# Boeing Alert Service Bulletin 767-27A0183: Revision 2

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- Document: [Boeing Alert Service Bulletin 767-27A0183](https://openairdocs.org/service-documents/boeing/767-27a0183.md)
- Title as filed: SB-767-27A0183-02
- Pages: 23
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## Text

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### Page 1

Commercial 
Airplanes
767
Service Bulletin
Number: 767-27A0183
Original Issue: May 09, 2002
Revision 2: September 25, 2014
ATA System: 2751 5751
SUBJECT: FLIGHT CONTROLS - Flaps - Outboard Flap - Deflection Control Track -
Inspection/Replacement
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2002 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
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767-27A0183Revision 2: September 25, 2014
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3.0

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Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 2
B. Concurrent Requirements ...................................... 1 2
C. Reason ................................................ 1 2
D. Description .............................................. 1 3
E. Compliance .............................................. 1 4
F. Approval ............................................... 1 4
G. Manpower .............................................. 1 4
H. Weight and Balance Changes .................................... 1 5
I. Electrical Load Data ......................................... 1 5
J. References .............................................. 1 5
1. Existing Data: ......................................... 1 5
2. Data Supplied with this Service Bulletin: ........................... 1 5
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 5
K. Publications Affected ........................................ 1 6
L. Interchangeability and Intermixability of Parts ........................... 1 6
M. Software Accomplishment Summary ................................ 1 6
2. MATERIAL INFORMATION ........................................ 1 7
A. Material - Price and Availability ................................... 1 7
B. Industry Support Information .................................... 1 7
C. Parts Necessary for Each Airplane ................................. 1 7
1. Kits/Parts: ........................................... 1 7
2. Parts and Materials Supplied by the Operator: ........................ 1 7
3. Parts Modified and Reidentified: ............................... 1 7
4. Parts Removed and Not Replaced: .............................. 1 7
D. Parts Necessary to Change Spares ................................. 1 7
E. Special Tooling - Price and Availability ............................... 1 7
F. Special Tooling Necessary to do this Service Bulletin ....................... 1 7
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 9
A. GENERAL INFORMATION ..................................... 1 9
B. WORK INSTRUCTIONS ....................................... 2 0
FIGURE 1: LOGIC DIAGRAM OF INSPECTION AND MAINTENANCE ALTERNATIVES ....... 2 1
FIGURE 2: OUTBOARD FLAP DETECTION CONTROL TRACK - AFT LOWER LUG INSPECTION . 22
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Commercial 
Airplanes
767
Service Bulletin
Revision Transmittal SheetNumber: 767-27A0183Original Issue: May 09, 2002
Revision 2: September 25, 2014
ATA System: 2751 5751
SUBJECT: FLIGHT CONTROLS - Flaps - Outboard Flap - Deflection Control Track -
Inspection/Replacement
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Airworthiness Directive AD 2004-07-11 is related to this service bulletin.
No more work is necessary on the airplanes changed or inspected in accordance with the Revision 1 of this
service bulletin.
REASON FOR REVISION
This revision is sent to:
1. Revise the compliance time for airplanes VR087, VR106, VS710, VS711, VS712, VS731, VS732,
VS882, VS883, VS891, and VS896 which were added to this service bulletin in Revision 1 to be the
same as the original airplanes in the service bulletin. The initial compliance time for these airplanes
was 1,200 flight cycles from Revision 1 date. One operator noted that the compliance time for the
original airplanes in the service bulletin was before the accumulation of 12,000 total flight cycles, or
within 1,200 flight cycles after the effective date of FAA AD 2004-07-11, whichever occurs later, and
believes that it should be the same as the airplanes added in Revision 1. We agreed that the initial
compliance time for the airplanes added in Revision 1 should be the same as the original airplanes in
the service bulletin. This results in the effectivity being split into two groups to clarify the different
compliance times for the airplanes in the Original Issue and the airplanes added in Revision 1.
2. Clarify summary page illustration and work instructions to match changes in logic diagram made in
Revision 1.
3. Clarify the compliance time for Group 1 Airplanes in the logic diagram to add: whichever occurs later.
Add Effective date of AD 2004-07-11 to Compliance section.
These sections were changed:
1. Summary
a. Illustration - Revised text to match Action paragraph.
2. Planning Information
a. Paragraph 1.C., Reason - Added reason for Revision 2.
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b. Paragraph 1.D., Description - Added compliance information for Revision 2.
c. Paragraph 1.E., Compliance - Add effective date of AD 2004-07-11.
d. Paragraph 1.F., Approval - Added Revision 2 to AMOC Statement.
3. Material Information
a. No Changes.
4. Accomplishment Instructions
a. Paragraph 3.B., Work Instructions
(1) Step 3.B.2. - Added part number of track assembly requiring inspection to match logic diagram.
(2) Figure 1
(a) Added compliance time for Group 2 Airplanes.
(b) Corrected the compliance time for Group 1 airplane by adding, whichever occurs later.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,
to show the location of all content changes.
Pages with no vertical lines have no changes.
REVISION HISTORY
May 09, 2002Original Issue:
April 04, 2014Revision 1:
September 25, 2014Revision 2:
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Commercial 
Airplanes
767
Service Bulletin
SummaryNumber: 767-27A0183Original Issue: May 09, 2002
Revision 2: September 25, 2014
ATA System: 2751 5751
SUBJECT: FLIGHT CONTROLS - Flaps - Outboard Flap - Deflection Control Track -
Inspection/Replacement
CONCURRENT REQUIREMENTS
None.
BACKGROUND
The related 767-200, -300, and -300F service bulletin is 767-27-0184 for line numbers 1 through 921.
Accomplishment of this service bulletin will detect cracking of the outboard flap deflection control track. A fractured
deflection control track could result in the loss of an outboard flap in the event there is a loss of the primary flap
support.
The outboard flap deflection control track is located at the outboard end of the outboard flap. The track reduces
the deflection of the outboard flap and provides an alternate load path to retain the flap in the event there is a
loss of the primary flap support. Two operators have reported cracked or fractured deflection control tracks on
three airplanes with approximately 35,700 to 54,400 flight-hours and 6,550 to 14,100 flight-cycles. The cracks
all initiated in the aft lower lug run-out region. In one case the crack initiated at inclusions that is typical of the
slag products that are a result of the casting process. After a crack initiates it is propagated by fatigue until the
track fractures. The three cases of cracking all occurred on 767-300 airplanes. However the tracks on the
767-400ER airplane are similar in design and cracking could occur on these airplanes at the same location.
Inspection of the track will detect cracking before the track fractures. Installation of the new outboard flap
deflection control track assembly with thicker aft lug run-out will help prevent cracks and terminates the repeat
inspections.
Boeing Service Related Problem (SRP) 767-SRP-57-0154 and 767-SRP-57-0156 is related to this service
bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
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ReferenceAffectedPlanning Data
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedNoPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsYesKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION (PRR B12901-31S)
Extend the trailing edge flaps and deactivate. Do a High Frequency Eddy Current (HFEC) inspection of the aft
lower lug of the outboard flap deflection control track for cracks. If no cracks are found, repeat the inspections
at the interval shown in Figure 1. If cracks are found, replace the track assembly with a 113T8333-9 track
assembly and terminate the repeat inspections. Retract the flaps.
EFFECTIVITY
767-200, -300, and 400ER Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.
COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directive 2004-07-11 is related to this service bulletin.
See Figure 1 Logic Diagram of Inspection and Maintenance Alternatives.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection given in this service bulletin.
MANPOWER
Elapsed HoursTotal Task Hours
5.5017.00
MATERIAL INFORMATION
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 767-27A0183
SEE Q
WS
740  1000
TYPICAL CRACK
DO A HFEC INSPECTION OF THE AFT
LOWER LUG RUN-OUT AREA FOR CRACKS.
IF NO CRACKS ARE FOUND, REPEAT THE
INSPECTIONS. IF CRACKS ARE FOUND,
REPLACE THE TRACK ASSEMBLY WITH A
113T8333-9 TRACK ASSEMBLY AND
TERMINATE THE REPEAT INSPECTIONS
OUTBOARD FLAP DEFLECTION
FWD <  CONTROL TRACK ASSEMBLY
(LEFT WING SHOWN, RIGHT WING OPPOSITE)
V79743
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Commercial 
Airplanes
767
Service Bulletin
Number: 767-27A0183
Original Issue: May 09, 2002
Revision 2: September 25, 2014
ATA System: 2751 5751
SUBJECT: FLIGHT CONTROLS - Flaps - Outboard Flap - Deflection Control Track -
Inspection/Replacement
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index Document D6-24T001 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
This service bulletin is for the airplanes shown below. Refer to PRR-B 12901-31S (PART D) for
data about this change.
DESCRIPTIONCONFIGURATIONGROUP
767-400ER Airplanes line number 758 through 878.-1
767-200 and -300 airplanes 922 through 933-2
Airplane Models:
767-200, 767-300, 767-400ER
GroupVariable Number
1VQ001 - VQ021
1VQ071 - VQ086
2VR087
2VR106
2VS710 - VS712
2VS731 - VS732
2VS882 - VS883
2VS891
2VS896
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2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
The related 767-200, -300, and -300F service bulletin is 767-27-0184 for line numbers 1 through 921.
Accomplishment of this service bulletin will detect cracking of the outboard flap deflection control track.
A fractured deflection control track could result in the loss of an outboard flap in the event there is a
loss of the primary flap support.
The outboard flap deflection control track is located at the outboard end of the outboard flap. The track
reduces the deflection of the outboard flap and provides an alternate load path to retain the flap in the
event there is a loss of the primary flap support. Two operators have reported cracked or fractured
deflection control tracks on three airplanes with approximately 35,700 to 54,400 flight-hours and 6,550
to 14,100 flight-cycles. The cracks all initiated in the aft lower lug run-out region. In one case the crack
initiated at inclusions that is typical of the slag products that are a result of the casting process. After
a crack initiates it is propagated by fatigue until the track fractures. The three cases of cracking all
occurred on 767-300 airplanes. However the tracks on the 767-400ER airplane are similar in design
and cracking could occur on these airplanes at the same location.
Inspection of the track will detect cracking before the track fractures. Installation of the new outboard
flap deflection control track assembly with thicker aft lug run-out will help prevent cracks and terminates
the repeat inspections.
Boeing Service Related Problem (SRP) 767-SRP-57-0154 and 767-SRP-57-0156 is related to this
service bulletin.
Revision 1 is sent to:
1. This revision is sent to update the logic diagram in Figure 1 and add new outboard flap deflection
control track assembly with thicker aft lug run-out as terminating action to the repeat inspections.
After Installing the new outboard flap deflection control track assembly with thicker aft lug run-out,
it is not necessary to do the repeat inspections of the outboard flap deflection control track.
2. Add 767-200 and -300 Airplanes VR087, VR106, VS710, VS711, VS712, VS731, VS732, VS882,
VS883, VS891, and VS896 to the service bulletin. These airplanes were delivered with the same
flap installation as the 767-400ER airplanes and therefore should have been in this service bulletin.
3. The latest service bulletin format standards have also been updated where applicable.
4. Terminology has been changed in the Work Instructions to agree with the terminology defined in
Paragraph 3.A., General Information - Notes.
Revision 2 is sent to:
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1. Revise the compliance time for airplanes VR087, VR106, VS710, VS711, VS712, VS731, VS732,
VS882, VS883, VS891, and VS896 which were added to this service bulletin in Revision 1 to be
the same as the original airplanes in the service bulletin. The initial compliance time for these
airplanes was 1,200 flight cycles from Revision 1 date. One operator noted that the compliance
time for the original airplanes in the service bulletin was before the accumulation of 12,000 total
flight cycles, or within 1,200 flight cycles after the effective date of FAA AD 2004-07-11, whichever
occurs later, and believes that it should be the same as the airplanes added in Revision 1. We
agreed that the initial compliance time for the airplanes added in Revision 1 should be the same
as the original airplanes in the service bulletin. This results in the effectivity being split into two
groups to clarify the different compliance times for the airplanes in the Original Issue and the
airplanes added in Revision 1.
2. Clarify summary page illustration and work instructions to match changes in logic diagram made
in Revision 1.
3. Clarify the compliance time for Group 1 Airplanes in the logic diagram to add: whichever occurs
later. Add Effective date of AD 2004-07-11 to Compliance section.
D. Description
Extend the trailing edge flaps and deactivate. Do a High Frequency Eddy Current (HFEC) inspection
of the aft lower lug of the outboard flap deflection control track for cracks. If no cracks are found, repeat
the inspections at the interval shown in Figure 1. If cracks are found, replace the track assembly with
a 113T8333-9 track assembly and terminate the repeat inspections. Retract the flaps.
Revision 1:
1. No more work is necessary on airplanes changed as shown in the original issue of this service
bulletin. However, operators must continue to do the inspection detailed at the times given in
Paragraph 1.E., Compliance until new improved outboard flap deflection control track is installed.
After the installation of the new outboard flap deflection control track assembly with thicker aft lug
run-out, it is not necessary to do the repeat inspections of the outboard flap deflection control track
assembly.
2. Airplanes VR087, VR106, VS710, VS711, VS712, VS731, VS732, VS882, VS883, VS891, and
VS896 were added to this service bulletin effectivity. These airplanes should be inspected in
accordance with this service bulletin within 1,200 flight-cycles after the Revision 1 date of this
service bulletin. Continue to do the repeat inspection detailed at the times given in Paragraph 1.E.,
Compliance until new outboard flap deflection control track assembly with thicker aft lug run-out
is installed. After the installation of the new outboard flap deflection control track assembly with
thicker aft lug run-out, it is not necessary to do the repeat inspections of the outboard flap deflection
control track assembly.
Revision 2:
1. No more work is necessary on the airplanes changed or inspected in accordance with the Revision
1 of this service bulletin.
The work in this service bulletin is done in the maintenance zone(s) given below.
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Group 1:
Affected Maintenance Zones
ZoneModel
566, 666767-400ER
Group 2:
Affected Maintenance Zones
ZoneModel
566, 666767-200, 767-300
E. Compliance
See Figure 1 Logic Diagram of Inspection and Maintenance Alternatives.
Federal Aviation Administration (FAA) Airworthiness Directive 2004-07-11 is related to this service
bulletin.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2004-07-11 is related to this service
bulletin. The effective date of AD 2004-07-11 is May 11, 2004.
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
G. Manpower
The table below shows an estimate of the task-hours necessary to do this inspection for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task-hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
— Time to adjust to the workplace
— Time to schedule the work
— Time to examine the work
— Time to cure the materials
— Time to make the parts
— Time to find the tools.
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Elapsed HoursTask-HoursNumber of Per-
sons
Task
0.501.002Open Access
1.503.002Inspect
3.0012.004Replace
0.501.002Close Access
5.5017.00TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Engineering Change Memo PRR B12901-31S (PART D), PRR B12901-31S
b. Boeing Service Bulletin 767-27-0184
c. Boeing Service Related Problem (SRP) 767-SRP-57-0154, 767-SRP-57-0156
d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2004-07-11
e. 767 Aircraft Maintenance Manual (AMM) 27-51-00, 27-51-23
f. 767 Non-Destructive Testing (NDT) Manual Part 6, 57-50-01
g. 767-400 Aircraft Maintenance Manual (AMM) 27-51-00, 27-51-23
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Deflection Control and Aux. Track Installations, Outbd T.E. Flap113T1346
This drawing was used to prepare this service bulletin. This drawing is not necessary to make the
specified changes, and is not supplied with this service bulletin. This drawing may not be applicable
to all airplane configurations or operators.
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K. Publications Affected
1. Publications:
None.
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each
Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin
does not show the Boeing price and supply data.
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes inspection, and/or repair
procedures given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts:
None.
2. Parts and Materials Supplied by the Operator:
QTY column shows parts and materials required per airplane.
NotesNameQTYPart Number / Specifi-
cation
(a)TRACK ASSEMBLY2113T8333-9
(a) Install new outboard flap deflection control track assembly 113T8333-9 as Terminating Action
to the repeat inspections.
3. Parts Modified and Reidentified:
None.
4. Parts Removed and Not Replaced:
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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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. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
7. 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.
8. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
9. 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.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 09, 2002
767-27A0183Revision 2: September 25, 2014
19 of 23
BOEING SERVICE BULLETIN 767-27A0183

### Page 20

10. 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.
11. FIGURE 1 is a logic diagram of Inspection and Maintenance Alternatives.
B. WORK INSTRUCTIONS
1. Extend the trailing edge flaps to detent 20 or greater and deactivate. Refer to 767 AMM 27-51-00
or 767-400 AMM 27-51-00 as accepted procedures.
2. Do a High Frequency Eddy Current (HFEC) inspection of the outboard flap deflection control track,
113T8333-3 or -7, aft lower lug in accordance with FIGURE 2.
3. If no cracks are found, repeat the inspections at the interval in accordance with FIGURE 1. If cracks
are found, replace the track assembly with a 113T8333-9 track assembly and terminate the repeat
inspections. Refer to 767 AMM 27-51-23 or 767-400 AMM 27-51-23 as accepted procedures to
replace tracks.
4. Activate and retract the trailing edge flaps. Refer to 767 AMM 27-51-00 or 767-400 AMM 27-51-00
as accepted procedures.
5. Put the airplane back to a serviceable condition.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 09, 2002
767-27A0183Revision 2: September 25, 2014
20 of 23
BOEING SERVICE BULLETIN 767-27A0183

### Page 21 (OCR)

BOEING SERVICE BULLETIN 767-27A0183
GROUP 1 AIRPLANES:
BEFORE THE ACCUMULATION OF 12,000 TOTAL FLIGHT CYCLES, OR
WITHIN I,LOU FLIGHT CYCLES AFTER THE EFFECTIVE DATE OF FAA AD
2004-07-11, WHICHEVER OCCURS LATER.
GROUP 2 AIRPLANES:
BEFORE THE ACCUMULATION OF 12,000 TOTAL FLIGHT CYCLES, OR
WITHIN 1,200 FLIGHT CYCLES AFTER THE REVISION 1 DATE OF THIS
SERVICE BULLETIN, WHICHEVER OCCURS LATER.
DO A HFEC INSPECTION OF THE OUTBOARD FLAP
DEFLECTION CONTROL TRACK, 113T8333-3 OR -7,
AFT LOWER LUG.
NO CRACKS FOUND.  CRACKS FOUND.
WITHIN 1,200
FLIGHT-CYCLES.
REPLACE TRACK
ASSEMBLY.
TRACK ASSEMBLY
113T8333-9
TERMINATING  ACTION  V79739
FIGURE 1: LOGIC DIAGRAM OF INSPECTION AND MAINTENANCE ALTERNATIVES
(SHEET 1 OF 1)
Original Issue: May 09, 2002
Revision 2 September 25, 2014  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  767-27A0183
Work - See page 1 for details.  21 of 23

### Page 22 (OCR)

BOEING SERVICE BULLETIN 767-27A0183
SEE D
WS  WS
740  1000
TYPICAL CRACK
FWD
OUTBOARD FLAP DEFLECTION CONTROL TRACK
(LEFT WING SHOWN, RIGHT WING OPPOSITE)
V79741
FIGURE 2: OUTBOARD FLAP DETECTION CONTROL TRACK - AFT LOWER LUG INSPECTION
(SHEET 1 OF 2)
Original Issue: May 09, 2002
Revision 2 September 25, 2014  Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  767-27A0183
Work - See page 1 for details.  22 of 23

### Page 23

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
More DataQtyIdentificationNameTaskStep
Do a High Frequency Eddy
Current Inspection for cracks in
the aft lower lug run-out area in
accordance with 767 NDT Part
6, 57-50-01.
1113T8333-3 OR -7TRACK ASSEMBLYInspect1
FIGURE 2: OUTBOARD FLAP DETECTION CONTROL TRACK - AFT LOWER LUG INSPECTION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 09, 2002
767-27A0183Revision 2 September 25, 2014
23 of 23
BOEING SERVICE BULLETIN 767-27A0183

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