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.

382-57-82

Revision 6, July 11, 2013 82-771

* REVISION NOTICE *

WINGS - CENTER WING UPPER AND LOWER RAINBOW FITTING INSPECTION FOR CRACKS AND 

REPLACEMENT

Attached is Revision 6, dated July 11, 2013, to Service Bulletin 82-771/382-57-82. Information added or changed 

in this issue is indicated by a vertical revision bar in the outside margin of affected pages, or pointing hand for 

illustrations.

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 for the center wing rainbow fittings to safeguard the aircraft against widespread 

fatigue damage up to the LOV, which include updates to the initial and recurring inspection schedule.

This revision is a complete reissue and replaces Revision 5 of this Service Bulletin dated August 12, 2010. 

Retain this notice with your copy of this Service Bulletin.

List of Previous Revisions and/or Reissues

Basic December 7, 2004

Revision 1 (Reissue) February 24, 2005

Revision 2 (Reissue) February 15, 2007

Revision 3 (Reissue) April 25, 2008

Revision 4 (Reissue) May 20, 2009

Revision 5 (Reissue) August 12, 2010

___________#__________

File: I-2996R6

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.

382-57-82

December 7, 2004 82-771

Revision 6, July 11, 2013 Page 1 of 17

WINGS - CENTER WING UPPER AND LOWER RAINBOW FITTING INSPECTION FOR CRACKS AND 

REPLACEMENT

NOTE: This Service Bulletin contains Appendices A, B, and C.

1. PLANNING INFORMATION

A. EFFECTIVITY

(1) 382-57-82, 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) 82-771, 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) 82-771, 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) Fatigue cracking of the wing upper and lower rainbow fittings on the durability test and on inservice aircraft indicates a requirement to perform inspections prior to the current published 

Hercules Airfreighter Series Progressive Inspection Procedures and Hercules Airfreighter 

Progressive Inspection Procedures intervals. Analysis of in-service cracking has shown that 

these fittings are susceptible to Multiple Site Damage (MSD) and a more frequent inspection is 

required to ensure that multiple adjacent node cracking does not occur resulting in an 

unacceptable reduction in residual strength. This Service Bulletin identifies revised inspection 

intervals in order to reduce the probability of failure to an acceptably low level until such time as 

the wing joint fittings are replaced consistent with the recommendations identified herein.

NOTE: The inspection intervals provided are subject to individual operator usage severity. 

The intervals provided in this Service Bulletin are based on the Lockheed Martin 

Baseline Military and/or Commercial mission profiles and utilization rates. Operators 

who have completed a Lockheed Martin usage evaluation analysis may adjust the 

intervals provided in the Service Bulletin by the severity factors developed for their 

inspection programs.

(2) 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. Revision 6 incorporates maintenance actions 

required for the center wing rainbow fittings to safeguard the aircraft against widespread fatigue 

damage up to the LOV, which include updates to the initial and recurring inspection intervals.
HERCULES Lockheed Martin Aeronautics Company

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Page 2 Revision 6, July 11, 2013

(3) Lockheed Martin Aeronautics Company recommends that the inspection specified herein be 

accomplished on all military aircraft center wings that have accumulated more than 10,000 

Equivalent Baseline Hours (EBH) as determined from Service Bulletin 82-788 Paragraph 2.A. or 

from Lockheed Martin Aeronautics Company Operational Usage Evaluation in accordance with 

Service Bulletin 82-788, paragraph 2.B.(2). The initial inspection should be performed at the next 

convenient maintenance period but not to exceed 365 days or 600 flight hours, whichever occurs 

first, after receipt of this Service Bulletin. For center wings that have accumulated 15,000 or more

total EBH, Lockheed Martin Aeronautics Company recommends restricting the aircraft in 

accordance with Service Bulletin 82-788 Paragraph 2.B.(4) until the inspection is accomplished. 

For center wings that have accumulated 20,000 or more total EBH, Lockheed Martin Aeronautics 

Company recommends grounding the aircraft until the inspection is accomplished. 

Accomplishment of this inspection in accordance with the basic or Revision 1 of this Service 

Bulletin meets the intent of the initial inspection. Recurring inspection is recommended at 2,500

EBH for center wings with less than 25,000 total EBH and at 1,000 EBH for center wing that have 

accumulated 25,000 or more total EBH.

(4) For commercial operators, Lockheed Martin Aeronautics Company recommends inspections be 

completed as follows:

(a) The upper surface rainbow fitting inspection specified in Appendix A should be 

accomplished for commercial center wings that have accumulated 10,000 or more flight 

hours. The initial inspection should be performed at the next convenient maintenance 

period but not to exceed 365 days or 600 flight hours, whichever occurs first, after receipt 

of this Service Bulletin. For center wings that have accumulated 20,000 or more flight 

hours, Lockheed Martin Aeronautics Company recommends grounding the aircraft until the 

inspection is accomplished. Accomplishment of this inspection in accordance with the 

basic or earlier revisions of this Service Bulletin meets the intent of the initial inspection. 

Recurring inspection is recommended at 2,500 flight hours.

(b) The lower surface rainbow fitting inspection specified in Appendix B should be 

accomplished for commercial center wings that have accumulated 15,000 or more flight 

hours. The initial inspection should be performed at the next convenient maintenance

period but not to exceed 365 days or 600 flight hours, whichever occurs first, after receipt

of this Service Bulletin. For center wings that have accumulated 20,000 or more flight 

hours, Lockheed Martin Aeronautics Company recommends grounding the aircraft until the

inspection is accomplished. Accomplishment of this inspection in accordance with the

basic or earlier revisions of this Service Bulletin meets the intent of the initial inspection. 

Recurring inspection is recommended at 3,600 flight hours.

(5) Lockheed Martin Aeronautics Company recommends that both upper and lower joint fittings be 

replaced on military aircraft at 25,000 EBH and on commercial aircraft at 30,000 flight hours. 

This will reset the EBH or flight hours to zero with respect to the inspection requirements 

identified in this Service Bulletin.
HERCULES Lockheed Martin Aeronautics Company

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Revision 6, July 11, 2013 Page 3

C. DESCRIPTION

Inspect center wing upper and lower rainbow fitting for cracks in accordance with Appendices A and B

of this Service Bulletin. Hercules Airfreighter Progressive Inspection Procedures and Hercules 

Airfreighter Series Progressive Inspection Procedures work cards SP-176 (upper fitting) and SP-257 

(lower fitting) meet the intent of this Service Bulletin.

Remove installed upper and lower rainbow fitting. Prior to installation of a new rainbow fitting, an 

Automated Bolt Hole Eddy Current Inspection should be competed in accordance with Appendix C. 

After all necessary repairs have been completed, install new rainbow fitting.

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.

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. The manpower estimates provided have not been validated and should not 

be construed as being acceptable for use in making fixed price quotes for accomplishment of the work. 

These estimates are provided only as a convenience for aircraft owner/operator planning purposes. It is 

estimated that manhours required, crew size, and elapsed time while the aircraft is out of service are as 

follows:

TASK MANHOURS CREW SIZE ELAPSED TIME

Inspection Appendix A & B 24 2 12

Removal and Installation of fitting 740 6 410

Inspection Appendix C 24 2 12
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Page 4 Revision 6, July 11, 2013

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, as noted, if desired. Direct 

inquiries concerning prices 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

(1) For Appendix A:

 Eddy current inspection unit, Nortec 19e, or equivalent.

 Probe, shielded, right angle, 1/2-inch drop, VM Products P/N VM202RA-1/2, or equivalent.

 Probe, pencil, surface, 1/8-inch diameter, Mu Metal shielded, stainless steel body, VM 

Products P/N VM200-3, or equivalent.

 Cable, 6 foot, Microdot connector, VM Products P/N VM99BM, or equivalent.

 Calibration standard, aluminum, Lockheed Martin Aeronautics Company P/N PDL 457A as 

illustrated in Nondestructive Inspection (NDI) Procedures Manual Supplement 

Section 20-40-00 or equivalent.

(2) For Appendix B:

 Eddy Current Flaw Detector, Zetec P/N MIZ-20A, or equivalent.

 Probe, surface, right angle, 1/4-inch drop, VM Products P/N VM202RA-1/4, or equivalent.

 Probe, pencil, surface, 1/8-inch diameter, Mu Metal shielded, stainless steel body, VM 

Products P/N VM200-3, or equivalent.

 Cable, 6-foot Microdot connector, VM Products P/N VM99BM, or equivalent.

 Calibration standard, aluminum, Lockheed Martin Aeronautics Company P/N PDL 457A as 

illustrated in Nondestructive Inspection (NDI) Procedures Manual Supplement 

Section 20-40-00 or equivalent.
HERCULES Lockheed Martin Aeronautics Company

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Revision 6, July 11, 2013 Page 5

(3) For Removal and Installation of Rainbow Fitting:

 3302624-16F Fixture to locate the New Joint Fitting.

 3302624-L/R-18F Fixture to Mill the nodes of the new Joint Fitting.

 185R105-002A Router for milling the new Joint Fitting.

 446E101-015C Cutter for above router.

 730M200-004A Depth Micrometer.

 Jig Transit (with Optical micrometer)

(4) For Appendix C:

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

 Mini probe drive - GE Inspection Technologies P/N 33A100 or equivalent

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

 Probe, rotating hole, reflection type, 200 kHz to 2 MHz, 3/16”, 1/4”, and 5/16” diameter -

GE Inspection Technologies P/N 620-546-156 or equivalent

 Calibration standard, aluminum - VM Products, Inc. P/N VM30889-C1A or equivalent (see 

Figure C1)

H. WEIGHT AND BALANCE

None.

I. REFERENCES

Nondestructive Inspection (NDI) Procedures Manual Supplement

(1) 382-57-82, FAA Certificated Aircraft:

Hercules Maintenance Manual

Hercules Airfreighter Progressive Inspection Procedures

Service Bulletin 382-57-84/ Wing - Operational Usage Evaluation and Service Life Assessment

(2) 82-771, Foreign Military Aircraft:

Hercules Maintenance Instructions Manual

Hercules Airfreighter Series Progressive Inspection Procedures

Service Bulletin 82-788 / Wing - Operational Usage Evaluation and Service Life Assessment
HERCULES Lockheed Martin Aeronautics Company

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82-771 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. December 7, 2004

Page 6 Revision 6, July 11, 2013

(3) The following Lockheed Martin drawings may be needed for reference

DWG NO. DESCRIPTION A/C EFFECTIVITY

LM 398801 LWR Surface Instl 4314-5214

LM 398802 LWR Surface Assy 4314-5214 & MEP 

12Y,4R,7W

LM 3333915 LWR Surface Instl 5215 & Subsequent

LM 3333917 LWR Surface Assy 5215 & Subsequent

LM 398803 UPR Surface Instl 4314–5305

LM 398804 UPR Surface Assy 4314–5214 & MEP 

12Y,4R,7W

LM 3337184 UPR Surface Instl 5306 & Subsequent

LM 3333918 UPR Surface Assy 5215 & Subsequent

LM 398800 Center Wing Assy 4299–5509

LM 3356018 Center Wing Assy 5510 & Subsequent

LM 370500 Wing Joint Basic Dimension

J. OTHER PUBLICATIONS AFFECTED

Hercules Airfreighter Progressive Inspection Procedures

Hercules Airfreighter Series Progressive Inspection Procedure
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2. ACCOMPLISHMENT INSTRUCTIONS

A. INITIAL INSPECTION

(1) This Service Bulletin changes the initial inspection in the Hercules Airfreighter Series Progressive 

Inspection Procedures to 10,000 Equivalent Baseline Hours (EBH) on military aircraft for cracks 

in center wing upper and lower rainbow fitting (see Appendix A and Appendix B).

(2) This Service Bulletin changes the initial inspection in the Hercules Airfreighter Progressive 

Inspection Procedures for commercial aircraft to 10,000 flight hours for cracks in center wing 

upper rainbow fitting (see Appendix A) and 15,000 flight hours for cracks in center wing lower 

rainbow fitting (see Appendix B).

B. RECURRING INSPECTION

(1) This Service Bulletin changes the recurring inspection in the Hercules Airfreighter Series 

Progressive Inspection Procedures to 2,500 EBH on military aircraft with less than 25,000 total 

EBH accumulated on the center wing and 1,000 EBH on military aircraft that have accumulated 

25,000 or more EBH total on the center wing.

(2) This Service Bulletin changes the recurring inspection in the Hercules Airfreighter Progressive 

Inspection Procedures on commercial aircraft to 2,500 flight hours for the center wing upper 

rainbow fitting and 3,600 flight hours for the lower center wing rainbow fitting.

C. REPLACEMENT OF WING JOINT FITTINGS

(1) This Service Bulletin recommends replacement of the upper and lower wing joint fittings in 

accordance with Hercules Maintenance Instructions Manual on military aircraft with more than 

25,000 total EBH accumulated on the center wing.

(2) This Service Bulletin recommends replacement of the upper and lower wing joint fittings in 

accordance with Hercules Maintenance Manual on commercial aircraft with more than 30,000 

total flight hours accumulated on the center wing.

(3) Preparation for Replacement

(a) Perform Alignment and Symmetry on Aircraft in accordance with SMP583 Structural Repair 

Manual, Chapter 51-100-00. Retain this data for future reference.

(b) Remove Outer Wings using instructions in SMP581 Fig 57-10-03 or TM382C-2-1 Fig 7-4

and place wings on Cradle.

(c) Remove No. 2 and 3 Engines including lower nacelles.

(d) Conduct a survey of the WS 220 center wing joint plane using a suitable optical transit. 

Record any disparity in planarity between all nodes. Ref drawings 398800 and 3356018. 

Contact Lockheed Martin Aeronautics Company if the four corner fittings are not co-planar 

within drawings requirements.
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Page 8 Revision 6, July 11, 2013

(e) Removal of all components such as plumbing and wiring necessary to facilitate installation 

of joint fittings will be accomplished in area between WS 178 and WS 220.

(f) Remove as necessary or disconnect one end of the CWS 213 truss mount diagonal brace. 

Ref. Drawing (339166).

(g) Remove clips, four per side, common to the corner fittings, wing joint fittings, and skin.

See Figure 1 depicting the removed upper rainbow fitting and connections.

(4) Upper Fitting Replacement

WARNING: REPLACE UPPER OR LOWER FITTINGS ONE AT A TIME. RIGHT AND LEFT 

SIDE MAY BE DONE SIMULTANEOUSLY.

(a) Remove upper fitting by removing attaching fasteners and breaking fay surface sealant.

Use caution as to not damage wing structure and attach holes. See Figure 2 for illustrative

view of uninstalled Rainbow fittings.

WARNING: EXERCISE CAUTION WHEN INSTALLING OR REMOVING THE NEW FITTING 

TO AND FROM THE WING. AVOID APPLYING UNDUE FORCE DURING THIS 

PROCESS TO PREVENT CRACKING THE FITTING AND OTHER WING 

COMPONENTS.

(b) Clean wing attaching structure such as skin panels, stringers, corner fittings, attaching

angles, and straps, of sealant and other particles.

(c) Visually inspect the wing faying structure for possible damage or cracks and perform 

Automated Bolt Hole Eddy Current inspection of all opened fitting attachment fastener 

holes in skins, stringers, straps, and angles while fitting is removed in accordance with

Appendix C of this Service Bulletin.

(d) Place the new fitting in the wing. Some amount of force may be required to properly align 

fitting. Reference Drawing 398804 or 3333918 Upper Surface Assy.

(e) Install P/N 3302624-16F (Figure 3) locating fixture and attach it to the four corner fittings. 

A shim of suitable size and thickness must be placed between the fixture and each of the 

four corner fittings to allow the joint fitting nodes to protrude for final node milling to assure 

joint planarity. All four shims must be the same thickness. Reference Engineering 

Drawing 398800 or 3356018 for wing joint node thickness requirements. All nodes of the 

rainbow fitting shall be tight against fixture before proceeding.

(f) Check all fitting to wing attaching fastener holes for proper edge distance (2 X Hole 

Diameter nominal & 1 1/2 X Hole Diameter minimum).

(g) Visually check the new joint fitting for proper placement/alignment prior to drilling 

operations.

(h) Transfer all fastener holes from center wing mating structure to new joint fitting.
HERCULES Lockheed Martin Aeronautics Company

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(i) Remove the locating fixture and joint fitting from wing. Clean fitting and the surrounding 

wing area for debris and burrs.

(j) Reposition the new joint fitting in the wing, picking up previously drilled holes. Fay surface

seal in accordance with SMP583 SRM.

(k) Wet install oversize fasteners of appropriate type per engineering drawing and SMP583 

SRM.

(l) Install clips common to the corner fitting, wing joint fitting, and skin as shown on 

engineering drawing.

(5) Lower Fitting Replacement

(a) Remove lower fitting by removing attaching fasteners and breaking fay surface sealant. 

Remove straps and angles common to the fitting, skin, and stringers. Use caution as to 

not damage wing structure and attach holes.

(b) Clean wing attaching structure such as skin panels, stringers, and corner fittings of sealant

and other particles.

WARNING: EXERCISE CAUTION WHEN INSTALLING OR REMOVING THE NEW FITTING 

TO AND FROM THE WING. AVOID APPLYING UNDUE FORCE DURING THIS 

PROCESS TO PREVENT CRACKING THE FITTING AND OTHER WING 

COMPONENTS.

WARNING: VISUALLY INSPECT THE WING FAYING STRUCTURE FOR POSSIBLE 

DAMAGE OR CRACKS AND PERFORM AUTOMATED BOLT HOLE EDDY 

CURRENT INSPECTION OF ALL OPENED FITTING ATTACHMENT 

FASTENER HOLES IN SKINS, STRINGERS, STRAPS, AND ANGLES WHILE

FITTING IS REMOVED IN ACCORDANCE WITH APPENDIX C OF THIS 

SERVICE BULLETIN.

(c) Place the new fitting in the wing. Some amount of force may be required to properly align 

fitting. Reference Drawing 398802 or 3333917 Lower Surface Assy for proper fit and 

installation.

(d) Install 3302624-16F (Figure 3) locating fixture and attach it to the four corner fittings. A 

shim of suitable size and thickness must be placed between the fixture and each of the 

four corner fittings to allow the joint fitting nodes to protrude for final node milling to assure 

joint planarity. All four shims must be the same thickness. Reference engineering drawing 

398800 or 3356018 for wing joint node thickness requirements. All nodes of fitting shall be

tight against fixture before proceeding.

(e) Check all fitting to wing attaching fastener holes for proper edge distance. (2 X Hole 

Diameter nominal & 1 1/2 X Hole Diameter minimum)

(f) Visually check the new joint fitting for proper placement/alignment prior to drilling 

operations.
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(g) Transfer all remaining fastener holes from center wing mating structure to new joint fitting

(h) Remove the locating fixture, joint fitting, straps, and angles from wing. Clean components

and the surrounding wing area for debris and burrs.

(i) Reposition the new joint fitting, straps, and angles in the wing, picking up previously drilled

holes. Fay surface seal in accordance with SMP583 SRM.

(j) Wet install oversize fasteners of appropriate type per engineering drawing and SMP583 

SRM.

(k) Install clips common to the corner fitting, wing joint fitting, and skin.

(l) Continue to Fitting Node Procedures.

(6) Fitting Node Milling Procedure

(a) This step is required for milling and optical procedures: Support the aircraft using nose 

and main landing gear jacks. Mechanically lock jacks to avoid movement during 

machining. Do not utilize wing jacks. Shoring is required if jacks cannot be mechanically

locked.

(b) Position optical transit as required to adequately read the location of the wing joint fittings. 

Adjust the jacks until the four corner fitting node faces are in the same vertical plane. This 

step will not be necessary if a suitable transit is used that is equipped with degrees of 

freedom that permit setting the transit line of sight in a non-vertical plane with the four 

corner fitting nodes. Verify that the four corner fitting nodes are coplanar and check the

amount of joint fitting node face protrusion. Node thickness requirements are defined by 

Engineering Drawing 398800 or 3356018.

(c) Ensure that Steps 2.C.(6)(a) and 2.C.(6)(b) are accomplished before milling. 

(d) Position Milling Fixture 3302624-18F Left or Right (Figure 4) to wing. Using a proper router 

with micro depth adjustment (Ref: 185R105-002A), measure the depth to corner fitting 

nodes. Cross check using the transit. Verify that the milling operation will yield the node 

thickness requirements as defined by 398800 or 3356018 Engineering Drawing. Use 

router to mill each node.

(e) When replacing both joint fittings, continue the same procedure until all upper and lower 

nodes are milled to the same plane as the corner fittings. Always cross check optically 

with transit.

(f) Remove milling fixture.

(g) Ream wing mate holes to final size in accordance with Engineering Drawing 370500.

(h) Touch up finish the milled nodes with MIL-DTL-81706 per specification MIL-C-5541 in 

accordance with Engineering Drawing 398800 or 3356018.
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Revision 6, July 11, 2013 Page 11

(7) Final Installation steps

(a) Re-install lower nacelle, engines, outer wings, and any components removed to facilitate 

replacement of the wing joint fittings.

(b) Perform an Alignment and Symmetry Check and compare reading to those taken at the 

start of procedure.

(c) Perform necessary functional checks of disturbed systems and return aircraft to service.

D. RESTORE AIRCRAFT TO SERVICE

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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Page 12 Revision 6, July 11, 2013 (Reissue)

Center Wing With Removed Upper Rainbow Fittings

Figure 1
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Rainbow Fittings

Figure 2
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Page 14 Revision 6, July 11, 2013 (Reissue)

Locating Fixture P/N 3302624-16F Attached To Center Wing

Figure 3
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Milling Fixture For Replacement Of Upper And Lower Rainbow Fitting

Figure 4
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Page 16 Revision 6, July 11, 2013 (Reissue)

THIS PAGE INTENTIONALLY LEFT BLANK.
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Revision 6, July 11, 2013 (Reissue) Page 17

3. MATERIAL INFORMATION

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.

NEW PART 

NUMBER QUANTITY KEY WORD

OLD PART 

NUMBER

INSTRUCTIONS/ 

DISPOSITION

370517-11/-12 1 each Upper Surface Wing Joint Fitting (1)

398335-1/-2 1 each Upper Surface Wing Joint Fitting (2)

398335-3/-4 1 each Upper Surface Wing Joint Fitting (3)

370518-3/-4 1 each Lower Surface Wing Joint Fitting (1)

398827-1/-2 1 each Lower Surface Wing Joint Fitting (4)

398827-3/-4 1 each Lower Surface Wing Joint Fitting (5)

NOTE: 1. Lockheed Martin Serial Numbers 4299, 4300, 4302, 4303, 4314 through 4322, and 4324.

2. Lockheed Martin Serial Numbers 4323, 4325 through 4937, and Center Wing Replacement 

MEPs 04R, 07R, 07W, and 12Y. 

3. Lockheed Martin Serial Numbers 4301, 4938 and up. 

4. Lockheed Martin Serial Numbers 4325 through 4637, and Center Wing Replacement 

MEPs 04R, 07R, 07W, and 12Y

5. Lockheed Martin Serial Numbers 4301, 4638 and up.

_______#_______

File: I-2996R6

HERCULES Lockheed Martin Aeronautics Company

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APPENDIX A 382-57-82

December 7, 2004 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. 82-771

Revision 6, July 11, 2013 Page A1 of A4

NOTE: This appendix shows the intent of Work Card SP-176.

NDI CENTER WING UPPER RAINBOW FITTING ACCESS CUTOUTS, CWS 216 TO 219

1. Perform nondestructive inspection of the center wing upper surface wing joint (rainbow) fitting, left, and right, 

in access cutouts for wing attachment bolts at CWS 216 to CWS 219. (See Figure A1.)

NOTE: Both Primary and Back-up Procedures are to be performed.

2. DESCRIPTION. The upper surface wing joint (rainbow) fitting is fabricated from 7075-T6 aluminum and 

finished with a sulfuric acid anodize followed with a coating of integral fuel tank polyurethane. The upper 

surface skin panels are attached to the rainbow fitting in the general inspection area with steel fasteners. 

The thickness of the rainbow fitting tang tapers from approximately 0.25 to 0.37 inches in the inspection area. 

The inspection area is located at approximately CWS 216 to CWS 219 on the fore and aft sides of each 

access cutout for the eleven (11) center wing attach bolts, right, and left wings.

3. DEFECTS. Cyclic loading may cause fatigue cracks to begin in the attach bolt hole counterbore and spot 

face area or along the edges of the outboard tapered portion of the bolt access cutout in the panel attachment 

tang and propagate in a chordwise direction.

4. PRIMARY NDI PROCEDURE - EDDY CURRENT.

NOTE: For support data and locally manufactured items and acceptance/rejection criteria, refer to the 

Nondestructive Inspection (NDI) Procedures Manual Supplement.

A. NDI equipment:

(1) Eddy current inspection unit, Nortec 19e, or equivalent.

(2) Probe, shielded, right angle, 1/2-inch drop, VM Products P/N VM202RA-1/2, or equivalent.

(3) Probe, pencil, surface, 1/8-inch diameter, Mu Metal shielded, stainless steel body, VM Products

P/N VM200-3, or equivalent.

(4) Cable, 6 foot, Microdot connector, VM Products P/N VM99BM, or equivalent.

(5) Calibration Standard, aluminum, Lockheed Martin Aeronautics Company P/N PDL 457A as 

illustrated in Nondestructive Inspection (NDI) Procedures Manual Supplement Section 20-40-00 

or equivalent.

B. Preparation of airplane: Remove center wing upper surface Wing Joint Access cover on left and right 

wings in accordance with applicable maintenance instructions.

C. Access: Access to the upper wing surfaces may be accomplished using the Top Forward Emergency 

Exit or with appropriate maintenance stands. Use safety restraint harnesses or other available safety 

equipment when working on top of the wings.
HERCULES Lockheed Martin Aeronautics Company

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382-57-82 APPENDIX A

82-771 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. December 7, 2004

Page A2 Revision 6, July 11, 2013 (Reissue)

D. Preparation of part: Remove sealant, scaling paints, oil, and grease in the inspection area using the 

procedures detailed in the Nondestructive Inspection (NDI) Procedures Manual Supplement Section 

20-00-00.

E. Instrument settings/calibration: Set up and calibrate the eddy current instrument as specified in 

Nondestructive Inspection (NDI) Procedures Manual Supplement, Section 20-10-04 for surface scan of 

Aluminum.

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

F. Inspection:

(1) Inspect the upper wing joint fittings at each attach bolt cutout along the complete accessible edge 

of the cutout from the aft radius area to the forward radius area as illustrated in Figure 1. Use the 

surface probe to inspect along the accessible upper surface of the fitting tang along the edge of 

the cutout, starting at the edge of the wing panel overlap, proceeding outboard around the nose 

of the cutout, then inboard to the opposite wing panel overlap. Use the right angle probe to 

inspect the interior edge at the fore and aft cutout radius areas. Inspect eleven (11) cutouts on 

the upper surface rainbow fitting on each left and right wings. Use care when inspecting near 

steel fasteners in the inspection areas.

(2) A change in the CRT presentation as noted during calibration will indicate a probable crack in the 

part being inspected.

G. Mark and report suspected defects: Proceed to Backup NDI Procedure.

5. BACKUP NDI PROCEDURE - EDDY CURRENT.

NOTE: For support data and locally manufactured items and acceptance/rejection criteria, refer to the 

Nondestructive Inspection (NDI) Procedures Manual Supplement.

A. NDI equipment: Same as Primary NDI Procedure.

B. Preparation of airplane: Same as Primary NDI Procedure.

C. Access: Same as Primary NDI Procedure.

D. Preparation of part: Same as Primary NDI Procedure.
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APPENDIX A 382-57-82

December 7, 2004 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. 82-771

Revision 6, July 11, 2013 (Reissue) Page A3

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

NOTE: A fluorescent penetrant inspection of the suspect area may be performed, but should not be 

interpreted so as to rule out the possibility of a defect existing if no penetrant indication is visible. 

Penetrant inspection should therefore be considered for this application only as a possible aid in 

locating and measuring the defect.

E. Instrument settings/calibration: Set up and calibrate the eddy current instrument as specified in 

Nondestructive Inspection (NDI) Procedures Manual Supplement, Section 20-10-04 for surface scan of 

aluminum.

WARNING: PENETRANT INSPECTION MATERIALS CAN INTRODUCE POTENTIAL FIRE AND 

HEALTH HAZARDS. REFER TO SMP 515-C-NDI PROCEDURES MANUAL 

SUPPLEMENT SECTION 20-20-00 FOR SAFETY PRECAUTIONS.

F. Inspection: Repeat the Primary NDI Procedure (eddy current scans). Use one of the methods outlined 

below.

(1) Preferred Method: Different inspector using a different instrument calibrated in accordance with

Nondestructive Inspection (NDI) Procedures Manual Supplement Section 20-10-04.

(2) Alternate Method No.1: Different inspector using the same instrument re-calibrated in 

accordance with Nondestructive Inspection (NDI) Procedures Manual Supplement Section 20-10-

04.

(3) Alternate Method No.2: The same inspector, after a one hour delay, using the same instrument 

re-calibrated in accordance with Nondestructive Inspection (NDI) Procedures Manual Supplement 

Section 20-10-04.

G. Mark and report indicated defects. If defects are indicated, take appropriate corrective action. If no 

defects are indicated, proceed to System Securing.

6. SYSTEM SECURING. Restore finishes and sealants, reinstall removed components, remove equipment and 

supplies from the inspection area, and perform operational checkouts as required in accordance with

applicable maintenance instructions.
HERCULES Lockheed Martin Aeronautics Company

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382-57-82 APPENDIX A

82-771 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. December 7, 2004

Page A4 Revision 6, July 11, 2013

Figure A1. Upper Surface Wing Joint (Rainbow) Fitting, Attachment Bolt Access Cutouts (Sheet 1 of 2)

Figure A1. Upper Surface Wing Joint (Rainbow) Fitting, Attachment Bolt Access Cutouts (Sheet 2)
HERCULES Lockheed Martin Aeronautics Company

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APPENDIX B 382-57-82

December 7, 2004 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. 82-771

Revision 6, July 11, 2013 Page B1 of B4

NOTE: This appendix shows a partial intent of Work Card SP-257.

NDI OF CENTER WING LOWER SURFACE RAINBOW FITTING ACCESS CUTOUT, WS 216 TO 219

1. Perform nondestructive inspection of all nodes of the center wing lower surface rainbow fitting, both left and 

right side. Fatigue cracks may initiate in the rainbow fitting at the lower surface panel and stringer attachment 

fastener holes or in the attachment bolt counterbore and spot face areas. Cracks will propagate in the fitting 

in a fore-aft (chordwise) and/or vertical direction. (See Figure B1.) The most common location of cracking is 

from the outboard part of the bolt access cutout extending across the horizontal face of the node then up the 

vertical scalloped area between nodes.

The material within the inspection area is 7075-T6 aluminum.

NOTE: Both Primary and Back-up Procedures are to be performed.

CAUTION: THE SAFETY NOTES AND PRECAUTIONS OF THE HERCULES MAINTENANCE MANUAL AND 

NONDESTRUCTIVE INSPECTION (NDI) PROCEDURES MANUAL SUPPLEMENT MUST BE 

COMPLIED WITH THROUGHOUT THE WORK DETAILED IN THIS WORK CARD.

2. PRIMARY NDI PROCEDURE - EDDY CURRENT.

A. NDI equipment:

(1) Eddy Current Flaw Detector, Zetec P/N MIZ-20A, or equivalent.

(2) Probe, surface, right angle, 1/4-inch drop, VM Products P/N VM202RA-1/4, or equivalent.

(3) Probe, pencil, surface, 1/8-inch diameter, Mu Metal shielded, stainless steel body, VM Products

P/N VM200-3, or equivalent.

(4) Cable, 6-foot, Microdot connector, VM Products P/N VM99BM, or equivalent.

(5) Calibration standard, aluminum, Lockheed Martin Aeronautics Company P/N PDL 457A as 

illustrated in Nondestructive Inspection (NDI) Procedures Manual Supplement Section 20-40-00 

or equivalent.

CAUTION: ENSURE POWER IS ISOLATED FROM ALL SYSTEMS IN THE INSPECTION AREA. 

FAILURE TO ISOLATE POWER MAY CAUSE PERSONNEL INJURY AND AIRPLANE 

DAMAGE.

B. Preparation of airplane:

(1) Isolate power from all systems in the inspection area.

(2) Remove the lower surface wing joint access strip.

C. Access: Access to the center wing upper and lower surface is obtained with use of the appropriate 

maintenance stands.
HERCULES Lockheed Martin Aeronautics Company

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382-57-82 APPENDIX B

82-771 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. December 7, 2004

Page B2 Revision 6, July 11, 2013

D. Preparation of part: Remove sealant, scaling paints, oil, and grease in the inspection area using the 

procedures detailed in the Nondestructive Inspection (NDI) Procedures Manual Supplement

Section 20-00-00.

E. Instrument settings/calibration: Set up and calibrate the eddy current instrument as specified in 

Nondestructive Inspection (NDI) Procedures manual Supplement, Section 20-10-04 for eddy current 

surface scanning of aluminum.

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

F. Inspection:

(1) Scan the entire exposed exterior surface of the rainbow fitting including the exposed radius area 

in the wing joint between nodes. Scan in both an up and down direction as well as a forward and 

aft direction. (See Figure B1, View B.)

(2) Scan along the exposed edge of the rainbow fitting tang under the lower surface skin panel. 

Scan in both an inboard and outboard direction as well as a forward and aft direction. (See 

Figure B1, View C.)

(3) Lockheed Martin Aeronautics Company recommends two inspectors for this procedure: one to 

perform the surface scan and the other to monitor the display. Any signal, as noted when 

scanning notches during calibration, will indicate a probable crack in the part being inspected.

G. Mark and report suspected defects. Proceed to Backup NDI Procedure.

3. BACKUP NDI PROCEDURE - EDDY CURRENT.

A. NDI equipment: Same as the Primary NDI Procedure.

B. Preparation of airplane: Same as the Primary NDI Procedure.

C. Access: Same as the Primary NDI Procedure.

D. Preparation of part: Same as the Primary NDI Procedure.

E. Instrument settings/calibration: Same as the Primary NDI Procedure.

F. Inspection: In order to verify suspect defects repeat the Primary NDI Procedure using one of the 

methods outlined below.

(1) Preferred Method: Different inspector using different eddy current equipment.

NOTE: The eddy current instrument must be recalibrated before reinspection.

(2) Alternate Method No. 1: Different inspector using the same eddy current equipment.

(3) Alternate Method No. 2: The same inspector using the same eddy current equipment after a 

one-hour delay.
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APPENDIX B 382-57-82

December 7, 2004 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. 82-771

Revision 6, July 11, 2013 Page B3

G. Mark and report confirmed defects: Complete the Primary NDI Procedure and then go to System 

Securing.

4. SYSTEM SECURING. Restore finishes and sealants; remove equipment and supplies from the inspection 

area; reinstall removed components; and perform operational checkouts as required.
HERCULES Lockheed Martin Aeronautics Company

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382-57-82 APPENDIX B

82-771 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. December 7, 2004

Page B4 Revision 6, July 11, 2013

Figure B1. Inspection of Center Wing Lower Surface Rainbow Fitting (Sheet 1 of 2)

Figure B1. Inspection of Center Wing Lower Surface Rainbow Fitting (Sheet 2)
HERCULES Lockheed Martin Aeronautics Company

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APPENDIX C 382-57-82

April 25, 2008 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. 82-771

Revision 6, July 11, 2013 Page C1 of C7

NDI OF CENTER WING UPPER AND LOWER SURFACE PANELS, STRINGERS, SPLICE STRAPS AND 

SPLICE ANGLES WITH RAINBOW FITTING REMOVED 

1. The purpose of this inspection is to verify the fastener holes in the upper and lower surface skin panel, 

stringers, splice straps and splice angles that are common to the rainbow fittings are free of defects/damage 

prior to installing the new. After removal of the rainbow fitting and prior to installing the new rainbow fitting, 

perform the Primary Inspection procedure.

2. PRIMARY PROCEDURE. AUTOMATED BOLT HOLE EDDY CURRENT

A. NDI Equipment:

(1) Eddy current instrument - Zetec MIZ-21A or equivalent

(2) Mini probe drive - GE Inspection Technologies P/N 33A100 or equivalent

(3) Cable, MIZ-21 to mini probe drive - Zetec P/N 2100-03-04 or equivalent

(4) Probe, rotating hole, reflection type, 200 kHz to 2 MHz, 3/16”, 1/4”, and 5/16” diameter - GE 

Inspection Technologies P/N 620-546-156 or equivalent

(5) Calibration standard, aluminum - VM Products, Inc. P/N VM30889-C1A or equivalent (see

Figure C1)

B. 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.

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

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.
HERCULES Lockheed Martin Aeronautics Company

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382-57-82 APPENDIX C

82-771 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. April 25, 2008

Page C2 Revision 6, July 11, 2013

(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 calibration standard (P/N VM30889-C1A) 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 C2.

(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 C3.

(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 C3.

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. Perform ABHEC scan of all 

open holes in the upper and lower skin panels, stringers, attach angles and straps. 

(2) To confirm suspected damage, conduct a redundant ABHEC backup procedure in accordance 

with Paragraph F.
HERCULES Lockheed Martin Aeronautics Company

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APPENDIX C 382-57-82

April 25, 2008 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. 82-771

Revision 6, July 11, 2013 Page C3

F. Redundant Inspection (for confirmation only):

(1) Inspector Verification

(a) Wrong alignment

1 Reset and recalibrate the same equipment. The same inspector repeats the

inspection. If crack is confirmed, complete the verification outlined below.

(b) Verification

1 Preferred Method – Different inspector repeats the inspection using the same 

equipment, after resetting and recalibrating the equipment.

2 Alternate Method No. 1 – Inspector re-inspects the area with an appropriate 

alternate method.

G. Mark and Report Damage:

(1) Report any damage detected by this inspection procedure 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 SMP 583 for repair instructions. Contact 

Lockheed Martin Aeronautics Company if the damage exceeds the repair limits defined in the 

Structural Repair Manual:

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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382-57-82 APPENDIX C

82-771 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. April 25, 2008

Page C4 Revision 6, July 11, 2013

Figure C1 - General Purpose Eddy Current Calibration Standard 7075-T6 Aluminum
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APPENDIX C 382-57-82

April 25, 2008 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. 82-771

Revision 6, July 11, 2013 Page C5

Figure C2 - Typical X-Y Signal Response from 0.030” X 0.030” Notch
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382-57-82 APPENDIX C

82-771 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. April 25, 2008

Page C6 Revision 6, July 11, 2013

Figure C3 - Typical Time-based Signal Response from 0.030” X 0.030” Notch
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APPENDIX C 382-57-82

April 25, 2008 USE, COPYING AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. 82-771

Revision 6, July 11, 2013 Page C7

Figure C4 - Lift-off and Notch Signals