MODEL L-382/C-130

SMP 515 C INSPECTION PROCEDURES

SYSTEM WINGS CHAPTER 57

ZONE

REV DATE

500/600

14 DEC 08

CARD NO. SP-123 1 OF 9

NDI OUTER WING LOWER FORWARD BEAM CAP OWS 72 AND 90 WARNING:COMPLY WITH SFAR 88 CDCCL REQUIREMENTS, REFER TO SP-322 AND SP-323 1.

Perform nondestructive inspection of the left and right outer wing front beam lower cap and web at OWS 72 and OWS 90.

2.

DESCRIPTION. The front beam lower cap is fabricated from 7075-T6 or 7075-T73 aluminum and machined. Between OWS 72 and OWS 90 the cap is located between the pylon attach fitting and front beam web on the forward side, and the cap reinforcing angle and backup fitting attaching to the rib assembly on the aft side. When Service Bulletin 382-187 or 82-371 is incorporated, drawing 3312416 replaces the aluminum front beam web in the inspection area; the new web is fabricated from 0.080 inch thick 301 stainless steel, and passivated. All components in the inspection areas are fabricated from aluminum. Fasteners attaching the front beam aluminum web to the lower cap immediately adjacent to the pylon fitting were, on aircraft Serials LAC 3609 through 4347, of the countersunk type with the aluminum web being countersunk for fastener installation. Some airplanes had pylon fittings installed which partially overlapped the countersunk fasteners. Modifications were made to some of these early aircraft which stepped up the fastener hole sizes to remove the countersink in the web and installed a button head fastener. Aircraft Serials LAC 4348 and Up removed countersunk fasteners and replaced them with button heads. Aircraft incorporating the stainless steel web in this area per Service Bulletin 382-187 or 82-371 had the web installed with button head fasteners. The fitting and web are joined to the cap with a fay seal of fuel tank sealing compound. All aluminum parts are sulfuric acid anodized followed by a coating of polyurethane for integral tanks.

3.

DEFECTS. Cyclic loading may cause fatigue cracks to begin in the lower cap in the common attach holes of the lower inboard and outboard corner attach fasten-

THIS MATERIAL CONTAINS PROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICAL SYSTEMS. USE COPYING AND/OR DISCLOSURE WITHOUTH WRITTEN AUTHORIZATION IS PROHIBITED.

MODEL L-382/C-130

SMP 515 C INSPECTION PROCEDURES

SYSTEM WINGS CHAPTER 57

ZONE

REV DATE

500/600

14 DEC 08

CARD NO. SP-123 2 OF 9

ers of the pylon attach fitting and cap. Cracks will propagate downward into the horizontal legs of the cap, and upward to the upper edge of the cap vertical leg. Fatigue cracks may initiate in the countersunk fastener holes located in the aluminum web immediately adjacent to each lower corner of the pylon fitting. Cracks will propogate in approximately a vertical direction in the web. 4.

PRIMARY NDE PROCEDURE NO. 1 - EDDY CURRENT. A.

NDE equipment: (3) Crack Detector, Magnaflux, P/N ED-520, or equivalent. (4) Probe, bolt hole, 3/16-inch diameter, V.M. Products, P/N VM101B-3/16, or equivalent. (5) Cable, 6 foot, Microdot/BNC, Mastercraft Enterprises, Inc. P/N HMT-7-41-BIN, or equivalent. (6) Calibration standard, aluminum, as provided with Magnaflux ED-520, or Lockheed-Georgia Co. P/N PDL 457A, or equivalent.

B.

Preparation of airplane:

WARNING: ENSURE THAT POWER IS ISOLATED FROM ALL SYSTEMS IN THE INSPECTION AREA. FAILURE TO COMPLY MAY RESULT IN SERIOUS INJURY TO PERSONNEL. (3) Isolate power from all systems in the inspection area in accordance with applicable maintenance manuals. WARNING: ENSURE THAT ALL APPLICABLE SAFETY PRECAUTIONS PERTAINING TO WORK IN FUEL /FUME AREAS SPECIFIED IN THE APPLICABLE MAINTENANCE MANUAL ARE STRICTLY OBSESSES WHILE WORKING IN THE FUEL KTANKS AND DRY BAY AREAS. PERSONEL SHALL WEAR NON-SPARKING PROTECTIVE CLOTHING.

THIS MATERIAL CONTAINS PROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICAL SYSTEMS. USE COPYING AND/OR DISCLOSURE WITHOUTH WRITTEN AUTHORIZATION IS PROHIBITED.

MODEL L-382/C-130

SMP 515 C INSPECTION PROCEDURES

SYSTEM WINGS CHAPTER 57

ZONE

REV DATE

500/600

14 DEC 08

CARD NO. SP-123 3 OF 9

ENTRY INTO THE FUEL TANKS AND DRY BAY AREAS FOR DEPUDDLING MUST NOT BE MADE UNTIL THE AREAS HAVE BEEN PURGED TO THE FIRE-SAFE 20 PERCENT LOWER EXPLOSURE LIMIT (LEL), AS DETERMINED USING FUEL VAPOR DETECTION AND MEASURING EQUIPMENT. FUEL FACEPIECE RESPIRATOR MUST BE WORN UNTIL EACH AREA HAS BEEN PURGED TO THE HEALTHSAFE 0.0 TO 1.5 PERCENT LEL AND 19.5 PERCENT OXYGEN CONTENT. FAILURE TO COMPLY MAY RESULT IN SERIOUS INJURY OR DEATH TO PERSONNEL AND DAMAGE TO THE AIRCRAFT. (4) Drain and purge the inboard fuel tanks to provide a fuel and fume free area within 0 and 1.5 percent of the lower explosive limit. All personnel are to wear non-sparking protective clothing while working in an area where fuel/fumes have been present. (5) Remove the section of leading edge assembly between OWS 0 and OWS 158, L/R, in accordance with applicable maintenance manuals. C. Access: Use appropriate maintenance platforms for access to the front beam area. D. Preparation of part: Locate and mark the most inboard and most outboard fasteners (total of four at each pylon fitting) attaching the pylon fitting to the lower front beam cap and web. Remove the fasteners at both left and right outer wings per applicable Structural Repair Manual. Thoroughly clean the fastener holes using a stiff nylon (not metal) bristle brush wet with Federal Specification 0-T-620, Type I, Trichloroethane, or commercial equivalent. E.

Instrument settings/calibration: Set up and calibrate instrument as specified in SMP 515-C, Work Card SP-76, Appendix A, for bolt hole scanning of aluminum.

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

THIS MATERIAL CONTAINS PROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICAL SYSTEMS. USE COPYING AND/OR DISCLOSURE WITHOUTH WRITTEN AUTHORIZATION IS PROHIBITED.

MODEL L-382/C-130

SMP 515 C INSPECTION PROCEDURES

SYSTEM WINGS CHAPTER 57

ZONE

REV DATE

500/600

14 DEC 08

CARD NO. SP-123 4 OF 9

NOTE:

5.

If Service Bulletin 382-187 or 82-371 has been incorporated, the front beam web is 0.080 thick stainless steel. The inspector should check the web immediately adjacent to the inspection area to determine whether the Service Bulletin has been incorporated; use the bolt hole probe, calibrated for aluminum, and watch for full scale meter deflection when a steel web is present. Where a stainless web has been installed no inspection of the front beam cap is required. F. Inspection: Perform .eddy current bolt hole inspection of the fastener holes through each layer of material as illustrated when no stainless steel front beam web is installed. Refer to SMP 515-C, Work Card SP-76, Appendix A, for bolt hole scanning techniques. A sharp meter deflection as noted during calibration will indicate a probable crack in the part being inspected. G. Mark and report suspected defects. H. To confirm suspected defects proceed to Backup NDE Procedure No. 1. If no defects are suspected, proceed to Primary NDE Procedure No. 2. PRIMARY'NDE PROCEDURE NO. 2 - EDDY CURRENT. A. NDE equipment: (3) Crack detector, Magnaflux, P/N ED-520, or equivalent. (4) Probe, shielded, pencil, straight, VM Products P/N VM200-3, or equivalent. (5) Cable, 6 foot, Microdot/BNC, Mastercraft Enterprises P/N HMT 7-41-BM, or equivalent. (6) Standard, aluminum, as furnished with the Magnaflux instrument, or Lockheed-Georgia Co. P/N PDL 457A. B. Preparation of airplane:

THIS MATERIAL CONTAINS PROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICAL SYSTEMS. USE COPYING AND/OR DISCLOSURE WITHOUTH WRITTEN AUTHORIZATION IS PROHIBITED.

MODEL L-382/C-130

SMP 515 C INSPECTION PROCEDURES

SYSTEM WINGS CHAPTER 57

ZONE

REV DATE

500/600

14 DEC 08

CARD NO. SP-123 5 OF 9

WARNING: ENSURE THAT POWER IS ISOLATED FROM ALL SYSTEMS IN THE INSPECTION AREA PRIOR TO APPROACHING THE INSPECTION AREA. FAILURE TO COMPLY MAY RESULT IN SERIOUS INJURY TO PERSONNEL. (3) Isolate power from all systems in the leading edge inspection area in accordance with applicable maintenance manuals. (4) Remove the section of leading edge assembly between OWS 0 and OWS 158, L/R, in accordance with applicable maintenance manuals. C. Use appropriate maintenance platforms for access to the front beam area. D. Preparation of part: WARNING: PROVIDE ADEQUATE VENTILATION WHEN USING CLEANING SOLVENTS AND AVOID BREATHING FUMES. FAILURE TO COMPLY MAY CAUSE SERIOUS INJURY TO PERSONNEL. (3) Provide adequate ventilation to prevent breathing fumes from cleaning solvlents. Cleaning personnel should use rubber glove when using cleaning solvents to prevent skin irritation. (4) Wipe the inspection area of the front beam web around the two countersunk fasteners immediately adjacent to the lower inboard and outboard corners of the pylon fitting; remove stains, oil, etc., using clean cotton cloths wet with Federal Specification 0-T-620, Type I, Trichloroethane, or commercial equivalent. E.

Instrument settings/calibration: Set up and calibrate instrument as specified in SMP.515-C,

Work Card SP-76, Appendix A, for surface scanning of aluminum. NOTE: The eddy current instrument must be recalibrated when probes are changed.

THIS MATERIAL CONTAINS PROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICAL SYSTEMS. USE COPYING AND/OR DISCLOSURE WITHOUTH WRITTEN AUTHORIZATION IS PROHIBITED.

MODEL L-382/C-130 F.

SMP 515 C INSPECTION PROCEDURES

SYSTEM WINGS CHAPTER 57

ZONE

REV DATE

500/600

14 DEC 08

CARD NO. SP-123 6 OF 9

Inspection: Perform surface eddy current scan around two countersunk fasteners through the front beam web, cap, and stiffener immediately adjacent to the lower inboard and outboard corners of the pylon fittings, L/R wings. Inspection around button head fasteners is not required. Refer to SMP 515-C, Work Card SP-76, Appendix A, for surface scanning techniques. The countersunk fasteners may be partially covered by the edge of the pylon fittings on some airplanes; scan around accessible portions of the fastener heads when partially covered. A sharp meter deflection as noted during calibration will indicate a probable crack in the front beam web.

G. Mark and report suspected defects. H. To confirm suspected defects proceed to Backup NDE Procedure No. 2. If no defects are suspected, proceed to System Securing. 6.

BACKUP NDE PROCEDURE NO. 1 - EDDY CURRENT. NOTE:

For support data and locally manufactured items and acceptance/rejection criteria, refer to SMP 515-C, Work Card No. SP-76, Appendix A.

A.

NDE equipment: Same as Primary NDE Procedure No. 1.

B.

Preparation of airplane: Same as Primary NDE Procedure No. 1.

C. Access: Same as Primary NDE Procedure No. 1. D. Preparation of part: Same as Primary NDE Procedure No. 1. E.

Instrument settings/calibration: Set up and calibrate instrument as specified in SMP 515-C, Work Card No. SP-76, Appendix A, for bolt hole scanning on aluminum.

NOTE:

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

THIS MATERIAL CONTAINS PROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICAL SYSTEMS. USE COPYING AND/OR DISCLOSURE WITHOUTH WRITTEN AUTHORIZATION IS PROHIBITED.

MODEL L-382/C-130

SMP 515 C INSPECTION PROCEDURES

SYSTEM WINGS CHAPTER 57

ZONE

REV DATE

500/600

14 DEC 08

CARD NO. SP-123 7 OF 9

F.

7.

Inspection: To verify the defect, repeat the Primary NDE Procedure (eddy current scans) using the probe appropriate for the area where the suspect defect is located. Use one of the methods outlined below. (3) Preferred Method - Different inspector using a different eddy current instrument and a different probe, calibrated in accordance with SMP 515-C, Work Card SP-76, Appendix A, for surface scanning on aluminum. (4) Alternate Method No. 1 - Different inspector using the same instrument and probe as used to find the original suspect defect, recalibrated as above. (5) Alternate Method No. 2 - Same inspector using the same instrument and probe, after resetting and recalibrating, to re-examine the suspect area. G. Mark and report indicated defects. If defects are indicated, take appropriate corrective action. If no defects are indicated, proceed to System Securing. BACKUP NDE PROCEDURE NO. 2 - FLUORESCENT PENETRANT. A. NDE equipment: All chemicals shall use the family concept - they shall all be from the same manufacturer for NOTE: Type I, Group VI, Method C, per MIL-12535 (3) Penetrant, fluorescent, Magnaflux P/N ZL-22A, or equivalent. (4) Remover, penetrant,Magnaflux P/N SKC/NF/C-7, or equivalent. (5) Developer, penetrant, Magnaflux P/N ZP-9B, or equivalent. (6) Black light, portable, Magnaflux P/N ZB-26, or equivalent. B. Preparation of airplane: Same as Primary NDE Procedure No. 2. C. Access: Same as Primary NDE Procedure No. 2.

THIS MATERIAL CONTAINS PROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICAL SYSTEMS. USE COPYING AND/OR DISCLOSURE WITHOUTH WRITTEN AUTHORIZATION IS PROHIBITED.

MODEL L-382/C-130

SMP 515 C INSPECTION PROCEDURES

SYSTEM WINGS CHAPTER 57

ZONE

REV DATE

500/600

14 DEC 08

CARD NO. SP-123 8 OF 9

D. Preparation of part: Remove paints in the inspection area with stripping materials and procedure specified in SMP 515-C, Work Card SP-76, Appendix A.

8.

E. Instrument settings/calibration - Not applicable. F. Inspection: NOTE: If the temperature of the part or inspection materials to be used is below 60-degrees F, preheat and maintain the temperature at or above 60-degrees F during application of penetrant materials. The surface may be heated with a hot air heater. (3) Pre-clean the area to be inspected with the solvent cleaner (Remover, SKC/NF/ZC-7B) and wipe dry with a clean, dry, lint free cloth. (4) Apply warm air to the inspection area to remove all moisture. (5) Apply penetrant to the front beam web in the suspect area. Allow a minimum dwell time of 30 minutes before proceeding to next step. (6) Wipe inspection area with a clean, dry, lint free cloth. Wipe remaining penetrant from part with a clean, lint free cloth dampened with penetrant remover. Check the area to be inspected with the black light to ensure that the excess penetrant has been removed prior to applying the developer. (7) Spray a light film of developer over the area to be inspected. Allow a minimum dwell time of 15 minutes. (8) Using the black light, inspect the suspect area. G. Mark and report confirmed defects. If no defects are noted, proceed to System Securing. 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.

THIS MATERIAL CONTAINS PROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICAL SYSTEMS. USE COPYING AND/OR DISCLOSURE WITHOUTH WRITTEN AUTHORIZATION IS PROHIBITED.

MODEL L-382/C-130

SMP 515 C INSPECTION PROCEDURES

SYSTEM WINGS CHAPTER 57

ZONE

REV DATE

500/600

14 DEC 08

CARD NO. SP-123 9 OF 9

Figure 1. Front Beam Lower Cap and Web Pylon Fitting, OWS 72 and OWS 90

THIS MATERIAL CONTAINS PROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICAL SYSTEMS. USE COPYING AND/OR DISCLOSURE WITHOUTH WRITTEN AUTHORIZATION IS PROHIBITED.