bischoffm

:D

no worries!! I just wanted to correct that point the rest of you pump statement made sense, I've seen no one state that it was wrong, Finding TO's to help the troop is my job, that is why I had the answer to that, here to help.

Someone will get rich figuring out how to resurrect the dead (maybe it's a ZOMBIE horse!!)

Read paragraph 22.4.2.3 (Using a screwdriver) turn clockwise to screw in and counterclockwise to unscrew (that's rightie, tightie leftie loosy) Sorry about hijacking this post!!!!:cool:

Not to be a smart ass, but the T.O. for the use of hand tools to to include screw drivers is AIR FORCE TO 32-1-101 section 22 You have got to remember the Air Force has practically everything!

Apples and oranges!!! The gauges are still bad you are just prolonging the inevitable. Do you think this horse is dead yet!!!

Agreed, The answer to our younger troops should ALWAYS be follow what the tech order says period, not some old or new ways we found to do things unless it's in the book!!!

That pretty much what the Hydro Mite does!! http://www.rentfrowinc.com/

What about this statement "form a "fillet" of Sealing Compound" , this is no panel. I think it's French for "filling the gap":D Interpreting Blueprints 230 defines it as this: fillet- A rounded internal corner. A fillet adds strength to the corner and is often easier to machine. personally I like the one about two sides of the fish!!:cool:

Just because the T.O. doesn't say not beat on the LOX bottle with a hammer doesn't make it the RIGHT way to do it!!

The amount of air that may be loosened by this mallet method is not worth the possibility of someone using something other than a dead blow mallet and is just is not worth the aggravation. (worked few other airframes and never heard the strut banging thing) The Hydro Mite is the strut servicing cart the Navy has been using forever and is currently used at USAF C-130 ISO's and is the ALTERNATE PREFERRED method for servicing all strut without even jacking the aircraft. Hopefully we will have one here at Kadena soon (working on that).

Im Deutschland!!

The A-6 is used for ALL C-130's except for some specialtiy and the J model they have there own. It covers and is used on the C-130H aircraft.

Here is the TCTO that added the lights INSTALLATION OF ADDITIONAL TAXI LIGHTS, C-130 AIRCRAFT TO 1C-130-754 8 October 1974 I don't see where these light would interfer with the MAD they are wired with the postion lights unless someone screw up the routing. Because the TCTO is correct and made no chages addressing the issue that been have stated to have occured.

Maybe this will help! 04132 A. AFTER AN ENGINE OVER TORQUE EXCEEDING 19600 BUT NOT MORE THAN 21500 INCH POUNDS, ENTER OVER TORQUE IN QEC, ENGINE, AND AIRFRAME AFTO FORM 95 FOR HISTORICAL PURPOSES. 005 B. WITHIN 25 AIRFRAME HOURS AFTER AN ENGINE OVER TORQUE EXCEEDING 21500 BUT NOT MORE THAN 23000 IN-LBS., INSPECT THE FOLLOWING QEC, NACELLE AND SUPPORT STRUCTURE FOR CONDITIONS NOTED(SEE TO 1C-130H-2-70FI-00-1-2 FOR ADDITIONAL REQUIREMENTS.) AFTO FORM 95 ENTRY REQUIRED. 11540 (1) QEC UPPER AND LOWER LONGERONS AND FASTENERS ATTACHING UPPER LONGERON TO FIREWALL FOR CRACKS (190) AND LOOSE OR MISSING (105) FASTENERS. 020 11540 (2) PART NO. 362522 QEC BEAM FOR CRACKS (190). 015 11540 (3) QEC DIAGONAL BRACE FOR CRACKS (190). 010 11540 (4) DISCONNECT FITTINGS IN AFT END OF QEC FOR CRACKS (190), ALIGNMENT (127), AND SECURITY (730). 010 11540 (5) TRUSS MOUNT LONGERONS, DIAGONALS AND SWAY BRACE AND ATTACHMENT TO FRONT BEAM FOR CRACKS (190) AND LOOSE OR MISSING (105) FASTENERS. 030 0411B (6) PERFORM NDI OF THE UPPER TRUSS MOUNT VERTICAL LEGS (1154Z) AND TANGS (1154Y) IAW TO 1C-130A-36, N-11. (APPLICABLE TO OVER TORQUES ON #1 AND #4 ENGINES ONLY). REMOVAL OF ENGINE IS NOT REQUIRED. 030 0411B (7) PERFORM NDI OF WING LOWER SURFACE PANELS (UNDER NACELLE FAIRING ATTACH ANGLES) AND ENGINE DRAG FITTINGS (11540) IAW TO 1C-130A-36, CW-23 OR OW-47 AS APPLICABLE. 015 11540 (8) VISUALLY INSPECT NACELLE FAIRING ATTACH ANGLES FOR LOOSE OR MISSING (105) FASTENERS. REF TO 1C-130A-36, CW-23 OR OW-47. 005 11540 (9) NACELLE SKINS AND FAIRING FOR BUCKLES (780) AND LOOSE OR MISSING (105) FASTENERS. 045 11550 11580(10) PERFORM A THOROUGH VISUAL INSPECTION OF THE IR HEAT SHIELD LOWER TUB AND UPPER TRACK ASSEMBLIES FOR EVIDENCE OF BUCKLES (780) AND LOOSE OR MISSING (105) FASTENERS. 045 C. ENGINE OVER TORQUE EXCEEDING 23000 IN-LBS. (FOR AIRCRAFT AT LOCATIONS WHERE NDI CAPABILITY DOES NOT EXIST, THE NDI REQUIREMENTS WILL BE ACCOMPLISHED AT THE FIRST FACILITY WITH NDI CAPABILITY, NOT TO EXCEED 25 AIRFRAME HOURS) SEE TO 1C-130H-2-70FI-00-1-2 FOR ADDITIONAL REQUIREMENTS. AFTO FORM 95 ENTRY REQUIRED. (1) ACCOMPLISH ALL ITEMS LISTED UNDER PARAGRAPH 4.B. ABOVE. (2) NDI THE FOLLOWING STRUCTURE FOR THE CONDITIONS NOTED. THE POWER PLANT MAY REMAIN INSTALLED. 0411B (a) PERFORM NDI OF ENGINE TRUSS MOUNT SWAY BRACE ATTACH LUGS (1154Y) IAW TO 1C-130A-36, N-9. 015 0411B ( PERFORM NDI OF FORWARD OR FORWARD UPPER (AS APPLICABLE) BOLT HOLES OF ENGINE TRUSS MOUNT UPPER TANGS (1154Y) IAW TO 1C-130A-36, N-10, SCANS 13 OR 15 AND 8 OR 18 AS APPLICABLE. NDI BOLTS BY MAGNETIC PARTICLE TEST BEFORE REINSTALLATION. 015 (3) WITH THE ENGINE IN A NO-LOAD CONDITION, CHECK THE FOLLOWING BOLTS FOR MINIMUM TORQUE IN THE TIGHTENING DIRECTION. IF BELOW MINIMUM TORQUE, REMOVE AND REPLACE WITH NEW BOLTS OR REMOVE, NDI AND REPLACE THE FOLLOWING BOLTS: 1154P (a) UPPER QEC AFT ATTACHING BOLTS, 3700 IN-LBS (FOR AIRCRAFT WITH TCTO 1C-130- 1340 COMPLIED WITH MINIMUM TORQUE FOR #2 & #3 UPPER ATTACH BOLTS IS 4800 IN-LBS). 005 1154Q ( LOWER QEC AFT ATTACHING BOLTS, 2300 IN-LBS. 005 1154M (4) WITH THE ENGINE IN A NO-LOAD CONDITION (REF TO 1C-130H-2-71JG-00-2, 71-20-10), CHECK MINIMUM TORQUE ON THE FRONT ENGINE MOUNTS (LORD MOUNT) ATTACHING BOLTS. IF THE TORQUE IS LESS THAN 400 IN-LBS IN THE TIGHTENING DIRECTION, REMOVE AND REPLACE FRONT ENGINE MOUNTS (LORD MOUNTS). TAG FOR OVERHAUL IAW TO 2RA3-2-3: 060 1154M (5) IF THE RUBBER OF THE FRONT ENGINE MOUNT HAS FLEX CRACKS WHICH HAVE PROGRESSED INWARDLY TO A DEPTH OF ¼ INCH. REMOVE AND REPLACE FRONT ENGINE MOUNTS (LORD MOUNTS). TAG FOR OVERHAUL IAW TO 2RA3-2-3:

USAF uses the 1C-130A-6 for it's inspection criteria (for the -15 engines)

Do you mean nacelle interface unit??

Did not C-130A 5500022 (Lone Wolf) retire with a still active formard cargo door?

Because someone was messing around with the forms (some crew chief humor!!)

These tanks were mixed alot we got rid of the Lockheed tanks (solid) 388236-1 and sent them to the bone yard for ease of maintenance and installed100001-300. As you can see the tank T.O. 6J14-2-12-93 does say not to mix them; however, the 1C-130H-4-28-1 makes no distinction. This could be a good AFTO 22 for someone!!

They are the same part number tanks!

if you follow the 16W14-12-3, it means you don't have to have any on the lower edge to call the panel secure. I think that protection from the wind on the ground not air flow!! There is still NO book telling it's OK or NOT OK to fly with any fasteners missing! Like it has been said common sense rules for those who have any!

You have changed the ATM right??

Lots of times that is the best place for some ocifers!!:cool:

They are doing or a TCTO so maintenance can add a digital pressure gauge to adjust the regulator within those T.O. limits. Some AC may not be done yet!