Commercial

Airplane

Group

767

Service Bulletin

Number: 767-57-0068 Revision Transmittal Sheet Date: September 16, 1999

Revision 1: May 9, 2002

ATA System: 5740 2781 2811

SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Slat Track Housing Electrostatic Bond

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.

More work is necessary on the airplanes reworked as shown in the initial release of this service bulletin.

Boeing recommends the PART 2 - Additional Work be completed within 48 months from the release date of

Revision 1 of this service bulletin. The original bonding jumper "A" installation sequence as noted by the

red and blue bands was reversed. The reversed installation could cause dissimilar metal contact between

the bonding jumpers and result in galvanic corrosion.

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.

Clarify the BMS 5-45 sealant call out in the operator supplied material section.

Clarify the bonding jumper installation sequence given in Figure 1 note "a".

Add Part 2 - Additional Work requirements to correct the bonding jumper "A" installations originally installed

as shown in the initial release of this service bulletin.

Add the data given in Information Notice 767-57-0068 IN 01.

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

Original Release: September 16, 1999

Revision 1: May 9, 2002

767-57-0068

Revision Transmittal Page 1 of 1

Commercial

Airplane

Group

767

Service Bulletin

Number: 767-57-0068 Summary Date: September 16, 1999

Revision 1: May 9, 2002

ATA System: 5740 2781 2811

SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Slat Track Housing Electrostatic Bond

Rework

CONCURRENT REQUIREMENTS

None

BACKGROUND

Accomplishment of this service bulletin will provide

an improved electrostatic bond path for the number

5 and 8 inboard slat track housing drain tube

assemblies.

A production change (PRRB12900-133) was

incorporated at Boeing to install a new slat track

housing drain tube assembly for the number 5 and 8

inboard slat track. The purpose of this change was

to prevent possible fuel leaks at these locations.

After production incorporation of the new drain tube

assemblies, Boeing determined that the installation

did not meet current required bonding specifications.

Incorporation of this service bulletin will ensure

proper bonding of the number 5 and 8 inboard slat

track drain tube assemblies.

ACTION (PRRB13024)

Part 1 - Rework

Open the main tank and dry bay access panels.

Remove the bonding jumper assembly from the

number 5 and 8 inboard slat track housing drain

tube installations. Remove and replace the

fasteners common to drain tube doubler assembly.

Install bonding jumper brackets to the rib stiffeners.

Install bonding jumpers between the drain tube

assemblies and the brackets installed on the rib

stiffeners. Close the main tank and dry bay access

panels.

Part 2 - Additional Work

Open the main tank access panels. Rework the

bonding jumper assembly for the number 5 and 8

inboard slat track housing drain tube installations.

Close the main tank access panels.

EFFECTIVITY

All 767 airplanes line numbers 672 through 757.

COMPLIANCE

Boeing recommends the Part 1 - Rework be

completed within 5000 flight-cycles or 22 months,

whichever is earlier from the initial release date of

this service bulletin. Boeing recommends the PART

2 - Additional Work be completed within 48 months

from the release date 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.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for

airplanes in warranty as of September 29, 1998.

Please refer to Paragraph 2.B., Industry Support

Information.

MANPOWER

Total Elapsed Time

Per Airplane Man-Hours (Hours)

25 7.5

MATERIAL INFORMATION

Boeing Supplied Kits/Parts

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

Availability.

767-57-0068

Summary Page 1 of 2
BOEING SERVICE BULLETIN 767-57-0068

RIB NO. 9

WING LOWER

SKIN

HOUSING

SLAT TRACK

FRONT SPAR

A

SEE A

DOUBLER ASSEMBLY

TO THE DRAIN TUBE

THE FASTENERS COMMON

REMOVE AND REPLACE

REMOVE AND REPLACE EXISTING

BONDING JUMPER AND CLAMPS

INSTALL NEW BONDING

JUMPER AND BRACKET

FWD INBD

UP

S96564

September 16, 1999 767-57-0068

Revision 1: May 9, 2002 Summary Page 2 of 2
Commercial

Airplane

Group

767

Service Bulletin

Number: 767-57-0068

Date: September 16, 1999

Revision 1: May 9, 2002

ATA System: 5740 2781 2811

SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Slat Track Housing Electrostatic Bond

Rework

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 PRRB13024 for data about this change.

Airplane Models:

767-300 767-300F

IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER

AEROMEXICO (AMX)

VS211

AIR DO (HIA)

VS176-VS177

AIR MADAGASCAR (MAD)

VS316

AIR NEW ZEALAND (ANZ)

VN658 VS111

AIR 2000 (ATZ)

VS216

ALITALIA (ALI)

VS366-VS367 VS401

ALL NIPPON AIRWAYS (ANA)

VR401

AMERICAN AIRLINES (AAL)

VS196-VS203

ASIANA AIRLINES (AAR)

VR426

September 16, 1999 767-57-0068

Revision 1: May 9, 2002 Page 1 of 22
BOEING SERVICE BULLETIN 767-57-0068

BOEING (TBC)

VY999

BRITANNIA AIRWAYS (BRI)

VS051-VS054

BRITISH AIRWAYS (BAB)

VS246-VS248

DELTA AIR LINES (DAL)

VN274-VN276 VR471-VR472 VS066-VS070 VS073-VS078 VS266-VS272

ETHIOPIAN AIRLINES (ETH)

VS306

JAPAN AIRLINES (JAL)

VK016 VK186 VR461

KLM - ROYAL DUTCH AIRLINES (KLM)

VS136

LANCHILE AIRLINES (LAN)

VN970 VR251 VS131-VS133

LAUDA AIR (LAL)

VS301

LTU (LTU)

VS061

QANTAS (QAN)

VS186-VS187

SHANGHAI AIRLINES (SHA)

VR421

SKYMARK AIRLINES (SKM)

VS261-VS262

TWA (TWA)

VS206-VS207

UNITED AIRLINES (UAL)

VS091-VS096

UPS (UPS)

VR201-VR207 VW719-VW721

IDENTIFICATION BY VARIABLE NUMBER

VK016 VK186 VN274-VN276 VN658 VN970 VR201-VR207

VR251 VR401 VR421 VR426 VR461 VR471-VR472

VS051-VS054 VS061 VS066-VS070 VS073-VS078 VS091-VS096 VS111

VS131-VS133 VS136 VS176-VS177 VS186-VS187 VS196-VS203 VS206-VS207

VS211 VS216 VS246-VS248 VS261-VS262 VS266-VS272 VS301

VS306 VS316 VS366-VS367 VS401 VW719-VW721 VY999

September 16, 1999 767-57-0068

Revision 1: May 9, 2002 2
BOEING SERVICE BULLETIN 767-57-0068

2. Spares Affected

None

September 16, 1999 767-57-0068

Revision 1: May 9, 2002 3
BOEING SERVICE BULLETIN 767-57-0068

B. Concurrent Requirements

None

C. Reason

Accomplishment of this service bulletin will provide an improved electrostatic bond path for the

number 5 and 8 inboard slat track housing drain tube assemblies.

A production change (PRRB12900-133) was incorporated at Boeing to install a new slat track

housing drain tube assembly for the number 5 and 8 inboard slat track. The purpose of this change

was to prevent possible fuel leaks at these locations. After production incorporation of the new drain

tube assemblies, Boeing determined that the installation did not meet current required bonding

specifications.

Incorporation of this service bulletin will ensure proper bonding of the number 5 and 8 inboard slat

track drain tube assemblies.

Revision 1 is issued to:

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

Amendment 39-12330 is related to this service bulletin.

Clarify the BMS 5-45 sealant call out in the operator supplied material section.

Clarify the bonding jumper installation sequence given in Figure 1 note "a".

Add Part 2 - Additional Work requirements to correct the bonding jumper "A" installations originally

installed as shown in the initial release of this service bulletin.

Add the data given in Information Notice 767-57-0068 IN 01.

D. Description

Part 1 - Rework

Open the main tank and dry bay access panels. Remove the bonding jumper assembly from the

number 5 and 8 inboard slat track housing drain tube installations. Remove and replace the

fasteners common to drain tube doubler assembly. Install bonding jumper brackets to the rib

stiffeners. Install bonding jumpers between the drain tube assemblies and the brackets installed on

the rib stiffeners. Close the main tank and dry bay access panels.

Part 2 - Additional Work

Open the main tank access panels. Rework the bonding jumper assembly for the number 5 and 8

inboard slat track housing drain tube installations. Close the main tank access panels.

More work is necessary on the airplanes reworked as shown in the initial release of this service

bulletin. The original bonding jumper "A" installation sequence as noted by the red and blue bands

was reversed. The reversed installation could cause dissimilar metal contact between the bonding

jumpers and result in galvanic corrosion.

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.

September 16, 1999 767-57-0068

Revision 1: May 9, 2002 4
BOEING SERVICE BULLETIN 767-57-0068

E. Compliance

Boeing recommends the Part 1 - Rework be completed within 5000 flight-cycles or 22 months,

whichever is earlier from the initial release date of this service bulletin. Boeing recommends the

PART 2 - Additional Work be completed within 48 months from the release date 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.

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 modification defined in this service bulletin as an alternative

method of compliance to the requirements of paragraph (c) 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

The tables below show an estimate of the man-hours necessary to do the changes for each airplane.

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 1 - Rework

Task Number of Persons Man-Hours Elapsed Time (Hours)

Open Main Tank and

Dry Bay Access Panels

4 13 3.25

Remove and Install

Bonding Assembly

2 2 1

Close Main Tank

Access Panels / Refuel

4 7 1.75

Perform Leak Check 2 2 1

Close Dry Bay Access

Panels

2 1 .5

TOTAL FOR EACH AIRPLANE 25 7.5

September 16, 1999 767-57-0068

Revision 1: May 9, 2002 5
BOEING SERVICE BULLETIN 767-57-0068

Part 2 - Additional Work

Task Number of Persons Man-Hours Elapsed Time (Hours)

Open Main Tank

Access Panels

4 8 2

Rework Bonding

Jumper Assembly

2 2 1

Close Main Tank

Access Panels

4 4 1

TOTAL FOR EACH AIRPLANE 14 4

H. Weight and Balance Changes

Change in Weight Change in Moment

Airplane (Pounds) (Pound-Inches)

+ 0.4 lbs + 364.0 lb-in

I. Electrical Load Data

Not changed

September 16, 1999 767-57-0068

Revision 1: May 9, 2002 6
BOEING SERVICE BULLETIN 767-57-0068

J. References

1. Existing Data:

a. Engineering Change Memo PRRB13024, PRRB12900-133

b. 767 Maintenance Manual (AMM) Subject 12-11-01, 28-11-00 and 28-26-00

c. Boeing Standard Wiring Practices Manual (BSWPM) 20-20-00

d. Boeing Standard Overhaul Practices Manual (BSOPM) 20-11-03, 20-41-02, 20-43-03, and

20-50-19

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

2. Data supplied with this service bulletin:

None

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

Drawing Number Title

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, 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 Illustrated Parts Catalog 57-40

767 Maintenance Manual 12-21, 28-11

L. Interchangeability and Intermixability of Parts

None

September 16, 1999 767-57-0068

Revision 1: May 9, 2002 7
BOEING SERVICE BULLETIN 767-57-0068

BLANK PAGE

September 16, 1999 767-57-0068

Revision 1: May 9, 2002 8
BOEING SERVICE BULLETIN 767-57-0068

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 (QTY) of kits, a supply sequence is given by Spares.

Unit Price thru

Kit Number Name Date QTY Jan 31/00

015T1623-1 Top Kit Nov 9/99 87 $ 322.00

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

acknowledgment. After the Unit Price date, new price 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 September 29, 1998. 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 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.

015T1623 TOP KIT - SLAT TRACK HOUSING ELECTROSTATIC

BONDING

-2 -1

Quantity Part Number Name

. - 015T1623-1 Top Kit

- 2 015T1623-2 Sub Kit

1 . 287T0020-325 Bracket

12 . BACB30FP6A4 Bolt

12 . BACC30M6 Collar

1 . BACJ40AC44-6 Jumper

1 . BACJ40AC44-8 Jumper

2 . BACN10YR3CD Nut

1 . BACN10YR3CM Nut

4 . BACR15FT6AD6 Rivet

1 . BACS12GU3K8 Screw

1 . BACS12GU3K9 Screw

September 16, 1999 767-57-0068

Revision 1: May 9, 2002 9
BOEING SERVICE BULLETIN 767-57-0068

(Continued)

015T1623 TOP KIT - SLAT TRACK HOUSING ELECTROSTATIC

BONDING

-2 -1

Quantity Part Number Name

4 . NAS1149C0316R Washer

2 . NAS1149C0363R Washer

5 . NAS1149D0316H Washer

2 . NAS1149D0363H Washer

1 . AN735C8 Clamp,

1 . AN735DC8 Clamp,

(a) The kit has more parts than are necessary for installation. Discard

parts that are not used or keep the parts for spares.

(c) If grip length shown is not available at Boeing, fasteners supplied in

kits may be one grip length longer than indicated.

2. Parts and Materials Supplied by the Operator:

QTY Part Number {Specification} Name

8 ounces BMS 10-20 Type II (a) Primer

8 ounces BMS 5-45 Class B (a) Sealant

(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

E. Existing Parts Accountability

None

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 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.

September 16, 1999 767-57-0068

Revision 1: May 9, 2002 10
BOEING SERVICE BULLETIN 767-57-0068

3. ACCOMPLISHMENT INSTRUCTIONS

GENERAL NOTES

1. The paragraphs identified with a letter give the general work instructions and the necessary tests.

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, other than rivet and bolt edge margins, is plus or minus 0.03

inch

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

- Angular tolerance is plus or minus 2 degrees

- Hole dimensions for standard solid rivets are given in 767 Structural Repair Manual, Chapter 51

- Torque limits to tighten nuts and bolts are given in 767 Structural Repair Manual, Chapter 51.

3. Alternative fasteners are given in 767 Structural Repair Manual, Chapter 51.

4. Obey all of the warnings and cautions given in the specified manual sections.

5. As an alternative to the Boeing specified manuals, operators equivalent procedures can be used.

6. More work is necessary on the airplanes reworked as shown in the initial release of this service

bulletin. Boeing recommends the PART 2 - Additional Work be completed within 48 months from

the release date of Revision 1 of this service bulletin.

WORK INSTRUCTIONS

PART 1 - REWORK

A. Defuel the main tanks as specified in 767 AMM 28-26-00.

B. Open the main tank 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 drain tube assembly.

Panel Number Location

533AB Left Wing Dry Bay

633AB Right Wing Dry Bay

532FB Left Wing Main Tank

632FB Right Wing Main Tank

C. Replace the bonding jumper assembly for the number 5 and 8 inboard slat track housing drain

tube installation as shown in Figure 1.

D. Close the main tank access panels listed below as specified in 767 AMM 28-11-00.

Panel Number Location

532FB Left Wing Main Tank

632FB Right Wing Main Tank

September 16, 1999 767-57-0068

Revision 1: May 9, 2002 11
BOEING SERVICE BULLETIN 767-57-0068

E. Refuel the main tanks as specified in 767 AMM 12-11-01.

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

for fuel leaks of the slat track drain tube assembly.

F. Perform a visual inspection of the number 5 and 8 inboard slat track housing drain tube opening,

located in the dry bay to make sure there are no fuel leaks.

G. Close the dry bay access panels listed below as specified in 767 AMM 28-11-00.

Panel Number Location

533AB Left Wing Dry Bay

633AB Right Wing Dry Bay

H. Put the airplane back to a serviceable condition.

PART 2 - ADDITIONAL WORK

A. Defuel the main tanks as specified in 767 AMM 28-26-00.

B. Open the main tank access panels listed below as specified in 767 AMM 28-11-00, to access the

number 5 and 8 inboard slat track housing drain tube assembly.

Panel Number Location

532FB Left Wing Main Tank

632FB Right Wing Main Tank

C. Rework the bonding jumper assembly for the number 5 and 8 inboard slat track housing drain tube

installation as shown in Figure 2.

D. Close the main tank access panels listed below as specified in 767 AMM 28-11-00.

Panel Number Location

532FB Left Wing Main Tank

632FB Right Wing Main Tank

E. Put the airplane back to a serviceable condition.

September 16, 1999 767-57-0068

Revision 1: May 9, 2002 12
BOEING SERVICE BULLETIN 767-57-0068

FIGURE TABLE OF CONTENTS

Title Page

FIGURE 1. INBOARD SLAT TRACK DRAIN TUBE ELECTROSTATIC BOND

REWORK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

FIGURE 2. INBOARD SLAT TRACK DRAIN TUBE ELECTROSTATIC BOND

ADDITIONAL WORK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

September 16, 1999 767-57-0068

Revision 1: May 9, 2002 13
BOEING SERVICE BULLETIN 767-57-0068

RIB NO. 9

WING LOWER

SKIN

HOUSING

SLAT TRACK

FRONT SPAR

SEE D

SEE B

A

SEE A

FWD INBD

UP

S96566

FIGURE 1. INBOARD SLAT TRACK DRAIN TUBE ELECTROSTATIC BOND REWORK

September 16, 1999 SHEET 1 OF 5 767-57-0068

Revision 1: May 9, 2002 14
BOEING SERVICE BULLETIN 767-57-0068

D

C 1 2 3 4

7

5

A-A

HOSE

FLEX

B

DRAIN

TUBE

SEE C

FWD

UP

C

E

.90

+/-0.10

(12 LOCATIONS)

JUMPER (b)

BONDING

ASSEMBLY

DOUBLER BRACKET

(4 LOCATIONS)

FWD

A

A

FWD INBD

UP

+/-0.10

4.20

S96671

FIGURE 1. INBOARD SLAT TRACK DRAIN TUBE ELECTROSTATIC BOND REWORK

September 16, 1999 SHEET 2 OF 5 767-57-0068

Revision 1: May 9, 2002 15
BOEING SERVICE BULLETIN 767-57-0068

JUMPER A

BONDING 6 7

6 7

WASHER B

WASHER C

WASHER E

WASHER F

CLAMP A

WASHER D

CLAMP B

BONDING JUMPER B

WASHER A WASHER D

JUMPER A

WASHER A

SCREW

NUT

BONDING

A

SCREW

B

BONDING NUT

D

ASSEMBLY

COUPLING

BONDING

6 7

S96762

FIGURE 1. INBOARD SLAT TRACK DRAIN TUBE ELECTROSTATIC BOND REWORK

September 16, 1999 SHEET 3 OF 5 767-57-0068

Revision 1: May 9, 2002 16
BOEING SERVICE BULLETIN 767-57-0068

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

The QTY numbers shown below are the numbers 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 by alternating

fastener removal, removing and installing

only 6 fasteners at a time. Alternating the

fastener removal and installation will

maintain the doubler assembly fuel seal

and prevent the potential of misalignment

during the drill and ream procedures.

2 Drill /

Ream

Holes 12 in the doubler assembly as indicated.

3 Install Fasteners --- 12 in the doubler assembly as indicated.

4 Apply Fillet Seal BMS 5-45 - to both ends of the (12) fasteners installed

in the doubler assembly. Refer to BSOPM Class B 20-50-19.

5 Install Bracket 287T0020-325 1 to the rib 9 stiffener as indicated. Refer to

BSOPM 20-11-03 and BSWPM 20-20-00

Fasteners for bonding requirements. --- 4

6 Remove /

Discard

Bonding Clamp AN735D8 2

Bonding Jumper BACJ40A20-6 1

Fasteners --- 2

7 Install Bonding

Clamp

"A" AN735DC8 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, 2 or 3 as applicable 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 "A"

and "B" 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" AN735C8 1

Bonding

Jumper

"A" BACJ40AC44-6 1

Bonding

Jumper

"B" BACJ40AC44-8 1

Fasteners --- 3

(a) Install bonding jumper "A" with the terminal end marked by a blue band to bonding clamp "B" and

connect the terminal end marked with a red band to bonding clamp "A". Install bonding jumper

"B" 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 1. INBOARD SLAT TRACK DRAIN TUBE ELECTROSTATIC BOND REWORK

September 16, 1999 SHEET 4 OF 5 767-57-0068

Revision 1: May 9, 2002 17
BOEING SERVICE BULLETIN 767-57-0068

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 lower right 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 BACS12GU3K8 ---

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 Screw BACS12GU3K9 ---

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

and as required to facilitate differences

in the washer stackup.

Washer "D" NAS1149C0316R

Washer "E" NAS1149C0363R

Washer "F" NAS1149C0316R Use two washers if and as required to

prevent crushing of drain tube.

Nut BACN10YR3CM

C Bolt BACB30FP6A4 0.1991 - 0.2011

Collar BACC30M6

D Rivet BACR15FT6AD6 0.191 - 0.202

E Washer NAS1149D0316H ---

Nut BACN10YR3CD

FIGURE 1. INBOARD SLAT TRACK DRAIN TUBE ELECTROSTATIC BOND REWORK

September 16, 1999 SHEET 5 OF 5 767-57-0068

Revision 1: May 9, 2002 18
BOEING SERVICE BULLETIN 767-57-0068

SEE B

RIB NO. 9

WING LOWER

SKIN

HOUSING

SLAT TRACK

FRONT SPAR

A

SEE A

FWD INBD

UP

V77922

FIGURE 2. INBOARD SLAT TRACK DRAIN TUBE ELECTROSTATIC BOND ADDITIONAL WORK

September 16, 1999 SHEET 1 OF 4 767-57-0068

Revision 1: May 9, 2002 19
BOEING SERVICE BULLETIN 767-57-0068

CLAMP B

BONDING 2 3

2 3

2 3

JUMPER B

BONDING

2 3

JUMPER A

BONDING

1

WASHER B

WASHER C

WASHER E

WASHER F

CLAMP A

WASHER D

WASHER A WASHER D

JUMPER A

WASHER A

SCREW

NUT

BONDING

A

SCREW

B

BONDING NUT

B

ASSEMBLY

COUPLING

V77923

FIGURE 2. INBOARD SLAT TRACK DRAIN TUBE ELECTROSTATIC BOND ADDITIONAL WORK

September 16, 1999 SHEET 2 OF 4 767-57-0068

Revision 1: May 9, 2002 20
BOEING SERVICE BULLETIN 767-57-0068

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

The QTY numbers shown below are the numbers of parts necessary for one side of the airplane.

STEP TASK NAME PART NUMBER QTY NOTES

1 Verify Bonding

Jumper

"A" BACJ40AC44-6 1 installation sequence matches Note (a).

NOTE: If the bonding jumper installation matches Note (a), no further action per Figure 2 is

required. If the bonding jumper installation is reversed, complete the following tasks to

correct the installation.

2 Remove /

Keep

Bonding

Clamp

"A" AN735DC8 1 Bonding jumper "B" does not need to be

removed at the terminal end connected to

the rib 9 stiffener. Bonding

Clamp

"B" AN735C8 1

Bonding

Jumper

"A" BACJ40AC44-6 1

Bonding

Jumper

"B" BACJ40AC44-8 1

Fasteners --- 2

3 Install Bonding

Clamp

"A" AN735DC8 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, 2 or 3 as applicable 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 "A"

and "B" 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" AN735C8 1

Bonding

Jumper

"A" BACJ40AC44-6 1

Bonding

Jumper

"B" BACJ40AC44-8 1

Fasteners --- 2

(a) Install bonding jumper "A" with the terminal end marked by a blue band to bonding clamp "B" and

connect the terminal end marked with a red band to bonding clamp "A". Install bonding jumper

"B" 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 2. INBOARD SLAT TRACK DRAIN TUBE ELECTROSTATIC BOND ADDITIONAL WORK

September 16, 1999 SHEET 3 OF 4 767-57-0068

Revision 1: May 9, 2002 21
BOEING SERVICE BULLETIN 767-57-0068

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 lower right corner gives the grip length of the fastener.

COUNTERSINK FASTENER

C

D

EXAMPLE OF FASTENER SYMBOL

LENGTH/GRIP

FASTENER

6F

7

LETTER CODE

DIAMETER

(OPTIONAL)

HEAD LOCATION

N = NEAR SIDE

F = FAR SIDE

(OPTIONAL)

(OPTIONAL)

V75018

CODE NAME PART NUMBER HOLE DIA NOTES

A Screw BACS12GU3K8 ---

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

and as required to facilitate differences

in the washer stackup.

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 Screw BACS12GU3K9 ---

Washer "D" NAS1149C0316R

Washer "E" NAS1149C0363R

Washer "F" NAS1149C0316R Use two washers if and as required to

prevent crushing of drain tube.

Nut BACN10YR3CM

FIGURE 2. INBOARD SLAT TRACK DRAIN TUBE ELECTROSTATIC BOND ADDITIONAL WORK

September 16, 1999 SHEET 4 OF 4 767-57-0068

Revision 1: May 9, 2002 22
Commercial

Airplane

Group

767

Service Bulletin

Number: 767-57-0068 Evaluation Form Date: September 16, 1999

Revision 1: May 9, 2002

ATA System: 5740 2781 2811

Prepared By: Robert Mehring

SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Slat Track Housing Electrostatic Bond

Rework

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