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-165 1 OF 6

NDI OUTER WING RIB CAPS AND BRACES 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 rib caps and braces at OWS 18 through OWS 544. The ribs at OWS 0, 144, 214, 283, 421, and 562 do not contain braces nor caps that require inspection. Ends of braces and caps inside of surge boxes at OWS 18 and 231 do not require inspection.

2. DESCRIPTION. (See Figure 1.) The rib caps and braces are fabricated from 7075-T6 or 7075-T73 aluminum extrusion sulfuric acid anodized, coated with polyurethane for aircraft integral fuel tanks. The braces are attached to the rib caps with aluminum rivets, steel bolts and nuts.

3. DEFECTS. Cyclic loading may cause fatigue cracks to occur in the fastener holes common to the rib caps and braces and in the edges of the stiffening flanges of the braces. The cracks will propagate in both a horizontal and vertical direction.

4. PRIMARY NDE PROCEDURE- EDDY CURRENT. A.

NDE equipment: (1) Crack Detector, Magnaflux P/N ED-530M, or equivalent. (2) Probe, shielded, right angle, VM Products P/N VM202RA-3/8, or equivalent. (3) Probe, shielded, straight, VM Products P/N VM200-3, or equivalent. (4) Cable, 6 foot, Microdot/BNC connector, QualTech P/N BNC-MD-6, or equivalent. (5) Calibration standard, aluminum, as furnished with the Magnaflux (6) Solvent, Cleaner/Remover, Magnaflux P/N SKC-HF, or equivalent.

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-165 2 OF 6

WARNING: Ensure that power is isolated from all systems in the inspection area before approaching the inspection area. Failure to comply may result in serious injury to personnel. (1) Isolate power from all systems in the inspection areas in accordance with the Hercules Maintenance Manual. WARNING: Ensure that all applicable safety precautions pertaining to work in fuel/fume areas specified in the Hercules Maintenance Manual are strictly observed while working in the wing dry bays and main fuel tank areas. Failure to comply may result in serious injury or death to personnel and damage to the airplane. (2) Remove the left and right inboard dry bay access panels. (3) Remove the number 2 and number 3 main inboard fuel tank bulkhead access panels. (4) Remove the left and right outboard dry bay access panels. (5) Remove the number 1 and number 4 main outboard fuel tank bulkhead access panels. (6) Remove the four upper surface access panels for the number 1 and number 4 main outboard fuel tanks. (7) Drain and purge the outer wing fuel tanks in accordance with the Hercules Maintenance Manuals to the 0.0 to 1.5 percent LEL and 19.5 percent oxygen content. NOTE: It is permissible to remove rib braces normally removable for access plus one (1) additional brace at any rib location without supporting the wing.

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-165 3 OF 6

Removal of braces in excess of this requirement or the removal of a rib cap will require jacking in accordance with the applicable Structural Repair Manual for outer wing repair. C. Access: Use appropriate maintenance platforms/stands for access to the upper surfaces of the wings. Access to rib caps and braces in each fuel tank requires removal of braces in the center of the rib which are attached to the rib caps with nuts and bolts for easy removal. Identify braces and fasteners sufficiently to insure reinstallation or replacement at the proper location. Solvent is toxic to skin, eyes, and respiratory tract. Avoid repeated or prolonged contact. Skin and eye protection is required. Good general ventilation is required. Failure to comply could result in serious injury to personnel. D. Preparation of part: Remove sealant and scaling paint in the inspection area using nonmetallic scrapers. Remove oil, grease, and residual sealant by wiping the area with clean cotton rags wet with solvent. Wipe the inspection area dry using clean, dry, cotton rags. E. Instrument settings/calibration: Set up and calibrate the instrument as specified in SMP 515-C, Work Card SP76, Appendix A, for eddy current surface scanning of aluminum. WARNING:

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-165 4 OF 6

Inspection. (1) Eddy current surface scan the web, flange, flange to web radius, and around fasteners of each brace as shown in Figure 1. Inspect both upper and lower end of each brace. (2) Eddy current surface scan the fasteners and web portion of each upper and lower wing rib cap on the side opposite the braces for a distance of approximately 2.0 inches beyond the edges of the brace, both forward and aft side. On those rib caps having beef-up plates installed on the cap web side opposite the brace, surface scan the rib cap adjacent to the brace flange on the same side as the brace, both forward and aft side., (3) A sharp meter deflection, as noted during calibration, will indicate a probable crack in the part being inspected.

G. Mark, report, and verify suspected defects. If no defects are suspected, proceed to System Securing. H. Defect Verification: In order to verify suspect defect, repeat the Primary NDE Procedure in the area where the suspect defect is located. Use one of the methods outlined below. (1) Preferred Method: Different inspector using a different instrument calibrated in accordance with SMP515-C, Work Card SP-76, Appendix A. (2) Alternate Method No. 1: Different inspector using the same instrument recalibrated in accordance with SMP515-C, Work Card SP-76, Appendix A. (3) Alternate Method No. 2: The same inspector using the same instrument recalibrated in accordance with SMP515-C, Work Card SP-76, Appendix A.

5. SYSTEM SECURING. Restore finishes and sealants; reinstall removed components; remove equipment and supplies from the inspection area; and perform operational

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-165 5 OF 6

Figure 1. Inspection of Outer Wing Rib Caps and Braces (Sheet 1 of 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-165 6 OF 6

Figure 1. Inspection of Outer Wing Rib Caps and Braces (Sheet 2 of 2)

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