MODEL 382/C-130

SMP 515 C INSPECTION PROCEDURES

SYSTEM WINGS CHAPTER 28

ZONE

REV DATE

500/600

14 DEC 08

CARD NO. SP 322 1 OF 7

FUEL TANK ACCESS PROCEDURES This inspection/test shall be performed each time a fuel tank is to be entered and closed to meet the inspection requirements of S/Bs 382-28-19/82-770 and to comply with Special Federal Aviation Regulation SFAR88 (FAR 121.1113/AD2008-20-01) and AMOC letters dated 14 November 2008 and 5 December 2008. Critical Design Configuration Control Limitations (CDCCL) A CDCCL is a limitation requirement to preserve a critical ignition feature of the fuel system that is necessary to prevent the occurrence of an unsafe condition. The purpose of the CDCCL is to provide instructions to retain the critical ignition source prevention feature that may be caused by alterations, repairs or maintenance actions. A critical ignition source prevention feature may exist in the fuel system and its related installation that, if a failure condition were to develop, could interact with the fuel system without this limitation. CDCCL items are mandatory maintenance actions and/or inspection processes. These items are identified by the symbol in the inspection procedures. WARNING: ENSURE THAT APPLICABLE SAFETY PRECAUTIONS PERTAINING TO WORK IN FUEL/FUME AREAS ARE STRICTLY OBSERVED. PERSONNEL SHALL WEAR NONSPARKING PROTECTIVE CLOTHING. ENTRY INTO TANKS AND DRY BAY MUST NOT BE MADE UNTIL AREAS HAVE BEEN PURGED TO A FIRE-SAFE 20 PERCENT LOWER EXPLOSION LIMIT (LEL), AS DETERMINED USING FUEL VAPOR DETECTION AND MEASURING EQUIPMENT. FULLFACE RESPIRATORS MUST BE WORN UNTIL 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.

THIS MATERIAL CONTAINS PROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICAL SYSTEMS. USE COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION IS PROHIBITED.

MODEL 382/C-130

SMP 515 C INSPECTION PROCEDURES

SYSTEM WINGS CHAPTER 28

ZONE

REV DATE

500/600

14 DEC 08

CARD NO. SP 322 2 OF 7

WARNING: FUEL TANK DEFUELING, DRAINING, PURGING AND MAINTENANCE REQUIRING ENTRY INTO THE TANK(S) SHALL BE PERFORMED ONLY IN DESIGNATED AREAS HAVING CLEAR ACCESS PATHS FOR FIRE FIGHTING AND EMERGENCY EQUIPMENT. THESE AREA(S) SHALL BE PROMINENTLY IDENTIFIED AS FUEL SYSTEM WORK AREA(S) AND POSTED WITH NO SMOKING AND AUTHORIZED PERSONNEL ONLY SIGNS. WARNING: PORTABLE FIRE EXTINGUISHERS MUST BE POSITIONED IN CONVENIENT LOCATIONS. FIRE FIGHTING PERSONNEL AND EQUIPMENT SHALL BE STATIONED NEARBY DURING DEFUELING, DRAINING, AND PURGING OPERATIONS. CAUTION: MAINTENANCE AND INSTALLATION PERSONNEL MUST EXERCISE CAUTION WHILE PERFORMING THESE INSPECTION TO ENSURE THAT WIRING SYSTEMS ARE PROTECTED AND KEPT CLEAN AT ALL TIMES. NOTE THAT METAL SHAVINGS CAUSED BY DRILLING AND OTHER FORMS OF DEBRIS THAT CONTACT WIRE BUNDLES MAY IMPAIR WIRE SYSTEM INTEGRITY AND SHORTEN SYSTEM AND COMPONENT SERVIES LIFE. CAUTION: DO NOT ATTEMPT TO AIR-PURGE TANKS IF AN ELECTRICAL STORM OR WIND IN EXCESS OF 15 KNOTS IS FORECAST. DUST OR OTHER FOREIGN MATTER MAY ENTER THE TANK OPENINGS.

THIS MATERIAL CONTAINS PROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICAL SYSTEMS. USE COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION IS PROHIBITED.

MODEL 382/C-130

SMP 515 C INSPECTION PROCEDURES

SYSTEM WINGS CHAPTER 28

ZONE

REV DATE

500/600

14 DEC 08

CARD NO. SP 322 3 OF 7

WARNING: ALL EQUIPMENT, INCLUDING WORK STANDS, SHALL BE ELECTRICALLY GROUNDED TO THE AIRPLANE AND TO AN APPROVED GROUNDING POST. GROUND WIRES SHALL BE SECURELY ATTACHED TO CONNECTING POINTS TO MINIMIZE ACCIDENTAL DISCONNECTION. WORK STANDS SHALL BE EQUIPPED WITH COPPER, ZINC, OR ZINCCOATED GROUNDING PLATES THAT CAN BE CONVENIENTLY CONTACTED BY PERSONNEL ENTERING THE WORK AREA. CAUTION: WORK DIRECTLY ASSOCIATED WITH THIS INSPECTION SHALL BE ALLOWED ONLY DURING FUEL TANK MAINTENANCE. CAUTION: AT ALL TIMES, CARE MUST BE TAKEN TO PREVENT ENTRY OF CONTAMINANTS INTO THE FUEL TANK(S) THROUGH THE OPENING. OPENING SHALL BE COVERED WITH LINT-FREE CHEESECLOTH WHENEVER THE TANK COVERS ARE REMOVED AND WORK IS NOT IN PROGRESS. A. PREPARE AIRCRAFT FOR INSPECTION AND/OR MODIFICATION 1. Static ground aircraft in accordance with appropriate Hercules Maintenance Manual or Hercules Maintenance Instructions Manual. 2. Lower flaps to full down position to allow access to wing trailing edge. 3. Defuel and purge the tank(s) as required. 4. After defueling, close all applicable fuel valves to retain the remaining fuel in unaffected tanks. THIS MATERIAL CONTAINS PROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICAL SYSTEMS. USE COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION IS PROHIBITED.

MODEL 382/C-130

SMP 515 C INSPECTION PROCEDURES

SYSTEM WINGS CHAPTER 28

ZONE

REV DATE

500/600

14 DEC 08

CARD NO. SP 322 4 OF 7

5. Remove electrical power from aircraft (including external ground power). Disconnect aircraft battery; attach warning tag to battery cable and external power receptacle. 6. Rope off an area for a 50-foot radius from all open tanks and vents. Post fuel hazard banners or signs in the area. 7. Remove access panels to fuel tanks, dry bays, wing trailing edges, pylon tank(s) and cross beam sections as required. CAUTION: USE RUBBER MATS TO PROTECT THE BOTTOM OF TANK(S). B. TANK PREPARATION 1. Ventilate the tank per the Maintenance Manual and maintain a continuous supply of fresh air. 2. Ensure all ducting used to supply purging air to the tank(s) is properly secured to the air blower and purge to remove dust and other contaminates. A positive flow of dry, filtered air must be established though the duct before it is inserted in the tank opening. The duct must be grounded to the airplane at the tank entry point. C. TANK ACCESS Access to the inboard compartment of the tank is by removing an access cover in the inboard end bulkhead, accessible from the outboard dry bay area. Access to the outboard compartments is by the removable panels in the wing upper surface. An access panel in the wing rear beam provides maintenance and inspection access to the interior of the surge box and to the fuel boost pump. THIS MATERIAL CONTAINS PROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICAL SYSTEMS. USE COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION IS PROHIBITED.

MODEL 382/C-130

SMP 515 C INSPECTION PROCEDURES

SYSTEM WINGS CHAPTER 28

ZONE

REV DATE

500/600

14 DEC 08

CARD NO. SP 322 5 OF 7

1. Remove the access panels as required. 2. Bag and secure attaching hardware to the removed panel. 3. Internal tank areas must be protected by clean fuel tank work pads, rubber mats or equivalent. D. TANK INSPECTION PRIOR TO CLOSURE Check the surrounding areas where maintenance was performed inside the tank. Pay particular attention to CDCCL items. 1. Check the accessible fuel quantity wiring to ensure that it hasn’t been disturbed or damaged during tank entry and subsequent maintenance. 2. Ensure that the fuel probe wiring does not chafe on structure or plumbing. 3. Check accessible fuel lines to ensure that they haven’t been disturbed or damaged during tank entry and subsequent maintenance. 4. Check fuel boost pump wiring conduit for damage and impeller screen is in place and secure. Check the screen for obvious damage and evidence of contamination. Check security of pump hardware. 5. Check fuel dump pump wiring conduit for damage and impeller screen is in place and secure. Check the screen for obvious damage and evidence of contamination. Check security of pump hardware. 6. Check fuel level valve wiring conduit for damage and evidence of arcing. Check the security of the mounting hardware.

THIS MATERIAL CONTAINS PROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICAL SYSTEMS. USE COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION IS PROHIBITED.

MODEL 382/C-130

SMP 515 C INSPECTION PROCEDURES

SYSTEM WINGS CHAPTER 28

ZONE

REV DATE

500/600

14 DEC 08

CARD NO. SP 322 6 OF 7

E. PREPARATION AND CLEANING OF ELECTRICALLY BONDED SURFACES 1. Remove excess debris and excess grease, oil or other loose contamination from the bond area by vacuuming, wiping, scrubbing or other physical means. 2. Using a non-metallic brush or wiper, clean the width approximately two times wider than the width of the bond surface. 3. Wipe off all solvent while the surface is wet, using a 4. Clean wiping material or non metallic bristle brush. Apply light pressure between the brush or wiper and the surface. Avoid use of excessive amount of solvent. 5. Ensure that all dust/debris is contained and not allowed in the fuel tank. F. FUEL TANK SECURITY AND CLOSURE 1. Check inside the fuel tank around the area where work was performed thoroughly for loose objects and contamination (Good Housekeeping Practices) prior to tank closure. 2. Check that the anchor and dome nuts are serviceable and properly sealed. 3. Install new seals on all panels that were opened. 4. Reinstall access panels and torque in accordance with Maintenance Manual. 5. Seal in accordance with SMP 515-B. 6. Check bonding resistance between tank access panel and wing structure. The maximum resistance is 0.37 milliohms. 7. Check each panel that was removed for proper bonding. THIS MATERIAL CONTAINS PROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICAL SYSTEMS. USE COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION IS PROHIBITED.

MODEL 382/C-130

SMP 515 C INSPECTION PROCEDURES

SYSTEM WINGS CHAPTER 28

ZONE

REV DATE

500/600

14 DEC 08

CARD NO. SP 322 7 OF 7

G. TANK LEAK CHECK Allow enough time for any sealant applied in the tank, including sealant applied to the wiring conduit to set up before adding fuel. 1. Fill the tank adequately to check for leakage around access panels 2. Fill the tank adequately to check for leakage around any sealant repairs accomplished and around wiring conduit, if level-control valve or pump has been changed.

THIS MATERIAL CONTAINS PROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICAL SYSTEMS. USE COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION IS PROHIBITED.