Attach 5 Safety summary chapter 1.pdf

CHAPTER 1

GENERAL PREPARATION

SECTION I PREPARATION OF SURFACES FOR CORROSION INSPECTION

1.1 CLEANING THE AIRCRAFT.

Properly cleaning the aircraft is one of the most important factors in controlling airframe corrosion. Improperly cleaned surfaces can impede inspections for corrosion, cracks, and other defects. Clean surfaces are much less prone to corrode, and corrosion can substantially impact maintenance costs, non-availability hours, and operational readiness.

1.1.1 Frequency Requirement for Washing. Periodic

cleaning is the first step in an effective corrosion prevention program. The general factors which influence frequency in-clude environmental severity, aircraft mission profile, and cargo.

1.1.2 Standard Wash Requirements and Frequency.

Washing/cleaning shall be IAW Chapter 1, TO 1C-130A- 23CL-1, and TO 1-1-691.

1.1.3 Wash Waivers. When unique operational require-

ments or resource limitations severely impact the ability to wash as prescribed in TO 1-1-691, Table 3-1, submit a wash waiver request IAW Engineering Technical Assistance Re-quest (TAR) guidance in AFMCMAN 63-1202 and TO 00- 25-107. Requests shall include the aircraft’s current environ-mental severity, previous wash date, requested wash date, details pertaining to the inability to perform the wash, and any actions taken to pursue alternatives. The After-Wash Corrosion Inspection requirements contained in TO 1C- 130A-23CL-1, Chapter 5 shall be accomplished no later than the original wash cycle due date(s) during the waiver period.

Major Command (MAJCOM) coordination is required on the TAR. Aircraft undergoing Programmed Depot Mainte-nance (PDM) do not accrue time for wash intervals if they receive a wash IAW TO 1C-130A-23CL-1 during the PDM.

The wash cycle schedule shall be reset upon completion of the PDM.

1.1.4 Deployment Wash Requirements. Aircraft shall

be washed within 14 days prior to any deployment sched-uled to last for 30 or more days.

1.1.5 Operation in Environments with Increased Cor-

rosion Severity. When exposed to a severe environment for 20 or more days in a 30-day window, follow the “Severe” wash interval IAW TO 1-1-691, Table 3-1, until the comple-tion of the next wash after return to home station.

1.2 CLEANING EQUIPMENT PECULIAR ITEMS.

Observe the following limitations/restrictions when using general purpose equipment defined in Chapter 3 of TO 1-1- 691.

Rinse pressure shall not be boosted above that of normal tap pressure.

a. To ensure complete and rapid removal of cleaning so-lutions from exterior surfaces, the rinsing hoses shall have an inside diameter of 1-1/2 inches minimum. The purpose of the large diameter rinse hose is to provide a large volume of water, not pressure.

b. Use MA-1 spray equipment, barrel pumps, or foamers, mops, and soft bristle brushes to apply and agitate cleaning solutions. Refer to T.A. 480 and Chapter 3 and Appendix B of TO 1-1-691 for authorized wash rack equipment and materials.

Do not use steam cleaning equipment.

c. Always use hot water in a temperature range of 120 °F to 140 °F to wash and rinse the aircraft unless heated water can not be provided at the wash location. Depot facilities shall always use hot water.

1.3 AIRCRAFT COMPONENT REMOVALS RE-

QUIRED.

The following components shall be removed from the air-craft prior to exterior washing:

a. Deleted.

b. On the crash position indicator system, remove the RBA-6 airfoil and MT-3714A mount. Install the cover, and mask to prevent water entry.

TO 1C-130A-23

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Attach 5, Dec 11 2024

1.4 MASKING TO PREVENT WATER ENTRY.

Masking to prevent water entry could involve the covering, of very sensitive vents such as those of a fuel tank. For this reason it is important to re-move all such masking immediately after washing the aircraft. In the event that masking tape was left covering such vents, the function of the vent would be denied, resulting in possible failure of the tank to supply fuel to the engines or possible rupture of the tank structure during refueling.

Cleaning solutions and rinse water shall be excluded from sheltered areas of the aircraft by applying waterproof cover-ing and/or waterproof tape per the instructions in Chapter 3 of TO 1-1-691. Aircraft peculiar items are as follows:

a. Install weather excluding covers and plugs provided with the aircraft as defined in the applicable aircraft maintenance manual.

b. Apply waterproof tape over the seams separating the crash position transmitter and the adjacent surfaces if the transmitter is installed.

c. Cover static port holes.

d. On aircraft modified by TO 1C-130-949, prior to wash-ing the aircraft or stripping paint, the Universal Aerial

Refueling Receptacle/Slipway Assembly must be pro-tected. The unit may be masked and sealed off with waterproof tape and barrier paper, or it may be re-moved from the aircraft. It is absolutely imperative that no moisture, cleaning solvents or paint remover be al-lowed to enter the unit. For removal and installation procedures, refer to TO 1C-130H-2-28JG-50-1.

e. On aircraft modified by TO 1C-130-1323, TO 1C-130- 1388, TO 1C-130-1465, TO 1C-130-1466, all AC- 130W aircraft, and aircraft AF91-01231 and up, apply waterproof tape over seam around defensive system flare and chaff dispensers.

f. Install protective covers on All Light Level Television (ALLTV), Infrared Detection System (IDS), FWD scanner and AFT observer windows. (On aircraft modi-fied by TO 1C-130(A)U-665). Install waterproof cov-ering using waterproof tape to cover the Multispectral Television (MTV) turret assembly. Do not apply any tape to the turret windows.

g. Deleted.

h. Deleted

i. On AC-130W aircraft, install waterproof covering us-ing waterproof tape over gun pressure seals.

j. On aircraft equipped with ALQ-157, cover the ALQ- 157 transmitters and place a masking tape barrier on the connectors behind the air deflector doors.

A1901696

Figure 1-1. Typical Washing Facility

TO 1C-130A-23

1-2

k. On aircraft modified by TO 1C-130-1818, TO 1C-130- 2092, TO 1C-130(A)U-662, or TO 1C-130(M)H-649 and AC-130W aircraft, prior to washing the aircraft or stripping paint, the AN/AAQ-24 transmitters, sensor units, and fairings must be protected. The units may be masked and sealed off with plastic bags or locally manufactured covers, or they may be removed from the aircraft. It is absolutely imperative that no mois-ture, cleaning solvents or paint remover be allowed to enter the unit. For removal and installation procedures, refer to TO 1C-130H-2-99JG-10-6, TO 1C-130-2- WA-2, or TO 1C-130(M)H-2-99JG-10-8.

l. On AC-130W aircraft, install covers and plugs on 30MM gun, 105MM gun, and Standoff Precision Guided Munitions (SOPGM) portals.

1.5 EXTERIOR WASHING SEQUENCE.

Ensure that all drain holes are open and operative and then proceed in accordance with the sequence indicated in Figure 1-2. The following materials are approved for full exterior wash, MIL-PRF-87937, Type IV cleaning solution (one part cleaning solution and four parts water) and MIL-PRF-85570, Type I and II. See TO 1-1-691 for additional instructions for the use of these materials and for specific area cleaning in-structions. Clean the exterior surface area by area, starting at the lower surface and working upward. Squeegee off any water that does not readily drain from the surface as required to avoid skin stains similar to those shown in Figure 1-3.

After exterior washing is complete, the windshields and win-dows may be cleaned with SAEAMS-1535, Window Jetkleer and Aero Clean X-405 or X-405 Electronic Flight Instru-ment Systems (EFIS) are authorized as listed in Chapter 9 of this manual.

1.6 LOCAL INTERIOR CLEANING.

Interior areas of the aircraft subject to the accumulation 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 fin-ishes originally applied. See Figure 1-4 for typical soil accu-mulation. Areas of the aircraft where such accumulations may occur are:

a. The wing-to-fuselage fillets discussed in Chapter 3, Item No. F-2, form a trap for dirt and debris under the wing leading edge-to-fuselage fillet, where no drainage provisions are provided. At the general cleaning cycle, remove the forward panel assembly on the fuselage under the wing to gain access to the compartment un-der the fillet. Access is available through the small hole in the bulkhead frame just forward of the removed ac-cess panel. Vacuum loose debris from the compartment using a thin tube wand. The task is not easy because of the duct installation a few inches aft of the access hole.

• Cleaning compound MIL-PRF-87937 may af-fect skin, eyes, and respiratory tract. Use in a well ventilated area. Industrial safety goggles or face shield, and neoprene gloves shall be worn. Personal injury could result.

• MIL-DTL-85054 and Cor-Ban 35 Corrosion Preventive Compounds (CPCs) are flammable and toxic to the skin, eyes, and respiratory tract.

Avoid skin and eye contact. Good general ven-tilation is normally adequate. Keep away from open flames or other sources of ignition.

b. Engine dry bays become soiled from carbon residues.

During each depot maintenance, thoroughly clean inte-rior of all dry bays aft of the engines using water. Wash the dry bay interior using clean rags. Dry the area us-ing clean, dry rags. During cleaning of dry bays, if more aggressive cleaning is required, use MIL-PRF- 87937, Type IV, as directed by TO 1-1-691. Do not use large volume of water. Dry the area by wiping with clean dry rags. Ensure that all cleaning solution is re-moved and no residue remains. Apply a light coat of Cor-Ban 35 (Preferred) or, MIL-DTL-85054, Type IIA by brushing or spraying with a non-aerosol pump sprayer to areas where the coating system is cracked, missing or damaged.

c. Give particular attention to floor chine caps and the troughs at the entrance doors when cleaning the inside of the fuselage. Clean the dirt from the wells and radii.

Vacuum up as much of the loose debris as practical to prevent it from falling into and becoming trapped in crevices below the door threshold. Periodically, floor boards shall be removed for thorough cleaning of un-derfloor structure, using MIL-PRF-87937, Type IV cleaning compound as prescribed in TO 1-1-691.

d. Remove loose soils in the flight compartment, cargo ramp, and ramp 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 four to one solution of water and MIL-PRF-87937, Type IV or A-A-59921, Class 1A cleaner. Clean the mop frequently. Use a stiff bristle brush to remove stubborn soils. DO NOT use high volumes of water inside the aircraft. Ensure the floor, including all tie down receptacles are thoroughly dry.

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

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On AC-130W aircraft, ensure water spray is not directed at the Standoff Precision Guided Muni-tions (SOPGM) equipment and portals.

(1) Pressure is limited to no more than 500 PSI.

(2) Water temperature is limited to 120 °F.

(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 com-partment.

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

(6) On AC-130W aircraft, tape off and plug SOPGM portals.

(7) Mask off any electrical or hydraulic equipment which could be made wet by spray or mist during cleaning operations. Ensure water cannot get be-hind insulation blankets.

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

(9) After completion of cleaning operations, ensure the cargo floor is completely dried and chine cov-ers are dry and free of dirt/debris.

f. Periodically remove and clean soundproofing with MIL-PRF-87937, Type IV or A-A-59921 Class 1A cleaner.

• Cleaning compounds MIL-PRF-87937 and A-A-59921 cleaners are toxic to skin, eyes, and respiratory tract. Avoid skin and eye contact.

Good general ventilation is normally adequate.

• MIL-DTL-85054, Type IA and Cor-Ban 35 CPC are flammable and toxic to the skin, eyes, and respiratory tract. Avoid skin and eye con-tact. Good general ventilation is normally ad-equate. Keep away from open flames or other sources of ignition.

g. Clean the sloping longerons, fuselage station 737 to 1041.5, and the aft fuselage station 737 bulkhead (when accessible) with MIL-PRF-87937, Type IV cleaner so-lution, or A-A-59921 Class 1A cleaner, followed with MIL-PRF-87937, Type IV cleaner solution, in accor-dance with TO 1-1-691. Then apply Cor-Ban 35 (Pre-ferred) or MIL-DTL-85054, Type IA CPC to the slop-ing longeron areas.

h. Clean all accessible areas of the cargo ramp edges and attach area with MIL-PRF-87937, Type IV cleaner so-lution in accordance with TO 1-1-691. Inspect all drainage paths in the cargo ramp to ensure that drain holes are free of obstructions.

1.6.1 Disinfecting. For C-130 aircraft interiors that require disinfection, use Calla® 1452 manufactured by Zip-Chem® Aviation Product or other general disinfectants approved by TO 1-1-691. Use IAW manufacturer’s instructions, the fol-lowing steps/guidelines, and Bioenvironmental Engineering.

If these products are not available, general disinfection with a 70% solution of Isopropyl Alcohol IAW TO 1-1-691 is an acceptable alternative; observe all cautions, warnings, and notes regarding the use of Isopropyl Alcohol in TO 1-1-691.

• Personnel Protective Equipment (PPE) shall be worn. Work with local bioenvironmental engineer-ing to determine PPE requirements.

• Ground and cleaning crews shall not board the air-craft until all personnel have disembarked.

• Cleaning teams shall be trained on and demonstrate an understanding of when to use PPE, what PPE is required, how to properly don and doff PPE.

• After doffing PPE, cleaning staff shall immediately clean hands with soap and water for at least 20 sec-onds. If soap and water area not available and hands are not visibly dirty, an alcohol-based hand sanitizer that contains at least 60% alcohol may be used.

However, if hands are visibly dirty, always wash hands with soap and water.

• Cleaning crews shall be provided with alcohol-based hand sanitizer for personal use.

• Cleaning crews shall immediately report breaches in PPE (e.g., tears in gloves etc.,) or any potential exposures (e.g., contact with blood or bodily fluids without wearing appropriate PPE) to their supervi-sor.

• Cleaning crews shall dispose of PPE and other dis-posable items used in cleaning.

• Cleaning crews shall immediately notify their su-pervisor if they develop symptoms.

1-4 Change 5

Do not spray flammable solvents/disinfectants.

Hand pump trigger spray bottles and low pressure coarse sprayers may be used to spray non-flam-mable disinfectants only. Do not use synthetic wiping cloths with flammable solvents/disinfec-tants such as TT-I-735 Isopropyl Alcohol (IPA).

Ensure electrical power is removed IAW TO 1C- 130H-2-00JG-00-1 prior to disinfecting. Open crew door and lower ramp for circulation while disinfecting. Following disinfection, allow aircraft to be properly ventilated before applying power to the aircraft. Solid streaming, or anything close to a solid stream, of disinfectant is not authorized and may cause damage to aircraft avionics/elec-tronics and otherwise affect aircraft safety, opera-tions, and availability. Avoid pointing atomizing nozzles/equipment directly on or at aircraft avion-ics/electronics equipment.

a. Methods

(1) Definitions

(a) Cleaning. Physical removal of visible surface contaminants.

(b) Disinfecting. Application of liquid chemicals to a surface to kill pathogens.

(2) N/A

b. Requirements

(1) Prohibited Materials. The following commonly used materials are prohibited and shall not be used on any area of the aircraft or aircraft hardware:

(a) Chlorine Bleach

(b) Hydrogen Peroxide

(c) Quaternary Ammonium

(d) Chlorine Dioxide

(2) Post Treatment. Refer to manufacturer’s instruc-tions for post cleaning requirements.

(3) Effectiveness (efficacy) Refer to the Centers for Disease Control (CDC) or the Environmental Pro-tection Agency (EPA) for guidance on contact time for a specific target contaminant. Where ef-ficacy of a disinfectant has not been validated by the CDC or the EPA for a target contaminant, consult the World Health Organization (WHO) or locally recognized public health organization.

(4) Hazardous Materials. Materials referenced in this section may be hazardous. Refer to the Safety Data Sheets (SDS) for safe use conditions and proper Personal Protective Equipment (PPE).

(5) Equipment

(a) Cloths and Wipes. Use cloths in accordance with Table 1-4 to apply cleaning and disin-fecting solutions by wipe methods. Wipes pre-saturated with solutions listed in the specification may also be used when available.

Table 1-1. Cloths and Wipes

Material Specification Cotton Cleaning Cloths Commercial Cotton Cleaning Rags A-A-2522, CID Cotton Shop Towels AMS3819, Class 1, Grade A Synthetic Shop Towels Shop Towels AMS3819, Grade B, Class 1 or 2

Do not use sprayers near flammable materials and avoid solid stream nozzle settings.

(b) Sprayers. When surface wetting is allowed for a given substrate as indicated in Tables 1-6 and Table 1-7, cleaning and disinfecting products may be applied using any suitable hand pump or other lowpressure sprayer in accordance with manufacturer’s instructions.

Protect any areas or materials not suitable for spraying.

(c) Barrier Materials. Suitably protect areas where the application of products is not re-quired or would be detrimental. Use water-proof paper or polyethylene plastic sheet and pressure sensitive waterproof masking tape

Change 5 1-4.1 found in Table 1-5. Plugs and covers may also be used, provided a watertight barrier is achieved. The use of polyvinylchloride plas-tic sheet material is prohibited. It can degrade when exposed to sunlight or heat and subse-quently react with moisture to form hydro-chloric acid.

NOTE

Barrier material has a waterproof side that should be placed against the aircraft to protect the area.

Table 1-1.1. Barrier Materials

Material Specification Barrier Material MIL-PRF-121, Type II

MIL-PRF-131, Class 1 or 2 Masking Tape SAE AMS-T-21595 or SAE AMS-T-22085, Type II

The use of electrostatic sprayers is very technique dependent. Special attention must be given to pre-vent pooling or running (dripping) of fluid on the surfaces being sprayed. Failure to monitor appli-cation levels could result in damage to, or destruc-tion of, equipment or loss of mission effective-ness.

(d) Electrostatic Sprayers. Electrostatic sprayers may be used that charge disinfectant as it passes through the nozzle. The positively charged droplets are attracted to negatively charged environmental surfaces allowing for improved coverage on hard, non-porous sur-faces. This equipment conserves disinfectant and decreases time for manual application.

Operators must be properly trained and ca-pable of applying chemicals in a manner that avoids pooling, running (dripping), crazing, etc. prior to using them on an aircraft. The operating distance from the nozzle of the sprayer to the decontamination target varies by electrostatic sprayer and sprayer settings which must be determined prior to use. Ap-plication of disinfectant by electrostatic sprayer method can be highly variant in spray pattern shapes and diameters between manu-facturers/models of electrostatic sprayers and are also affected by application procedures and operators. Therefore, it is preferred that each maintenance unit not use sprayers with different characteristics that would cause con-fusion with operators and require separate hands-on training. Only System Program Of-fice (SPO) approved electrostatic sprayers shall be used.

1 Approved Equipment. The following elec-trostatic sprayers have been approved, along with corresponding surface wetness strips used to ensure dwell time is achieved for efficacy. It is not recommended to use alternative electrostatic sprayers without testing certain specifications including:

spray diameter, spray density, spray repeat-ability, efficacy against a target microor-ganism, and electrical compatibility. Con-tact SPO engineering if desiring to use an alternative sprayer.

a. EMist™ EM360™ Cordless Backpack Electro-static Disinfectant Sprayer. -Use EMist™ EM360™ with the nozzle of the sprayer approxi-mately 3.5 feet from the surface. Maintain con-stant movement of the nozzle.

2 N/A

(e) Hydrion® Water Finding Test Paper

• Hydrion® Water Finding Test Paper is recommended to monitor surface wetness in order to achieve 10-min-ute minimum dwell time. The test pa-per uses a chemically treated paper which reacts in the presence of disin-fectant or water to change color. The degree of color change can be used to quantify the amount of disinfectant applied to a surface.

• Test strips are commercially avail-able, as required.

• When wet, the strips turn from white to bright pink. It is recommended to reapply disinfectant when the strip begins to pale in color.

• The drying times of the strips do not directly correlate to the drying times of all surfaces within aircraft (e.g., 1-4.2 Change 5 aluminum vs. porous materials), es-pecially when considering extremes in environment conditions (i.e., high humidity).

• Test strips are considered a valid in-dicator of drying on solid, non-porous surfaces for disinfectant re- applica-tion. The color change of Hydrion® strips between suitable liquid present (bright pink) and no liquid present (white).

c. Preparation Procedures. Prior to disinfecting the inte-rior of the aircraft, the aircraft must be ventilated in accordance with AFI 48- 107V1, Table A14.1. Run the air conditioning system in accordance with TO 1C-

130H-2-21JG-00-1, 21-00-1.

(1) Mixing procedures. Materials purchased as a con-centrate shall be mixed in accordance with manu-facturer’s instructions. Ready to Use (RTU) ma-terials shall be applied as purchased.

(2) Decontamination Methods and Products.

Disinfectant concentrate is toxic to skin and eyes.

Skin and eye protection is required.

(a) Cleaning. Cleaning shall be performed in ac-cordance with the applicable procedure from Table 1-6, when necessary. One or more of the applicable products listed may be used.

Some of the approved cleaning methods may also be effective for disinfecting depending on the type of contamination. See effective-ness (efficacy) section.

Table 1-1.2. Cleaning Materials and Applicable Methods

Material Applicable Methods/Products Stainless Steel

Solvent Clean Carbon and Low Alloy Steel Aluminum Titanium Copper Plastics and Acrylics – Including Transparent and Opaque (1)

Wipe with cloth and MIL-PRF-87937 or Aliphatic Naphtha, TT-N-95, Type II SAE-AMS1535 Cleaner, Zip-Chem X-405 and

X-405 EFIS

Glass SAE-AMS1535 Cleaner, Zip-Chem X-405 and

X-405 EFIS

LCD Screens/Electronic Flight Instrument Systems

(EFIS)

SAE-AMS1535 Cleaner, Zip-Chem X-405 and

X-405 EFIS

Rubber/Vinyl (2) Wipe with TT-I-735 Grade A or ASTM D770 IPA Painted metallic surfaces Solvent Clean Airplane exterior MIL-PRF-87937

MIL-PRF-85570

Fabrics Use mild detergent to launder or spot clean Thermoset plastics and unpainted composite surfaces

Solvent Clean

Notes:

1. Precautions for cleaning of transparent plastics: To prevent scratching, rub lightly until dry. Under no circumstances shall any other solvent, or compound be used on or in contact with plastic. Use of any other cleaners or materials in contact with the plastic may result in surface crazing or cause delayed catastrophic failure.

2. Do not apply to surface or allow to dry on surface; wipe on with clean cloth.

Change 5 1-4.3

NOTE

In the event that the aircraft has been used to haul plants, live animals or poultry, or if there is evi-dence of rodents aboard, or if disinfection is nec-essary, spray or mop the cargo floor with a germi-cide/disinfectant in accordance with Table 1-7.

Follow manufacturer’s mixing instructions for proper solution.

(b) N/A

1.6.1.1 Disinfecting Procedures. Disinfecting materials

shall be applied as directed by the manufacturer. Efficacy may be dependent upon method of application and surface wet time. See Table 1-7 for approved materials by substrate.

Table 1-1.3. Disinfecting Material and Methods

Substrate Disinfecting Product Procedure Painted and unpainted metallic surfaces including aluminum, titanium, carbon steel, and cadmium plated steel

Calla 1452 Manufacturer’s Instructions 70 percent Isopropyl Alcohol 1.6.1.1.a.(1) 62-71 percent Ethanol 1.6.1.1.a.(1)

Plastic and Acrylic (1) Calla 1452 Manufacturer’s Instructions Rubber and vinyl (2) Calla 1452 Manufacturer’s Instructions Glass 70 percent Isopropyl Alcohol 1.6.1.1.a.(1) Avionics, Displays, Display Screens, Touch Screens, Head Up Displays. Screens with Films

(3) (4) (5)

70 percent Isopropyl Alcohol 1.6.1.1.a.(2)

Fabrics (6) Calla 1452 Manufacturer’s Instructions Unpainted composite surfaces 70 percent Isopropyl Alcohol 1.6.1.1.a.(1) Notes:

1. Do not use Ethanol or Isopropyl alcohol to disinfect acrylic surfaces or plastic surfaces.

2. Do not Isopropyl alcohol on sulfide-based elastomers.

3. Do not spray liquid directly on avionics screens; apply liquid to a wipe first.

4. Isopropyl alcohol only approved for use on C-130 Heads Up Displays.

5. Includes anti-glare, anti-reflective and anti-impact films.

6. Do not use Isopropyl alcohol on nylon.

TT-I-735 and ASTM DD-770 isopropyl alcohol is highly flammable and toxic. Good general ventila-tion is normally adequate. Skin and eye protection is required. Avoid all sources of ignition.

a. Wipe down disinfecting procedures.

(1) Disinfecting Using Isopropyl Alcohol and Etha-nol. Apply liquid to a cloth or use a pre-saturated wipe to wipe the affected area. Do not pour the liquid directly onto the surface. Reapply as nec-essary to keep wet for a wet time sufficient for effectiveness (efficacy), see Disinfecting Require-ments. Allow surface to air dry or wipe dry with a clean cloth.

1-4.4 Change 5

Do not spray liquid directly on avionics or electri-cal equipment. Turn off all avionics and electrical components that will be disinfected.

(2) Avionics Specific Procedures.

NOTE

Use a pre-saturated wipe with at least 70 percent Isopropyl alcohol solution. Reapply alcohol as necessary to keep wet for a contact time sufficient for efficacy. If pre-saturated wipes are not avail-able, spray Isopropyl alcohol on paper towel, tech wipe or similar product until damp but not satu-rated.

(a) Dampen surface with the towelette (i.e., key-board, monitor, console panels, etc.). Leave the surface visibly damp and allow it to air dry. After an extended dwell period, wipe re-sidual liquid clean with tech wipe, paper towel or equivalent.

(b) N/A

(3) To disinfect inanimate, hard, and non-porous sur-faces, mix general disinfectants IAW manufactur-er’s instructions.

(4) Apply solution with a mop, cloth, sponge, hand pump trigger sprayer, low pressure coarse sprayer.

(5) Surfaces shall be thoroughly coated to ensure sur-faces remain wet for period of time suggested by the manufacturer or local authority. Over satura-tion is acceptable to ensure surfaces remain wet.

After a dwell period sufficient for effectiveness (efficacy), wipe residual liquid clean/dry.

(6) Clean porous (soft) surfaces (e.g., seat covers) by removing spots and/or areas of visible contamina-tion if present and using appropriate cleaners that are compatible with aircraft surfaces. For items that can be laundered, use the warm setting and dry items completely on high heat.

(7) Following all spot cleaning and laundering, thor-oughly spray the entire area using a disinfectant from Table 1-7 ensuring complete coverage and saturation of seats, seatbelts, ensuring the lower/ bottom surfaces are covered. Follow the manu-facturer’s instructions for the efficacy of fabrics.

(8) Focus on high-touch non-porous (hard) surfaces, including armrests, plastic and metal parts of the seats and seatbacks, tray tables, seat belt latches, loadmaster lighting cargo and hydraulic system (cargo ramp and door) controls, overhead com-partment handles, adjacent walls, bulkheads, win-dows and all galley equipment.

(9) Lavatory/Urinal Specific Procedures.

(a) Clean toilet/urinals, including toilet platform locking device, toilet platform and toilet seat.

(b) Clean urinal lid, tank outer surfaces, and floor area around urinals.

(c) Clean the servicing pan internal area, drain cover, charge fitting, control lever, and ac-cess door after the toilet has been serviced.

(10) Properly dispose of any items that cannot be dis-infected and/or cleaned (e.g., pillows, safety plac-ards, and other similar items).

b. Electrostatic Sprayer Procedures

Do not use flammable materials such as Isopropyl alcohol or ethanol in electrostatic sprayers. Only use approved, non-flammable, disinfectants. Fail-ure to comply may result in injury to personnel and damage to the aircraft.

Do not use electrostatic sprayers with power on aircraft or with any wiring disconnected or when maintenance is occurring. Do not use electrostatic spray equipment on the flight deck. Due to typical overspray, avoid spraying within 2 feet of sensi-tive equipment, such as screens, displays, LRU’s, control panels, lights, non-shielded wiring, and outlets.

NOTE

Portable light fixtures will need to be used inside aircraft during disinfection. The use of tripod light fixtures in cargo compartment can provide suit-able illumination. Hands-On Training must be completed prior to use on aircraft.

(1) Mix disinfectant per manufacturers recommenda-tions prior to filling sprayer tank.

(2) Operating EMist™ EM360™ Electrostatic Spray-ers

Change 5 1-4.5

(a) Fill backpack tank with mixed disinfectant solution.

(b) Install fully charged battery.

(c) Put on backpack and grounding strap in ac-cordance with manufacturer’s instructions.

(d) Test electrostatic sprayer operation off-air-craft to verify functionality.

1 Depress the applicator power button until the green light displays.

2 Once the applicator trigger switch is de-pressed, the fan will turn on first, followed by the liquid spray.

3 Verify that Hydrion® Water Finding test paper is still effective by verifying color change when contacted with fluid.

4 The yellow LED signifies that the high voltage power supply is charging the liq-uid.

5 Once the applicator trigger is released, the liquid will stop and the fan will turn off after a slight hesitation to ensure the liquid is cleared inside the applicator.

(e) Use EMist™ EM360™ with the nozzle of the sprayer 3.5 feet from the surface using constant movement of nozzle. Maintain stand-off distance from end of sprayer nozzle to application surface. Drips and runs will occur if sprayer is too close to the surface, and when too far, the particles will not reach and properly wet the surfaces.

(3) Spray the surface using a sweeping motion using an “S” pattern, with a 50 percent overlap to en-sure consistent coverage. Avoid over application resulting in drips and runs.

(4) Additional passes may be required to achieve 10-minute minimum dwell time to achieve efficacy.

Limit spraying to two passes with 2-3 minute in-tervals between each pass. Move the nozzle at approximately 3 feet per second.

(5) Significant overspray will be present 2 feet in ei-ther direction from the center line of the spray.

Do not spray within 2 feet of surfaces which shall not be contacted by disinfectant.

(6) Keep electrostatic spray/overspray away from electrostatic discharge susceptible components, instrumentation, or displays. Charged spray is ca-pable of inducing voltages on nearby, electrically isolated objects. This is not a concern for shielded wiring but is a concern if this wiring is discon-nected and connectors are exposed to spray. En-sure no maintenance is occurring during electro-static sprayer use. Do not spray electrical outlets or wires with cracked insulation.

(7) The disinfectant manufacturer recommended dwell time for the specific chemical being sprayed must be achieved. For most disinfectants, the manufacturer recommended dwell time is 10 min-utes.

(8) Dwell times can vary based on temperature, hu-midity, air flow, etc. If there is difficulty achiev-ing required dwell times, steps can be taken to reduce air flow in the aircraft, increase humidity, or decrease the ambient temperature. Additional passes may be used to maintain surface wetness and increase the dwell time.

(9) When the surfaces are 30 percent dry, reapply disinfectant. Keep at least 70 percent wet for the full dwell time stated.

(10) There will be differences in spray patterns and dwell times based on operators. Use Hydrion® Water Finding Test Paper strips to permit surfaces to be visually monitored as operators become fa-miliar with the electrostatic spraying process.

1-4.6 Change 5

1.7 PAINT REMOVAL PROCEDURES PECULIAR

TO THE AIRCRAFT.

Use extreme care in protecting high strength steel materials when paint removal operations are per-formed.

1.7.1 Paint Remover Compounds. Most paint removal

compounds authorized for use on aircraft by TO 1-1-8 will attack sealing compounds, adhesives, plastics, fabrics, and rubber. Unless specified by TO 1-1-8 as being safe for use on high-strength steel, regard a paint stripping compound as being hydrogen embrittling to the steel. Refer to Section III of Chapters 2 through 6 for locations of high-strength steel parts on the aircraft. (See Figure 1-5.)

1.7.2 Masking. Masking prior to paint removal shall be in

accordance with procedures in Chapter 2 of TO 1-1-8 except as noted in this manual. All items discussed in paragraph 1.4 shall be masked as well as all items indicated in Figure 1-6.

All hinges, all openings, all propellers, all seams on pylons and engines, all antennas, all fairing-to-skin lap-type seams, and all seams around doors, hatches, and removable panels shall be masked. When the paint on the auxiliary longerons (FS 737 to FS 1041), or attach fittings is to be removed, joint areas shall be masked. Areas to be protected from damage caused by contact with paint removal compounds shall be masked with barrier protective materials prescribed in Chap-ter 2 of TO 1-1-8, and masked with masking tape, SAE AMS-T-23397, Type II (72 hour protection) or 3M425 only.

Examples of areas requiring mask which are peculiar to the aircraft are:

Change 1 1-5

A1901697

STEP 3. WASH FORWARD FUSELAGE:

(a) WASH UNDER SURFACES FIRST, PROGRESSING

UPWARD. START AT MID-FUSELAGE AND SPRAY

FORWARD.

(b) SCRUB IN CLEANING SOLUTIONS IN SEQUENCE.

NOTE: ALL AREAS MUST BE KEPT WET WITH

CLEANING SOLUTIONS OR WATER AT ALL TIMES.

RINSE OFF ALL OVERSPRAY OF SOLUTIONS.

(c) RINSE FROM TOP TO BOTTOM.

STEP 4. WASH AFT FUSELAGE:

NOTE: KEEP AREAS WET, EITHER WITH CLEANING

SOLUTION OR WATER AT ALL TIMES.

(a) WASH THE UNDER SURFACE FIRST (CARGO

RAMP AND DOOR), PROGRESSING UPWARDS.

(b) RINSE FROM TOP TO BOTTOM.

STEP 2. WASH MID-FUSELAGE:

NOTE: THIS SHOULD BE DONE IN CONJUNCTION

WITH WING IF POSSIBLE.

(a) WASH THE UNDER SURFACE FIRST, PROGRESSING UPWARD.

NOTE: KEEP AREAS WET, EITHER WITH

SOLUTIONS OR WATER AT ALL TIMES.

(b) RINSE FROM TOP TO BOTTOM.

STEP 1. WASH WHEEL WELLS:

(a) WASH WHEEL WELLS, CONCENTRATING FIRST

ON THE INTERIOR WELL STRUCTURE.

(b) CLEAN LANDING GEAR COMPONENTS.

(c) RINSE.

STEP 5. WASH EMPENNAGE:

NOTE: KEEP ALL SURFACES WET, EITHER

WITH SOLUTIONS OR WATER AT ALL TIMES.

(a) WASH BOTTOM OF HORIZONTAL STABILIZER.

(b) WASH TOP OF HORIZONTAL STABILIZER.

(c) WASH VERTICAL TAIL, 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.

Figure 1-2. Exterior Washing Sequence (Sheet 1 of 2)

1-6

A1901698

WASH WINGS:

WASH THE LOWER AND THEN THE UPPER SIDE OF WINGS.

START AT CENTER AND MOVE TOWARD WING TIPS. RINSE

TOWARD CENTERLINE.

NOTE: KEEP THOSE AREAS PREVIOUSLY CLEANED WELL

FLUSHED WITH WATER DURING WASHING UPPER WING.

STEP 6.

ON COMPLETE AIRCRAFT WASH OPERATION, FLUSH DOWN ALL

AIRCRAFT EXTERIOR SURFACES TO REMOVE RESIDUAL

CLEANING SOLUTIONS.

STEP 7.

AFTER EACH AIRCRAFT WASHING. SAE AMS-1659 SOIL BARRIER

MAY BE APPLIED TO FLAP WELLS, EXHAUST PATHS AND LANDING

GEAR WHEEL WELLS AT THE USER'S OPTION. (SEE CHAPTER 3,

TO 1-1-691). NO MASKING IS NECESSARY FOR APPLICATION OF

THE SOIL BARRIER COATING. HOWEVER, PRECAUTION AND CARE

SHOULD BE USED TO AVOID AS MUCH AS POSSIBLE, SPRAYING

MOVING PARTS SUCH AS LANDING GEAR STRUTS, BEARINGS,

FLAP SCREW JACKS AND TRACKS OR PLEXIGLAS/WINDOWS OR

ELECTRICAL CONTACT FAYING SURFACES. INADVERTENT LIGHT

SPRAY ON THESE AREAS SHOULD CAUSE NO PROBLEMS.

STEP 8.

DELETED.STEP 10.

RELUBRICATE FUNCTIONAL SURFACES:STEP 9.

DELETED.STEP 12.

AFTER EACH AIRCRAFT WASHING ON AC-130W AIRCRAFT: LUBRICATE

30MM AND 105MM GUNS PER TO 1C-130(A)W-2-94GS-00-1 AND

TO 1C-130(A)W-2-94JG-50-1.

STEP 11.

Figure 1-2. Exterior Washing Sequence (Sheet 2)

Change 3 1-7

MIL-C-83982 was cancelled in December 1996 and replaced by MIL-PRF-81733, Class 1, Grade A, Type II.

a. Seams between attaching wing panels, except on air-craft AF73-01580 and up. These aircraft and some ear-lier modified production aircraft have polyurethane sealant MIL-C-83982 (Goodrich PL410 sealant with PL106 primer) which resists paint remover.

b. Seams between wing panels and spar caps, except for these aircraft denoted in paragraph a above and aircraft fabricated after December 1996.

c. Seams around access doors and panels.

d. Over edges of the bonded-beaded panels.

e. Over the gap between the wing joint attachment (rain-bow) fitting and the skin panels at WS 220. (See Item No. W-3.)

f. Seams on upper surfaces of horizontal stabilizer and each side of the vertical stabilizer shall be masked.

g. Deleted.

h. Forward and Aft Scanner windows.

i. On AC-130W aircraft, 30MM and 105MM gun barrels and pressure seals.

j. On AC-130W aircraft, SOPGM portals.

1.7.3 Paint Removal. Use the materials and procedures

authorized in Chapter 2 of TO 1-1-8 for removing paint from all structure with the following exceptions:

Use extreme care when stripping paint near AN/ AAQ-24 sensor fairing and RAM. Do not use abrasive blasting on Sensors, Fairing or RAM.

a. When removing paint from the aircraft, the skin seams on the fuselage, the lower wing surface panel seams, and the lower surface seams on the horizontal stabi-lizer need not be masked.

A1901699

SURFACE ETCHED OR STAINED

BY UNAUTHORIZED CLEANING

COMPOUNDS.

Figure 1-3. Skin Stains From Unauthorized Cleaning Compounds

1-8 Change 3

Acetone (ASTM D329) is flammable toxic to the skin, eyes, and respiratory tract. Skin and eye pro-tection is required. Avoid prolonged contact. Use only with adequate ventilation Personal injury could result.

b. When removing paint from bonded-beaded panels, use tape over edges of bonded surfaces and over drain holes. Clean the remaining paint after tape removal using (ASTM D329) acetone.

1.8 SEALANT REMOVAL.

NOTE

• When required, adhesion promoters shall be used in accordance with Chapter 6 of TO 1-1- 691.

• SAE AMS-3265, Type I or II, Class 1, Grade B, or MIL-PRF-81733, Type I or Type II, Class 1, Grade B, non-chromate corrosion inhibiting sealant may be used as an alternate for MIL-

PRF-81733.

When an aircraft is completely stripped and repainted, all exterior seams shall be inspected to determine if the sealant is damaged, deteriorated, or missing. Damaged, deteriorated, or missing sealant shall be replaced with a fillet type seal of MIL-PRF-81733, Class 1, Grade A, Type II. Refer to Section VII of this chapter and Chapter 6 of TO 1-1-691 for instruc-tions on use of sealant. Refer to TO 1C-130A-3 for aircraft peculiar requirements on sealant application. Locations on the aircraft that shall be sealed include:

a. Upper and lower wing panel seams (including leading and trailing edges).

b. Horizontal and vertical stabilizer panel seams (includ-ing leading and trailing and edges).

c. Flap panel seams.

d. Antennas.

e. Anti-collision lights.

f. External doublers.

g. Control surfaces (ailerons, rudder, elevators).

h. Fuselage panel seams.

i. Exterior fillets and gaps of cargo door skin panels.

A1901700

DRY BAY (TYP)

IN

BD

Figure 1-4. Dry Bay Cleaning

1-9

A1901701

Figure 1-5. Paint Stripping

1-10

A1901702

OUTER WING LOCATION, AIRCRAFT PRIOR TO AF73-01580 NOT

MODIFIED BY TO 1C-130-1039.

NOTENOTE

Figure 1-6. Masking of Surfaces for Paint Stripping (Sheet 1 of 2)

1-11

A1901703

E

NACELLE AND EXTERNAL FUEL TANKS

NACELLE AND PROPELLER

MASKING FOR PARTIAL STRIPPING

NACELLE AND PROPELLER

PIANO HINGES

DRY BAY ACCESS DOORANTENNA

SCUE

Figure 1-6. Masking of Surfaces for Paint Stripping (Sheet 2)

1-12 Change 3

Figure 1-7. Deleted

Change 3 1-13

A1901705

RH AFT MWS SENSOR

LH AFT MWS SENSOR

LH AND RH AFT AND DNWRD SENSORS

DNWRD MWS SENSOR

RH AND LH FWD SENSORS

RH

LH

Figure 1-8. AN/AAQ-24(V) System Sensor Locations (Paint Stripping) (MC-130H Aircraft Modified by TO 1C-130(M)H-649)

1-14

A1901706

RIGHT

AN/AAQ-24(V)6

SENSOR

FAIRING

WINDOW FASTENERS

TRIM ON INSTALLATION

TO PROVIDE A MINIMUM

0.20 INCH CLEARANCE

FORWARD FUSELAGE UPPER SURFACE

VIEW LOOKING DOWN

AN/ALQ-172

OMNI-DIRECTIONAL

LOW-BAND ANTENNA

RADOME

LEFT

AN/AAQ-24(V)6

SENSOR

FAIRING

Figure 1-9. Radar Absorbing Material (RAM) Locations

Change 1 1-15

A1901707

4 3

1. RH FWD MISSILE WARNING SENSOR

2. LH FWD MISSILE WARNING SENSOR

3. RH AFT MISSILE WARNING SENSOR

4. LH AFT MISSILE WARNING SENSOR

5. DNWRD MISSILE WARNING SENSOR

Figure 1-10. AN/AAQ-24(V) System Sensor Locations (Paint Stripping)

1-16

A1901708

0.25

0.50 (STD. PIPE THREAD)

0.625 DIA.

0.188 DIA. (FOUR PLACES)

Figure 1-11. Drain Tool for Condensate Drain Valves

1-17

SECTION II CORROSION INSPECTION METHODS

1.9 GENERAL.

Inspecting for corrosion can involve a visual examination, a testing procedure, or both. Testing procedures discussed in this manual pertain only to nondestructive inspection meth-ods. Regardless of the inspection procedure employed, sur-faces shall be adequately clean for performing the test and/or examination. Frequency of performance is specified in TO 1C-130A-6.

1.10 VISUAL INSPECTION.

Visual examination is accomplished on surfaces exposed to view, using the naked eye or with the aid of a magnifying glass of 10 to 30 power. A good light source, such as a flashlight, is necessary when performing visual inspection for corrosion on aircraft structure.

1.11 NONDESTRUCTIVE INSPECTION TECH-

NIQUES.

There are five techniques in common use excluding visual which are applicable and acceptable for aircraft alloys. These techniques and support equipment are as follows:

1.11.1 Fluorescent Penetrant Inspection. This method

is a three-step process:

a. Spray or immerse the inspection surface in the liquid penetrant.

b. Remove excess liquid from the surface.

c. Inspect the surface with black light.

1.11.1.1 Penetrant inspection methods are normally used

for examining nonporous materials for defects open to the surface, such as cracks, pits, seams, laps, etc. Fluorescent penetrant contains a material which fluoresces brilliantly un-der Ultraviolet Light (UV) light.

1.11.2 Eddy Current Inspection. Equipment and acces-

sories are provided to support eddy current methods which make use of electrical currents in detecting flaws in metal parts such as cracks, inclusions, voids, seams, laps, etc., as well as sorting according to alloy, temper, conductivity, and other metallurgical factors, by variations in electrical charac-teristics and/or energy losses. The basic principle is one of inducing eddy currents in the metal part and detecting the effect of these currents on a measuring probe or coil.

1.11.3 Magnetic Particle Inspection. Equipment and ac-

cessories are provided to support magnetic methods which make use of magnetic fields for the purpose of rapid and dependable detection of very fine discontinuities at or near the surface of the part. The inspection method is limited to ferromagnetic materials; for nonmagnetic materials, pen-etrant methods should be used. The magnetic particle method can use both alternating and direct currents for magnetizing.

The inspection medium may be either wet or dry. In the wet method technique, a suspension of magnetic particles in oil or water is allowed to flow over the part, while in the dry method, magnetic powder is blown over the part to be in-spected.

1.11.4 Ultrasonic Inspection. Equipment and accessories

are provided to support (ultra)sonic methods defined as the techniques which employ the generation, measurement and/or interpretation of sonic and ultrasonic wave radiation traveling through, or being reflected or absorbed by metallic or nonmetallic substances for purpose of determining dis-continuities or measuring thickness. The three methods used in ultrasonic testing are:

a. Pulse echo.

b. Through transmission.

c. Resonance.

1.11.5 Radiographic Inspection. Equipment and acces-

sories are provided to support radiological methods which employ the use of X-rays, gamma rays, or similar radiation for the purpose of penetrating, or being scattered by sub-stances by or at real flaws or defects in the specimen being examined. Detailed information on NDI procedures can be found in TO 33B-1-1 or TO 1C-130A-36.

1-18

SECTION III POST CLEANING LUBRICATION

1.12 GENERAL.

Exposed external lubrication points can and probably will have the lubricant removed during the cleaning operations.

After cleaning and inspection of these areas, reapply the proper lubricant in accordance with instructions contained in the applicable Ground Handling, Servicing and Airframe Maintenance manual. Since the lubricant provides corrosion protection, lubrication shall be accomplished immediately after completion of the wash rack cleaning and inspection.

1-19

SECTION IV INSPECTING, CLEANING, AND STERILIZING FUEL TANKS

1.13 GENERAL.

Fuel tanks containing jet fuel are often contaminated with the fuel from poorly maintained fuel supply sources. The most common contaminant water and sometimes the con-taminants in dirty water are microbiological growth such as fungus, bacteria, yeast, and associated micro-organisms.

Presence of micro-organisms is a good indication of a dete-riorated coating and corrosion inside the affected tank. In-spection of fuel tanks for microbial contamination must be accomplished on a regular calendar schedule and as fre-quently as every 60 days in areas where:

a. The quality of the fuel is unknown.

b. The quality of the fuel is known to be poor.

On aircraft AF73-01580 and up, and aircraft modified by TO 1C-130-1039, a water removal system is installed which considerably lessens the danger of microbial growth. This system is most effective when the boost pumps and the en-gines are operated frequently, when the aircraft is not using JP4 fuel, and when a biocidal additive or an anti-icing addi-tive is used in the fuel.

1.14 DEFUELING.

Aircraft fuel tanks are to be defueled in accordance with general instructions contained in TO 1-1-3 and in accordance with aircraft peculiar requirements contained in the aircraft Fuel Systems technical manual. Residual fuel can be re-moved from low points in the tank by removing the poppet inserts of each condensate drain valve and inserting the drain valve tool illustrated in Figure 1-11. A rubber hose attached to the lower end of the tool must be used to direct the drained fuel into a suitable container.

1.15 PURGING.

Prior to entering a fuel tank, the tank must be purged in accordance with the procedures contained in TO 1-1-3. Lim-ited entry into a fuel tank is permissible at a Lower Explo-sive Limit (LEL) value that is higher than the value required for complete entry. Limited entry is defined as a head and shoulder entry only.

1.16 TANK ENTRY.

Access to integral fuel tanks is provided through the bulk-head doors in the dry bays located aft of each of the four engine nacelles and through the upper surface panel doors of the outer wing. Access to the auxiliary cells in the center wing is provided through removable door panels on the lower surfaces. (See Figure 1-12.)

1.17 LIMITED ENTRY INSPECTION.

Limited entry inspection is usually sufficient to determine the presence of dirty water or microbial growth along with the attendant breakdown of protective coatings and corro-sion. Inspection is performed using a bright explosion proof light. The presence of contamination in the tank is usually heaviest in areas that can be seen by head and shoulder en-try. In this examination, look for black to gray deposits, murky water, discolored and dislodged coating or sealants and for corrosion blisters. Clean water lying under the fuel is not of major concern. When the water is agitated by a gloved hand and fingers, it should break free immediately and sepa-rate from the fuel. If it does not, it can be suspected of being contaminated. When inspecting the auxiliary tanks, if the ac-cess doors are contaminated or corroded on the inside sur-face, the fuel bags shall be assumed to be contaminated.

1.17.1 First Phase Removals.

Water should be low in dissolved solids and free of suspended matter. If any doubt exists about the quality of the water available, depuddle as out-lined in TO 1-1-3 using sponges.

Conduct first phase removals only after verifying the LEL of TO 1-1-3 have been met. First phase removals for both inte-gral and auxiliary fuel tanks consist of removing fuel boost pumps. Prior to removing the pumps and level control valves from the auxiliary fuel cells, spray the bottom of the cells with water to float out fuel trapped in pockets. After remov-ing the pumps auxiliary control valves, dry off any surfaces the removed items that were wetted with water.

1.17.2 Depuddling of Integral Fuel Tanks. Direct a flow

of tap water into the tanks to float out all fuel puddles through the opened condensate drain valves with the adapter pipe and hose installed. Continue the water flow with periodic interruption until all residual fuel has been displaced and floated out of the tanks.

1.17.3 Second Phase Removals. Once the LEL reading

in the integral fuel tanks is within TO 1-1-3 approved limits, on aircraft prior to AF73-01580 and aircraft not modified by TO 1C-130-1039, remove the surge box covers and the ac-cess doors for the scavenge and jettison pumps. Remove the

1-20 Change 1 scavenge and jettison pumps. Plug the vent eductor outlet.

On…