### 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 A SEE

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 UPS96564

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

D SEE B SEE



## A A SEE

FWD INBD UPS96566

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 

### 1234

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

4.20S96671

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 7 6 7 6 WASHER B WASHER C

WASHER E WASHER F CLAMP A WASHER D CLAMP B BONDING JUMPER B WASHER D WASHER A JUMPER A WASHER A SCREW

NUT BONDING A



### SCREW B



### BONDING NUT



## DASSEMBLY COUPLING BONDING 7 6S96762

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 NUMBERQTY 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 20-50-19. Class B 5 Install Bracket 287T0020-325 1 to the rib 9 stiffener as indicated. Refer to BSOPM 20-11-03 and BSWPM 20-20-00 for bonding requirements. Fasteners
--- 4 6 Remove / Discard Bonding Clamp AN735D8 2 Bonding JumperBACJ40A20-6 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 HEAD LOCATION LETTER CODE

D CB53324

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
--- ScrewBACS12GU3K*
--- 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



### B SEERIB NO. 9

WING LOWER SKIN HOUSING SLAT TRACK FRONT SPAR



## A A SEE

FWD INBD UPV77922

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 23 23

23 JUMPER B BONDING

23
JUMPER A BONDING 1 WASHER B WASHER C

WASHER E WASHER F CLAMP A WASHER D WASHER D WASHER A JUMPER A WASHER A SCREW

NUT BONDING A



### SCREW B



### BONDING NUT



## BASSEMBLY COUPLINGV77923

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 NUMBERQTY 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 Use this evaluation form to tell us what you think of the quality of this service bulletin. We will use the data that you give us to improve the quality of our service bulletins. NOTE: Please do not use this evaluation form to tell us to make changes to your manuals. To make these changes, please use a Publication Change Request (PCR) form. Please give us this data: (If necessary, please use the other side. Thank you for the time you used to give us your comments.) OPERATOR: TODAY'S DATE: PREPARED BY: TITLE: ORGANIZATION: TELEX CODE: TELEPHONE NUMBER: BASE: Please rate the quality of this service bulletin: (good)4321 (poor) Please rate the quality of the illustrations: (good)4321 (poor) Will you do the change given by this service bulletin? Yes No If not, please explain: Is this service bulletin easy to understand? Yes No If not, please explain: Is this service bulletin easy to use? Yes No If not, please explain: Are the Planning Information, Material Information, and Accomplishment Instructions accurate? Yes No If not, please explain: Is the Manpower estimate accurate? Yes No If not, please explain:
Give the completed evaluation form to your Boeing Field Service Representative or send the evaluation form directly to this address: Manager Service Bulletin Engineering Boeing Commercial Airplane Group P.O. Box 3707, Mail Stop 2H-37 Seattle, WA 98124-2207