MODEL 382/C-130

SMP 515-C INSPECTION PROCEDURES

SYSTEM WINGS CHAPTER 57

ZONE

REV DATE

517/617

1 DEC 04

CARD NO. SP 216 1 OF 4

NDI LOWER SURFACE SKIN PANELS AT CUTOUT CORNERS, CWS 216 1. Perform nondestructive inspection of the left and right center wing lower surface skin panels at cutout radii for the forward and aft corner fittings, and for mating bolt installation accesses at CWS 216. (See Figure 1.) 2. DESCRIPTION. The lower surface skin panels are fabricated from 7075-T6/T73 aluminum, sulfuric acid anodized, and finished with epoxy polyamide primer and polyurethane paint. Customer peculiar paints may also be applied to the exterior surfaces. The lower forward corner fittings are machined from forgings of 7075-T6/T73 aluminum, sulfuric acid anodized, and finished like the above panels. The lower aft corner fittings are machined from forgings of 17-4PH steel, passivated, and finished like the above panels. The wing joint fitting (rainbow fitting) is fabricated from 7075-T6 aluminum, sulfuric acid anodized, and finished like the above panels. Attaching fasteners are steel Hi-Loks/Taper-Loks. 3. DEFECTS. Fatigue cracks may initiate in the lower surface panel fastener attach holes and radii adjacent to the cutouts for the corner fittings and wing mate bolt access, and propagate in approximately a chordwise direction. 4. PRIMARY NDI PROCEDURE - EDDY CURRENT

Note: For support data and locally manufactured items and acceptance/rejection criteria, refer to SMP 515-C-NDI, Procedures Manual Supplement.

a.

NDI equipment: (1) Eddy current inspection unit, Nortec 19e, or equivalent. (2) Probe, surface, shielded VM Products, P/N VM200-3, or equivalent. (3) Cable, 6-foot, BNC-to-Microdot connector, VM Products P/N VM99BM, or equivalent. (4) Calibration standard, aluminum, Lockheed Martin P/N PDL 457A as illustrated in SMP 515-C-NDI, Section 20-40-00. (5) Solvent, cleaner/remover, Magnaflux P/N SKC-HF, or equivalent.

THIS MATERIAL CONTAINS LOCKHEED MARTIN PROPRIETARY INFORMATION. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION FROM LOCKHEED MARTIN CORPORATION IS PROHIBITED.

MODEL 382/C-130

b.

SMP 515-C INSPECTION PROCEDURES

SYSTEM WINGS CHAPTER 57

ZONE

REV DATE

517/617

1 DEC 04

CARD NO. SP 216 2 OF 4

Preparation of aircraft:

WARNING:

Ensure that power is isolated from all systems in the inspection areas prior to approaching the inspection area. Failure to comply may result in serious injury to personnel and damage to the aircraft.

(1) Isolate power from all systems in the inspection area in accordance with applicable maintenance manuals. (2) Remove the left and right lower surface wing joint access panels (D4) in accordance with applicable maintenance manuals. c.

Access: Use appropriate maintenance platforms/stands for access to the center wing lower surfaces.

WARNING:

Solvent is toxic to skin, eyes, and respiratory tract, Skin and eye protection is required. Avoid repeated or prolonged contact. Good general ventilation is normally adequate. Failure to comply could result in injury to personnel.

d.

Preparation of parts: Clean excess sealant from the lower surface skin panels in the area around the fastener at the corner of the cutouts for corner fittings and wing mate bolt access from front to rear beams at CWS 216. Remove sealant, scaling paints, oil, and grease in the inspection area using the procedures detailed in SMP 515-C-NDI, Section 20-00-00.

e.

Instrument settings/calibration: Set up and calibrate the eddy current instrument as specified per SMP 515-C-NDI, Section 20-10-04, for surface scan of aluminum.

f.

Inspection: (1) Surface scan the lower surface skin panels, left and right, around the fastener and radius at the corners of the cutouts at fore and aft corner fittings, and at wing mate bolt access. Inspect for cracks that will originate in the fastener holes or corner radius and propagate in an approximate chordwise direction.

THIS MATERIAL CONTAINS LOCKHEED MARTIN PROPRIETARY INFORMATION. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION FROM LOCKHEED MARTIN CORPORATION IS PROHIBITED.

MODEL 382/C-130

SMP 515-C INSPECTION PROCEDURES

SYSTEM WINGS CHAPTER 57

ZONE

REV DATE

517/617

1 DEC 04

CARD NO. SP 216 3 OF 4

(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. If no defects are suspected, proceed to System Securing.

h.

Defect verification: In order to verify a suspect defect, repeat the Primary NDI 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 SMP 515-C-NDI, Section 20-10-04 (2) Alternate Method No.1: Different inspector using the same instrument recalibrated in accordance with SMP 515-C-NDI, Section 20-10-04 (3) Alternate Method No.2: The same inspector using the same instrument recalibrated in accordance with SMP 515-C-NDI, Section 20-10-04

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

THIS MATERIAL CONTAINS LOCKHEED MARTIN PROPRIETARY INFORMATION. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION FROM LOCKHEED MARTIN CORPORATION IS PROHIBITED.

MODEL 382/C-130

SMP 515-C INSPECTION PROCEDURES

SYSTEM WINGS CHAPTER 57

ZONE

REV DATE

517/617

1 DEC 04

CARD NO. SP 216 4 OF 4

Figure 1. Lower Surface Skin Panels at Cutout Corners, CWS 216 THIS MATERIAL CONTAINS LOCKHEED MARTIN PROPRIETARY INFORMATION. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION FROM LOCKHEED MARTIN CORPORATION IS PROHIBITED.