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.

December 16, 2013 382-57-95

Page 1 of 17

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

REPLACEMENT

NOTE: This Service Bulletin includes Appendix A.

1. PLANNING INFORMATION

A. EFFECTIVITY

This service bulletin is applicable to all Model 382, 382B, 382E, 382F, and 382G series FAA certificated 

Hercules aircraft having Outer Wing Serials 4542 or later, or all MEP replacement outer wings except the 

14Y Series (Part No. 388021-9/-10).

B. REASON

(1) Fatigue cracking of the outer wing upper and lower rainbow fittings on the durability test and on 

in-service aircraft indicates a requirement to perform inspections of the rainbow fittings. Analysis 

of in-service cracking has shown that these fittings are susceptible to Multiple Site Damage 

(MSD) and an inspection is required to ensure that cracking does not occur in the skin 

panel-to-fitting fastener holes, resulting in an unacceptable reduction in residual strength. The 

inspection intervals provided in this service bulletin will ensure that the probability of failure 

remains acceptably low until the rainbow fittings are replaced.

(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 have incorporated the LOV into their maintenance program by 

July 14, 2013 to comply with FAR §121.1115 or §129.115. This service bulletin incorporates 

maintenance actions required for the outer wing rainbow fittings to safeguard the aircraft against 

widespread fatigue damage up to the LOV.

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

accomplished on all commercial aircraft outer wings that have accumulated 30,000 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. Recurring inspection is recommended at 2,000 flight hours.

(4) Lockheed Martin Aeronautics Company recommends that both upper and lower rainbow fittings 

be replaced at 50,000 flight hours. This replacement coincides with center wing replacement per 

Service Bulletin 382-57-94. Replacement of the rainbow fittings will reset the flight hours to zero 

with respect to the inspection requirements identified in this Service Bulletin.

NOTE: For commercial operators of aircraft with outer wings that have had previous military usage, 

contact Lockheed Martin for adjusted compliance times.
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NOTE: The replacement times indicated in this service bulletin do not apply to military operators of 

382, 382B, 382E, 382F, and 382G aircraft. Contact Lockheed Martin for an Operational 

Usage Evaluation/Service Life Assessment to determine an appropriate replacement 

schedule.

C. DESCRIPTION

(1) This Service Bulletin contains instructions for inspecting outer wing upper and lower rainbow 

fittings using Eddy Current Surface Scan to detect cracks propagating from fasteners attaching 

the fittings to skin panels. Perform inspections in accordance with Paragraph 2.A. of this Service 

Bulletin.

(2) This Service Bulletin contains instructions for replacing upper and lower rainbow fittings on the 

outer wing. Prior to installation of new rainbow fittings, inspect all open fastener holes in mating 

structure using Automated Bolt Hole Eddy Current as defined in Appendix A of this Service 

Bulletin. Make necessary repairs and install new rainbow fittings in accordance with 

Paragraph 2.B. of this Service Bulletin.

D. APPROVAL

(1) The aircraft owner/operator will 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: 

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

(3) This Service Bulletin has been approved by the FAA as complying with applicable Federal 

Aviation Regulations.

E. MANPOWER

The work prescribed in this Service Bulletin has not been performed at the Lockheed Martin facility. 

Therefore, 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 customer 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

Primary ECSS Inspection 24 2 12 hrs

Removal and Installation of one fitting 515 6 285 hrs

Primary BHEC Inspection 24 2 12 hrs
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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.

F. MATERIAL - COST AND AVAILABILITY

(1) Parts/Materials listed in section 3 of this service bulletin are to be supplied by the aircraft 

owner/operator. Parts listed in section 3 of this service bulletin may also be purchased from 

Lockheed Martin, if desired. Parts bearing Lockheed Martin Aeronautics Company part numbers 

are considered proprietary and shall be purchased from Lockheed Martin Aeronautics Company 

unless methods of fabrication are shown in this publication. Inquiries concerning current prices, 

applicability, and availability of kits may be directed 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: (817) 655-9700

(2) Additional bulk materials, not included in the kit, will be supplied by the aircraft owner/operator.

G. TOOLING - PRICE AND AVAILABILITY

(1) For ECSS Inspections:

Eddy current inspection unit, Nortec 2000D/D+, or equivalent.

Probe, shielded, right angle, 1/2-inch drop, 50-500 kHz, Fischer/LEMO Triax Connector, Olympus 

MTF-905-60, or equivalent.

Probe, shielded, straight, 50-500 kHz, Fischer/LEMO Triax Connector, Olympus MTF-40, or 

equivalent.

Cable, 6 foot, Fischer/LEMO Triax to 16-pin LEMO connector, Olympus P/N 9122244, or 

equivalent.

Calibration Standard, aluminum, VM Products, Inc. P/N VM30889-C1A or P/N VM30889-C1A/AF, 

or equivalent.

(2) For BHEC Inspections defined in Appendix A:

Eddy current instrument, Nortec 2000D/D+, or equivalent

Scanner, high-speed, MiniMite, 4-pin Fischer, Olympus P/N 9744738, or equivalent.
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Probe, bolt hole, shielded reflection (100 kHz–2 MHz), 3/16-inch diameter (.156-.187), 4-pin 

Fischer, Olympus SPO-5965, P/N 9230061, or equivalent.

Probe, bolt hole, shielded reflection (100 kHz–2 MHz), 1/4-inch diameter (.218-.250), 4-pin 

Fischer, Olympus SPO-5965, P/N 9219980, or equivalent.

Probe, bolt hole, shielded reflection (100 kHz–2 MHz), 5/16-inch diameter (.281-.312), 4-pin 

Fischer, Olympus SPO-5965, P/N 9219982, or equivalent.

Probe, bolt hole, shielded reflection (100 kHz–2 MHz), 3/8-inch diameter (.312-.375), 4-pin 

Fischer, Olympus SPO-5965, P/N 9219982, or equivalent.

Cable, scanner, high-speed, 16-pin Lemo, Olympus P/N 9122090, or equivalent.

Calibration Standard, aluminum, VM Products, Inc. P/N VM30889-C1A or P/N VM30889 C1A/AF, 

or equivalent.

(3) For Removal and Installation of Rainbow Fitting:

3307043-1/2-16F Fixture to locate the new joint fitting.

3307043-1/2-18F Fixture to mill the nodes of the new joint fitting.

185R105-002A Router, or equivalent, for milling the new joint fitting.

446E101-015C Cutter, or equivalent, for above router.

730M200-004A Depth Micrometer or equivalent.

Jig Transit (with Optical micrometer) or equivalent.

H. WEIGHT AND BALANCE

None.

I. REFERENCES

SMP 515-C-NDI, Nondestructive Inspection (NDI) Procedures Manual Supplement

SMP 581, Hercules Maintenance Manual

SMP 583, Structural Repair Manual

Hercules Airfreighter Progressive Inspection Procedures

Service Bulletin 382-57-94/ Wings - Replacement of Center Wing

The following Lockheed Martin drawings may be needed for reference:

DWG NO. DESCRIPTION OUTER WING EFFECTIVITY*

3308150 Outer Wing Assy 4542 thru 4960

3319669 Outer Wing Assy 4992 thru 5320
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DWG NO. DESCRIPTION OUTER WING EFFECTIVITY*

3308152 Box Structure, Outer Wing 

Assy

4542 thru 4960

3319672 Box Structure, Outer Wing 

Assy

4992 thru 5320

3308153 LWR Surface Instl 4542 thru 4960

3325532 LWR Surface Instl 4992 thru 5320

3308154 UPR Surface Assy 4542 thru 4960

3325535 UPR Surface Assy 4992 thru 5320

3308155 UPR Surface Instl 4542 thru 4960

3325531 UPR Surface Instl 4992 thru 5320

3308156 LWR Surface Assy 4542 thru 4960

3325536 LWR Surface Assy 4992 thru 5320

370500 Wing Joint Basic Dimension All

* Outer wing serial number is indicated on the outer wing identification placard located on 

the rear beam web near OWS180.

J. OTHER PUBLICATIONS AFFECTED

Hercules Airfreighter Progressive Inspection Procedures
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2. ACCOMPLISHMENT INSTRUCTIONS

A. INITIAL AND RECURRING INSPECTIONS

This service bulletin defines the initial inspection for cracks in outer wing upper and lower rainbow 

fittings on commercial aircraft at 30,000 flight hours and a recurring inspection at intervals of 2,000 flight 

hours. Perform nondestructive inspection of the outer wing upper and lower rainbow fitting to skin panel 

attachments, left and right, as shown in Figure 1 and Figure 2. The upper and lower inspection areas 

are located at OWS 3 to OWS 7 between the forward and aft corner fittings and include 2 inboard

chord-wise fastener rows containing approximately 180 fasteners.

The wing joint rainbow fittings are fabricated from 7075-T73511 aluminum. The rainbow fitting tangs 

taper in thickness from approximately 0.35 to 0.10 inches in the inspection areas. The upper and lower 

surface skin panels are attached to the rainbow fittings in the inspection areas with steel fasteners. 

Cyclic loading may cause fatigue cracks to begin in the rainbow fitting at the panel attachment fasteners 

and propagate in a chord-wise direction.

These inspections shall be performed as follows:

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

the SMP 515-C-NDI Nondestructive Inspection Procedures Manual Supplement.

(1) NDI equipment: Required equipment is listed in Paragraph 1.G.(1).

(2) Access: Access to the upper and lower wing surfaces may be accomplished using appropriate 

maintenance stands. Use safety restraint harnesses or other available safety equipment when 

working on top of the wings.

(3) Preparation of parts: Remove sealant, scaling paint, oil, and grease in the inspection areas using 

the procedures detailed in the SMP 515-C-NDI Nondestructive Inspection Procedures Manual 

Supplement, Section 20-00-00.

(4) Instrument settings/calibration: Set up and calibrate the eddy current instrument as specified in 

SMP 515-C-NDI Nondestructive Inspection Procedures Manual Supplement, Section 20-10-04 for 

eddy current scanning of aluminum. The calibration standard is specified in Paragraph 1.G.(1). 

See Figure 3 for the expected signal responses after calibration of the surface scanning probes 

noted in this inspection.

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

(5) Inspection - Upper Surface:

(a) Scan around all fasteners attaching the upper rainbow fitting to the wing skin panels as 

illustrated in Figure 1. Use the raised fastener heads as a guide when inspecting around 

the fasteners in the inspection area. Fatigue cracking is expected to propagate in a 

chord-wise (fore-aft) direction.

(b) An instrument screen presentation, as noted during calibration, will indicate a suspected 

defect in the part being inspected.
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(6) Inspection - Lower Surface:

(a) Scan around all fasteners attaching the lower rainbow fitting to the wing skin panels as 

illustrated in Figure 2. Use the raised fastener heads as a guide when inspecting around 

the fasteners in the inspection area. Fatigue cracking is expected to propagate in a 

chordwise (fore-aft) direction.

(b) An instrument screen presentation, as noted during calibration, will indicate a suspected 

defect in the part being inspected.

(7) Mark and report suspected defects. If defects are suspected, proceed to the Backup NDI 

Procedure. If no defects are suspected, complete the Primary NDI Procedure and proceed to 

System Securing.

(8) BACKUP NDI PROCEDURE

(a) To confirm suspected defects, remove the fastener and perform an Automated Bolt Hole 

Eddy Current inspection of the open hole in accordance with Appendix A.

(b) Report any damage detected by this inspection procedure to Lockheed Martin Aeronautics 

Company Enterprise Operations Center in accordance with the note at the end of the 

accomplishment instructions. Provide the following information for all damage detected:

1 Aircraft Serial Number.

2 Outer Wing Flight Hours (or Aircraft Flight Hours if outer wing hours are unknown).

3 Part number and description.

4 Location (Wing Station, Fuselage Station) and specific fastener hole location.

5 Length, depth, and orientation of crack.

NOTE: Prior to reporting any detected damage to Lockheed Martin Aeronautics Company, it is 

recommended that a borescope inspection (side view lens) of the hole bore be performed to 

determine if the reported damage is due to fatigue cracking, embedded metal at faying 

surfaces or mechanical damage (gouging, reamer/drill marks, elongation) within the hole 

bore.

(9) 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.

B. REPLACEMENT OF WING JOINT FITTINGS

(1) This Service Bulletin recommends replacement of the outer wing upper and lower rainbow fittings 

in accordance with Hercules Maintenance Manual on commercial aircraft outer wings having 

accumulated more than 50,000 total flight hours.
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(2) Preparation for Replacement

(a) Perform Alignment and Symmetry on aircraft in accordance with SMP 583 Structural 

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

(b) Remove outer wings using instructions in SMP 581 Fig 57-10-03 and place wings on 

cradle. Secure the cradle with mechanical locks to avoid movement during Step 2.B.(2)(c). 

Shoring is required if cradle cannot be mechanically locked.

(c) Conduct a survey of the OWS 0 outer wing joint plane using a suitable optical transit. 

Record any disparity in planarity between all nodes. Reference drawings 3308150 and 

3319669. Contact Lockheed Martin if the four corner fittings are not co-planar within 

drawing requirements.

(d) Remove all components such as plumbing and wiring necessary to facilitate installation of 

replacement rainbow fittings in area between OWS 0 and OWS 7.

(3) Upper Rainbow Fitting Replacement

CAUTION: REPLACE UPPER OR LOWER RAINBOW FITTINGS ONE AT A TIME. UNDER NO 

CIRCUMSTANCES SHOULD THE RAINBOW FITTINGS AND SPAR CAP CORNER 

FITTINGS BE REMOVED AT THE SAME TIME. THE CORNER FITTINGS ARE USED 

AS A REFERENCE IN THE MACHINING OF THE RAINBOW FITTINGS AND 

SHOULD NOT BE REMOVED UNTIL THE MACHINING OF THE RAINBOW FITTINGS 

HAS BEEN COMPLETED.

CAUTION: EXERCISE CAUTION WHEN INSTALLING OR REMOVING THE NEW RAINBOW

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

THIS PROCESS TO PREVENT CRACKING THE FITTING AND OTHER WING 

COMPONENTS.

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

sealant. Use caution to avoid damage to wing structure and attach holes.

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

angles, and rib web of sealant and other particles.

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

(d) Perform Automated Bolt Hole Eddy Current inspection of all open fastener holes in skins, 

stiffeners, webs, and angles while fitting is removed in accordance with Appendix A of this 

Service Bulletin. If confirmed cracks are found, repair in accordance with Hercules 

Structural Repair Manual SMP 583 or contact Lockheed Martin Aeronautics Company 

Enterprise Operations Center in accordance with the note at the end of the 

accomplishment instructions.

(e) Place the new rainbow fitting in the wing. Some amount of force may be required to 

properly align fitting. Reference Drawing 3308154 or 3325535 Upper Surface Assembly.
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(f) Install 3307043-1/2-16F 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 rainbow fitting nodes to protrude for final node milling to assure joint 

planarity. All four shims must be the same thickness. Reference Drawing 3308152 or 

3319672 for wing joint node thickness requirements. All nodes of the rainbow fitting shall 

be tight against fixture before proceeding.

(g) Check all fitting-to-wing skin panel attaching fastener holes for proper edge distance (1.5 x 

Final Hole Diameter minimum.)

(h) Visually check the new rainbow fitting for proper placement/alignment prior to drilling 

operations.

(i) Transfer all fastener holes from outer wing mating structure to new rainbow fitting in 

accordance with SMP 583 Structural Repair Manual, Chapter 51-70.

(j) Remove the locating fixture and rainbow fitting from wing. Clean fitting and the 

surrounding wing area for debris and burrs.

(k) Reposition the new rainbow fitting in the wing, picking up previously drilled holes. Fay 

surface seal in accordance with SMP 583 Structural Repair Manual.

(l) Wet install oversize fasteners of appropriate type in accordance with SMP 583 Structural 

Repair Manual, Chapter 51-70.

NOTE: Perform Step 2.B.(4) Lower Rainbow Fitting Replacement before performing Step 

2.B.(5) Fitting Node Milling Procedure.

(4) Lower Rainbow Fitting Replacement

CAUTION: EXERCISE CAUTION WHEN INSTALLING OR REMOVING THE NEW RAINBOW

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

THIS PROCESS TO PREVENT CRACKING THE FITTING AND OTHER WING 

COMPONENTS.

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

sealant. Use caution as to not damage wing structure and attach holes.

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

angles, and rib web of sealant and other particles.

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

(d) Perform Automated Bolt Hole Eddy Current inspection of all open fastener holes in mating 

structure while fitting is removed in accordance with Appendix A of this service bulletin. If 

confirmed cracks are found, repair in accordance with Hercules Structural Repair Manual 

SMP 583 or contact Lockheed Martin Aeronautics Company Enterprise Operations Center 

in accordance with the note at the end of the accomplishment instructions.

(e) Place the new rainbow fitting in the wing. Some amount of force may be required to 

properly align fitting. Reference Drawing 3308156 or 3325536 Lower Surface Assembly

for proper fit and installation.
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(f) Install P/N 3307043-1/2-16F 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 rainbow fitting nodes to protrude for final node milling to assure 

joint planarity. All four shims must be the same thickness. Reference Drawing 3308152 or 

3319672 for wing joint node thickness requirements. All nodes of the rainbow fitting shall 

be tight against fixture before proceeding.

(g) Check all fitting-to-wing skin panel attaching fastener holes for proper edge distance (1.5 x 

Final Hole Diameter minimum)

(h) Visually check the new rainbow fitting for proper placement/alignment prior to drilling 

operations.

(i) Transfer all fastener holes from outer wing mating structure to new rainbow fitting in 

accordance with SMP 583 Structural Repair Manual, Chapter 51-70.

(j) Remove the locating fixture and rainbow fitting from wing. Clean components and the 

surrounding wing area for debris and burrs.

(k) Reposition the new rainbow fitting in the wing, picking up previously drilled holes. Fay 

surface seal in accordance with SMP 583 Structural Repair Manual.

(l) Wet-install oversize fasteners of appropriate type in accordance with SMP 583 Structural 

Repair Manual, Chapter 51-70.

NOTE: Continue to Step 2.B.(5) Fitting Node Milling Procedure only after completing Steps 

2.B.(3) and 2.B.(4).

(5) Fitting Node Milling Procedure

(a) This step is required for milling procedures: Support the outer wing using instructions in 

SMP 581 Fig 57-10-03. Secure the cradle with mechanical locks to avoid movement 

during machining. Shoring is required if cradle cannot be mechanically locked.

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

Adjust the cradle 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 rainbow fitting node face protrusion. Node thickness requirements are defined 

by engineering drawing 3308152 and 3319672.

(c) Ensure that Steps 2.(5)(a) and 2.(5)(b) are completed before milling.

(d) Position milling fixture 3307043-1/2-18F Left or Right to the outer wing. Using a proper 

router with micro depth adjustment as specified in paragraph 1.G.(3), 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 Drawings 3308152 or 3319672. Use 

router to mill each node.

(e) Continue the same procedure until all upper and lower rainbow fitting nodes are milled to 

the same plane as the corner fittings. Always cross check optically with transit.
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(f) Remove milling fixture.

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

edges of wing mate holes in accordance with Drawing 3308152 or 3319672.

(h) Touch-up finish the milled nodes with Alodine and one coat of AMS-C-27725 Polyurethane, 

or equivalent in accordance with Drawings 3308152 or 3319672.

(6) Final Installation

(a) Re-install any components removed to facilitate replacement of the rainbow fittings.

(b) Re-install outer wings per SMP 581, Figure 57-10-03.

(c) Perform an Alignment and Symmetry Check and compare readings to those taken at the 

start of procedure.

C. RESTORE AIRCRAFT TO SERVICE

Perform necessary functional checks of interrupted systems per SMP 581, Figure 57-10-03, Step 39 

and return aircraft to service.

NOTE: If assistance 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

Dept. 3E1M, Zone 0591

Marietta, GA 30063, USA
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FWD

OTBD

VIEW LOOKING DOWN ON LEFT WING. 

RIGHT WING OPPOSITE. 

UPPER

RAINBOW 

FITTING

UPPER SKIN PANEL

UPPER

RAINBOW 

FITTING

ECSS AROUND EACH FASTENER IN 

THE TWO (2) INBOARD ROWS 

ATTACHING RAINBOW FITTING TO 

SKIN ON UPPER EXTERIOR 

SURFACE OF EACH OUTER WING.

A

SECTION B-B

ROTATED 90 DEG C W

Eddy Current Surface Scan Inspection of Outer Wing Upper Rainbow Fitting

Figure 1
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FWD

OTBD

VIEW LOOKING UP ON RIGHT WING. 

LEFT WING OPPOSITE. 

LOWER

RAINBOW 

FITTING

LOWER SKIN PANEL

LOWER

RAINBOW 

FITTING

A

SECTION B-B

ROTATED 90 DEG CW

ECSS AROUND EACH FASTENER IN 

THE TWO (2) INBOARD ROWS 

ATTACHING RAINBOW FITTING 

TO SKIN ON LOWER EXTERIOR 

SURFACE OF EACH OUTER WING.

FUS STA

517.00

OWS

0.00

Eddy Current Surface Scan Inspection of Outer Wing Lower Rainbow Fitting

Figure 2
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Calibrated Lift-Off and EDM Notch Responses for Eddy Current Surface Scan

Figure 3
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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

QTY. PER

WING KEY WORD

OLD PART 

NUMBER

INSTRUCTIONS/ 

DISPOSITION

3308183-9/-10 1 each Upper Surface Rainbow

Fitting

3308183-3/-4 Note 1

3308183-9/-10 1 each Upper Surface Rainbow 

Fitting

3308183-9/-10 Note 2

3308182-9/-10 1 each Lower Surface Rainbow 

Fitting

3308182-3/-4 Note 1

3308182-9/-10 1 each Lower Surface Rainbow 

Fitting

3308182-9/-10 Note 2

NOTE: 1. Applies to outer wings originally installed on Serials* 4542 thru 4765.

2. Applies to outer wings originally installed on Serials* 4766 thru 5320.

* Outer wing serial number is indicated on the outer wing identification placard located on 

the rear beam web near OWS180.

_______#______ 

File: I-3684

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Page A1 of A7

APPENDIX A

AUTOMATED BOLT HOLE EDDY CURRENT INSPECTION PROCEDURE

1. PRIMARY NDI PROCEDURE - AUTOMATED BOLT HOLE 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 instrument, Nortec 2000D/D+, or equivalent.

(2) Scanner, high-speed, MiniMite, 4-pin Fischer, Olympus P/N 9744738, or equivalent.

(3) Probe, bolt hole, shielded reflection (100 kHz–2 MHz), 3/16-inch diameter (0.156-0.187), 4-pin 

Fischer, Olympus SPO-5965, P/N 9230061, or equivalent.

(4) Probe, bolt hole, shielded reflection (100 kHz–2 MHz), 1/4-inch diameter (0.218-0.250), 4-pin 

Fischer, Olympus SPO-5965, P/N 9219980, or equivalent.

(5) Probe, bolt hole, shielded reflection (100 kHz–2 MHz), 5/16-inch diameter (0.281-0.312), 4-pin 

Fischer, Olympus SPO-5965, P/N 9219982, or equivalent.

(6) Probe, bolt hole, shielded reflection (100 kHz–2 MHz), 3/8-inch diameter (0.312-0.375), 4-pin 

Fischer, Olympus SPO-5965, P/N 9219982, or equivalent.

(7) Cable, scanner, high-speed, 16-pin Lemo, Olympus P/N 9122090, or equivalent.

(8) Calibration standard, aluminum - VM Products, Inc. P/N VM30889-C1A or P/N VM30889-C1A/AF,

or equivalent.

B. Preparation of Part: Remove sealant from the fastener holes with a nylon bristled brush of the 

appropriate diameter and an approved alcohol or solvent. Refer to the procedures detailed in the 

SMP 515-C-NDI Nondestructive Inspection Procedures Manual Supplement, Section 20-00-00 for 

cleaning of the holes to allow for acceptable probe contact with the part.

C. Equipment Calibration:

NOTE: Allow the instrument to warm-up for a period of 10-15 minutes prior to performing the 

inspection to minimize drifting of the signal.

(1) Connect the scanner, cable and the appropriate diameter probe to the eddy current instrument. 

Turn on the instrument and allow it to reach operating temperatures.
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(2) Adjust the initial instrument settings on the equipment to the following:

MAIN MENU

Frequency 1 (FREQ) 500 kHz (see Note #1)

Frequency 2 (FREQ) Off

Horizontal Gain (H-GAIN) 55 dB

Vertical Gain (V-GAIN) 55 dB

Phase Angle (ANGLE) 0°

FILTER MENU

Low Pass Filter (LP FILTER) See Note #2

High Pass Filter (HP FILTER) See Note #2

Continuous Null (CONT) OFF

DISPLAY MENU

Sweep Grid (SWEEP) OFF

Vertical Screen Position (V-POS) 50%

Horizontal Screen Position (H-POS) 50%

Persistence (PERSIS) OFF

Display Erase Rate (DIS ERASE) 0.2 sec

Grid Display (GRATICLE) ON

Focal Spot Shape (DOT/BOX) DOT

SETUP MENU

Frequency (1) SINGLE

Probe Drive (4) HIGH

Scanner Rotation Rate (RPM) 1300

Sync Angle (SYNC ANG) 0

NOTES:

1. The frequency may be adjusted within the 200-500 kHz range to maintain an improved signal 

response. Higher frequencies will result in greater sensitivity to surface defects; whereas, 

lower frequencies will result in reduce noise levels and better resolution of sub-surface 

defects.

2. When required, utilize the noted low pass and high pass filter settings for the following probe 

diameters:

1/8ʺ-7/32ʺ D. (0.156ʺ-0.219ʺ D.), LPF of 500 Hz, HPF of 150 Hz

7/32ʺ-5/16ʺ D. (0.219ʺ-0.312ʺ D.), LPF of 500 Hz, HPF of 200 Hz

5/16ʺ-7/16ʺ D. (0.312ʺ-0.437ʺ D.), LPF of 700 Hz, HPF of 300 Hz

(3) Turn on the scanner. With the probe placed in the air, press the NULL soft key on the instrument 

and wait for nulling to complete. The null point on the impedance plane should be located at the 

screen center at 50% horizontal screen width (HSW) and 50% vertical screen height (VSH).

(4) Place the probe on the calibration standard, normal to the surface and away from any edges, 

holes, or EDM notches as illustrated in Figure A1. Generate an initial lift-off response and verify 

the initial lift-off has a narrow response as illustrated in Figure A1. If a wide looped lift-off is 

noted, press the V-GAIN soft key and reduce the vertical gain until a flat line response is 

achieved.
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(5) If the lift-off response is not horizontal, press the ANGLE soft key and adjust the phase angle until 

the lift-off response is as near horizontal as possible. See Figure A1 for an illustration of the 

expected phase adjusted lift-off response.

(6) Insert the probe into the appropriate diameter hole in the calibration standard adjacent to the 

0.030” X 0.030” notch located at the Layer 1-2 interface (on calibration standard VM30889-C1A or 

–C1A/AF) or adjacent to the 0.030ʺx0.030ʺ notch on an equivalent standard.

(7) Maximize the notch response on the impedance plane screen, press the H-GAIN soft key and 

adjust the horizontal notch response to 50% full screen width (FSW). Press the V-GAIN soft key 

and adjust the vertical notch response to 50% full screen height (FSH). Confirm the notch 

response has a 45 degree angle and orientation from the upper left corner to the lower right 

corner of the impedance plane screen.

(8) Press the GAIN soft key and adjust the notch response until an 80% FSW and 80% FSH 

response is achieved. The notch response should have a symmetric "Figure 8" pattern split 

above and below the lift-off line/null point located at the 50% VSH location. The lift-off noise, 

resulting from probe rotation or "chattering" in the hole should be maintained below 40% FSW. 

See Figure A2 for the expected calibrated notch response and the acceptable limits for lift-off 

noise.

NOTE: If a symmetric notch response cannot be achieved, slight adjustments (± 100 Hz) may be 

made to the low-pass and hi-pass filter settings to improve symmetry of the notch response.

(9) The instrument is now properly calibrated for the impedance plane screen. No additional 

changes should be made to the phase setting from this point forward, unless a new calibration is 

being performed. Any additional changes to the phase angle will result in a change in lift-off from 

the horizontal orientation earlier established.

(10) Press the DISPLAY soft key, then press the SWEEP soft key twice to enter SWEEP EXTRN

mode.

NOTE: Instrument adjustment made at this time will only affect the sweep screen notch response and 

will have no effect on the impedance plane screen calibration.

(11) With the probe placed in the air, press the NULL soft key on the instrument, and wait for nulling to 

complete. The null baseline response on the sweep screen should be located at the center of the 

instrument screen at the 50% VSH position.

(12) Turn the scanner on and reinsert the probe into the same hole in the calibration standard. Locate 

the 0.030” x 0.030” EDM notch and maximize the notch response on the sweep screen.

(13) Press the GAIN soft key and adjust the notch response until an 80% FSH response is achieved. 

The notch response should be symmetric above and below the null baseline and the noise level 

of the baseline should be below 20% FSH. See Figure A2 for the expected calibrated notch 

response and the acceptable limits for baseline noise.

(14) The instrument is now calibrated for completion of the inspection requirements for the fastener 

holes within the diameter range of the probe being used.
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D. Inspection:

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

(1) Ensure instrument is calibrated as in accordance with Paragraph 1.C. Perform ABHEC scan of all 

open holes through all structural layers.

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

with Paragraph 2.

E. Mark and report suspected defects. If defects are suspected, proceed to the Backup NDI Procedure. If 

no defects are suspected, complete the Primary NDI Procedure.

2. BACKUP NDI PROCEDURE - REDUNDANT AUTOMATED BOLT HOLE 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. Preparation of part: Re-clean and/or hone the hole bore to remove any edge burrs, embedded metal at 

faying surfaces or mechanical damage that may have resulted in defect indications noted during the 

Primary NDI Procedure.

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

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

Primary NDI Procedure.

E. Inspection: Repeat the Primary NDI Procedure
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3. MARK AND REPORT DAMAGE:

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. Outer Wing Flight Hours (or Aircraft Flight Hours if outer wing hours are unknown).

C. Part number and description.

D. Location (Wing Station, Fuselage Station) and specific fastener hole location.

E. Length, depth, and orientation of crack.

NOTE: Prior to reporting any detected damage to Lockheed Martin Aeronautics Company, it is 

recommended that a borescope inspection (side view lens) of the hole bores be performed to 

determine if the reported damage is due to fatigue cracking, embedded metal at faying 

surfaces, or mechanical damage (gouging, reamer/drill marks, elongation) within the hole 

bore.
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Typical Automated Bolt Hole Eddy Current Lift-Off Signal Responses

Figure A1
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Typical Impedance Plane and Sweep Display Signal Responses From 0.030" x 0.030" Notch

Figure A2