MODEL L-382/C-130

SMP 515-C INSPECTION PROCEDURES

SYSTEM POWER PLANT CHAPTER 71

ZONE ENGINE NO. 4 ZONE 442

REV DATE 1 OCT 08

CARD NO. C-44 1 of 13

NUMBER 4 POWER PLANT INSPECTION 1. Check No. 4 Engine and Nacelle as follows: a. QEC for general condition and security (see figure 1):

Note:

Elastomeric pressure hose assemblies in the QEC and aft nacelle area are recommended for replacement at five (5) years in-service life or if date is unknown. Recommended replacement requirement does not apply to drain lines, breather lines and teflon hose assemblies. (1) (2) (3)

Note

b.

QEC fuel and hydraulic lines/hose assemblies for evidence of leaks, corrosion, damage, deterioration and security. QEC firewall frame for cracks and corrosion. Splice area below the lower truss mount forward attach boss, and the accessible portions of the QEC lower (horizontal) and upper (sloping) longerons on both sides of the QEC for cracks and corrosion.

Engine Dynafocal Mounts P/N LM-200-SA27 with P/N LM-200-127 bonded cores are Life Limited to 6000 landings or seven (7) years from date of manufacture, whichever occurs first. Later series mounts, P/N LM-200-SA38 and up with P/N LM-200-132 and up bonded cores are not Life Limited. Inspect the engine mounts and remove for overhaul if any of the following conditions are found: (1) Check the mount cores and end plates for nicks, dents, and other surface damage to the forward mounts. (2) Check the forward mount insulation pads for cracks and crushed corners. (3) Check the rubber of the forward engine mounts for flex cracks (surface failure due to flexing) which have progressed inwardly to a depth of 1/4 inch. (4) Check the rubber of the rear mount for flex cracks that have progressed inwardly to a depth of 1/8 inch. THIS MATERIAL CONTAINS LOCKHEED MARTIN PROPRIETARY INFORMATION. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION FROM LOCKHEED MARTIN CORPORATION IS PROHIBITED.

MODEL

SMP 515-C INSPECTION PROCEDURES

L-382/C-130 (5) (c)

d.

SYSTEM POWER PLANT CHAPTER 71

ZONE ENGINE NO. 4 ZONE 442

REV DATE 1 OCT 08

CARD NO. C-44 2 of 13

Check to ensure no gap between rear mount and beam at attach point or between shoulder of bushing and mount.

Engine Control Arm Assembly (See Figure 2): (1)

Inspect the upper and lower engine control arms for evidence of corrosion paying particular attention to the area at each rod end. Pull each arm firmly in an outboard direction then examine for evidence of deformation.

(2)

Check cables and pulleys on control arm assembly for evidence of excessive wear, damage and security: (a)

Rotate throttle to full reverse or takeoff position to allow clear access to gimbal yoke retaining bolt. Verify that the bolt protrudes into coordinator shaft groove.

(b)

Pull on yoke assembly to ensure it is secure on the coordinator shaft and that the yoke does not slip off the shaft spline.

(c)

Remove the cotter key and nut from the retaining bolt, and with bolt still installed, attempt to pull the yoke off the coordinator shaft.

(d)

If gimbal remains secure, remove the bolt and inspect for evidence of wear or damage caused by serrated coordinator shaft.

(e)

Inspect each part of the complete gimbal assembly for condition, security and proper installation.

Heatshield Installation – Aft Nacelle: (1)

Perform a detailed inspection of the heatshield (firewall web).

(2) Pay particular attention to wrinkled areas, for cracks, folding, buckling and oil canning. Buckling and oil canning may be evident but are not cause for heatshield replacement.

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

MODEL L-382/C-130 e.

f. g. h. i. j. k.

Note: l.

SMP 515-C INSPECTION PROCEDURES

SYSTEM POWER PLANT CHAPTER 71

ZONE ENGINE NO. 4 ZONE 442

REV DATE 1 OCT 08

CARD NO. C-44 3 of 13

Aft Nacelle Area (Horse Collar Area) Inspection. Gain entry into the aft nacelle area and remove upper access door H1 and side access panels 10 and 36: (1) Inspect the entire area for cleanliness. (2) Fuel and hydraulic lines/hose assemblies for evidence of leaks, corrosion, damage, deterioration and security. (3) Wire harnesses for security and condition (worn, evidence of chafing). (4) Bleed air ducting for security and condition (loose or damaged insulation, dents, evidence of corrosion, and/or evidence of leakage). (5) Bleed air pressure regulating and shut-off valve for condition and security. (6) Accessible structure for loose or missing fasteners, cracks and evidence of corrosion. (7) Reinstall all panels. Check engine thermocouples, harness, leads and connections for general condition and security. Check accessible wiring for evidence of fraying, chafing, discoloration from overheating, security and connectors for evidence of corrosion, lockwire (except self-locking type) and security. Check fire detection elements and overheat detectors for general condition and security. Check fire extinguisher lines for general condition, security and freedom from obstruction. Check engine ice detector probe for general condition, security and cleanliness. Check engine starter pressure sensing hose or hoses in accordance with applicable maintenance manual. Aircraft with push-button starting have one (1) hose and aircraft with toggle switch starting have two (2) hoses. Inspect air duct assembly between starter control valves and starter inlet port for evidence of leakage and cracks in the flexible joint (s). THIS MATERIAL CONTAINS LOCKHEED MARTIN PROPRIETARY INFORMATION. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION FROM LOCKHEED MARTIN CORPORATION IS PROHIBITED.

MODEL L-382/C-130 m.

n.

p.

SYSTEM POWER PLANT CHAPTER 71

ZONE ENGINE NO. 4 ZONE 442

REV DATE 1 OCT 08

CARD NO. C-44 4 of 13

Compressor Fifth and Tenth Stage Blade Inspection. Check the 5th and 10th stage compressor blades with bleed valves removed. Remove the engine for repair if the following conditions exist: (1)

Erosion of the fifth-stage blade tips to the point that the remaining chordal width at the blade tip is less that 31/32 inch wide.

(2)

Erosion of the tenth-stage tip to the point that the remaining chordal width at the blade tip is less than 15/32 inch wide.

(3)

Any blade with concentrated corrosion and pitting on the inner one-third of the blade length.

(4)

Any blade is broken off.

(5)

Any blade is cracked.

(6)

Install bleed valves with new gaskets.

Air Inlet Housing Inspection. Check the air inlet housing for corrosion and erosion paying particular attention to the anti-ice lip assembly for evidence of cracks in the bulkhead, common to the lip plenum. (1)

o.

SMP 515-C INSPECTION PROCEDURES

Corrosion pits in the leading and/or trailing edges of the struts in excess of 0.100 inch are cause for air inlet housing replacement.

(2)

Corrosion pits in the rear flange area in excess of 0.100 inch is cause for air inlet housing replacement.

(3)

If abrasion or erosion of the air inlet housing struts has occurred and corrosion is evident, refer to the applicable maintenance manual for the appropriate repair action.

Turbine Inlet Casing Inspection. Inspect the turbine inlet casing assembly for cracks as follows: (1)

Axial cracks in the key slot areas of the turbine inlet casing assembly are acceptable up to, but not into, the thick portion of the flange.

(2)

Circumferential cracks are acceptable up to 0.250 inch in length as measured from the side of the slot.

Turbine Rear Bearing Support Inspection. Inspect the rear bearing support for cracks as follows: THIS MATERIAL CONTAINS LOCKHEED MARTIN PROPRIETARY INFORMATION. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION FROM LOCKHEED MARTIN CORPORATION IS PROHIBITED.

MODEL

SMP 515-C INSPECTION PROCEDURES

L-382/C-130 (1)

SYSTEM POWER PLANT CHAPTER 71

ZONE ENGINE NO. 4 ZONE 442

REV DATE 1 OCT 08

CARD NO. C-44 5 of 13

Hat band cracks. Repair or replace the unit if any of the following are exceeded: (a)

Maximum 3 inches length for any one crack.

(b) There can be any number of cracks provided the total length of the cracks does not exceed 21 inches and crack separation is a minimum of two inches. (c) (2) q.

Stop drill serviceable cracks, using a 1/8-inch drill.

Marman Clamp flange; no visible cracks permitted.

Tailpipe Extension Inspection. Inspect the tailpipe for general condition and security. Check the tailpipe and clamp assembly for cracks and excessive distortion and proper torque (80) to 90 inch pounds). If cracks are suspected in the clamp assembly, remove the tailpipe and perform a dye-penetrant or magnaflux inspection. Replace defective parts. Check the tailpipe as follows: (1)

Marman clamp flange and area adjacent to the flange ring; no visible cracks are permitted.

(2)

Tailpipe skin:

(3)

(a)

Minor cracks, not to exceed 1-1/2 inches, may be stop-drilled using 0.125-inch diameter drill. Minor cracks must be separated a minimum of 3 inches and the total length of all cracks shall not exceed 6 inches.

(b)

Cracks extending through the skin and hat section reinforcing rings require tailpipe replacement.

Hat section reinforcing rings: (a)

Drain hole cracks in the mid and aft hat section reinforcing rings that do not exceed 0.50 inch in length shall be stop-drilled using 0.125 inch drill.

(b)

Cracks exceeding 0.50 inch shall be TIG welded. The total length of all cracks in each ring shall not exceed 6 inches.

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

MODEL

SMP 515-C INSPECTION PROCEDURES

L-382/C-130 (4)

Note:

SYSTEM POWER PLANT CHAPTER 71

ZONE ENGINE NO. 4 ZONE 442

REV DATE 1 OCT 08

CARD NO. C-44 6 of 13

Tailpipe stiffener cracks: (a) Stop drill both ends of the crack using a No. 30 (0.1285-inch diameter) drill, if the following limitations are not exceeded.

See the following table for the maximum number of cracks per stiffener and the maximum length of a crack. The minimum distance between any two cracks is 5 inches. NUMBER OF CRACKS PER STIFFENER 1 2 3 4 5 (b) (c)

LENGTH OF ANY ONE CRACK 0.50 0.44 0.38 0.31 0.25

Stop drill shall not penetrate radius of stiffener. Permanent repair must be accomplished on temporary repaired stiffeners at the next ‘C’ check/major inspection, whichever occurs first.

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

MODEL L-382/C-130

SMP 515-C INSPECTION PROCEDURES

SYSTEM POWER PLANT CHAPTER 71

ZONE ENGINE NO. 4 ZONE 442

REV DATE 1 OCT 08

CARD NO. C-44 7 of 13

Figure 1. (Sheet 1 of 6) THIS MATERIAL CONTAINS LOCKHEED MARTIN PROPRIETARY INFORMATION. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION FROM LOCKHEED MARTIN CORPORATION IS PROHIBITED.

MODEL L-382/C-130

SMP 515-C INSPECTION PROCEDURES

SYSTEM POWER PLANT CHAPTER 71

ZONE ENGINE NO. 4 ZONE 442

REV DATE 1 OCT 08

CARD NO. C-44 8 of 13

Figure 1. (Sheet 2 of 6) THIS MATERIAL CONTAINS LOCKHEED MARTIN PROPRIETARY INFORMATION. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION FROM LOCKHEED MARTIN CORPORATION IS PROHIBITED.

MODEL L-382/C-130

SMP 515-C INSPECTION PROCEDURES

SYSTEM POWER PLANT CHAPTER 71

ZONE ENGINE NO. 4 ZONE 442

REV DATE 1 OCT 08

CARD NO. C-44 9 of 13

Figure 1. (Sheet 3 of 6) THIS MATERIAL CONTAINS LOCKHEED MARTIN PROPRIETARY INFORMATION. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION FROM LOCKHEED MARTIN CORPORATION IS PROHIBITED.

MODEL L-382/C-130

SMP 515-C INSPECTION PROCEDURES

SYSTEM POWER PLANT CHAPTER 71

ZONE ENGINE NO. 4 ZONE 442

REV DATE 1 OCT 08

CARD NO. C-44 10 of 13

Figure 1. (Sheet 4 of 6) THIS MATERIAL CONTAINS LOCKHEED MARTIN PROPRIETARY INFORMATION. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION FROM LOCKHEED MARTIN CORPORATION IS PROHIBITED.

MODEL L-382/C-130

SMP 515-C INSPECTION PROCEDURES

SYSTEM POWER PLANT CHAPTER 71

ZONE ENGINE NO. 4 ZONE 442

REV DATE 1 OCT 08

CARD NO. C-44 11 of 13

Figure 1. (Sheet 5 of 6) THIS MATERIAL CONTAINS LOCKHEED MARTIN PROPRIETARY INFORMATION. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION FROM LOCKHEED MARTIN CORPORATION IS PROHIBITED.

MODEL L-382/C-130

SMP 515-C INSPECTION PROCEDURES

SYSTEM POWER PLANT CHAPTER 71

ZONE ENGINE NO. 4 ZONE 442

REV DATE 1 OCT 08

CARD NO. C-44 12 of 13

Figure 1. (Sheet 6 of 6) THIS MATERIAL CONTAINS LOCKHEED MARTIN PROPRIETARY INFORMATION. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION FROM LOCKHEED MARTIN CORPORATION IS PROHIBITED.

MODEL L-382/C-130

SMP 515-C INSPECTION PROCEDURES

SYSTEM POWER PLANT CHAPTER 71

ZONE ENGINE NO. 4 ZONE 442

REV DATE 1 OCT 08

CARD NO. C-44 13 of 13

Figure 2. Engine Control Arm Assembly THIS MATERIAL CONTAINS LOCKHEED MARTIN PROPRIETARY INFORMATION. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION FROM LOCKHEED MARTIN CORPORATION IS PROHIBITED.