Atch_6_-_T.O._1C-130A-23CL-1.PDF

TO 1C-130A-23CL-1

ORGANIZATIONAL

MAINTENANCE CHECKLIST

WASHING AND CLEANING

USAF SERIES

ALL C-130 AIRCRAFT

ATOS/DLDSS

DISCLOSURE NOTICE - This information is fur-nished upon the condition that it will not be released to another nation without the specific authority of the Department of the Air Force of the United States, that it will be used for military purposes only, that individ-ual or corporate rights originating in the information, whether patented or not, will be respected, that the recipient will report promptly to the United States, any known or suspected compromise, and that the information will be provided substantially the same degree of security afforded it by the Department of Defense of the United States. Also, regardless of any other markings on the document, it will not be down-graded or declassified without written approval of the originating United States agency.

DISTRIBUTION STATEMENT D - Distribution author-ized to the Department of Defense and U.S. DoD contractors only (Administrative or Operational Use) (1 May 2000). Refer other requests for this docu-ment to AFLCMC/WIUEG, Robins AFB, GA 31098.

WARNING - This document contains technical data whose export is restricted by the Arms Export Control Act (Title 22, U.S.C., Sec 2751, et seq.) or the Export Administration Act of 1979, as amended, Title 50, U.S.C., App. 2401 et seq. Violations of these export laws are subject to severe criminal penalties. Dis-seminate in accordance with provisions of DoD Direc-tive 5230.25.

HANDLING AND DESTRUCTION NOTICE - Comply with distribution statement and destroy by any method that will prevent disclosure of contents or reconstruction of the document.

Published under authority of the Secretary of the Air Force

1 MAY 2000

CHANGE 19 - 15 OCTOBER 2015

BASIC AND ALL CHANGES HAVE BEEN MERGED TO MAKE THIS A COMPLETE PUBLICATION

LIST OF EFFECTIVE PAGES

Insert latest changed pages; dispose of superseded pages in accordance with applicable regulations.

NOTE: On a changed page, the portion of the text affected by the latest change is indicated by a vertical line, or other change symbol, in the outer margin of the page. Changes to illustrations are indicated by miniature pointing hands. Changes to wiring diagrams are indicated by shaded areas.

Dates of issue for original and changed pages are:

Original................... 0 .............................. 1 May 2000 Change.................... 1 .........................30 March 2001 Change.................... 2 ...................18 December 2001 Change.................... 3 ..................15 September 2002 Change.................... 4 ...................15 December 2002 Change.................... 5 ...................... 15 October 2003 Change.................... 6 ..................15 September 2004 Change.................... 7 ...................15 December 2004 Change.................... 8 .........................15 March 2005 Change.................... 9 .................... 1 November 2005 Change.................. 10 ........................... 15 June 2007 Change.................. 11 ......................... 1 August 2007 Change.................. 12 ......................1 February 2008 Change.................. 13 ............................. 1 June 2008 Change.................. 14 .................... 1 November 2008 Change.................. 15 .........................15 March 2009 Change.................. 16 ......................... 1 August 2009 Change.................. 17 ........................1 January 2013 Change.................. 18 ......................1 February 2014 Change.................. 19 ...................... 15 October 2015

Total number of pages in this manual is 84, consisting of the following:

Page *Change Page *Change No. No. No. No.

Title A B Added C Blank Added i ii Blank iii iv Blank v vi - viii 1-1 - 1-2 1-3 1-4 1-5 1-6 Blank 2-1 - 2-2

2-2.1 - 2-2.2 Added 2-3 2-4 - 2-8 3-1 - 3-4 3-5 - 3-6 Added 4-1 4-2 4-3 - 4-4 4-5 Added 4-6 Blank Added 5-1 - 5-4 Added 5-5 5-6 - 5-12 Added 5-13 5-14 - 5-16 Added 6-1 - 6-3 Added

*Zero in this column indicates an original page

Change 19 A

LIST OF EFFECTIVE PAGES (Cont)

Page *Change Page *Change No. No. No. No.

6-4 6-5 - 6-8 Added 6-9 6-10 - 6-11 Added 6-12 6-13 - 6-22 Added 6-23 - 6-24 6-25 - 6-26 Added 6-27 6-28 Added

*Zero in this column indicates an original page

Change 19 B/(C blank)

TABLE OF CONTENTS

Section/Para Page

FOREWORD............................................... iii

SAFETY SUMMARY...................................v

I PREPARATION FOR CLEAN-

ING AND WASHING .............................. 1-1

II CLEANING AND WASHING ................. 2-1

III POST CLEANING AND

WASHING ................................................ 3-1

IV POST CLEANING AND WASH-

ING LUBRICATION................................ 4-1

V AFTER WASH CORROSION

INSPECTION........................................... 5-1

VI POST-DESERT AFTER WASH

CORROSION INSPECTION................... 6-1

Change 18 i/(ii blank)

FOREWORD

NOTE

All references (if any), in this manual, per-taining to MC-130W airplanes shall now be known as AC-130W airplanes. Any TO references to the 1C-130(M)W series shall apply to the corresponding 1C-130(A)W TO. Technical Orders in the 1C-130(M)W series will be transitioned to 1C-130(A)W TO numbers as changes are made to the

TO.

This checklist provides instructions for aircraft wash-ing. These instructions do not replace detailed instruc-tions in TO 1C-130A-23, and TO 1-1-691, but are to be used as a guide while performing the work to ensure that no item is overlooked.

It is expected that mechanics using this checklist will not need detailed instruction for performing routine maintenance operations. However, less experienced personnel may find it helpful to make occasional refer-ence to the maintenance manual.

The table of contents preceding these instructions enables quick access to the required procedure.

Change 17 iii/(iv blank)

SAFETY SUMMARY

The supervisor will ensure that personnel are familiar with AFOSH 91-100, AFOSH 91-501, TO 1C-130A-23 and TO 1-1-691. Supervisor will brief all personnel of personal injury hazards as follows:

WARNING

. Avoid breathing toxic fumes.

. Avoid skin contact with compounds.

. Avoid climbing on wet surfaces by us-ing long handled brushes and mainte-nance stands. When it is absolutely necessary to walk on aircraft wing dur-ing washing, an approved fall restraint system will be used and extreme care will be exercised.

. Guard rails must be used properly on stands.

. In the event of chemical injury, seek medical aid immediately.

. In the event of cleaner being splashed in eyes, rinse thoroughly with fresh water for 15 minutes, seek medical at-tention.

. Remove clothing saturated with clean-ing solution immediately and flush ex-posed skin areas with fresh water.

Change 9 v

SAFETY SUMMARY - Continued

WARNING

. While washing and cleaning the air-craft, personnel will wear eye protec-tion, rubber gloves, and clothing, as required by TO 1-1-691. However, when high temperatures are exper-ienced outside, personnel will take an occasional break from washing activi-ties to preclude the possibility of heat prostration.

. Solvents will not be mixed with the cleaning compound solution.

. Compressed air used for drying pur-poses or cleaning can create airborne particles that may enter the eyes or penetrate skin. Eye protection is re-quired. Do not direct compressed air against skin. Compressed air shall be dry and oil-free. Air pressure shall con-form to the identified task pressure and not exceed 15 PSI.

. The anti-reflective coating on the infra-red window for the AAQ-17 infrared re-ceiver contains slightly radioactive thorium fluoride. The only potential hazard involves ingestion of this coat-ing material. Do not grind, sand, file, scrub, or direct high pressure liquid at the coated infrared window. Avoid pro-longed skin contact with chips or power residue from broken or damaged win-dow assembly.

vi Change 19

WARNING

. Soil Barrier, Cee Bee A-6 can cause ir-ritation to the skin and eyes. Avoid skin and eye contact. Wear rubber gloves, face shield or goggles to avoid contact with eyes and skin. Eye protec-tion is always absolutely essential. For large scale operations, full wash rack gear is recommended. Good general ventilation is normally adequate.

. MIL-PRF-83282, hydraulic fluid, is toxic to skin, eyes, and respiratory tract. Skin and eye protection is re-quired. Avoid repeated or prolonged contact. Good general ventilation is normally adequate.

. MIL-DTL-85054 Corrosion Preventive Compound (CPC) is flammable and toxic to skin, eyes, and respiratory tract. Avoid skin and eye contact. Con-sult the local safety office and Bioenvi-ronmental Engineer for Personal Protective Equipment (PPE) require-ments. Good general ventilation is nor-mally adequate. Keep away from open flames or other sources of ignition.

. CPC’s have been revised to eliminate ODC’s. Some reformulated products now contain flammable solvents and/or propellants. Pay close attention to all CAUTION/WARNING labels on the product containers.

Change 19 vii

WARNING

. Do not use synthetic wiping rags or cloths with CPC materials as they will dissolve the synthetic cloth/rag.

. Ensure all areas where MIL-DTL-85054 is applied are fully cured before sealing an area. Although MIL-DTL-85054 is a corrosion preventive compound, its sol-vent vapors may cause corrosion if not allowed to dissipate.

. MIL-PRF-87937 and MIL-PRF-85570 cleaning compounds, are toxic to skin, eyes, and respiratory tract. Avoid skin and eye contact. Industrial safety gog-gles or face shield and neoprene gloves shall be worn. Consult the local safety office and Bioenvironmental Engineer for PPE requirements. Good general ventilation is normally adequate.

. Wear ANSI Z87.1, Type II goggles, pro-tective wet weather clothing, solvent re-sistant gloves, boots, and head covering.

Use a respirator fitted with organic va-por cartridges when working in an en-closed area. Ensure good ventilation is maintained. Consult the local safety of-fice and Bioenvironmental Engineer for PPE requirements.

viii Change 19

SECTION I

PREPARATION FOR CLEANING AND WASHING

1-1. AIRCRAFT WASHING AND CLEANING PREPARATION

PROCEDURES.

NOTE

All materials and supplies used will be in accordance with TO 1C-130A-23 and TO 1- 1-691. Commercial equivalents to the above materials and supplies, are authorized.

1. Park aircraft at a designated wash area in accordance with TO 1C-130H-2-09JG-10-1 and TO 1C-130H-2-10JG-00-1.

2. Lower wing flaps to full down position.

3. Open air deflector doors, pull and attach warning tag to PARATROOP AIR

DEFLECTOR CONTROL/PARATROOP

AIR DEFLECTOR CONT circuit breaker.

3A. Protect all electrical and electronic equipment with tape and/or barrier paper to prevent water/solvent damage.

4. Close all doors, windows, hatches, and openings through which water and/or cleaning fluids could enter.

5. On aircraft modified by TO 1C-130-949, protect the Universal Aerial Refueling Receptacle/Slipway Installation (UARRSI) with tape and barrier paper.

Change 19 1-1

1-1. AIRCRAFT WASHING AND CLEANING PREPARATION

PROCEDURES. (Cont)

6. Install a plastic bag or locally manufactured cover on upper and lower radar cooling fans (HD-150) in the NLG wheel well.

6A. Install a plastic bag or locally manufactured cover on AN/AAQ-24 transmitters, sensors, and fairings.

6B. (On AC-130W aircraft) Install a plastic bag or locally manufactured cover on AN/AAQ- 24(V)13 SLTAs, sensors, and fairings.

7. Protect all electronic equipment in NLG with tape or barrier paper.

8. Disconnect all aircraft electric batteries.

Protect the battery electrical receptacles with caps and plugs or barrier paper.

9. Remove left and right ramp hinge panels, belly band, and ramp closure access panels

PN 344444-4L/R.

10. Secure protective covers or waterproof barrier material over the main wheels and nose wheels ensuring that wheel bearings are protected.

11. Install the following covers/plugs as applicable:

. Pitot tube covers

. Engine intake

. Exhaust plugs PN 355419-1 only

1-2 Change 19

PROCEDURES. (Cont)

. Flight deck and cargo air-condition covers

. APU exhaust covers and intake covers

. Gun covers

. AAR-44

. AAR-47

. ALLTV

. IDS/FLIR

. AFT AN/ALQ-172 cooling intake and exhausts

. 25mm purge fan exhaust cover and ensure gaspurge door is closed and handle pinned

. Nose Ram air cooling cover

. ATM intake

. ALQ-157 transmitters

. Ensure Standoff Precision Guided Munitions portal plugs are installed on cargo ramp door (MC-130W airplanes)

12. Tape/cover the following components:

. APQ-180 radar panel in the nose wheel well

. Three slotted vent holes on the infrared detecting set (IDS) mounting structure located on the left fuselage section directly above the IDS turret (AC-130U only)

. External ECM sensors

Change 17 1-3

PROCEDURES. (Cont)

NOTE

Tape will not be placed over static ports.

Use of barrier material, MIL-PRF-131 and pressure sensitive adhesive tape, SAE- AMS-T-21595, Type III per TO 1-1-691 is recommended.

. All static ports

. Oxygen vent tube(s)

. Landing and auxiliary landing light motor and panel hinge areas

. Left and right flap asymmetry brakes

. Brake accumulator drain hole in bottom of pressure gages

. TAS probe

. Seam around chaff and flare dispenser covers

. Electrical and/or electronic equipment loca-tion behind paratroop doors

. Cargo compartment window vent and drain holes

. APN-241 Radar cooling inlet

. AN/AAQ-24 transmitters and sensors

. ALQ-157 connectors behind the air deflector doors

. Standoff Precision Guided Munitions portals located on cargo ramp door (AC-130W air-craft).

1-4 Change 18

PROCEDURES. (Cont)

13. Remove all IR heat shield lower tub and upper track assemblies prior to each Isochronal Inspection (ISO) and each Home Station Check (HSC). Ensure lower wing skin area under heat shields are thoroughly clean of all soot, dirt and other contaminates. IR heat shield assemblies will remain off until after accomplishment of the ISO/HSC. (Applicable to AC-130U aircraft)

14. Remove right and left wing inboard and outboard flap carriage covers.

15. Remove No. 1 and 2 heat shields prior to the No. 1 and 3 Isochronal Inspection.

Remove No. 3 and 4 heat shields prior to the No. 2 and 4 Isochronal Inspections in accordance with TO 1C-130H-2-51JG-00-1, 51-20-06. Ensure area under heat shields is thoroughly clean of all soot, dirt and other contaminates. Heat shields will remain off until after accomplishment of the isochronal inspection. (N/A to AC- 130U aircraft)

16. Disconnect external power in accordance with TO 1C-130H-2-05JG-00-1 or deactivate the cargo door in accordance with TO 1C-130H-2-52JG-00-1 when performing maintenance, washing, cleaning, or inspecting aft of FS 865.

17. Remove insulation blankets under latrine area at right and left FS 737 to FS 800 WL 164 to WL 200.

18. Deleted.

Change 19 1-5/(1-6 blank)

2-1. AIRCRAFT EXTERIOR AND INTERIOR

CLEANING AND WASHING PROCEDURES.

WARNING

MIL-PRF-87937 and MIL-PRF-85570 cleaning compounds, are toxic to the skin, eyes, and respiratory tract. Avoid skin and eye contact. Industrial safety goggles or face shield, and neoprene gloves shall be worn. Consult the local safety office and Bioenvironmental Engineer for Per-sonal Protective Equipment (PPE) require-ments. Good general ventilation is nor-mally adequate.

Change 19 2-1

CLEANING AND WASHING PROCEDURES.

(Cont)

CAUTION

. Ensure all areas where MIL-DTL-85054 is applied are fully cured before sealing an area. Although MIL-DTL-85054 is a corro-sion preventive compound, its solvent vapors may cause corrosion if not allowed to dissipate.

. Do not use a direct spray of water or cleaning compound on carbon brakes, wheels, or wheel hubs. If wheel bearings are suspected of contamination, corrosion, or loss of lubricant, remove wheel bearings and re-lubricate in accordance with appli-cable system specific maintenance instruc-tions and TO 4W-1-61. If carbon brakes are suspected of contamination, decontam-inate per applicable system specific main-tenance instructions and TO 4B-1-32.

. Abrasive pads will not be used on windows.

. Avoid direct water spray to the AN/AAQ- 24 transmitters, ALQ-172 antenna, APR-

46, IDS/FLIR, AAR-44, AAR-47, ALLTV,

and on AC-130W aircraft Standoff Preci-sion Guided Munitions portals located on cargo ramp door to prevent water damage.

2-2 Change 19

CLEANING AND WASHING PROCEDURES.

(Cont)

NOTE

. MIL-DTL-85054 (Cor-Ban 35) Corrosion Preventive Compound (CPC) may have been applied to some aircraft at Depot; in accordance with TO 1C-130A-23. Specific Depot application locations are identified in the TO. The CPC application appears as an transparent salmon color hard finish which may have shade differences and possible runs/sags. Chapter 7, Section 1 covers Field Level CPC application in-structions and application locations.

. Current specifications and associated Qualified Products List (QPL) authorized for total aircraft wash are listed in

TO 1-1-691.

2-1.1. EXTERIOR WASHING SEQUENCE.

Ensure all drain holes are open and operative and then proceed in accordance with the following sequence.

The following materials are approved for full exterior wash, MIL-PRF-87937, Type I, III, IV, and MIL-PRF- 85570, Types I, III, IV. See TO 1-1-691 for specific instructions on the use of these materials. Clean the exterior surface area by area, starting at the lower sur-face and working upward.

NOTE

All areas must be kept wet with cleaning solutions or water at all times. Rinse off all overspray of solutions.

1. WASH WHEEL WELLS:

Change 19 2-2.1

2-1.1. EXTERIOR WASHING SEQUENCE. (Cont)

a. Wash wheel wells, concentrating first on the interior well structure.

b. Clean landing gear components.

c. Rinse from top to bottom.

2. WASH MID-FUSELAGE:

a. Wash the under surface first, progressing upward.

b. Rinse from top to bottom.

c. Deleted.

3. WASH FORWARD FUSELAGE:

a. Wash under surfaces first, progressing upward. Start at mid-fuselage and spray forward.

b. Rinse from top to bottom.

4. WASH AFT-FUSELAGE:

2-2.2 Change 19

a. Wash exposed areas of the FS 737 bulkhead and under left and right ramp corner panels.

b. Wash the under surface first (cargo ramp and door), progressing upwards.

c. Rinse from top to bottom.

5. WASH EMPENNAGE:

a. Wash bottom of horizontal stabilizer.

b. Wash top of horizontal stabilizer.

c. Wash vertical stabilizer and that portion of aft fuselage subject to fluid run-down. Begin at base and wash to tip.

d. Rinse from tip to base, including aft fuselage.

6. WASH WINGS:

Wash the lower and then the upper surfaces of wings. Start at fuselage wing root area and move toward wing tips. Rinse toward centerline.

Change 18 2-3

7. THOROUGHLY RINSE AIRCRAFT EXTERIOR

SURFACES:

After completion of wash, flush down all aircraft exterior surfaces to remove residual cleaning solutions.

WARNING

Soil Barrier, Cee Bee A-6, can cause irrita-tion to the skin and eyes. Avoid skin and eye contact. Wear rubber gloves, face shield or goggles to avoid contact with eyes and skin. Eye protection is always absolutely essential. For large scale oper-ations, full wash rack gear is recom-mended. Good general ventilation is nor-mally adequate.

8. SOIL BARRIER APPLICATION:

After each aircraft washing, soil barrier may be applied to exhaust paths to include flaps at users option. (See TO 1-1-691).

When applying soil barrier coating, care should be used to avoid spraying moving parts such as landing gear struts, bearings, flap jackscrew and tracks, Plexiglas/windows or electrical contact surfaces. Inadvertent light spray on these areas should cause no problems.

2-1.2. LOCAL INTERIOR CLEANING.

Interior areas of the aircraft subject to the accumula-tion of dirt, debris, and aircraft fluids residue should be cleaned as required for the prevention of corrosion as well as to afford the detection of a breakdown in the corrosion protection finishes originally applied.

2-4 Change 19

2-1.2. LOCAL INTERIOR CLEANING. (Cont)

a. Remove loose soil in the flight deck, cargo compartment, cargo ramp, and cargo door by vacuuming. Lower cargo ramp and raise cargo door to full up and locked position. Scrub the flooring on the flight deck, cargo deck, and ramp with a mop dampened with a 5 to 1 solution of water and cleaner MIL-PRF-87937, Type I.

Clean the mop frequently. Use a stiff bristle brush to remove stubborn stains.

CAUTION

Do not use high volumes of water inside the aircraft.

b. High pressure, low volume, water spray equipment may be used for cleaning heavily soiled floorboards, subject to the restrictions below:

(1) Pressure is limited to approximately

500 PSI.

(2) Water temperature is limited to 120oF.

(3) Water volume shall be limited to approximately 2 gallons/minute.

(4) Cleaning operation shall be accomplished using water only. No detergents or soap shall be used with the pressure equipment inside the cargo compartment.

Change 19 2-5

WARNING

Prior to opening cargo ramp and door, ensure that Common Launch Tubes are not installed in Standoff Precision Guided Munitions portals located on cargo ramp door (AC-130W aircraft).

(5) Cargo ramp and door shall be fully opened.

(6) Start cleaning operation aft of FS 245 and direct all spray toward rear of cargo compartment.

(7) After completion of cleaning operation, ensure the cargo floor and tie-down receptacles are completely dried.

c. Clean soundproofing (as required) with cleaner MIL-PRF-87937, Type IV or MIL- PRF-85570, Type II.

NOTE

MIL-DTL-85054 (Cor-Ban 35) CPC may have been applied to some aircraft at Depot in accordance with TO 1C-130A-23.

Specific Depot application locations are identified in the TO. The CPC application appears as a transparent salmon color hard finish which may have shade differ-ences and possible runs/sags. TO 1C- 130A-23 covers Field Level CPC applica-tion instructions and locations.

2-6 Change 19

d. Clean the sloping longerons, FS 737 to 1041.5, and aft 737 bulkhead (where accessible) with cleaning compound, MIL- PRF-87937, Type I or IV. Then apply MIL-DTL-85054 (Cor-Ban 35 preferred) to the sloping longeron (if not already applied) areas in accordance with TO 1C- 130A-23.

e. Clean the interior skin, ribs, and stringers in the latrine area FS 737 to FS 800, WL 146 to WL 200 using cleaning compound MIL-PRF-87937, Type I or IV per TO 1-1-

691. Pay particular attention to the crevices and areas along sloping longeron where water and other contaminants can accumulate. Dry area thoroughly and apply MIL-DTL-85054 (Cor-Ban 35 preferred) in accordance with TO 1C- 130A-23.

f. Clean all accessible areas of the cargo ramp edges with cleaning compound MIL- PRF-87937, Type I or Type III, or MIL- PRF-85570, Type II per TO 1-1-691.

Inspect all drainage paths in the cargo door to ensure that drain holes are free of obstructions.

g. Wash upper and lower FS 737 bulkhead area.

h. Flush aft urinal drain line with cleaner MIL-PRF-87937 Type I, or equivalent.

Use DXX290, Red Layout Dye Number 8 and check for any leaks in accessible urinal tubing. Repair or replace as needed.

Change 19 2-7

i. Inspect aft urinal drain, pipes, B-nuts, and adjacent area for corrosion, cleanliness, and security.

2-8 Change 19

SECTION III

POST CLEANING AND WASHING

3-1. AIRCRAFT POST WASHING PROCEDURES.

NOTE

MIL-DTL-85054 (Cor-Ban 35) Corrosion Preventive Compound (CPC) may have been applied to some aircraft at Depot in accordance with TO 1C-130A-23. Specific application locations are identified in the TO. The CPC application appears as an transparent salmon color hard finish which may have shade differences and possible runs/sags. TO 1C-130A-23 details Field Level CPC application instructions and locations.

1. Remove stands, protective clothing, and equipment and secure in designated areas.

2. Remove covering from cargo compartment window vent and drain holes.

3. Remove covering from the Universal Aerial Refueling Receptacle/Slipway Installation (UARRSI) or reinstall assembly.

4. Remove covering from radar cooling fans (HD-150) and APQ-180 radar panels in nose wheel well.

5. Remove protective covering from MLG and NLG wheel and tire. Ensure water is not puddled in wheel well areas.

Change 19 3-1

3-1. AIRCRAFT POST WASHING PROCEDURES. (Cont)

6. Remove covering from static ports, oxygen vent line(s), and all other port openings that are covered.

7. Remove covering from left and right asymmetry brake drain holes. Ensure water is not puddled in flap well areas.

8. Install Infrared (IR) shields.

9. Remove covering and tape from the left and right landing and auxiliary landing light motor and panel hinge areas.

10. Remove tape from the seam around chaff and flare dispenser covers.

11. Install left and right ramp hinge panels, belly band, and ramp closure access panels PN 344444-4L/R, after completing after wash inspection.

3-2 Change 19

WARNING

Compressed air used for drying purposes or cleaning can create airborne particles that may enter the eyes or penetrate skin.

Eye protection is required. Compressed air shall be dry and oil-free. Air pressure will not exceed 15 PSI.

CAUTION

Failure to remove residual water from the oil cooler tubes may result in rupture of the cooler tubes.

12. Remove residual water that may have accumulated during aircraft wash from the engine oil cooler tubes by soaking up water with a rag, sponge, or by compressed air (not to exceed 15 PSI). If moving the aircraft from a heated washing facility into a freezing environment; annotate in the aircraft forms to motor engines as soon as the aircraft is located on parking spot.

13. Install right and left wing inboard and outboard flap carriage covers.

14. Remove protective material from electrical and/or electronic equipment located behind air deflector doors.

Change 19 3-3

15. Remove caps and plugs or barrier paper from battery electrical receptacles and reconnect all aircraft electric batteries.

Secure battery quick disconnects with 0.020-inch copper safety wire.

16. Reactivate cargo door in accordance with

TO 1C-130H-2-52JG-00-1.

3-4 Change 19

WARNING

MIL-DTL-85054, CPC is flammable and toxic to the skin, eyes, and respiratory tract. Avoid skin and eye contact. Con-sult the local safety office and Bioenviron-mental Engineer for Personal Protective Equipment (PPE) requirements. Good general ventilation is normally adequate.

Keep away from open flames or other sources of ignition.

CAUTION

Ensure all areas where MIL-DTL-85054 is applied are fully cured before sealing an area. Although MIL-DTL-85054 is a corro-sion preventive compound, its solvent vapors may cause corrosion if not allowed to dissipate.

17. Reapply MIL-DTL-85054, CPC (Cor-Ban

35) to areas identified in TO 1C-130A-23 that had previous applications applied, touch-up as required.

18. Reinstall insulation blankets under latrine area at right and left FS 737 to FS 800 WL 164 to WL 200.

19. Reinstall the left wing root access panel between fuselage station 597 and 617, on washes prior to isochronal inspection only.

Change 19 3-5

20. Remove protective covering from IDS/FLIR turret units.

21. Remove protective covering from Standoff Precision Guided Munitions portals located on cargo ramp door (AC-130W airplanes).

22. Remove the covers from the ALQ-157 transmitters and masking tape on the connectors behind the air deflector doors.

23. Remove protective material from the AN/ AAQ-24 transmitters, sensors, and fairings.

24. Remove tape/cover from:

. External ECM sensors

. All static ports

. Oxygen vent tube(s)

. Brake accumulator drain hole in bottom of pressure gauges

. TAS probe

. APN-241 Radar cooling inlet

3-6 Change 19

SECTION IV

POST CLEANING AND WASHING

LUBRICATION

4-1. AIRCRAFT POST WASHING LUBRICATION

PROCEDURES.

NOTE

. Exposed external lubrication points will have the lubricant removed during the cleaning operation. After cleaning and inspecting these areas, reapply the proper lubricant in accordance with the following instructions. Since the lubricant provides corrosion protection, lubrication shall be accomplished immediately after comple-tion of the wash rack cleaning and inspection.

. When aircraft is washed for ISO inspec-tion, the requirement for lubrication can be completed during the ISO inspection, except for f lap tracks, jackscrews, and ballscrews and all exposed chrome (i.e.

struts and actuators).

4-1

4-1. AIRCRAFT POST WASHING LUBRICATION

PROCEDURES. (Cont)

1. Lubricate exposed areas of the aileron control rods IAW TO 1C-130H-2-12JG-20-1.

2. Lubricate exposed areas of the flap components IAW TO 1C-130H-2-12JG-20-1.

3. Lubricate exposed areas of the MLG and MLG doors and MLG ski components (as applicable) IAW TO 1C-130H-2-12JG-20-1.

4. Lubricate exposed areas of the NLG and NLG doors and NLG ski components (as applicable) IAW TO 1C-130H-2-12JG-20-1.

5. Lubricate exposed areas of the cargo ramp and door IAW TO 1C-130H-2-12JG-20-1.

6. Lubricate exposed areas of the ground test checkout valve components IAW TO 1C-

130H-2-12JG-20-1.

7. Lubricate the air deflector door components

IAW TO 1C-130H-2-12JG-20-1.

7A. Close PARATROOP AIR DEFLECTOR

CONTROL/PARATROOP AIR

DEFLECTOR CONT circuit breaker and remove the warning tag.

8. Lubricate the exterior door/hatch release handles and release plungers on the emergency exit doors IAW TO 1C-130H-2-

12JG-20-1.

9. Lubricate exposed life raft release cables in the flap wells IAW TO 1C-130H-2-12JG- 20-1.

4-2 Change 16

PROCEDURES. (Cont)

WARNING

MIL-PRF-81309, Type II, Corrosion Pre-ventive Compound (CPC) is flammable and toxic to skin, eyes, and respiratory tract. Avoid skin and eye contact. Con-sult local safety office and Bioenvironmen-tal Engineer for Personal Protective Equipment (PPE) requirements. Good general ventilation is normally adequate.

Keep away from open flames or other sources of ignition.

10. Spray piano hinges with MIL-PRF-81309, CPC (do not apply to the LOX service door, bottle, or lines).

11. Spray all AN/ALQ-17, aft panel hinges with MIL-PRF-81309, CPC.

WARNING

SAE-AS-8660 silicone grease is toxic to the eyes, skin, and respiratory tract. Avoid repeated or prolonged contact. Good gen-eral ventilation is normally adequate.

12. Lubricate the HF external wire antenna mast support sleeve and antenna take-up spring/mechanism with Silicone grease

SAE-AS-8660.

Change 19 4-3

PROCEDURES. (Cont)

NOTE

On AF serial number 80-0332 and up an interference bolt/cone bushing is installed in the elevator trim tab horn fitting to jackscrew rod end. Do not remove for lubrication.

13. Lubricate rudder, elevator, and aileron trim tab hinges with MIL-PRF-32033 oil while moving the tab through full travel in accordance with TO 1C-130H-2-12JG-20-1.

14. Lubricate elevator trim tab jackscrew rod ends at attaching points in accordance with

TO 1C-130H-2-12JG-20-1.

15. With a clean cloth, apply a light coat of MIL-L-14107, lubricating oil, on all external gun surfaces.

16. Deleted.

17. Lubricate accessible crew entrance door components in accordance with TO

1C-130H-2-12JG-20-1.

4-4 Change 19

PROCEDURES. (Cont)

WARNING

MIL-PRF-83282, hydraulic fluid, is toxic to skin, eyes, and respiratory tract. Skin and eye protection is required. Avoid repeated or prolonged contact. Good general venti-lation is normally adequate.

CAUTION

Lubricate landing gear wheel bearings and axles, if they have been exposed to water and solvent during the wash, in accor-dance with TO 4W-1-61.

18. With a clean cloth apply a light film of MIL-PRF-83282 hydraulic fluid to yoke actuating cylinders.

19. Lubricate landing gear wheel bearings (TO 4W-1-61) and axles if they have been exposed to water and solvent during the wash.

20. Lubricate the oil cooler actuator rod in accordance with TO 1C-130H-2-12JG-20-1 (aircraft with oil cooler augmentation installed).

21. Lubricate door/hatch seals in accordance with TO 1C-130H-2-12JG-20-1.

Change 19 4-5/(4-6 blank)

SECTION V

AFTER WASH CORROSION INSPECTION

5-1. INSPECTION REQUIREMENTS.

a. This section is used to accomplish corrosion inspections after every wash.

Depending on which areas of the aircraft are accessible, refer to Section II, Cleaning and Washing or Section VI, Post Desert Wash Corrosion Inspection.

b. These instructions do not replace detailed instructions in TO 1C-130A-23 and TO 1- 1-691, but will be used as a guide while performing the inspection to ensure that no item or area is overlooked.

c. While these instructions point out specific areas of the aircraft to be visually inspected, the aircraft should be observed as a whole while performing this inspection.

d. This inspection shall be performed by 2A7X3 personnel.

Change 18 5-1

5-2. DOCUMENTATION REQUIREMENTS.

NOTE

Clear and concise descriptions of both dis-crepancies and corrective actions are criti-cal to corrosion data mining collection and research.

Corrosion discovered during this inspection requiring repair will be reported using the AFTO Form 781A, Maintenance Discrepancy and Work Document and the Inspection Corrosion and Repair Recording (ICARR) website to make inputs to the Automated Inspection Repair Corrosion and Aircraft Tracking (AIRCAT) database. Provide a detailed description of the type of corrosion found, location and repair procedures used in the ‘‘other’’ category. This is an Aircraft Structural Integrity Program (ASIP) requirement. See https://C130aircat.robins.af.mil/ for program, instruc-tions, and information on ICARR.

5-2 Change 18

5-3. AFTER WASH CORROSION INSPECTION.

5-3.1 FUSELAGE EXTERIOR.

1. WINDOW FRAMES:

a. Visually inspect the window frame structural components for evidence of rust, powdery oxides, pitting, exfoliation, intergranular, stress corrosion, chipped and deteriorating paint and cracks.

(1) Skin surface around the window frames

(2) Lap and butt joints

(3) Inspect all hardware for loose, missing and corroded fasteners (i.e.

rivets, screws, nuts, washers, bolts, etc.)

2. FUSELAGE FS 93 TO FS 1041:

a. Visually inspect the following fuselage areas and structural components for evidence of rust, powdery oxides, pitting, exfoliation, intergranular, stress corrosion, chipped and deteriorating paint and cracks.

(1) Pressure Skin surfaces

(2) Lap and butt joints

(3) Inspect all hardware for loose, missing and corroded fasteners (i.e.

rivets. screws, nuts, washers, bolts, etc.)

Change 18 5-3

5-3.1 FUSELAGE EXTERIOR. (Cont)

NOTE

To exercise the flapper valves, insert eraser end of a pencil through the drain holes from outside the aircraft, lifting the valve upward to release any residual water and to dislodge any barrier on the valve.

(4) Drain holes and flapper valves

(5) Inside of battery box area

(6) Power receptacle mount area

(7) Pitot tube and mounting screws

(8) Bulkhead assembly FS 737 and ramp hinge mounts

3. ACCESS PANELS AND SERVICING DOORS:

a. Visually inspect all external access and servicing doors for evidence of rust, powdery oxides, pitting, exfoliation, intergranular, stress corrosion, chipped and deteriorating paint and cracks.

(1) Skin surface

(2) Inspect all hardware for loose, missing and corroded fasteners (i.e.

rivets. screws, nuts, washers, bolts, etc.)

(3) Ensure all areas are free of sand, debris and other contaminants

5-4 Change 18

5-3.1 FUSELAGE EXTERIOR. (Cont)

4. AIR DEFLECTOR DOORS:

a. Visually inspect hardware and structural components for rust, powdery oxides, pitting, exfoliation, intergranular, stress corrosion, chipped and deteriorating paint.

(1) Inspect all hardware for loose, missing and corroded fasteners (i.e.

rivets, screws, nuts, washers, bolts, etc.)

(2) Ensure all areas are free of sand, debris and other contaminants

5-3.2. NOSE LANDING GEAR.

1. NOSE LANDING GEAR ASSEMBLY, WHEEL

WELL AND DOORS:

a. Visually inspect the following areas and components for rust, powdery oxides, pitting, exfoliation, intergranular, stress corrosion, chipped and deteriorating paint.

(1) All visible hydraulic lines, fittings, steering control valve, and manifold steering actuators

(2) Landing gear trunnions, torque tubes, shock strut, fulcrum, pressure diaphragm skin, attach angles, and hardware

(3) Steering control cables

Change 19 5-5

5-3.2. NOSE LANDING GEAR (Cont)

(4) Inspect all hardware for loose, missing and corroded fasteners (i.e.

rivets, screws, nuts, washers, bolts, etc.)

(5) Nose gear doors, actuating rods and rod ends

(6) Wheel well area

5-3.3. MAIN LANDING GEAR

1. MAIN LANDING GEAR (MLG) AND WHEEL

WELLS:

a. Visually inspect the following areas and components for rust, powdery oxides, pitting, exfoliation, intergranular, stress corrosion, chipped and deteriorating paint.

(1) All visible hydraulic lines, fittings, and components

(2) MLG struts, ball-screws, torque strut, trunnion, and door linkages

(3) Vertical beams, chine angle, shelf brackets, and hardware

(4) MLG doors, hinge area and torque tubes

(5) Inspect all hardware for loose, missing and corroded fasteners (i.e.

rivet, screws, nuts, washers, bolts, 5-6 Change 18

5-3.4. WINGS

1. WING UPPER AND LOWER EXTERIOR

SURFACE:

a. Visually inspect for breaks in corrosion protection around fasteners and along butt and lap joints. Inspect the surface for blisters which are indicative of exfoliation under the painted surface.

Look for spots of grayish powdery deposits, that when wiped away, will reveal an absence of paint and pitting in the metal surface.

(1) Inspect exhaust exposure areas for evidence of pitting corrosion

(2) Inspect all hardware for loose, missing and corroded fasteners (i.e.

rivets, screws, nuts, washers, bolts, etc.)

(3) Inspect skin and panel surfaces

(4) Inspect the life raft door and hinge areas

2. WING BONDED-BEADED TRAILING EDGE

SKINS AND FLAPWELL AREAS:

a. Visually inspect for breaks in corrosion protection around fasteners and along butt and lap joints. Inspect the surface for blisters which are indicative of exfoliation under the painted surface.

Look for spots of grayish powdery deposits, that when wiped away, will reveal an absence of paint and pitting in the metal surface.

Change 18 5-7

5-3.4. WINGS (Cont)

(1) Inspect the upper and lower trailing edge panels (flap well) for any sign of corrosion, chipped, blistered, or deteriorating paint

(2) Inspect bond lines for signs of corrosion or disbond

(3) Inspect all hardware for loose, missing and corroded fasteners (i.e.

rivets, screws, nuts, washers, bolts, etc.)

(4) Inspect all structural components, ribs, stiffeners, joints, in flapwell area

3. WING FLAP TRACKS:

NOTE

When scale or heavy pitting is observed, the part shall be inspected by Nondestruc-tive Inspection (NDI) procedures in accor-dance with TO 1C-130A-36.

a. Visually inspect the tracks and attachments for rust, brownish-red oxide buildup and scale.

(1) Inspect all hardware for loose, missing and corroded fasteners (i.e.

rivets, screws, nuts, washers, bolts, 5-8 Change 18

4. INBOARD AND OUTBOARD FLAPS:

a. Visually inspect for breaks in corrosion protection around fasteners and along butt and lap joints. Inspect the surface for blisters which are indicative of exfoliation under the painted surface.

Look for spots of grayish powdery deposits, that when wiped away, will reveal an absence of paint and pitting in the metal surface.

(1) Inspect the upper and lower surfaces for pitting, exfoliation and oxide buildup

(2) Skin panels, butt and lap joints, and recesses on the flap

(3) Structural components

(4) Inspect all hardware for loose, missing and corroded fasteners (i.e.

rivets, screws, nuts, washers, bolts, etc.)

(5) Inspect the metal around and aft of drain holes for stains and pitting

5. AILERONS:

a. Visually inspect the ailerons for rust, exfoliation and pitting corrosion; paying particular attention to the following areas:

(1) Along the edges, seams, and skin lap joints

Change 18 5-9

(2) Inspect all hardware for loose, missing and corroded fasteners (i.e.

rivets, screws, nuts, washers, bolts, etc.)

(3) All hinges

(4) Push/pull rods and guide rollers

5-3.5. EMPENNAGE

1. HORIZONTAL STABILIZER AND HORIZONTAL

TO FUSELAGE FILLET AREAS:

a. Visually inspect the following areas for evidence of rust, pitting, intergranular, exfoliation, delamination, chipped and deteriorating paint.

(1) Horizontal stabilizer upper and lower surfaces

(2) Fuselage to stabilizer farings

(3) Mooring fittings

(4) Inspect all hardware for loose, missing and corroded fasteners (i.e.

rivets, screws, nuts, washers, bolts, etc.)

2. ELEVATOR:

a. Visually inspect the following areas for evidence of rust, pitting, intergranular, exfoliation, delamination, chipped and deteriorating paint.

(1) Butt and lap joints, seals and hinges

5-10 Change 18

5-3.5. EMPENNAGE (Cont)

(2) Edges of honeycomb trim tab

(3) Elevator, counterbalance and trim tab drain holes

(4) Inspect all hardware for loose, missing and corroded fasteners (i.e.

rivets, screws, nuts, washers, bolts, etc.)

3. RUDDER:

a. Visually inspect the following areas for evidence of rust, pitting, intergranular, exfoliation, delamination, chipped and deteriorating paint:

(1) Butt and lap joints, seals and hinges

(2) Edges of honeycomb trim tab

(3) Inspect all hardware for loose, missing and corroded fasteners (i.e.

rivets, screws, nuts, washers, bolts, etc.)

5-3.6. FUSELAGE INTERIOR

1. WINDSHIELD RETAINERS AND FORWARD

SENSOR PANEL RETAINERS:

a. Visually inspect the windshield for milky, foggy, or cloudy areas; these are indicators of water intrusion in the windshield frame. Inspect retainers for evidence of water lying in seams, flaking paint, uniform etch, pitting, intergranular, and exfoliation corrosion, paying particular attention to the following areas:

Change 18 5-11

5-3.6. FUSELAGE INTERIOR (Cont)

(1) Windshields and retainers junctures

(2) Along the lower seams

(3) Around the border of the windshield

(4) Junctures of the sensor panels

(5) Fasteners and gasket material

2. FLIGHT DECK CHINE PLATES AND CIRCUIT

BREAKER PANELS:

a. Visually inspect chine plates and area behind the pilot’s and copilot’s circuit breaker panels for exfoliation corrosion particularly around fastener holes and around edges and any indication of sand deposits and debris.

(1) Ensure all areas are free of sand, debris and other contaminants

3. SEATS:

a. Visually inspect seat tracks, seat mechanisms and components.

(1) Inspect all hardware for loose, missing and corroded fasteners (i.e.

rivets, screws, nuts, washers, bolts, etc)

(2) Ensure all areas are free of sand, 5-12 Change 18

5-3.7. INTERNAL FUSELAGE.

1. ELECTRONIC EQUIPMENT RACKS:

a. Visually inspect the electronic support structure for evidence of chipped and deteriorating paint, grayish powdery deposits, exfoliated metal, crevice and pitting corrosion paying particular attention to the following areas:

NOTE

A damp floor or the smell of urine may suggest corrosion on the hidden mating surface.

(1) The base of the racks in contact to the floor

(2) The stand-off hat sections

(3) Transformer-rectifier grounding studs

2. AUTOPILOT AND RADIO JUNCTION BOXES:

NOTE

Junction boxes are susceptible to rain entering through the open crew door.

Leaks in the flight deck escape hatch clo-sure which seeps through the floor.

a. Visually inspect the bases of the boxes which are in contact with the floor for chipped and deteriorating paint, grayish powdery deposits, corrosion, and exfoliated metal.

Change 19 5-13

5-3.7. INTERNAL FUSELAGE (Cont)

3. FWD FUSELAGE - FS 165 TO FS 196:

a. Remove the flight deck ladder and visually inspect the under deck area from FS 165 to FS 196 for fluids, sand, debris, rust, pitting, intergranular, exfoliation and stress corrosion, paying particular attention to the following areas, surfaces, and structural components.

(1) Inspect the areas where the nose wheel well and fuselage structure come together from FS 165 to FS 196

(2) Flight deck floor support beams

4. CARGO COMPARTMENT CHINE CAPS FS

245 TO FS 737:

NOTE

If mission equipment or racks are perma-nently installed, visually inspect only accessible areas.

a. Visually inspect the chine caps for pitting, intergranular, exfoliation, and stress corrosion, pay particular attention to the machined radii and the following areas:

(1) Surfaces around fasteners and low points in the wells

5. CARGO RAMP AND DOOR:

a. Visually inspect accessible areas of the cargo ramp and cargo door sides for dirt, debris, pitting, intergranular, exfoliation, and stress corrosion in the following areas:

5-14 Change 18

(1) Low areas along side flanges

(2) Around actuator mount bracket

(3) Around ramp hooks

(4) In lower forward areas of cargo doors

(5) Ensure all drainage holes are free of sand, debris and other contaminants

(6) Scuff plate

6. SLOPING LONGERON AREA FS 737 - FS

1041:

NOTE

The forward end of the sloping longerons and associated structures are highly prone to severe corrosion from urine and moisture.

a. Visually inspect the following areas of the sloping longeron for rust, powdery oxides, pitting, exfoliaiton, intergranular, stress corrosion, chipped and deteriorating coatings (paint and Self-Leveling Green sealant).

(1) Sloping longeron

(2) Sloping longeron doublers

(3) Sloping longeron end fitting

(4) Deposits of urine salts

Change 18 5-15

(5) Inspect the fuselage skin for separation or lifting and corrosion products between the skin and longeron

(6) Inspect all hardware for loose, missing and corroded fasteners (i.e.

rivets, screws, nuts, washers, bolts, etc)

(7) Ensure all areas are free of sand, 5-16 Change 18

SECTION VI

POST-DESERT AFTER WASH CORROSION

INSPECTION

6-1. INSPECTION REQUIREMENTS.

a. This section is used for aircraft returning from Southwest Asia (SWA). These aircraft require a more in depth visual inspection of the areas listed in this checklist than of aircraft operating in other environments.

b. These instructions do not replace detailed instructions in TO 1C-130A-23, and TO 1- 1-691, but will be used as a guide while performing the inspection to ensure that no item or area is overlooked.

c. While these instructions point out specific areas of the aircraft to be visually inspected, the aircraft should be observed as a whole while performing this inspection.

d. This inspection shall be performed by personnel qualified in corrosion detection who have attended appropriate corrosion prevention and control courses established by AETC and the MAJCOM, as required by AFI 20-114.

Change 18 6-1

6-1. INSPECTION REQUIREMENTS. (Cont)

e. A visual inspection should be accomplished on all surfaces exposed to view using the naked eye or with the aid of, a mirror and flashlight when required.

Use of a 10 power magnifying glass should be used when evaluating the severity of corrosion or after corrosion repair to ensure all corrosion has been removed.

NOTE

Use of vacuum system without non-HEPA filtration system can redistribute fine chlo-ride containing dust throughout the aircraft.

f. Ensure all sand and debris is removed on all surfaces exposed to view with approved vacuums that are equipped with HEPA filtration system.

6-2 Change 18

6-2. DOCUMENTATION REQUIREMENTS.

Corrosion discovered during this inspection requiring repair will be reported using the AFTO Form 781A, Maintenance Discrepancy and Work Document and the Inspection Corrosion and Repair Recording (ICARR) website to make inputs to the Automated Inspection Repair Corrosion and Aircraft Tracking (AIRCAT) database. Provide a detailed description of the type of corrosion found, location and repair procedures used in the ‘‘other’’ category. This is an Aircraft Structural Integrity Program (ASIP) requirement. See https:// C130aircat.robins.af.mil/ for program, instructions and information on ICARR.

Change 18 6-3

6-3. PREPARATION FOR INSPECTION.

a. Open/remove the following items in accordance with applicable TOs to facilitate the corrosion inspection.

(1) Open the nose and main landing gear doors

(2) Open all four horsecollars

(3) Open aileron swing down panels

(4) Remove left and right wing root access panels

(5) Remove both left and right lower elevator/rudder counter balance access panels, (beavertail panels)

(6) Remove the flight deck ladder and crew entry floor panel

(7) Remove the access panels below the left and right paratroop doors

(8) Remove the left and right wing root camlock panels

(9) Deleted

6-4 Change 19

6-4. POST-DESERT AFTER WASH CORROSION INSPEC-

TION.

6-4.1. FUSELAGE EXTERNAL.

1. WINDOW FRAMES:

a. Visually inspect the window frame structural components for evidence of rust, powdery oxides, pitting, exfoliation, intergranular, stress corrosion, chipped and deteriorating paint and cracks.

(1) Skin surface around the window frames

(2) Lap and butt joints

(3) Inspect all hardware for loose, missing and corroded fasteners (i.e.

rivets, screws, nuts, washers, bolts, etc)

2. FUSELAGE FS 93 TO FS 1041:

a. Visually inspect the following fuselage area and structural components for evidence of rust, powdery oxides, pitting, exfoliation, intergranular, stress corrosion, chipped and deteriorating paint and cracks.

(1) Skin surface

(2) Lap and butt joints

(3) Inspect all hardware for loose, missing and corroded fasteners (i.e.

rivets, screws, nuts, washers, bolts, etc)

Change 18 6-5

6-4.1. FUSELAGE EXTERNAL. (Cont)

NOTE

To exercise the flapper valves, insert eraser end of a pencil through the drain holes from outside the aircraft, lifting the valve upward to release any residual water and to dislodge any barrier on the valve.

(4) Drain holes and flapper valves

(5) Inside of battery box area

3. LONGERON FITTING UNDER PARATROOP

DOOR SILL FS 693 TO 737:

a. Gain access and visually inspect the longeron fitting and fitting attachment.

Visually inspect the outboard side under the paratroop door sills for evidence of rust, powdery oxides, pitting, exfoliation, intergranular, stress corrosion, chipped and deteriorating paint and cracks.

Ensure all areas are free of sand, debris, other contaminants and ensure forward and aft drain holes are operational.

(1) Remove the access panel located on the outer fuselage below the paratroop door sill

(2) Visually inspect the two ends for breaks in the paint finish and evidence of corrosion along the longitudinal fastener line and/or skin joint

6-6 Change 18

6-4.1. FUSELAGE EXTERNAL. (Cont)

4. ACCESS PANELS AND SERVICING DOORS:

a. Visually inspect all external access and servicing doors for evidence of rust, powdery oxides, pitting, exfoliation, intergranular, stress corrosion, chipped and deteriorating paint and cracks.

(1) Skin surface

(2) Inspect all hardware for loose, missing and corroded fasteners (i.e.

rivets, screws, nuts, washers, bolts, etc)

(3) Ensure all areas are free of sand, debris and other contaminants

5. DEFLECTOR DOORS:

a. Visually inspect structural components for rust, powdery oxides, pitting, exfoliation, intergranular, stress corrosion, chipped and deteriorating…