Commercial

Airplane

Group

767

Service Bulletin

Number: 767-57A0060 Revision Transmittal Sheet

Date: January 30, 1997

Revision 2: January 31, 2002

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

Federal Aviation Administration (FAA) Airworthiness Directive 2001-14-19, Amendment 39-12330, is related

to this service bulletin.

No more work is necessary on airplanes inspected or reworked as shown in the initial release and Revision 1

of this service bulletin as a result of this revision. However, repeat inspections are required until terminating

action is accomplished.

REASON FOR REVISION

This revision is sent to:

Add information that Federal Aviation Administration (FAA) Airworthiness Directive AD 2001-14-19,

Amendment 39-12330 is related to this service bulletin.

Delete flag note 2 in Figure 1. Flag note 2 allowances for an MPD inspection did not meet the minimum fuel

requirements for the leak check inspections given in this service bulletin.

Clarify the rivet diameter and screw length in the fastener tables of Figures 4, 5 and 6.

Add minimum fuel requirements for the leak check inspection to Part III and Part IV of the Accomplishment

Instructions.

Add a material call out to the operators supplied material section for the slat track drain tube shim allowance

added to Figures 4 and 5.

Clarify the BMS 5-95 sealant call out in Figures 4, 5 and the operator supplied material section.

Add lockwire MS20995AB32 to the operators supplied material section and clarify the lockwire diameter call

out for Figures 3, 4 and 5.

Add the data given in Information Notice 767-57A0060 IN 01.

767-57A0060

Revision Transmittal Page 1 of 2
BOEING SERVICE BULLETIN 767-57A0060

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

Revision 2: January 31, 2002

767-57A0060

Revision Transmittal Page 2 of 2
Commercial

Airplane

Group

767

Service Bulletin

Number: 767-57A0060 Summary Date: January 30, 1997

Revision 2: January 31, 2002

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.

Federal Aviation Administration (FAA) Airworthiness

Directive 2001-14-19, Amendment 39-12330, is

related to this service bulletin.

767-57A0060

Summary Page 1 of 2
BOEING SERVICE BULLETIN 767-57A0060

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.

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 2: January 31, 2002 Summary Page 2 of 2
Commercial

Airplane

Group

767

Service Bulletin

Number: 767-57A0060

Date: January 30, 1997

Revision 2: January 31, 2002

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.

Airplane Models:

767-200 767-300 767-300F

IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER

AAR AIRCRAFT SALES AND LEASING (AFD)

1 VA804 VN153 VN166

ABX AIR (ABX)

1 VA803 VA807-VA809 VB101-VB115 VB302

AERO CONTINENTE (COH)

1 VB301 VE104 VF051

AEROMEXICO (AMX)

1 VF071-VF072 VF091 VF093

AIR ALGERIE (ALG)

1 VK131-VK133

AIR ATLANTA ICELANDIC (AID)

1 VB326-VB328

AIR CANADA (ACN)

1 VA701-VA719 VB001-VB002 VB201-VB202 VN051-VN054 VN057-VN062 VN531-VN532

VN536 VN556 VN731-VN732 VN751-VN752 VN931-VN936

January 30, 1997 767-57A0060

Revision 2: January 31, 2002 Page 1 of 42
BOEING SERVICE BULLETIN 767-57A0060

AIR CHINA (BEJ)

1 VE064-VE065 VE083-VE086 VK161-VK164

AIR EUROPA (ARE)

1 VB323

AIR EUROPE ITALY (EIY)

1 VL931-VL932 VN682

AIR FRANCE (AFA)

1 VN631-VN635

AIR GABON (GBN)

1 VE021

AIR MADAGASCAR (MAD)

1 VE117

AIR MAURITIUS (MAU)

1 VF001-VF002

AIR NEW ZEALAND (ANZ)

1 VB324 VE101-VE103 VN651-VN657

AIR PACIFIC (APC)

1 VN676

AIR SEYCHELLES (ASY)

1 VL941

AIR ZIMBABWE (ZMB)

1 VF061-VF062

AIR 2000 (ATZ)

1 VN921-VN922

AIRTOURS INT'L AIRWAYS (GUE)

1 VN951-VN953

ALITALIA (ALI)

1 VL701-VL702 VN422-VN427

ALL NIPPON AIRWAYS (ANA)

1 VB116-VB125 VK081-VK113 VN191-VN198

AMERICAN AIRLINES (AAL)

1 VA501-VA530 VN001-VN041

ANSETT AUSTRALIA (ANS)

1 VB051-VB055 VB321-VB322 VB325 VE118 VL755 VN811-VN813

ANSETT WORLDWIDE AVIATION (AWW)

1 VN388 VN436

ASIANA AIRLINES (AAR)

1 VK141-VK148 VL703 VN636 VN753 VW851

January 30, 1997 767-57A0060

Revision 2: January 31, 2002 2
BOEING SERVICE BULLETIN 767-57A0060

AVIANCA (AVI)

1 VE171-VE172 VF092 VF161 VN152 VN385

BANK OF AMERICA (BOB)

1 VA806

BOEING (TBC)

1 VA001

BRITANNIA AIRWAYS (BRI)

1 VB329-VB332 VL911-VL913

BRITANNIA AIRWAYS (TNS)

1 VL914

BRITISH AIRWAYS (BAB)

1 VN111-VN114 VN118-VN122 VN124-VN127 VN133-VN137

C-S AVIATION SERVICES (CSV)

1 VE041

CHINA YUNNAN AIRLINES (YUN)

1 VL871-VL873

CONDOR (CDF)

1 VN683-VN691

DELTA AIR LINES (DAL)

1 VA301-VA315 VK031-VK056 VL753 VN251-VN273 VN301-VN306

EGYPTAIR (EGP)

1 VN211

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 VL004-VL006 VN307-VN310 VN313-VN314

H.M.S.F. AND AMEDEO CORP. (BWN)

1 VF180

IBERIA AIRLINES (IBE)

1 VN546-VN547

ITOCHU CORPORATION (CIT)

1 VF181-VF184

JAPAN AIRLINES (JAL)

1 VB371-VB373 VK001-VK015 VK021-VK022 VK181

January 30, 1997 767-57A0060

Revision 2: January 31, 2002 3
BOEING SERVICE BULLETIN 767-57A0060

K.B.A. FOUNDATION (KBA)

1 VN312

KALAIR (BERMUDA) (KLB)

1 VN311

KLM - ROYAL DUTCH AIRLINES (KLM)

1 VL891-VL900

LAM (LAM)

1 VF162

LANCHILE AIRLINES (LAN)

1 VN063-VN064 VN557 VN966-VN969 VN971

LAUDA AIR (LAL)

1 VL011

LAUDA AIR S.P.A. (LDI)

1 VN242-VN243 VN671

LOT POLISH AIRLINES (LOT)

1 VF041-VF042 VN291-VN293

LTU (LTU)

1 VN171-VN174 VN381

MALEV HUNGARIAN AIRLINES (HGA)

1 VF171-VF172 VL003

MARTINAIR HOLLAND (MTH)

1 VN221-VN225 VN672

MID EAST JET (SKL)

1 VF251

QANTAS (QAN)

1 VE061-VE063 VE067-VE069 VN081-VN099 VN115-VN117 VN123 VN130-VN132

2 VE066

ROYAL BRUNEI AIRLINES (RBA)

1 VN372 VN382-VN384 VN386-VN387 VN637-VN638

SAS (SAS)

1 VN151 VN154-VN158 VN163-VN165 VN167-VN168

SHANGHAI AIRLINES (SHA)

1 VK171

SOUTH AFRICAN AIRWAYS (SAA)

1 VE022-VE023

SPANAIR (SPP)

1 VN541-VN542

TACA INTERNATIONAL AIRLINES (TAC)

1 VE116

January 30, 1997 767-57A0060

Revision 2: January 31, 2002 4
BOEING SERVICE BULLETIN 767-57A0060

TRANSBRASIL (TBL)

1 VB251-VB253 VL001-VL002

TWA (TWA)

1 VA801-VA802 VA805 VA810 VN376 VN537 VN551

VN561-VN562 VN681

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 VN056 VN231-VN234

VIETNAM AIRLINES (VIE)

1 VL751-VL752 VL754 VN421 VN972

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 2: January 31, 2002 5
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.

Revision 2 is sent to:

Add information that Federal Aviation Administration (FAA) Airworthiness Directive AD 2001-14-19,

Amendment 39-12330 is related to this service bulletin.

Delete flag note 2 in Figure 1. Flag note 2 allowances for an MPD inspection did not meet the

minimum fuel requirements for the leak check inspections given in this service bulletin.

Clarify the rivet diameter and screw length in the fastener tables of Figures 4, 5 and 6.

Add minimum fuel requirements for the leak check inspection to Part III and Part IV of the

Accomplishment Instructions.

January 30, 1997 767-57A0060

Revision 2: January 31, 2002 6
BOEING SERVICE BULLETIN 767-57A0060

Add a material call out to the operators supplied material section for the slat track drain tube shim

allowance added to Figures 4 and 5.

Clarify the BMS 5-95 sealant call out in Figures 4, 5 and the operator supplied material section.

Add lockwire MS20995AB32 to the operators supplied material section and clarify the lockwire

diameter call out for Figures 3, 4 and 5.

Add the data given in Information Notice 767-57A0060 IN 01.

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.

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.

Federal Aviation Administration (FAA) Airworthiness Directive 2001-14-19, Amendment 39-12330, is

related to this service bulletin.

January 30, 1997 767-57A0060

Revision 2: January 31, 2002 7
BOEING SERVICE BULLETIN 767-57A0060

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.

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

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

bulletin as an alternative method of compliance to the requirements of paragraphs (a) and (b) of AD

2001-14-19. All provisions of AD 2001-14-19 that are not specifically referenced in the above

sentence remain fully applicable and must be complied with.

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.

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

January 30, 1997 767-57A0060

Revision 2: January 31, 2002 8
BOEING SERVICE BULLETIN 767-57A0060

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

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

h. FAA Airworthiness Directive 2001-14-19, Amendment 39-12330

2. Data supplied with this service bulletin:

None

January 30, 1997 767-57A0060

Revision 2: January 31, 2002 9
BOEING SERVICE BULLETIN 767-57A0060

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 2: January 31, 2002 10
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 2: January 31, 2002 11
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

. . 1 1 BACJ40AC44-6 Jumper

January 30, 1997 767-57A0060

Revision 2: January 31, 2002 12
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 BACJ40AC44-8 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

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 Parts / Material Required Name

4 2024-T3 (Thickness x 1.5 x 1.5) (b) Aluminum Clad Sheet

4 2024-T351 (Thickness x 1.5 x 1.5) (b) Aluminum Clad Sheet (Optional to 2024-T3)

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 B (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)

4 NAS1738E8 (c) Rivet

--- MS20995AB32 Lockwire (Quantity as required)

(a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier

data.

(b) Fabricate shims from aluminum clad sheet if and as required per Figure 4 and 5. Adjust material

thickness from (.100 to .200) to fill the gap that may exist between the slat track housing and the

drain tube assembly interface.

(c) Use this rivet as an option to the BACR15FR6E5 rivets, if shims are used per Figure 4 and 5. Adjust

rivet length if and as required to facilitate differences in shim thickness.

January 30, 1997 767-57A0060

Revision 2: January 31, 2002 13
BOEING SERVICE BULLETIN 767-57A0060

D. Parts Necessary to Change Spares

None

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

Revision 2: January 31, 2002 14
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 U.S. 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

Revision 2: January 31, 2002 15
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 debris.

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.

NOTE: A minimum of 4400 U.S. gallons of fuel is required in each wing tank to adequately check

for leaks common to the drain tube.

January 30, 1997 767-57A0060

Revision 2: January 31, 2002 16
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 serviceable 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 debris.

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.

NOTE: A minimum of 4400 U.S. gallons of fuel is required in each wing tank to adequately check

for leaks common to the drain tube.

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 serviceable condition.

January 30, 1997 767-57A0060

Revision 2: January 31, 2002 17
BOEING SERVICE BULLETIN 767-57A0060

FIGURE TABLE OF CONTENTS

Title Page

FIGURE 1. GROUP 1 - LOGIC DIAGRAM FOR INSPECTION AND

MAINTENANCE ALTERNATIVES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

FIGURE 2. VISUAL INSPECTION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

FIGURE 3. INBOARD SLAT TRACK DRAIN TUBE REMOVAL . . . . . . . . . . . . . . . . . 23

FIGURE 4. GROUP 1 - INBOARD SLAT TRACK DRAIN TUBE

INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

FIGURE 5. GROUP 2 - INBOARD SLAT TRACK DRAIN TUBE

INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

FIGURE 6. GROUP 2 - INBOARD SLAT TRACK DRAIN TUBE ADDITIONAL

WORK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

January 30, 1997 767-57A0060

Revision 2: January 31, 2002 18
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 PART I - VISUAL

REPEAT THE PART 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

1 2

R93564

FIGURE 1. GROUP 1 - LOGIC DIAGRAM FOR INSPECTION AND MAINTENANCE ALTERNATIVES

January 30, 1997 SHEET 1 OF 2 767-57A0060

Revision 2: January 31, 2002 19
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 This flag note has been deleted. Flag note 2 allowances for an MPD inspection did not meet the

minimum fuel requirements for the leak check inspections given in this service bulletin.

FIGURE 1. GROUP 1 - LOGIC DIAGRAM FOR INSPECTION AND MAINTENANCE ALTERNATIVES

January 30, 1997 SHEET 2 OF 2 767-57A0060

Revision 2: January 31, 2002 20
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

Revision 2: January 31, 2002 21
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

Revision 2: January 31, 2002 22
BOEING SERVICE BULLETIN 767-57A0060

RIB NO. 9

SKIN

LOWER WING

0.40 + 0.06

HOUSING

SLAT TRACK

FRONT SPAR

SEE A

SEE B

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

Revision 2: January 31, 2002 23
BOEING SERVICE BULLETIN 767-57A0060

B

6

CAP 4

LOCKWIRE 4

4 O-RING

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

Revision 2: January 31, 2002 24
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 20-41-02 Primer BMS 10-20, -

TYPE II

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 MS20995AB32 -

5 Apply Injection Seal BMS 5-26 - to fill the drain exit cavity and make flush

common to the exterior lower wing panel. Type II - Class B Refer to BSOPM 20-50-19 and 20-50-11.

6 Apply Fillet Seal BMS 5-26 - around the coupling cap assembly.

Refer to BSOPM 20-50-19. Type II - Class B

FIGURE 3. INBOARD SLAT TRACK DRAIN TUBE REMOVAL

January 30, 1997 SHEET 3 OF 3 767-57A0060

Revision 2: January 31, 2002 25
BOEING SERVICE BULLETIN 767-57A0060

SEE A

RIB NO. 9

A

SEE D

WING LOWER

SKIN

HOUSING

SLAT TRACK

FRONT SPAR

SEE E

SEE B

FWD INBD

UP

S26912

FIGURE 4. GROUP 1 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION

January 30, 1997 SHEET 1 OF 6 767-57A0060

Revision 2: January 31, 2002 26
BOEING SERVICE BULLETIN 767-57A0060

C

6

6

4

TUBE

DRAIN

FLEX

HOSE

O-RING

RETAINING RING

B

SEE C

C 6F

9 1 5

D 17

C

7

7

C 6F

8

16

14

4

4

3 6

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. GROUP 1 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION

January 30, 1997 SHEET 2 OF 6 767-57A0060

Revision 2: January 31, 2002 27
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 A 10 11 12

9 11

13

O-RING

RING

RETAINING

0.53 + 0.06

17

1

S27291

FIGURE 4. GROUP 1 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION

January 30, 1997 SHEET 3 OF 6 767-57A0060

Revision 2: January 31, 2002 28
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 Type II Class B BSOPM 20-50-19.

8 Apply Fillet Seal BMS 5-95 - common to the inboard side of the web and the

doubler assembly as indicated. Refer to Class B BSOPM 20-50-19.

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 Type II Class B 20-50-19.

13 Apply Fillet Seal BMS 5-26 - common to the slat track drain housing and the

drain tube assembly as indicated. Refer to Type II Class B BSOPM 20-50-19.

FIGURE 4. GROUP 1 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION

January 30, 1997 SHEET 4 OF 6 767-57A0060

Revision 2: January 31, 2002 29
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

Lockwire MS20995AB32 - radius is 0.75.

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 MS20995AB32 -

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 procedure 1-3 if finish

is present or cleaning procedure 5 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 "a".

FIGURE 4. GROUP 1 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION

January 30, 1997 SHEET 5 OF 6 767-57A0060

Revision 2: January 31, 2002 30
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

LETTER CODE HEAD LOCATION

D

C

B53324

CODE NAME PART NUMBER HOLE DIA NOTES

A Rivet BACR15FR6E5 0.205 - 0.209

Rivet NAS1738E8 Optional rivet to be used if shims are

required as indicated. Adjust rivet

length if and as required to facilitate

differences in shim thickness.

B Screw BACS12GU3K6 ---

Screw BACS12GU3K* --- Optional screw. Adjust screw length if

and as required to facilitate differences

in the washer stack up.

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 BACR15FT6AD* 0.190 - 0.193

D Washer NAS1149D0316H ---

Nut BACN10YR3CD

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FLAG NOTE

1 If a gap exists between the slat track housing and the drain tube assembly interface, install shims

if and as required. Fabricate shims from 2024-T3 or 2024-T351 (thickness x 1.5 x 1.5) aluminum

clad sheet. Adjust material thickness from (.100 to .200) to fill the gap between the slat track

housing and the drain tube assembly interface. Trim and fit the shims to match the footprint of

the filler pads attached to the drain tube assembly. Apply alodine and BMS 10-20 type II primer

to the shims. Refer to BSOPM 20-43-03 and 20-41-02. Install shims and the drain tube

assembly with the optional fasteners as indicated.

FIGURE 4. GROUP 1 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION

January 30, 1997 SHEET 6 OF 6 767-57A0060

Revision 2: January 31, 2002 31
BOEING SERVICE BULLETIN 767-57A0060

SEE D

FRONT SPAR

SLAT TRACK

HOUSING

SKIN

WING LOWER

SEE B

SEE C

A

RIB NO. 9

SEE A

FWD INBD

UP

S72210

FIGURE 5. GROUP 2 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION

January 30, 1997 SHEET 1 OF 6 767-57A0060

Revision 2: January 31, 2002 32
BOEING SERVICE BULLETIN 767-57A0060

1

C F 4

FWD A-A

UP

12

HOSE

FLEX

O-RING

RETAINING RING

DRAIN

TUBE

4

4

3

2 6

2 4 5

B

A

A

FWD INBD

UP

+/-0.10

3.21

+/-0.10

4.20

S72209

FIGURE 5. GROUP 2 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION

January 30, 1997 SHEET 2 OF 6 767-57A0060

Revision 2: January 31, 2002 33
BOEING SERVICE BULLETIN 767-57A0060

RETAINING

RING

A 10

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

BONDING

14 16

WASHER (b)

WASHER (c)

WASHER (a)

NUT

B 16

CLAMP

C

FWD

UP

SLAT TRACK HOUSING

8 9

7 9

D

1

S72211

FIGURE 5. GROUP 2 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION

January 30, 1997 SHEET 3 OF 6 767-57A0060

Revision 2: January 31, 2002 34
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 Type II Class B 20-50-19.

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 B

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 Type II Class B 20-50-19.

11 Apply Fillet Seal BMS 5-26 - common to the slat track drain housing and the

drain tube assembly as indicated. Refer to Type II Class B BSOPM 20-50-19.

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 MS20995AB32 -

FIGURE 5. GROUP 2 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION

January 30, 1997 SHEET 4 OF 6 767-57A0060

Revision 2: January 31, 2002 35
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 MS20995AB32 -

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. GROUP 2 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION

January 30, 1997 SHEET 5 OF 6 767-57A0060

Revision 2: January 31, 2002 36
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

LETTER CODE HEAD LOCATION

D

C

B53324

CODE NAME PART NUMBER HOLE DIA NOTES

A Rivet BACR15FR6E5 0.205 - 0.209

Rivet NAS1738E8 Optional rivet to be used if shims are

required as indicated. Adjust rivet

length if and as required to facilitate

differences in shim thickness.

B Screw BACS12GU3K6 ---

Screw BACS12GU3K* --- Optional screw. Adjust screw length

if and as required to facilitate

differences in the washer stack up.

Washer (a) NAS1149D0316J

Washer (b) NAS1149D0363J

Washer (c) NAS1149D0316J Use 2 washers if and as required to

prevent crushing of drain tube.

Nut BACN10YR3CD

C Bolt BACB30VT6K4 0.187 - 0.190

Collar BACC30BP6

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FLAG NOTE

1 If a gap exists between the slat track housing and the drain tube assembly interface, install shims

if and as required. Fabricate shims from 2024-T3 or 2024-T351 (thickness x 1.5 x 1.5) aluminum

clad sheet. Adjust material thickness from (.100 to .200) to fill the gap between the slat track

housing and the drain tube assembly interface. Trim and fit the shims to match the footprint of

the filler pads attached to the drain tube assembly. Apply alodine and BMS 10-20 type II primer

to the shims. Refer to BSOPM 20-43-03 and 20-41-02. Install shims and the drain tube

assembly with the optional fasteners as indicated.

FIGURE 5. GROUP 2 - INBOARD SLAT TRACK DRAIN TUBE INSTALLATION

January 30, 1997 SHEET 6 OF 6 767-57A0060

Revision 2: January 31, 2002 37
BOEING SERVICE BULLETIN 767-57A0060

SEE A

RIB NO. 9

A

SEE D

WING LOWER

SKIN

HOUSING

SLAT TRACK

FRONT SPAR

SEE E

SEE B

FWD INBD

UP

S71995

FIGURE 6. GROUP 2 - INBOARD SLAT TRACK DRAIN TUBE ADDITIONAL WORK

January 30, 1997 SHEET 1 OF 5 767-57A0060

Revision 2: January 31, 2002 38
BOEING SERVICE BULLETIN 767-57A0060

C

6

6

4

A-A

HOSE

FLEX

B

DRAIN

TUBE

SEE C

B 1 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. GROUP 2 - INBOARD SLAT TRACK DRAIN TUBE ADDITIONAL WORK

January 30, 1997 SHEET 2 OF 5 767-57A0060

Revision 2: January 31, 2002 39
BOEING SERVICE BULLETIN 767-57A0060

CLAMP (a)

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

5 6 BONDING

ASSEMBLY

COUPLING

WASHER (a)

BONDING

JUMPER (b)

BONDING

5 6

BONDING JUMPER (c)

DRAIN TUBE

S72239

FIGURE 6. GROUP 2 - INBOARD SLAT TRACK DRAIN TUBE ADDITIONAL WORK

January 30, 1997 SHEET 3 OF 5 767-57A0060

Revision 2: January 31, 2002 40
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 procedure 1-3 if finish is present

or cleaning procedure 5 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 "a".

FIGURE 6. GROUP 2 - INBOARD SLAT TRACK DRAIN TUBE ADDITIONAL WORK

January 30, 1997 SHEET 4 OF 5 767-57A0060

Revision 2: January 31, 2002 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

LETTER CODE HEAD LOCATION

D

C

B53324

CODE NAME PART NUMBER HOLE DIA NOTES

A Screw BACS12GU3K6 ---

Screw BACS12GU3K* --- Optional screw. Adjust screw length if

and as required to facilitate differences

in the washer stack up.

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 BACR15FT6AD* 0.190 - 0.193

D Washer NAS1149D0316H ---

Nut BACN10YR3CD

FIGURE 6. GROUP 2 - INBOARD SLAT TRACK DRAIN TUBE ADDITIONAL WORK

January 30, 1997 SHEET 5 OF 5 767-57A0060

Revision 2: January 31, 2002 42
Commercial

Airplane

Group

767

Service Bulletin

Number: 767-57A0060 Evaluation Form

Date: January 30, 1997

Revision 2: January 31, 2002

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:

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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:

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Accomplishment Instructions accurate? Yes No If not, please explain:

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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