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-199 1 OF 9

NDI OUTER WING LOWER SURFACE SKIN PANELS AT KINGPIN RISER PITTING OWS 35 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 lower surface skin panels for cracks in integral risers at termination of kingpin riser stiffeners at OWS 35. (See Figure 1.)

2.

DESCRIPTION. The outer wing lower surface skin panels are fabricated from 7075-T73 aluminum extrusions and machined to contour. The external surfaces are finished with epoxy polyamide primer and polyurethane paint. There are stiffeners attached on each side of the kingpin risers number 12 through 24. The inspection area is located between OWS 29 and OWS 35 on the lower surface skin panels at the 13 kingpin riser locations, left and right outer wings, as illustrated.

3.

DEFECTS. Fatigue loading can cause cracking in the skin panel starting at the most outboard fastener holes in the kingpin risers common to the stiffeners. Cracking may begin at the attachment hole, run to the upper edge and/or into the lower surface of the panel through the riser. The next inboard fastener will then increase its load and cracking may begin, etc.

4.

PRIMARY NDE PROCEDURE - EDDY CURRENT NOTE: For support data and locally manufactured items and acceptance/ rejection criteria, refer to SMP 515-C, Work Card SP-76, Appendix A. A.

NDE equipment: (1) Crack Detector, Magnaflux P/N ED-520, or equivalent. (2) Probe, shielded, right angle, VM Products, P/N VM202A-3, or equivalent. (3) Cable, 6 foot, Microdot/BNC connector, Mastercraft Enterprises P/N HST 7-41-BM, or equivalent. (4) Calibration standard, aluminum, as provided with Magnaflux ED-520, or LASC P/N PDL 457A, or equivalent.

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 B.

SMP 515 C INSPECTION PROCEDURES

SYSTEM WINGS CHAPTER 57

ZONE

REV DATE

500/600

14 DEC 08

CARD NO. SP-199 2 OF 9

Preparation of airplane: 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. (1) 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 OBSERVED WHILE WORKING IN THE FUEL TANKS AND DRY BAY AREAS. PERSONNEL SHALL WEAR NON-SPARKING PROTECTIVE CLOTHING. 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 EXPLOSIVE LIMIT (LEL), AS DETERMINED BY USING FUEL VAPOR DETECTION AND MEASURING EQUIPMENT. FULL FACEPIECE RESPIRATOR MUST BE WORN UNTIL EACH AREA HAS BEEN PURGED TO THE HEALTH-SAFE 0.0 TO 1.5 PERCENT LEL AND 19.5 PERCENT OXYGEN CONTENT. FAILURE TO COMPLY MAY RESULT IN SERIOUS INJURY OR DEATH TO PERSONNEL AND DAMAGE TO THE AIRCRAFT. (2) Drain and purge the outer wing inboard fuel tanks, left and right, in accordance with the applicable maintenance manual to 0.0 to 1.5 percent LEL. All personnel are to wear nonsparking protective clothing while working in an area where fuel/fumes have been present. (3) Remove center wing Hydraulic and Fuel Equipment and Tank Access doors (133/134), and Inboard Fuel Tank Access (K11), left and right, for access to the inboard fuel tanks. Monitor the tanks with a combustible gas indicator and provide constant movement of fresh air through the opened tanks. The center wing dry bay area shall also be

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-199 3 OF 9

purged to 0.0 to 1.5 percent LEL. C. Access: Access to the center wing upper surfaces is available through the top forward, center or aft emergency exits if maintenance stands are not available for access from ground level. WARNING: PROVIDE ADEQUATE VENTILATION WHEN USING CLEANING SOLVENTS AND AVOID BREATHING FUMES. FAILURE TO COMPLY MAY CAUSE SERIOUS INJURY TO MAINTENANCE PERSONNEL. D. Preparation of part: Remove sealing compound from forward and aft sides of each kingpin riser above and below the ends of the riser stiffeners from approximately the sixth fastener from the outboard end of the stiffeners and common to the riser and stiffeners outboard to the end of the stiffeners. Remove sealing compound by scraping with wooden or phenolic scrapers and wetting the sealant with Federal Specification O-T-620, Type I, Trichloroethane or commercial equivalent. Careful attention to sealant removal must be accomplished to prevent errors in reading the eddy current instruments. It will be noted that the stiffeners are bonded to the risers with an epoxy bond and further secured with rivets; no attempt should be made to remove the epoxy or fasteners. Clean fore and aft sides of each kingpin riser on left and right outer wings. E.

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

F.

Inspection: (1) Surface scan the fore and aft side of each kingpin riser above and below the outboard five attach fasteners at the outboard ends of the stiffeners attached to the risers. Use the stiffeners as a guide and

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-199 4 OF 9

scan in an inboard-outboard direction, scanning for cracks initiating in the attach holes and propagating in an approximate vertical direction in the riser. (2) Surface scan the fore and aft sides of all 13 kingpin risers on left and right outer wings as defined above. A sharp meter deflection, as noted during calibration, will indicate a probable crack in the panel riser. G. Mark and report suspected defects. H. To confirm suspected defects, proceed to Backup NDE Procedure. If no defects are suspected, proceed to System Securing. 5.

BACKUP NDE PROCEDURE - EDDY CURRENT A.

NDE equipment: (1) Crack Detector, Magnaflux, P/N ED-520, or equivalent. (2) Probe, bolt hole, 5/32-inch diameter x 1.0 inch long, with cable, VM Products, P/N VM101BC-5/32-1, or equivalent. (3) Probe, bolt hole, 3/16-inch diameter x 1.0 inch long, with cable, VM Products, P/N VM101BC-3/16-1, or equivalent. (4) Calibration standard, as furnished with the Magnaflux instrument, or LASC P/N PDL 457A.

B.

Preparation of airplane: Same as Primary NDE Procedure.

C. Access: Same as Primary NDE Procedure. D. Preparation of part: (1) Remove the outboard five fasteners attaching the stiffeners to the riser on each riser where a suspect condition was noted when performing Primary NDE Procedure. Remove in accordance with SMP 583; it is suggested that a right angle drill be used with a short drill bit that will fit between risers for removing all permanently installed fasteners. 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-199 5 OF 9

WARNING: PROVIDE ADEQUATE VENTILATION WHEN USING CLEANING SOLVENTS AND AVOID BREATHING FUMES. FAILURE TO COMPLY MAY CAUSE SERIOUS INJURY TO MAINTENANCE PERSONNEL. (2) Clean the holes with a stiff nylon bristle brush (not metal) wet with Federal Specification O-T-620 Type I, Trichloroethane. 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.

F.

Inspection: bolt hole scan each of the five holes in each riser where a suspect condition was noted on left and right outer dings. scan through each layer of material. Refer to SPIP 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 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 new fasteners, 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-199 6 OF 9

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-199 7 OF 9

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-199 8 OF 9

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-199 9 OF 9

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