support Rib Bearings at the Flap Support Rib Assembly

in Flap Positions 1, 2, 7 and 8.

Repeat Interval

(not to Exceed)

Compliance

Time

Condition Action

Before further -

flight

Replace the TE rotary actuator at the TE Flap support

rib assembly in the applicable Flap Position(s) where

CONDITION 3 is found:

PART 2, STEP 1.e, CONDITION 3 - Both bearings

at the TE Flap support rib

assembly in Flap Position

1 have all faces that meet

the definitions of moderately damaged or fractured

bearing face

- Flap Position 1 - In accordance with Accomplishment Instructions PART 2,

Step 1.e, CONDITION 3,

Step 1

Or

PART 2, STEP 2.e, CONDITION 3 - Both bearings

at the TE Flap support rib

assembly in Flap Position

2 have all faces that meet

the definitions of moderately damaged or fractured

bearing face

- Flap Position 2 - In accordance with Accomplishment Instructions PART 2,

Step 2.e, CONDITION 3,

Step 1

- Flap Position 7 - In accordance with Accomplishment Instructions PART 2,

Step 3.e, CONDITION 3,

Step 1

Or

PART 2, STEP 3.e, CONDITION 3 - Both bearings

at the TE Flap support rib

assembly in Flap Position

7 have all faces that meet

the definitions of moderately damaged or fractured

bearing face

- Flap Position 8 - In accordance with Accomplishment Instructions PART 2,

Step 4.e, CONDITION 3,

Step 1

Or

PART 2, STEP 4.e, CONDITION 3 - Both bearings

at the TE Flap support rib

assembly in Flap Position

8 have all faces that meet

the definitions of moderately damaged or fractured

bearing face

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.

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
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

Group 1-3, Configuration 2:

Table 2: Inspection/Replacement of the TE Flap Support Rib Bearings at the TE Flap Support Rib

Assembly in Flap Position 2

Task Number of Persons Task-Hours Elapsed Hours Notes

PREPARE 1 1.75 1.75

FIGURE 1 2 2.50 1.25

FIGURE 2 2 2.50 1.25

FIGURE 3 2 2.50 1.25 (a)

FIGURE 4 2 2.50 1.25 (a)

FIGURE 6 2 2.50 1.25

FUNCTIONAL TEST 2 1.00 0.50 (b)

Total per rib position 12.75 8.50

(a) FIGURE 3 and FIGURE 4 are required only if the bearing inspection in FIGURE 1 and FIGURE

2 finds bearings with a roller retention feature.

(b) FUNCTIONAL TEST is required only if bearings are replaced in any of the applicable Flap Positions (1, 2, 7 or 8).

Group 1-3, Configuration 2:

Table 1: Inspection/Replacement of the TE Flap Support Rib Bearings at the TE Flap Support Rib

Assembly in Flap Position 1

Task Number of Persons Task-Hours Elapsed Hours Notes

PREPARE 1 1.75 1.75

FIGURE 1 2 2.50 1.25

FIGURE 2 2 2.50 1.25

FIGURE 3 2 2.50 1.25 (a)

FIGURE 4 2 2.50 1.25 (a)

FIGURE 5 2 2.50 1.25

FUNCTIONAL TEST 2 1.00 0.50 (b)

Total per rib position 12.75 8.50

(a) FIGURE 3 and FIGURE 4 are required only if the bearing inspection in FIGURE 1 and FIGURE

2 finds bearings with a roller retention feature.

(b) FUNCTIONAL TEST is required only if bearings are replaced in any of the applicable Flap Positions (1, 2, 7 or 8).

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Group 1-3, Configuration 2:

Table 3: Inspection/Replacement of the TE Flap Support Rib Bearings at the TE Flap Support Rib

Assembly in Flap Position 7

Task Number of Persons Task-Hours Elapsed Hours Notes

PREPARE 1 1.75 1.75

FIGURE 1 2 2.50 1.25

FIGURE 2 2 2.50 1.25

FIGURE 3 2 2.50 1.25 (a)

FIGURE 4 2 2.50 1.25 (a)

FIGURE 7 2 2.50 1.25

FUNCTIONAL TEST 2 1.00 0.50 (b)

Total per rib position 12.75 8.50

(a) FIGURE 3 and FIGURE 4 are required only if the bearing inspection in FIGURE 1 and FIGURE

2 finds bearings with a roller retention feature.

(b) FUNCTIONAL TEST is required only if bearings are replaced in any of the applicable Flap Positions (1, 2, 7 or 8).

Group 1-3, Configuration 2:

Table 4: Inspection/Replacement of the TE Flap Support Rib Bearings at the TE Flap Support Rib

Assembly in Flap Position 8

Task Number of Persons Task-Hours Elapsed Hours Notes

PREPARE 1 1.75 1.75

FIGURE 1 2 2.50 1.25

FIGURE 2 2 2.50 1.25

FIGURE 3 2 2.50 1.25 (a)

FIGURE 4 2 2.50 1.25 (a)

FIGURE 8 2 2.50 1.25

FUNCTIONAL TEST 2 1.00 0.50 (b)

Total per rib position 12.75 8.50

(a) FIGURE 3 and FIGURE 4 are required only if the bearing inspection in FIGURE 1 and FIGURE

2 finds bearings with a roller retention feature.

(b) FUNCTIONAL TEST is required only if bearings are replaced in any of the applicable Flap Positions (1, 2, 7 or 8).

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Group 1, 3, Configuration 1:

Table 5: Reidentify the TE Flap Support Rib Sssembly at Flap Position 1 and Position

8 with the Correct New Part Numbers

Number of Per- Task-Hours Elapsed Hours

sons

Task

Prepare 1 1.75 1.75

FIGURE 9 2 0.50 0.25

Total per rib position 2.25 2.00

Group 2, Configuration 1:

No further action required.

H. Weight and Balance Changes

None.

I. Electrical Load Data

None.

J. References

1. Existing Data:

a. Boeing Service Bulletin 767-27A0222, 767-27-0223

b. Boeing Service Related Problem (SRP) 767-SRP-57-0235, 767-SRP-57-0255

c. Component Maintenance Manual (CMM) 27-51-10, 27-51-49

d. Service Bulletin Index D624T001

e. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-50-10

f. 767 Aircraft Maintenance Manual (AMM) 06-44-00, 20-10-23, 24-22-00, 27-51-00, 27-51-21,

27-51-22, 27-51-45, 27-61-00, 29-11-00, 32-00-15, 32-00-20

2. Data Supplied with this Service Bulletin:

None.

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

Drawing Number Title

113T1328 RIB - SUPPORT NO. 1 T.E FLAP

113T1329 RIB - SUPPORT NO. 2 T.E FLAP

113T1345 RIB INSTL - OUTBOARD T.E. FLAP SUPPORT

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ALERT ALERT
These drawings were used to prepare this service bulletin. These drawings are not necessary to

make the specified changes, and are not supplied with this service bulletin. These drawings may

not be applicable to all airplane configurations or operators.

K. Publications Affected

1. Publications:

Publication Chapter-Section

767 Aircraft Maintenance Manual 27-51

767 Illustrated Parts Catalog 27-51

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated the repairs 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

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

information.

M. Software Accomplishment Summary

Not affected.

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ALERT ALERT
2. MATERIAL INFORMATION

A. Material - Price and Availability

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

below. If there is a limit to the quantity of available kits, a supply sequence is given by Spares. More

kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date

Boeing gets the purchase order.

Unit Price thru

August 31, 2013

Kit Number Name ROLT (Weeks)

Top Kit - 767 TE Flap Bearing 43 $1,484.00

Replacement

015T1847-2

(a) One (1) kit required per applicable Flap Position: up to four (4) kits required per airplane (one

for each TE Flap support rib assembly in Flap Positions 1, 2, 7, and 8).

The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.

After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars.

Terms: Net 30 days.

Reference this service bulletin and submit your purchase order by one of the methods that follow:

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

2. Fax to (206) 662-7145

3. Mail to:

Spares Customer Support - MC 36-65

Boeing Spares Department

P.O. Box 3707

Seattle, Washington 98124-2207 USA

B. Industry Support Information

Boeing warranty remedies are available for 767 airplanes in warranty as of July 15, 2009. For task hour

reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Commercial

Airplanes Group - Warranties. The kits and parts for airplanes in warranty as of that date will be supplied

at no charge. Send a purchase order for the kits and parts to Boeing Spares. Please refer to this service

bulletin number and reference the airplane variable numbers in your purchase order.

C. Parts Necessary for Each Airplane

1. Kits/Parts

To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.

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ALERT ALERT
Kit 015T1847-2

Existing Part Notes

Number

New Part Number QTY Name

-

(a) (b)

(c) (d)

60B00178-23

(DAT72-90A1-

501)

SB-1131 2 BEARING

113T1256-31 4 SEAL 113T1256-31 (c) (d)

(a) SB-1131 bearings (McGill) have a roller retention feature, and qualify

to two Boeing specifications, 60B00178-23 and S113T134-1. Boeing

specification 60B00178-23 does not require a roller retention feature

for the bearings, while Boeing specification S113T134-1 does. McGill

bearings packing and documentation usually include the part information

for the vendor part number (SB-1131, in this case) and a Boeing

specification number (60B00178-23 or S113T134-1). For this service

bulletin, the intent is to install new bearings that comply with Boeing

specification number S113T134-1, regardless if the bearing qualifies

for other Boeing specifications as well. Any substitute bearing for the

McGill SB-1131 must have a roller retention feature and meet Boeing

specifications given in S113T134-1 (such as DAT72-90A1-506, for example),

(b) The second bearing qualified to the 60B00178-23 Boeing specification

is the bearing DAT72-90A1-501 (Rexnord). This bearing does not have

a roller retention feature. Rexnord bearings DAT72-90A1-501 must be

removed from spares inventories and service.

(c) Discard the existing part. For the existing bearings, discard as long as

there is no roller retention feature.

(d) You cannot use the existing part to replace the new or changed part.

NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by

the Operator, are necessary for each Trailing Edge Flap position. A total of four kits are

necessary per airplane.

2. Parts and Materials Supplied by the Operator

Part Number / QTY Name Notes

Specification

MS20995NC40 - Safety Lockwire or equivalent.

BMS3-38 - Corrosion Inhibiting Compound -

BMS3-33 - Grease -

BMS11-9 - Solvent or equivalent.

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ALERT ALERT
Part Number / QTY Name Notes

Specification

Quantity of TE rotary actuators depends on the number

of rotary actuators that need

to be replaced. Up to 4 TE

rotary actuators may be

needed per airplane.

256T3250-4 0-4 Trailing Edge (TE) Rotary Actuator

(a)

Quantity of TE rotary actuators depends on the number

of rotary actuators that need

to be replaced. Up to 4 TE

rotary actuators may be

needed per airplane.

256T6110-3 0-4 TE Rotary Actuator

(b)

(a) 767-200/-300/-300F Airplanes. Applicable CMM 27-51-10.

(b) 767-400ER Airplanes. Applicable CMM 27-51-49.

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.

Group 1:

Existing Part QTY Name New Part Number Notes

Number

113T1328-1 1 RIB SUPPORT 1 015T1847-7 (a)

113T1328-5 1 RIB SUPPORT 1 015T1847-3 (a)

113T1328-7 1 RIB SUPPORT 1 015T1847-5 (a)

113T1329-1 1 RIB SUPPORT 2 113T1329-93 (a)

113T1329-3 1 RIB SUPPORT 2 113T1329-95 (a)

113T1329-5 1 RIB SUPPORT 2 113T1329-97 (a)

113T1329-2 1 RIB SUPPORT 7 113T1329-94 (a)

113T1329-4 1 RIB SUPPORT 7 113T1329-96 (a)

113T1329-6 1 RIB SUPPORT 7 113T1329-98 (a)

113T1328-4 1 RIB SUPPORT 8 015T1847-8 (a)

113T1328-6 1 RIB SUPPORT 8 015T1847-4 (a)

113T1328-8 1 RIB SUPPORT 8 015T1847-6 (a)

(a) This is the new rib support part number after the bearing replacement is done in accordance

with this service bulletin.

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ALERT ALERT
Group 2:

Existing Part QTY Name New Part Number Notes

Number

113T1328-99 1 RIB SUPPORT 1 113T1328-105 (a)

113T1329-5 1 RIB SUPPORT 2 113T1329-97 (a)

113T1329-6 1 RIB SUPPORT 7 113T1329-98 (a)

113T1328-100 1 RIB SUPPORT 8 113T1328-106 (a)

(a) This is the new rib support part number after the bearing replacement is done in accordance

with this service bulletin.

Group 3:

Existing Part QTY Name New Part Number Notes

Number

113T1328-1 1 RIB SUPPORT 1 015T1847-7 (a)

113T1345-133 1 RIB SUPPORT 1 015T1847-9 (a)

113T1329-1 1 RIB SUPPORT 2 113T1329-93 (a)

113T1345-131 1 RIB SUPPORT 2 015T1847-10 (a)

113T1345-135 1 RIB SUPPORT 2 015T1847-13 (a)

113T1345-187 1 RIB SUPPORT 2 015T1847-15 (a)

113T1345-259 1 RIB SUPPORT 2 015T1847-17 (a)

113T1329-2 1 RIB SUPPORT 7 113T1329-94 (a)

113T1345-132 1 RIB SUPPORT 7 015T1847-11 (a)

113T1345-136 1 RIB SUPPORT 7 015T1847-14 (a)

113T1345-188 1 RIB SUPPORT 7 015T1847-16 (a)

113T1345-260 1 RIB SUPPORT 7 015T1847-18 (a)

113T1328-2 1 RIB SUPPORT 8 015T1847-19 (a)

113T1328-4 1 RIB SUPPORT 8 015T1847-8 (a)

113T1345-134 1 RIB SUPPORT 8 015T1847-12 (a)

(a) This is the new rib support part number after the bearing replacement is done in accordance

with this service bulletin.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None.

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ALERT ALERT
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.

Refer to Boeing drawing number 0A-27128 'REMOVAL/INSTALLATION EQPT - OUTBOARD FLAP

ACTUATOR, CRANK ARM MECHANISM'.

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT

BLANK PAGE
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

– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch

– Angular tolerance is plus or minus 2 degrees

– Hole dimensions for standard solid rivets 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. If the length of any fastener specified in this service bulletin does not meet installation

standards given in SRM Chapter 51, then a fastener of the same specification, or

an approved substitute, with a length which meets the installation standards given

in SRM Chapter 51 may be used. In addition, washers may be installed for fastener

grip length in accordance with SRM Chapter 51.

6. 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 enhance visual access to all exposed surfaces

in the inspection area. This level of inspection is made under normally 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.

7. 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.

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ALERT ALERT
8. Boeing Service Letter 767-SL-51-036, 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.

9. Refer to APPENDIX A for guidance to find if the TE rotary actuator(s) at Flap Positions

1, 2, 7, or 8 are serviceable or if they need to be overhauled or replaced.

10. The instructions in Paragraph 3.B., Work Instructions and the figures can include

operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated

Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing

Index contain data on versions of the tools or test equipment that you can use. It is

permitted to use replaced tools. It is not permitted to use superseded tools.

11. 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.

12. Where the work instructions include installation of a kept part, a new or serviceable

part with the same part number can be installed as an alternative to the kept part.

13. This service bulletin includes functional test procedures for the systems changed by

this service bulletin. More functional tests can possibly be necessary in accordance

with standard maintenance practices because of interruption to other airplane systems.

14. Boeing tool kit drawing 0A-27128 provides dimensions and information for fabricating

the recommended tools to accomplish the service bulletin work instructions.

B. WORK INSTRUCTIONS

Group 2, Configuration 1:

No further action required.

Group 1-3, Configuration 2:

PREPARE ACCESS TO DO PART 1A OF THIS SERVICE BULLETIN ACCOMPLISHMENT

INSTRUCTIONS:

1. Make sure downlocks are installed on the nose and main landing gear. Refer to 767 AMM 32-00-20

as an accepted procedure.

WARNING: THE DOORS OPEN AND CLOSE QUICKLY AND CAN CAUSE INJURY TO PERSONS

OR DAMAGE TO EQUIPMENT.

2. Open the doors for the landing gear and install the door locks. Refer to 767 AMM 32-00-15 as an

accepted procedure.

3. Supply electrical power. Refer to 767 AMM 24-22-00 as an accepted procedure.

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ALERT ALERT
WARNING: KEEP PERSONS AND EQUIPMENT AWAY FROM ALL CONTROL SURFACES AND

THE WHEEL WELLS WHEN HYDRAULIC POWER IS SUPPLIED. AILERONS,

ELEVATORS, RUDDER, SLATS, SPOILERS, AND STABILIZERS ARE FULLY

POWERED SURFACES. WHEN YOU MOVE THE FLAP CONTROL LEVER WITH THE

HYDRAULIC SYSTEM PRESSURISED, THE FLAPS AND FLAP DRIVE MECHANISMS

WILL MOVE QUICKLY. INJURY TO PERSONS OR DAMAGE TO EQUIPMENT CAN

OCCUR WHEN HYDRAULIC POWER IS SUPPLIED.

WARNING: MAKE SURE THE ACESS DOOR FOR THE ENGINER STRUT, THE INBOARD FAN

COWLING, AND THE THRUST REVERSER COWLING ARE CLEAR FROM THE

MOVEMENT OF THE SLATS. IF THE MOVEMENT OF THE SLATS IS BLOCKED, IT

CAN CAUSE DAMAGE TO THE AIRPLANE

4. Pressurize the center hydraulic system and reservoir. Refer to 767 AMM 29-11-00 as an accepted

procedure.

5. Move the Flap control lever to the 5-unit detent and permit the Flaps and slats to move to position.

NOTE: Flaps should remain at the 5-unit detent for the inspection or replacement of the TE Flap

support rib bearings. The Airplane Maintenance Manual (AMM) procedures for removal

and installation of components may be accomplished with the Flaps at the 5-unit detent,

instead of Flaps at the 30-unit detent. The Flaps at the 5-unit detent allow access for

disconnecting the Outboard Flap Actuator Crank Arm Mechanism from the 5 - 8 link,

accomplished by removing the pins at Joint 5 of the Flap linkage mechanism.

6. Deactivate the Trailing Edge Flap. Refer to 767 AMM 27-51-00 as an accepted procedure.

Group 1-3, Configuration 2:

PART 1A: INSPECT THE TE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITIONS 1, 2, 7, AND 8

1. Get access to the Trailing Edge (TE) Flap support rib assembly for Flap Positions 1, 2, 7 and 8 by

removing access panels 561JB, 561HB, 561GB on the lower surface of the wing trailing edge.

Refer to 767 AMM 06-44-00.

2. Remove the applicable TE rotary actuators. Refer to 767 AMM 27-51-22 as an accepted procedure.

NOTE: Keep the actuator attach bolts in the retainers.

3. Remove the applicable TE position transmitters. Refer to 767 AMM 27-51-45 as an accepted

procedure.

4. Do a General Visual Inspection (GVI) of each exposed face of the TE Flap support rib bearings

at the TE Flap support rib assembly in Flap Positions 1, 2, 7 and 8 to determine if the bearings

have a roller retention feature:

CONDITION 1: TWO BEARINGS WITH A ROLLER RETENTION FEATURE ARE INSTALLED

AT TE FLAP SUPPORT RIB ASSEMBLY IN TE FLAP POSITION 1, 2, 7, or 8

a. Confirm that both TE Flap support bearings at the applicable TE Flap support rib assembly

have a retention feature with an inner race roller retainer. Refer to FIGURE 1 and FIGURE 2

as an accepted procedure.

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ALERT ALERT
NOTE: If visible, bearings with a roller retention feature can also be identified by the vendor

(McGill) part number, SB-1131. Also, McGill bearings have a single roller

configuration, with 40 rollers in total.

b. Restore the applicable TE Flap support rib assembly in Flap Position(s) 1, 2, 7 or 8. Refer to

FIGURE 3 as an accepted procedure to restore the outboard side of each support rib assembly.

Refer to FIGURE 4 as an accepted procedure to restore the inboard side of each support rib

assembly.

NOTE: If both bearings installed at a TE Flap support rib assembly in Flap Position(s) 1, 2,

7 or 8 have a roller retention feature, the bearings at the applicable Position do not

need to be replaced.

c. Put the airplane back to a serviceable condition. Refer to Part 1B of this service bulletin

accomplishment instructions as an accepted procedure.

CONDITION 2: AT LEAST ONE BEARING WITHOUT A ROLLER RETENTION FEATURE IS

INSTALLED AT TE FLAP SUPPORT RIB ASSEMBLY IN TE FLAP POSITION 1, 2, 7, or 8

a. Confirm that at least one of the two TE Flap support bearings installed at the applicable TE

Flap support rib assembly does not have a roller retention feature. Refer to FIGURE 1 and

FIGURE 2 as an accepted procedure.

NOTE: Bearings that do not have a retention feature have a double roller configuration with

57 rollers per bearing face for a total of 114 rollers, and a roller spacer between roller

sides. The vendor (Rexnord) part number for these bearings is DAT72-90A1-501.

b. If at least one of the two bearings installed at the TE Flap support rib assembly in Flap

Position(s) 1, 2, 7 or 8 does not have a roller retention feature, replace both bearings at the

at the applicable TE Flap support rib assembly in accordance with PART 2 of this service

bulletin accomplishments instructions.

Group 1-3, Configuration 2:

PART 1B: PUT THE AIRPLANE BACK TO A SERVICEABLE CONDITION

1. Install the applicable TE position transmitters. Refer to 767 AMM 27-51-45 as an accepted

procedure.

2. Install the applicable TE rotary actuators. Refer to 767 AMM 27-51-22 as an accepted procedure.

3. Install the applicable access panels at the lower surface of the wing trailing edge. Refer to 767

AMM 06-44-00 as an accepted procedure.

4. Activate the Trailing Edge Flap. Refer to 767 AMM 27-51-00 as an accepted procedure.

5. Remove electrical power, if it is not necessary. Refer to 767 AMM 24-22-00 as an accepted

procedure.

6. Put the airplane back to a serviceable condition.

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ALERT ALERT
Group 1-3, Configuration 2:

PART 2: REPLACE THE TE FLAP SUPPORT BEARINGS AR THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITIONS 1, 2, 7, AND 8

1. If the inspection in PART 1A of the TE Flap support bearings at the TE Flap support rib assembly

in Flap Position 1 found at least one bearing without a roller retention feature, replace the TE Flap

support rib bearings at actuator support rib in Position 1:

a. Remove the applicable Outboard Flap Actuator Crank Arm Mechanism. Refer to 767 AMM

27-51-21 as an accepted procedure.

b. Get access to the bearings at the TE Flap support rib assembly in Flap Position 1. Refer to

FIGURE 5 as an accepted procedure.

c. Replace both bearings at the TE Flap support rib assembly. Refer to FIGURE 5 as an accepted

procedure.

d. Do a General Visual Inspection (GVI) of the removed TE Flap support bearings and look for

bearing damage.

NOTE: Bearing damage can be detected by finding one or more of the following conditions:

— Migrated or missing rollers in the bearing face. A migrated roller is a loose roller

that has partially moved or shifted horizontally out of the bearing race but is still

part of the bearing assembly. A missing roller can be detected by an empty roller

slot in the roller race or by counting the rollers in the exposed bearing face; there

should be a total of 57 rollers in each Rexnord bearing face.

— Damage on the bearing race, metal wear debris in the bearing and in the bearing

grease, and bearing abrasion on the bearing face. Detecting damage on the

bearing cage or the bearing race includes finding a bent, broken, cracked,

indented, spalled, fractured, brinelled, nicked, burred, eroded, or deformed

bearing race. Also, rollers grinding each other or the bearing race or spacer can

create metal wear filings, debris, flakes, or splinters inside and around the

bearing, leading to bearing abrasion or other damage conditions.

(1) Record the condition of the removed TE Flap support bearings. Refer to APPENDIX A

for the accepted bearing damage definitions and a suggested worksheet to record the

condition of the removed bearings.

NOTE: Damage of the TE support rib bearings can result in the introduction of side

loading into the associated TE rotary actuator, compromising it. Overhaul or

replacement of the applicable TE rotary actuator may be required depending

on the condition of the removed bearings.

e. Find if the TE rotary actuators at Flap Position 1 is serviceable or if it needs to be overhauled

or replaced. Refer to APPENDIX A for the accepted bearing damage definitions.

CONDITION 1: Both bearings at the TE Flap support rib assembly have at least one

face each that meets the definitions of good or slightly damaged bearing face

(1) If there is at least one good or slightly damaged bearing face in each bearing at the TE

Flap support rib assembly in Flap Position 1, the TE rotary actuator is acceptable and

may be used as-is.

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ALERT ALERT
(2) Install the Outboard Flap Actuator Crank Arm Mechanism. Refer to 767 AMM 27-51-21

as an accepted procedure.

NOTE: As part of the installation of the Outboard Flap Actuator Crank Arm Mechanism,

the instructions include steps to restore the TE Flap support rib assembly and

reinstall the TE position transmitter and the torque tube.

CONDITION 2: Only one bearing at the TE Flap support rib assembly has at least one

face that meets the definition of good or slightly damaged bearing face. The other

bearing at the same TE Flap support rib assembly has faces that meet the definitions

of moderately damaged or fractured bearing face

(1) If there is at least one good or slightly damaged bearing face in only one bearing at the

TE Flap support rib in Flap Position 1, do one of the two options:

OPTION 1: Overhaul the TE Rotary Actuator

(a) Overhaul the removed TE rotary actuator in accordance with CMM 27-51-10 or CMM

27-51-49.

NOTE: The removed TE rotary actuator cannot be returned to service unless a

complete disassembly of the unit, a Non-Destructive Inspection (NDI) of all

components, check all rotary actuator parts, repair, if necessary, clean,

reassemble the unit, and test, are completed in accordance with CMM

27-51-10 or CMM 27-51-49.

(b) Install the Outboard Flap Actuator Crank Arm Mechanism. Refer to 767 AMM 27-51-21

as an accepted procedure.

NOTE: As part of the installation instructions for the Outboard Flap Actuator Crank

Arm Mechanism, reinstall the overhauled TE rotary actuator.

Also as part of the installation of the Outboard Flap Actuator Crank Arm

Mechanism, the instructions include steps restore the TE Flap support rib

assembly and reinstall the TE position transmitter and the torque tube.

OPTION 2: Replace the TE Rotary Actuator

(a) Get a serviceable replacement for the removed TE rotary actuator.

NOTE: The removed TE rotary actuator cannot be returned to service unless a

complete disassembly of the unit, a Non-Destructive Inspection (NDI) of all

components, check all rotary actuator parts, repair, if necessary, clean,

reassemble the unit, and test, are completed in accordance with CMM

27-51-10 or CMM 27-51-49

A serviceable replacement for the removed TE rotary actuator can be a

new or overhauled unit that is in serviceable condition.

(b) Install the Outboard Flap Actuator Crank Arm Mechanism. Refer to 767 AMM 27-51-21

as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: February 12, 2013

767-27A0227

42 of 78

BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
NOTE: As part of the installation instructions for the Outboard Flap Actuator Crank

Arm Mechanism, install an overhauled or new TE rotary actuator.

Also as part of the installation of the Outboard Flap Actuator Crank Arm

Mechanism, the instructions include steps restore the TE Flap support rib

assembly and reinstall the TE position transmitter and the torque tube.

CONDITION 3: Both bearings at the TE Flap support rib assembly have all faces that

meet the definitions of moderately damaged or fractured bearing face

(1) Get a serviceable replacement for the removed TE rotary actuator if the GVI finds that

there are two moderately damaged or fractured bearing faces in each bearing at the TE

Flap support rib assembly in Flap Position 1.

NOTE: A serviceable replacement for the removed TE rotary actuator can be a new or

overhauled unit that is in serviceable condition.

(2) Discard the removed TE rotary actuator.

(3) Install the Outboard Flap Actuator Crank Arm Mechanism. Refer to 767 AMM 27-51-21

as an accepted procedure.

NOTE: As part of the installation instructions for the Outboard Flap Actuator Crank Arm

Mechanism, install an overhauled or new TE rotary actuator.

Also as part of the installation of the Outboard Flap Actuator Crank Arm

Mechanism, the instructions include steps restore the TE Flap support rib

assembly and reinstall the TE position transmitter and the torque tube.

2. If the inspection in PART 1A of the TE Flap support bearings at the TE Flap support rib assembly

in Flap Position 2 found at least one bearing without a roller retention feature, replace the TE Flap

support rib bearings at actuator support rib in Position 2:

a. Remove the applicable Outboard Flap Actuator Crank Arm Mechanism. Refer to 767 AMM

27-51-21 as an accepted procedure.

b. Get access to the bearings at the TE Flap support rib assembly in Flap Position 2. Refer to

FIGURE 6.

c. Replace both bearings at the TE Flap support rib assembly. Refer to FIGURE 6.

d. Do a General Visual Inspection (GVI) of the removed TE Flap support bearings and look for

bearing damage.

NOTE: Bearing damage can be detected by finding one or more of the following conditions:

— Migrated or missing rollers in the bearing face. A migrated roller is a loose roller

that has partially moved or shifted horizontally out of the bearing race but is still

part of the bearing assembly. A missing roller can be detected by an empty roller

slot in the roller race or by counting the rollers in the exposed bearing face; there

should be a total of 57 rollers in each Rexnord bearing face.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: February 12, 2013

767-27A0227

43 of 78

BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
— Damage on the bearing race, metal wear debris in the bearing and in the bearing

grease, and bearing abrasion on the bearing face. Detecting damage on the

bearing cage or the bearing race includes finding a bent, broken, cracked,

indented, spalled, fractured, brinelled, nicked, burred, eroded, or deformed

bearing race. Also, rollers grinding each other or the bearing race or spacer can

create metal wear filings, debris, flakes, or splinters inside and around the

bearing, leading to bearing abrasion or other damage conditions.

(1) Record the condition of the removed TE Flap support bearings. Refer to APPENDIX A

for the accepted bearing damage definitions and a suggested worksheet to record the

condition of the removed bearings.

NOTE: Damage of the TE support rib bearings can result in the introduction of side

loading into the associated TE rotary actuator, compromising it. Overhaul or

replacement of the applicable TE rotary actuator may be required depending

on the condition of the removed bearings.

e. Find if the TE rotary actuators at Flap Position 2 is serviceable or if it needs to be overhauled

or replaced. Refer to APPENDIX A for the accepted bearing damage definitions.

CONDITION 1: Both bearings at the TE Flap support rib assembly have at least one

face each that meets the definitions of good or slightly damaged bearing face

(1) If there is at least one good or slightly damaged bearing face in each bearing at the TE

Flap support rib assembly in Flap Position 2, the TE rotary actuator is acceptable and

may be used as-is.

(2) Install the Outboard Flap Actuator Crank Arm Mechanism. Refer to 767 AMM 27-51-21

as an accepted procedure.

NOTE: As part of the installation of the Outboard Flap Actuator Crank Arm Mechanism,

the instructions include steps to restore the TE Flap support rib assembly and

reinstall the TE position transmitter and the torque tube.

CONDITION 2: Only one bearing at the TE Flap support rib assembly has at least one

face that meets the definition of good or slightly damaged bearing face. The other

bearing at the same TE Flap support rib assembly has faces that meet the definitions

of moderately damaged or fractured bearing face

(1) If there is at least one good or slightly damaged bearing face in only one bearing at the

TE Flap support rib in Flap Position 2, do one of the two options:

OPTION 1: Overhaul the TE Rotary Actuator

(a) Overhaul the TE rotary actuator in accordance with CMM 27-51-10 or CMM 27-51-49.

NOTE: The removed TE rotary actuator cannot be returned to service unless a

complete disassembly of the unit, a Non-Destructive Inspection (NDI) of all

components, check all rotary actuator parts, repair, if necessary, clean,

reassemble the unit, and test, are completed in accordance with CMM

27-51-10 or CMM 27-51-49.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: February 12, 2013

767-27A0227

44 of 78

BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
(b) Install the Outboard Flap Actuator Crank Arm Mechanism. Refer to 767 AMM 27-51-21

as an accepted procedure.

NOTE: As part of the installation instructions for the Outboard Flap Actuator Crank

Arm Mechanism, reinstall the overhauled TE rotary actuator.

Also as part of the installation of the Outboard Flap Actuator Crank Arm

Mechanism, the instructions include steps restore the TE Flap support rib

assembly and reinstall the TE position transmitter and the torque tube.

OPTION 2: Replace the TE Rotary Actuator

(a) Get a serviceable replacement for the removed TE rotary actuator.

NOTE: The removed TE rotary actuator cannot be returned to service unless a

complete disassembly of the unit, a Non-Destructive Inspection (NDI) of all

components, check all rotary actuator parts, repair, if necessary, clean,

reassemble the unit, and test, are completed in accordance with CMM

27-51-10 or CMM 27-51-49

A serviceable replacement for the removed TE rotary actuator can be a

new or overhauled unit that is in serviceable condition.

(b) Install the Outboard Flap Actuator Crank Arm Mechanism. Refer to 767 AMM 27-51-21

as an accepted procedure.

NOTE: As part of the installation instructions for the Outboard Flap Actuator Crank

Arm Mechanism, install an overhauled or new TE rotary actuator.

Also as part of the installation of the Outboard Flap Actuator Crank Arm

Mechanism, the instructions include steps restore the TE Flap support rib

assembly and reinstall the TE position transmitter and the torque tube.

CONDITION 3: Both bearings at the TE Flap support rib assembly have all faces that

meet the definitions of moderately damaged or fractured bearing face

(1) Get a serviceable replacement for the removed TE rotary actuator if the GVI finds that

there are two moderately damaged or fractured bearing faces in each bearing at the TE

Flap support rib assembly in Flap Position 2.

NOTE: A serviceable replacement for the removed TE rotary actuator can be a new or

overhauled unit that is in serviceable condition.

(2) Discard the removed TE rotary actuator.

(3) Install the Outboard Flap Actuator Crank Arm Mechanism. Refer to 767 AMM 27-51-21

as an accepted procedure.

NOTE: As part of the installation instructions for the Outboard Flap Actuator Crank Arm

Mechanism, install an overhauled or new TE rotary actuator.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: February 12, 2013

767-27A0227

45 of 78

BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Also as part of the installation of the Outboard Flap Actuator Crank Arm

Mechanism, the instructions include steps restore the TE Flap support rib

assembly and reinstall the TE position transmitter and the torque tube.

3. If the inspection in PART 1A of the TE Flap support bearings at the TE Flap support rib assembly

in Flap Position 7 found at least one bearing without a roller retention feature, replace the TE Flap

support rib bearings at actuator support rib in Position 7:

a. Remove the applicable Outboard Flap Actuator Crank Arm Mechanism. Refer to 767 AMM

27-51-21 as an accepted procedure.

b. Get access to the bearings at the TE Flap support rib assembly in Flap Position 7. Refer to

FIGURE 7.

c. Replace both bearings at the TE Flap support rib assembly. Refer to FIGURE 7.

d. Do a General Visual Inspection (GVI) of the removed TE Flap support bearings and look for

bearing damage.

NOTE: Bearing damage can be detected by finding one or more of the following conditions:

— Migrated or missing rollers in the bearing face. A migrated roller is a loose roller

that has partially moved or shifted horizontally out of the bearing race but is still

part of the bearing assembly. A missing roller can be detected by an empty roller

slot in the roller race or by counting the rollers in the exposed bearing face; there

should be a total of 57 rollers in each Rexnord bearing face.

— Damage on the bearing race, metal wear debris in the bearing and in the bearing

grease, and bearing abrasion on the bearing face. Detecting damage on the

bearing cage or the bearing race includes finding a bent, broken, cracked,

indented, spalled, fractured, brinelled, nicked, burred, eroded, or deformed

bearing race. Also, rollers grinding each other or the bearing race or spacer can

create metal wear filings, debris, flakes, or splinters inside and around the

bearing, leading to bearing abrasion or other damage conditions.

(1) Record the condition of the removed TE Flap support bearings. Refer to APPENDIX A

for the accepted bearing damage definitions and a suggested worksheet to record the

condition of the removed bearings.

NOTE: Damage of the TE support rib bearings can result in the introduction of side

loading into the associated TE rotary actuator, compromising it. Overhaul or

replacement of the applicable TE rotary actuator may be required depending

on the condition of the removed bearings.

e. Find if the TE rotary actuators at Flap Position 7 is serviceable or if it needs to be overhauled

or replaced. Refer to APPENDIX A for the accepted bearing damage definitions.

CONDITION 1: Both bearings at the TE Flap support rib assembly have at least one

face each that meets the definitions of good or slightly damaged bearing face

(1) If there is at least one good or slightly damaged bearing face in each bearing at the TE

Flap support rib assembly in Flap Position 7, the TE rotary actuator is acceptable and

may be used as-is.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: February 12, 2013

767-27A0227

46 of 78

BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
(2) Install the Outboard Flap Actuator Crank Arm Mechanism. Refer to 767 AMM 27-51-21

as an accepted procedure.

NOTE: As part of the installation of the Outboard Flap Actuator Crank Arm Mechanism,

the instructions include steps to restore the TE Flap support rib assembly and

reinstall the TE position transmitter and the torque tube.

CONDITION 2: Only one bearing at the TE Flap support rib assembly has at least one

face that meets the definition of good or slightly damaged bearing face. The other

bearing at the same TE Flap support rib assembly has faces that meet the definitions

of moderately damaged or fractured bearing face

(1) If there is at least one good or slightly damaged bearing face in only one bearing at the

TE Flap support rib in Flap Position 7, do one of the two options:

OPTION 1: Overhaul the TE Rotary Actuator

(a) Overhaul the TE rotary actuator in accordance with CMM 27-51-10 or CMM 27-51-49.

NOTE: The removed TE rotary actuator cannot be returned to service unless a

complete disassembly of the unit, a Non-Destructive Inspection (NDI) of all

components, check all rotary actuator parts, repair, if necessary, clean,

reassemble the unit, and test, are completed in accordance with CMM

27-51-10 or CMM 27-51-49.

(b) Install the Outboard Flap Actuator Crank Arm Mechanism. Refer to 767 AMM 27-51-21

as an accepted procedure.

NOTE: As part of the installation instructions for the Outboard Flap Actuator Crank

Arm Mechanism, reinstall the overhauled TE rotary actuator.

Also as part of the installation of the Outboard Flap Actuator Crank Arm

Mechanism, the instructions include steps restore the TE Flap support rib

assembly and reinstall the TE position transmitter and the torque tube.

OPTION 2: Replace the TE Rotary Actuator

(a) Get a serviceable replacement for the removed TE rotary actuator.

NOTE: The removed TE rotary actuator cannot be returned to service unless a

complete disassembly of the unit, a Non-Destructive Inspection (NDI) of all

components, check all rotary actuator parts, repair, if necessary, clean,

reassemble the unit, and test, are completed in accordance with CMM

27-51-10 or CMM 27-51-49

A serviceable replacement for the removed TE rotary actuator can be a

new or overhauled unit that is in serviceable condition.

(b) Install the Outboard Flap Actuator Crank Arm Mechanism. Refer to 767 AMM 27-51-21

as an accepted procedure.

NOTE: As part of the installation instructions for the Outboard Flap Actuator Crank

Arm Mechanism, install an overhauled or new TE rotary actuator.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: February 12, 2013

767-27A0227

47 of 78

BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Also as part of the installation of the Outboard Flap Actuator Crank Arm

Mechanism, the instructions include steps restore the TE Flap support rib

assembly and reinstall the TE position transmitter and the torque tube.

CONDITION 3: Both bearings at the TE Flap support rib assembly have all faces that

meet the definitions of moderately damaged or fractured bearing face

(1) Get a serviceable replacement for the removed TE rotary actuator if the GVI finds that

there are two moderately damaged or fractured bearing faces in each bearing at the TE

Flap support rib assembly in Flap Position 7.

NOTE: A serviceable replacement for the removed TE rotary actuator can be a new or

overhauled unit that is in serviceable condition.

(2) Discard the removed TE rotary actuator.

(3) Install the Outboard Flap Actuator Crank Arm Mechanism. Refer to 767 AMM 27-51-21

as an accepted procedure.

NOTE: As part of the installation instructions for the Outboard Flap Actuator Crank Arm

Mechanism, install an overhauled or new TE rotary actuator.

Also as part of the installation of the Outboard Flap Actuator Crank Arm

Mechanism, the instructions include steps restore the TE Flap support rib

assembly and reinstall the TE position transmitter and the torque tube.

4. If the inspection in PART 1A of the TE Flap support bearings at the TE Flap support rib assembly

in Flap Position 8 found at least one bearing without a roller retention feature, replace the TE Flap

support rib bearings at actuator support rib in Position 8:

a. Remove the applicable Outboard Flap Actuator Crank Arm Mechanism. Refer to 767 AMM

27-51-21 as an accepted procedure.

b. Get access to the bearings at the TE Flap support rib assembly in Flap Position 8. Refer to

FIGURE 8.

c. Replace both bearings at the TE Flap support rib assembly. Refer to FIGURE 8.

d. Do a General Visual Inspection (GVI) of the removed TE Flap support bearings and look for

bearing damage.

NOTE: Bearing damage can be detected by finding one or more of the following conditions:

— Migrated or missing rollers in the bearing face. A migrated roller is a loose roller

that has partially moved or shifted horizontally out of the bearing race but is still

part of the bearing assembly. A missing roller can be detected by an empty roller

slot in the roller race or by counting the rollers in the exposed bearing face; there

should be a total of 57 rollers in each Rexnord bearing face.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: February 12, 2013

767-27A0227

48 of 78

BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
— Damage on the bearing race, metal wear debris in the bearing and in the bearing

grease, and bearing abrasion on the bearing face. Detecting damage on the

bearing cage or the bearing race includes finding a bent, broken, cracked,

indented, spalled, fractured, brinelled, nicked, burred, eroded, or deformed

bearing race. Also, rollers grinding each other or the bearing race or spacer can

create metal wear filings, debris, flakes, or splinters inside and around the

bearing, leading to bearing abrasion or other damage conditions.

(1) Record the condition of the removed TE Flap support bearings. Refer to APPENDIX A

for the accepted bearing damage definitions and a suggested worksheet to record the

condition of the removed bearings.

NOTE: Damage of the TE support rib bearings can result in the introduction of side

loading into the associated TE rotary actuator, compromising it. Overhaul or

replacement of the applicable TE rotary actuator may be required depending

on the condition of the removed bearings.

e. Find if the TE rotary actuators at Flap Position 8 is serviceable or if it needs to be overhauled

or replaced. Refer to APPENDIX A for the accepted bearing damage definitions.

CONDITION 1: Both bearings at the TE Flap support rib assembly have at least one

face each that meets the definitions of good or slightly damaged bearing face

(1) If there is at least one good or slightly damaged bearing face in each bearing at the TE

Flap support rib assembly in Flap Position 8, the TE rotary actuator is acceptable and

may be used as-is.

(2) Install the Outboard Flap Actuator Crank Arm Mechanism. Refer to 767 AMM 27-51-21

as an accepted procedure.

NOTE: As part of the installation of the Outboard Flap Actuator Crank Arm Mechanism,

the instructions include steps to restore the TE Flap support rib assembly and

reinstall the TE position transmitter and the torque tube.

CONDITION 2: Only one bearing at the TE Flap support rib assembly has at least one

face that meets the definition of good or slightly damaged bearing face. The other

bearing at the same TE Flap support rib assembly has faces that meet the definitions

of moderately damaged or fractured bearing face

(1) If there is at least one good or slightly damaged bearing face in only one bearing at the

TE Flap support rib in Flap Position 8, do one of the two options:

OPTION 1: Overhaul the TE Rotary Actuator

(a) Overhaul the TE rotary actuator in accordance with CMM 27-51-10 or CMM 27-51-49.

NOTE: The removed TE rotary actuator cannot be returned to service unless a

complete disassembly of the unit, a Non-Destructive Inspection (NDI) of all

components, check all rotary actuator parts, repair, if necessary, clean,

reassemble the unit, and test, are completed in accordance with CMM

27-51-10 or CMM 27-51-49.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: February 12, 2013

767-27A0227

49 of 78

BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
(b) Install the Outboard Flap Actuator Crank Arm Mechanism. Refer to 767 AMM 27-51-21

as an accepted procedure.

NOTE: As part of the installation instructions for the Outboard Flap Actuator Crank

Arm Mechanism, reinstall the overhauled TE rotary actuator.

Also as part of the installation of the Outboard Flap Actuator Crank Arm

Mechanism, the instructions include steps restore the TE Flap support rib

assembly and reinstall the TE position transmitter and the torque tube.

OPTION 2: Replace the TE Rotary Actuator

(a) Get a serviceable replacement for the removed TE rotary actuator.

NOTE: The removed TE rotary actuator cannot be returned to service unless a

complete disassembly of the unit, a Non-Destructive Inspection (NDI) of all

components, check all rotary actuator parts, repair, if necessary, clean,

reassemble the unit, and test, are completed in accordance with CMM

27-51-10 or CMM 27-51-49

A serviceable replacement for the removed TE rotary actuator can be a

new or overhauled unit that is in serviceable condition.

(b) Install the Outboard Flap Actuator Crank Arm Mechanism. Refer to 767 AMM 27-51-21

as an accepted procedure.

NOTE: As part of the installation instructions for the Outboard Flap Actuator Crank

Arm Mechanism, install an overhauled or new TE rotary actuator.

Also as part of the installation of the Outboard Flap Actuator Crank Arm

Mechanism, the instructions include steps restore the TE Flap support rib

assembly and reinstall the TE position transmitter and the torque tube.

CONDITION 3: Both bearings at the TE Flap support rib assembly have all faces that

meet the definitions of moderately damaged or fractured bearing face

(1) Get a serviceable replacement for the removed TE rotary actuator if the GVI finds that

there are two moderately damaged or fractured bearing faces in each bearing at the TE

Flap support rib assembly in Flap Position 8.

NOTE: A serviceable replacement for the removed TE rotary actuator can be a new or

overhauled unit that is in serviceable condition.

(2) Discard the removed TE rotary actuator.

(3) Install the Outboard Flap Actuator Crank Arm Mechanism. Refer to 767 AMM 27-51-21

as an accepted procedure.

NOTE: As part of the installation instructions for the Outboard Flap Actuator Crank Arm

Mechanism, install an overhauled or new TE rotary actuator.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: February 12, 2013

767-27A0227

50 of 78

BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Also as part of the installation of the Outboard Flap Actuator Crank Arm

Mechanism, the instructions include steps restore the TE Flap support rib

assembly and reinstall the TE position transmitter and the torque tube.

5. Install the applicable access panels at the lower surface of the wing trailing edge. Refer to 767

AMM 06-44-00 as an accepted procedure.

6. Remove the applicable spoiler locks. Refer to 767 AMM 27-61-00 as an accepted procedure.

Group 1-3, Configuration 2:

FUNCTIONAL TEST AFTER TE FLAP SUPPORT BEARINGS REPLACEMENT

1. Pressurize the center hydraulic system. Refer to 767 AMM 29-11-00 as an accepted procedure.

2. Operate the Flap control lever through a full cycle and make sure the Flaps operate correctly.

3. Put the airplane back to a serviceable condition.

Group 1, 3, Configuration 1:

PART 3: RE-IDENTIFY THE TRAILING EDGE (TE) FLAP SUPPORT RIB ASSEMBLY FOR

APPLICABLE FLAP POSITIONS WITH CORRECT NEW PART NUMBERS

1. Deactivate Trailing Edge Flap. Refer to 767 AMM 27-51-00 as an accepted procedure.

2. Get access to the Trailing Edge (TE) Flap support rib assembly for Flap Positions 1 and 8 by

removing access panels 561JB, 561HB, 561GB on the lower surface of the wing trailing edge.

Refer to 767 AMM 06-44-00 as an accepted procedure.

3. Group 1, Configuration 1:

Reidentify the TE Flap support rib assembly in Flap Positions 1 and 8 with the correct new part

numbers. Refer to FIGURE 9.

4. Group 3, Configuration 1:

Reidentify the TE Flap support rib assembly in Flap Positions 1, 2, 7 and 8 with the correct new

part numbers. Refer to FIGURE 9.

5. Activate Trailing Edge Flap. Refer to 767 AMM 27-51-00 as an accepted procedure.

6. Remove the power from the center hydraulic system. Refer to 767 AMM 29-11-00 as an accepted

procedure.

7. Remove electrical power. Refer to 767 AMM 24-22-00 as an accepted procedure.

8. Put the airplane back to a serviceable condition.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

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Original Issue: February 12, 2013

767-27A0227

51 of 78

BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
This Figure applies only to: Group 1-3, Configuration 2.

FIGURE 1: INSPECT THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITIONS 1, 2, 7, AND 8, OUTBOARD SIDE

(SHEET 1 OF 3)

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767-27A0227

52 of 78

BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
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 side of the TE Flap support rib.

Step Task Name Identification Qty More Data

1 Remove / Keep Nut - 2 (a)

Remove / Keep Washer - 2 (a)

2 Remove / Keep Nut - 1 (a)

Remove / Keep Washer - 1 (a)

3 Remove / Keep Transmitter Housing - 1 (a)

4 Remove Safety lockwire - - (a)

5 Remove / Keep Nut - 1 (b)

6 Remove / Keep Washer - 1

7 Remove / Keep Nut - 6 (a)

Remove / Keep Washer - 6 (a)

8 Remove / Keep Nut - 3 (a)

Remove / Keep Washer - 3 (a)

9 Remove / Keep Rib Doubler - 1

10 Locate Bearing - 1

FIGURE 1: INSPECT THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITIONS 1, 2, 7, AND 8, OUTBOARD SIDE

(SHEET 2 OF 3)

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767-27A0227

53 of 78

BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Step Task Name Identification Qty More Data

carefully, as required, with a piece

of cloth to get visual

access to bearing

face

11 Clean Grease - -

Do a General Visual

Inspection (GVI) of

the removed TE

Flap support bearings and look for

bearing type and

possible bearing

damage

12 Inspect Bearing - 1

13 Clean Rib Doubler - 1 (c)

(a) Make a note or write down the location of removed nuts and washers. During installation, the bolts,

washers, and nuts should be placed in their original locations to prevent any damage.

(b) Refer to 0A-27128 for suggested spanner wrench tool.

(c) Clean off grease and, if present, Mastinox compound. Refer to SOPM 20-30-03.

FIGURE 1: INSPECT THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITIONS 1, 2, 7, AND 8, OUTBOARD SIDE

(SHEET 3 OF 3)

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767-27A0227

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
This Figure applies only to: Group 1-3, Configuration 2.

FIGURE 2: INSPECT THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITIONS 1, 2, 7, AND 8, INBOARD SIDE

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

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Original Issue: February 12, 2013

767-27A0227

55 of 78

BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
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 side of the TE Flap support rib.

Step Task Name Identification Qty More Data

1 Remove / Keep Nut - 7 (a)

Remove / Keep Washer - 7 (a)

2 Remove / Keep Nut - 3 (a)

Remove / Keep Washer - 3 (a)

3 Remove / Keep Nut - 3 (a)

Remove / Keep Washer - 3 (a)

4 Remove / Keep Nut - 2 (a)

Remove / Keep Washer - 2 (a)

5 Remove / Keep Nut - 1 (a)

Remove / Keep Washer - 1 (a)

6 Remove / Keep Reaction Ring - 1

7 Remove / Keep Shim - 1

8 Locate Bearing - 1

FIGURE 2: INSPECT THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITIONS 1, 2, 7, AND 8, INBOARD SIDE

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Step Task Name Identification Qty More Data

carefully, as required, with a piece

of cloth to get visual

access to bearing

face

9 Clean Grease - -

Do a General Visual

Inspection (GVI) of

the removed TE

Flap support bearings and look for

bearing type and

possible bearing

damage

10 Inspect Bearing - 1

11 Clean Shim - 1 (b)

Clean Reaction Ring - 1 (b)

(a) Make a note or write down the location of removed nuts and washers. During installation, the bolts,

washers, and nuts should be placed in their original locations to prevent any damage.

(b) Clean off grease and, if present, Mastinox compound. Refer to SOPM 20-30-03.

FIGURE 2: INSPECT THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITIONS 1, 2, 7, AND 8, INBOARD SIDE

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
This Figure applies only to: Group 1-3, Configuration 2.

FIGURE 3: RESTORE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITIONS 1, 2, 7, AND 8, OUTBOARD SIDE

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
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 side of the TE Flap support rib.

Step Task Name Identification Qty More Data

Apply BMS3-33

grease to mating

surface

1 Install (Kept) Rib Doubler - 1

Tighten nut to torque

range of 220-410

Inch-Pounds

2 Install (Kept) Washer - 6

Install (Kept) Nut - 6

3 Install (Kept) Washer - 3

Tighten nut to torque

range of 95-105

Inch-Pounds

Install (Kept) Nut - 3

4 Install (Kept) Washer - 1

Tighten nut to torque

range of 2800-3500

Inch-Pounds

5 Install (Kept) Nut - 1

(a)

FIGURE 3: RESTORE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITIONS 1, 2, 7, AND 8, OUTBOARD SIDE

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Step Task Name Identification Qty More Data

such that the pigtail

is on top of the bearing retainer nut

6 Install (New) Safety lockwire MS20995NC40 -

(c)

7 Install (Kept) Transmitter Housing - 1

8 Install (Kept) Washer - 2 (b)

Install (Kept) Nut - 2 (b)

Tighten nut to torque

range of 95-105

Inch-Pounds

9 Install (Kept) Nut - 1 (b)

Install (Kept) Washer - 1 (b)

Apply grease at this

location until you

see clean grease

come out from the

seal

10 Inject Grease BMS3-33 -

(a) Refer to 0A-27128 for suggested spanner wrench tool.

(b) Temporarily install fastener. Final installation to be performed with systems installation.

(c) Refer to 767 AMM 20-10-23 as an accepted procedure.

FIGURE 3: RESTORE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITIONS 1, 2, 7, AND 8, OUTBOARD SIDE

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
This Figure applies only to: Group 1-3, Configuration 2.

FIGURE 4: RESTORE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITIONS 1, 2, 7, AND 8, INBOARD SIDE

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
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 side of the TE Flap support rib.

Step Task Name Identification Qty More Data

1 Install (Kept) Shim - 1

Apply BMS3-33

grease to mating

surface

2 Install (Kept) Reaction Ring - 1

3 Install (Kept) Washer - 3

Tighten nut to torque

range of 220-410

Inch-Pounds

Install (Kept) Nut - 3

4 Install (Kept) Washer - 2

Tighten nut to torque

range of 370-690

Inch-Pounds

Install (Kept) Nut - 2

5 Install (Kept) Washer - 3

Tighten nut to torque

range of 220-410

Inch-Pounds

Install (Kept) Nut - 3

6 Install (Kept) Washer - 7

Tighten nut to torque

range of 370-690

Inch-Pounds

Install (Kept) Nut - 7

7 Install (Kept) Washer - 1

Tighten nut to torque

range of 150-170

Inch-Pounds

Install (Kept) Nut - 1

Apply grease at this

location until you

see clean grease

come out from the

seal

8 Inject Grease BMS3-33 -

FIGURE 4: RESTORE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITIONS 1, 2, 7, AND 8, INBOARD SIDE

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
This Figure applies only to: Group 1-3, Configuration 2.

FIGURE 5: REPLACE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITION 1

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
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 TE Flap support rib.

Step Task Name Identification Qty More Data

1 Remove / Keep Bushing - 1 (b)

CAUTION: MAKE A NOTE OF THE SEAL ORIENTATION. DURING INSTALLATION, THE SEAL MUST

BE CORRECTLY ORIENTED TO AVOID BEARING DAMAGE DUE TO LACK OF LUBRICATION.

2 Remove Seal 113T1256-31 4

with wet primer

BMS10-11

Install (New) SEAL 113T1256-31 4

CAUTION: DO NOT HIT THE ENDS OF THE SHAFT WHEN YOU REMOVE OR INSTALL THE SHAFT

ON THE SUPPORT RIBS AS THIS CAN APPLY FORCES ON THE BEARING INNER RACE

AND CAUSE DAMAGE TO THE BEARINGS.

CAUTION: DO NOT APPLY FORCE ON THE SUPPORT RIBS TO INSTALL OR REMOVE THE SHAFT

AS THIS CAN CAUSE DAMAGE TO THE SUPPORT RIBS.

CAUTION: MAKE SURE THAT THE PARTS, LUBRICANT, AND CORROSION INHIBITING COMPOUND

ARE CLEAN. CONTAMINATION ON THE PARTS CAN CAUSE DAMAGE TO THE MATING

SURFACES.

Refer to APPENDIX

A bearing damage

definitions and a

suggested worksheet to record the

condition of the removed bearings

3 Remove Bearing 60B00178-23 2

or any other bearing

that meets Boeing

specifications

S113T134-1

BEARING, SPHERI- SB-1131 2

CAL ROLLER, AIRFRAME, INCH

Install (New)

(a) (b) (c)

4 Clean Bushing - 1 (d)

Clean Shaft - 1 (d)

Clean Crank arm assy - 1 (d)

Clean Rib Doubler - 1 (d)

Clean Bearing Retainer - 1 (d)

Corrosion Inhibiting BMS3-38 - (e)

Compound

5 Apply

FIGURE 5: REPLACE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITION 1

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Step Task Name Identification Qty More Data

6 Install (Kept) Bushing - -

TE Flap support rib as- - 1 (f) (g)

sembly

7 Identify

(a) Install with BMS3-33 grease.

(b) Refer to Boeing tool kit drawing 0A-27128 for suggested shaft removal/installation and spanner wrench

tools. Use tool to push the end of the shaft, the crank arm, and the bushing together.

(c) You can tap the shaft with a light mallet to help align the bearing to the shaft during bearing installation.

Refer to Boeing tool kit drawing 0A-27128 for suggested bearing installation tool.

(d) Clean off grease and, if present, Mastinox compound. Refer to SOPM 20-30-03.

(e) Apply corrosion-inhibiting compound to surfaces of cavities and splines that make contact between the

shaft and the crank arm. Wipe off squeeze-out with dry wiper.

(f) Refer to Paragraph 2.C.3., Parts Modified and Reidentified for existing and new part numbers.

(g) Repart mark the TE Flap support rib assembly. Refer to SOPM 20-50-10.

FIGURE 5: REPLACE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITION 1

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
This Figure applies only to: Group 1-3, Configuration 2.

FIGURE 6: REPLACE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITION 2

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
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 TE Flap support rib.

Step Task Name Identification Qty More Data

1 Remove / Keep Bushing - 1 (b)

CAUTION: MAKE A NOTE OF THE SEAL ORIENTATION. DURING INSTALLATION, THE SEAL MUST

BE CORRECTLY ORIENTED TO AVOID BEARING DAMAGE DUE TO LACK OF LUBRICATION.

2 Remove Seal 113T1256-31 4

with wet primer

BMS10-11

Install (New) SEAL 113T1256-31 4

CAUTION: DO NOT HIT THE ENDS OF THE SHAFT WHEN YOU REMOVE OR INSTALL THE SHAFT

ON THE SUPPORT RIBS AS THIS CAN APPLY FORCES ON THE BEARING INNER RACE

AND CAUSE DAMAGE TO THE BEARINGS.

CAUTION: DO NOT APPLY FORCE ON THE SUPPORT RIBS TO INSTALL OR REMOVE THE SHAFT

AS THIS CAN CAUSE DAMAGE TO THE SUPPORT RIBS.

CAUTION: MAKE SURE THAT THE PARTS, LUBRICANT, AND CORROSION INHIBITING COMPOUND

ARE CLEAN. CONTAMINATION ON THE PARTS CAN CAUSE DAMAGE TO THE MATING

SURFACES.

Refer to APPENDIX

A bearing damage

definitions and a

suggested worksheet to record the

condition of the removed bearings

3 Remove Bearing 60B00178-23 2

or any other bearing

that meets Boeing

specifications

S113T134-1

BEARING, SPHERI- SB-1131 2

CAL ROLLER, AIRFRAME, INCH

Install (New)

(a) (b) (c)

4 Clean Bushing - 1 (d)

Clean Shaft - 1 (d)

Clean Crank arm assy - 1 (d)

Clean Rib Doubler - 1 (d)

Clean Bearing Retainer - 1 (d)

Corrosion Inhibiting BMS3-38 - (e)

Compound

5 Apply

FIGURE 6: REPLACE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITION 2

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Step Task Name Identification Qty More Data

6 Install (Kept) Bushing - -

TE Flap support rib as- - 1 (f) (g)

sembly

7 Identify

(a) Install with BMS3-33 grease.

(b) Refer to Boeing tool kit drawing 0A-27128 for suggested shaft removal/installation and spanner wrench

tools. Use tool to push the end of the shaft, the crank arm, and the bushing together.

(c) You can tap the shaft with a light mallet to help align the bearing to the shaft during bearing installation.

Refer to Boeing tool kit drawing 0A-27128 for suggested bearing installation tool.

(d) Clean off grease and, if present, Mastinox compound. Refer to SOPM 20-30-03.

(e) Apply corrosion-inhibiting compound to surfaces of cavities and splines that make contact between the

shaft and the crank arm. Wipe off squeeze-out with dry wiper.

(f) Refer to Paragraph 2.C.3., Parts Modified and Reidentified for existing and new part numbers.

(g) Repart mark the TE Flap support rib assembly. Refer to SOPM 20-50-10.

FIGURE 6: REPLACE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITION 2

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
This Figure applies only to: Group 1-3, Configuration 2.

FIGURE 7: REPLACE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITION 7

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
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 TE Flap support rib.

Step Task Name Identification Qty More Data

1 Remove / Keep Bushing - 1 (b)

CAUTION: MAKE A NOTE OF THE SEAL ORIENTATION. DURING INSTALLATION, THE SEAL MUST

BE CORRECTLY ORIENTED TO AVOID BEARING DAMAGE DUE TO LACK OF LUBRICATION.

2 Remove Seal 113T1256-31 4

with wet primer

BMS10-11

Install (New) SEAL 113T1256-31 4

CAUTION: DO NOT HIT THE ENDS OF THE SHAFT WHEN YOU REMOVE OR INSTALL THE SHAFT

ON THE SUPPORT RIBS AS THIS CAN APPLY FORCES ON THE BEARING INNER RACE

AND CAUSE DAMAGE TO THE BEARINGS.

CAUTION: DO NOT APPLY FORCE ON THE SUPPORT RIBS TO INSTALL OR REMOVE THE SHAFT

AS THIS CAN CAUSE DAMAGE TO THE SUPPORT RIBS.

CAUTION: MAKE SURE THAT THE PARTS, LUBRICANT, AND CORROSION INHIBITING COMPOUND

ARE CLEAN. CONTAMINATION ON THE PARTS CAN CAUSE DAMAGE TO THE MATING

SURFACES.

Refer to APPENDIX

A bearing damage

definitions and a

suggested worksheet to record the

condition of the removed bearings

3 Remove Bearing 60B00178-23 2

or any other bearing

that meets Boeing

specifications

S113T134-1

BEARING, SPHERI- SB-1131 2

CAL ROLLER, AIRFRAME, INCH

Install (New)

(a) (b) (c)

4 Clean Bushing - 1 (d)

Clean Shaft - 1 (d)

Clean Crank arm assy - 1 (d)

Clean Rib Doubler - 1 (d)

Clean Bearing Retainer - 1 (d)

Corrosion Inhibiting BMS3-38 - (e)

Compound

5 Apply

FIGURE 7: REPLACE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITION 7

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Step Task Name Identification Qty More Data

6 Install (Kept) Bushing - -

TE Flap support rib as- - 1 (f) (g)

sembly

7 Identify

(a) Install with BMS3-33 grease.

(b) Refer to Boeing tool kit drawing 0A-27128 for suggested shaft removal/installation and spanner wrench

tools. Use tool to push the end of the shaft, the crank arm, and the bushing together.

(c) You can tap the shaft with a light mallet to help align the bearing to the shaft during bearing installation.

Refer to Boeing tool kit drawing 0A-27128 for suggested bearing installation tool.

(d) Clean off grease and, if present, Mastinox compound. Refer to SOPM 20-30-03.

(e) Apply corrosion-inhibiting compound to surfaces of cavities and splines that make contact between the

shaft and the crank arm. Wipe off squeeze-out with dry wiper.

(f) Refer to Paragraph 2.C.3., Parts Modified and Reidentified for existing and new part numbers.

(g) Repart mark the TE Flap support rib assembly. Refer to SOPM 20-50-10.

FIGURE 7: REPLACE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITION 7

(SHEET 3 OF 3)

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ALERT ALERT
This Figure applies only to: Group 1-3, Configuration 2.

FIGURE 8: REPLACE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITION 8

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
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 TE Flap support rib.

Step Task Name Identification Qty More Data

1 Remove / Keep Bushing - 1 (b)

CAUTION: MAKE A NOTE OF THE SEAL ORIENTATION. DURING INSTALLATION, THE SEAL MUST

BE CORRECTLY ORIENTED TO AVOID BEARING DAMAGE DUE TO LACK OF LUBRICATION.

2 Remove Seal 113T1256-31 4

with wet primer

BMS10-11

Install (New) SEAL 113T1256-31 4

CAUTION: DO NOT HIT THE ENDS OF THE SHAFT WHEN YOU REMOVE OR INSTALL THE SHAFT

ON THE SUPPORT RIBS AS THIS CAN APPLY FORCES ON THE BEARING INNER RACE

AND CAUSE DAMAGE TO THE BEARINGS.

CAUTION: DO NOT APPLY FORCE ON THE SUPPORT RIBS TO INSTALL OR REMOVE THE SHAFT

AS THIS CAN CAUSE DAMAGE TO THE SUPPORT RIBS.

CAUTION: MAKE SURE THAT THE PARTS, LUBRICANT, AND CORROSION INHIBITING COMPOUND

ARE CLEAN. CONTAMINATION ON THE PARTS CAN CAUSE DAMAGE TO THE MATING

SURFACES.

Refer to APPENDIX

A bearing damage

definitions and a

suggested worksheet to record the

condition of the removed bearings

3 Remove Bearing 60B00178-23 2

or any other bearing

that meets Boeing

specifications

S113T134-1

BEARING, SPHERI- SB-1131 2

CAL ROLLER, AIRFRAME, INCH

Install (New)

(a) (b) (c)

4 Clean Bushing - 1 (d)

Clean Shaft - 1 (d)

Clean Crank arm assy - 1 (d)

Clean Rib Doubler - 1 (d)

Clean Bearing Retainer - 1 (d)

Corrosion Inhibiting BMS3-38 - (e)

Compound

5 Apply

FIGURE 8: REPLACE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITION 8

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
Step Task Name Identification Qty More Data

6 Install (Kept) Bushing - -

TE Flap support rib as- - 1 (f) (g)

sembly

7 Identify

(a) Install with BMS3-33 grease.

(b) Refer to Boeing tool kit drawing 0A-27128 for suggested shaft removal/installation and spanner wrench

tools. Use tool to push the end of the shaft, the crank arm, and the bushing together.

(c) You can tap the shaft with a light mallet to help align the bearing to the shaft during bearing installation.

Refer to Boeing tool kit drawing 0A-27128 for suggested bearing installation tool.

(d) Clean off grease and, if present, Mastinox compound. Refer to SOPM 20-30-03.

(e) Apply corrosion-inhibiting compound to surfaces of cavities and splines that make contact between the

shaft and the crank arm. Wipe off squeeze-out with dry wiper.

(f) Refer to Paragraph 2.C.3., Parts Modified and Reidentified for existing and new part numbers.

(g) Repart mark the TE Flap support rib assembly. Refer to SOPM 20-50-10.

FIGURE 8: REPLACE THE TRAILING EDGE FLAP SUPPORT BEARINGS AT THE TE FLAP SUPPORT RIB

ASSEMBLY IN FLAP POSITION 8

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
This Figure applies only to: Group 1, 3, Configuration 1.

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 TE Flap support rib.

Step Task Name Identification Qty More Data

TE Flap support rib as- - - (a) (b)

sembly

1 Identify

(a) Repart mark the applicable TE Flap support rib assembly in Flap Positions 1, 2, 7 and 8. Refer to SOPM

20-50-10.

(b) Refer to Paragraph 2.C.3., Parts Modified and Reidentified for existing and new part numbers.

FIGURE 9: RE-IDENTIFY THE TRAILING EDGE (TE) FLAP SUPPORT RIB ASSEMBLY FOR APPLICABLE

FLAP POSITIONS WITH CORRECT NEW PART NUMBERS

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
This Appendix applies only to: Group 1-3, Configuration 2.

If damage is found in Trailing Edge (TE) Flap support bearings for Positions 1, 2, 7 or 8, find if the TE rotary

actuator(s) at the Flap Positions 1, 2, 7, or 8 are serviceable or if they need to be overhauled or replaced. The

actuator may be used “as-is", it may have to be overhauled, or it may have to be replaced by a new or a spare

unit, depending on the TE Flap support bearings damage, as defined below.

TABLE 1: BEARING FACE DAMAGE TYPE DEFINITIONS, NEEDED TO FIND IF

THE TE ROTARY ACTUATOR(S) AT FLAP POSITIONS 1, 2, 7 or 8 ARE SERVICEABLE OR IF THEY NEED TO BE OVERHAULED OR REPLACED

Bearing Face Description

Damage Type

A "good" Rexnord bearing face has

no signs of damage. All McGill

bearings are considered good

bearings.

Good

A "slightly damaged" bearing face

is detected by finding up to 10 migrated or missing rollers in the

bearing face.

Slightly damaged

A "moderately damaged" bearing

face is detected by finding more

than 10 migrated or missing rollers

in the bearing face.

Moderately damaged

A "fractured" bearing face is detected by finding damage on the bearing race or the bearing spacer,

metal wear debris inside and

around the bearing, and possibly in

the bearing grease, and bearing

abrasion. A fractured bearing will

likely also have loose, migrated, or

missing rollers.

Fractured

APPENDIX A: BEARING DAMAGE DEFINITIONS AND SUGGESTED WORKSHEET TO RECORD THE

CONDITION OF THE REMOVED BEARINGS

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
TABLE 2: TRAILING EDGE FLAP SUPPORT RIBS DAMAGED BEARINGS COMBINATIONS

Other Bearing at the TE Flap support rib

assembly

Either Bearing at the TE Flap support rib

assembly

TE Flap Support

Bearings Damage

Type / Bearing

Combination Quantity of Moderately Damaged or

Fractured Bearing

Faces

Quantity of Good or

Slightly Damaged

Bearing Faces

Quantity of Moderately Damaged or

Fractured Bearing

Faces

Quantity of Good or

Slightly Damaged

Bearing Faces

CONDITION 1:The 2 or 1 0 or 1 2 or 1 0 or 1

two bearings at the

TE Flap support rib

assembly have at

least one face each

that meets the definitions of good or

slightly damaged

bearing face

CONDITION 2: Only 2 or 1 0 or 1 0 2

one bearing at the

TE Flap support rib

assembly has at

least one face that

meets the definition

of good or slightly

damaged bearing

face. The other bearing at the same TE

Flap support rib has

faces that meet the

definitions of moderately damaged or

fractured bearing

face

CONDITION 3:The 0 2 0 2

two bearings at the

TE Flap support rib

assembly have all

faces that meet the

definitions of moderately damaged or

fractured bearing

face

Suggested data sheet for operator to record inspection results and bearing conditions, if desired for record

keeping.

APPENDIX A: BEARING DAMAGE DEFINITIONS AND SUGGESTED WORKSHEET TO RECORD THE

CONDITION OF THE REMOVED BEARINGS

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: February 12, 2013

767-27A0227

77 of 78

BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT
APPENDIX A: BEARING DAMAGE DEFINITIONS AND SUGGESTED WORKSHEET TO RECORD THE

CONDITION OF THE REMOVED BEARINGS

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: February 12, 2013

767-27A0227

78 of 78

BOEING SERVICE BULLETIN 767-27A0227

ALERT ALERT