HERCULES Lockheed Martin Aeronautics 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 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.

© 2013 LOCKHEED MARTIN CORPORATION. LOCKHEED MARTIN PROPRIETARY INFORMATION.

382-57-85

Revision 3, July 8, 2013 82-790

* REVISION NOTICE *

WING - CENTER WING LOWER SURFACE GENERALIZED CRACKING AND WIDESPREAD FATIGUE 

DAMAGE INSPECTION REQUIREMENTS

Attached is Revision 3, dated July 8, 2013, to Service Bulletin 82-790/382-57-85. Information added or changed 

in this issue is indicated 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 Paragraph 2.A.(1) through (3) of Service Bulletin 82-788 should 

adhere to the schedule 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 this 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 must 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 include 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.

This revision affects Pages 1 through 18 and Appendix A Pages A1 through A14 of this Service Bulletin, Revision 

2, dated August 23, 2007. Retain Appendices B through G. Please remove existing Pages 1 through 18 and 

Appendix Pages A1 through A14 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 Service 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

Revision 2 August 23, 2007

___________#__________

File: CR C130-03912 / I-3884R3

HERCULES Lockheed Martin Aeronautics 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 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.

© 2013 LOCKHEED MARTIN CORPORATION. LOCKHEED MARTIN PROPRIETARY INFORMATION.

382-57-85

August 4, 2005 82-790

Revision 3, July 8, 2013 Page 1 of 18

WING - CENTER WING LOWER SURFACE GENERALIZED CRACKING AND WIDESPREAD FATIGUE 

DAMAGE INSPECTION REQUIREMENTS

NOTE: This Service Bulletin contains Appendices A through G.

1. PLANNING INFORMATION

A. EFFECTIVITY

(1) 382-57-85, FAA Certificated Aircraft: This Service Bulletin is applicable to all model 382, 382B, 

382E, 382F, and 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 (excluding C-130J Hercules aircraft).

B. REASON

(1) Service Bulletins 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-130 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) Recommendations for military operators are 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 Paragraph 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 Usage Evaluation (OUE) or Damage Tolerance 

Assessment (DTA) or with the Initial Usage Assessment procedures identified in 

Paragraph 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.
HERCULES Lockheed Martin Aeronautics Company

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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 

Paragraph 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 of this Service Bulletin and prior to reaching 45,000 EBH. These 

aircraft are subject to the flight restrictions as defined in Paragraph 2.B.(4) of Service 

Bulletin 82-788 until this inspection is accomplished.

3 For military aircraft that have accumulated 45,000 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 in Paragraph 

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 aircraft 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, 

published 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 Aeronautics 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 

recommended compliance period of this Service Bulletin can be addressed by completion 

of a Lockheed Martin Operational Usage Evaluation (OUE) in accordance with Paragraph 

2.B.(2) of Service Bulletin 382-57-84.
HERCULES Lockheed Martin Aeronautics Company

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Revision 3, July 8, 2013 Page 3

C. DESCRIPTION

(1) The inspection procedures identified in this Service Bulletin consist of surface eddy current, bolt 

hole eddy current and visual Nondestructive Inspection (NDI) methods to detect generalized 

fatigue cracking and the possible onset of widespread fatigue damage of the center wing lower 

surface structure. These inspection procedures are intended to supplement the existing Hercules 

Airfreighter Series Inspection Program, SMP 515-C, requirements and previously issued Service 

Bulletins. There are no previous inspection procedures that meet the full intent of this Service 

Bulletin.

(2) The inspection procedures used in this Service Bulletin have been selected with crack detection 

targets as shown in Table 1.

Table 1

Crack Detection Targets

Technique 50% 90%

Automated Bolt Hole Eddy Current 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 Probability Of Detection (POD) analysis is not

implied.

(3) Lockheed Martin Aeronautics Company recommends the use of independent repeat inspection 

for all Primary Automated Bolt Hole Eddy Current (ABHEC) NDI Procedures found in the 

Appendices. The additional manpower requirements for independent repeat inspection is small in 

relation to preparation time, yet has the potential for reducing inspection misses in the critical 

structure inspected by this Service Bulletin. Use of check lists or other appropriate means are 

encouraged to minimize the possibility of missing one or more fastener holes in the inspection 

procedure.

(4) Techniques and procedures utilized in this Service Bulletin were chosen to ensure 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 inspection 

procedures called in Appendices 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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Page 4 Revision 3, 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 Attach Angle, WS 58 

to WS 61, FS 517 to FS 597, Left and Right (Appendix A)

 NDI of Center Wing Lower Surface Panels 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 216

Left to WS 216 Right (Appendix D)

 NDI of Center Wing Lower Surface 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 surface panels at the rainbow fitting in accordance 

with Appendix A of Service Bulletin 82-783/382-57-83

 Perform NDI of the center wing lower forward corner fitting in accordance with Service 

Bulletin 82-766/382-57-79

D. APPROVAL

(1) The aircraft owner/operator shall 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 notify Lockheed Martin Aeronautics 

Company of compliance with this Service Bulletin at website address:

www.lockheedmartin.com/eoc and log into Data Library.

(3) 382-57-85, FAA Certificated Aircraft: FAA approval of the Inspection Program 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 Directive 2011-09-04, and the FAA may issue a revised directive based on the 

Revision 3 changes.
HERCULES Lockheed Martin Aeronautics Company

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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 Bulletins 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 prescribed 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 identified 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 owner/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-130 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 Instrument - Zetec MIZ-21A or equivalent

 Mini Probe Drive - GE Inspection Technologies PN 33A100 or equivalent

 Probe, shielded pencil - Zetec PN DT30PS 50-500 kHZ or equivalent

 Cable, MIZ-21 to mini probe drive - Zetec PN 2100-03-04 or equivalent

 Probe Cable - Zetec PN DTPH-3 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 - 200 kHz to 2 MHz, 5/32” diameter, GE Inspection 

Technologies PN 620-546-156 or equivalent

 Probe, rotating hole, reflection type - 200 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

 Draftsman’s Template
HERCULES Lockheed Martin Aeronautics Company

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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) Procedures Manual Supplement

(1) 382-57-85, FAA Certificated Aircraft:

Hercules Maintenance Manual

Hercules Service Bulletin 382-53-61

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

Hercules Airfreighter Series Inspection Program, SMP 515-C

(2) 82-790, Foreign Military Aircraft:

Hercules Maintenance Instructions Manual

Hercules Service Bulletin 82-481

Hercules Service Bulletin 82-557

Hercules Service Bulletin 82-752

Hercules Service Bulletin 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
HERCULES Lockheed Martin Aeronautics Company

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Revision 3, July 8, 2013 Page 7

J. OTHER PUBLICATIONS AFFECTED

(1) 382-57-85, FAA Certificated Aircraft:

Hercules Airfreighter Series Inspection Program, SMP 515-C

(2) 82-790, Foreign Military Aircraft:

Hercules Airfreighter Series Inspection Program, SMP 515-C
HERCULES Lockheed Martin Aeronautics Company

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Page 8 Revision 3, July 8, 2013 (Reissue)

THIS PAGE INTENTIONALLY LEFT BLANK.
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2. ACCOMPLISHMENT INSTRUCTIONS

WARNING: ENSURE THAT APPLICABLE SAFETY PRECAUTIONS PERTAINING TO WORK IN 

FUEL/FUME AREAS, SPECIFIED IN THE HERCULES MAINTENANCE MANUAL OR 

HERCULES MAINTENANCE INSTRUCTIONS MANUAL, ARE STRICTLY OBSERVED 

WHILE WORKING IN THE CENTER WING DRY BAY AREA. PERSONNEL SHALL WEAR 

NONSPARKING PROTECTIVE CLOTHING. ENTRY INTO THE DRY BAY FOR 

DEPUDDLING MUST NOT BE MADE UNTIL THE AREA HAS BEEN PURGED TO FIRESAFE 20 PERCENT LOWER EXPLOSIVE LIMIT (LEL), AS DETERMINED USING FUEL 

VAPOR DETECTION AND MEASURING EQUIPMENT. FULL-FACE RESPIRATOR MUST

BE WORN UNTIL AREA HAS BEEN PURGED TO THE HEALTH-SAFE 0.0- TO 

1.5-PERCENT LEL AND 19.5 PERCENT OXYGEN CONTENT. FAILURE TO COMPLY 

MAY RESULT IN SERIOUS INJURY, OR DEATH.

WARNING: ENSURE THAT APPLICABLE SAFETY PRECAUTIONS PERTAINING TO ELECTRICAL 

AND FUEL SYSTEM MAINTENANCE ARE STRICTLY OBSERVED WHILE 

ACCOMPLISHING THE WORK DESCRIBED HEREIN. ENSURE THAT POWER IS

ISOLATED FROM THE AIRCRAFT PRIOR TO STARTING WORK.

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

OR PROLONGED CONTACT. SKIN AND EYE PROTECTION IS REQUIRED. GOOD 

VENTILATION IS REQUIRED. FAILURE TO COMPLY COULD RESULT IN SERIOUS 

INJURY TO PERSONNEL.

WARNING: USE SEALANTS IN A WELL-VENTILATED AREA. AVOID REPEATED CONTACT WITH 

SKIN. WASH HANDS AFTER HANDLING SEALANT AND BEFORE 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, INCLUDING WORK STANDS, SHALL BE ELECTRICALLY 

GROUNDED TO THE AIRPLANE AND TO AN APPROVED GROUNDING POST. 

GROUND WIRES SHALL BE SECURELY ATTACHED TO CONNECTING POINTS TO 

MINIMIZE ACCIDENTAL DISCONNECTION. WORK STANDS SHALL BE EQUIPPED 

WITH COPPER, ZINC, OR ZINC-COATED GROUNDING PLATES THAT CAN BE 

CONVENIENTLY CONTACTED BY PERSONNEL ENTERING 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 dry 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 fuselage nose jacks.
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(5) Install and firmly snug main landing gear stands in position in accordance with Figure 57-10-02 of 

Hercules Structural Repair Manual. Release the WS 220 jacks so that the entire weight is 

supported by the main landing gear stands and fuselage nose jacks. Install horizontal stabilizer 

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 the 

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 inches. Install fuselage support cradles in accordance with Figure 51-110-01 of Hercules 

Structural Repair Manual. Raise the WS 220 jacks snug against the jack pads.

(6) Remove all four QECs 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 

Hercules Structural Repair Manual. The center wing is to be placed in the “no-load” condition for

the installation of repairs in accordance with Chapter 57-10 of Hercules Structural Repair Manual. 

Position outer wing support beams at OWS 369 in accordance with Figure 57-10-02 of Hercules 

Structural Repair Manual and record the elevation of each wing at OWS 369 above a fixed datum 

on the wing support jacks. Raise each OWS 369 wing support beam 3.4 (±0.1) inches above the 

elevation recorded. The WS 220 jacks may be lowered. Ensure all jacks are mechanically 

locked prior to proceeding.

CAUTION: MAINTENANCE AND INSTALLATION PERSONNEL MUST EXERCISE CAUTION

WHILE INCORPORATING THIS SERVICE BULLETIN TO ENSURE THAT WIRING 

SYSTEMS ARE PROTECTED AND KEPT CLEAN AT ALL TIMES. NOTE THAT 

METAL SHAVINGS CAUSED BY DRILLING AND OTHER FORMS OF DEBRIS THAT 

CONTACT WIRE BUNDLES MIGHT IMPAIR WIRE SYSTEM INTEGRITY AND 

SHORTEN SYSTEM AND COMPONENT SERVICE 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 RUBBER 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 gain access to lower 

surface.

(11) Remove center wing fuel lines as necessary for access to inspection areas. Figure 1 illustrates 

installed fuel lines.

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

except items attached with blind fasteners.

(13) Remove the nacelle fairings, lower aft nacelle, and engine heat shield from Nacelles 2 and 3.
HERCULES Lockheed Martin Aeronautics Company

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NOTE: The Nacelle Attach Fitting is installed with blind Taper-Lok fasteners under the center of 

each stringer (hat). Exercise caution when removing these fasteners to avoid damaging the 

lower surface panel, stringers and nacelle attach fitting.

(14) Remove Engine 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 Chapter 51-70 

of the Hercules Structural Repair Manual for removal of the Taper-Lok fasteners.

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

chapter 51-70 of the Hercules Structural Repair Manual for removal of the Taper-Lok 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 have 

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 removal of the Taper-Lok and HiLok 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 panels, 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 accordance 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 Bulletin 82-783/382-57-83.

(9) Perform NDI of the center wing lower forward corner fitting in accordance with Service Bulletin 

82-766/382-57-79.
HERCULES Lockheed Martin Aeronautics Company

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C. REPAIRS

(1) Report any damage detected by the Paragraph 2.B inspection procedures to Lockheed Martin 

Aeronautics Company. Provide the following information of all damage detected:

(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) calculated in accordance with Service 

Bulletin 82-788.

(d) Part number and description

(e) Location (Wing 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 and TL200 Taper-Lok fasteners with 

Hi-Tigue 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 between fasteners (not less than 2.5 times the 

final fastener nominal diameter). The May 2005 Revision of Hercules Structural 

Repair Manual contains Lockheed Martin Aeronautics Company approved procedures 

for cold working in chapter 51-70.

Replacement of Protruding-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, HLT124, HLT128, HLT420PB, HLT620PB, 

HLT714PB, HLT422PB, HLT622PB, or HLT716PB.

Replacement 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-fit fastener (Hi-Tigue) of 108 ksi or greater shear 

strength, such as an HLT115, HLT123, HLT127, HLT421PB, 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, HLT422PB, HLT622PB, or 

HLT716PB.

(a) Install the wing attach angle doublers (or straps) that were removed in Paragraph 2.A.(16).

(b) Install misc/blankets covering the wing attach angle at BL 61, left and right removed in 

Paragraph 2.A.(17).

(c) Install drain troughs at WS 56, 72, 174 and 208, left and right removed in Paragraph 

2.A.(15).

(d) Install Engine 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 Paragraph 2.A.(14).

(e) Install the nacelle fairing, lower aft nacelle, and engine heat shield on Nacelle 2 and 3 that 

were removed in Paragraph 2.A.(13).

(f) Install all plumbing brackets common to the upper crown of all lower surface stringers 

(hats) that were removed in Paragraph 2.A.(12).
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(g) Install center wing fuel lines that were removed in Paragraph 2.A.(11). (See Figure 1.)

(h) Install backing boards to the bottom of the auxiliary tanks that were removed in 

Paragraph 2.A.(10).

(i) Install all auxiliary fuel tank bladders that were removed in Paragraph 2.A.(9) in 

accordance with appropriate Hercules Maintenance Manual or Hercules Maintenance 

Instructions Manual.

(j) Install wing lower fillet fairing assemblies that were removed in Paragraph 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. Remove OWS 369 wing support 

beams.

(3) Install all four QECs that were removed in Paragraph 2.A.(6) in accordance with the appropriate 

Hercules Maintenance Manual or Hercules Maintenance Instructions Manual.

(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) The 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 Service 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 assistance 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 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
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Revision 3, July 8, 2013 (Reissue) Page 15

Figure 1 - Center Wing Fuel Cell Connecting Piping
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3. MATERIAL INFORMATION

A. The following parts/materials, required to modify each aircraft listed in Paragraph 1.A., will be provided 

by the aircraft owner/operator. Parts may be obtained from Lockheed Martin Aeronautics Company in 

accordance with Paragraph 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 

NUMBER 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)

390624-5 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 Installation – 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 61.625, 

Assembly of Drawing

(6)(7)(8)
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NEW PART 

NUMBER 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 Note 2.

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

3. Lockheed Martin Serial Numbers 4299 through 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 TL100, 1st oversize TL110, 2nd oversize TL130 and 

standard TL200, 1st oversize TL210, and 2nd oversize TL230.

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

standard TL200, 1st oversize TL210, 2nd oversize TL230.

(3) Nacelle Attach Fitting and Fairing Attach Angle Fasteners: standard TL200, 1st 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, 20133 Page A1 of A14

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

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 Figures 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 panels and stringers at the indicated fastener attachment holes. The 

Primary Procedure applies Automated Bolt Hole Eddy Current (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 Procedure 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 attach 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 attach angle, then proceed with removing the opposite attach angle repeating 

the inspection, repair and installation of a new attach angle. If any existing lower surface skin panel 

repair doublers are found under the wing attach angle, these should also be removed to facilitate 

Primary Inspection Procedure No. 2.

Center wing lower surface panels, stringers and wing attach angle are fabricated from 7075 aluminum alloy. 

Steel Taper-Lok fasteners attach the wing lower surface assembly to the wing attach angle assembly. 

Service Bulletin 82-481/382-57-50 replaces four Taper-Lok fasteners with larger diameter Hi-Tigue 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 cracks may be orientated slightly inboard or outboard (up to 15 degrees) from the 

chordwise direction.

The fatigue damage originates in the fastener holes of the lower surface panels, stringers and/or front and 

rear beam caps and propagates in a primarily forward and aft direction.

4. PREPARATION OF AIRPLANE

A. Prepare the airplane in accordance with Paragraph 2.A of Service Bulletin 82-790/382-57-85. Ensure 

aircraft is jacked, leveled, fuselage cradles installed, horizontal tail jacks installed, and aft fuselage and 

wing is placed in the “no-load” condition prior to proceeding 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 Hercules Structural Repair Manual for 

fastener removal instructions. Exercise caution in removing fasteners to avoid damaging the structure.
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Page A2 Revision 3, July 8, 2013

5. PRIMARY PROCEDURE NO. 1

ABHEC scan of the center wing lower surface panel assembly fastener holes common to the wing attach 

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 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 - 200 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 A4.)

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. Equipment 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.
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(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 A5.

(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 Figure A6.

(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 approximately 98% as shown in Figure A6.

E. Inspection:

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

(1) Ensure instrument is calibrated in accordance with Paragraph D. 

(2) Scan each fastener hole common to the center wing lower surface panels and stringers (or beam 

caps) from FS 517 to FS 597. (See Figures A1 and A2.)

(3) Conduct a redundant ABHEC backup procedure to confirm suspect damage in accordance with 

Paragraph F.
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Page A4 Revision 3, July 8, 2013

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.

Alternate Method No. 1 – Inspector reinspects 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 the crack (See Figure A3, locations 1 and 2), and perform a ABHEC scan at this 

additional fastener location.

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 82-790/382-57-85 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 lower panel in the area covered by the 

PN 390624 wing attach angle. (See Figures A1 and A2.)

A. NDI Equipment:

 Eddy Current Instrument - Zetec MIZ-21A or equivalent

 Probe, Shielded Pencil - Zetec PN DT30PS 50-500 kHz or equivalent

 Probe Cable - Zetec PN DTPH-3 or equivalent

 Calibration Standard, aluminum - VM Products, Inc. PN VM30889-C1A or equivalent (See figure A3.)

 Draftsman’s Template
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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 acceptable probe contact with the 

part using the procedures detailed in the Nondestructive Inspection (NDI) Procedures 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 signal as shown in Figure A7.

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 Figure A7.

E. Inspection:

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

(1) Ensure instrument is calibrated as in accordance with Paragraph 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 of 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 fastener holes.

(2) To confirm suspected damage, conduct a redundant eddy current surface scan backup procedure in 

accordance with Paragraph F.
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Page A6 Revision 3, 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 below.

(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 Paragraph 2.C.(2) of Service Bulletin 82-790/382-57-85. 

Inspect any holes in the center wing lower surface panel where fasteners are removed for repair installation 

using the ABHEC inspection method described in Paragraph 5 of this Appendix. 
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Revision 3, July 8, 2013 (Reissue) Page A7

8. SYSTEM SECURING

A. Attach Angle Installation:

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

installation of Hi-Tigue fasteners in cold 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. (See Paragraph 2.D of 

Service Bulletin 82-790/382-57-85.)

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 and 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 Taper-Lok fasteners in the wing panel 

assembly in accordance with Chapter 51-70 of Hercules Structural Repair Manual 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 Taper-Lok is essential to attain required durability. Install all 

fasteners wet with sealant in accordance with Chapter 51-40 of Hercules Structural Repair Manual.

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 Instruction Manual.
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382-57-85 APPENDIX A

82-790 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. August 4, 2005

Page A8 Revision 3, July 8, 2013 (Reissue)

Figure A1 - Inspection Location
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Revision 3, July 8, 2013 (Reissue) Page A9

Figure A2 - Outer View of Inspection Area
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382-57-85 APPENDIX A

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Page A10 Revision 3, July 8, 2013

Figure A3 - Conditional Outboard Row Inspection
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Revision 3, July 8, 2013 Page A11

Figure A4 - Calibration Standard, Aluminum - VM Products, Inc. PN VM30889-C1A
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382-57-85 APPENDIX A

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Page A12 Revision 3, July 8, 2013

Figure A5 - Typical X-Y Signal Response from 0.030” X 0.030” Notch
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Revision 3, July 8, 2013 Page A13

Figure A6 - Typical Time-based Signal Response from 0.030” X 0.030” Notch
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Page A14 Revision 3, July 8, 2013

Figure A7 - Lift-off and Notch Signals
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Revision 1, March 8, 2007 Page B1 of B12

NDI OF CENTER WING LOWER SURFACE PANELS AND STRINGERS UNDER NACELLE ATTACH FITTING

AND FAIRING ATTACH ANGLE, WS 178 AND WS 213, 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 panels and stringers at all fastener holes 

common to the nacelle attach fitting and fairing attach angles as shown in figures B1 and B2. Fatigue cracks 

can originate in the center wing lower surface wing panels and stringers at the indicated fastener attachment 

holes. Primary Procedure No. 1 applies Automated Bolt Hole Eddy Current (ABHEC) through each 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 nacelle attach fitting and 

exposed area of the center 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 fabricated from 7075 aluminum alloy. On some aircraft, 

stainless steel 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 Taper-Lok 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 Series Progressive Inspection Procedures Special Inspection SP-254 

inspects this area by radiography.

3. DAMAGE

The fatigue damage originates in the fastener holes of the lower surface panels, stringers and front beam 

lower cap and propagates in a chordwise direction.

4. PREPARATION OF AIRPLANE

Prepare the airplane in accordance with paragraph 2.A of Service Bulletin 82-790/382-57-85.

5. PRIMARY PROCEDURE NO. 1

ABHEC scan of the center wing lower surface panel fastener holes common to the nacelle attach fitting and 

fairing attach angles. (See figures B1 and B2.)

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

 Calibration Standard, aluminum - VM Products, Inc. PN VM30889-C1A or equivalent (See figure B3.)
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

SERVICE BULLETIN

382-57-85 APPENDIX B

82-790 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.

Page B2 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 using the procedures detailed in the Nondestructive 

Inspection (NDI) Procedures Manual Supplement, Section 20-00-00.

D. Equipment 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

 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 B4.

(9) Change MODE to TRG SWP and press the BAL button to null the instrument.
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

SERVICE BULLETIN

APPENDIX B 382-57-85

USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. 82-790

Revision 1, March 8, 2007 Page B3

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

as shown in figure B5.

(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 approximately 98% as shown in figure B5.

E. Inspection:

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

Ensure instrument is calibrated in accordance with paragraph D. Scan each fastener hole common to the 

nacelle attach fitting and fairing attach angles as shown in figure B2.

Conduct 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.

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 front beam cap. 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 82-790/382-57-85 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
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

SERVICE BULLETIN

382-57-85 APPENDIX B

82-790 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.

Page B4 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 Instrument - Zetec MIZ-21A or equivalent

 Probe, Shielded Pencil - Zetec PN DT30PS 50-500 kHz or equivalent

 Probe Cable - Zetec PN DTPH-3 or equivalent

 Calibration Standard, aluminum - VM Products, Inc. PN VM30889-C1A or equivalent (See figure B3.)

 Draftsman’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 acceptable probe contact with the 

part using the procedures detailed in the Nondestructive Inspection (NDI) Procedures 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 signal as shown in figure 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 figure B6.
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

SERVICE BULLETIN

APPENDIX B 382-57-85

USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. 82-790

Revision 1, March 8, 2007 Page B5

E. Inspection:

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

Ensure instrument is calibrated as in accordance with paragraph D. With the nacelle attach fitting 

removed, scan the fitting using overlapping scans. Scan both along the length and across 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 fairing attach angle, and the 

truss mount lower tang for corrosion and/or fretting damage; pay particular attention to the area in and 

around fastener holes.

To confirm suspected damage, conduct a redundant eddy current surface scan 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) 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, 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 30063-0591, USA
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

SERVICE BULLETIN

382-57-85 APPENDIX B

82-790 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.

Page B6 Revision 1, March 8, 2007

7. DAMAGE REPAIR

Repair any damage found in accordance with paragraph 2.C.(2) of Service Bulletin 82-790/382-57-85.

8. SYSTEM SECURING

A. Fastener Installation:

NOTE: Either original type fasteners may be installed 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 adequate training and the necessary tooling and procedures to perform this fatigue 

improvement. (See paragraph 2.D of Service Bulletin 82-790/382-57-85.)

Reinstall the next oversize Taper-Lok fasteners in accordance with Chapter 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 Taper-Lok is essential to attain maximum 

durability. Install all fasteners wet with sealant in accordance with Chapter 51-40 of Hercules Structural 

Repair Manual.

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.
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

SERVICE BULLETIN

APPENDIX B 382-57-85

USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. 82-790

Revision 1, March 8, 2007 Page B7

Figure B1 - Center Wing Lower Surface Inspection Area
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

SERVICE BULLETIN

382-57-85 APPENDIX B

82-790 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.

Page B8 Revision 1, March 8, 2007

Figure B2 - Center Wing Lower Surface Panels Under Left Nacelle, Right Opposite
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

SERVICE BULLETIN

APPENDIX B 382-57-85

USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. 82-790

Revision 1, March 8, 2007 Page B9

Figure B3 - Calibration Standard, Aluminum - VM Products, Inc. PN VM30889-C1A
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

SERVICE BULLETIN

382-57-85 APPENDIX B

82-790 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.

Page B10 Revision 1, March 8, 2007

Figure B4 - Typical X-Y Signal Response from 0.030” X 0.030” Notch
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

SERVICE BULLETIN

APPENDIX B 382-57-85

USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. 82-790

Revision 1, March 8, 2007 Page B11

Figure B5 - Typical Time-based Signal Response from 0.030” X 0.030” Notch
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

SERVICE BULLETIN

382-57-85 APPENDIX B

82-790 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.

Page B12 Revision 1, March 8, 2007

Figure B6 - Lift-off and Notch Signals
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

SERVICE BULLETIN

APPENDIX C 382-57-85

USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. 82-790

Revision 1, March 8, 2007 Page C1 of C14

NDI OF CENTER WING LOWER SURFACE PANELS AND STRINGERS UNDER THE DRAIN TROUGH, 

WS 56, 72, 174, AND 208, 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 panels 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 figure C1. Fatigue

cracks can originate in the center wing lower surface wing panels at the indicated fastener attachment holes 

and drain holes. Primary Procedure No. 1 applies Automated Bolt Hole Eddy Current (ABHEC) scans of the 

attachment fastener holes. Primary Procedure No. 2 applies eddy current surface scans around each drain 

hole in the center wing lower surface panels. The backup procedure is a redundant ABHEC/surface scan.

2. DESCRIPTION

Center wing lower surface panels are fabricated from 7075 aluminum alloy. Aluminum 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. 

Hercules Structural Repair Manual Special Inspection SP-314 inspects this area by radiography.

3. DAMAGE

The fatigue damage originates in the fastener holes of the lower surface panel and stringers common to the 

drain trough attachment and also in the lower surface 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 82-790/382-57-85.

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 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

 Calibration Standard, aluminum - VM Products, Inc. PN VM30889-C1A or equivalent (See figure C2.)
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

SERVICE BULLETIN

382-57-85 APPENDIX C

82-790 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.

Page C2 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. Equipment 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

 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 C3.

(9) Change MODE to TRG SWP and press the BAL button to null the instrument.
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

SERVICE BULLETIN

APPENDIX C 382-57-85

USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. 82-790

Revision 1, March 8, 2007 Page C3

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

as shown in figure C4.

(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 approximately 98% as shown in figure C4.

E. Inspection:

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

Ensure instrument 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 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.

Alternate Method No. 1 – Inspector reinspects 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 representative or the Technical Support Center in Marietta, Georgia, USA, with a

damage report in accordance with paragraph 2.C of Service Bulletin 82-790/382-57-85 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
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

SERVICE BULLETIN

382-57-85 APPENDIX C

82-790 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.

Page C4 Revision 1, March 8, 2007

6. PRIMARY PROCEDURE NO. 2

Eddy current surface scan of the center wing lower surface panels around 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:

 Eddy Current Instrument - Zetec MIZ-21A or equivalent

 Probe, Shielded Pencil - Zetec PN DT30PS 50-500 kHz or equivalent

 Probe Cable - Zetec PN DTPH-3 or equivalent

 Calibration Standard, aluminum - VM Products, Inc. PN VM30889-C1A or equivalent (See figure C2.)

 Draftsman’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 acceptable probe contact with the 

part using the procedures detailed in the Nondestructive Inspection (NDI) Procedures 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 signal as shown in figure C5.

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 figure C5.
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

SERVICE BULLETIN

APPENDIX C 382-57-85

USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. 82-790

Revision 1, March 8, 2007 Page C5

E. Inspection:

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

(1) Ensure instrument is calibrated in accordance with paragraph 6.D. Using the drain plug (bushing) 

attach nut as a guide, scan the lower surface panels from the exterior around each indicated drain 

hole at WS 56, 72, 174, and 208 as shown in figure C6. Scan in both a clockwise and 

counterclockwise direction.

(2) Where access permits, scan the lower surface panels from the interior of the center wing tank at each 

drain plug (bushing) location. See figure 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 suspected 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 suspected damage, remove bushing and perform backup ABHEC scan.

(1) 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

 Calibration Standard, 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.
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

SERVICE BULLETIN

382-57-85 APPENDIX C

82-790 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.

Page C6 Revision 1, March 8, 2007

(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 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 

obtain 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 paragraph (2). Perform a backup inspection of 

suspect damage using an ABHEC scan.
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

SERVICE BULLETIN

APPENDIX C 382-57-85

USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. 82-790

Revision 1, March 8, 2007 Page C7

G. Mark and Report Damage:

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 damage 

report in accordance with paragraph 2.C of Service Bulletin 82-790/382-57-85 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

7. DAMAGE REPAIR

Repair any damage found in accordance with paragraph 2.C.(2) of Service Bulletin 82-790/382-57-85.

8. SYSTEM SECURING

A. Fastener Installation:

NOTE: Either original type fasteners may be installed 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 adequate training and the necessary tooling and procedures to perform this fatigue 

improvement. (See paragraph 2.D of Service Bulletin 82-790/382-57-85.)

Reinstall the next oversize Taper-Lok fasteners in accordance with Chapter 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 Taper-Lok is essential to attain maximum 

durability. Install all fasteners wet with sealant in accordance with Chapter 51-40 of Hercules Structural 

Repair Manual.

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.
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

SERVICE BULLETIN

382-57-85 APPENDIX C

82-790 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.

Page C8 Revision 1, March 8, 2007

Figure C1 - Drain Trough Locations
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

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APPENDIX C 382-57-85

USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. 82-790

Revision 1, March 8, 2007 Page C9

Figure C2 - Calibration Standard, Aluminum - VM Products, Inc. PN VM30889-C1A
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

SERVICE BULLETIN

382-57-85 APPENDIX C

82-790 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.

Page C10 Revision 1, March 8, 2007

Figure C3 - Typical X-Y Signal Response from 0.030” X 0.030” Notch
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

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APPENDIX C 382-57-85

USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. 82-790

Revision 1, March 8, 2007 Page C11

Figure C4 - Typical Time-based Signal Response from 0.030” X 0.030” Notch
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

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382-57-85 APPENDIX C

82-790 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.

Page C12 Revision 1, March 8, 2007

Figure C5 - Lift-off and Notch Signals
HERCULES Lockheed Martin Aeronautics Company

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APPENDIX C 382-57-85

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Revision 1, March 8, 2007 Page C13

Figure C6 - Typical Probe Placement Exterior Surface
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382-57-85 APPENDIX C

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Page C14 Revision 1, March 8, 2007

Figure C7 - Typical Probe Placement Interior Surface
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APPENDIX D 382-57-85

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Revision 1, March 8, 2007 Page D1 of D14

NDI OF CENTER WING LOWER SURFACE PANELS AT 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 panels at all exposed fastener 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 figure D1. Fatigue cracks can originate in the center wing 

lower surface panels 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 an Automated Bolt Hole Eddy Current (ABHEC) scan.

2. DESCRIPTION

Center wing lower surface panels are fabricated from 7075 aluminum alloy. Steel Taper-Lok fasteners and 

aluminum rivets attach the stringers to the skin panels. External splice plates (straps) fabricated from 

7075 aluminum alloy join panel number 1 to 2 and join panel number 2 to 3 from WS 65 to WS 166. 

Steel Taper-Lok 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 

removal by Service Bulletin 82-557/382-57-55. Service Bulletin 82-799/382-57-86 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. DAMAGE

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

4. PREPARATION OF AIRPLANE

Prepare the airplane in accordance with paragraph 2.A of Service Bulletin 82-790/382-57-85.

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

Service Bulletin 82-799/382-57-86 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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382-57-85 APPENDIX D

82-790 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.

Page D2 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:

 Eddy Current Instrument - Zetec MIZ-21A or equivalent

 Probe, Shielded Pencil - Zetec PN DT30PS 50-500 kHz or equivalent

 Probe Cable - Zetec PN DTPH-3 or equivalent

 Calibration Standard, aluminum - VM Products, Inc. PN VM30889-C1A or equivalent (See figure D2.)

 Draftsman’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 acceptable probe contact with the 

part using the procedures detailed in the Nondestructive Inspection (NDI) Procedures 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 to 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 SCALE and GAIN to 

obtain optimum separation of the defect signals as shown in figure D3.
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E. Inspection:

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

(1) Ensure instrument is calibrated as in accordance with paragraph D. Using the 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 figure D4. Use the smallest diameter hole in the template that 

will allow the placement of the probe as close to the edge of each hole as possible. Scan in both a 

clockwise and counterclockwise direction. See figure D4 for typical probe placement example. 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.

(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 right.

(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 edge 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 used to 

attach the fairing 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 suspected damage, remove fasteners and perform backup ABHEC scan.

(1) 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

 Calibration Standard, aluminum - VM Products, Inc. PN VM30889-C1A or equivalent 

(See figure D2.)
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Page D4 Revision 1, March 8, 2007

(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.

(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 D5.

(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 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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Revision 1, March 8, 2007 Page D5

(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.

G. Mark and Report Damage:

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 82-790/382-57-85 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

Automated Bolt Hole Eddy Current Inspection of lower surface forward panel at the PN 373275 attach 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 - 200 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 inspection area.
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Page D6 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) 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

 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 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.

(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 approximately 98% as shown in figure D6.
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E. Inspection:

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

Ensure instrument is calibrated 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.

Alternate Method No. 1 – Inspector reinspects 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 82-790/382-57-85 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

7. DAMAGE REPAIR

Repair any damage found in accordance with paragraph 2.C.(2) of Service Bulletin 82-790/382-57-85.
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Page D8 Revision 1, March 8, 2007

8. SYSTEM SECURING

A. Fastener Installation:

NOTE: Either original type fasteners may be installed 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 adequate training and the necessary tooling and procedures to perform this fatigue 

improvement. (See paragraph 2.D of Service Bulletin 82-790/382-57-85.)

Reinstall the next oversize Taper-Lok fasteners in accordance with Chapter 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 Taper-Lok is essential to attain maximum 

durability. Install all fasteners wet with sealant in accordance 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, 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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APPENDIX D 382-57-85

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Revision 1, March 8, 2007 Page D9

Figure D1 - Center Wing Lower Surface Inspection Area
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382-57-85 APPENDIX D

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Page D10 Revision 1, March 8, 2007

Figure D2 - Calibration Standard, Aluminum - VM Products, Inc. PN VM30889-C1A
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Revision 1, March 8, 2007 Page D11

Figure D3 - Lift-off and Notch Signals
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382-57-85 APPENDIX D

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Page D12 Revision 1, March 8, 2007

Figure D4 - Typical Probe Placement
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Revision 1, March 8, 2007 Page D13

Figure D5 - Typical X-Y Signal Response from 0.030” X 0.030” Notch
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382-57-85 APPENDIX D

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Page D14 Revision 1, March 8, 2007

Figure D6 - Typical Time-based Signal Response from 0.030” X 0.030” Notch
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APPENDIX E 382-57-85

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Revision 1, March 8, 2007 Page E1 of E10

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

1. PURPOSE

This procedure has been developed to detect cracks in the center wing lower surface panel stringers as 

shown in figure 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 wing lower surface stringers. The backup procedure is an Automated Bolt Hole 

Eddy Current (ABHEC) scan.

2. DESCRIPTION

Center wing lower surface stringers are fabricated from 7075 aluminum alloy. Steel Taper-Lok fasteners and 

aluminum rivets attach the stringers to the skin panels. Various types of steel fasteners attach miscellaneous 

systems hardware to the stringers. On Lockheed serial number 4334 and up, the stringer/strap assemblies 

were replaced with integrally reinforced stringers and the material temper was changed from T6 to T73; refer 

to Service Bulletin 82-752/382-53-61.

3. DAMAGE

Fatigue cracks 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 direction. 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 82-790/382-57-85. All systems 

attachment hardware is to be removed from the stringer hats except for blind attachment fasteners. 

Fasteners attaching the stringer internal reinforcing straps installed on aircraft prior to serial number 4334 

do not require removal. To gain access into the lower surface panel No. 3 stringers between 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. PRIMARY PROCEDURE

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

A. NDI Equipment:

 Eddy Current instrument - Zetec MIZ-21A or equivalent

 Probe, Shielded Pencil - Zetec PN DT30PS 50-500 kHz or equivalent

 Probe Cable - Zetec PN DTPH-3 or equivalent

 Calibration Standard, aluminum - VM Products, Inc. PN VM30889-C1A or equivalent (See figure E2.)

 Draftsman’s Template

B. Access:

Use appropriate maintenance stands to gain access to the inspection area.
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Page E2 Revision 1, March 8, 2007

C. Preparation of Part:

Remove sealant with a plastic or phenolic scraper as necessary for acceptable probe contact with the 

part using the procedures detailed in the Nondestructive Inspection (NDI) Procedures 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 signal as shown in figure 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.

Ensure 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 

figure 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 angles/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:

Ensure instrument is calibrated 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 internal reinforcing 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 ABHEC scan backup procedure in accordance with paragraph H.
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G. Inspection #3:

Ensure instrument is calibrated in accordance with paragraph D. In the area of rib attachments, scan the 

stringers at the nearest exposed edges for cracks propagating under the rib feet.

H. Backup Inspection (for confirmation only):

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

(1) 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

 Calibration Standard, aluminum - VM Products, Inc. PN VM30889-C1A or equivalent 

(See 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 mini 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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Page E4 Revision 1, March 8, 2007

(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 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 figure 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 82-790/382-57-85 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. DAMAGE REPAIR

Repair any damage found in accordance with paragraph 2.C.(2) of Service Bulletin 82-790/382-57-85.

7. 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.
HERCULES Lockheed Martin Aeronautics Company

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APPENDIX E 382-57-85

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Revision 1, March 8, 2007 Page E5

Figure E1 - Center Wing Lower Surface Stringers
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382-57-85 APPENDIX E

82-790 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.

Page E6 Revision 1, March 8, 2007

Figure E2 - Calibration Standard, Aluminum - VM Products, Inc. PN VM30889-C1A
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Revision 1, March 8, 2007 Page E7

Figure E3 - Lift-off and Notch Signals
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382-57-85 APPENDIX E

82-790 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.

Page E8 Revision 1, March 8, 2007

Figure E4 - Typical Probe Placement on Stringer Flange
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APPENDIX E 382-57-85

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Revision 1, March 8, 2007 Page E9

Figure E5 - Typical X-Y Signal Response from 0.030” X 0.030” Notch
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382-57-85 APPENDIX E

82-790 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.

Page E10 Revision 1, March 8, 2007

Figure E6 - Typical Time-based Signal Response from 0.030” X 0.030” Notch
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APPENDIX F 382-57-85

USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. 82-790

Revision 1, March 8, 2007 Page F1 of F22

NDI OF CENTER WING LOWER SURFACE FRONT AND REAR BEAM CAPS,

WS 210 LEFT TO WS 210 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 figure F1. Fatigue cracks can originate in the front and rear lower beam caps at the 

beam web and lower surface 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 Current (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 

backup procedure is an ABHEC scan.

2. DESCRIPTION

Center wing front and rear beam lower caps are fabricated 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 T6 temper; refer to Service Bulletin 82-768/382-57-81.

3. DAMAGE

Fatigue cracks 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 fabricated from 7075-T6 are 

prone to exfoliation corrosion and stress corrosion cracking.

4. PREPARATION OF AIRPLANE

A. Prepare the airplane in accordance with paragraph 2.A of Service Bulletin 82-790/382-57-85.

B. Remove the auxiliary tank attachment eyebolts (Figure F13), which 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, and 176

C. Remove each of the fasteners as indicated in figures F2, F3, F4 and F5 that are common to the center 

wing lower surface beam caps and lower corner fittings.
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382-57-85 APPENDIX F

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Page F2 Revision 1, March 8, 2007

5. PRIMARY PROCEDURE NO. 1

Eddy current surface scan of the center wing lower surface beam cap horizontal and vertical legs front and 

rear. (See figure F1.)

A. NDI Equipment:

 Eddy Current Instrument - Zetec MIZ-21A or equivalent

 Probe, Shielded Pencil - Zetec PN DT30PS 50-500 kHz or equivalent

 Probe Cable - Zetec PN DTPH-3 or equivalent

 Calibration Standard, aluminum - VM Products, Inc. PN VM30889-C1A or equivalent (See figure F6.)

 Draftsman’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 acceptable probe contact with the 

part using the procedures detailed in the Nondestructive Inspection (NDI) Procedures 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 signal as shown in figure F7.

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 F7.
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Revision 1, March 8, 2007 Page F3

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 appropriate probe, scan 

the center wing lower surface beam caps around each beam cap fastener hole WS 210 left to WS 210 

right. Scan in both a clockwise and counterclockwise direction. See figures F8 and F9 for typical probe 

placement example. For any areas that have sheet metal supports as shown in figure F10, 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 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 suspected damage, remove fasteners and perform backup ABHEC scan.

(1) 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

 Calibration Standard, aluminum - VM Products, Inc. PN VM30889-C1A or equivalent 

(See figure F6.)

(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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Page F4 Revision 1, March 8, 2007

(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 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 F12.

(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 F12.

(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.
HERCULES Lockheed Martin Aeronautics Company

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APPENDIX F 382-57-85

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Revision 1, March 8, 2007 Page F5

G. Mark and Report Damage:

Mark any damage to 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 82-790/382-57-85 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

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 F13.)

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, 5/32” diameter - GE Inspection Technologies 

PN 620-546-156 or equivalent

 Calibration Standard, aluminum - VM Products, Inc. PN VM30889-C1A or equivalent (See figure F6.)

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 acceptable 

probe contact with the part.

D. Equipment Calibration:

(1) Turn the instrument on.

(2) Connect the cable to the instrument.

(3) Connect the mini probe drive to the cable.
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Page F6 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 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 F11.

(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 figure F12.

(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 approximately 98% as shown in figure F12.

E. Inspection #1:

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

NOTE: The left and right aft corner fittings (see figures F2, F3, F4 and F5) are fabricated from steel and 

will not be inspected with this procedure. Spar 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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APPENDIX F 382-57-85

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Revision 1, March 8, 2007 Page F7

NOTE: High speed scanning of bolt holes reduces the potential effects of dissimilar metals at interfaces 

therefore RPM rates of 1000 or higher are required for equivalency with the probe gun and 

settings specified.

NOTE: Removal of the corner fitting may be required if interface indications cannot be resolved through 

additional cleaning and verification.

Ensure instrument is calibrated as in accordance with paragraph D. Scan each of the fastener holes as 

indicated in figures F2, F3, F4 and F5) that are common to the center wing lower surface beam caps and 

lower corner fittings, 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 figure F13.

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, and 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 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.

Alternate Method No. 1 – Inspector reinspects the area with an appropriate alternate method.
HERCULES Lockheed Martin Aeronautics Company

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382-57-85 APPENDIX F

82-790 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.

Page F8 Revision 1, March 8, 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 82-790/382-57-85 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

7. DAMAGE REPAIR

Repair any damage found in accordance with paragraph 2.C.(2) of Service Bulletin 82-790/382-57-85.

8. SYSTEM SECURING

A. Fastener Installation:

NOTE: Either original type fasteners may be installed 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 adequate training and the necessary tooling and procedures to perform this fatigue 

improvement. (See paragraph 2.D of Service Bulletin 82-790/382-57-85.)

(1) Reinstall the next oversize Taper-Lok fasteners in accordance with Chapter 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 Taper-Lok is essential to attain 

maximum durability. Install all fasteners wet with sealant in accordance with Chapter 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 fatigue crack indications. Ream 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 hole diameter exceeds 0.284 inches 

(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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APPENDIX F 382-57-85

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Revision 1, March 8, 2007 Page F9

Figure F1 - Center Wing Box, Front and Rear Lower Surface Beam Caps
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382-57-85 APPENDIX F

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Page F10 Revision 1, March 8, 2007

Figure F2 - Center Wing Corner Fittings, Lower Forward Fitting Shown (Long)
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APPENDIX F 382-57-85

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Revision 1, March 8, 2007 Page F11

Figure F3 - Center Wing Corner Fittings, Lower Forward Fitting Shown (Short)
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382-57-85 APPENDIX F

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Page F12 Revision 1, March 8, 2007

UP

OUT

LOWER AFT CORNER 

FITTING (STEEL)

WS 210.8 WS 205.7

VIEW INSIDE DRY BAY LOOKING AFT

UP

OUT

LOWER AFT CORNER 

FITTING (STEEL)

WS 210.8 WS 205.7

VIEW INSIDE DRY BAY LOOKING AFT

 Fasteners to be removed and holes inspected (ABHEC)

Figure F4 - Center Wing Corner Fittings, View Inside Dry Bay
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Revision 1, March 8, 2007 Page F13

OUT

UP

WS 210.8

WS 213.6

LOWER AFT CORNER 

FITTING (STEEL)

VIEW LOOKING FORWARD

OUT

UP

WS 210.8

WS 213.6

LOWER AFT CORNER 

FITTING (STEEL)

VIEW LOOKING FORWARD

 Fasteners to be removed and holes inspected (ABHEC)

Figure F5 – Center Wing Corner Fittings, External View of Rear Beam
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382-57-85 APPENDIX F

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Page F14 Revision 1, March 8, 2007

Figure F6 - Calibration Standard, Aluminum - VM Products, Inc. PN VM30889-C1A
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Revision 1, March 8, 2007 Page F15

Figure F7 – Lift-off and Notch Signals
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382-57-85 APPENDIX F

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Page F16 Revision 1, March 8, 2007

Figure F8 - Spar Cap Horizontal Leg Typical Probe Placement Primary Procedure No. 1
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Revision 1, March 8, 2007 Page F17

Figure F9 - Spar Cap Vertical Leg Typical Probe Placement Primary Procedure No. 1
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Page F18 Revision 1, March 8, 2007

Figure F10 - Rear Spar Cap at Sheet Metal Supports. Front Spar Cap 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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Revision 1, March 8, 2007 Page F19

Figure F11 - Typical X-Y Signal Response from 0.030” X 0.030” Notch
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382-57-85 APPENDIX F

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Page F20 Revision 1, March 8, 2007

Figure F12 - Typical Time-based Signal Response from 0.030” X 0.030” Notch
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APPENDIX F 382-57-85

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Revision 1, March 8, 2007 Page F21

Figure F13 - Auxiliary 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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382-57-85 APPENDIX F

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Page F22 Revision 1, March 8, 2007

THIS PAGE INTENTIONALLY LEFT BLANK
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APPENDIX G 382-57-85

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Revision 1, March 8, 2007 Page G1 of G12

NDI OF CENTER WING LOWER SURFACE PANEL REPAIRS

1. PURPOSE

This procedure has been developed to detect cracks in the center wing lower surface panel at repair doublers 

and/or straps as shown in figure 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 lower surface to determine if any repairs exist. Primary Procedure No. 2 applies 

Automated Bolt Hole Eddy Current (ABHEC) scan through each layer of selected attachment fastener holes 

common to the center wing lower surface panels and repair doublers and/or 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 surface panels are fabricated 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 which are 

recommended for permanent removal by Service Bulletin 82-557/382-57-55. 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 any composite material repair members.

3. DAMAGE

Fatigue cracks 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 paragraph 2.A of Service Bulletin 82-790/382-57-85.

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. Production 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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Page G2 Revision 1, March 8, 2007

6. PRIMARY PROCEDURE NO. 2

ABHEC scan of the center wing lower surface panel at the outer 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 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, 5/32” diameter - GE Inspection Technologies 

PN 620-546-156 or equivalent

 Calibration standard, aluminum - VM Products, Inc. PN VM30889-C1A or equivalent (See figure G2.)

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 acceptable 

probe contact with the part.

D. Equipment 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

 PRB GAIN 85

 MODE X-Y

 V SCALE 0.2

 H SCALE 0.4

 FILTER DIFF 01

 SCREEN SET AUTOCLEAR 0
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Revision 1, March 8, 2007 Page G3

(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 G3.

(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 figure 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 GAIN, V SCALE, H SCALE and PHASE to obtain a 

signal height of approximately 98% as shown in figure G4.

E. Inspection:

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

Ensure instrument is calibrated as in accordance with paragraph D. Perform ABHEC scan of the outer 

two inboard and outboard rows of fasteners attaching each repair doublers layer and/or straps to 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) 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.
HERCULES Lockheed Martin Aeronautics Company

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Page G4 Revision 1, March 8, 2007

G. Mark and Report Damage:

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 Service Bulletin 82-790/382-57-85 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

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 Instrument - Zetec MIZ-21A or equivalent

 Probe, Shielded Pencil - Zetec PN DT30PS 50-500 kHz or equivalent

 Probe Cable - Zetec PN DTPH-3 or equivalent

 Calibration Standard, aluminum - VM Products, Inc. PN VM30889-C1A or equivalent (See figure G2.)

 Draftsman’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 acceptable probe contact with the 

part using the procedures detailed in the Nondestructive Inspection (NDI) Procedures 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.
HERCULES Lockheed Martin Aeronautics Company

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Revision 1, March 8, 2007 Page G5

(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 figure 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 figure 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 wing 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 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 suspected damage, remove fasteners and perform backup ABHEC scan.

(1) 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

 Calibration Standard, aluminum - VM Products, Inc. PN VM30889-C1A or equivalent 

(See 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.
HERCULES Lockheed Martin Aeronautics Company

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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 the 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). Remove fasteners and perform 

a backup inspection of suspect damage using an ABHEC scan.
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

SERVICE BULLETIN

APPENDIX G 382-57-85

USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. 82-790

Revision 1, March 8, 2007 Page G7

G. Mark and Report Damage:

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 82-790/382-57-85 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

8. DAMAGE REPAIR

Repair any damage found in accordance with paragraph 2.C.(2) of Service Bulletin 82-790/382-57-85.

9. SYSTEM SECURING

A. Fastener Installation:

NOTE: Either original type fasteners may be installed 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 adequate training and the necessary tooling and procedures to perform this fatigue 

improvement. (See paragraph 2.D of Service Bulletin 82-790/382-57-85.) 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 Taper-Lok fasteners in accordance with Chapter 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 Taper-Lok is essential to attain maximum 

durability. Install all fasteners wet with sealant in accordance 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, 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.
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

SERVICE BULLETIN

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 Fasteners to be removed and holes inspected (ABHEC) at each end of the repair doublers

Figure G1 - Typical Center Wing Lower Surface Repair

LOWER SURFACE 

STRINGER (TYP)

LOWER SURFACE 

PANEL (TYP)

LOWER SURFACE 

REPAIR DOUBLERS 

(TYP)
HERCULES Lockheed Martin Aeronautics Company

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Revision 1, March 8, 2007 Page G9

Figure G2 - Calibration Standard, Aluminum - VM Products, Inc. PN VM30889-C1A
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

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Page G10 Revision 1, March 8, 2007

Figure G3 - Typical X-Y Signal Response from 0.030” X 0.030” Notch
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

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Revision 1, March 8, 2007 Page G11

Figure G4 - Typical Time-based Signal Response from 0.030” X 0.030” Notch
HERCULES Lockheed Martin Aeronautics Company

 Marietta, Georgia 30063

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382-57-85 APPENDIX G

82-790 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.

Page G12 Revision 1, March 8, 2007

Figure G5 – Lift-off and Notch Signals