# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN 

# * REVISION NOTICE 

# * FUEL- SFAR 88- DRY BAY ZONAL INSPECTION, INSPECTION/REPAIR OF STATIC GROUND TERMINALS OF FUEL SYSTEM PLUMBING, AND MARKING OF FUEL QUANTITY INDICATING SYSTEM WIRING Attached is Revision 4, dated September 18, 2008, to Service Bulletin 82-770/382-28-19. Information added or changed in this issu e is indicated by a vertical revision bar in the margin of affected pages, or pointing hand for i llustrations. This revision updates contact information, clarifies accomplishment instructions , and changes Section 2 , Paragraph C.(8)(a)2a to agree with text of Figure 29. This rev ision is a complete reiss ue and replaces Revision 3 of this Service Bulletin dated November 30 , 2006. Retain this notice w ith your copy of this Service Bulletin. Aircraft previously modified by this Service Bulletin should be re-inspected to ensure compl iance. Basic Revision 1 (Reissue) Revision 2 (Reissue) Revision 3 (Reissue)

_________ #
______ __ File: CSB 907 I M41 057 /1-3042

EXPORT CONTROLLED INFORMAT I ON October 17 , 2003 November 5, 2003 January 28, 2004 November 30, 2006

WARN ING • This document contains data whose export I s restricted by the Arms Export Control Act (Title 22, U
. S.C., Sec 2751, et seq.) as amended, or the Export Admin istration Act (Title 50, U
. S.C., App 2401 et seq.) as amended. Violations of these export laws are subject to severe c riminal and civ i l penalties.

C200& l0C(I'I£ f. O . \AA..

"C TIN COIV 'O'I: I\ T ON l OCI('i tiE D MAll: fiN PROP!t ' (. IAA Y I NFOIC,Al iON

Revision 4 , September 18 , 2008 

# 382-28-19 82-770

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN FUEL- SFAR 88- DRY BAY ZONAL INSPECTION, INSPECTION/REPAIR OF STATIC GROUND TERMINALS OF FUEL SYSTEM PLUMBING , AND MARKING OF FUEL QUANTITY INDICATING SYSTEM WIRING 1
. PLANNING INFORMATION A. 

### EFFECTIV ITY (1) 382-28-19, FAA Certificated Aircraft: This Service Bulletin is appl icab le to all model 382, 382B, 382E, 382F, and 382G series FAA Certifi cated Hercules airc raft (excluding 382J series aircraft). (2) 82-770 , Foreign Direct Sales Aircraft: This Service Bulletin is appl icable to a ll model 282, 382, 382C, and 382T series Hercules a ircraft (exclud i ng 382U and 382V series aircraft). (3) 82-770 , MAP/FMS/SAP Aircraft: Th is Service Bullet i n is app l icable to all mode l C-130 series He rcules a i rcraft (excluding C-130J Hercules ai rcraft)
. B. REASON (1) As part of compl iance with Special Federa l Av iation Regulation (SFAR) 88, the followi ng four requirements were identified, which are addressed in this Serv ice Bu lletin. Develop maintenance documents to implement repetitive deta i led i nspections for the Fuel Level Contro l Valve (FLCV) wires and conduits to verify there is no damage. Develop maintenance documents to i mp lement repet itive detailed inspections of the power wiring on the leading and trai l ing edges of the wing to verify that the separation of these wires to the tank wall has not been compromised
. This action is to preclude any arcing to the fuel tank
. This is the Zona l Inspection
. This ensures that the original design remains intact and is not defeated by subsequent installations and inspections. NOTE: Lockheed Martin used the Honeywell FG220A and FG430A class f uel quantity probes, not the Honeywell FG420A , Series 1, 2, and 3 that were brought into question by NTSB Recommendat ions A98-34 and A98-35
. Develop service i nformation to i mplement a program where any Honeywell Series 1 -3 Fue l Quantity tank probe connectors are rep laced with Series 4 type connectors
. • Develop service information to implement repetitive inspections of the fuel system electrical bonding system. These inspect ions should have meas urements for critical bonds (i
.e. electrical conduit, electrical components) and visual inspection for less critical bonds (i.e
. fuel tube static bonds). • Add identity marker for fuel quantity indicating system wire. EXPORT CONTROLLED INFORMATION WARNING. This document contains data whose export is restricted by the Arms Export Control Act (Title 22, U
. S
.C., Sec 2751, et seq.) as amended, or the Export Administration Act (Title 50, U.S.C., App 2401 et seq.) as amended. VIolations of these export laws are subject to severe criminal and civil pena l ties.



### October 17 , 2003 Revision 4, September 18, 2008 

# 382-28-19 82-770 Page 1 of 50 

# I

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN (2) The following background information resulted in a requ i rement to generate th is Service Bu ll etin
. (a) Federal Aviation Regulation (FAR) Section 25
. 901 (b)(4) requires electrically bond i ng the major components of the propulsion system to other parts of the aircraft. The affected major components of the propulsion system include the fuel tank system
. Compliance with this requ irement for fuel tank systems must be demonstrated by showi ng that all major components of the fuel tank are electrically bonded to the airplane structure
. This precludes accumulation of electrical charges on the components and the possible arcing in the fuel tank that could otherwise occur. In most cases, electrical bonding is accomplished by installing jumper wires from each major fue l tank system component to the airplane structure. Advisory Circular (AC) 25-8, "Auxiliary Fue l Tank I nstallat ions," also provides guidance for bonding of fue l tank system components and means of precluding ignition sources w ithin transport airplane fuel tanks
. (b) FAR Section 25
. 954 requires that the fuel tank system be designed and arranged to prevent the ignition of fuel vapor w ithin the system due to the effects of lightning strikes. Compliance with regulation is shown by i nco rporation of des ign features such as minimum fuel tank skin thickness, location of vent outlets out of likely lightning stri ke areas , and bonding of fuel tank system structure and components. Guidance for demonstrating compl iance with this regulation i s provided i n AC 20-53A , " Protecti on of Aircraft Fuel Systems Aga i nst Fuel Vapor Ignition Due to Lightning"
. (c) AC 25
.981-1C Draft paragraph 7
. C , requires several i nspections to verify that the components are in acceptable worki ng order and will not result in a catastroph ic event i n case of failure
. (3) An operator reported a fire in the No. 2 main tank
. Accord i ng to the operator, two of three breakers associated w ith the No. 2 fuel dump boost pump opened during a fuel tank purging operation. When the tank was entered to troubleshoot the failed boost pump , evidence of a fire was found
. A "teardown" of the pump in the lab found a conductor had an internal path to the pump housing (short). The lab also found that a non-conductive coating on the mounting base of the subject pump most likely prevented the pump from being electrically bonded to the aircraft structure
. These two findings support the theory that an arc occurred between the pump housing and a surrounding entity (possibly either a conduit or fuel line) and resulted in ignition of fuel vapors in the ullage areas of the fuel tank
. The mishap pump, P/N 60-371 D, SIN 9249, is not the correct part number for this app l icat ion. The correct part number is 60-37 1B
. The electrical conduit connection for this pump was altered for installation
. This may have been a contributing factor to the pump internal failure. (4) Lockheed Mart i n Aeronautics Company recommends that those operators who have not accomplished the previous revision to th is Service Bulletin comply with this revision on each affected aircraft at the next heavy mai ntenance but no later than 1 year after receipt of this Service Bulletin. Lockheed Martin Aeronauti cs Company further recommends that the Fuel Quantity Indicating System W ire Marker modification specified in Section 2 , Paragraph C(8)(b) herein be accompl ished duri ng this in spection or at the next heavy ma i ntenance period afte r January 1 , 2008
. (5) A i rcraft previously mod ifi ed by this Service Bulletin are affected by this revision by add i ng identity marker for fuel quantity i nd i cating system wire
. 

# 382-28-19 82-770 October 17, 2003 Page 2 Revision 4, September 18, 2008 (Reissue)

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN C. DESCRIPTION This Service Bulletin consists of visual/electrical inspections of fuel system plumbing grounding/bonding connections for corrosion and/or inco rrect resistance, misplaced or inappropriate ly installed grounding/bonding jumpe rs , i nstallation of new grounding/bonding jumpers , visual inspection of fuel system electrical wires. and visual i nspection of fuel tanks for contamination. Th is Zonal Inspection further expands into any system capable of developing enough energy to cause an ignition of the fuel system or is a source of fuel for a primary/root cause fi re. This Service Bulletin also modifies fuel quantity i ndicating system (FQIS) wiring by installation of color coded identificatio n cable marke rs or heat shrink sleeving to the existing FQIS wires from plugs that exit the fuel tanks or bladders, through outer wing breaks and wheel well pressure breaks to the individual fuel tank i ndicator plugs on the Fuel System Control Panel. D
. APPROVAL (1) The aircraft owner/operator shall make an appropriate entry in the aircraft log records upon compliance with this Service Bulletin
. (2) Please complete and mail a Notice of Service Bulletin Compliance after the work has been completed on each affected aircraft. (3) 382-28-19, FAA Certificated Aircraft: The rework instructions desc ribed in this Service Bulletin have been approved by the FAA as complying with applicable Federal Aviation Regulations. E
. MANPOWE R NOTE: This Service Bullet i n is based upon the configuration of the aircraft as it was delivered from Lockheed Martin. Previous service bulletins issued by Lockheed Martin have been considered in the preparation of this Service Bulletin, but no considerat ion has been g iven to peculiar changes made to the ai rcraft by the owner/operator since its delivery
. The work prescribed in this Service Bulletin has not been performed at the Lockheed Martin faci lity exactly as described herein
. Therefore, the manpower estimates prov ided have not been validated, and should not be construed as being acceptable for use in making fixed price quotes for accompl ishment of the work
. These estimates are provided only as a conven ience fo r customer planning purposes . It is esti mated that approximately 952 man-hours (a crew of 4) will be required to accomplish the work described herein on each affected aircraft. Th is inspection will take approximately 238 hours elapsed time while the aircraft is out of service
. F
. MATER IAL Parts li sted in paragraph 3 may also be purchased from Lockheed Martin, as noted , if desi red
. Direct i nquiries concerning prices and availabi l ity to the following:

October 17, 2003 Phone : (877)456-7278 E-Mail : 4
. 1mparts@lmco
.com

Mail: Lockheed Martin G lobal Supply Chain Services 210 I ndustrial Park Road Johnstown , PA 15904 , USA

Revision 4 , September 18 , 2008 

# 382-28-19 82-770 Page 3

# HERCULES Loc kheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN G. TOOLING AVTRON model T477W, P/N C15292 Bond i ng Meter with PIN C22161 Pistol Grip Probe or equiva l ent Stainless Steel Rotary Brush Manual or Power Drill Abrasive Paper or Cloth Sheet (150 to 400 grit alum i num oxide) H
. WEIGHT AND BALANCE Not Appl icable I. REFERENCES Special Federal Aviation Regulation 88 Federa l Aviation Regulation Section 25.901 Federa l Aviation Regulat ion Section 25.954 Advisory Circular 25-8 Advisory Circular 20-53A Hercules Wiring Diagram Manual Advisory Circular 25
.981-1 C Draft SAE-AS81531 , Marking of Electrical Insulating Materials Hercules Corrosion Prevention and Control Manual (1) 382-28-19, FAA Certificated Aircraft: Hercules Ma in tenance Manual Hercules Airfreighter Progressive Inspection Procedures (2) 82-770, Foreign Military Aircraft : Hercules Maintenance Instructions Manua l Hercules Airfreighter Series Progressive Inspection Procedures J. OTHER PUBLICATIONS AFFECTED (1) 382-28-19, FAA Certificated Aircraft : Hercules Airfreighter Progressive Inspect ion Procedures (2) 82-770, Foreign Military Aircraft: Hercules Airfreighter Series Progressive Inspection Procedures 

# 382-28-19 82-770 USE ,**CO~YINO; ,**  Ml).Qlt OlSCI.OSUR! i $ OOVER'I IEO 8Y lH E S llol EM ! 'I I 0 ";" lHf. flrt.lt PAG! 0 ' 111 :$ OOC:U U !MI October 17 , 2003 Page 4 Revision 4 , September 18 , 2008 (Reissue)

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN 2. ACCOMPLISHMENT INSTRUCTIONS WARNING: ENSURE THAT APPLICABLE SAFETY PRECAUTIONS PERTAINING TO WORK IN FUEL/FUME AREAS ARE STRICTLY OBSERVED
. PERSONNEL SHALL WEAR NONSPARKING PROTECTIVE CLOTHING. ENTRY INTO TANKS AND DRY BAY MUST NOT BE MADE UNTIL AREAS HAVE BEEN PURGED TO A F IRE -SAFE 20 PERCENT LOWER EXPLOSION LIMIT (LEL) , AS DETERMINED USING FUE L VAPOR DETECTION AND MEASURING EQUIPMENT. FULL-FACE RESPIRATORS MUST BE WORN UNTIL AREA HAS BEEN PURGED TO THE HEALTH-SAFE 0.0- TO 1
.5-PERCENT LELAND 19
.5 PERCENT OXYGEN CONTENT. FAILURE TO COMPLY MAY RESULT IN SERIOUS INJURY OR DEATH. WARNING: FUE L TANK DEFUELING, DRAINING, PURGING AND MAINTENANCE REQUIRING ENTRY INTO THE TANK(S) SHALL BE PERFORMED ONLY IN DESIGNATED AREAS HAVING CLEAR ACCESS PATHS FOR FIRE FIGHTING AND EMERGENCY EQUIPMENT. THESE AREA(S) SHALL BE PROMINENTLY IDENTIFIED AS FUEL SYSTEM WORK AREA(S) AND POSTED WITH NO SMOKING AND AUTHORIZED PERSONNEL ONLY SIGNS
. WARNING: PORTABLE FIRE EXTINGUISHERS MUST BE POSITIONED IN CONVENIENT LOCATIONS
. FIRE F IGH TING PERSONNEL AND EQUIPMENT SHALL BE STATIONED NEARBY DURING DEFUELING, DRAINING, AND PURGING OPERATIONS
. CAUTION: MAINTENANCE AND INS TALLATION PERSONNEL MUST EXERCISE CAUTION WHILE INCORPORATING TH IS SERVICE BULLETIN TO ENSURE THAT WIRING SYSTEMS ARE PROTECTED AND KEPT CLEAN AT ALL TIMES
. NOTE THAT METAL SHAVINGS CAUSED BY DRILLING AND OTHER FORMS OF DEBRIS THAT CONTACT WIRE BUNDLES MAY IM PAIR WIRE SYSTEM INTEGRITY AND SHORTEN SYSTEM AND COMPONENT SERVIES LIFE
. CAUTION: DO NOT ATTEMPT TO AIR-PURGE TANKS IF AN ELECTRICAL STORM OR WIND IN EXCESS OF 15 KNOTS IS FORECAST. DUST OR OTHER FOREIGN MATTER MAY ENTER THE TANK OPENINGS. 

### A PREPARE A I RCRAFT FOR INSPECTION AND/OR MODIFICATION WARNING: ALL EQU I PMENT, INCLUDING WORK STANDS, SHALL BE ELECTRICALLY GROUNDED TO THE AIRPLANE AND TO AN APPROVED GROUNDING POST. GROUND WIRES SHALL BE SECURELY ATTACHED TO CONNECTING PO I NTS TO MINIMIZE ACCIDENTAL DISCONNECTION
. WORK STANDS SHALL BE EQUIPPED W ITH COPPER. ZINC , OR ZINC-COATED GROUNDING PLATES THAT CAN BE CONVENIENTLY CONTACTED BY PERSONNEL ENTERING THE WORK AREA
. (1) 

### Static ground aircraft in accordance with appropriate Hercules Maintenance Manual or Hercu les Maintenance Instructions Manual. (2) Lower flaps to full down position to allow access to w i ng tra i l ing edge
. (3) Remove electrical power from aircraft (including external ground power). Disconnect aircraft battery and tag battery cable.

October 17 , 2003 USE, COPYI NG, A'ii).()FI 0 !$Cl0S V RE**IS GOVE~SfO**  81 Tt;[ SfAJft.I [ Nl ON hiE TITlE PAO t O F T HI S OOCU irot E'i l 

### Revision 4, September 18, 2008 (Reiss ue) 

# 382-28-19 82-770 Page 5

# HERCULES Lockheed Martin Aeronautics Compa ny Marietta, Georgia 30063 

# SERVICE BULLETIN (4) Rope off an area for a 50 -foot radius from all open tanks and vents. Post fuel hazard banners or signs i n the area . (5) Remove access panels to fuel tanks , dry bays , wing t raili ng edges , py lon tank(s) and cross beam sect ions as needed
. (6) Air-purge tank(s) as descri bed i n appropriate Hercu les Ma i ntenance Manua l or Hercules Ma i ntenance Instructions Manua l. After fumes have dissipated , ma i nta i n a cont i nuous supply of fresh air for personnel worki ng in the tank(s)
. CAUT I O N : WORK DIRECTLY ASSOC IATED WITH TH I S SERV I CE BULLETIN SHALL BE ALLOWED ONLY DURING F UEL TANK MAINTENANCE
. CAUTIO N : AT ALL T I MES, CARE MUST BE TAKEN TO PREVENT ENTRY OF CONTAM I NANTS INTO THE FUEL TANK( S) THROUGH THE OPEN I NG
. OPENING SHALL BE COVERED W I TH LINT-FREE CHEESECLOTH WHENEVER T HE TANK COVERS ARE REMOVED AND WORK IS NOT I N PROGRESS
. CA UTI ON: USE RUBBER MATS TO PROTECT THE BOTTOM OF TANK(S)
. NOTE: Should any inspection fail , rework the failed article i n accordance with Hercu les Corrosion Prevention and Control Manual. B
. INSIDE FUEL TANKS (1) V isual I nspection Perform all i nspections descri bed i n the fo ll owing paragraphs
. Us i ng a hi gh powe red explos ion-p roof light , i nspect all grou nd/bonding jumpers attach ed to f ue l components (tubes , plumb in g adapte rs , tube connect ions) fo r evi dence of corros ion and security
. Visible corrosion is defi ned as disco lorat ion, jumpe r strand separation , or jumper strand b reakage and all are cause for reject ion and repair or rep lacement. (a) Bonding Jumpers : 1 Inspect for corrosion of bonding jumper wires
. Corrosion can result in failure of the jumper
. 

### g I nspect ground attach ment po i nts for good contact and t ightness
.**~** 

### I nspect fo r jumpe rs that are worn o r f rayed
.**~** 

### I nspect all tub i ng and p l umb i ng fitt i ngs greate r than 3 i nches in length for presence of bonding jumpers or other means of bonding
.**~** 

### Any bonding jumper or attach points that fail the visua l i nspect ion should be reworked in accordance with Hercu les Corrosion Prevention and Co nt rol Manua l


# 382-28-19 82-770 Ull C:C>Pl' !NO**A.~O~~** D SC1.0SUU f SGOV'EIIIN£01V**f'"[SI AT** **l** 0'11 fH t fnlt P..U!O" f H !SOOCVM.f.IH 

### October 17, 2003 Page 6 Revision 4 , September 18, 2008 (Reissue)

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN (b) Electrical Wiring Conduits in Tank Ensure that. where electric wires are route d through conduits installed in a fuel tank; these conduits show no evidence of high surface temperatures or arcing through the conduit wall. All wiring conducting power (e.g. , fuel pump(s) , power supplies, fuel level sensor(s), Fue l Level Control Valves (FLCV), etc.) into or through a fuel tank should be evaluated assuming arcing to surfaces such as metallic conduits or wing surfaces , unless fail-safe protective features are provided
. If evidence of arcing is present rework or replace the conduit. (c) Fuel Quantity Indicating System (FQIS) Wiring 

## ! Ensure that wires are not spot tied inside fuel tanks. NOTE: Steps 

### f.**and~** are not applicable to Lockheed Martin serial numbers 4 144 through 4715 and aircraft with bayonet type connectors. 

### f. Ensure that shields are terminated within 0.5-inch of the HI-Z terminal lug using solder sleeves and 20 AWG jumper wire (if required).**~** Ensure that terminal lug size on FQIS wires are : • Hl-Z- size 6. • LO-Z- size 10
. • Ground - size 8. 

### 1 Should FQIS wiring not be in accordance with steps 1, 2, or 3 above ensure it is brought within specification immediate ly
.

October 17
. 2003 US ! , COPYcHG**A. O~**  O ISCLC»U'!:£**SGO VU** **t: ::I** **Y** fHt Sl A lEioi ! !H O !II I ME Hll E**PAU O~**  1 14tS OOCU M ! Nl Revision 4 , September 18 , 2008 (Reissue) 

# 382-28-19 82-770 Page 7

# HERCULES Lockheed Martin Aeronautics Company Marietta , Georgia 30063 

# SERVICE BULLETIN (d) Other Items : 

## 1 Inspect for corros ion that cou ld d i minish the effectiveness of the bonding surfaces for al l fuel tank access panels.**~** 

### Inspect for loose or corroded rivets that are along the bond-path for any component that is to be bonded
. For example , inspect the rivets used to in stall any bracket that a pump or va lve is bonded to , or a bracket that a bonding jumper is terminated to it. NOTE: If i nspection revea ls a missing or deteriorated bonding jumpe r , or if bond in g jumpe rs fa i l i nspection, the bonding jumper is to be removed and replaced
. Jumpers meeting the requirements of M I L-C-83413/8 type C (part number M83413/8-C(Iength)(lug)(lug)) are the preferred replacement bonding jumper ins ide the fuel tank , but if not avai lable i n stock, MS25083-2 bonding jumpe rs are authorized for use i n f ue l ce ll s . Refer to the following chart for bond i ng jumpers i nside of fue l tanks only: REPLACEMENT JUMPER M83413/8-C00488 M83413/8-C00488 M83413/8-C 00688 M83413/8-C00488 M83413/8-C00788 M83413/8-C00488 (2) Fuel Pump Inspection EXISTING JUMPER MS25083-1 883 MS25083-1 884 MS25083-1 886 MS25083-2884 MS25083-2887 MS25083- 3884

WARNING: ENSURE METER IS CERTIFIED FOR USE IN FUEL OR OXYGEN-R I CH EXPLOS IVE ENVIRONMENTS
. FA I LURE TO COMPLY MAY RESULT IN SEVERE I NJURY OR DEATH. I nspect all fuel pumps to ensure p roper grounding
. NOTE: Maximum res istance between aircraft structure and fuel pump shou ld be 0
. 37 m illiohms
. (a) Remove every fue l pump in accordance with appropriate Hercu les Maintenance Manual or Hercules Ma i ntenance Instructions Manual. (b) C lean the fay in g surface of each pump to remove all anod ized coating in accordance with paragraph (14)
. (c) Clean the aircraft mountin g surface for each pump to remove all pri mer in accordance w ith paragraph (14)
. 

# 382-28-19 82-770**t.. oP** **VI H3** **() 'II** **clo su** **~~: Go** **'l r:o** **ev tt** **srAJ ,..** **lo -.**  '" E l l h. EP.tO Eo" r n;$ oocu "' ' "'' October 17 , 2003 

### Page 8 Revision 4, September 18, 2008 (Reissue)

# HERCULES Lockheed Martin Aeronautics Company Ma rietta, Georgia 30063 

# SERVICE BULLETIN (d) Reinstall fuel pumps in accordance with appropriate Hercu les Ma i ntenance Manual or Hercules Maintenance Instructions Manual. (e) Perform resistance measurement in accordance with paragraph (4)
. (f) If the resistance check fails repeat steps (a) through (e) above
. (3) Fuel Level Control Valve (FLCV) Check conduit for evide nce of arcing or d iscoloration. NOTE: Should the conduit show evidence of arcing or discoloration replace it. (4) Grounding/Bonding Measurements WARNING: ENSURE METER IS CERTIFIED FOR USE IN FUE L OR OXYGEN-RICH EXPLOSIVE ENVIRONMENTS. FAILURE TO COMPLY MAY RESULT I N SEVERE INJURY OR DEATH. The max i mum resistance between aircraft structure and the following should be: • Fuel pump and associated conduit- 0.37 milliohms. • FLCV and associated conduit- 1
. 86 milliohms
. • Fuel tank access panels - 0.37 milliohms. • Fuel li nes - 1.00 ohm
. Perform res istance measurements on all fuel pumps and Fuel Level Control Valves (FLCV) in accordance with paragraphs (5) through (17). NOTE: If the measurement fails the test , the bonding/grounding terminat ion shall be reworked and retested until the resistance is less t han maximum listed above. (5) Bonding Verification Bonding verification should be performed and identified at a logical point so that any rework can be accomplished in a timely manner. (a) Measure bond resistance with connector plugs removed from equipment mounted on plastic tanks , pipes, etc. (b) In all cases , the resistance values refer to the overall resistance measured across the bond interface from the object to structure into which the bond is installed, unless otherwise i ndicated
. (c) Measurement instrument probes will be applied as near as possible to the bond
.

October 17 ' 2003 US! , COP YI NO, A.-. 0 ,0,11**SCl II:** **SGOV !:** **It N!O!I** **Y StAr** **,., fO** **~** U 1 t Wl!
... .. .. :a:o, hH$ oocuu E N f Revision 4, September 18, 2008 (Reissue) 

# 382-28-19 82-770 Page 9

# HERCULES Lockheed Martin Aeronautics Company Marietta , Georgia 30063 

# SERVICE BULLETIN (d) For bonds using a jumper or ground lead , the point for measuring the resistance will be any cleaned area on the same piece of metal , with i n 4-inches of the jumper or ground lead terminal be i ng checked
. ( e) Do not use test currents i n excess of 50 amps when measuri ng the bond res istance of current ground paths
. NOTE : Notify the loca l Fire and Safety Authority , or equivalent , and obtain perm iss ion before measuring bond resistance in any area where pure oxygen may combine with any foss il fuel or combustible l iquid
. (f) All meters used for measuring bonding resistance will have the appropriate certified measuring range . (g ) Do not measure bonding resistance from an insu l ated termina l. 

### 1 I nstall a dummy ( uninsu lated) terminal and take the measurement from that termina l.**~** Do not pierce the insulation of terminals
. (h) Impressions on electrica l wire terminals caused by resistance measuring equipment that do not expose th e base metal are acceptable. (i) Any part from wh ich the original finish has been removed to perform bonding resistance measurements will be refinished in accordance with paragraph (15)
. (j ) Perform a bond i ng meter check , when a un it requ i ri ng e l ectrical bonding i s removed and rep laced , before the i nsta ll ation /reinsta ll ation is accepted by Qua l ity Assu rance . (k) Should any inspection point fail the visual (corrosion) or resistance inspection , that item shall be reworked in accordance with Hercules Corrosion Prevention and Control Manual.



# 382-28-19 82-770 October 17, 2003 Page 10 Revision 4, September 18 , 2008 (Reissue)

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN (6) Resistance Measureme nt of Grounds WARNING: ENSURE METER IS CERTI FIED FOR USE IN FUEL OR OXYGEN-RICH EXPLOSIVE ENV I RONMENTS. FA I LURE TO COMPLY MAY RESULT IN SEVERE IN JURY OR DEATH. For d i rect meas u rement with a bonding meter, use secondary structure-to-primary structure bonds for res istance measurement. (See figures 1 , 2 , and 3.)



# / PRIMARY STRUCTURE BOND I NG METER

PRIMARY STRUCT URE 

# =---- STRUCTURE IN TERFACE 

# ---- ..!

PR E- INST ALLED BUILDUP DIRECT BU I LDUP RESISTANCE MEASUREMENT MUST BE AS CLOSE AS POSSIBLE TO BOND UNLESS OTHERWISE DICTATED
.



### Figure 1 Direct Resistance Measurement of Current Return Grou nds

October 17 , 2003 USE**COP V:.** **~Q .** **11. '10.0~** **01$C~O$ RE**  i S GOVERN E D I V THE STAT E iot ( 'I J 0'1 fHE l ! TU: PAQ( OF TH IS OOCV U (N t 

### Revision 4, September 18, 2008 (R eissue) SFAR- 88 - S B-2- 00 1



# 382-28-19 82-770 Page 11

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN

PR I MARY STRUCTU RE BOND I NG METER

SECONDARY STRUCTURE (BRACKE T)

Figure 2 BONDING JUMPER

SFAR- 8 8
- SB- l

- 002A Direct Resistance Measurement of a Bond i ng Jumpe r



# 382-28-19 82-770 Page 12 October 17, 2003 Revi sion 4 , September 18, 2008 (Re issue)

# HERCULES L ockheed Martin Aeronautics Company Marietta , Georgia 30063 

# SERVICE BULLETIN

PRIMARY STRUCTURE BONDING METER

SECONDARY STRUCTURE (BRACKET)

Figure 3 Direct Resistance Measurement of a Stud I nstallation

October 17, 2003 US( , COP Y NG A.'II O tOII OISCLOSU U!SGOVflt 'o f.0 1'1'1 otf.STAi l , ( HI O N 1,. (**TIT ~l** **ft AQl**  0'**3** OOCU\I l " l Revis io n 4 , September 18, 2008 (Reissue) SFAR-88
- SB
- 1
- 0026



# 382-28 - 19 82-770 Page 13

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN (7) Resistance Measureme nt of Faying Surfaces For resista nce measurement of fayi ng surfaces , reference paragraph (6) fo r meter connect ion procedu res and figure 

### 4.



# 382-28-19 82-770 Page 14 BONDI N G MET ER

FAYING SUR FAC E BOND
SFAR-88- SB - I - 003A Figure 

### 4 Resistance Measu rement of Faying Surface Bonds

US E, COPYiNG, A."ii).QR O.SC I.. OS I.IRE IS CO\It1tNfO !lY fHf S I AI !MfNl 0 , '1**H~f** f lllf**P~ E**  OF Tt1 iS OOCU iot EH f October 

### 17 . 2003 Revision 

### 4, September 

### 18 , 2008 (Reissue)

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN (8) Resistance Measurement Across Hydraulic Fittings and Tub ing Installations For res istance measurement across hydraulic fittings and tubing installations, reference paragraph (6) for meter connect ion procedures and figure 5
.

/ BONDING METER

BONDING METER

Figure 5 Resistance Measurement of Hyd raulic Fitti ngs and Tubing Installations

October 17, 2003 US! COI'Y!HG A"ii),()lt DdClOSU't!: 1 $GOVfJtNf08Yl"E SfA.f(.UfN t ON T HE flll,. t, PAG tOF HUSOOC UU!.N f Revision 4 , September 18 , 2008 (Re issue) SFA R-88-SB-1-004A



# 382-28-19 82-770 Page 15

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN (9) Resistance Measurement of Tube- To -Bu lkhead Fittings For resistance measurement of tube-to-bulkhead fittings, reference paragraph (6) for meter connection procedures and figure 6.

_... BOND I NG METER

END OF FITTING

SFA R - 88 - SB - 1 - 0 0 48 Figure 6 Resistance Measurement of Tube -To-Bulkhead Fittings
(1 0) Resistance Measurement of Bulkhead Fittings to Primary Structure For resistance measurement of bulkhead fittings to primary structure, reference paragraph (6) for meter connection procedures and figure 7
.



# 382-28-19 82-770 Page 16 ---BONDING METER

END OF FITTING
SFAR -88-SB-1-005 Figure 7 Resistance Measurement of Bulkhead Fittings to Primary Structure

VS!**CO~~'V HG** **, A~** **O.O~** OI S ClO SU,_E 1$ GO IIERNE O BY THE St ATE\II E N f**~** li't E lf l L

E P-'QE Of ll h $ CXX:U"'
- f Nl October 17, 2003 Revision 4 , September 18, 2008 (Reissue)

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georg ia 30063 

# SERVICE BULLETIN ( 11) Repairs When repairs are necessary, appropriate cleaning and surface preparation is required. Refer to paragraph (12} for cleaning methods and procedures. (12) Cleaning Methods and Procedures The following paragraphs provide approved cleaning methods and procedures
. (a) Abrasive Cleaning -Cleaning Method 1 

## 1 Anodic films vary in t hick ness and may be very difficult to remove with a wire brush. 

### f. If wire brushing fails to remove anodic film , use an abrasive disc. Ensure the area is cleaned properly if a disc is used.**~** Any one, or combination, of the following procedures will be used followed by a solvent wipe with a clean dry cloth
. NOTE: Comp lete the electrica l bond within 4 hours after completing the following procedures.**~** Method 1 - Abrasive Sheet**~** Abrasive sheets will be reused only on the same type of material on which they were used originally. 

### Q The surface will be prepared by hand, using Cleaning Method 3- paragraph (12)(c). 

### f A circular motion will be maintained with the abrasive sheet. 

### Q. The operation will be continued until the coating is removed , and a clean, bare metal surface is visible throughout the required bond area. §. Method 1 - Stainless Steel Rotary Brush

October 17 , 2003**~** The surface will be prepared using a rotary, sta i nless steel brush , mounted in a manual or power drill. 

### Q The wire brush is to be used with light , intermittent pressure , keeping the cutting face parallel with the surface being prepared
. 

### £ The results m ust be inspected after each intermittent application
. 

### Q. A minimum of the metal structure , carbon-composite structure, or conductive finish will be removed to expose a clean, bare metal surface throughout the required bond area.

US!:**IH AN** **OQ'l0 0SU.II:f** **OVf.II: f0** **(U 'T-tES** **A.r W:[** **Nf N**  hi [ rlf l.l:**P~ fO** **F** n mo OOCUM f. H I 

# 382-28-19 82-770 Revision 4 , September 18 , 2008 (Reissue) Page 17

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN §. Method 1 - Abrasive Disc**~** The surface will be prepared using a 150 to 400 grit abrasive pape r or cloth disc. 

### Q. The abrasive disc must be fixed to a rotary mandrel mounted on a manu a l or power drill and the appropriate s ized mandrel selected
. 

### £ As an alternate material , a fine or very fine Scotch-Brite or Bear-Tex pad disc wetted w ith water may be used
. 

## 9. The abrasive disc will be re-used only on the same type material on which it was originally used.**~** The abrasive d isc will be used with li ght , intermittent pressure, keeping the cutting face pa rallel with the surface being prepared
. f The operat ion will be cont inued until the coat i ng is removed and a clean , bare meta l surface is visib le throughout the requ i red bond area . 

### 9. The d i sc must be replaced when it becomes plugged with the material being removed. 

## b. Only a minimum of the metal will be removed. (b) Light Abrasive Cleaning - Cleaning Method 2 

## 1 Any one , or combination , of the following procedures will be used fo llowed by a solvent wipe with a clean dry cloth
.**~** Comp lete electrical bond within 4 hours after these procedures
. 

### ;! See paragraph (13) for treatment of surfaces cleaned with this method
. 

### 1 Method 2 - Abrasive Sheet**~** Abrasive sheets will be re-used only on the same type of material on which they were used orig i nally
. 

### Q. The surface mu st be prepared by han d , usin g an abrasive sheet of paper or clot h (240 to 400 g ri t), or very fine to u ltra fine Scotch - Brite/Bear-Tex pads
. 

### £ A circular motion will be maintained with the abras ive sheet. 

## 9. The operation will be continued until the coating is removed and a clean, bare metal surface is v isible throughout the required bond area.



# 382-28-19 82-770 Ioiii CQltVI -.0**.: •~**  I)() ,. 0**SC OS** **Uit IS** **G0V f..l** **l.;f: 8'fl** **1'1li 1~** **1( l**  ON 11'1 (. I II LE I'AO l O!' fM tSOOCU-.. ! "1 1 October 17
. 2003 Page 18 Revision 4 , September 18 , 2008 (Reissue)

# HERCULES Lockheed Martin Aeronautics Company Marietta , Georgia 30063 

# SERVICE BULLETIN §. Met hod 2 - Abrasive Disc 

### ;a. The surface will be prepared using a 240 to 400 grit abrasive paper o r cloth d isc. 

### Q The abrasive d isc will be fixed to a rotary mandre l mounted on a manual or power drill and the appropriate sized mandre l selected
. £ As an a lternate materia l, a fi ne or very f i ne Scotch-Brite or Bear-Tex pad disc wetted w ith water m ay be used
. 

### Q. The abrasive disc must be re-used only on the same type material on which it was origina l ly used.**~** The abrasive d isc wi ll be used w ith light , intermittent pressure , keepi ng the cutting face paralle l with the surface being prepa red
. The operat ion will be continued unti l the coat i ng is removed and a clean, bare metal surface is v is i ble throughout the requ i red bond area . 

### 9. The d isc must be replaced when it becomes plugged with the materia l be i ng removed
. 

### !:!. Only a minimum of the meta l will be removed. (c) So lvent Clea n ing -Clean i ng Method 3 Th is method wi ll be used fo r the c l eaning of termina ls, plated and C lass II conversion coated metals , and passivated CRES
. NOTE : When using this method , complete electrical bond within 24 hours
. 

## 1 Remove excess debris (chips, shavings , loose so i l, etc
. ) and excess grease , oi l , or other loose contamination f rom the bond area by vacuum i ng, w i ping , scrubbing, or other physical means .**~** Us i ng a non-metall i c b rush or wiper , clean a width approximately two times wider than the width of th e bond surface
.**~** Wipe off all solvent whi l e the surface is wet, using clean wiping material or non-meta ll ic bristle brush.**~** Apply li ght p ressure between the brush or wiper and t he surface
. 

### §. Avoid the use of excess ive amounts of so lvent. 

### §. Make app l ications of c l ean i ng solvent and wipi ng (or brus h ing) , using c l ean materials , unti l no residue is vis i ble on the bond i ng surface area .

October 17 , 2003 Revis ion 4 , September 18 , 2008 (Re issue) 

# 382-28-19 82-770 Page 19

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN (d) Light Abrasive Polish Cleaning -Cleaning Method 4 This method will be used for cleaning on scale free, lightly oxidized, bare titan ium alloys and nickel base alloy surfaces. NOTE : When using this method , complete electrical bond within 24 hours after cleaning
. 

## 1 Wash/solvent wipe bond area. 

## f. Abrade the faying surfaces with 400 grit aluminum oxide abrasive paper or cloth, ultra fine pads, or fine grit metal polish.**~** 

### Wipe off polishing residue with a dry, clean, soft , cotton cloth. (13) Treatment of Abrasively Cleaned Aluminum This procedure applies to aluminum that has been abrasively cleaned in accordance with pa ragraph (12)(a) and ( 12)(b). (a) Initiate this treatment step within 2 hours after the abrasive cleaning. (b) Re-clean the surfaces in accordance with paragraph (12)(c) if the 4-hour period is exceeded
. (c) Using a brush apply the conversion coating evenly and liberally to the surface. (14) Removal of Polysulfide Sealing Compounds from Faying Surfaces If the surface is to be electrically bonded , the polysulfide sealing compounds must be removed from the mating (faying) surfaces using non-metallic trimmers (scrapers). On the following surfaces , (See table 1) use the cleaning method specified: NOTE: The bond surfaces must be solvent cleaned using clean wipers soaked with solvent. (a) Group 1
. Cleaning Method 2- paragraph (12)(b). (b) Group 2. Passivated, plated and conversion coated
. Clean i ng Method 3- paragraph (12)(c). (c) Group 2. Primed, top coated and anodized. Clean i ng Method 1 -paragraph (12)(a)
.



# 382-28-19 82-770 USE, COPY',NG. A."iO.QR**~l S:.tRE**  ISCOV!.ItN !D ISV 1 . -tt**S1Af[ [N** **r** ON HIE TillE P,tr,Q;f OF TtH$ 00C1./'wt[NT 

### October 17, 2003 Page 20 Revision 4, September 18 , 2008 (Reissue)

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN Table 1. Surface Cleaning Methods SURFACE CLEANING METHODS MATERIAL SURFACE FINISH CLEAN I NG CLEANING FINISH CODES METHOD AGENTS Primed Topcoat 1, F, S, A Abrasive paper, cloth, pads , and MIL-A-8625, 51 , 46 1 glass beads
. Type Il l Anodized 

### AAA Para. (12)(a) Brushes or discs Bare N/A Fine to ultra-fine GROUP 1: MIL-C-5541, F 2 abrasive paper ALUMINUM Class 1A Para. (12)(b) Cloth pads, discs, MIL-A-8625 , A metal polish Types I and II

Anodized MIL-C-5541, 

# s 3 Solvent Clean

Class 3 Para. (12)(c) Passivated M 3 Solvent Clean

(CRES) Para. (12)(c) Plated metals C , CC 3 Solvent Clean

Conversion G Para
. (12)(c)

Coatings Phosphate



## ---- 3 Solvent Clean Fluoride on Para
. ( 12)(c) GROUP 2: T itanium TITANIUM , Primed 1, 

## c. cc . 1 Abrasive paper, STEEL (M ILD TO HIGH STRENGTH M Para. (12)(a) cloth, pads, and Topcoat glass beads
. CRES) 51,46 Brushes or discs TERM I NALS Chromate 2 Fine to ultra-fine



# --- Conversion Para
. (12)(b) abrasive paper.

Coated cloth pads. d iscs, Cadm i um Plated metal polish Bare


## --- 4 Ultra-fine abrasive Para. (12)(d) paper. cloth , paper, metal polish See paragraphs ( 12) and ( 13) for time l imits.

October 17 , 2003 U$f: COP YI-.o • .-..-.o. Oit OI SCLOSU "f I SGOVt.NN ! OitY 111! SfMOol
.f NT**0~** IM( fl1lf PAC;£ Or ht1$00CU MfNT Revision 4, September 18 , 2008 (Reissue) ADDITIONAL INFO. Conversion coating Class 2. Post treatment required on bare a l uminum surface Conversion coating Class 2
. Post treatment required on bare aluminum surface

Includes previous

masked areas Inc ludes previous

masked areas Includes previous

masked areas
Incl udes previous

masked areas



## ---

- --

Includes masked areas


# 382-28-19 82-770 Page 21

# HERCULES Lockheed Martin Aeronaut ics Company Marietta , Georg ia 30063 

# SERVICE BULLETIN (15) Refinishing and/or Resea l in g (a) After assembly and bond res istance tests on the fasteners to structure , fray surface bonds , etc ., when requ i red ; reapp ly all prim ers and seala nts to within 1/32-i nch m i ni mum of bond joint or test probe area . (b) Masked areas for elect rical disconnect panels require no touch-up if the masked area after in sta ll ation is less than 1 /8-inch. 

### (c) Do not paint machine-finished flanges of fu e l or hydrau l ic p u mps , valves, and s imi la r equipment that must maintain a liquid-tight seal at the mounting surface
. {d) Any exposed surfaces, fro m which paint or other non-conductive coatings have been removed , must be reapp l ied
. ( e) Any surfaces which have had the a nod ic fi ni shes removed wi ll be refin ished with varnish
. 

### (f) Refinishing of the bonded areas of magnesium alloy parts must be completed with i n 24 hours of the removal of the protective fini sh
. (g) After assembly, clam ped, riveted, or bolted jo ints will be refinished with one coat of epoxy pri mer and a top coat to match the adjacent parts
. (16) Installation of Faying Surface Bonds (a) Prepare the faying surfaces us i ng the approp r iate clean i ng method p rovided i n paragraph ( 12). WAR NIN G : ENSURE METER IS CERTIFIED FOR USE IN FUEL OR OXYGEN-R I C H EXPLOSIVE ENV I RONMENTS. FA ILURE TO COMPLY MAY RESULT IN SEVERE INJURY OR DEATH
. (b) Measure the resistance of the bond
. • Fuel pump and associated conduit - 0
. 37 milliohms
. • FLCV and associated condu it- 1
. 86 m il liohms
. • Fue l tank access pane l s- 0
. 37 m ill iohms
. • Fue l l i nes- 1
. 00 ohm
. (c) Resistance testing made on all items must meet the bonding requ irements specifie d in this Serv ice Bulletin
.



# 382-28-19 82-770 Vst**'It ~O**  A.'IO.O III 0-SCl OS,

n t£ !$ GOvtJIINIO (1;'1' 1 " ' 1 1 At lV l N I 0 "" l "l flllf**~'IJ{Jf** OF ' " -' OOC .J \II( "'t October 17 , 2003 Page 22 Revision 4, September 18 , 2008 (Reissue)

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN (17) Assembly of Bond Jumpers and Ground Leads (a) Assemble jumper to plated steel , CRES, or titanium bolted connection as shown in figure 8.

SCREW (LK106V() ()) LOCKWASHER (MS35228( ))

LOCKWASHER (MS35338 ( )) _ .--- TERMINAL

WASHER (NAS11490())

SCREW (LK106V() ()) TERMINAL**~~---- ----~~** **------ ~** 

REFINISH AFTER INSTALLATION TO WITHIN 1/32 INCH OF WASHER STRUCTURE

CLEAN BASE METAL AN AREA 1 -1 /4 TIMES THE DIAMETER OF THE TERMINAL

SFAR-88-SB-0-006 CLEAN AND REFINISH IN ACCORDANCE WITH PARAGRAPHS (12) AND (15) USE ONLY TITANIUM OR CRES FASTENER COMPONENTS I N TITAN I UM STRUCTURE Figure 8 Jumper to Plated Steel, CRES, or Titanium Bolted Connection

October 17, 2003 US£. COPYING. ANO.O ,. OI SCLOSIJ:'IE IS GOVtlt NE D I Y fM! S t A 1L \II[Nf 0 "1 tl'l!. llll !**P~ !**  OF TH I $**OOCU~!. l**  Revision 4 , September 18, 2008 (Reissue) 

# 382-28-19 82-770 Page 23

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN (b) Assemble jumper to tube clamp connection as shown in figure 9.

CLAMP (MATERIAL AS APPLICABLE TO TUBE) BONDING OR CURRENT RETURN JUMPER

R E F IN ISH AFT ER INST ALLATION TO WITHIN 1132 INCH MINIMUM OF CLAMP. NOTE 2, 3

BRUSH OR FILLET SEAL ALL EDGES OF CLAMP



# ram REFINISH AFTER INSTALLATION TO WITHIN 1132 INCH MINIMUM OF HARDWARE
. NOTE 2, 3

SEALING COMPOUND TO COVER ALL PORTIONS OF ATTACHMENTS CLEAN TO BASE METAL AN AREA 1 -114 TIMES THE CLAMP W IDTH AND INSIDE OF CLAMP NOT E 1

CLEAN AREA OF CLAMP TAB THAT TOUCHES TERM INAL TO BASE METAL. NOTE 1

1
. CONTACT AREA PREPARAT ION 1 - 114 T IM ES CONTACT AREA
.



# 382-28-19 82-770 Page 24 2
. SEAL AN AREA 1-114 TIMES THE PREPARED AREA. WHEN REQUIRED. 3. REFINISH I N ACCORDANCE WITH PARAGRAPH (15)
.

SFAR-88-SB-0-007 Figure 9 Jumper to Tube Clamp Connection

October 17. 2003 Revision 4, September 18, 2008 (Reissue)

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN (c) Assemb le j umper to al uminum bolted connect ion as shown i n figure 10
.

PANEL 

# 11m LK200F() NUT

NAS1149D( )J FLAT WASHER LK106V() BO LT

1
. PREPARE SURFACE AREA I N ACCORDANCE Wl T H PARAGRAPH ( 12)
. 2
. REF I N I SH TO Wl THIN 1/32 I NC H M I NIMUM O F WASHER. 3
. SEAL I N ACCORDANC E WlTH PARAG RAPH ( 15) WHEN SEA LI NG I S REQUIRED
.



### Figure 10 J umper to Aluminum Bo lted Connection

October 17 , 2003 USIE COPYI ,. ::O. A)IIO .OJIII O !SC tOS U't ( IS GOVU 'II lO BY lti( SJAlh t [ N l ON TH( l +Hl llt Nl ( 01' f,.. I :S OOCUV tHl 

### Revision 4, September 18 , 2008 (Reissue) SF .AR-88 - SB - o-008



# 382-28-19 82-770 Page 25

# I



# I HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN C. ZONAL INSPECTION OF DRY BAY AREAS AND OTHER REQUIRED AREAS The Zonal Safety Analysis (ZSA) formed a part of the safety compliance documents required to meet the requirements of Federal Aviation Administration, Special Federal Aviation Regulation SFAR 88 "Transport Airplane Fuel Tank System Design Review, Flammability Reduction, and Maintenance and Inspection Requirements. " The ZSA used SAE Aerospace "Guide l ines and Methods for Conducting the Safety Assessment Process on Civil Airborne Systems and Equipment" (SAE ARP4761) as a suggested format. The ZSA identified des ign and installation requirements and individual failure modes, which may have the potential to lead to a catastrophic or hazardous failure event. The analysis recognized the potential hazards of the physical installation of system hardware and the effect it has on the independence of associated systems
. It also i ncorpo rated analys is, of events outside the system(s) concerned, but which may influence events within the system(s)
. To assess these potential hazards or threats, the ZSA considered the installation aspects of new and/or modified individual system/components and the mutual influence between several systems/components installed in close proximity on the airplane
. To accomplish this task the engineering drawing package and actual aircraft installations were inspected to prove compliance with Lockheed Drawi_Q_gs and §P-e..c.ificatio_ns_prrd FAA requirements
. The aircraft as delivered to each customer met the design requirements that Lockheed Martin feels is the minimum to assure fuel tank safety. This section should be accomplished on any changes to the aircraft since delivery to the customer
. Original installations by the Lockheed Martin meet these requirements. The following documents are to be used in bring i ng the installation/repair i nto compliance:
• Hercules Corrosion Prevention and Control Manual • Hercules Airfreighter Progressive Inspection Procedures or Hercules Airfreighter Series Progressive Inspection Procedures • Hercules Maintenance Manual or Hercules Maintenance Instruct ions Manual • Hercules Wiring Diagram Manual The center wing dry bay, dry bays 1, 2, 3, and 4, the wing lead ing-edge, the wing trailing edge, and the fuel probes, shall be inspected in accordance with the following paragraphs: -.J ( 1) Electrical Systems Inspection Perform all inspections described i n the following paragraph
. (a) Alum i num W i re Ensure aluminum wire is not used in the following locations: 

## 1 Aluminum wire smaller than No. 4 AWG shall not be used for main generator cables
. 

### f. Aluminum wire shall not be installed in areas of corrosive fumes or severe vibration.**~** Aluminum wire shall not be connected to engine mounted accessories. 

### 1 Aluminum wire installation shall be permanent.**~** Aluminum wire runs shall be longer t han three feet 

# 382-28-19 82-770 Ust. COI"vti(O
.**A.NO.O itO!** **SC OSU~t**  I SGOvti'C N !O SY 1M! SlAThtE . •H ON Tt1 f. f i TlE P.-.GEOf**h~ 00C** **MfN l**  October 17, 2003 Page 26 Revision 4, September 18, 2008

# HERCULES Lockheed Martin Aeronautics Company Marietta , Georgia 30063 

# SERVICE BULLETIN (b) Copper Wire Ensure that no wire smaller that AWG 22 is used for in ter-connecting equipment(s). (c) Engine Mounted Accessories Ensure that for direct attachment to engine mounted accessories wire and cable smaller than No
. 20 AWG high strength alloy shall not be used. (d) Spare Cable Length Ensure that harnesses are installed to permit replacement or repair of individual cables without removal of the entire harness
. At least two inches of spare cable length shall be prov ided to allow for broken connections. (e) Insulating Tub in g Ens ure that insulating tubing i s placed over term in a ls (except pre-insulated types) to provide electrical protection and mechan ical support and is secured to prevent slippage of t h e tubing from the te rmin a l.

October 17 , 2003 vsE coPY!'iO, AN:l
.OitO ! SC !.OSUIU: • soovtiii Nt'.O II'f'f" e" "' l .., ! H I 01'1 '" ' tiH I! "A0l0f' '"' •oocv "" u" Revision 4, September 18 , 2008 (Reissue) 

# 382-28-19 82-770 Page 27

# HERCULES Lockheed Martin Aeronautics Company Marietta , Georgia 30063 

# SERVICE BULLETIN (f) Dead-Ended Wires Perform an inspection to ensure that electrically energized conductors are not dead-ended. If wi res must be dead-ended, however, wire end caps sha ll be used
. A minimum of 0
. 2- i nch between the end caps and/or metallic objects shall be maintained
. (See fi gures 11 and 12.)

Fig ure 11 Properly I nsta lled Wire End Caps

Figure 12 Improperly Terminated Wi res 

# 382-28-19 82-770**$E C0"'tl'fG** **AN0.0~ 0.$Ct0$U~E** **t: QO** **\I'EitNIE D8V**  T H E StAtE I.tt:H t O N TH E f iH-f, PAG ! C f T HIS OOC-0\fEN T October 17, 2003 Page 28 Revision 4, September 18, 2008 (Reissue)

# HERCULES Lockheed Martin Aeronautics Company Marietta , Georgia 30063 

# SERVICE BULLETIN (g) Wire Rout i ng 

## 1 Ensure that electrical w i re is not routed under fluid carrying tubes
.**~** Ensure that when running wires over a fluid li ne that sufficient cable clamps are installed so that a broken wire cannot contact the flu id line
. (See figure 13.)

Figure 13 Broken Wire Over Fluid Line**~** Ensure that wire bund les within clamps are not larger than two inches i n diameter
.**~** Ensure tha t generator feeder wires are bund l ed separately from all other wires in the wing leading edge and fuselage a reas . Ensure that all generator wire bundles , feed e r and contro l , are separated from fuel tank boundaries (wall or bulkheads) in the wing leading edge area per original type design; i.e ., feede r wires i n cable clamp and stand-off brackets in accordance w ith Step**(2)(a)~** and control wires tightly tied in accordance with Step 2.C.( 1 )(g)Z. us i ng suitable material. 

### §. Ensure the electrical power leaves t he nacelle in the upper left quadrant and fuel is del ivered to the engine i n the lowe r right quad ran t.

October 17, 2003 Revision 4 , September 18 , 2008 

# 382-28-19 82-770 Page 29

# I HERCULES Lockheed Martin Aeronautics Company Ma rietta, Georgia 30063 

# SERVICE BULLETIN §. Ensure that wires are routed at least six inches away from lines or equ i pment conta i ning flammables
. Wires or cables closer than six inches shall be supported so that they wi ll not deflect closer than 0
. 5-inches f rom the l i nes or equipment, except where i l")terven in g st ructu re or barriers ex ist between the lines or equipment and the wire or cables , which wou ld make contact i mpossib le. Where these req uire ments cannot be met, protect ion such as conduit or insulating material shall be used
. (See figure 14.)

Figure 14 Hydraulic - Electrical Lines Routed too Close 7 Ensure that wires are routed away from , or protected from , all hot equ i pment and l in es to prevent insulation b re akdown
. The normal safe distance from bundles to bleed ai r ducts is twelve inches, and essential coaxial cables are nine i nches. Ensure
. all**buodl ~~** **with** 2 to 12 i nches of hqtequiprnentaod lines are spot-tied us i ng f lame res i stant lacing bra id. Use fiberglass braid in power plant areas . 

### §. Ensure that electrical wires a re not routed th rough areas where they can be immersed in o r saturated with fluids. When this is i mpossib le , they should be enclosed in rigid conduit, plastic tub in g, or shrinkable tubing for a sufficient d istance to prevent any flu id contact with the wires or cables.



# 382-28-19 82-770 October 17 , 2003 Page 30 Revision 4, Septembe r 18 , 2008

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN jt Ensure that provisions have been insta lled to prevent insulation chafing
. Wires and bundles shou ld be installed by routing and clamping to ensure sufficient spacing from structure or other parts after any single failure. Bend radii should be large enough to ensure that insulation cracking does not occur. (See figure 15.)

October 17
. 2003 NO SUPPORT AT END OF BEND

2

DIAMETER Of WIRE OR CABLE

MINIMUM BEND RADIUS FOR WIRE INSTALLATION 

# mm & MINIMUM BEND RADI US - 10 TIMES THE DIAMETER OF THE WIRE OR CABLE. 

# & M INI MUM BEND RADI US - 3 TIMES THE DIAMETER OF THE WIRE OR CABLE. Figure 15 Minimum Bend Radii

U SE , COP 't\NG
. A,"il),QR 0-$C t. O SIJ RE. I SOOV't- 1tNE08Y l 11 E S T A.f£Mf,IU O lf T11E frll !! l>.r.G ! O f T,.:$ OOCU V !NT Revision 4, September 18 , 2008 (Reissue) SUPPORT A T BOTH ENDS Of WIRE BEND

SFAR
- 88-sa-o-ol**~**



# 382-28-19 82-770 Page 31

# HERCULES Lockheed Martin Aeronautics Company Ma rietta, Georgia 30063 

# SERVICE BULLETIN (h) Wiring Supports 

## 1 Ensure that wires and cab les are adequately supported to prevent excessive movement in a reas of high vibration (all wi ng areas)
. 

### f. Ensure that no frict ion or plastic tape has been used on the wires and/or cables under clamps . NOTE: Plastic type tapes will dry out i n service and p roduce a chemical react ion with the wire or cable i nsulation, or absorb moistu re .**~** Ensure that suitable clamps, g rommets, or other devices support wire and cables at i ntervals of not more the 24- i nches
. 

## 1. Ensure that metal standoffs are used to maintain clea rance between wire and structure. Emp loying tape or tubing is not acceptable as an alternative to standoffs for ma i ntain i ng clearance.**~** Ensure that clamps and ties around bundles do not present a rough surface that may damage the wire i nsulation
. The clamps should be tight enough to hold the wires i n place, but not so t ight that insulation damage would occur during installation, or later. (See figures 16 and 17.) NOTE: Filler rods may be used when a clamp does not ensure adequate clamp in g and there i s not a smaller clamp, which wi ll clamp properly . (See figure 18 .)

WEDGE POSIT I ON ON SIZE 2 AND 3 CLAMPS

PREFERRED

WEDGE POSI TION ON SIZE 4 AND UP C LA

MPS Figure 16 Proper I nstallation of Cable Clamps 

# 382-28-19 82-770 USE . COPVIN O . ANJ IO'\ OlS t: lOSURE IS**CO VER** **:>** 8 YIH E S fAI Ut! Nl**0~** II'(( tilL!**~A0 £0.**  TH I S OOCU !J ! Nl October 17, 2003 Page 32 Revis ion 4, September 18 , 2008 (Reissue)

# HERCULES Lockheed Martin Aeronautics Company Marietta , Georgia 30063 

# SERVICE BULLETIN

1/16 TO 1/4 INCH M

INIMUM



# t 

# t
NAS623 SCREW MS21042
- 3 LOCKNUT

TO STRU CTU RE TO BRACKETS

October 17, 2003 AMS3356 SLI CON E RUBBER fiLLER ROO

Revi sio n 4 , Septe mber 18 , 2008 (Reiss ue) Figure 17 Mounting Multiple Clamps

Figure 18 Filler Rod Insta ll atio n SFAR-88-SB-o-018**SFAJI-U-S8~1**T


# 382-28-19 82-770 Page 33

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN §. Ensure that phenol ic blocks, p lastic l i ners, o r rubber g rommets are installed in holes, bulkheads, floo rs, or structural me mbers where it is impossible to i nsta ll off- ang le clamps to mainta i n wi ring separat ion. I n such cases, additiona l protection in t he form of p lastic or i nsu lating tape may be used
. (See figures 19 and 20.)

RUB BER GROMMET

ANGLE BRACKE T WITH 

### --!1-4M TWO-POINT FASTENING
Figure 19 Protect ion for W i re or Cable when Passing through Bu l khead

Figure 20 W i re Resting on Li ghtening Port (Not Allowed)
?._ Ensure that i nsulati ng tubing is kept at a minimum and must be used to protect wi re and cable f rom abrasion, chafing , and exposure to flu ids , and/or other cond itions, which could affect the cable i nsu lation
. The use of insu lating tubing for support of wires and cables i n lieu of standoffs is prohibited
. 

# 382-28-19 82-770 USE . CO .. Y\1'1 :).**A~ O.OI'I**  OlSClOS VItf 1$ (i. :;)V£.ANE0 &Y**h~f** Sf A lhtfN T0/'1:**H~f** f lh
.E P.IOE OF t r;..S OCX::U Ut 'ft Octobe r 17 , 2003 Page 34 Revis ion 4 , Septembe r 18 , 2008 (Reissue)

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN §. Ensure that wire is routed i n such a manner as to prevent chafing of insulation. Support wire to prevent harnesses from sagging i nto sharp metall i c edges or rubbing the structure.

October 

### 17. 2003 (See figures 21 through 23
. )

F igure 21 Insufficient Space Under Cable

DRA I N HOLE FOR WEATHER PROTECTION Figure 22 1/8' HOLE AT LOWEST POINT

Dra i n Ho le in Slack W i ri ng Bund le

Revision 4 , September 18, 2008 ( Reissue) S POT TIE OR CLAMP TUBE AT ENDS

SF AR-88-SB - 0..015



# 382-28-19 82-770 Page 35

# HERCULES Lockheed Marti n Aeronautics Company Marietta , Georgia 30063 

# SERVICE BULLETIN
W IRE BUNDLE

ADAPTER

SFAR-88-SB-0-016 Figure 23 Drip Loops i n W i ring Bundle (i) Tying of Electrical Wires Ensu re that tying of wires with plastic straps and tying braid provide the proper wi re bundle and breakout integrity
. NOT E : The tying materia l has to be appropriate for the location within the aircraft. Figures 24 through 27 presents a sample of the proper use of tying mate rial and knot configuratio ns .



# 382-28-19 82-770 October 17 , 2003 Page 36 Revision 4, September 18 , 2008 (Reissue)

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georg ia 30063 

# SERVICE BULLET I N 1 Bundles shall be tied together with an approved p l astic strap or bra i d
. The number of spot t ies should be ke pt to a minimum , but shall be used as necessary to produce a neat and o rderly bundle
. (See figure 24
. ) NOTE : Plastic st raps sha ll meet the requirements of MIL-S-23190
.

Figure 24 Spot Tyi ng Method 

## f. Un l ess otherwise specified by an app roved eng in ee ri ng drawing , straps sha ll not be used under the fo ll owing restrict ions :

October 1 7. 2003**~** Where the tota l temperature exceeds 185°F (85°C)
. 

### Q. Fa i lure of the strap would perm it movement of the wires and cab les against parts wh ich could damage the i nsulation , fou l mechan ical l i nkage , or permit t he strap to fall into moving mechan ical parts
. 

### £ Do not use in high vi b ration areas, in areas of seve re w ind and/or where moisture problems exist such as whee l well s, near wing flap etc .; do not use on wire bundles containing coax ia l cables or other tha n those with so lid dielectric.

\ISl C OPYiNG. A.
.. O.QR 0**$ClOSV~l** £ $ GOVI 11Nf0 IV fHt I T At l"lN I ON tH t T ! T I.t IIN)l 0' 1 " .-S**OOC:U fi** **H** 

# 382-28-19 82-770 Revision 4 , Septe mber 18 , 2008 (R eiss ue) Page 37

# HERCULES Loc kheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN**~** When one or more wires break away from a bundle or harness , tie the breakout as shown in Figures 25, 26, and 27. When cable ties are used at "Y" breakouts, they must be wrapped around each sect ion of the breakout. When cable t ies are used at "T" breakouts on cable diameters over 3/4-inch , they must be wrapped around each section of the breakout.

Figure 25 Tying Harness for Multiple Breakouts

sFA

. R-ee-se-o-ol3 Figure 26 Cable Ties for "T" Breakout 

# 382-28-19 82-770 October 17 , 2003 Page 38 Revision 4 , September 18 , 2008 (Reissue)

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN

SFAR-88-SB-Q-012 Figure 27 Cable Ties for "Y" Breakout 

### U) Terminal Modules 

## 1 Ensure that terminal connections on terminal block studs and nuts on unused studs are tight. 

### g_ Ensure that terminal modules are securely mounted and provided with adequate electrical clearances or insulation strips between mounting hardware and conductive parts, except those used for grounding purposes. (See table 2 and figure 28.)

Stud Size

No.6 No. 10 1/4 inch 5/16 inch 3/8 inch 1/2 in ch

October 17, 2003 Revision 4 , September 18, 2008 (Reissue) Table 2. Torque Value for Terminal Lugs Torque Value in Inch-Pounds Copper Terminals Plain Nuts Self-Locking Nuts

12 to 17 16 to 20 15 to 20 25 to 30 45 to 60 45 to 60 70 to 80 120 to 130 110to120 180 to 190 135 to 150 245 to 260 Aluminum Terminals Plain or Self-Locking Nuts

45 to 60 135 to 165 220 to 250 440 to 470 

# 382-28-19 82-770 Page 39

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN
LUG&

OR NAS 1 149-0

STRUCTURE 

# liE & THESE LUGS CAN BE INVERTED. TERMINAL BLOCK LS35076-0-0 

# & USE MS21042 LOCKNUTS WITH NAS1149 WASHERS AND MS21043 LOCKNUTS WITH NAS1149C WASHERS. ffiMS14151-1, -21 -3, -4 AND -5 FLAT WASHER REQUIRED ON TERMINAL STUDS SIZE 6, 10, 1/4-, 5/16- AND 3/8-INCH TO RETAIN MS3373-0 STRIPS UNLESS BUS BAR IS INSTALLED. Figure 28 Installation of Terminal Block Assembly, Including MS 14151 Washers (k) Connectors SFAR-88-SB-0-010



## 1 Perform an i nspection to identify evidence of overheating (cause of over-heating shall be corrected), and the exteriors for corrosion and cracks. Also. wires leading to connectors must be inspected for deterioration due to overheating
. Replace all corroded connections and overheated connectors. 

## f. Ensure the installation of a cable clamp (M IL-C-85049) on all connectors, except those that are moisture-proof
. 

### ;! Ensure that sil icone tape is wrapped around wire that is secured with MS3057 cable clamps
.**~** Ensure that connectors are fully mated by checking position and tightness of coupling ring or its alignment with fully mated i nd icator l i ne on receptacle, if applicable. 

### §. Ensure that the coupling nut is safetied, by wire or other mechanical locking means . 

# 382-28-19 82-770 VSE , CO
...VI'oiQ
. ""O.OR.QtSCI.OSUIIE ISCOvt.!INf,OSV hi£ STAT(.U:£NT O'ol JH£ Tnt .! PHl!.O, hHSOOCUU [ 't f October 17. 2003 Page 40 Revision 4 , September 18, 2008 (Reissue)

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN (2) Un it Essential to Safe Operation Perform all un its essential to safe operation i nspection described in the following paragraphs. (a) Main Power Cables 

## 1 Ensure that main power cables (including generator cables) in the wing are installed to allow for a reasonable degree of deformation and stretching without failure and that they: 

### 9. Are isolated from flammable fluid lines. 

### Q. Run along the front wing spar, if they are generator cables, to provide isolation from the fuel tanks
.**~** Heavy-Current Carrying Cables (Leading Edge) CAUT I O N : CHANGES TO GENERATOR CABLES STANDOFF BRACKETS ARE NOT PERMITTED
. Ensure no mod ification has been made to compromise generator wires standoffs
. ( b) H i gh Energy W i ring Ensure that h igh ene rgy wiri ng is not routed through condu it or adjacent to fue l tank surfaces such that damage, inappropriate maintenance , or other fai l ure/wear conditions could result in arcing to the conduit or m eta llic tank surface and deve lopment of an ignition source i n the fue l tank
. The exception to this is the fuel pump condui t and fuel level control valves
. (3) Ligh tning Protection Ensure that individual bonding jumpers for lightn i ng protection are not less the No
. 12 AWG for tinned stranded copper or No. 10 AWG for t i nned stranded aluminum wire
. (4) Pneumatic System Failures Ensure that there is no leakage of ai r from dueling located near fuel tanks due to duct failure resulti ng i n undetected heating of tank surfaces above the auto-igniti on temperature
.

October 17, 2003 USf , COP'hNG MO.Oilt D.S:::LOSU!U !SCOVUNEOIY T/'1[ SfAU t.I [H T**0~** l" l TIHI ,AOtO' l i" I :S 00CU M(N1 Revision 4 , September 18, 2008 (Re i ssue) 

# 382-28-19 82-770 Page 41

# HERCULES Lockheed Martin Aeronautics Company Marietta , Georg ia 30063 

# SERVICE BULLETIN (5) Structural and Non -Electrica l Equ i pment Bonding WARNING : ENSURE METER IS CERTI FIED FOR USE IN FUE L OR OXYGEN-RICH EXPLOSIVE ENVIRONMENTS. FAI L URE TO COMPLY MAY R E SULT IN SEVERE INJURY OR DEATH
. Perform all structura l and non-electrical equ i pment bonding requiretnehts describe d In the follo'Ning paragraphs
. NOTE: If conductive couplin gs or fittings are used, bonding may be achieved through the equipment : if not , bo nd ing jumpers shall be used on each isolated section
. ( a) Ensu re that an y lines carrying fluids or gases i n motion are bonded to the structure
. NOTE: Res istance shall not exceed 1 ohm for each metal-to-meta l joint when dry
. (b) Ensu re that p lumb ing equ i pment and control devices 'Nith a line ar dimension over three i nches are e lectrically bonded d i rectly to the airp lane structure to prevent static bu il dup
. (6) ATAIJASC 28 - F uel Systems Perform all ATA/JASC 28 Fu e l System requirements described i n ' the following paragraphs. (a) E nsure that fuel l i nes have been routed such that they do not chafe against co ntrol cables , airframe structure, or come in contact 'Nith electrical wiring or cables
. In no case shou ld the fue l lin e support wi ring
. (b) E nsure that bends in t ubin g are ali g ned 'Nith all support clamps and end fittings and are not d rawn , pulled , or otherwise forced i nto place by the c lamps . (c) Ensu re that support c la mps or bracket for metallic l i nes are as shown below : Tube O
. D
. 1/8 inch - 3/16 i nch 1/4 inch - 5/16 i nch 3/8 inch - 1/2 inch 5/8 inch - 3/4 inch 1 i nch - 1-1/ 4 i nches 1 -1/2 inches - 2 inches 

### Approximate Distance Between Supports 9inches 12inches 16inch es 22inches 30inche s 40 i nches



# 382-28-19 82-770 October 17, 2003 Page 42 Revision 4 , September 18 , 2008 (Re issue)

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVIC E BULLETIN (7) Dra i ns and Vents Perform an inspection at metal dra i ns and vent fittings on the aircraft that shall satisfy a Class L bond requirement (dump mast). Class L- Li ghtning : minimizes potential caused by DC or audio frequency (f <500kHZ) currents such as those caused by l i ghtning strikes
. (Resistance value is 0 .0 025 ohm)
. (8) Fuel Quantity Indicating System (FQIS) Wiring Perform all FQ I S wiring requirements described in the following paragraphs. (a) Inspection

October 17, 2003 

## 1 Inspect the FQIS wiring for any visib le damage, wear , chafing , or indications of electrical arci ng . Repair FQIS wiring in accordance with appropriate Hercules Wiring Diagram Manua l , Hercules Mai ntenance Manual, or He rcules Maintenance I nstructions Manua l and procedures. 

## f. Ensure physical separat ion requirements have been maintai ned for FQIS wi ring as follows :**~** Ensure that FQ I S wires are routed separately from a ll AC power wires i n areas between FS 245
. 0 and FS 457
. 0 in the cargo compartment and i n the wing root area outside the pressure vessel and along the wing tra ili ng edge except where wires pass through cutouts in the structure
. A m i n i mum of 6 i nches separation sha ll be maintai ned in these areas. If impractical to obtain 6 inches , a minimum of 4 inch es shall be obtained and if i mpractical to obtain 4 inches , a minimum of 1 inch sha ll be obtained
. NOTE: Under certain conditions , lightning d i scharges have sufficiently h i gh rates of current rise that they produce an inductive potential that induces voltages into the fuel capacitance gage wiri ng and other wiring leading into the fuel tanks
. It is, therefore necessary that wiring from antennas, pitot heaters, wing tip lights, etc
.. be routed away from the e l ectric wi ring leading into fuel tanks and/or wiring should be shielded. 

### Q. Ensure that sh i elded wires are i n accordance with MIL-C-27500
. £ Ensure that AC ground wires from FQIS system are NOT grounded to DC or s ignal ground stud
. 

### Q. Ensure wire terminati ons at fue l probes are undamaged
. • Remove wires from fuel p robes
. • Inspect wires for damage
. • If wires are damaged replace w ires . • Connect wires to fuel probes
. 

### ;! Notify Lockheed Martin Techn ical Support Center of any d i screpancies found duri ng inspection
. 

# 382 -28-19 82-770 Revision 4, September 18, 2008 Page 43 

# I I

# HERCULES Lockheed Martin Aeronautics Company Marietta , Georgia 30063 

# SERVICE BULLETIN (b) Modification 

## 1 FQIS wires shall be marked in accordance with SAE-AS81531 with "FQIS" every 18 inches beginning at the p lugs that exit the fuel tanks or bladders, through outer wing breaks and wheel well pressure breaks to the individual fuel quantity indicator plugs on the Fuel System Control Pa nel. 

### f. FQIS wires shall not be bundled with high voltage carrying wires.**~** Fabricate pink identification cable markers (base part numbers CM-SCE - 1/4-4H-2L or CM-SCE-1/2-4H-2L) or sleeving (base part numbers M23053/5-106-P or M23053/5-108-P). 

### 1 Install ide ntification cable markers or sleeving on the wires within 8 inches of the end connector (near the existing wire identification) in accordance with Hercules Wiring Diagram Manual. 

### §. See figure 29 for a listing of the typical FQIS wire numbers that will require identification cable markers. NOTE: Refer to the appropriate aircraft wiring diagrams for specific aircraft FQIS wire XX numbers, 1E1 08CXX, 5E1 09BXX, etc
.



# 382-28-19 82-770 US! CO!)nNGMO.Oit O
. $C\.

OSIJ R E 1$G0V[JINE 0 8Y T H E StATEMEN t ON l 11f tlflt PAG !Ot' T H :SOOCU U l N I October 17, 2003 

# I Page 44 Revision 4 , September 18 , 2008

# HERCULES Lockheed Ma rt in Aerona uti cs Co mpa ny Marietta, Georgia 30 063 

# SERVICE BULLETIN

# ~LEFT IAUX

B L

ADDER C E LL 

# l
_ 1E108AXX 1E109AXX 1E107AXX

2E108AXX 2E109AXX 2E107AXX 

# ===,I

TANK N0
. 1 

# I IND 

# I I

TANK N0
. 2 

# I
I ND 

# I I 

# L---J I
LEFT AUX 

# I T A NKIND 

# I IC E NT E R

PIN 

# l
_ 7E 1 07AXX --+---< 

# I 

# L**LEFT** L E FT EXT T ANK LH WHEEL WIELL PR E SSURE BREAK EXTERNAL 

# I TANK I ND 

# IIIII (CARGO WALL) F U E L SYSTEM (TY PICAL AIRPLANE ) CONTROL PANEL 

# & ROUTE THESE WI R ES SEPARATELY FROM ALL AC POWIER WIRES IN AREAS BETWEEN F U S STA 245 AND 457 AND ALONG THE WING TRAILI N G EDGE EXCEPT WHERE INIRES PASS THROUGH CUTOUTS IN STRUCTURE
. A MINIMUM O F 6 INCH E S SEPARATI ON SHALL BE OBTAINED I N THESE AREAS
. I F I MPRACTICAL TO OBTAIN 6 1NCH E S , A M I N IMUM OF 4 1NCH E S SHALL BE OBTAINED AND IF I MPRACTICA L TO OBT A I N 4 INC HE S, A M I NIMUM OF 1 I N CH SHALL B E OBT AIN E D
. ANY SEPARAT I ON UNDER SINC H E S IN THESE AREAS MUST BE APPROV E D BY ENGINEERING
. 2
. I NSTALL MAR K ER WITH I N 8 I NCH E S OF CONNECTIONS AND EVERY 181NCHES ALONG WIRES 3
. REFER TO THE APPROPR IATE A I RCRAFT WIRING DI AGRAMS FOR SPECIFIC A I RCRAFT FQ I S INIRE XX NUMBERS , 1E108CXX, 5 E 109BXX, ETC
. SBB2 - 77 o-38 2- 28 - 19-XO I -29-I

October 17 , 2003 Fuel Q u antity Ind icat i ng System (FQIS) Wiri ng Marker F igure 29 (Sheet 1 of 2)

Ust C OPVI 'iG
. A. 'l0.01t O<SC lOS UII[ ! S GO\It"-N£0 S Y J o([ S l "-1tu t "' f ON T HE ll f Lf PAG f OF 1 11 1$ OOCU U E!H Revision 4 , Septembe r 18 , 2008 (Reissue) 

# 382-28-19 82-770 Page 45

# HERCULES Lockheed Marti n Aeronautics Company Marietta , Georgia 30063 

# SERVICE BULLETIN

TA NK N0.4 IND

TANK N0
. 3 IND

R I GHTAUX TANKIND

RIGHT 

# _j ER NAL KI ND FUEL SYSTEM CON TR OL PANEL



# 382-28-19 82-770 4E108AXX 4E 109AXX 4E107AXX

3E109AXX 3E107AXX

6E 1 09AXX 6E 107AXX

8E108AXX 8E109AXX 8E107AXX RH WH EE L WELL PRESSURE BREAK (FWD)**~** RIGHT OUTER WNGBREAK

(TYPICAL AIRPLANE) 8E108CXX 8E109CXX 8E107CXX

Fuel Quant ity Indicating System (FQIS) Wiring Marker Figure 29 (S heet 2) R IGHT 

# 1 AUX BLADDER 

# I CELL



## _j 

# -1

CENTER 

# I PIN



## _ j RIGHT EXT TANK

SSB2·770- 38 2· 28
- 19- XC 0-29-2

October 17 , 2003 Page 46 Revision 4 , September 18, 2008 (Reissue)

# HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN (9) ATAIJASC 29 - Hydraulic Systems Perform all ATA/JASC-29 Hydraulic Systems requirements described in the following paragraphs. (a) Ensure hydraulic li nes are located at least four inches from any heat source and never above a heat sou rce. (b) Ensure hydraulic lines are routed below e lectrical bundles
. F i nd hydraulic system components located on the wings and i nspect for damaged tubing , worn or damaged hoses, wear of moving parts, and security of mounting for all units, safetying, and any other condition specified in Hercules Corrosion Prevention and Control Manual , Hercules Wiri ng Diagram Manual, Hercu les Maintenance Manual or Hercules Maintenance Inst ructions Manual, and Hercules Airfreighter Progressive Inspection Procedures or Hercules Airfreighter Series Progressive Inspection Procedures D
. Return Aircraft to Service ( 1) Reinstall removed components and access panels. (2) Remove equipment and supplies from the inspect ion area. (3) Perform operat ional checkout as required in accordance with appropriate Hercules Ma i ntenance Manual or Hercules Maintenance I nstructions Manual. (4) Return aircraft to normal service. (5) The aircraft owner/operator shall make an appropriate entry i n the aircraft log records upon comp li ance with this Service Bulletin and maintenance planning documents to re qu i re a repeat inspection of FQ IS wiring , not to exceed 12 years. (6) After the work has been completed on each affected aircraft , p lease complete and mai l or fax (770-494 -5682) a Notice of Service Bulletin Compliance; or notify Lockheed Martin Aeronaut ics Company of compl iance with this Service Bulletin at website address: www .l ockheedmart i n.com/ams and log into Data Library. NOTE: If assistance pertaining to this Service Bulletin or i nformation regarding your Hercules aircraft is needed, contact your loca l Lockheed Marti n Aeronautics Company representative or the Technical Support Center in Marietta , Georgia, USA. as follows:

October 17 , 2003 Te lephone: (770) 494-9131 Fax: (770) 494-9122 E-Mail: hercules
.support@lmco
.com

Mai l: Lockheed Martin Aeronaut ics Company 86 South Cobb Drive Department 3E1 M , Zone 0591 Marietta , GA 30063 -0591, USA

Revision 4, September 18 , 2008 (Reissue) 

# 382-28-19 82-770 Page 47

# HERCULES Lockheed Marti n Aeronautics Company Marietta , Georgia 30063 

# SERVICE BULLETIN

382-28-19 82-770 Pag e 48 TH I S PAGE I NTENTIONALLY LEFT BLANK

October 17, 2003 Revision 4 , September 18, 2008 (Reissue)

# HERCULES Lock h eed Ma rt in Ae ro na uti cs Com pa ny Ma rietta, G eo rg ia 30063 

# SERVICE BULLETIN 3. MA T E RI AL INFOR M ATION The following parts/materia ls , requ i red to mod ify each aircraft l isted in parag raph 1 .A. , will be provided by the aircraft owner/ope rator. Parts may be obtained from Lockheed Marti n Ae ronaut ics Company i n accorda nce with paragraph 1
. F. NEW PART O L D PART INSTRUCTIONS/ N U MBER QUANT ITY KEYWORD NUMBER DISPOS IT ION MIL-T -43435 AR Laci ng Tape CM-SCE-Y..-4H-2 L AR Cable Marke r -T ie i n Place ( 1)(2) Y..-inch CM - SCE -Y2-4H-2 L AR Cable Ma rker-T ie i n P lace (1 )(2) Y2- i nch M23053/5- 106 - P AR Cable Marke r, Wraparound , (3) Heat-Shri nkab le Po lyo lefi n Y.. -i nch M23053/5- 108-P AR Cable Marker, Wrapa round (3) Heat-Shri nkable Po lyo lefin , Y2 - inch
N OTE : 1
. Specify pink cable marker-t ie. Select appropriate s ize of cab le marke r-t ie for each wire
. 2. Tyco E lectronics Raychem DBA Raychem E lectronics D iv is ion 300 Constitution Dr. Menlo Park, CA 94025 3. Specify p i nk cable ma rker wraparound
.

___ # . __ _ File : I -A013/I-3042

October 17 , 2003**US£ COPV** **'IG ...,.0.0~**  t>tSClOS U"f !S GO\It.Jt.Nf08Y lMf $1Alf \ll f l'lf0M 1 <4 [ TITlE P,IQ, f_ OJ T .,. ioS OOC'U M EN T Revision 4 , Septembe r 18 , 2008 (Reissue) 

# 382-28-19 82 -770 Page 49

# HERCULES Lockheed Martin Aeronautics Company Marietta , Georgia 30063 

# SERVICE BULLETIN

382-28-19 82-77 Page 50 THIS PAGE IN T ENTIONALLY LEFT BLANK

US! COF"Y'I"iG ,**ANOIO't0 1S** **CLOSUII:t SGOVEII:~E08Y**  fi; E$ TATE U EIH 0'1 T H E TIHE PAO IE Oc THIS OOCUU E "i t October 17, 2003 Revision 4, September 18 , 2008 (Re issue) 

# ·,