# Boeing Alert Service Bulletin 767-57A0060: U.S. DOT/FAA - Service Bulletin (SB-767-57-0060-01)

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- Document: [Boeing Alert Service Bulletin 767-57A0060](https://openairdocs.org/service-documents/boeing/767-57a0060.md)
- Title as filed: U.S. DOT/FAA - Service Bulletin (SB-767-57-0060-01)
- Pages: 47
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## Text

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### Page 1

Commercial
Airplane
Group
767
Service Bulletin
Number: 767-57A0060 Revision Transmittal SheetDate: January 30, 1997
Revision 1: December 31, 1998
ATA System: 5740 2781 2811
SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Slat Track Housing - Drain Tube Fuel
Leak Inspection and Rework
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
No more work is necessary on Group 1 airplanes inspected or reworked as shown in the initial release of this
service bulletin as a result of this revision. However, repeat inspections are required until terminating action
is accomplished.
More work is necessary on the Group 2 airplane VE066 reworked as shown in the Validation Copy 1 release
of this service bulletin. After the validation of this service bulletin was completed on VE066 additional
grounding requirements were added as given in the PART IV - ADDITIONAL WORK.
REASON FOR REVISION
This revision is sent to add terminating action to this service bulletin as follows:
1. Figures 3, 4, 5 and the PART - III TERMINATING ACTION are added to provide instructions to install a
new slat track housing drain tube assembly for Group 1 and 2 airplanes.
2. Figure 6 and PART IV - ADDITIONAL WORK are added to provide instructions to rework the slat track
housing drain tube assembly for the Group 2 airplane that incorporated PART III - TERMINATING
ACTION as specified in Validation Copy 1.
3. Manpower tables are added for installation of the new slat track housing drain tube assembly.
4. Kit and Material Availability information is added for the new slat track housing drain tube installation.
As part of a service bulletin validation program, this change was completed on airplane VE066 by Service
Bulletin 767-57A0060 Validation Copy 1 before the release of Revision 1 of this service bulletin. The change
completed on airplane VE066 by Service Bulletin 767-57A0060 Validation Copy 1 is equivalent to the release
of Revision 1 of this service bulletin except airplane VE066 requires more work as shown in PART IV -
ADDITIONAL WORK.
Paragraph 1.A., Effectivity, shows changes of airplane operators. Each operator should examine the
Effectivity paragraph for changes.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location
of important changes.
Pages with no vertical lines have no important changes.
REVISION HISTORY
Initial Release: January 30, 1997
Revision 1: December 31, 1998
767-57A0060
Revision Transmittal Page 1 of 1

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### Page 3

Commercial
Airplane
Group
767
Service Bulletin
Number: 767-57A0060 SummaryDate: January 30, 1997
Revision 1: December 31, 1998
ATA System: 5740 2781 2811
SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Slat Track Housing - Drain Tube Fuel
Leak Inspection and Rework
CONCURRENT REQUIREMENTS
None
BACKGROUND
This service bulletin gives instructions to inspect for
fuel leaks from the number 5 and 8 inboard slat
track housing drain locations near the engine
exhaust nozzles. Instructions are also given to
rework or replace the slat track housing drain tube
assembly as required. Fuel leaks from these drain
locations could result in a fire when the airplane is
standing still or in a low speed taxi.
Accomplishment of this service bulletin will ensure
the integrity of the drain tubes common to the slat
track housing and prevent possible fuel leaks near
an engine or exhaust nozzle when the airplane is on
the ground.
One operator reported a fuel leak from a slat track
housing drain tube where the drain tube penetrates
the lower wing skin. Further investigation revealed
the fuel leak originated from a loose drain tube
fitting. Six other operators have also reported fuel
leaks from the slat track housing drain tube where
the drain tube penetrates the lower wing skin.
Further investigation revealed the fuel leaks
originated from a crack in each of the drain tubes.
The slat track housing drain tubes provide a drain
path for moisture which can accumulate inside the
slat track housing. The drain tubes are located
inside the wing fuel tanks. Cracks in the drain tubes
or a loose fitting can result in fuel migration into the
drain tubes.
As part of a service bulletin validation program, this
change was completed on airplane VE066 by
Service Bulletin 767-57A0060 Validation Copy 1
before the release of Revision 1 of this service
bulletin. The change completed on airplane VE066
by Service Bulletin 767-57A0060 Validation Copy 1
is equivalent to the release of Revision 1 of this
service bulletin except airplane VE066 requires
more work as shown in PART IV - ADDITIONAL
WORK.
Boeing Service Related Problem (SRP)
767-SRP-57-0072 is related to this service bulletin.
ACTION (PRRB12900-133)
Inspect the exterior lower wing surface for fuel leaks
at the inboard slat track housing drain location of
each wing.
If an indication of a fuel leak is found:
1. Rework the drain tube per PART II - REWORK
and repeat the PART I - VISUAL INSPECTION
until the PART III - TERMINATING ACTION is
completed or,
2. Replace the drain tube per PART III -
TERMINATING ACTION.
Group 2 airplanes rework the drain tube per PART
IV - ADDITIONAL WORK.
EFFECTIVITY
All 767 airplanes line positions 1 through 671
divided in two groups.
COMPLIANCE
See Figure 1 for compliance recommendations and
maintenance alternatives. For the Group 2 airplane
Boeing recommends the PART IV - ADDITIONAL
WORK be completed within 5000 flight-cycles or 22
months, whichever is earlier from the release of
Revision 1 of this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are available for
airplanes in warranty as of May 6 1996. Please refer
to Paragraph 2.B., Industry Support Information.
767-57A0060
Summary Page 1 of 2

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BOEING SERVICE BULLETIN 767-57A0060
MANPOWER
See Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing Supplied Kits
Refer to Paragraph 2.A., Material - Price and
Availability.
OR REPLACE THE DRAIN TUBE IF REQUIRED.
DRAIN LOCATION OF EACH WING. REWORK
INSTALLATION
DRAIN TUBE
DO A VISUAL INSPECTION OF THE
LEFT WING SHOWN
RIGHT WING SIMILAR
SPAR
FRONT
AT THE INBOARD SLAT TRACK HOUSING
LOWER WING SURFACE FOR FUEL LEAKS
R93555
January 30, 1997 767-57A0060
Revision 1: December 31, 1998 Summary Page 2 of 2

### Page 5

Commercial
Airplane
Group
767
Service Bulletin
Number: 767-57A0060
Date: January 30, 1997
Revision 1: December 31, 1998
ATA System: 5740 2781 2811
SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Slat Track Housing - Drain Tube Fuel
Leak Inspection and Rework
THIS SERVICE 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
Refer to Service Bulletin Index Document D624T001, Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
This service bulletin is for the airplanes shown below. An equivalent change is on subsequent
production airplanes. Refer to PRRB12900-133 for data about this change.
IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER
ABX AIR (ABX)
1 VB101-VB105
AEROFLOT (ARO)
1 VN561-VN562
AEROMEXICO (AMX)
1 VF091 VF093 VN556
AIR ALGERIE (ALG)
1 VK131-VK133
AIR CANADA (ACN)
1 VA701-VA719 VB001-VB002 VB201-VB202 VN931-VN936
AIR CHINA (BEJ)
1 VE064-VE065 VE083-VE086 VK161-VK164
AIR EUROPA (ARE)
1 VB323 VB328 VN546-VN547
AIR EUROPE ITALY (EIY)
1 VL931-VL932 VN682 VN753 VN811-VN812 VN972
January 30, 1997 767-57A0060
Revision 1: December 31, 1998 Page 1 of 42

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BOEING SERVICE BULLETIN 767-57A0060
AIR FRANCE (AFA)
1 VN631-VN635
AIR MADAGASCAR (MAD)
1 VN376
AIR MAURITIUS (MAU)
1 VF001-VF002
AIR NAMIBIA (NAM)
1 VN385
AIR NEW ZEALAND (ANZ)
1 VB324 VE101-VE103 VN651-VN657 VN813
AIR PACIFIC (APC)
1 VN676
AIR SEYCHELLES (ASY)
1 VF051 VL941
AIR ZIMBABWE (ZMB)
1 VF061-VF062
AIRTOURS INT'L AIRWAYS (GUE)
1 VN951-VN953
ALITALIA (ALI)
1 VN422-VN427
ALL NIPPON AIRWAYS (ANA)
1 VB106-VB125 VK081-VK113 VN191-VN198
AMERICAN AIRLINES (AAL)
1 VA501-VA530 VN001-VN041
ANSETT AUSTRALIA (ANS)
1 VB051-VB055 VB321-VB322 VB325 VE118 VL755
ASIANA AIRLINES (AAR)
1 VK141-VK148 VL703 VN751 VW851
AVIANCA (AVI)
1 VE171-VE172 VF092 VN152
BIRGENAIR (BIR)
1 VE041
BRITANNIA AIRWAYS (BRI)
1 VB326-VB327 VB329-VB332 VL911-VL914 VN731
BRITISH AIRWAYS (BAB)
1 VN111-VN127 VN130-VN137
CANADIAN AIRLINES (CDI)
1 VN051-VN054 VN057-VN062 VN752
January 30, 1997 767-57A0060
Revision 1: December 31, 1998 2

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BOEING SERVICE BULLETIN 767-57A0060
CHINA SOUTHERN AIRLINES (GUN)
1 VL701-VL702
CHINA YUNNAN AIRLINES (YUN)
1 VL871-VL873
CITY BIRD (CBD)
1 VN436
CONDOR (CDF)
1 VN683-VN691
DELTA AIR LINES (DAL)
1 VA301-VA315 VK031-VK056 VL753 VN251-VN273 VN301-VN306
EGYPTAIR (EGP)
1 VN211-VN212
EL AL ISRAEL AIRLINES (ELA)
1 VB281-VB284 VF101-VF102
ETHIOPIAN AIRLINES (ETH)
1 VE001-VE002 VN371
EVA AIR (EVA)
1 VB441-VB444 VN471-VN472 VN791-VN792
GULF AIR (GUL)
1 VL003-VL006 VN307-VN310 VN313-VN314
H.M.S.F. AND AMEDEO CORP. (BWN)
1 VF180
ITOCHU CORPORATION (CIT)
1 VF181-VF184
JAPAN AIRLINES (JAL)
1 VB371-VB373 VK001-VK015 VK021-VK022 VK181
K.B.A. FOUNDATION (KBA)
1 VN312
KALAIR USA CORP (KLA)
1 VN311
KLM - ROYAL DUTCH AIRLINES (KLM)
1 VL891-VL900
LAM (LAM)
1 VF162
LANCHILE AIRLINES (LAN)
1 VN063-VN064 VN531 VN557 VN966-VN969 VN971
LAUDA AIR (LAL)
1 VN242-VN243 VN388
January 30, 1997 767-57A0060
Revision 1: December 31, 1998 3

### Page 8

BOEING SERVICE BULLETIN 767-57A0060
LAUDA AIR S.P.A. (LDI)
1 VL011 VN671
LEISURE INTERNATIONAL AIRWAYS (UKL)
1 VN921-VN922
LOT POLISH AIRLINES (LOT)
1 VF041-VF042 VN291-VN293
LTU (LTU)
1 VN171-VN174 VN381
MALEV HUNGARIAN AIRLINES (HGA)
1 VF171-VF172
MARTINAIR HOLLAND (MTH)
1 VN221-VN225 VN672
MID EAST JET (SKL)
1 VF251
MIDAIR (MAI)
1 VE021
QANTAS (QAN)
1 VE061-VE063 VE067-VE069 VN081-VN099
2 VE066
ROYAL BRUNEI AIRLINES (RBA)
1 VN372 VN382-VN384 VN386-VN387 VN637-VN638
SAS (SAS)
1 VF071 VN151 VN153-VN158 VN163-VN168 VN536 VN551
SHANGHAI AIRLINES (SHA)
1 VK171
SOBELAIR (SBL)
1 VN421 VN636
SOUTH AFRICAN AIRWAYS (SAA)
1 VE022-VE023
SPANAIR (SPP)
1 VN541-VN542
TACA INTERNATIONAL AIRLINES (TAC)
1 VE116 VN732
THE BOEING COMPANY (TBC)
1 VA001
TRANSBRASIL (TBL)
1 VB251-VB253 VE104 VE117 VF072 VF161 VL001-VL002
VN532
TWA (TWA)
1 VA801-VA810 VB301-VB302 VN681
January 30, 1997 767-57A0060
Revision 1: December 31, 1998 4

### Page 9

BOEING SERVICE BULLETIN 767-57A0060
UNITED AIRLINES (UAL)
1 VA002-VA020 VN491-VN513
UPS (UPS)
1 VW701-VW718
US AIRWAYS (USA)
1 VE141-VE152
UZBEKISTAN AIRWAYS (UZB)
1 VL806-VL807
VARIG AIRLINES (VAR)
1 VE121-VE126 VN055-VN056 VN231-VN234
VIETNAM AIRLINES (VIE)
1 VL751-VL752 VL754
WHIRLPOOL FINANCIAL CORP. (ZZW)
1 VN537
IDENTIFICATION BY VARIABLE NUMBER
GROUP 1
VA001-VA020 VA301-VA315 VA501-VA530 VA701-VA719 VA801-VA810 VB001-VB002
VB051-VB055 VB101-VB125 VB201-VB202 VB251-VB253 VB281-VB284 VB301-VB302
VB321-VB332 VB371-VB373 VB401 VB441-VB444 VE001-VE003 VE021-VE023
VE041-VE043 VE061-VE065 VE067-VE069 VE083-VE086 VE101-VE104 VE116-VE118
VE121-VE126 VE141-VE152 VE171-VE172 VF001-VF002 VF041-VF042 VF051
VF061-VF062 VF071-VF072 VF091-VF093 VF101-VF102 VF161-VF162 VF171-VF172
VF180-VF184 VF251 VK001-VK015 VK021-VK022 VK031-VK056 VK081-VK113
VK131-VK133 VK141-VK148 VK161-VK164 VK171 VK181 VL001-VL006
VL011 VL701-VL703 VL751-VL755 VL806-VL807 VL871-VL873 VL891-VL900
VL911-VL914 VL931-VL932 VL941 VN001-VN041 VN051-VN064 VN081-VN099
VN111-VN127 VN130-VN137 VN151-VN158 VN163-VN168 VN171-VN174 VN191-VN198
VN211-VN212 VN221-VN225 VN231-VN234 VN241-VN243 VN251-VN273 VN291-VN293
VN301-VN314 VN371-VN372 VN376 VN381-VN388 VN421-VN427 VN436
VN471-VN472 VN491-VN513 VN531-VN532 VN536-VN537 VN541-VN542 VN546-VN547
VN551 VN556-VN557 VN561-VN562 VN631-VN638 VN651-VN657 VN671-VN672
VN676 VN681-VN691 VN731-VN732 VN751-VN753 VN791-VN792 VN811-VN813
VN921-VN922 VN931-VN936 VN951-VN953 VN966-VN969 VN971-VN972 VW701-VW718
VW851
GROUP 2
VE066
2. Spares Affected
None
January 30, 1997 767-57A0060
Revision 1: December 31, 1998 5

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BOEING SERVICE BULLETIN 767-57A0060
B. Concurrent Requirements
None
C. Reason
This service bulletin gives instructions to inspect for fuel leaks from the number 5 and 8 inboard slat
track housing drain locations near the engine exhaust nozzles. Instructions are also given to rework
or replace the slat track housing drain tube assembly as required. Fuel leaks from these drain
locations could result in a fire when the airplane is standing still or in a low speed taxi.
Accomplishment of this service bulletin will ensure the integrity of the drain tubes common to the slat
track housing and prevent possible fuel leaks near an engine or exhaust nozzle when the airplane is
on the ground.
One operator reported a fuel leak from a slat track housing drain tube where the drain tube
penetrates the lower wing skin. Further investigation revealed the fuel leak originated from a loose
drain tube fitting. Six other operators have also reported fuel leaks from the slat track housing drain
tube where the drain tube penetrates the lower wing skin. Further investigation revealed the fuel
leaks originated from a crack in each of the drain tubes.
The slat track housing drain tubes provide a drain path for moisture which can accumulate inside the
slat track housing. The drain tubes are located inside the wing fuel tanks. Cracks in the drain tubes or
a loose fitting can result in fuel migration into the drain tubes.
Boeing Service Related Problem (SRP) 767-SRP-57-0072 is related to this service bulletin.
As part of a service bulletin validation program, this change was completed on airplane VE066 by
Service Bulletin 767-57A0060 Validation Copy 1 before the release of Revision 1 of this service
bulletin. The change completed on airplane VE066 by Service Bulletin 767-57A0060 Validation Copy
1 is equivalent to the release of Revision 1 of this service bulletin except airplane VE066 requires
more work as shown in PART IV - ADDITIONAL WORK.
Revision 1 is sent to add terminating action to this service bulletin as follows:
1. Figures 3, 4, 5 and the PART - III TERMINATING ACTION are added to provide instructions to
install a new slat track housing drain tube assembly for Group 1 and 2 airplanes.
2. Figure 6 and PART IV - ADDITIONAL WORK are added to provide instructions to rework the slat
track housing drain tube assembly for the Group 2 airplane that incorporated PART III -
TERMINATING ACTION as specified in Validation Copy 1.
3. Manpower tables are added for installation of the new slat track housing drain tube assembly.
4. Kit and Material Availability information is added for the new slat track housing drain tube
installation.
D. Description
Inspect the exterior lower wing surface for fuel leaks at the inboard slat track housing drain location of
each wing.
If an indication of a fuel leak is found:
1. Rework the drain tube per PART II - REWORK and repeat the PART I - VISUAL INSPECTION
until the PART III - TERMINATING ACTION is completed or,
2. Replace the drain tube per PART III - TERMINATING ACTION.
January 30, 1997 767-57A0060
Revision 1: December 31, 1998 6

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BOEING SERVICE BULLETIN 767-57A0060
Group 2 airplanes rework the drain tube per PART IV - ADDITIONAL WORK.
No more work is necessary on Group 1 airplanes inspected or reworked as shown in the initial
release of this service bulletin as a result of this revision. However, repeat inspections are required
until terminating action is accomplished.
More work is necessary on the Group 2 airplane VE066 reworked as shown in the Validation Copy 1
release of this service bulletin. After the validation of this service bulletin was completed on VE066
additional grounding requirements were added as given in the PART IV - ADDITIONAL WORK.
The airplane effectivity is divided into two groups. Group 1 consists of airplanes that have not had
terminating action incorporated prior to release of Revision 1 of this service bulletin. Group 2 consist
of the airplane that had terminating action incorporated as specified in Validation Copy 1 of this
service bulletin.
An evaluation form is attached to this service bulletin. Please use this form to tell us what you think
of the quality of this service bulletin.
NOTE: Inspection, rework and maintenance alternatives are shown in a diagram in Section 3.,
ACCOMPLISHMENT INSTRUCTIONS.
E. Compliance
See Figure 1 for compliance recommendations and maintenance alternatives. For the Group 2
airplane Boeing recommends the PART IV - ADDITIONAL WORK be completed within 5000
flight-cycles or 22 months, whichever is earlier from the release of Revision 1 of this service bulletin.
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes
specified in this service bulletin comply with the applicable Federal Aviation Regulations (FAR) and
are FAA approved. This service bulletin and the FAA approval were based on the airplane in its
original Boeing delivery configuration or as modified by other FAA 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
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
man-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.
PART I - VISUAL INSPECTION
Approximately 0.25 man-hours and 1 person is necessary to do the inspection for each wing.
January 30, 1997 767-57A0060
Revision 1: December 31, 1998 7

### Page 12

BOEING SERVICE BULLETIN 767-57A0060
PART II - REWORK
Approximately 10.0 man-hours and 2 persons are necessary to do the rework for each wing.
PART III - TERMINATING ACTION
Task Number of Persons Man-Hours Elapsed Time (Hours)
Open Access 2 6 3
Remove Drain
Tube Assy
2 4 2
Install Drain
Tube Assy
2 6 3
Close Access 2 4 2
TOTAL FOR EACH WING 20 10
TOTAL FOR EACH AIRPLANE 40 20
PART IV - ADDITIONAL WORK
Task Number of Persons Man-Hours Elapsed Time (Hours)
Open Access 2 6 3
Rework Drain
Tube Assy
2 4 2
Close Access 2 4 2
TOTAL FOR EACH WING 14 7
TOTAL FOR EACH AIRPLANE 28 14
H. Weight and Balance Changes
Change in Weight Change in Moment
+ 1.7 lbs + 1547 lb-in
I. Electrical Load Data
Not changed
January 30, 1997 767-57A0060
Revision 1: December 31, 1998 8

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BOEING SERVICE BULLETIN 767-57A0060
J. References
1. Existing Data:
a. Engineering Change Memo PRRB12900-133
b. Service Related Problem (SRP) 767-SRP-57-0072
c. 767 Maintenance Manual (AMM) Subjects 12-11-01, 28-11-00 and 28-26-00
d. Boeing Standard Wiring Practices Manual (BSWPM) 20-20-00
e. Boeing Standard Overhaul Practices Manual (BSOPM) 20-11-03, 20-41-02, 20-43-03,
20-50-02, 20-50-11 and 20-50-19
f. 767 Maintenance Planning Document (MPD) 12-21-08 and 57-50-00-A
g. Boeing Service Letter 767-SL-57-024
2. Data supplied with this service bulletin:
None
3. Installation Drawings Used in the Preparation of this Service Bulletin:
Drawing Number Title
112T2000 Front Spar Installation
112T2019 Drain Tube Installation
112T5090 Rib Installation
These drawings were used to prepare this service bulletin. These drawings are not necessary to
make the specified changes or do the specified inspections, and are not supplied with this service
bulletin. These drawings may not be applicable to all airplane configurations or operators.
K. Publications Changed
Publication Chapter-Section
767 Maintenance Manual 12-21, 28-11
767 Illustrated Parts Catalog 57-40
L. Interchangeability and Intermixability of Parts
Refer to Paragraph 2.E., Existing Parts Accountability, for interchangeability and intermixability
information.
January 30, 1997 767-57A0060
Revision 1: December 31, 1998 9

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BOEING SERVICE BULLETIN 767-57A0060
BLANK PAGE
January 30, 1997 767-57A0060
Revision 1: December 31, 1998 10

### Page 15

BOEING SERVICE BULLETIN 767-57A0060
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 in the quantity of kits, a supply sequence is given by Spares.
Kit Number Name Date Quantity
ROLT Unit Price thru
(weeks) June 1/99
015T1559-1 (a) Top Kit No Longer Available - -
015T1559-2 Top Kit Feb 25/99 178 52 5,236.00
015T1559-3 (b) Kit - Supplemental Feb 25/99 1 - 330.00
(a) Replaced by top kit 015T1559-2.
(b) Supplements top kit 015T1559-1 and is only necessary for the Group 2 airplane.
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.
Send purchase orders and letters about the supply data to the Director of Spares and refer to this
service bulletin number.
B. Industry Support Information
Boeing warranty remedies are available for 767 airplanes in warranty as of May 6, 1996. For
man-hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing
Product Assurance Contracts. The kits for airplanes in warranty as of that date will be supplied at no
charge. Send a purchase order for the kits to Boeing Spares. Please refer to this service bulletin
number and reference the airplane variable number(s) in your purchase order.
C. Parts Necessary For Each Airplane
1. Kits:
To get the kits shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the
Operator, are necessary for each airplane.
015T1559 TOP KIT - SLAT TRACK CAN DRAIN TUBE.
-4 -3 -2 -1
Quantity Part Number Name
. . . - 015T1559-1 (a) Top Kit
. . - . 015T1559-2 Top Kit
. - . . 015T1559-3 (b) Kit, Supplemental
- 2 . . 015T1559-4 Sub Kit
. . . 1 112T2031-1 Kit Assy
. . 1 . 112T2031-15 Kit Assy
. . 1 . 112T2031-16 Kit Assy
January 30, 1997 767-57A0060
Revision 1: December 31, 1998 11

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BOEING SERVICE BULLETIN 767-57A0060
(Continued)
015T1559 TOP KIT - SLAT TRACK CAN DRAIN TUBE.
-4 -3 -2 -1
Quantity Part Number Name
. . . 1 112T2031-2 Kit Assy
1 . . . 287T0020-325 Wire Support Assy
12 . . . BACB30FP6A4 Bolt
12 . . . BACC30M6 Collar
1 . . . BACJ40AC44-6 Jumper
1 . . . BACJ40AC44-8 Jumper
1 . . . BACJ40A20-8 Jumper
4 . . . BACN10YR3CD Nut
4 . . . BACR15FT6AD6 Rivet
3 . . . BACS12GU3K6 Screw
1 . . . AN735C8 Clamp
1 . . . AN735DC56 Clamp
1 . . . AN735DC8 Clamp
20 . . . NAS1149D0316H Washer
12 . . . NAS1149D0363H Washer
(a) No longer available, replaced by top kit 015T1559-2
(b) Supplements top kit 015T1559-1 and is only necessary for the Group 2 airplane.
112T2031 KIT - SLAT TRACK CAN DRAIN TUBE OFSS 428.683 - WING.
-1 -2 -16 -15
Quantity Part Number Name
. . . - 112T2031-15 Subkit, Kit Assy
. . - . 112T2031-16 Subkit, Kit Assy
. - . . 112T2031-2 Subkit, Kit Assy
- . . . 112T2031-1 Subkit, Kit Assy
1 . . 1 112T2031-3 Drain Tube Assy
1 1 . 112T2031-4 Drain Tube Assy
. . 2 2 112T2031-17 Doubler
1 1 1 1 112T5093-1 Doubler Assy
. . 1 1 287T0020-325 Bracket Assy
1 1 1 1 112T5093-3 Doubler
1 1 1 1 AN735C8 Clamp, Bonding
. . 1 1 AN735DC56 Clamp, Bonding
1 1 1 1 AN735DC8 Clamp, Bonding
12 12 . . BACB30VT6K4 Bolt
12 12 . . BACC30BP6 Collar
January 30, 1997 767-57A0060
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BOEING SERVICE BULLETIN 767-57A0060
(Continued)
112T2031 KIT - SLAT TRACK CAN DRAIN TUBE OFSS 428.683 - WING.
-1 -2 -16 -15
Quantity Part Number Name
. . 1 1 BACJ40AC44-6 Jumper
. . 1 1 BACJ40AC44-8 Jumper
1 1 . . BACJ40A20-6 Jumper Assy
. . 1 1 BACJ40A20-8 Jumper
2 2 4 4 BACN10YR3CD Nut
2 2 2 2 BACR15FR6E5 Rivet
. . 4 4 BACR15FT6AD6 Rivet
. . 16 16 BACR15FT6AD7 Rivet
. . 12 12 BACR15FT6AD9 Rivet
2 2 3 3 BACS12GU3K6 Screw
3 3 3 3 MS20995AB Lockwire
4 4 4 4 MS29513-114 O-Ring
. . 12 12 NAS1149D0363H Washer
. . 20 20 NAS1149D0316H Washer
6 6 . . NAS1149D0316J Washer
2 2 . . NAS1149D0363J Washer
1 1 1 1 200-030-0001-501 Drain Tube
1 1 1 1 305B387S8 Coupling Assy
1 1 1 1 355B387S8 Coupling Assy
1 1 1 1 6310-8 Cap, Drain
2. Material Supplied by the Operator:
Quantity Material Required Name
8 ounces BMS 3-24 (a) Grease
8 ounces BMS 5-26 Type II - Class B (a) Sealant (Optional to BMS 5-45)
8 ounces BMS 5-45 (a) Sealant
8 ounces BMS 5-95 - Class C (a) Sealant
8 ounces BMS 10-20 Type II (a) Primer
8 ounces BMS 11-7 (a) Solvent, Methyl Ethyl Ketone (MEK) or
Optional, Methyl Propyl Ketone (MPK)
(a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier
data.
D. Parts Necessary to Change Spares
None
January 30, 1997 767-57A0060
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BOEING SERVICE BULLETIN 767-57A0060
E. Existing Parts Accountability
The parts shown below are changed as shown in this service bulletin. Quantity (QTY) is the number
of parts changed on each airplane.
Existing Part Number RUC Name QTY New Part Number PNC RC
112T2001-( ) RWK Drain Tube 2 - N A
355B387S8 DIS Coupling Nut 2 - - B
RUC Recommended Use Code
DIS - Discard the part.
- Keep the part if there are other uses for it.
RWK - Make the change given in this service bulletin.
PNC Part Number Code
N - There is no equivalent Boeing part number for the changed part. Identify on the part
that the change given in this service bulletin was made.
RC Replacement Code
A - Do not use the existing part to replace the new or changed part.
B - This part is removed from the airplane. This part has no replacement.
F. Special Tooling - Price and Availability
None
G. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the inspection or 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.
January 30, 1997 767-57A0060
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BOEING SERVICE BULLETIN 767-57A0060
3. ACCOMPLISHMENT INSTRUCTIONS
GENERAL NOTES
1. The paragraphs identified with a letter give the general work instructions. The instructions
identified with numbers on the figures give the recommended sequence of steps.
2. Unless shown differently, these dimensions and tolerances are used:
- Linear dimensions are in inches
- Tolerance on linear dimensions is plus or minus 0.03 inch
- Angular tolerance is plus or minus 2 degrees
- Torque limits to tighten nuts and bolts are given in 767 Structural Repair Manual Chapter 51.
3. Obey all of the warnings and cautions given in the specified manual sections.
4. See Figure 1 for compliance recommendations and maintenance alternatives.
5. As an alternative to the Boeing specified manuals, operators equivalent procedures can be used.
WORK INSTRUCTIONS
THE ACCOMPLISHMENT INSTRUCTIONS ARE DIVIDED INTO THESE PARTS:
Group 1 and 2 Airplanes
PART I - VISUAL INSPECTION
Required on both exterior lower wing surfaces, common to the inboard slat track housing
drain tube penetration until PART III - TERMINATING ACTION is completed.
PART II - REWORK
Required if a leak is found during the per PART I - VISUAL INSPECTION and the PART III -
TERMINATING ACTION is not desired.
PART III - TERMINATING ACTION
Required if terminating action of the PART I - VISUAL INSPECTION is desired. See Figure
1 for details of compliance recommendations and maintenance alternatives.
Group 2 Airplane
PART IV - ADDITIONAL WORK
More work is necessary on the Group 2 airplane, reworked as shown in the Validation Copy
1 release of this service bulletin. After the validation of this service bulletin was completed,
additional grounding requirements were added. Boeing recommends the PART IV -
ADDITIONAL WORK be completed within 5000 flight-cycles or 22 months, whichever is
earlier from the release of Revision 1 of this service bulletin
PART I - VISUAL INSPECTION
A. Perform a visual inspection for fuel leaks or evidence of a fuel leak per Figure 2.
NOTE: A minimum of 4400 gallons of fuel is required in each wing tank to adequately check for
leaks common to the drain tube.
B. If a fuel leak is not found, and terminating action is not desired, repeat the visual inspections at the
intervals shown in Figure 1.
January 30, 1997 767-57A0060
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BOEING SERVICE BULLETIN 767-57A0060
C. If a fuel leak is found and terminating action is not desired, rework the drain tube per PART II -
REWORK and repeat the visual inspections at the intervals shown in Figure 1.
PART II - REWORK
A. If an indication of a fuel leak is found and terminating action is not desired repair the drain tube as
specified in 767 AMM 28-11-00.
B. Continue the PART I - VISUAL INSPECTION at the intervals shown in Figure 1, until terminating
action is completed per PART III - TERMINATING ACTION.
C. Restore the airplane to a serviceable condition.
PART III - TERMINATING ACTION
If terminating action of the PART I - VISUAL INSPECTION is desired complete the following:
A. Defuel the main tanks as specified in 767 AMM 28-26-00.
B. Open the main tank access and dry bay access panels listed below as specified in 767 AMM
28-11-00, to access the number 5 and 8 inboard slat track housing drains.
PANEL # LOCATION
533AB LEFT WING DRY BAY
633AB RIGHT WING DRY BAY
532FB LEFT WING MAIN TANK
632FB RIGHT WING MAIN TANK
C. Remove the number 5 and 8 inboard slat track drain tube assemblies as shown in Figure 3.
D. Group 1 airplanes, install the new number 5 and 8 inboard slat track drain tube assemblies as
shown in Figure 4.
E. Group 2 airplane, install the new number 5 and 8 inboard slat track drain tube assemblies as
shown in Figure 5.
F. Make sure the number 5 and 8 inboard slat track housing drain tube assemblies are free and clear
of debree.
G. Close the main tank access panels listed below as specified in 767 AMM 28-11-00.
PANEL # LOCATION
532FB LEFT WING MAIN TANK
632FB RIGHT WING MAIN TANK
H. Refuel the main tanks as specified in 767 AMM 12-11-01.
I. Perform a visual inspection of the number 5 and 8 inboard slat track drain tube opening, located in
the dry bay to make sure there are no fuel leaks.
January 30, 1997 767-57A0060
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BOEING SERVICE BULLETIN 767-57A0060
J. Close the dry bay access panels listed below as specified in 767 AMM 28-11-00.
PANEL # LOCATION
533AB LEFT WING DRY BAY
633AB RIGHT WING DRY BAY
K. Restore the airplane to a servicable condition.
PART IV - ADDITIONAL WORK
A. Defuel the main tanks as specified in 767 AMM 28-26-00.
B. Open the main tank access and dry bay access panels listed below as specified in 767 AMM
28-11-00, to access the number 5 and 8 inboard slat track housing drains.
PANEL # LOCATION
533AB LEFT WING DRY BAY
633AB RIGHT WING DRY BAY
532FB LEFT WING MAIN TANK
632FB RIGHT WING MAIN TANK
C. Rework the number 5 and 8 inboard slat track drain tube assemblies as shown in Figure 6.
D. Make sure the number 5 and 8 inboard slat track housing drain tube assemblies are free and clear
of debree.
E. Close the main tank access panels listed below as specified in 767 AMM 28-11-00.
PANEL # LOCATION
532FB LEFT WING MAIN TANK
632FB RIGHT WING MAIN TANK
F. Refuel the main tanks as specified in 767 AMM 12-11-01.
G. Perform a visual inspection of the number 5 and 8 inboard slat track drain tube opening, located in
the dry bay to make sure there are no fuel leaks.
H. Close the dry bay access panels listed below as specified in 767 AMM 28-11-00.
PANEL # LOCATION
533AB LEFT WING DRY BAY
633AB RIGHT WING DRY BAY
I. Restore the airplane to a servicable condition.
January 30, 1997 767-57A0060
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BOEING SERVICE BULLETIN 767-57A0060
FIGURE TABLE OF CONTENTS
Title Page
FIGURE 1. GROUP 1 - LOGIC DIAGRAM FOR INSPECTION AND
MAINTENANCE ALTERNATIVES .............................. 1 9
FIGURE 2. VISUAL INSPECTION. . ...................................... 2 1
FIGURE 3. INBOARD SLAT TRACK DRAIN TUBE REMOVAL . . . .............. 2 3
FIGURE 4. GROUP 1 - INBOARD SLAT TRACK DRAIN TUBE
INSTALLATION ............................................ 2 6
FIGURE 5. GROUP 2 - INBOARD SLAT TRACK DRAIN TUBE
INSTALLATION ............................................ 3 2
FIGURE 6. GROUP 2 - INBOARD SLAT TRACK DRAIN TUBE ADDITIONAL
WORK. . .................................................. 3 8
January 30, 1997 767-57A0060
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BOEING SERVICE BULLETIN 767-57A0060
THE INITIAL RELEASE OF THIS SERVICE BULLETIN.
DO THE FOLLOWING WITHIN 500 FLIGHT−HOURS FROM
DO PART III − TERMINATING ACTION.
FLIGHT−HOURS.
INSPECTION WITHIN 500
PART II − REWORK.
DRAIN TUBE AS SHOWN IN
FLIGHT−HOURS.
INSPECTION WITHIN 500
REPEAT THE PAR T I − VISUAL
REPEAT THE PAR T I − VISUAL
FUEL LEAK FOUND.
REWORK THE SLAT TRACK HOUSING
NO FUEL LEAK FOUND.
SLAT TRACK HOUSING DRAIN TUBE PENETRATIONS.
DO PART I − VISUAL INSPECTION OF BOTH EXTERIOR LOWER
WING SURFACE AREAS FOR A FUEL LEAK FROM THE INBOARD
21
R93564
FIGURE 1. GROU P 1 - LOGIC DIAGRAM FOR INSPECTION AND MAINTENANCE ALTERNATIVES
January 30, 1997 SHEET 1 OF 2 767-57A0060
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BOEING SERVICE BULLETIN 767-57A0060
The flag note numbers shown below agree with the number shown in the flag symbols in the figure.
FLAG
NOTE NOTES
1 If the inspection per Boeing Service Letter 767-SL-57-024, dated March 7, 1995 or later, has
been accomplished then the initial inspection is not required. Repeat inspection per PART I -
VISUAL INSPECTION is required, within 500 flight-hours after completion of inspections per
Boeing Service Letter 767-SL-57-024.
2 If operators are in compliance with the Boeing Transit Check Inspection recommendations per
Boeing 767 MPD 57-50-00-A, the initial inspection and repeat inspections listed in this service
bulletin are not required.
FIGURE 1. GROU P 1 - LOGIC DIAGRAM FOR INSPECTION AND MAINTENANCE ALTERNATIVES
January 30, 1997 SHEET 2 OF 2 767-57A0060
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BOEING SERVICE BULLETIN 767-57A0060
1
RIGHT WING SIMILAR
LEFT WING SHOWN
INSTALLATION
DRAIN TUBE
SPAR
FRONT
R93556
FIGURE 2. VISUAL INSPECTION
January 30, 1997 SHEET 1 OF 2 767-57A0060
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BOEING SERVICE BULLETIN 767-57A0060
The step number shown below agree with the number shown in the circle symbol in the figure.
STEP TASK LOCATION PROCEDURE NOTES
1 Inspect Exterior lower wing
panel at the most
inboard drain location
767 AMM 28-11-00
or 767 MPD Section
5, Number 12-21-08
visually for a fuel leak or evidence
of a fuel leak. Refer to 767 AMM
28-11-00 for fuel leak limits.
FIGURE 2. VISUAL INSPECTION
January 30, 1997 SHEET 2 OF 2 767-57A0060
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BOEING SERVICE BULLETIN 767-57A0060
RIB NO. 9
SKIN
LOWER WING
0.40 + 0.06
HOUSING
SLAT TRACK
FRONT SPAR
ASEE
BSEE
A
1 3
2
FWD INBD
UP
S26953
FIGURE 3. INBOARD SLAT TRACK DRAIN TUBE REMOVAL
January 30, 1997 SHEET 1 OF 3 767-57A0060
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BOEING SERVICE BULLETIN 767-57A0060
B
6
4CAP
4LOCKWIRE
O−RING4
SKIN SURFACE
WING LOWER
5
FWD INBD
UP
S27033
FIGURE 3. INBOARD SLAT TRACK DRAIN TUBE REMOVAL
January 30, 1997 SHEET 2 OF 3 767-57A0060
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BOEING SERVICE BULLETIN 767-57A0060
The step number shown below agree with the number shown in the circle symbol in the figure.
The QTY numbers shown below are the number of parts necessary for one side of the airplane.
STEP TASK NAME PART NUMBER QTY NOTES
1 Cut Drain Tube 112T2001-( ) 1 from the slat track housing as indicated.
Maintain a finish of 125 AA or better with
no burrs.
2 Remove /
Discard
Cut Drain Tube
and Jumper Assy
112T2001-( ) 1 by disconnecting the half coupling
assembly common to the wing skin.
Coupling Nut 355B387S8 1
3 Apply Alodine 600 - to refinish the cut end of the drain tube
common to the slat track housing. Refer
to BSOPM 20-43-03 and 20-41-02Primer BMS 10-20, TYPEII -
4 Install O-Ring MS29513-114 1 by lightly applying a layer of BMS 3-24 to
the coupling components prior to
assembly. Assemble and lockwire
coupling cap assembly. Refer to
BSOPM 20-50-02.
Cap 6310-8 1
Lockwire MS20995AB -
5 Apply Injection Seal BMS 5-26 Type II -
Class B
- to fill the drain exit cavity and make flush
common to the exterior lower wing panel.
Refer to BSOPM 20-50-19 and 20-50-11.
6 Apply Fillet Seal BMS 5-26 Type II -
Class B
- around the coupling cap assembly.
Refer to BSOPM 20-50-19.
FIGURE 3. INBOARD SLAT TRACK DRAIN TUBE REMOVAL
January 30, 1997 SHEET 3 OF 3 767-57A0060
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BOEING SERVICE BULLETIN 767-57A0060
ASEE
RIB NO. 9
A
DSEE
WING LOWER
SKIN
HOUSING
SLAT TRACK
FRONT SPAR
ESEE
BSEE
FWD INBD
UP
S26912
FIGURE 4. GROU P 1 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION
January 30, 1997 SHEET 1 OF 6 767-57A0060
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BOEING SERVICE BULLETIN 767-57A0060
C
6
6
4
TUBE
DRAIN
FLEX
HOSE
O−RING
RETAINING RING
B
SEE C
C6 F
951
D17
C
7
7
C6 F
8
16
14
4
4
63
2
FWD
UP
A−A
JUMPER (c)
BONDING
FWD
(4 LOCATIONS)
DOUBLER
BRACKET
A
A
FWD INBD
UP
3.21
+/−0.10
4.20
+/−0.10
S27116
FIGURE 4. GROU P 1 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION
January 30, 1997 SHEET 2 OF 6 767-57A0060
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BOEING SERVICE BULLETIN 767-57A0060
B
WASHER (a)
JUMPER (a)
BONDING
WASHER (b)
WASHER (c)
NUT
WASHER (a)
RETAINING
RING
17 BONDING
CLAMP (c)
D
CLAMP (a)
BONDING
17
RETAINER
HALF
COUPLING
BODY
COUPLING
NUT 15
E
JUMPER (a)
BONDING
B
BONDING
JUMPER (b)
WASHER (b)
WASHER (c)
BONDING JUMPER (c)
B
WASHER (a)
JUMPER (b)
WASHER (a)
BONDING
NUT
CLAMP (b)
BONDING
SLAT TRACK HOUSING
SEAL
PREPACK
FWD
UP A10 1211
119
13
O−RING
RING
RETAINING
0.53 + 0.06
17
S27291
FIGURE 4. GROU P 1 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION
January 30, 1997 SHEET 3 OF 6 767-57A0060
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BOEING SERVICE BULLETIN 767-57A0060
The step number shown below agree with the number shown in the circle symbol in the figure.
The QTY numbers shown below are the number of parts necessary for one side of the airplane.
STEP TASK NAME PART NUMBER QTY NOTES
1 Locate Doubler 112T2031-17 2 in position on the inboard and outboard sides
of rib 9 web as indicated.
2 Drill Hole --- 1 through both doublers and the rib 9 web to a
0.420 - 0.480 inch diameter. Clean and deburr
hole maintain a finish of 125 AA or better.
3 Locate Doubler 112T5093-3 1 in position common to rib 9 web as indicated.
Doubler Assy 112T5093-1 1
4 Drill Holes --- 28 in the doublers, doubler assembly and the rib 9
web as indicated. Clean and deburr holes.
5 Install Doubler 112T2031-17 2 wet by applying a faying surface seal between
the doublers and the web using BMS 5-95.
Refer to BSOPM 20-50-19. Install fasteners as
indicated.
Fasteners --- 16
6 Install Doubler 112T5093-3 1 wet by applying a faying surface seal between
the installed doublers and the doublers using
BMS 5-95. Refer to BSOPM 20-50-19. Install
fasteners as indicated.
Doubler Assy 112T5093-1 1
Fasteners --- 12
7 Apply Fillet Seal BMS 5-26 - common to the outboard side of the web and
the doubler assembly as indicated. Refer to
BSOPM 20-50-19.Type II Class B
8 Apply Fillet Seal BMS 5-95 - common to the inboard side of the web and the
doubler assembly as indicated. Refer to
BSOPM 20-50-19.Class C
9 Locate Drain Tube
Assy
112T2031-3
112T2031-4
(LH)
(RH)
1 in position common to the slat track drain
housing as indicated.
10 Drill Holes --- 2 in drain tube assembly and slat track drain
housing as indicated. Clean and deburr holes
then apply alodine 600 and BMS 10-20, Type
II. Refer to BSOPM 20-43-03 and 20-41-02.
11 Install Drain Tube
Assy
112T2031-3
112T2031-4
(LH)
(RH)
1 wet by prepacking with seal between the slat
track drain housing and the drain tube
assembly using BMS 5-26. Install fasteners
wet with BMS 5-26, Type II Class B as
indicated. Refer to BSOPM 20-50-19.Fasteners --- 2
12 Apply Fillet Seal BMS 5-26 - common to the fastener head and the drain
tube assembly as indicated. Refer to BSOPM
20-50-19.Type II Class B
13 Apply Fillet Seal BMS 5-26 - common to the slat track drain housing and the
drain tube assembly as indicated. Refer to
BSOPM 20-50-19.Type II Class B
FIGURE 4. GROU P 1 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION
January 30, 1997 SHEET 4 OF 6 767-57A0060
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BOEING SERVICE BULLETIN 767-57A0060
(Continued)
STEP TASK NAME PART NUMBER QTY NOTES
14 Install O-Ring MS29513-114 1 by lightly applying a layer of BMS 3-24 to the
coupling components prior to assembly. Install
the o-ring between the retaining rings included
with the coupling assembly. Hand tighten
coupling nut. Lockwire per BSOPM 20-50-02.
Drain Tube 200-030-0001-501 1
Coupling Assy 355B387S8 1 NOTE: During hand forming of drain tube use
care not to overbend or flatten the flex
portion of tube. Minimum inside bend
radius is 0.75.Lockwire MS20995AB -
15 Install O-Ring MS29513-114 2 by lightly applying a layer of BMS 3-24 to the
coupling components prior to assembly. Install
the o-rings between the retaining rings and the
retainer halve included with the coupling
assembly as indicated. Place the tube ends
together with a gap of (0.150 plus or minus
0.050 inches) between the ferrules. Snap the
retainer halves together. Hand tighten
coupling nut to the body of the coupling
assembly. Make sure the assembled coupling
meets the indicated dimension of (0.53 plus or
minus 0.06). Lockwire per BSOPM 20-50-02.
Coupling Assy 305B387S8 1
Lockwire MS20995AB -
16 Install Bracket 287T0020-325 1 to the rib 9 stiffener as indicated. Refer to
BSOPM 20-11-03.Fasteners --- 4
17 Install Bonding
Clamp
"a" AN735C8 1 Designated (electrostatic) bond path. Prepare
fay surface bond and install parts per BSWPM
20-20-00, except fillet seal bonding clamps
with BMS 5-45, Class B. Refer to BSOPM
20-50-19. Ensure entire bond surface is free
of finish. Use cleaning method CM1 if finish is
present or CM3 if surface is bare. Refer to
BSWPM 20-20-00. Apply alodine 600 and
BMS 10-20, Type II to any bare metal areas
remaining after the bonding clamps and fillet
seal is installed. Refer to BSOPM 20-43-03
and 20-41-02. Reference Note (a) for bonding
jumper "b" and "c" installation sequence.
Verify resistance does not exceed .010 OHMS.
Measure the resistance from the rib 9 stiffener
at least .25 inches away from the bonding
bracket to the slat track drain can at least .25
inches away from the bonding jumper
attachment. Refer to BSWPM 20-20-00 and
BSOPM 20-11-03.
Bonding
Clamp
"b" AN735DC8 1
Bonding
Clamp
"c" AN735DC56 1
Bonding
Jumper
"a" BACJ40A20-8 1
Bonding
Jumper
"b" BACJ40AC44-6 1
Bonding
Jumper
"c" BACJ40AC44-8 1
Fasteners --- 4
(a) Install bonding jumper "b" with the terminal end marked by a red band to bonding clamp "b" and
connect the terminal end marked with a blue band to bonding clamp "a". Install bonding jumper
"c" with the terminal end marked by a red band to the bracket installed on the rib 9 stiffener and
connect the terminal end marked with a blue band to bonding clamp "b".
FIGURE 4. GROU P 1 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION
January 30, 1997 SHEET 5 OF 6 767-57A0060
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BOEING SERVICE BULLETIN 767-57A0060
The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the
figure. A number in the upper right corner gives the diameter of the fastener. A number in the lower right
hand corner gives the grip length of the fastener.
COUNTERSINK
(OPTIONAL)EXAMPLE OF FASTENER CODE LENGTH/GRIP
FASTENER
7
6F
(OPTIONAL)
DIAMETER
FASTENER
(OPTIONAL)
F = FAR SIDE
N = NEAR SIDE
HEAD LOCATIONLETTER CODE
D
C
B53324
CODE NAME PART NUMBER HOLE DIA NOTES
A Rivet BACR15FR6E5 0.205 - 0.209
B Screw BACS12GU3K6 ---
Washer (a) NAS1149D0316H
Washer (b) NAS1149D0363H
Washer (c) NAS1149D0316H Use two washers if and as required to
prevent crushing of drain tube.
Nut BACN10YR3CD
C Rivet BACR30FT6AD* 0.190 - 0.193
D Washer NAS1149D0316H ---
Nut BACN10YR3CD
FIGURE 4. GROU P 1 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION
January 30, 1997 SHEET 6 OF 6 767-57A0060
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BOEING SERVICE BULLETIN 767-57A0060
DSEE
FRONT SPAR
SLAT TRACK
HOUSING
SKIN
WING LOWER
BSEE
CSEE
A
RIB NO. 9
ASEE
FWD INBD
UP
S72210
FIGURE 5. GROU P 2 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION
January 30, 1997 SHEET 1 OF 6 767-57A0060
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BOEING SERVICE BULLETIN 767-57A0060
1
C F4
A−AFWD
UP
12
HOSE
FLEX
O−RING
RETAINING RING
DRAIN
TUBE
4
4
3
2 6
542
B
A
A
FWD INBD
UP
+/−0.10
3.21
+/−0.10
4.20
S72209
FIGURE 5. GROU P 2 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION
January 30, 1997 SHEET 2 OF 6 767-57A0060
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BOEING SERVICE BULLETIN 767-57A0060
RETAINING
RING
A10
SEAL
PREPACK
11
WASHER (a)
BONDING JUMPER
BONDING JUMPER
RING
RETAINING
O−RING
0.53 + 0.06
HALF
RETAINER
COUPLING
NUT
BODY
COUPLING
BONDING 15 16
13
CLAMP
BONDING14 16
WASHER (b)
WASHER (c)
WASHER (a)
NUT
B16
CLAMP
C
FWD
UP
SLAT TRACK HOUSING
8 9
97
D
S72211
FIGURE 5. GROU P 2 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION
January 30, 1997 SHEET 3 OF 6 767-57A0060
Revision 1: December 31, 1998 34

### Page 39

BOEING SERVICE BULLETIN 767-57A0060
The step number shown below agree with the number shown in the circle symbol in the figure.
The QTY numbers shown below are the number of parts necessary for one side of the airplane.
STEP TASK NAME PART NUMBER QTY NOTES
1 Drill Hole --- 1 to a 0.420 - 0.480 diameter in rib 9 web as
indicated. Maintain a finish of 125 AA or better
with no burrs.
2 Locate Doubler 112T5093-3 1 in position common to rib 9 web as indicated.
Doubler Assy 112T5093-1 1
3 Drill Holes --- 12 in doubler, doubler assembly and the rib 9
web as indicated.
4 Install Doubler 112T5093-3 1 wet by applying a faying surface seal between
the doublers and the web using BMS 5-95.
Refer to BSOPM 20-50-19. Install fasteners as
indicated.
Doubler Assy 112T5093-1 1
Fasteners --- 12
5 Apply Fillet Seal BMS 5-26 - common to the outboard side of the web and
the doubler assembly. Refer to BSOPM
20-50-19.Type II Class B
6 Apply Fillet Seal BMS 5-95 - common to the inboard side of the web and the
doubler assembly. Refer to BSOPM 20-50-19.Class C
7 Locate Drain Tube
Assy
112T2031-3
112T2031-4
(LH)
(RH)
1 in position common to the slat track drain
housing as indicated.
8 Drill Holes --- 2 in drain tube assembly and slat track drain
housing as indicated.
9 Install Drain Tube
Assy
112T2031-3
112T2031-4
(LH)
(RH)
1 wet by prepacking with seal between the slat
track drain housing and the drain tube
assembly using BMS 5-26. Refer to BSOPM
20-50-19. Install fasteners as indicated.Fasteners --- 2
10 Apply Fillet Seal BMS 5-26 - common to the fastener head and the drain
tube assembly as indicated. Refer to BSOPM
20-50-19.Type II Class B
11 Apply Fillet Seal BMS 5-26 - common to the slat track drain housing and the
drain tube assembly as indicated. Refer to
BSOPM 20-50-19.Type II Class B
12 Install O-Ring MS29513-114 1 by lightly applying a layer of BMS 3-24 to the
coupling components prior to assembly. Install
the o-ring between the retaining rings included
with the coupling assembly. Hand tighten
coupling nut. Lockwire per BSOPM 20-50-02.
Drain Tube 200-030-0001-501 1
Coupling
Assy
355B387S8 1 NOTE: During hand forming of drain tube use
care not to overbend or flatten the flex
portion of tube. Minimum bend radius
is 0.75.Lockwire MS20995AB -
FIGURE 5. GROU P 2 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION
January 30, 1997 SHEET 4 OF 6 767-57A0060
Revision 1: December 31, 1998 35

### Page 40

BOEING SERVICE BULLETIN 767-57A0060
(Continued)
STEP TASK NAME PART NUMBER QTY NOTES
13 Install O-Ring MS29513-114 2 by lightly applying a layer of BMS 3-24 to the
coupling components prior to assembly. Install
the o-rings between the retaining rings and the
retainer halve included with the coupling
assembly as indicated. Place the tube ends
together with a gap of (0.150 plus or minus
0.050 inches) between the ferrules. Snap the
retainer halves together. Hand tighten coupling
nut to the body of the coupling assembly.
Make sure the assembled coupling meets the
indicated dimension of (0.53 plus or minus
0.06). Lockwire per BSOPM 20-50-02.
Coupling
Assy
305B387S8 1
Lockwire MS20995AB -
14 Locate Bonding
Clamp
AN735C8 1 as indicated.
15 Locate Bonding
Clamp
AN735DC8 1 as indicated.
16 Install Bonding
Clamp
AN735C8 1 Bond and assemble with indicated fasteners as
specified in BSOPM 20-11-03. Except total
resistance across each bond is to be (0.010
ohms maximum). BMS 10-20 fuel tank coating
is not required after the electrical bonding on
the aluminum slat track drain tube.
Bonding
Clamp
AN735DC8 1
Bonding
Jumper
BACJ40A20-6 1
Fasteners --- 2
FIGURE 5. GROU P 2 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION
January 30, 1997 SHEET 5 OF 6 767-57A0060
Revision 1: December 31, 1998 36

### Page 41

BOEING SERVICE BULLETIN 767-57A0060
The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the
figure. A number in the upper right corner gives the diameter of the fastener. A number in the lower right
hand corner gives the grip length of the fastener.
COUNTERSINK
(OPTIONAL)EXAMPLE OF FASTENER CODE LENGTH/GRIP
FASTENER
7
6F
(OPTIONAL)
DIAMETER
FASTENER
(OPTIONAL)
F = FAR SIDE
N = NEAR SIDE
HEAD LOCATIONLETTER CODE
D
C
B53324
CODE NAME PART NUMBER HOLE DIA NOTES
A Rivet BACR15FR6E5 0.205 - 0.209
B Screw BACS12GU3K6 ---
Use 2 washers if and as required
to prevent crushing of drain tube.
Washer (a) NAS1149D0316J
Washer (b) NAS1149D0363J
Washer (c) NAS1149D0316J
Nut BACN10YR3CD
C Bolt BACB30VT6K4 0.187 - 0.190
Collar BACC30BP6
FIGURE 5. GROU P 2 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION
January 30, 1997 SHEET 6 OF 6 767-57A0060
Revision 1: December 31, 1998 37

### Page 42

BOEING SERVICE BULLETIN 767-57A0060
ASEE
RIB NO. 9
A
DSEE
WING LOWER
SKIN
HOUSING
SLAT TRACK
FRONT SPAR
ESEE
BSEE
FWD INBD
UP
S71995
FIGURE 6. GROU P 2 - INBOARD SLAT TRACK DRAIN TUBE ADDITIONAL WORK
January 30, 1997 SHEET 1 OF 5 767-57A0060
Revision 1: December 31, 1998 38

### Page 43

BOEING SERVICE BULLETIN 767-57A0060
C
6
6
4
A−A
HOSE
FLEX
B
DRAIN
TUBE
SEE C
B1 2 3
FWD
UP
C
D
ASSEMBLY
DOUBLER BRACKET
JUMPER (c)
BONDING
(4 LOCATIONS)
FWD
A
A
FWD INBD
UP
+/−0.10
4.20
S72202
FIGURE 6. GROU P 2 - INBOARD SLAT TRACK DRAIN TUBE ADDITIONAL WORK
January 30, 1997 SHEET 2 OF 5 767-57A0060
Revision 1: December 31, 1998 39

### Page 44

BOEING SERVICE BULLETIN 767-57A0060
WASHER (a)
A
JUMPER (a)
BONDING
D
WASHER (b)
SLAT TRACK HOUSING
NUT
WASHER (a)
FWD
UP
CLAMP (c)
6 BONDING
WASHER (c)
A
NUT
A
BONDING
JUMPER (a)
WASHER (c)
WASHER (b)
WASHER (a)
E
CLAMP (b)
JUMPER (b)
BONDING
65BONDING
ASSEMBLY
COUPLING
WASHER (a)
BONDING
JUMPER (b)
BONDING
CLAMP65
BONDING JUMPER (c)
DRAIN TUBE
S72239
FIGURE 6. GROU P 2 - INBOARD SLAT TRACK DRAIN TUBE ADDITIONAL WORK
January 30, 1997 SHEET 3 OF 5 767-57A0060
Revision 1: December 31, 1998 40

### Page 45

BOEING SERVICE BULLETIN 767-57A0060
The step number shown below agree with the number shown in the circle symbol in the figure.
The QTY numbers shown below are the number of parts necessary for one side of the airplane.
STEP TASK NAME PART NUMBER QTY NOTES
1 Remove /
Discard
Fasteners 12 from the doubler assembly.
2 Install Fasteners --- 12 in the doubler assembly as indicated.
3 Apply Fillet Seal BMS 5-45 - to both ends of the (12) fasteners installed
in the doubler assembly. Refer to BSOPM
20-50-19.
4 Install Bracket 287T0020-325 1 to the rib 9 stiffener as indicated. Refer to
BSOPM 20-11-03.Fasteners --- 4
5 Remove /
Discard
Bonding Clamp AN735C8 1
Bonding Clamp AN735DC8 1
Bonding Jumper BACJ40A20-6 1
Fasteners --- 2
6 Install Bonding
Clamp
"a" AN735C8 1 Designated (electrostatic) bond path.
Prepare fay surface bond and install parts
per BSWPM 20-20-00, except fillet seal
bonding clamps with BMS 5-45, Class B.
Refer to BSOPM 20-50-19. Ensure entire
bond surface is free of finish. Use
cleaning method CM1 if finish is present or
CM3 if surface is bare. Refer to BSWPM
20-20-00. Apply alodine 600 and BMS
10-20, Type II to any bare metal areas
remaining after the bonding clamps and
fillet seal is installed. Refer to BSOPM
20-43-03 and 20-41-02. Reference Note
(a) for bonding jumper "b" and "c"
installation sequence. Verify resistance
does not exceed .010 OHMS. Measure
the resistance from the rib 9 stiffener at
least .25 inches away from the bonding
bracket to the slat track drain can at least
.25 inches away from the bonding jumper
attachment. Refer to BSWPM 20-20-00
and BSOPM 20-11-03.
Bonding
Clamp
"b" AN735DC8 1
Bonding
Clamp
"c" AN735DC56 1
Bonding
Jumper
"a" BACJ40A20-8 1
Bonding
Jumper
"b" BACJ40AC44-6 1
Bonding
Jumper
"c" BACJ40AC44-8 1
Fasteners --- 4
(a) Install bonding jumper "b" with the terminal end marked by a red band to bonding clamp "b" and
connect the terminal end marked with a blue band to bonding clamp "a". Install bonding jumper
"c" with the terminal end marked by a red band to the bracket installed on the rib 9 stiffener and
connect the terminal end marked with a blue band to bonding clamp "b".
FIGURE 6. GROU P 2 - INBOARD SLAT TRACK DRAIN TUBE ADDITIONAL WORK
January 30, 1997 SHEET 4 OF 5 767-57A0060
Revision 1: December 31, 1998 41

### Page 46

BOEING SERVICE BULLETIN 767-57A0060
The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the
figure. A number in the upper right corner gives the diameter of the fastener. A number in the lower right
hand corner gives the grip length of the fastener.
COUNTERSINK
(OPTIONAL)EXAMPLE OF FASTENER CODE LENGTH/GRIP
FASTENER
7
6F
(OPTIONAL)
DIAMETER
FASTENER
(OPTIONAL)
F = FAR SIDE
N = NEAR SIDE
HEAD LOCATIONLETTER CODE
D
C
B53324
CODE NAME PART NUMBER HOLE DIA NOTES
A Screw BACS12GU3K6 ---
Washer (a) NAS1149D0316H
Washer (b) NAS1149D0363H
Washer (c) NAS1149D0316H Use two washers if and as required to
prevent crushing of drain tube.
Nut BACN10YR3CD
B Bolt BACB30FP6A4 0.200 - 0.203
Collar BACC30M6
C Rivet BACR30FT6AD* 0.190 - 0.193
D Washer NAS1149D0316H ---
Nut BACN10YR3CD
FIGURE 6. GROU P 2 - INBOARD SLAT TRACK DRAIN TUBE ADDITIONAL WORK
January 30, 1997 SHEET 5 OF 5 767-57A0060
Revision 1: December 31, 1998 42

### Page 47

Commercial
Airplane
Group
767
Service Bulletin
Number: 767-57A0060 Evaluation FormDate: January 30, 1997
Revision 1: December 31, 1998
ATA System: 5740 2781 2811
Prepared By: Robert Mehring
SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Slat Track Housing - Drain Tube Fuel
Leak Inspection and Rework
Use this evaluation form to tell us what you think of the quality of this service bulletin. We will use the data
that you give us to improve the quality of our service bulletins.
NOTE: Please do not use this evaluation form to tell us to make changes to your manuals. To make these
changes, please use a Publication Change Request (PCR) form.
Please give us this data:
(If necessary, please use the other side. Thank you for the time you used to give us your comments.)
OPERATOR: TODAY'S DATE:
PREPARED BY: TITLE:
ORGANIZATION: TELEX CODE:
TELEPHONE NUMBER: BASE:
Please rate the quality of this service bulletin: (good) 4321 (poor)
Please rate the quality of the illustrations: (good) 4321 (poor)
Will you do the change given by this service bulletin? Yes No If not, please explain:
Is this service bulletin easy to understand? Yes No If not, please explain:
Is this service bulletin easy to use? Yes No If not, please explain:
Are the Planning Information, Material Information, and
Accomplishment Instructions accurate? Yes No If not, please explain:
Is the Manpower estimate accurate? Yes No If not, please explain:
Give the completed evaluation form to your Boeing Field Service Representative or send the evaluation form
directly to this address:
Manager
Service Bulletin Engineering
Boeing Commercial Airplane Group
P.O. Box 3707, Mail Stop 2H-37
Seattle, WA 98124-2207
Revision 1: December 31, 1998

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