# HERCULES Lockheed Martin A eronautics Company Marietta, Georgia 30063 

# SERVICE BULLETIN

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 Expor t 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 penalties.

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* REVISION NOTICE *

WING

- CENTER WING LOWER SU RFACE GENERALIZED CR ACKING AND WIDESPREA D FATIGUE DAMAGE INSPECTION RE QUIREMENTS

Attached is Revision 3, date d July 8, 2013
, t o Service Bulletin 82

- 790/382

- 57

- 85. Information added or changed in this issue is i ndicated by a vertical revision bar in the margin of affected pages, or pointing hand for illustrations.

For military operators: This revision incorporates updates to the inspection schedule, removes the recurring inspection, and defines the service life of the center wing box. Furthermore, Appendix A defines additional inspections of adjacent fastener holes when hole

- to

- hole or hole

- to

- edge cracking is found during the primary inspection. The updated inspection schedule is based on an Operational Usage Evaluation (OUE) or Damage Tolerance Assessment (DTA) performed by Lockheed Martin Aeronautics Company. Operators using the Initial Usage Assessment procedures identified in P aragraph 2.A.(1) through (3) of Service Bulletin 82

- 788 should adhere to the sch edule defined in this revision and contact Lockheed Martin for completion of an OUE.

For commercial operators: The 14 CFR Part 26, Subpart C Aging Aircraft Safety

- Widespread Fatigue Damage rule became effective on January 14, 2011. In compliance with t his rule, Lockheed Martin Aeronautics Company established a Limit of Validity (LOV) for 382 series aircraft, published in Section VII of customer specific Service Manual Publication (SMP) 515

- C Inspection Programs. 14 CFR Part 121 or Part 129 operators mu st incorporate the LOV into their maintenance program by July 14, 2013 to comply with FAR §121.1115 or §129.115. This revision incorporates maintenance actions required to safeguard the aircraft against widespread fatigue damage up to the LOV, which inclu de removal of the recurring inspection, establishment of the terminating action, and reference to the commercial center wing replacement service bulletin. Furthermore, Appendix A defines additional inspections of adjacent fastener holes when hole

- to

- hole or hole

- to

- edge cracking is found during the primary inspection.

T his revision affects Pages 1 through 18 and Appendix A Pages A1 through A 14 of this Service Bulletin, Revision 2, dated August 23, 2007. Retain Appendices B through G. Please remove existi ng Pages 1 through 18 and Appendix Pages A1 through A 14 from your copy of this Service Bulletin, and attach the enclosed pages to Appendices B through G. Retain this notice with your copy of this Service Bulletin.

Aircraft previously inspected by this Se rvice Bulletin are not required to perform any additional inspections described in Appendix A. However, they are affected by the center wing box service life and replacement defined in this revision.

Basic August 4, 2005
Revision 1 March 8, 2007
Rev ision 2 August 23, 2007

___________#__________

File: CR C130

- 03912 / I

- 3884R3

# HERCULES Lockheed Martin Aeronautics Company Mariett a, Georgia 30063 

# SERVICE BULLETIN

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 penalties.

© 20 13 LOCKHEED MARTIN CORP ORATION. LOCKHEED M ARTIN PROPRIETARY IN FORMATION. 

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August 4, 2005 

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Revision 3
, July 8, 2013 Page 1 of 18 WING

- CENTER WIN G LOWER SURFACE GENERALIZED CRACKING AND WIDE SPREAD FATIGUE DAMAGE INSPECTION RE QUIREMENTS

NOTE: This Service Bulletin contains Appendi ces A through G

.

1. PLANNING INF ORMATION

A. EFFECTIVITY

(1) 3 82

- 57

- 85 , FAA Certificated Aircraft: This Service Bulletin is applicable to all model 382, 382B, 382E, 382F, a nd 382G series FAA Certificated Hercules aircraft (excluding 382J series aircraft).

(2) 82

- 790 , Foreign Direct Sales Aircraft: This Service Bulletin is applicable to all model 282, 382, 382C, and 382T series Hercules aircraft (excluding 382U and 382V series aircraft).

(3) 82

- 790 , MAP/FMS/SAP Aircraft: This Service Bulletin is applicable to all model C

- 130 series Hercules aircraft (e xcluding C

- 130J Hercules aircraft).

B. REASON

(1) Service Bulletin s 82

- 788 (military) and 382

- 57

- 84 (commercial) identify the reasons for implementation of enhanced inspection requirements for the center wing lower surface structure on certain 282, 382 and /or C

- 1 30 aircraft. This Service Bulletin contains the inspection requirements for detection of generalized fatigue cracking and the possible onset of widespread fatigue damage of the center wing lower surface structure.

(2) R ecommendations for military operators a re as follows :
(a) The inspection schedule is based on an Operational Usage Evaluation (OUE) or Damage Tolerance Assessment (DTA) performed by Lockheed Martin Aeronautics Company. Operators using the Initial Usage Assessment procedures identified in P aragraph 2.A.(1) through (3) of Service Bulletin 82

- 788 should adhere to the schedule defined in this bulletin herein and contact Lockheed Martin for completion of an OUE.

(b) Lockheed Martin Aeronautics Company recommends that the one

- time inspection specified herein be accomplished on all affected military aircraft as follows:

1 For military aircraft that have accumulated between 38,000 and 40,000 Center Wing Equivalent Baseline Hours (EBH), as calculated by a Lockheed Martin Aeronautics Company performed Operational U sage Evaluation (OUE) or Damage Tolerance Assessment (DTA) or with the Initial Usage Assessment procedures identified in P aragraph 2.A.(1) through (3) of Service Bulletin 82

- 788, the inspection should be performed at the next convenient maintenance period prior to reaching 40,000 EBH.

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USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. August 4, 2005 Page 2 Revision 3
, July 8, 2013 2 For military aircraft that have accumulated more than 40,000 Center Wing Equivalent Baseline Hours (EBH), as calculated by a Lockheed Martin Aeronautics Company performed Operational Usage Evaluation (OUE) or Damage Tolerance Assessment (DTA) or with the Initial Usage Assessment procedures identified in P aragraph 2.A.(1) through (3) of Service Bulletin 82

- 788, the inspection should be performed at the next convenient maintenance period but not to exceed 90 days after receipt o f this Service Bulletin and prior to reaching 45,000 EBH. These aircraft are subject to the flight restrictions as defined in P aragraph 2.B.(4) of Service Bulletin 82

- 788 until this inspection is accomplished.

3 For military aircraft that have accumulated 4 5,000 or more Center Wing Equivalent Baseline Hours (EBH), as calculated by a Lockheed Martin Aeronautics Company performed Operational Usage Evaluation (OUE) or Damage Tolerance Assessment (DTA) or with the Initial Usage Assessment procedures identified i n P aragraph 2.A.(1) through (3) of Service Bulletin 82

- 788, the aircraft should be grounded until replacement of the center wing box has been accomplished.

(c) Lockheed Martin Aeronautics Company recommends a center wing box replacement for all military aircra ft exceeding 45,000 Center Wing Equivalent Baseline Hours (EBH). Contact Lockheed Martin Aeronautics Company for wing kit availability and replacement instructions.

(3) Recommendations for commercial operators of model 382 series aircraft are as follows:

(a) The 14 CFR Part 26, Subpart C Aging Aircraft Safety

- Widespread Fatigue Damage rule became effective on January 14, 2011. In compliance with this rule, Lockheed Martin Aeronautics Company established a Limit of Validity (LOV) for 382 series aircraft, publish ed in Section VII of customer specific Service Manual Publication (SMP) 515

- C Inspection Programs. This service bulletin incorporates maintenance actions required to safeguard the aircraft against widespread fatigue damage up to the LOV.

(b) Lockheed Martin A eronautics Company recommends that the one

- time inspection specified herein be accomplished on commercially certified aircraft as follows:

1 Commercially certified aircraft that have accumulated 40,000 Center Wing Flight Hours (FH), or more, within 365 days of receipt of this Service Bulletin.

2 Commercially certified aircraft that have accumulated 50,000 Center Wing Flight Hours (FH), or more, should be grounded until replacement of the center wing box has been accomplished.

(c) Lockheed Martin Aeronautics Company recommends a center wing box replacement be completed for all aircraft by 50,000 Center Wing Flight Hours (FH) per instructions given in Service Bulletin 382

- 57

- 094.

(d) Commercial operators of model 382 series aircraft are advised that an extension of the
re commended compliance period of this Service Bulletin can be addressed by completion of a Lockheed Martin Operational Usage Evaluation (OUE) in accordance with P aragraph 2.B.(2) of Service Bulletin 382

- 57

- 84.

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Revision 3, July 8, 2013 Page 3 C. DESCRIPTION

(1) The inspection procedures identifi ed in this Service Bulletin consist of surface eddy current, bolt hole eddy current and visual N ondestructive I nspection (NDI) methods to detect generalized fatigue cracking and the possible onset of widespread fatigue damage of the center wing lower surfa ce structure. These inspection procedures are intended to supplement the existing Hercules Airfreighter Series Inspection Program, SMP 515

- C, requirements and previously issued Service B ulletins. There are no previous inspection procedures that meet the full intent of this Service Bulletin

. (2) The inspection procedures used in this S ervice B ulletin have been selected with crack detection targets as shown in Table 1

.
Table 1 Crack Detection Targets Technique 50% 90% Automated B olt H ole E ddy C urrent 0.03 0.05 Eddy Current Surface Scan 0.10 0.20 Visual 0.5 1.0
NOTE:

 All dimensions in inches

.

 All dimensions are exposed and inspectable surface lengths. Actual lengths could be larger due to cracking which originates from faying surfaces as well as obstructions such as installed brackets, doublers, sealant, fastener heads

, and collars.

 50% and 90% columns represent the estimated crack size at which 50% and 90% of cracks in a given set would be found. Rigorous P robability O f D etection (POD) analysis is not implied.

(3) Lockh eed Martin Aeronautics Company recommends the use of independent repeat inspection for all Primary Automated Bolt Hole Eddy Current ( ABHEC ) NDI Procedure s found in the Appendices. The additional manpower requirements for independent repeat inspection is s mall in relation to preparation time
, yet has the potential for reducing inspection misses in the critical structure inspected by this S ervice B ulletin. Use of check lists or other appropriate means are encouraged to minimize the possibility of missing on e or more fastener holes in the inspection procedure

. (4) Techniques and procedures utilized in this S ervice B ulletin were chosen to e nsure that adequate inspection could be carried out within the capabilities of all operators of C

- 130/282/382 model aircraft. NDI scanning systems such as the SAIC UltraImage and MAUS systems
, as well as Magneto Optical Imaging and Eddy Current Array technologies

, may be used as first layer inspection tools in place of specified techniques for the eddy current surface scan inspe ction procedures called in Appendi ces D, E, and F. Operators are responsible for all alternate procedure development including standards and validation consistent with the targets listed in Table 1 above. No other techniques are considered equivalent by Lockheed Martin Aeronautics Company

.

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, July 8, 2013

(5) This Service Bulletin consists of the following Center Wing Lower Surface Generalized Cracking and Widespread Fatigue Damage Inspection Requirements :

 NDI of Center Wing Lower Surface Panels and Stringers Under Wing Att ach Angle, WS 58 to WS 61, FS 517 to FS 597, Left and Right ( Appendix A )

 NDI of Center Wing Lower Surface Panel s and Stringers Under Nacelle Attach Fitting and Fairing Attach Angle, WS 178 and WS 213, Left and Right (Appendix B)

 NDI of Center Wing Lower Surface Panels and Stringers Under the Drain Trough, WS 56, 72, 174 and 208, Left and Right (Appendix C)

 NDI of Center Wing Lower Surface Panels at Stringer and Beam Cap Attachments, WS 21 6 Left to WS 21 6 Right (Appendix D)

 NDI of Center Wing Lower Surfa ce Stringers, WS 214 Left to WS 214 Right (Appendix E)

 NDI of Center Wing Lower Surface Front and Rear Beam Caps, WS 210 Left to WS 210 Right (Appendix F)

 NDI of Center Wing Lower Surface Panel Repairs (Appendix G)

 Perform NDI of the center wing lower su rface panels at the rainbow fitting in accordance with Appendix A of Ser vice Bulletin 82

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 Perform NDI of the center wing lower forward corner fitting in accordance with Se rvice Bulletin 82

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D. APPROVAL

(1) The aircraft owner/operator sha ll make an appropriate entry in the aircraft log records upon compliance with this Service Bulletin.

(2) After the work has been completed on each affected aircraft, please complete and mail or fax (770

- 494

- 5682) a Notice of Service Bulletin Compliance; or no tify Lockheed Martin Aeronautics Company of compliance with this Service Bulletin at website address: www.lockheedmartin.com/eoc and log into Data Library

. (3) 382

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- 85, FAA Certificated Aircraft: FAA appro val of the Inspection Pro gram change in this Service Bulletin has not been solicited and customers with FAA Certificated airplanes are urged to follow up with the agency for approval if necessary. This service bulletin is subject to FAA Airworthiness Dire ctive 2011

- 09

- 04, and the FAA may issue a revised directive based on the Revision 3 changes.

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Revision 3, July 8, 2013 Page 5 E. MANPOWER

NOTE: This Service Bulletin is based upon the configuration of the aircraft as it was delivered from

Lockheed Martin Aeronautics Company. Previous Service Bul letins issued by Lockheed Martin Aeronautics Company have been considered in the preparation of this Service Bulletin, but no consideration has been given to peculiar changes made to the aircraft by the owner/operator since its delivery.

The work prescribe d in this Service Bulletin has not been performed at the Lockheed Martin facility exactly as described herein. Operators are requested to provide Lockheed Martin Aeronautics Company with the approximate manhours required to perform each inspection identif ied in Appendix A through G of this Service Bulletin. Manhours required to perform each inspection will be provided in a subsequent revision.

F. MATERIAL

- COST AND AVAILABILITY

Parts/Materials listed in Paragraph 3 are to be supplied by the aircraft owne r/operator.
Parts listed in Paragraph 3 may also be purchased from Lockheed Martin Aeronautics Company, as noted, if desired. Direct all inquiries concerning price and availability to the following:

MAIL: Lockheed Martin Aeronautics Company

C

- 13 0 Commercial Contracts Department F532 Zone 0195 86 South Cobb Drive Marietta, GA 30063

- 0195, USA
TELEPHONE: (770) 494

- 5165
FAX: (770) 494

- 7657

G. TOOLING

- PRICE AND AVAILABILITY

 Eddy Current I nstrumen t

- Z etec MIZ

- 21A or equivale nt

 Mini Probe D rive

- GE Inspection Techno logies PN 33A100 or equivalen t

 Probe, shielded pencil

- Z etec PN DT30PS 50

- 500 kHZ or equivalent

 Cable, MIZ

- 21 to mini probe drive

- Z etec PN 2100

- 03

- 04 or equivalen t

 Probe C able

- Z etec PN DTPH

- 3 or equivalen t

 Pro be, rotating hole, reflection type

- 200 kHz to 2 MHz, 3/16” diameter, GE Inspection Technologies PN 620

- 546

- 187 or equivalent

 Probe, rotating hole, reflection type

- 200 kHz to 2 MHz, 5/32” diameter, GE Inspection Technologies PN 620

- 546

- 156 or equivalen t

 Probe, rotating hole, reflection type

- 200 kHz to 2 MHz, 1/4” diameter, GE Inspection Technologies PN 620

- 546

- 016 or equivalent

 Calibration S tandard, a luminum

- VM Products, Inc. PN VM308 89

- C1A or equivalent

 Draftsman’s T emplate

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USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. August 4, 2005 Page 6 Revision 3, July 8, 2013 H. WEIGHT AND BALANCE

None.

I. REFERENCES

Hercules Structural Repair Manual
Hercules Corrosion Prevention and Control Manual Nondestructive Inspection (NDI) Procedur es Manual Supplement

(1) 382

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- 85 , FAA Certificated Aircraft :

Hercules Maintenance Manual
Hercules Service Bulletin 382

- 53

- 6 1
Hercules Service Bulletin 382

- 57

- 50
Hercules Service Bulletin 382

- 57

- 55
Hercules Service Bulletin 382

- 57

- 79
Hercules Service Bulletin 382

- 57

- 81
Hercules Service Bulletin 382

- 57

- 83
Hercules Service Bulletin 382

- 57

- 84
Hercules Service Bulletin 382

- 57

- 86
H ercules Airfreighter Series Inspection Program, SMP 515

- C

(2) 82

- 790 , F oreign Military Aircraft :

Hercules Maintenance Instructions Manual
Hercules Service Bulletin 82

- 481
Hercules Service Bulletin 82

- 557
Hercules Service Bulletin 82

- 752
Hercules Service Bullet in 82

- 766
Hercules Service Bulletin 82

- 768
Hercules Service Bulletin 82

- 783
Hercules Service Bulletin 82

- 788
Hercules Service Bulletin 82

- 799 Hercules Airfreighter Series Inspection Program, SMP 515

- C

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Revision 3, July 8, 2013 Page 7 J. OTHER PUBLICATIONS AFFECTED

(1) 382

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Hercules Airfreighter Series Inspection Program, SMP 515

- C

(2) 82

- 790 , Foreign Military Aircraft :
Hercules Airfreighter Series Inspection Program, SMP 515

- C

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Revision 3
, July 8, 2013 (Reissue) Page 9 2. ACCOMPLISHMENT INSTR UCTIONS

WARNING: ENSURE THAT APPLICAB L E SAFETY PRECAUTIONS PERTAINING TO WORK I N

FUEL/FUME AREAS, SPE CIFIED IN THE HERCULES MAINTENANCE MANUAL OR HERCULES MAINTENANCE INSTRUCTIONS MANUAL , ARE STRICTLY OBSER VED WHILE WORKING IN THE CENTER WING DRY BAY AREA. PERSONNEL SHA LL WEAR NONSPARKING PRO TECTIVE CLOTHING. E NTRY INTO THE DRY BA Y FOR DEPUDDLING MUST NOT BE MADE UNTIL THE AR EA HAS BEEN PURGED T O FIRE

SAFE 20 PERCENT LOWE R EXPLOSIVE LIMIT (L EL), AS DETERMINED U SING FUEL VAPOR DETECTION AND MEASURING EQUIPMENT. FULL

- FACE RESPIRATOR MUST BE WO RN UNTIL AREA HAS BE EN PURGED TO THE HEA LTH

- SAFE 0.0

- TO 1.5

- PERCENT LEL AND 19.5 PERCENT OXYGEN CONTE NT. FAILURE TO COMP LY MAY RESULT IN SERIOU S INJURY, OR DEATH.

WARNING: ENSURE THAT APPLICABLE SAFETY PRECAUTIONS P ERTAINING TO ELECTRI CAL

AND FUEL SYSTEM MAIN TENA NCE ARE STRICTLY OBS ERVED WHILE ACCOMPLISHING THE WO RK DESCRIBED HEREIN. ENSURE THAT POWER IS ISOLATED FROM THE AI RCRAFT PRIOR TO STAR TING WORK.

WARNING: SOLVENT IS TOXIC TO SKIN, EYES, AND RESP IRATORY TRACT. AVOID REPEATED

OR PROLONGED CONTACT

. SKIN AND EYE PRO TECTION IS REQUIRED. GOOD VENTILATION IS REQUIRED. FAILURE TO COMPLY CO ULD RESULT IN SERIOU S INJURY TO PERSONNEL

.
WARNING: USE SEALANTS IN A WELL

- VENTILATED AREA. AVOID REPEATED CONTA CT WITH

SKIN. WASH HANDS AFTER HAN DLING SEALANT AND BE FORE EATING OR SMOKING. OBSERVE NO SMOKING REGULATIONS

.
A. PREPARE AIRCRAFT FOR INSPECTION AND/OR REPAIR

(1) Remove electrical power from aircraft in accordance with appropriate Hercules Maintenance Manual or Hercules Maintenance Instructions Manual

.
WARNING: ALL EQUIPMENT, INCLU DING WORK STAND S, SHALL BE ELECTRIC ALLY

GROUNDED TO THE AIRPLANE AND TO AN APPROVED GROUN DING POST. GROUND WIRES SHALL B E SECURELY ATTACHED TO CONNECTING POINTS TO MINIMIZE ACCIDENTAL DISCONNECTION. WORK STANDS SHALL BE EQUI PPED WITH COPPER, ZINC, O R ZINC

- COATED GROUND ING PLATES THAT CAN BE CONVENIENTLY CONTACT ED BY PERSONNEL ENTE RING THE WORK AREA.

(2) Static ground aircraft in accordance with appropriate Hercules Maintenance Manual or Hercules Maintenance Instructions Manual

. (3) Defuel the aircraft and purge fuel tanks and d ry bays in accordance with the appropriate Hercules Maintenance Manual or Hercules Maintenance Instructions Manual.

(4) Jack and level aircraft in accordance with the appropriate Hercules Maintenance Manual or Hercules Maintenance Instructions Manual using the WS 220 jacks and f uselage nose jacks.

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(5) Install and firmly snug m ain l anding g ear stands in position in accordance with F igure 57

- 10

- 02 of Hercules Structural Repair Manual. Release the WS 220 jacks so that the entire weight is supported by the m ain l andi ng g ear stands and f uselage n ose jacks. Install h orizontal s tabilizer jacks at horizontal stabilizer station HSS 122L & R
, the associated support pads should be positioned under the rib cap flanges at those locations and extend from the forward edge of th e front beam caps and the aft edge of the rear beam caps with pad lengths of approximately 5.5 in. Place the aft fuselage in a “no

- load” condition by raising the horizontal stabilizer jacks by 0.36

- 0.38 inch es

. Install fuselage support cradles in accor dance with F igure 51

- 110

- 01 of Hercules S tructural Repair Manual . Raise the WS 220 ja cks snug against the jack pads.

(6) Remove all four QEC s in accordance with the appropriate Hercules Maintenance Manual or Hercules Maintenance Instructions Manual.

(7) Refer to the specific jacking instructions for Inspection and Repair of the Center Wing in the He rcules Structural Repair Manual. The center wing is to be placed in the “no

- load” condition for the installation of repairs in accordance with C hapter 57

- 10 of Hercule s S tructural Repair M anual

. Position outer wing support beams at OWS 369 in accordance with F igure 57

- 10

- 02 of Hercules S tructural Repair M anual and record the elevation of each wing at OWS 369 above a fixed datum on the wing support jacks. Raise each OW S 369 wing support beam 3.4 ( ± 0.1) inches above the elevation recorded. T he WS 220 jacks may be lowered. Ensure all jacks are mechanica lly locked prior to proceeding.

CAUTION: MAINTENANCE AND INST ALLATION PERSONNEL M UST EXERCISE CAUTION

WHILE INCORPORATING THIS S ERVICE BULLETIN TO E NSURE THAT WIRING SYSTEMS ARE PROTECTE D AND KEPT CLEAN AT ALL TIMES. NOTE THA T METAL SHAVINGS CAUSE D BY DRILLING AND OT HER FORMS OF DEBRIS THAT CONTACT WIRE BUNDLES MIGHT IMPAIR WIRE SY STEM INTEGRITY AND SHORTEN SYSTEM AND C OMPONENT SE RVICE LIFE.

(8) Remove wing lower fillet fairing assemblies in accordance with appropriate Hercules Maintenance Manual or Hercules Maintenance Instructions Manual.

CAUTION: THE OUTER LAYER (FABRIC) OF THE BLADDER CELL IS ONLY COVERED WITH

A THIN COATING OF SYNTHETIC R UBBER AND CAN BE EASILY DAMAGED

. (9) Remove all auxiliary fuel tank bladders in accordance with appropriate Hercules Maintenance Manual or Hercules Maintenance Instructions Manual.

(10) Remove backing boards from the bottom of the auxiliary tanks as required to gai n access to lower surface.

(11) Remove c enter w ing f uel lines as necessary for access t o inspection areas

. F igure 1 illustrates installed fuel lines

. (12) Remove all plumbing brackets common to the upper crown of all lower surface stringers (hats)

- except items at tached with blind fasteners.

(13) Remove the nacelle fairings

, lower aft nacelle , and engine heat shield from N acelles 2 and 3.

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NOTE: The Nacelle Attach Fitting is installed with blind T aper
- L ok fasteners under the center of

each stringer (hat). Exercise caut ion when removing these fasteners to avoid damaging the lower surface panel, stringers and nacelle attach fitting.

(14) Remove E ngine 2 and 3 nacelle attach fittings (PN 390612) and aft nacelle fairing attach angle ( PN 370657) from the wing lower surface panels . Follow applicable instructions in C hapter 51

- 70 of the Hercules Structural Repair Manual for remo val of the T aper
- L ok fasteners.

(15) Remove drain troughs at WS 56, 72, 174 and 208, left and right. Follow applicable instructions in
c hapter 51

- 70 of the Herc ules Structural Repair Manual for removal of the T aper
- L ok fasteners.

(16) Remove the wing attach angle doublers (PN 394013 angle or PN 3313369 straps) at FS 580 to FS 612, WS 61 left and right. Note that prior to SN 4653 and aircraft with MEP center wings hav e a single piece angle doubler (PN 394013), later configurations have a strap (PN 3313369) installed on the horizontal and vertical flanges of the attach angle

. Follow applicable instructions in chapter 51

- 70 of the Hercules Structural Repair Manual for r emoval of the T aper
- L ok and H i

L ok fasteners.

(17) Remove misc/blankets covering the wing attach angle at BL 61, Left and Right.

B. INSPECTION

(1) Perform NDI of center wing lower surface panels and stringers under wing attach angle, WS 58 to WS 61, FS 517 to FS 597, left and right in accordance with Appendix A.

(2) Perform NDI of center wing lower surface panel s , and stringers under nacelle attach fitting and fairing attach angle, WS 178 and WS 213 , left and right in accordance with Appendix B.

(3) Perform NDI of center wing lower surface panels and stringers under the drain trough, WS 56, 72, 174
, and 208 , left and right in accordance with Appendix C.

(4) Perform NDI of center wing lower surface panels at stringer and beam cap attachments, WS 216 left to WS 216 right in accordanc e with Appendix D.

(5) Perform NDI of center wing lower surface stringers, WS 214 left to WS 214 right in accordance with Appendix E.

(6) Perform NDI of center wing lower surface front and rear beam caps, WS 210 left to WS 210 right in accordance with Appendix F.

(7) Perform NDI of center wing lower surface panel repairs in accordance with Appendix G.

(8) Perform NDI of the center wing lower surface panels at the rainbow fitting in accordance with Appendix A of Service Bulle tin 82

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. (9) Perform NDI of the center w ing lower forward corner fitting in accordance with Service Bulletin 82

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(1) Report any damage detected by the P aragraph 2.B inspection procedures to Lockheed Martin Aeronautics Company. Provide the following information of all damage d etected:
(a) Aircraft Serial Number

(b) Center Wing Flight Hours (or Aircraft Flight Hours if center wing hours is unknown)

(c) Center Wing Equivalent Baseline Hours (EBH) calc ulated in accordance with Service Bulletin 82

- 788.
(d) Part number and description
(e) Location (Win g Station, Fuselage Station), and specific fastener hole location

(f) Length, depth and orientation of crack

(2) Refer to the Hercules Structural Repair Manual for repair instructions. Contact Lockheed Martin Aeronautics Company if the damage exceeds the repair limits defined in the Hercules Structural Repair Manual.

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Revision 3, July 8, 2013 Page 13 D. RESTORE AIRCRAFT TO SERVICE

(1) Reinstall removals performed in section 2.A.

NOTE : Operators and Service Centers with adequate training and experience should

consider replacement of the removed TL100 a nd TL200 T aper
- L ok fasteners with H i

- T igue fasteners installed in cold worked holes; providing adequate edge distance is present in all layers of the fastened joint (not less than 1.4 times the final fastener hole diameter) and sufficient spacing exists be tween fasteners (not less than 2.5 times the final fastener nominal diameter). The May 2005 Revision of H ercules Structural Repair Manual contains Lockheed Martin Aeronautics Company approved procedures for cold working in chapter 51

- 70.

Repla cement of P rotruding

- head Taper

- Lok Fasteners (TL200): If edge distance and fastener

- to

- fastener spacing allow, cold

- work, drill for, and install a straight shank interference

- fit fastener (Hi

- Tigue) of 108 ksi or greater shear strength, such as an HLT114, HLT116, HL T124, HLT128, HLT420PB, HLT620PB, HLT714PB, H LT422PB, HLT622PB, or HLT716PB.

Replace ment of Flush

- head Taper

- Lok Fasteners (TL100): If edge distance and fastener

- to

- fastener spacing allow, cold

- work, drill for, and install a straight shank interference

- fi t fastener (Hi

- Tigue) of 108 ksi or greater shear strength, such as an HLT115, HLT123, HLT127, H LT421PB, HLT621PB, or HLT715PB.
Replacement of Protruding

- head Lockbolt Fasteners (H1446, H1448, SALP

- T8, NAS7036H, NAS7038H): If edge distance and fastener

- to

- fastener spacing allow, cold

- work, drill for, and install a straight shank interference

- fit tension head fastener (Hi

- Tigue) of 108 ksi or greater shear strength, such as an HLT116, HLT124, HLT128, H LT422PB, HLT622PB, or HLT716PB.
(a) Install the wing attach angle doublers (or straps) that were removed in P aragraph 2.A.(16).

(b) Install misc/blankets covering the wing attach angle at BL 61, l eft and r ight removed in P aragraph 2.A.(17)

. (c) Install drain troughs at WS 56, 72, 174 and 208, left and right removed in P ara graph 2. A .(15)

. (d) Install E ngine 2 and 3 nacelle attach fitting ( PN 390612) and aft nacelle fairing attach angle ( PN 370657) on the wing lower surface that were removed in P aragraph 2. A .(14).

(e) Install the nacelle fairing, lower aft nacelle, and engine heat sh ield on N acelle 2 and 3 that
were removed in P aragraph 2. A .(13).

(f) Install all plumbing brackets common to the upper crown of all lower surface stringers (hats) that were removed in P aragraph 2. A .(12).

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(g) Install center wing fuel lines that were removed in P ar agraph 2. A .(11). (See F igure 1.)

(h) Install backing boards to the bottom of the auxiliary tanks that were removed in P aragraph 2. A .(10)

. (i) Install all auxiliary fuel tank bladders that were removed in P aragraph 2. A .(9) in accordance with appropriate Hercules M aintenance Manual or Hercules Maintenance Instructions Manual.
(j) Install wing lower fillet fairing assemblies that were removed in P aragraph 2. A .(8) in accordance with appropriate Hercules Maintenance Manual or Hercules Maintenance Instructions Manual

. (2) Raise the WS 220 Jacks and firmly snug against the jack pads. Remo ve OWS 369 wing support beams.
(3) Install all four QEC s that were removed in P aragraph 2.A.(6) in accordance with the appropriate Hercules Maintenance Manual or Hercules Maintenance Instructions Ma nual.
(4) Remove the horizontal stabilizer supports.
(5) Raise the aircraft on the WS 220 and fuselage nose jacks sufficiently to take load off the main landing gear stands and fuselage cradles. Remove the stands and cradles. Lower the aircraft to the ground.
(6) Th e aircraft owner/operator shall make an appropriate entry in the aircraft log records upon compliance with this Service Bulletin.

(7) After the work has been completed on each affected aircraft, please complete and mail or fax (770

- 494

- 5682) a Notice of Ser vice Bulletin Compliance; or notify Lockheed Martin Aeronautics Company of compliance with this Service Bulletin at website address: www.lockheedmartin.com/eoc and log into Data Library.

NOTE: If assistanc e pertaining to this Service Bulletin or information regarding your Hercules aircraft

is needed, contact your local Lockheed Martin Aeronautics Company representative or the Enterprise Operations Center

- Technical Support in Marietta, Georgia, USA, as fol lows :
Telephone: (770 ) 494

- 9131
Fax: ( 770) 494

- 9122
E

- Mail: hercules.support@lmco.com

Mail: Lockheed Martin Aeronautics Company 86 South Cobb Drive Department 3E1M, Zone 0591 Marietta, GA 30063

- 0591, US A

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- Center Wing Fuel Cell Connecting Piping

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.

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Revision 3, July 8, 2013 Page 17 3. MATERIAL INFORMATION

A. The following parts/materials, required to modify each aircraft listed in P aragraph 1.A., will be provided by the aircra ft owner/operator. Parts may be obtained from Lockheed Martin Aeronautics Company in accordance with P aragraph 1.F.

NOTE: Drawings and diagrams have been listed with the most recent revision. However, superseding

revisions may be packed in the Kit.

NEW PART NU MBER QUANTITY KEY WORD OLD PART NUMBER INSTRUCTIONS/

DISPOSITION

373268

- 5 1 Attach Angle ( 3 ) (4 )

373268

- 6 1 Attach Angle ( 3 ) ( 4 )

390624

- 1 1 Attach Angle (2 )

390624

- 2 1 Attach Angle (2 )

390624

- 3 1 Attach Angle (5 )

390624

- 4 1 Attach Angle ( 5 )

3906 24

- 5 1 Attach Angle ( 6 ) ( 7 ) ( 8 )

390624

- 6 1 Attach Angle ( 6 ) ( 7 ) (8 )

373256 Rev. K 1 Attach Angle Installation

– Wing to Fuselage, Center Wing Station 61.625 Drawing (3 )

398914 Rev. C 1 Attach Angle Installation

– Wing to Fuselage, Center Wing Station 61. 625 Drawing (4 )

373277 Rev. L 1 Attach Angle

– Wing to Fuselage, Center Wing Station 61.625, Assembly of Drawing ( 3 ) ( 4 ) (5 )

393624 Rev. E 1 Attach Angle

– Wing to Fuselage, Center Wing Station 61.625 Drawing (2 )

3302629 Rev. C 1 Attach Angle Installat ion

– Center Wing to Fuselage, BL 61.625 FS 477 to 617, Mod Kit Drawing (2)

3303602 Rev. A 1 Attach Angle Installation

– Wing to Fuselage, Center Wing Station 61.625 Drawing (5 )

3305083 Rev. A 1 Attach Angle

– Wing to Fuselage, Center Wing Station 61.6 25, Assembly of Drawing ( 6 )( 7 ) ( 8 )

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, July 8, 2013 NEW PART NU MBER QUANTITY KEY WORD OLD PART NUMBER INSTRUCTIONS/

DISPOSITION

3305084 Rev. F 1 Attach Angle Installation

– Wing to Fuselage, Center Wing Station 61.625 Drawing (6 )

3313368 Rev. D 1 Attach Angle Installation

– Wing to Fuselage, Center Wing Station 61.625 Drawing (7 )

3333964 Rev. NC 1 Attach Angle Installation

– Wing to Fuselage, Center Wing Station 61.625 Drawing (8 )

NOTE: 1. If replacement wings are installed on aircraft

, use N ote 2.

2. MEP 4R, 7R, 7W, 8W, 12Y and 14Y Replacement Center Wings.

3. Lockheed Martin Serial Numbers 4299 throug h 4313

.

4. Lockheed Martin Serial Numbers 4314 through 4362

.

5. Lockheed Martin Serial Numbers 4363 through 4382

.
6. Lockheed Martin Serial Numbers 4383 through 4652

.

7. Lockheed Martin Serial Numbers 4653 through 5214

.
8. Lockheed Martin Serial Numbers 5215 through 5305

.
B. Replacement fasteners will be required for fasteners removed to carry out the inspection. The operator should ensure that adequate supplies of Taper

- Lok standard and oversize fasteners are available as follows:

(1) Wing Attach Angle Fasteners: standard TL 100, 1 st oversize TL110, 2 nd oversize TL130 and standard TL200, 1 st oversize TL210, and 2 nd oversize TL230.

(2) Drain Trough Attach Fasteners: standard TL100, 1 st oversize TL110, 2 nd oversize TL130 and standard TL200, 1 st oversize TL210, 2 nd oversize TL230.

(3) N acelle Attach Fitting and Fairing Attach Angle Fasteners: standard TL200, 1 st oversize TL210, 2 nd oversize TL230; and blind VA213 and oversize VA223.

_______#____

_ __
File: CR C130

- 03912 / I

- 3884R3

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Revision 3
, July 8, 2013 3 Page A 1 of A 1 4 NDI OF CENTER WING LOWER SURFACE PANEL S AND STRINGERS UNDER WING ATTACH ANGLE, WS 58 TO WS 61, FS 517 TO FS 597, LEFT AN D RIGHT REPLACEMENT OF ATTACH ANGLE AT CENTER WING STATION 61.625

1. PURPOSE

This procedure has been developed to detect generalized fatigue cracking and/or the possible onset of widespread fatigue damage in the center wing lower surface panels and stringers at all fastener holes common to the wing attach angle as shown in F igures A1 and A2 and as required for those fasteners common to the beam cap/stringer feet and rib caps as shown in Figure A3 . Fatigue cracks can originate in the center wing lower surface wing panel s and stringers at the indicated fastener attachment holes. The P rimary Procedure applies Automated Bolt Hole Eddy C urrent (ABHEC) through each layer of the attachment fastener holes of the center wing lower surface panels, stringers, and wing attach angle. The backup procedure for the Primary Proce dure is a redundant ABHEC scan.

2. DESCRIPTION

NOTE: Lockheed Martin Aeronautical Company recommends removing and replacing the wing attach

angle assembly with new manufactured parts. Do not remove both atta ch angles at the same time. Remove one attach angle (left or right), perform Primary Procedures 1 and 2, perform any required repairs, install a new attac h angle, the n proceed with removing the opposite attach angle repeating the inspection, repair and in stallation of a new attach angle. If any existing lower surface skin panel repair doublers are found under th e wing attach angle, these should also be removed to facilitate Primary Inspection Procedure No. 2. Center wing lower surface panels, stringers an d wing attach angle are fabricated from 7075 aluminum alloy

. Steel T aper
- L ok fasteners attach the wing lower surface assembly to the wing attach angle assembly. Service Bulletin 82

- 481/382

- 57

- 50 replaces four T aper
- L ok fasteners with larger diameter H i

- T igue fasteners in the area of FS 597

. Hercules Airfreighter Progressive Inspection Procedures or Hercules Airfreighter Series Progressive Inspection Procedures SP

- 138 inspects the area between FS 517 and 597 with radiography.

3. DAMAGE

NOTE : Some fatigue cra cks may be orientate d slightly inboard or outboard (up to 15 degrees) from the chordwise direction.
The fatigue damage originate s in the fastener holes of the lower surface panel s, stringers and/or front and rear beam caps and propagate s in a primarily for ward and aft direction

.

4. PREPARATION OF AIRPLANE

A. Prepare the airplane in accordance with P aragraph 2.A of Service Bulletin 82

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- 85. Ensure aircraft is jacked, leveled, fuselage cradles installed, horizontal tail jacks installed, and aft fuselage a nd wing is placed in the “no

- load” condition prior to proc eeding with fastener removals.

B. Remove the P/N 3305081 and P/N 3305082 Straps and P/N 390624 Wing Attach Angle

– do not remove both left and right attach angle at the same time. Refer to the Hercule s Structural Repair Manual for fastener removal instructions. Exercise caution in removing fasteners to avoid damaging the structure

.

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, July 8, 2013 5. PRIMARY PROCEDURE N O . 1

A BHEC scan of the center wing lower surface panel assembly fastener holes c ommon to the wing at tach angle assembly

. (See figures A1 and A2

. ) This includes approximately 154 fasteners shown in Figure A3. Verified damage requires additional inspection as described in paragraph 5.f. (See Figure A3.)

A. NDI Equipment:

 Eddy C urrent I nstrumen t

- Z etec MI Z

- 21A or equivalent

 Mini Probe D rive

- GE Inspection Techno logies PN 33A100 or equivalent

 Cable, MIZ

- 21 to mini probe drive

- Z etec PN 2100

- 03

- 04 or equival ent

 Probe, rotating hole, reflection type, 200 kHz to 2 MHz, 3/16” diameter

- GE Inspection Technolo gie s PN 620

- 546

- 187 or equivalen t

 Probe, rotating hole, reflection type

- 200 kHz to 2 MHz, 1/4” diameter, GE Inspection Technologies PN 620

- 546

- 016 or equivalent

 Calibration S tandard, a luminum

- VM Products, Inc. PN VM30889

- C1 A or equivalent ( S ee F igure A 4

. )

B. Access:

Use appropriate maintenance stands to gain access to the inspection area.

C. Preparation of Part:

Remove sealant from the fastener hole(s) with a nylon bristled brush of the appropriate diameter as necessary for acceptabl e probe contact with the part.

D. Equipment Calibration :
(1) Turn the instrument on.

(2) Conne ct the cable to the instrument.

(3) Connect the mini probe drive to the cable.

(4) Insert the appropriate diameter probe into the mini probe drive.

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Revision 3
, July 8, 2013 Page A 3 (5) Use the following initial instrume nt settings:

 FREQ 500K

 PRB REFL HI

 PRB GAIN 85

 MODE X

- Y

 V SCALE 0.2

 H SCALE 0.4

 FILTER DIFF 01

 SCREEN AUTOCLEAR 0

(6) Press the BAL button to null the instrument.

(7) Using the rocker switch on the probe controller, turn the rotating probe gun to the on po sition at the slow er of the two available speeds.

(8) Insert the probe coil into the standard adjacent to the 0.030” X 0.030” notch at the top of the appropriate diameter fastener hole. Adjust the PRB GAIN and PHASE to obtain a signal as shown in F igure A 5

. (9) Change MODE to TRG SWP and press the BAL button to null the instrument.

NOTE : It may be necessary to rotate the position of the probe controller to obtain a similar signal position

as shown in F igure A 6

. (10) With the rotating probe coil still hel d adjacent to the 0.030” X 0.030” notch at the top of the appropriate diameter fastener hole, adjust PRB GAIN
, V SCALE

, H SCALE and PHASE to obtain a signal height of approximately 98% as shown in F igure A 6

.
E. Inspection:

NOTE : The eddy current instrument must be recalibrated when probes are changed.

(1) Ensure instrument is calibrated in accordance with P aragraph D

. (2) S can each fastener hole common to the center wing lower surface panels and stringers (or beam caps) from FS 517 to FS 597

. (See F igures A1 and A2. )

(3) C onduct a redundant ABHEC backup procedure to confirm suspect damage in accordance with P aragraph F

.

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USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. August 4, 2005 Page A 4 Revision 3
, July 8, 2013 F. Redundant ABHEC Inspection (for confirmation only) :
(1) Inspector Verification

Reset and recalibrate the same equipment . The s ame inspector repea ts the inspection. If crack is confirmed, complete the verification outlined below.

(2) Verification

Preferred Method

– Different inspector repeats the inspection using the same equipment, after resetting and recalibrating the equipment.

Altern ate Method No. 1

– Inspector re inspects the area with an appropriate alternate method.

If a crack is verified in the lower surface center wing panel that extends from the hole to the edge of the panel common to the attach angle and beam cap (See Figure A3, Detail A) or extends from hole

- to

- hole common to the attach angle and stringers (See Figure A3, Detail B), remove the fastener immediately outboard of the attach angle common to the center wing lower surface panel and BL 61 rib at the beam cap or stringer nearest t he crack (See Figure A3, locations 1 and 2), and perform a ABHEC scan at this additional fastener location.

G

. Mark and Report D amage :

Mark damage in the panels, stringers and/or beam caps. Contact your local Lockheed Martin Aeronautics Company representa tive or the Technical Support Center in Marietta, Georgia, USA, with a damage report in accordance with P aragraph 2.C of Service Bulletin 82

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- 57

- 85 as follows :

Telephone: (770 ) 494

- 9131
Fax: ( 770) 494

- 9122
E

- Mail: hercules.support@lmco.com

Mail: Lockheed Martin Aeronautics Company 86 South Cobb Drive Department 3E1M, Zone 0591 Marietta, GA 30063

- 0591, USA

6. PRIMARY PROCEDURE NO. 2

Eddy current surface scan and visual inspection of the center wing lo wer panel in the area covered by the PN 390624 wing attach angle. (See F igures A1 and A2.)

A. NDI Equipment:

 Eddy Current Instrument

- Zetec MIZ

- 21A or equivalent

 Probe, Shielded Pencil

- Zetec PN DT30PS 50

- 500 k Hz or equivalent

 Probe Cable

- Zetec PN DTP H

- 3 or equivalent

 Calibration Standard, aluminum

- VM Products, Inc. PN VM30889

- C1A or equiv alent (See figure A3.)

 Draftsman’s Template

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Revision 3
, July 8, 2013 Page A 5 B. Access:

Use appropriate maintenance stands to gain access to the inspection area.

C. Preparation of Part:

Remove seal ant with a plastic or phenolic scraper as necessary for acceptable probe contact with the part using the procedures detailed in the Nondestructive Inspection (NDI) Procedur es Manual Supplem ent Section 20

- 00

- 00.

D. Equipment Calibration:

(1) Turn the instru ment on.
(2) Connect the probe/cable to the instrument.

(3) Select a frequency of 100 kHz.

(4) Place the probe on a defect free area of the standard.

(5) Press the BAL button to null the instrument.

(6) Remove the probe from the standard and note the dir ection of movement of the signal.

(7) Adjust the PRB GAIN and PHASE to obtain a lift

- off signal as shown in F igure A 7

.
NOTE : Adjusting the V SCALE and/or H SCALE may cause the lift

- off signal to be slightly distorted. This is a normal condition.

(8) Scan the four 0.100

- long notches in the standard and adjust the V SCALE

, H SCALE and GAIN to obtain optimum separation of the defect signals as shown in F igure A 7

.
E. Inspection:

NOTE : The eddy current instrument must be recalibrated when probes are changed.

(1 ) Ensure instrument is calibrated as in accordance with P aragraph D. With the wing attach angle removed, scan the exposed surface of the lower surface wing panel in the area of the removed attach angle from FS 517 to 597 and BL 58 to 61. Scan in both an inboard/outboard direction and chordwise direction on the panel. Any signal similar to the signals generated when scanning the notches in the standard will indicate a probable fatigue crack in the part being inspected. Perform a close visual inspection o f the panel in the area of the removed attach angle for cracks, corrosion and/or fretting damage; pay particular attention to the area in and around fastene r holes.

(2) To confirm suspected damage, conduct a redundant eddy current surface scan backup procedure in accordance with P aragraph F.

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, July 8, 2013 F. Redundant Inspection (for confirmation only):

(1) Inspector Verification

Reset and recalibrate the same equipment. The same inspector repeats the inspection. If crack is confirmed, complete the verification outlined b elow.

(2) Verification

Preferred Method

– Different inspector repeats the inspection using the same equipment, after resetting and recalibrating the equipment.

Alternate Method No. 1

– Inspector reinspects the area with an appropriate alternate method.

G. Mark and Report Damage:

Mark any damage in the panels, stringers and beam caps. Contact your local Lockheed Martin Aeronautics Company representative or the Enterprise Operations Center

- Technical Support in Marietta, Georgia, USA, with a report of any defects as follows :

Telephone: (770 ) 494

- 9131
Fax: ( 770) 494

- 9122
E

- Mail: hercules.support@lmco.com

Mail: Lockheed Martin Aeronautics Company 86 South Cobb Drive Department 3E1M, Zone 0591 Marietta, GA 30063

- 0591, USA

7. DAMAGE REPAIR

Repair any damage found in accordance with P aragraph 2.C.(2) of Service Bulletin 82

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. SYSTEM SECURING

A. Attach Angle Installation :

NOTE : Either original type fasteners may be installed at all removed locations for inspection, or installation of H i

- T igue fasteners in col d worked holes in accordance Hercules Structural Repair Manual may be performed where adequate edge distance and spacing exists. Operators and Service Centers are responsible for determining if they possess adequate training and the necessary tooling and procedures to perform this fatigue improvement

. (S ee P aragraph 2.D of Serv ice Bulletin 82

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- 85.)

Install a new PN 390624 attach angle and reinforcing straps (if applicable) according to the following drawing numbers:

NOTE: If MEP 4R, 7R, 7W, 8W, 12Y an d 14Y Replacement Center Wings are installed on aircraft use drawing number 3302629.

373256 Production Serial Numbers 4299 thru 4313

398914 Production Serial Numbers 4314 thru 4362

3303602 Production Serial Numbers 4363 thru 4382

3305084 Production Serial Numbers 4383 thru 4652

3313368 Production Serial Numbers 4653 thru 5214

3333964 Production Serial Numbers 5215 thru 5305

Reinstall the attach angle assembly with the next oversize T aper
- L ok fasteners in the wing panel assembly in accordance with C hapter 51

- 70 of Hercules S tructural Repair M anual and the above drawing numbers . Ensure proper fastener hole fit is attained in accordance with the hole inspection requirements of this manual. Proper installation of the T aper
- L ok is essential to attain required d urability. Install all fasteners wet with sealant in accordance with C hapter 51

- 40 of Hercules S tructural Repair M anual

.
B. System Securing :
For work directed by this Appendix only, restore finishes and sealants in accordance with Hercules Corrosion Preve ntion and Control M anual , reinstall removed components, remove equipment and supplies from the inspection area, and perform operational checkouts as required in accordance with applicable Hercules Maintenance Manual or Hercules Maintenance Instruction Manu al

.

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- Inspection Location

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- Outer View of Inspection Area

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- Conditional Outboard Row Inspection

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Figure A 4

- Calibration Standard, Aluminum

- VM Products, Inc. PN VM30889

- C1A

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Figure A 5

- Typical X

- Y Signal Response from 0.030” X 0.030” Notch

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Figure A 6

- Typical Time

- based Signal Response from 0.030” X 0.030” Notc h

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- Lift

- off and Notch Signals

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Revision 1, March 8
, 2007 Page B 1 of B12 NDI OF CENTER WING LOWER SURFACE PANEL S AND STRINGERS UNDER NACELLE ATTACH FITTING

AND FAIRING ATTACH ANGLE, WS 178 AND WS 213 , LEFT AND RIGHT

1. PURPOSE

Th is procedure has been developed to detect generalized fatigue cracking and/or the possible onset of widespread fatigue damage in the center wing lower surface panel s and stringers at all fastener holes common to the nacelle attach fitting and fairing attac h angles as shown in f igures B1 and B2. Fatigue cracks
can originate in the cente r wing lower surface wing panel s and stringers at the indicated faste ner attachment holes. Primary P rocedure No. 1 applies Automated Bolt Hole Eddy C urrent (ABHEC) through e ach layer of the attachment fastener holes of the center wing lower surface panels

, stringers , front beam lower cap and rib cap

. Primary Procedure No. 2 applies eddy current surface scans of the removed n acelle a ttach f itting and exposed area of the cente r wing lower surface panel after the fitting is removed. The backup procedure is a redundant ABHEC /surface scan inspection.

2. DESCRIPTION
Center wing lower surface panels and stringers are fabri cated from 7075 aluminum alloy. On some aircraft, stainless st eel lower surface panel doubler repairs may exist under the WS 213 nacelle attach fitting. At Lockheed Martin Serial Number 4351 and up and Center Wing MEP No. 12Y

- 0042, the nacelle attach fitting was redesigned and the material temper was changed from T6 to T73. The T6 tempered attach fitting is prone to stress corrosion cracking. Steel T aper
- L ok fasteners attach the lower nacelle attach fitting and aft nacelle fairing attach angle to the lower surface panel assembly. Hercules Airfreighter Progressive Inspection Procedure or Hercules Airfreighter S eries P rogressive Inspection Procedures Special Inspection SP

- 254 inspects this area by radiography.

3. D AMAGE

The fatigue damage originates in the fastener holes of the lower surface panels, stringers and front beam lower cap and propagate s in a chordwise direction.

4. PREPARATION OF AIRPLANE

Prepare the airplane in accordance with paragraph 2.A of Service Bulletin 82

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5. PRIMARY PROCEDURE NO. 1

A BHEC scan of the center wing lower surface panel fastener h oles common to the nacelle attach fitting and fairing attach angles. (See figures B1 and B2.)

A. NDI Equipment:

 Eddy Current I nstrumen t

- Zetec MIZ

- 21A or equivalent

 Mini Probe D rive

- GE Inspection Techno logies PN 33A100 or equivalent

 Cable, MIZ

- 21 to mini probe drive

- Zet ec PN 2100

- 03

- 04 or equivalent

 Probe, rotating hole, reflection type, 200 kHz to 2 MHz, 3/16” diameter

- GE Inspection Technologie s PN 620

- 546

- 187 or equivalent

 Calibration S tandard, a luminum

- VM Products, Inc. PN VM30889

- C1A or equivalen t ( S ee f igure B 3

. )

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USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DO CUMENT. Page B 2 Revision 1, March 8
, 2007 B. Access:

Use appropriate maintenance stands to gain access to the inspection area.

C. Preparation of Part:

Remove sealant from the fastener hole(s) with a nylon bristled brush of the appropriate diameter as necessary for acceptable probe co ntact with the part using the procedures detailed in the Nondestructive Inspection (NDI) Procedur es Manual Supplement

, Section 20

- 00

- 00.

D. Equipment Calibration :
(1) Turn the instrument on.

(2) Conne ct the cable to the instrument.

(3) Connect the mini probe drive to the cable.

(4) Insert the appropriate diameter probe into the mini probe drive.

(5) Use the following initial instrument settings:

 FREQ 500K

 PRB REFL HI

 PRB GAIN 85

 MODE X

- Y

 V SCALE 0.2

 H SCALE 0.4

 FILTER DIFF 01

 SCREEN AUTOCLEAR 0

(6) Press the BAL button to null the in strument.

(7) Using the rocker switch on the probe controller, turn the rotating probe gun to the on position at the slower of the two available speeds.

(8) Insert the probe coil into the standard adjacent to the 0.030” X 0.030” notch at the top of the appropriate diameter fastener hole. Adjust the PRB GAIN and PHASE to obtain a signal as shown in f igure B 4.

(9) Change MODE to TRG SWP and press the BAL button to null the instrument.

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Revision 1, March 8
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(10) With the rotating probe coil still held adjacent to the 0.030” X 0.030” notch at the top of the appropriate diameter fastener hole, adjust PRB GAIN
, V SCALE

, H SCALE and PHASE to obtain a signal height of appr ox imately 98% as shown in f igure B 5.

E. Inspection:

NOTE : The eddy current instrument must be recalibrated when probes are changed.

Ensure instrument is calibrated in accordance with paragraph D

. S can each fastener hole common to the nacelle attach fitting a nd fairing attach angle s as shown in f igure B 2.

C onduct a redundant ABHEC backup procedure to confirm suspected damage in accordance with paragraph F

.
F. Redundant ABHEC Inspection (for confirmation only):

(1) Inspector Verification

Reset and recalibrate the same equipment. The same inspector repeats the inspection. If crack is confirmed, complete the verification outlined below.

(2) Verification

Preferred Method

– Different inspector repeats the inspection using the same equipment, after resetting and recalibrating the equipment.

Altern ate Method No. 1

– Inspector re inspects the area with an appropriate alternate method.

G. Mark and Report Damage :
Mark any damage in the panels, stringers and front beam cap . Contact your local Lockheed Martin Aeronautics Company rep resentative or the Technical Support Center in Marietta, Georgia, USA, with a damage report in accordance with paragraph 2.C of Service Bulletin 82

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Telephone: (770 ) 494

- 9131
Fax: ( 770) 494

- 9122
E

- Mail: hercules.support@lmco.com
Mail: Lockheed Martin Aeronautics Company 86 South Cobb Drive Department 3E1M, Zone 0591 Marietta, GA 30063

- 0591, USA

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USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DO CUMENT. Page B 4 Revision 1, March 8
, 2007 6. PRIMARY PROCEDURE NO. 2

Eddy current surface scan and visual inspection of the center wing lower nacelle attach fitting (PN 390612), and the center wing lower surface panel in the area covered by the nacelle attach fitting

. (See figures B1 and B2.)

A. NDI Equipment:

 Eddy Current I nstrument

- Zetec MIZ

- 21A or equivalent

 Probe, Shielded Pen cil

- Zetec PN DT30PS 50

- 500 k Hz or equivalent

 Probe Cable

- Zetec PN DTPH

- 3 or equivalent

 Calibration S tandard, a luminum

- VM Products, Inc. PN VM30889

- C1A or equiv alent ( S ee f igure B3

. )

 Draftsman’s Template

B. Access:

Use appropriate maintenance stands t o gain access to the inspection area.

C. Preparation of P art:

Remove sealant with a plastic or ph e n o lic scraper as necessary for acceptable probe contact with the part using the procedures detailed in the Nondestructive Inspection (NDI) Procedur es Manual S upplement Section 20

- 00

- 00.

D. Equipment C alibration:

(1) Turn the instrument on.

(2) Connect the probe/cable to the instrument.

(3) Select a frequency of 100 kHz.

(4) Place the probe on a defect free area of the standard.

(5) Press the BAL button to null the instrument.

(6) Remove the probe from the standard and note the direction of movement of the signal.

(7) Adjust the PRB GAIN and PHASE to obtain a lift

- off signal as shown in f igure B6.

NOTE : Adjusting the V SCALE and/or H SCALE may cause the lift

- off signal to be slightly distorted. This is a normal condition.

(8) Scan the four 0.100

- long notches in the standard and adjust the V SCALE

, H SCALE and GAIN to obtain optimum separation of the defect signals as shown in f igure B6.

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Revision 1, March 8
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NOTE : The eddy current instrument must be recalibrated when probes are changed.

Ensure instrument is calibrated as in accordance with paragraph D. With the n acelle a ttach f itting removed, scan the fitting using overlapping scans. Scan both along the length and acr oss the width of the fitting. In addition, scan the exposed surface of the lower surface wing panel in the area of the removed attach fitting and fairing attach angle

. Scan in both an inboard/outboard direction and chordwise direction on the panel. Any signal similar to the signals generated when scanning the notches in the standard will indicate a probable fatigue crack in the part being inspected. Perform a close visual inspection of the panel in the area of the removed nacelle attach fitting

, and fai ring attach angle
, and the truss mount lower tang for c orrosion and/or fretting damage; pay particular attention to the area in and around fastener holes.

To confirm suspected d amage , conduct a redundant eddy current surface scan backup procedure in accord ance with paragraph F

.
F. Redundant Inspection (for confirmation only) :
(1) Inspector Verification

Reset and recalibrate the same equipment. The same inspector repeats the inspection. If crack is confirmed, complete the verification outlined below.

(2) V erification

Preferred Method

– Different inspector repeats the inspection using the same equipment, after resetting and recalibrating the equipment.

Altern ate Method No. 1

– Inspector re inspects the area with an appropriate alternate method.

G. Mark and Re port D amage :
Mark any damage in the panel s , stringers, front beam cap and nacelle attach fitting . Contact your local Lockheed Martin Aeronautics Company representative or the Technical Support Center in Marietta, Georgia, USA, with a report of any defects as follows :

Telephone: (770 ) 494

- 9131
Fax: ( 770) 494

- 9122
E

- Mail: hercules.support@lmco.com

Mail: Lockheed Martin Aeronautics Company 86 South Cobb Drive Department 3E1M, Zone 0591 Marietta, GA 30063

- 0 591, USA

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, 2007 7

. DAMAGE REPAIR

Repair any damage found in accordance with paragraph 2.C.(2) of Service Bulletin 82

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8. SYSTEM SECURING

A. Fastener Installation :

NOTE : Either original type fasteners may be installed at all removed locations for in spection, or installation of H i

- T igue fasteners in cold worked holes may be performed where adequate edge distance and spacing exists. Operators and Service Centers are responsible for determining if they possess adequate training and the necessary toolin g and procedures to perform this fatigue improvement

. (S ee paragraph 2.D of Ser vice Bulletin 82

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Reinstall the next oversize T aper
- L ok fasteners in accordance with C hapter 51

- 70 of Hercules S tructural Repair Manual . Ensure proper fastener hole fit is attained in accordance with the hole inspection requirements of this manual. Proper installation of the T aper
- L ok is essential to attain maximum durability. Install all fasteners wet with sealant in accordance with C hapter 51

- 40 of Hercules S tructural Repair M anual

.
B. System Securing :
For work directed by this Appendix only, restore finishes and sealants in accordance with Hercules Corrosion Prevention and Control M anual , reinstall removed components, remove equipment and supplies from the in spection area, and perform operational checkouts as required in accordance with applicable Hercules Maintenance Manual or Hercules Maintenance Instructions Manual

.

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- Center Wing Lower Surface Inspection Area

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Figure B 2

- Center Wing Lowe r Surface Panels Under Left Nacelle, Right Opposite

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Figure B 3

- Calibration Standard, Aluminum

- VM Products, Inc. PN VM30889

- C1A

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Figure B 4

- Typical X

- Y Signal Response from 0.030” X 0.030” Notch

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Figure B 5

- Typical Time

- based Signal Respon se from 0.030” X 0.030” Notch

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USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DO CUMENT. Page B 12 Revision 1, March 8
, 2007 Figure B 6

- Lift

- off and Notch Signals

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Revision 1, March 8
, 2007 Page C 1 of C 14 NDI OF CENTER WING LOWER SURFACE PANEL S AND STRINGERS UNDER THE DRAIN TROUGH , WS 56, 72, 174, AND 2 08 , LEFT AND RIGHT

1. PURPOSE

This procedure has been developed to detect generalized fatigue cracking and/or the possible onset of widespread fatigue damage in the center wing lower surface panel s and stringers at fastener holes common to the drain trough and around each drain hole at WS 56, 72, 174 and 208 as shown in f igure C 1. Fatigue cracks can originate in the center wing lower surface wing panel s at the indicated fastener attachment h oles and drain holes. Primary P rocedure No. 1 applies A utomated B olt H ole E ddy C urrent (ABHEC) scans of the attachment fastener holes. Primary P roced ure No. 2 applies eddy current surface scans around each drain hole in the center wing lower surface panel s . The backup procedure is a redundant ABHEC /surface scan.

2. DESCRIPTION

Center wing lower surface panels are fabri cated from 7075 aluminum alloy. Alu minum alloy drain troughs are installed on the exterior surface of the lower panels to collect and drain fluids from inside the wing box. Steel and/or Titanium drain plugs (bushings) are installed in the skin panels between each adjacent stringer foot. H ercules S tructural Repair M anual Special Inspection SP

- 314 insp ects this area by radiography.

3. D AMAGE

The fatigue damage originate s in the fastener holes of the lower surface panel and stringers common to the drain trough attachment and also in the lower su rface panels at the drain plug (bushing) holes and propagate in a chordwise direction.

4. PREPARATION OF AIRPLANE

Prepare the airplane in accordance with paragraph 2.A of Service Bulletin 82

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5. PRIMARY PROCEDURE NO. 1

ABHEC scan of the center wing lower surface panel at WS 56, 72, 174, and 208

. (See figure C1.)

A. NDI Equipment:

 Eddy Current I nstrumen t

- Zetec MIZ

- 21A or equivalent

 Mini Probe D rive

- GE Inspection Techno logies PN 33A100 or equivalent

 Cable, MIZ

- 21 to mini probe drive

- Zet ec PN 2100

- 03

- 04 or equivalent

 Probe, rotating hole, reflection type, 200 kHz to 2 MHz, 3/16” diameter

- GE Inspection Technologie s PN 620

- 546

- 187 or equivalent

 Calibration S tandard, a luminum

- VM Products, Inc. PN VM30889

- C1A or equivalent (S ee f igure C2

. )

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USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THI S DOCUMENT. Page C 2 Revision 1, March 8
, 2007 B. Access:

Use appropriate maintenance stands to gain access to the inspection area.

C. Preparation of Part:

Remove sealant from the fastener hole(s) with a nylon bristled brush of the appropriate diameter as necessary for acceptable probe contact with the part.

D. Equipme nt Calibration :
(1) Turn the instrument on.

(2) Connect the cable to the instrument.

(3) Connect the mini probe drive to the cable.

(4) Insert the appropriate diameter probe into the mini probe drive.

(5) Use the following initial instrument settings:

 FREQ 500K

 PRB REFL HI

 PR B GAIN 85

 MODE X

- Y

 V SCALE 0.2

 H SCALE 0.4

 FILTER DIFF 01

 SCREEN AUTOCLEAR 0

(6) Press the BAL button to null the instrument.

(7) Using the rocker switch on the probe controller, turn the rotating probe gun to the on position at the slower of the two available spe eds.

(8) Insert the probe coil into the standard adjacent to the 0.030” X 0.030” notch at the top of the appropriate diameter fastener hole. Adjust the PRB GAIN and PHASE to obtain a signal as shown in f igure C 3

. (9) Change MODE to TRG SWP and press the BAL butto n to null the instrument.

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Revision 1, March 8
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. (10) With the rotating probe coil still held adjacent to the 0.030” X 0.030” notch at the top of the
a ppropriate diameter fastener hole, adjust PRB GAIN
, V SCALE

, H SCALE and PHASE to obtain a signal height of approx imately 98% as shown in f igure C4

.
E. Inspection:

NOTE : The eddy current instrument must be recalibrated when probes are changed.

Ensure instrume nt is calibrated as in accordance with paragraph D. Scan each fastener hole common to the removed drain troughs through all layers of material. Any signal similar to the signals generated when scanning the notches in the standard will indicate a probable fatigue crack in the part being inspected.

To confirm suspected damage , conduct a redundant ABHEC backup procedure in accordance with paragraph F

.
F. Redundant ABHEC Inspection (for confirmation only):

(1) Inspector Verification

Reset and recalibrate the same eq uipment. The same inspector repeats the inspection. If crack is confirmed, complete the verification outlined below.

(2) Verification

Preferred Method

– Different inspector repeats the inspection using the same equipment, after resetting and recalibrating th e equipment.

Altern ate Method No. 1

– Inspector re inspects the area with an appropriate alternate method.

G. Mark and Report Damage :
Mark any damage in the lower surface panel and stringers . Contact your local Lockheed Martin Aeronautics Company represent ative or the Technical Support Center in Marietta, Georgia, USA, with a damage report in accordance with paragraph 2.C of Service Bulletin 82

- 790/382

- 57

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Telephone: (770 ) 494

- 9131
Fax: ( 770) 494

- 9122
E

- Mail: hercules.support@lmco.com

Mail: Lockheed Martin Aeronautics Company 86 South Cobb Drive Department 3E1M, Zone 0591 Marietta, GA 30063

- 0591, USA

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USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THI S DOCUMENT. Page C 4 Revision 1, March 8
, 2007 6. PRIMARY PROCEDURE NO. 2

Eddy current surface scan of the center wing lower surface panel s a round the drain holes at WS 56, 72, 174

, and 208 and a visual inspection of the panel in the area covered by the drain troughs

. (See figure C1.)

A. NDI Equipment:

 E ddy Current I nstrument

- Zetec MIZ

- 21A or equivalent

 P robe, Shielded Pencil

- Zetec PN DT30 PS 50

- 50 0 k Hz or equivalent

 Probe Cable

- Zetec PN DTPH

- 3 or equivalent

 Calibration S tandard, a luminum

- VM Products, Inc. PN VM30889

- C1A or equivalent (See f igure C2

. )

 Draft sman’s Template

B. Access:

Use appropriate maintenance stands to gain access to th e inspection area.

C. Preparation of P art:

Remove sealant with a plastic or ph e n o lic scraper as necessary for acceptable probe contact with the part using the procedures detailed in the Nondestructive Inspection (NDI) Procedur es Manual Supplement Section 2 0

- 00

- 00.

D. Equipment C alib ration :
(1) Turn the instrument on.

(2) Connect the probe/cable to the instrument.

(3) Select a frequency of 100 kHz.

(4) Place the probe on a defect free area of the standard.

(5) Press the BAL button to null the instrument.

(6) Remove the probe from t he standard and note the direction of movement of the signal.

(7) Adjust the PRB GAIN and PHASE to obtain a lift

- off signal as shown in f igure C5

.
NOTE : Adjusting the V SCALE and/or H SCALE may cause the lift

- off signal to be slightly distorted. This is a nor mal condition.

(8) Scan the four 0.100

- long notches in the standard and adjust the V SCALE

, H SCALE and GAIN to obtain optimum separation of the defe ct signals as shown in f igure C5

.

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Revision 1, March 8
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NOTE : The eddy current instrument must be recalibrated when p robes are changed.

(1) En sure instrument is calibrated in accordance with paragraph 6. D. Using the drain plug (bushing) attach nut as a guide, scan the lower surface panel s from the exterior around each indicated drain hole at WS 56, 72, 174, and 208 as s hown in f igure C6 . Scan in both a clockwise a nd counterclockwise direction.

(2) Where access permits, scan the lower surface panel s from the interior of the center wing tank at each drain plug (bushing) location. See f igure C7 for typical probe placement on the interior surface

. (3) Any signal similar to the signals generated when scanning the notches in the standard will indicate a probable fatigue crack in the part being inspected.

(4) To confirm su spected damage, remove bushing at suspected damage and conduct an ABHEC scan backup procedure in accordance with paragraph F.

F. Backup Inspection (for confirmation only):

To confirm suspec ted damage, remove bushing and perform backup ABHEC scan.

(1) NDI Equipment:

 Eddy Current I nstrument

- Zetec MIZ

- 21A or eq uivalent

 Mini Probe D rive

- GE Inspection Technologies PN 33A100 or equivalent

 Cable, MIZ

- 21 to mini probe drive

- Zetec PN 2100

- 03

- 04 or equivalent

 Probe, rotating hole, reflection type, 200 kHz to 2 MHz, 3/16” diameter

- GE Inspection Technologies PN 620

- 546

- 187 or equivalent

 Calibration S tandard, aluminum

- VM Products, Inc. PN VM30889

- C1A or equivalent (See figure C2

. )

(2) Equipment Calibration:

(a) Turn the instrument on.

(b) Connect the cable to the instrument.

(c) Connect the mini probe drive to the cable.

(d) Insert the appropriate diameter probe into the mini probe drive.

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(e) Use the following initial instrument settings:

 FREQ 500K

 PRB REFL HI

 PRB GAIN 85

 MODE X

- Y

 V SCALE 0.2

 H SCALE 0.4

 FILTER DIFF 01

 SCREEN AUTOCLEAR 0

(f) Press the BAL button to null the instrument.

(g) Using the rocker switch on the probe controller, turn the rotating probe gun to the on position at the slower of the two available speeds.

(h) Insert the probe coil into the standard adjacent to the 0.030” X 0.030” notch at the to p of the appropriate diameter fastener hole. Adjust the PRB GAIN and PHASE to obtain a signal as shown in figure C3

. (i) Change MODE to TRG SWP and press the BAL button to null the instrument.

NOTE : It may be necessary to rotate the position of the probe controller to obtain a similar signal position as shown in figure C4

. (j) With the rotating probe coil still held adjacent to the 0.030” X 0.030” notch at the top of the appropriate diameter fastener hole, adjust PRB GAIN
, V SCALE

, H SCALE and PHASE to obt ain a signal height of approximately 98% as shown in figure C4

. (3 ) Inspection:

NOTE : The eddy current instrument must be recalibrated when probes are changed.

Ensure instrument is calibrated as in accordance with paragr aph (2). P erform a backup inspecti on of suspect damage using an ABHEC scan.

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Mark any damage in the lower surface panels . Contact your local Lockheed Martin Aeronautics Company representative or the Technical Support Center in Marietta, Georgia, USA, with a dama ge report in accordance with paragraph 2.C of Service Bulletin 82

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Telephone: (770 ) 494

- 9131
Fax: ( 770) 494

- 9122
E

- Mail: hercules.support@lmco.com

Mail: Lockheed Martin Aeronaut ics Company 86 South Cobb Drive Department 3E1M, Zone 0591 Marietta, GA 30063

- 0591, USA

7

. DAMAGE REPAIR

Repair any damage found in accordance with paragraph 2.C.(2) of Service Bulletin 82

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8. SYSTEM SECURING

A. Fastener Installation :

NOTE : E ither original type fasteners may be installed at all removed locations for inspection, or installation of H i

- T igue fasteners in cold worked holes may be performed where adequate edge distance and spacing exists. Operators and Service Centers are responsi ble for determining if they possess adequate training and the necessary tooling and procedures to perform this fatigue improvement

. (S ee paragraph 2.D of Ser vice Bulletin 82

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Reinstall the next oversize T aper
- L ok fasteners in accordance wit h C hapter 51

- 70 of Hercules S tructural Repair M anual . Ensure proper fastener hole fit is attained in accordance with the hole inspection requirements of this manual. Proper installation of the T aper
- L ok is essential to attain maximum durability. Install all fasteners wet with sealant in accordance with C hapter 51

- 40 of Hercules S tructural Repair M anual

.
B. System Securing :
For work directed by this Appendix only, restore finishes and sealants in accordance with Hercules Corrosion Prevention and Control M anual , reinstall removed components, remove equipment and supplies from the inspection area, and perform operational checkouts as required in accordance with applicable Hercules Maintenance Manual or Hercules Maintenance Instructions Manual

.

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, 2007 Figure C 1

- Drain Trough Locations

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Figure C2

- Calibration Standard, Aluminum

- VM Products, Inc. PN VM30889

- C1A

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, 2007

Figure C3

- Typical X

- Y Signal Response from 0.030” X 0.030” Notch

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Figure C4

- Typical Time

- based Signal Response from 0.030” X 0.030” No tch

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, 2007 Figure C5

- Lift

- off and Notch Signals

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- Typical Probe Placement Exterior Surface

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, 2007 Figure C7

- Typical Probe Placement Interior Surface

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Revision 1, March 8
, 2007 Page D 1 of D1 4 NDI OF CENTER WING LOWER SURFACE PANEL S A T STRINGER AND BEAM CAP ATTACHMENTS , WS 216 LEFT TO WS 216 RIGHT

1. PURPOSE

This procedure has been developed to detect generalized fatigue cracking and/or the possible onset of widespread fatigue damage in the center wing lower surface panel s at all exposed fasten er holes in the lower surface panels to include forward and aft beam cap attachment fasteners

, all stringer attachments and lower wing joint (rainbow) fitting attachments as shown in f igure D 1. Fatigue cracks can originate in the center wing lower surface panel s at the indicated fastener attachment holes. Primary procedure No. 1 applies eddy current surface scans around attachment fastener holes of the center wing lower surface panels. Primary procedure No. 2 applies an Automated Bolt Hole Eddy Current ( ABHEC) scan to the lower surface panels at the front beam cap where angles are installed attaching the center wing assembly to the FS 517 Main Frames. The backup procedure is a n A utomated Bolt H ole Eddy C urrent (ABHEC) scan.

2. DESCRIPTION

Center wing lo wer surface panels are fabri cated from 7075 aluminum alloy. Steel T aper
- L ok fasteners and aluminum rivets attach the stringers to the skin panels. External splice plates ( straps ) fabricated from 7075 aluminum alloy join panel num ber 1 to 2 and join panel number 2 to 3 from WS 65 to WS 166. Steel T aper
- L ok fasteners attach the front and rear beam caps to the skin panels. External doublers installed at production may exist at the panel splice locations at WS 62 to 68 which are recommended for permanent

re moval by Service Bulletin 82

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- 86 inspects the exposed part of the lower surface number 1 (forward) panel around the PN 373275 angle attaching the panel to the FS 517 Main Frame, Primary Procedure No. 2 in this Appendix will detect significantly shorter cracks in the panel by using an ABHEC procedure at all attachment fastener locations.

3. D AMAGE

The fatigue c racks originate in the fastener holes in the skin panels and propagate in a chordwise direction.

4. PREP ARATION OF AIRPLANE

Prepare the airplane in accordance with paragraph 2.A of Service Bulletin 82

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Remove the PN 373275 angle attaching the lower surface forward panel to the FS 517 Main Frame. Refer to Service Bulletin 82

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- 86 for the location of this angle. Refer to the Hercules Structural Repair Manual for fastener removal instructions. Exercise caution in removing fasteners to avoid damaging the structure.

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USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. Page D 2 Revision 1, March 8
, 2007 5. PRIMARY PROCEDURE NO. 1

Eddy current surface scan of the center wing lower surface panels

. (See figure D1.)

A. NDI Equipment:

 E ddy Current I nstrument

- Zetec MIZ

- 21A or equivalent

 Probe, Shielded Pencil

- Zetec PN DT30PS 50

- 50 0 k Hz or equivalent

 Probe Cable

- Zetec PN DTPH

- 3 or equivalent

 Calibration S tandard, a luminum

- VM Products, Inc. PN VM30889

- C1A or equivalent ( S ee f igure D 2

. )

 Draft sman’s Template

B. Access:

Use appropriate maintenance stands to gain access to the inspection area.

C. Preparation of Part:

Remove sealant with a plastic or phenolic scraper as necessary for a cceptable probe contact with the part using the procedures detailed in the Nondestructive Inspection (NDI) Procedur es Manual Supplement Section 20

- 00

- 00.

D. Equipment Calibration:

(1) Turn the instrument on.

(2) Connect the probe/ cable to the instrument.

(3) Select a frequency of 100 kHz

. (4) Place the probe on a defect free area of standard

. (5) Press the BAL button to null the instrument

. (6) Remove the probe from the standard and note the direction of movement of the signal. Adjust the PRB GAIN and PHASE t o obtain a lift

- off signal as shown in figure D3.

NOTE : Adjust the V SCALE and/or H SCALE may cause the lift

- off signal to be slightly distorted. This is a normal condition.

(7) Scan the four 0.100

- long notches in the standard and adjust the V SCALE

, H SC ALE and GAIN to obtain optimum separation of the defect signals as shown in figure D3.

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NOTE : The eddy current instrument must be recalibrated when probes are changed.

(1) Ensure instrument is calibrated as in accordance with paragraph D. Using th e draftsman’s template or the protruding head of the fastener, scan the external center wing lower surface panels around each accessible fastener as shown in f igure D4

. Use the smallest diameter hole in the template that will allow the placement of the pr obe as close to the edge of each hole as possible. Scan in both a clockwise and countercl ockwise direction. See figure D4 for typical probe placement example. Any signal similar to the signals generated when scanning the notches in the standard will ind icate a probable fatigue crack in the part being inspected.

(2) Ensure all fasteners common to the front and rear beam lower caps , the thirteen lower surface panel stringers and the lower wing joint (rainbow) fitting are inspected from WS 216 left to WS 216 ri ght

. (3) In the area of the external skin panel spanwise splice plates ( straps ) between Panel No. 1 and 2 and between Panel No. 2 and 3 (from WS 75 to WS 166) scan along the forward and aft edge of the strap. Fatigue cracks may propagate out from under the ed ge of the straps.

(4) In the area around the wing fillet fairing attach holes at WS 80, scan around the open attach holes and riveted nut plate attachment fasteners.

(5) In the area of the removed aft nacelle fairing assembly , scan around the exposed stud bolts us ed to attach the fairi ng to the lower surface panel.

To confirm suspected damage, remove fasteners at suspected damage and conduct an ABHEC scan backup procedure in accordance with paragraph F.

F. Backup Inspection (for confirmation only):

To confirm suspe cted damage, remove fasteners and perform backup ABHEC scan.

(1) NDI Equipment:

 Eddy C urrent I nstrument

- Zetec MIZ

- 21A or equivalent

 Mini Probe D rive

- GE Inspection Technologies PN 33A100 or equivalent

 Cable, MIZ

- 21 to mini probe drive

- Zetec PN 2100

- 0 3

- 04 or equivalent

 Probe, rotating hole, reflection type, 200 kHz to 2 MHz, 3/16” diameter

- GE Inspection Technologies PN 620

- 546

- 187 or equivalent

 Calibration S tandard, aluminum

- VM Products, Inc. PN VM30889

- C1A or equivalent ( S ee figure D2

. )

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USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. Page D 4 Revision 1, March 8
, 2007 (2) Equip ment Calibration:

(a) Turn the instrument on.

(b) Connect the cable to the instrument.

(c) Connect the mini probe drive to the cable.

(d) Insert the appropriate diameter probe into the mini probe drive.

(e) Use the following initial instrument settings:

 FR EQ 500K

 PRB REFL HI

 PRB GAIN 85

 MODE X

- Y

 V SCALE 0.2

 H SCALE 0.4

 FILTER DIFF 01

 SCREEN AUTOCLEAR 0

(f) Press the BAL button to null the instrument.

(g) Using the rocker switch on the probe controller, turn the rotating probe gun to the on position at the s lower of the two available speeds.

(h) Insert the probe coil into the standard adjacent to the 0.030” X 0.030” notch at the top of the appropriate diameter fastener hole. Adjust the PRB GAIN and PHASE to obtain a signal as shown in figure D 5

. (i) Change M ODE to TRG SWP and press the BAL button to null the instrument.

NOTE : It may be necessary to rotate the position of the probe controller to obtain a similar signal position as shown in figure D6

. (j) With the rotating probe coil still held adjacent to the 0.030” X 0.030” notch at the top of the appropriate diameter fastener hole, adjust PRB GAIN
, V SCALE

, H SCALE and PHASE to obtain a signal height of approximately 98% as shown in figure D6

.

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NOTE : The eddy current instrument must be recali brated when probes are changed.

Ensure instrument is calibrated as in accordance with paragraph (2)

Remove fasteners and perform a backup inspection of suspect damage using an ABHEC scan.

G. Mark and R eport D amage :
Mark any damage in the lower surface panel

. Contact your local Lockheed Martin Aeronautics Company representative or the Technical Support Center in Marietta, Georgia, USA, with a damage report in accordance with paragraph 2.C of Service Bulletin 82

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Telephone: (770 ) 494

- 9 131
Fax: ( 770) 494

- 9122
E

- Mail: hercules.support@lmco.com

Mail: Lockheed Martin Aeronautics Company 86 South Cobb Drive Department 3E1M, Zone 0591 Marietta, GA 30063

- 0591
, USA

6

. P RIMARY PROCEDURE NO. 2

Automated Bolt Hole Eddy Current Inspection of lower surface forward panel at the PN 373275 at tach angle to FS 517 Main Frame.

A. NDI Equipment:

 Eddy Current Instrument

- Zetec MIZ

- 21A or equivalent

 Mini Probe Drive

- GE Inspection Technologies PN 33A100 or equivalent

 Cable, MIZ

- 21 to mini probe drive

- Zetec PN 2100

- 03

- 04 or equivalent

 Probe, rotating hole, reflection type, 200 kHz to 2 MHz, 3/16” diameter

- GE Inspection Technologies PN 620

- 546

- 187 or equivalent

 Probe, rotating hole, reflection type

- 20 0 kHz to 2 MHz, 1/4” diameter, GE Inspection Technologies PN 620

- 546

- 016 or equivalent

 Calibration Standard, aluminum

- VM Products, Inc. PN VM30889

- C1A or equivalent (See figure D2 .)

B. Access:

Use appropriate maintenance stands to gain access to the insp ection area.

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USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. Page D 6 Revision 1, March 8
, 2007 C. Preparation of Part:

Remove sealant from the fastener hole(s) with a nylon bristled brush of the appropriate diameter as necessary for acceptable probe contact with the part.

D. Equipment Calibration:

(1) Turn the instrument on.

(2) Conne ct the cable to the instrument.

(3) Connect the mini probe drive to the cable.

(4) Insert the appropriate diameter probe into the mini probe drive.

(5) Use the following initial instrument settings:

 FREQ 500K

 PRB REFL HI

 PRB GAIN 85

 MODE X

- Y

 V SCALE 0.2

 H SCALE 0.4

 FILTER DIFF 01

 SCREEN AUTOCLEAR 0

(6) Press the BAL button to null the instrument.

(7) Using the rocker switch on the probe controller, turn the rotating probe gun to the on position at the slower of the two available speeds.

(8) Insert the probe coil into the standard adjacent to the 0.030” X 0.030” notch at the top of the appropriate diameter fastener hole. Adjust the PRB GAIN and PHASE to obtain a signal as shown in figure D5

. (9) Change MODE to TRG SWP and press the BAL button to null the ins trument.

NOTE : It may be necessary to rotate the position of the probe controller to obtain a similar signal position

as shown in figure D6

. (10) With the rotating probe coil still held adjacent to the 0.030” X 0.030” notch at the top of the appropriate di ameter fastener hole, adjust PRB GAIN
, V SCALE

, H SCALE and PHASE to obtain a signal height of approximately 98% as shown in figure D6

.

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NOTE : The eddy current instrument must be recalibrated when probes are changed.

Ensure instrument is ca librated in accordance with paragraph D.
Scan each open fastener hole common to the center wing lower surface panels and front beam cap from approximately WS 63 to WS 71.

Conduct a redundant ABHEC backup procedure to confirm suspect damage in accordance with paragraph F.

F. Redundant ABHEC Inspection (for confirmation only):

(1) Inspector Verification

Reset and recalibrate the same equipment. The same inspector repeats the inspection. If crack is confirmed, complete the verification outlined below.

(2) Verification

Preferred Method

– Different inspector repeats the inspection using the same equipment, after resetting and recalibrating the equipment.

Altern ate Method No. 1

– Inspector re inspects the area with an appropriate alternate method.

G. Mark and Report Damage:

Mark damage in the panels, stringers and/or beam caps. Contact your local Lockheed Martin Aeronautics Company representative or the Technical Support Center in Marietta, Georgia, USA, with a damage report in accordance with paragraph 2.C of Service Bulletin 82

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Telephone: (770 ) 494

- 9131
Fax: ( 770) 494

- 9122
E

- Mail: hercules.support@lmco.com

Mail: Lockheed Martin Aeronautics Company 86 South Cobb Drive Department 3E 1M, Zone 0591 Marietta, GA 30063

- 0591, USA

7. DAMAGE REPAIR Repair any damage found in accordance with paragraph 2.C.(2) of Service Bulletin 82

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USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. Page D 8 Revision 1, March 8
, 2007 8. SYSTEM SECURING

A. Fastener Installation:

NOTE : Either original type fasteners may be instal led at all removed locations for inspection, or installation of Hi

- Tigue fasteners in cold worked holes may be performed where adequate edge distance and spacing exists. Operators and Service Centers are responsible for determining if they possess adequat e training and the necessary tooling and procedures to perform this fatigue improvement. (See paragraph 2.D of Service Bulletin 82

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Reinstall the next oversize Taper

- Lok fasteners in accordance with Chapter 51

- 70 of Hercules Structural Repa ir Manual . Ensure proper fastener hole fit is attained in accordance with the hole inspection requirements of this manual. Proper installation of the Taper

- Lok is essential to attain maximum durability. Install all fasteners wet with sealant in accordan ce with Chapter 51

- 40 of Hercules Structural Repair Manual

.
B. Systems Securing:

For work directed by this Appendix only, restore finishes and sealants in accordance with Hercules Corrosion Prevention and Control Manual

, reinstall removed components, remov e equipment and supplies from the inspection area, and perform operational checkouts as required in accordance with applicable Hercules Maintenance Manual or Hercules Maintenance Instr uctions Manual

.

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- Center Wing Lower Surface Inspection Ar ea

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, 2007

Figure D 2

- Calibration Standard, Aluminum

- VM Products, Inc. PN VM30889

- C1A

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- Lift

- off and Notch Signals

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USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. Page D 12 Revision 1, March 8
, 2007 Figure D4

- Typical Probe Placement

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Figure D5

- Typical X

- Y Signal Response from 0.030” X 0.030” Notch

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, 2007

Figure D6

- Typical Time

- based Signal Response from 0.030” X 0.030” Notch

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NDI OF CENTER WING LOWER SURFACE STRINGER S , WS 214 LEFT TO WS 214 RIGHT

1. PURPOSE

This procedure has been developed to detect cracks in the center wing lower surface panel strin gers as shown in f igure E1. Fatigue cracks can originate in the center wing lower surface stringer feet at the indicated fastener attachment holes. Primary procedure applies eddy current surface scans around the attachment fastener holes of the center wi ng lower surface stringers. The backup procedure is a n A utomated Bolt H ole Eddy C urrent (ABHEC) sc an.

2. DESCRIPTION

Center wing lower surface stringers are fabri cated from 7075 aluminum alloy. Steel T aper
- L ok fasteners and aluminum rivets attach the string ers to the skin panels. Various types of steel fasteners attach miscellaneous systems hardware to the stringers. On Lockheed s eria l number 4334 and up , the stringer/strap assemblies were replaced with integrally reinforced stringers and the material temp er was changed from T6 to T73; refer to Service Bulletin 82

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- 61

.
3. D AMAGE

Fatigue c racks originate in the fastener holes common to the lower surface panel and systems hardware attachment fasteners in the stringer hats and propagate in a chordwise d irection. The T6 temper material stringers are prone to stress corrosion cracking.

4. PREPARATION OF AIRPLANE

Prepare the airplane in accordance with paragraph 2.A of Service Bulletin 82

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- 85. All systems attachment hardware is to be removed from t he stringer hats except for blind attachment fasteners. Fasteners attaching the stringer internal reinforcing straps installed on air craft prior to serial n umbe r 4334 do not require removal. To gain access into the lower surface panel No. 3 stringers bet ween WS 61 and WS 90, left and right, and inboard of the diagonal bulkhead, remove the BL 61 bulkhead rib access door at approximately FS 580.

5. PRIMAR Y PROCEDURE

Eddy current surface scan of the center wing lower surface panel stringer s. (See figure E1. )

A. NDI Equipment:

 Eddy C urrent instrument

- Zetec MIZ

- 21A or equivalent

 Probe, Shielded Pencil

- Zetec PN DT30PS 50

- 500 k Hz or equivalent

 Probe Cable

- Zetec PN DTPH

- 3 or equivalent

 Calibration S tandard, a luminum

- VM Products, Inc. PN VM30889

- C1A or equ ivalent (S ee f igure E2

. )

 Draft sman’s Template

B. Access:

Use appropriate maintenance stands to gain access to the inspection area.

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USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THI S DOCUMENT. Page E 2 Revision 1, March 8
, 2007 C. Preparation of Part:

Remove sealant with a plastic or ph e n o lic scraper as necessary for acceptable probe contact with the part using the procedures detailed in the Nondestructive Inspection (NDI) Procedur es Manual Supplement Section 20

- 00

- 00.

D. Equipment Calibration:

(1) Turn the instrument on.
(2) Connect the probe/cable to the instrument.

(3) Select a frequency of 100 kHz.

(4) Place the probe on a defect free area of the standard.
(5) Press the BAL button to null the instrument.
(6) Remove the probe from the standard and note the direction of movement of the signal.

(7) Adjust the PRB GAIN and PHASE to obtain a lift

- off sig nal as shown in f igure E3

.
NOTE : Adjust the V SCALE and/or H SCALE may cause the lift

- off signal to be slightly distorted. This is a normal condition.
(8) Scan the four 0.100

- long notches in the standard and adjust the V SCALE

, H SCALE and GAIN to obtain optimum separation of the defect signals as shown in figure E3.

E. Inspection #1:

NOTE : The eddy current instrument must be recalibrated when probes are changed.

Ensur e instrument is calibrated in accordance with paragraph D. Using the fastener collar as a guide, scan the center wing lower surface stringer foot around each indicated fastener hole as shown in f igure E4. In the area of the wing joint attach fitting, scan along the exposed area of the stringer adjacent to the stringer foot and crown splice a ngles/straps attaching the stringer to the rainbow fitting. Any signal similar to the signals generated when scanning the notches in the standard will indicate a probable fatigue crack in the part being inspected.

F. Inspection #2:

Ens ure instrument is ca librated in accordance with paragraph D. Scan the exposed stringer crown, and vertical/horizontal flanges at each removed plumbing bracket, clamp, etc

., that attach to the upper crown flange. Scan around the stringer crown fasteners attaching the interna l rein forcing strap to the stringer (serial number 4299 through 4334 only). Visually inspect the entire stringer for corrosion, stress corrosion cracks, or other damage. To confirm suspected damage, remove fasteners at suspected damage and conduct an ABH EC scan backup procedure in accordance with paragraph H

.

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Ensure instrument is c alibrated in accordance with paragraph D. In the area of rib attachments, scan the stringers at the nearest exposed edges for cracks propagating under the ri b feet.

H

. Backup Inspection (for confirmation only):

To confirm suspected damage, remove fasteners and perform backup ABHEC scan.

(1) NDI Equipment:

 Eddy Current I nstrument

- Zetec MIZ

- 21A or equivalent

 Mini probe drive

- GE Inspection Technologies PN 33A 100 or equivalent

 Cable, MIZ

- 21 to mini probe drive

- Zetec PN 2100

- 03

- 04 or equivalent

 Probe, rotating hole, reflection type, 200 kHz to 2 MHz, 3/16” diameter

- GE Inspection Technologies PN 620

- 546

- 187 or equivalent

 Calibration S tandard, aluminum

- VM Pr oducts, Inc. PN VM30889

- C1A or equivalent (S ee figure E2

. )

(2) Equipment Calibration:

(a) Turn the instrument on.

(b) Connect the cable to the instrument.

(c) Connect the mini probe drive to the cable.

(d) Insert the appropriate diameter probe into the min i probe drive.

(e) Use the following initial instrument settings:

 FREQ 500K

 PRB REFL HI

 PRB GAIN 85

 MODE X

- Y

 V SCALE 0.2

 H SCALE 0.4

 FILTER DIFF 01

 SCREEN AUTOCLEAR 0

(f) Press the BAL button to null the instrument.

(g) Using the rocker switch on the probe controller, turn the rotating probe gun to the on position at the slower of the two available speeds.

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(h) Insert the probe coil into the standard adjacent to the 0.030” X 0.030” notch at the top of the appropriate diameter fastener hole. Adjust the PRB G AIN and PHASE to obtain a signal as shown in figure E5

. (i) Change MODE to TRG SWP and press the BAL button to null the instrument.

NOTE : It may be necessary to rotate the position of the probe controller to obtain a similar signal

position as shown in fig ure E6

. (j) With the rotating probe coil still held adjacent to the 0.030” X 0.030” notch at the top of the appropriate diameter fastener hole, adjust PRB GAIN
, V SCALE

, H SCALE and PHASE to obtain a signal height of approximately 98% as shown in figure E6

. (3 ) Inspection:

NOTE : The eddy current instrument must be recalibrated when probes are changed.

Ensure instrument is calibrated as in accordance with paragraph (2). Remove fasteners and perform a backup inspection of suspect damage using an ABHEC scan.

I

. Mark and Report Damage :
Mark any damage in the stringer. Contact your local Lockheed Martin Aeronautics Company representative or the Technical Support Center in Marietta, Georgia, USA, with a damage report in accordance with paragraph 2.C of Service Bulletin 82

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Telephone: (770 ) 494

- 9131
Fax: ( 770) 494

- 9122
E

- Mail: hercules.support@lmco.com

Mail: Lockheed Martin Aeronautics Company 86 South Cobb Drive Department 3E1M, Zone 0591 Marietta, GA 30063

- 0591, USA

6

. DAMAGE REPAIR

Repair any damage found in accordance with paragraph 2.C.(2) of Service Bulletin 82

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7. SYSTEM SECURING

For work directed by this Appendix only, restore finishes and sealants in accordance wi th Hercules Corrosion Prevention and Control Manual

, reinstall removed components, remove equipment and supplies from the inspection area, and perform operational checkouts as required in accordance with applicable Hercules Maintenance Manual or Hercules M aintenance Instructions Manual

.

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- Center Wing Lower Surface Stringers

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Figure E 2

- Calibration Standard, Aluminum

- VM Products, Inc. PN VM30889

- C1A

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- Lift

- off and Notch Signals

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- Typical Probe Placement on Stringer Flange

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Figure E5

- Typical X

- Y Signal Response from 0.030” X 0.030” Notch

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Figure E6

- Typical Time

- based Signal Response from 0.030” X 0.030” Notch

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NDI OF CENTER WING LOWER SURFACE FRONT AND REAR BEAM CAPS, WS 21 0 LEFT TO W S 21 0 RIGHT

1. PURPOSE

This procedure has been developed to detect cracks in the center wing box, front and rear lower surface beam caps as shown in f igure F 1. Fatigue cracks can originate in the front and rear lower beam caps at the beam web and lower su rface panel attachment fasteners

, and at the auxiliary tank lacing “eye bolt” attachment holes. Primary Procedure No. 1 applies eddy current surface scans of the beam caps around the attachment fastener holes of the horizontal and vertical legs. Primary Procedure No. 2 applies Automated Bolt Hole Eddy C urrent (ABHEC) inspection of selected fasteners common to the front and rear corner fittings and selected fasteners at the auxiliary tank eyebolt attachments in the vertical leg of the beam caps. The backu p procedure is an ABHEC sc an.

2. DESCRIPTION

Center wing front and rear beam lower caps are fabri cated from 7075 aluminum alloy. Prior to Lockheed serial number 4358, and on certain MEP number replacement center wings, beam caps were heat treated to the T 6 temper; refer to Serv ice Bulletin 82

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3. DAMAGE

Fatigue c racks originate in the beam cap fastener holes attaching the beam webs and lower surface panels to the cap and propagate in a chordwise and/or vertical direction. Beam caps fabricate d from 7075

- T6 are prone to exfoliation corrosion and stress corrosion cracking.

4. PREPARATION OF AIRPLANE

A. Prepare the airplane i n accordance with paragraph 2.A of Service Bulletin 82

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B. Remove the auxiliary tank attachment eyebolt s (Fig ure F1 3 ) , which are locat ed at the following locations:

 f ront lower beam cap at WS 63, 98, 104 , 138 , 143 and 176

 r ear lower beam cap at WS 97 , 105 , 137, 142, and 176

C

. Remove each of the fasteners as indi cated in f igure s F 2 , F3 , F4 and F 5 that are common to the center wing lower surface beam caps and lower corner fittings.

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Eddy c urrent s urface scan of the center wing lower surface beam cap horizontal and vertical legs front and
rear

. (See figure F1

. )

A. NDI Equipment:

 Eddy Curre nt I nstrument

- Zetec MIZ

- 21A or equivalent

 Probe, Shielded Pencil

- Zetec PN DT30PS 50

- 500 k Hz or equivalent

 Probe Cable

- Zetec PN DTPH

- 3 or equivalent

 Calibration S tandard, a luminum

- VM Products, Inc. PN VM30889

- C1A or equivalent (See f igure F 6

. )

 Draft sman’s Template

B. Access:

Use appropriate maintenance stands to gain access to the inspection area.

C. Preparation of Part:

Remove sealant with a plastic or ph e n o lic scraper as necessary for acceptable probe contact with the part using the procedures detailed i n the Nondestructive Inspection (NDI) Procedur es Manual Supplement Section 20

- 00

- 00.

D. Equipment Calib ration :
(1) Turn the instrument on.

(2) Connect the probe/cable to the instrument.

(3) Select a frequency of 100 kHz.

(4) Place the probe on a defect free a rea of the standard.

(5) Press the BAL button to null the instrument.

(6) Remove the probe from the standard and note the direction of movement of the signal.

(7) Adjust the PRB GAIN and PHASE to obtain a lift

- off signal as shown in f igure F 7

.
NOTE : Adjust the V SCALE and/or H SCALE may cause the lift

- off signal to be slightly distorted. This

is a normal condition.

(8) Scan the four 0.100

- long notches in the standard and adjust the V SCALE

, H SCALE and GAIN to obtain optimum separation of the defect s ignal s as shown in f igure F 7

.

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NOTE : The eddy current instrument must be recalibrated when probes are changed.

Ensure instrument is calibrated as in accordance with paragraph D. Using the appropriate probe, scan the center wing lower surface bea m caps around each beam cap fastener hole WS 210 left to WS 210 right . Scan in both a clockwise and counterclockwise direction. See f igure s F 8 and F 9 for typical probe placement example. For any areas that have sheet metal supports as shown in f igure F 1 0 , scan the remaining area of the spar cap above the sheet metal supports. Any signal similar to the signals generated when scanning the notches in the standard will indicate a probable fatigue crack in the part being inspected.

To confirm suspected damag e, remove fasteners at suspected damage and conduct an ABHEC scan backup procedure in accordance with paragraph F.

F. Backup Inspection (for confirmation only):

To confirm suspected damage, remove fasteners and perform backup ABHEC scan.

(1) NDI Equipment:

 Eddy Current I nstrument

- Zetec MIZ

- 21A or equivalent

 Mini Probe D rive

- GE Inspection Technologies PN 33A100 or equivalent

 Cable, MIZ

- 21 to mini probe drive

- Zetec PN 2100

- 03

- 04 or equivalent

 Probe, rotating hole, reflection type, 200 kHz to 2 MHz, 3/16 ” diameter

- GE Inspection Technologies PN 620

- 546

- 187 or equivalent

 Calibration S tandard, aluminum

- VM Products, Inc. PN VM30889

- C1A or equivalent (See figure F 6

. )

(2) Equipment Calibration:

(a) Turn the instrument on.

(b) Connect the cable to the instru ment.
(c) Connect the mini probe drive to the cable.

(d) Insert the appropriate diameter probe into the mini probe drive.

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(e) Use the following initial instrument settings:

 FREQ 500K

 PRB REFL HI

 PRB GAIN 85

 MODE X

- Y

 V SCALE 0.2

 H SCALE 0.4

 FILTER DIFF 01

 SCREEN AUTOCLEAR 0

(f) Press the BAL button to null the instrument.

(g) Using the rocker switch on the probe controller, turn the rotating probe gun to the on position at the slower of the two available speeds.

(h) Insert the probe coil into the standard a djacent to the 0.030” X 0.030” notch at the top of the appropriate diameter fastener hole. Adjust the PRB GAIN and PHASE to obtain a signal as shown in figure F11

. (i) Change MODE to TRG SWP and press the BAL button to null the instrument.

NOTE : It may be necessary to rotate the position of the probe controller to obtain a similar signal

position as shown in figure F1 2

. (j) With the rotating probe coil still held adjacent to the 0.030” X 0.030” notch at the top of the appropriate diameter fastener hole, ad just PRB GAIN
, V SCALE

, H SCALE and PHASE to obtain a signal height of approximately 98% as shown in figure F1 2

. (3 ) Inspection:

NOTE : The eddy current instrument must be recalibrated when probes are changed.

Ensure instrument is calibrated as in accordanc e with paragraph (2). Remove fasteners and perform a backup inspection of suspect damage using an ABHEC scan.

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Revision 1, March 8
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Mark any damage to the beam caps . Contact your local Lockheed Martin Aeronautics Company representative or the Techn ical Support Center in Marietta, Georgia, USA, with a damage report in accordance with paragraph 2.C of Service Bulletin 82

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Telephone: (770 ) 494

- 9131
Fax: ( 770) 494

- 9122
E

- Mail: hercules.support@lmco.com

Mail: Lockheed Martin Aeronautics Company 86 South Cobb Drive Department 3E1M, Zone 0591 Marietta, GA 30063

- 0591, USA

6. PRIMARY PROCEDURE N O . 2

ABHEC scan of the center wing lower surface beam cap fastener holes common to the front and rear corner fittings and auxiliary tank eyebolt attachments. (See figures F1, F2, F3, F4, F5, and F 1 3 .)

A. NDI Equipment:

 Eddy Current I nstrumen t

- Zetec MIZ

- 21A or equivalent

 Mini Probe D rive

- GE Inspection Techno logies PN 33A100 or equivalent

 Cable, MIZ

- 21 to mini probe drive

- Zetec PN 2100

- 03

- 04 or equivalen t

 Probe, rotating hole, reflection type, 200 kHz to 2 MHz, 5/32” diameter

- GE Inspection Technologies PN 620

- 546

- 156 or equivalent

 Calibration S tandard, a luminum

- VM Products, Inc. PN V M30889

- C1 A or equivalent ( S ee f igure F 6

. )

B. Access:

Use appropriate maintenance stands to gain access to the inspection area.

C. Preparation of Part:

Remove the indicated fasteners in accordance with the Structural Repair Manual. Remove sealant from the fastener hole(s) with a nylon bristled brush of the appropriate diameter as necessary for acceptab le probe contact with the part.

D. Equ ipment Calibration:

(1) Turn the instrument on.

(2) Conne ct the cable to the instrument.

(3) Connect the mini probe driv e to the cable.

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USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOC UMENT. Page F 6 Revision 1, March 8
, 2007 (4) Insert the appropriate diameter probe into the mini probe drive.

(5) Use the following initial instrument settings:

 FREQ 500K

 PRB REFL HI

 PRB GAIN 85

 MODE X

- Y

 V SCALE 0.2

 H SCALE 0.4

 FILTER DIFF 01

 SCREEN SET AUTOCLEAR 0

(6) Press the B AL button to null the instrument.

(7) Using the rocker switch on the probe controller, turn the rotating probe gun to the on position at the slow er of the two available speeds.

(8) Insert the probe coil into the standard adjacent to the 0.030” X 0.030” not ch at the top of the appropriate diameter fastener hole. Adjust the PRB GAIN and PHASE to obtain a signal as shown in f igure F 1 1

. (9) Change MODE to TRG SWP and press the BAL button to null the instrument.

NOTE : It may be necessary to rotate the position of the probe controller to obtain a similar signal

position as shown in f igure F 1 2

. (10) With the rotating probe coil still held adjacent to the 0.030” X 0.030” notch at the top of the appropriate diameter fastener hole, adjust PRB GAIN
, V SCALE

, H SCALE a nd PHASE to obtain a signal height of approximately 98% as shown in f igure F1 2

.
E. Inspection #1:

NOTE : The eddy current instrument must be recalibrated when probes are changed.

NOTE : The left and right aft corner fittings (see figure s F2, F3, F 4 and F5 ) a re fabricated from steel and will not be inspected with this procedure. S par caps, wing panels and spar webs are fabricated from aluminum and will be inspected

.
NOTE: Fastener holes common to the steel corner fitting shall be inspected as would normally be done in a part stack

- up

. Care must be taken to observe the steel/aluminum interface location using both the instrument screen presentation as well as utilizing the visible depth of the steel fitting.

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NOTE: Removal of the corner fitting may be required if interface indications cannot be resolved through addition al cleaning and verification.

Ensure instrument is calibrated as in accordance with paragraph D. Scan each of the fastener holes as indicated in f igure s F 2 , F3 , F4 and F 5 ) that are common to the center wing lower surface beam caps and lower corner fittin gs , through each layer of material

.
F. Inspection #2:
Ensure instrument is calibrated as in accordance with paragraph D. Scan each indicated fastener hole, common to the auxiliary tank eyebolt attachment, through each layer of material as shown in f igure F1 3

. Perform a close visual inspection with a 10X magnification glass of the hole for corrosion. The eyebolts are located at the following locations:

 Front lower beam cap at WS 63, 98, 104 , 138 , 143 and 176

 Rear lower beam cap at WS 97 , 105 , 137, 142, a nd 176

To confirm suspected defects, conduct a redundant ABHEC backup procedure in accordance with paragraph G

.
G. Redundant Inspection (for confirmation only):

(1) Inspector Verification

Reset and recalibrate the same equipment. The same inspector repeats the i nspection. If crack is confirmed, complete the verification outlined below.

(2) Verification

Preferred Method

– Different inspector repeats the inspection using the same equipment, after resetting and recalibrating the equipment.

Altern ate Method No. 1

– Insp ector re inspects the area with an appropriate alternate method.

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, 2007 H. Mark and Report Damage :
Mark any damage in the beam caps. Contact your local Lockheed Martin Aeronautics Company representative or the Technical Support Center in Marietta, Georgia, USA, with a damage report in accordance with paragraph 2.C of Service Bulletin 82

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Telephone: (770 ) 494

- 9131
Fax: ( 770) 494

- 9122
E

- Mail: hercules.support@lmco.com

Mail: Lockheed Mart in Aeronautics Company 86 South Cobb Drive Department 3E1M, Zone 0591 Marietta, GA 30063

- 0591, USA

7

. DAMAGE REPAIR

Repair any damage found in accordance with paragraph 2.C.(2) of Service Bulletin 82

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8. SYSTEM SECURING

A. Fastener Installati on :

NOTE : Either original type fasteners may be installed at all removed locations for inspection, or installation of H i

- T igue fasteners in cold worked holes may be performed where adequate edge distance and spacing exists. Operators and Service Centers a re responsible for determining if they possess adequate training and the necessary tooling and procedures to perform this fatigue improvement

. (S ee paragraph 2.D of Ser vice Bulletin 82

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(1 ) Reinstall the next oversize T aper
- L ok fasteners in accordance with C hapter 51

- 70 of Hercules Structural Repair Manual . Ensure proper fastener hole fit is attained in accordance with the hole inspection requirements of this manual. Proper installation of the T aper
- L ok is essential to attain maximum durab ility. Install all fasteners wet with sealant in accordance with C hapter 51

- 40 of Hercules Structural Repair Manual

. (2 ) For the AN43 eyebolts, reinstall existing diameter fasteners unless oversizing is required to remove corrosion damage and/or small fat igue crack indications. R eam the hole to remove the corrosion and/or fatigue damage and install an appropriate sized acres sleeve in accordance with applicable maintenance instructions. Contact Lockheed Martin if the final hol e diameter exceeds 0.284 inc hes (for a second oversize 1⁄4 inch acres sleeve).

B. System Securing :
For work directed by this Appendix only, restore finishes and sealants in accordance with Hercules Corrosion Prevention and Control Manual , reinstall removed components, remove equipment and supplies from the inspection area, and perform operational checkouts as required in accordance with applicable Hercules Maintenance Manual or Hercules Maintenance Instructions Manual

.

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Figure F 1

- Center Wing Box, Front and Rear Lower Surface Beam Caps

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Figure F 2

- Center Wing Corner Fittings, Lower Forward Fitting Shown (Long)

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Figure F 3

- Center Wing Corner Fittings, Lower Forward Fitting Shown (Short)

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, 2007 Fasteners to be removed and holes inspected (ABHEC)

Figure F 4

- Center Wing Corner Fittings, View Inside Dry Bay

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Figure F 5

– Center Wing Corner Fittings, External View o f Rear Beam

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Figure F 6

- Calibration Standard, Aluminum

- VM Products, Inc. PN VM30889

- C1A

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– Lift

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Figure F 8

- Spar Cap Horizontal Leg Typical Probe Placement Primary Pro cedure No. 1

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Figure F 9

- Spar Cap Vertical Leg Typical Probe Placement Primary Procedure No. 1

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- Rear Spar Cap at Sheet Metal Supports

. Front Spar Ca p Similar, Primary Procedure No. 1 Perform eddy current surface scan above the fasteners in these areas (typical for front and rear beams).

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Figure F 1 1

- Typical X

- Y Signal Response from 0.030” X 0.030” Notch

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Figure F 1 2

- Typical Time

- based Signal Response from 0.030” X 0.030” Notch

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Figure F1 3

- Aux iliary Tank Eyebolt Front Spar Cap

, Typical
, Rear Spar Cap Similar Perform removals and ABHEC at the aux tank AN43 eyebolt attachment fastener holes.

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Revision 1, March 8
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1. PURPOSE

This procedure has been developed to detect cracks in the center wing lower surface panel at r epair doublers and/or straps as shown in f igure G1. Fatigue cracks originate in the center wing lower surface wing panel at the indicated fastener attachment holes. Primary Procedure No. 1 performs an internal and external visual inspection of the wing l ower surface to determine if any repairs exist. Primary Procedure No. 2 applies Automated Bolt H ole Eddy C urrent (ABHEC) scan through each layer of selected attachment fastener holes common to the center wing lower surface panels and repair doublers and/o r straps. Primary Procedure No. 3 applies eddy current surface scans around the forward and aft edges of each repair doubler and/or strap on the center wing lower surface panel. The backup procedure is an ABHEC scan.

2. DESCRIPTION

Center wing lower surf ace panels are fabri cated from 7075 aluminum alloy. External or internal doubler/strap repairs may have been installed in service for repair of corrosion and/or fatigue cracking. External doubler repairs are common at the wing joint area and in the area of WS 61, FS 597. Repair members are typically 7075 aluminum alloy or stainless steel sheet. These repairs introduce potential sites for fatigue cracking. External doublers installed at production may exist at the panel splice locations at WS 62 to 68 w hich are recommended for permanent removal by Serv ice Bulletin 82

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- 55. This inspection is not applicable to composite material repair doublers installed on the wing lower surface. Contact Lockheed Martin if Primary Procedure No. 1 identifies an y composite material repair members.

3. D AMAGE

Fatigue c racks can originate in the lower surface panel fastener holes common to the repair members and propagate in a chordwise direction.

4. PREPARATION OF AIRPLANE

Prepare the airplane in accordance with pa ragraph 2.A of Service Bulletin 82

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5. PRIMARY PROCEDURE NO. 1

Perform a visual inspection of the center wing lower surface from WS 220 left to WS 220 right, FS 517 to FS 597 to identify any internal or external repair doublers and straps. P roduction installed straps exist at the panel spanwise splice locations and these areas do not require inspection. If no repair doublers exist, proceed to paragraph 8.

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A BHEC scan of the center wing lower surface panel at the ou ter two inboard and outboard rows of fasteners attaching the repair doublers and/or straps to the wing lower surface panels. (See figure G1.)

A. NDI Equipment:

 Eddy Current I nstrument

- Zetec MIZ

- 21A or equivalent

 Mini Probe D rive

- GE Inspection Techno logie s PN 33A100 or equivalent

 Cable, MIZ

- 21 to mini probe drive

- Zet ec PN 2100

- 03

- 04 or equivalent

 Probe, rotating hole, reflection type, 200 kHz to 2 MHz, 5/32” diameter

- GE Inspection Technologie s PN 620

- 546

- 156 or equivalent

 Calibration s tandard, a luminum

- VM Products, Inc. PN VM30889

- C 1A or equivalent ( S ee f igure G 2

. )

B. Access:
Use appropriate maintenance stands to gain access to the inspection area.

C. Preparation of Part:

Remove the indicated fasteners in accordance with the Structural Repair Manual. Re move sealant from the fastener hole(s) with a nylon bristled brush of the appropriate diameter as necessary for acceptable probe contact with the part.

D. Equipment Calib ration:
(1) Turn the instrument on.
(2) Connect the cable to the instrument.
(3) Conne ct the mini probe drive to the cable.
(4) Insert the appropriate diameter probe into the mini probe drive.
(5) Use the following initial instrument settings:

 FREQ 500K

 PRB REFL HI

 PRB GAIN 85

 MODE X

- Y

 V SCALE 0.2

 H SCALE 0.4

 FILTER DIFF 01

 SCREEN SET AUTOC LEAR 0

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(7) Using the rocker switch on the probe controller, turn the rotating probe gun to the on position at the slower of the two available speeds.

(8) Insert the probe coil into the standard adjacent to the 0.030” X 0.030” notch at the top of the appropriate diameter fastener hole. Adjust the PRB GAIN and PHASE to obtain a signal as shown in f igure G3

. (9) Change MODE to TRG SWP and press the BAL button to null the instrument.

NOTE : It may be necessary t o rotate the position of the probe controller to obtain a similar signal position

as shown in f igure G4

. (10) With the rotating probe coil still held adjacent to the 0.030” X 0.030” notch at the top of the appropriate diameter fastener hole, adjust PRB GAI N
, V SCALE

, H SCALE and PHASE to obtain a signal height of approximately 98% as shown in f igure G4.

E. Inspection :

NOTE : The eddy current instrument must be recalibrated when probes are changed.

Ensure instrument is calibrated as in accordance with paragra ph D. P erform ABHEC scan of the outer two inboard and outboard rows of fasteners attaching each repair doublers layer and/or straps t o the wing lower surface panels

. (See figure G1

. )

To confirm suspected damage , conduct a redundant ABHEC backup procedure in accordance with paragraph F

.
F. Redundant Inspection (for confirmation only):

(1) Inspector Verification

Reset and recalibrate the same equipment. The same inspector repeats the inspection. If crack is confirmed, complete the verification outlined below.

(2) Ve rification

Preferred Method

– Different inspector repeats the inspection using the same equipment, after resetting and recalibrating the equipment.

Altern ate Method No. 1

– Inspector re inspects the area with an appropriate alternate method.

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. Mark and Re port D amage :
Mark any damage to the lower panels . Contact your local Lockheed Martin Aeronautics Company representative or the Technical Support Center in Marietta, Georgia, USA, with a damage report in accordance with paragraph 2.C of Ser vice Bulletin 82

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Telephone: (770 ) 494

- 9131
Fax: ( 770) 494

- 9122
E

- Mail: hercules.support@lmco.com

Mail: Lockheed Martin Aeronautics Company 86 South Cobb Drive Department 3E1M, Zone 0591 Mariet ta, GA 30063

- 0591, USA

7. Primary Procedure No. 3

Eddy current surface scan of the center wing lower surface panel at the forward and aft edges of repair doublers and/or straps

. (See figure G1.)

A. NDI Equipment:

 Eddy Current I nstrument

- Zetec MIZ

- 21A or equivalent

 Probe, Shielded Pencil

- Zetec PN DT30PS 50

- 500 k Hz or equivalent

 Probe Cable

- Zetec PN DTPH

- 3 or equivalent

 Calibration S tandard, a luminum

- VM Products, Inc. PN VM30889

- C1A or equivalent (S ee f igure G2

. )

 Draft sman’s Template

B. Access:

Use a ppropriate maintenance stands to gain access to the inspection area.

C. Preparation of Part:

Remove sealant with a pl astic or ph e n o lic scraper as necessary for acceptable probe contact with the part using the procedures detailed in the Nondestructive Inspe ction (NDI) Procedur es Manual Supplement Section 20

- 00

- 00.

D. Equipme nt Calibration :
(1) Turn the instrument on.

(2) Connect the probe/cable to the instrument.

(3) Select a frequency of 100 kHz.

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(5 ) Press the BAL button to null the instrument.

(6) Remove the probe from the standard and note the direction of movement of the signal.

(7) Adjust the PRB GAIN and PHASE to obtain a lift

- off signal as shown in f igure G5

.
NOTE : Adjusting the V SCALE and/or H SCALE may cause the lift

- off signal to be slightly distorted.

This is a normal condition.

(8) Scan the four 0.100

- long notches in the standard and adjust the V SCALE

, H SCALE and GAIN to obtain optimum separation of the defect signals as shown in f igure G5

.
E. Inspection:

NOTE : The eddy current instrument must be recalibrated when probes are changed.

Ensure instrument is calibrated as in accordance with paragraph D. Using the forward and aft edges of the repair doubler(s) as a guide, scan the center win g lower surface panel along the edge of each repair. Any signal similar to the signals generated when scanning the notches in the standard will indicate a probable fatigue crack in the part being inspected. To confirm suspected d amage , remove fasteners a t suspected damage and conduct an ABHEC scan backup procedure in accordance with paragraph F

.
F

. Backup Inspection (for confirmation only):

To confirm suspected damage, remove fasteners and perform backup ABHEC scan

. (1) NDI Equipment:

 Eddy Current I nstrum ent

- Zetec MIZ

- 21A or equivalent

 Mini Probe D rive

- GE Inspection Technologies PN 33A100 or equivalent

 Cable, MIZ

- 21 to mini probe drive

- Zetec PN 2100

- 03

- 04 or equivalent

 Probe, rotating hole, reflection type, 200 kHz to 2 MHz, 3/16” diameter

- GE Inspe ction Technologies PN 620

- 546

- 187 or equivalent

 Calibration S tandard, aluminum

- VM Products, Inc. PN VM30889

- C1A or equivalent (S ee figure G2

. )

(2) Equipment Calibration:

(a) Turn the instrument on.

(b) Connect the cable to the instrument.

(c) Connect the mini probe drive to the cable.

(d) Insert the appropriate diameter probe into the mini probe drive.

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(e) Use the following initial instrument settings:

 FREQ 500K

 PRB REFL HI

 PRB GAIN 85

 MODE X

- Y

 V SCALE 0.2

 H SCALE 0.4

 FILTER DIFF 01

 SCREEN AUTOCLEAR 0

(f) Press the BAL button to null the instrument.

(g) Using the rocker switch on the probe controller, turn the rotating probe gun to the on position at the slower of the two available speeds.

(h) Insert the probe coil into the standard adjacent to the 0.030” X 0.030” notch at the top of the appropriate diameter fastener hole. Adjust the PRB GAIN and PHASE to obtain a signal as shown in figure G3

. (i) Change MODE to TRG SWP and press the BAL button to null the instrument.

NOTE : It may be necessary to rotate th e position of the probe controller to obtain a similar signal

position as shown in figure G4

. (j) With the rotating probe coil still held adjacent to the 0.030” X 0.030” notch at the top of the appropriate diameter fastener hole, adjust PRB GAIN
, V SCALE

, H SCALE and PHASE to obtain a signal height of approximately 98% as shown in figure G4

. (3 ) Inspection:

NOTE : The eddy current instrument must be recalibrated when probes are changed.

Ensure instrument is calibrated as in accordance with paragraph (2). R emove fasteners and p erform
a backup inspection of suspect damage using an ABHEC scan.

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. Mark and Report D amage :
Mark any d amage in the lower surface panel . Contact your local Lockheed Martin Aeronautics Company representative or the Technical Support C enter in Marietta, Georgia, USA, with a damage report in accordance with paragraph 2.C of Ser vice Bulletin 82

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Telephone: (770 ) 494

- 9131
Fax: ( 770) 494

- 9122
E

- Mail: hercules.suppo rt@lmco.com

Mail: Lockheed Martin Aeronautics Company 86 South Cobb Drive Department 3E1M, Zone 0591 Marietta, GA 30063

- 0591, USA

8

. DAMAGE REPAIR

Repair any damage found in accordance with paragraph 2.C.(2) of Service Bulletin 82

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9. SYSTE M SECURING

A. Fastener Installation :

NOTE : Either original type fasteners may be installed at all removed locations for inspection, or installation of H i

- T igue fasteners in cold worked holes may be performed where adequate edge distance and spacing exists. Operators and Service Centers are responsible for determining if they possess adequate training and the necessary tooling and procedures to perform this fatigue improvement

. (S ee paragraph 2.D of Service Bulletin 82

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- 85.) For repairs that are not Lockheed Martin Aeronautics Company approved, contact the applicable repair design/approval authority to obtain authorization to oversize, cold work and install Hi

- Tigue fasteners in these locations.

Reinstall the next oversize T aper
- L ok fasteners in accordance with C hapter 51

- 70 of Hercules Structural Repair Manual . Ensure proper fastener hole fit is attained in accordance with the hole inspection requirements of this manual. Proper installation of the T aper
- L ok is essential to attain maximum durabi lity. Install all fasteners wet with sealant in accordance with C hapter 51

- 40 of Hercules Structural Repair Manual

.
B. Systems Securing :
For work directed by this Appendix only, restore finishes and sealants in accordance with Hercules Corrosion Preventio n and Control Manual , reinstall removed components, remove equipment and supplies from the inspection area, and perform operational checkouts as required in accordance with applicable Hercules Maintenance Manual or Hercules Maintenance Instructions Manual

.

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Figure G 1

- Typical Center Wing Lower Surface Repair LOWER SURFACE STRINGER (TYP)

LOWER SURFACE PANEL (TYP)

LOWER SURFACE

REPAIR DOUBLERS (TYP)

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Figure G 2

- Calibration Standard, Aluminum

- VM Produc ts, Inc. PN VM30889

- C1A

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Figure G3

- Typical X

- Y Signal Response from 0.030” X 0.030” Notch

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Figure G4

- Typical Time

- based Signal Response from 0.030” X 0.030” Notch

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– Lift

- off and Notch Signals