T.0. 1L-1A-6 (Formerly 1L-19A-6) TECHNICAL MANUAL INSPECTION REQUIREMENTS USAF SERIES NAVY MODEL L-19A, L-19E, TL-19A, TL-19D OEF-1 & TL-19E AIRCRAFT 1 LATEST CHANGED PAGES SUPERSEDE N THE SAME PAGES OF PREVIOUS DATE A Insert changed pages into basic _ Oss Sonik publication iste} saparteded popes. EACH TRANSMITTAL OF THIS DOCUMENT OUTSIDE OF THE DEPARTMENT OF DEFENSE MUST HAVE APPROVAL, OF THE TECHNICAL ORDER DISTRIBUTION CONTROL ACTIVITY. REFER TO T.0, 00-52. PUBLISHED UNDER AUTHORITY OF TEE SICRETARY OF THE AIR FORCE nies "AND THE CHIEP OF THE BUREAU OF AERONAL 1 MARCH 1957 CHANGED 25 NOVEMBER 19687.0. MetA-6 tion for non-military use of the information or illustrations contained in this publication {in not permitted without specific approval of the issuing service (BuAer or AMC), The policy for use of Classified Publications is estaziished for the Air Force in AFR 208-1 and for the Navy in Navy Regulations, Article 1509, NOTE: Th pono en llacnd by hn chapel indicted UST OF EFFECTIVE PAGES Opi emia a mer anes aya ‘TOTAL MUMBER OF PAGES IM THIS PUBLICATION IS 48. , CONSISTING OF THE FOLLOWING: INSERT LATEST CHANGED PAGES, DESTROY SUPERSEDED PAGES. thew 27-8°°27"25 Original thru 9-2 22212) Original PIII ape 69 4-10 2000 4-11 thru 416 BL eee Bel 5-3 thru 6-6 “6-1 thru 6-2 7-1 thr 7-4 Te a niet ogee change, add, a deleed by he cmon shane. ADDITIONAL COPIES OF THIS PUBLICATION MAY BE OBTAINED AS FOLLOWS: USAP ACTIVI “te soordene wit tac! Onin Ne. 2, usar NAYY. ACTIVITES Gab nee, esr lec form Naren NAS, Alama, Cait "Seog Gea Rad ucoevle Pas NA Resa V Es 8ABD, Otte, WASEEPRNnAnp Par A ha ngs, Ca HU et Knog of eradae mr sd den of dition te Neral Aarne Pains Inde Never 600. A Changed 25 November 1968T.0. 1L-19A-6 Table of Contents Introduction TABLE OF CONTENTS Section Page INTRODUCTION booobosau dns : bo 1 PREFLIGHT INSPECTION doo5e0basb0 ray M —« POSTFLIGHT INSPECTION. .....-..-.-......- a4 MI _ INTERMEDIATE INSPECTION (Not identified at Present for Air Force Usage) Ree ere 34 IV PERIODIC INSPECTION, 2... - 2 41 V SPECIAL INSPECTION REQUIREMENTS... . 5-1 VI REPLACEMENT SCHEDULE... . . . eee ee et VII TEST FLIGHT INSPECTION REQUIREMENTS... . . era INTRODUCTION This handbook contains complete requirements for scheduled maintenance inspections, test flight in- spections, and scheduled replacement of accessories and components applicable to the aircraft to which the ‘handbook pertains. This handbook does not contain in- structions for repair, adjustment, or other means of rectifying defective conditions; nor does it contain de- tailed instructions for troubleshooting to find causes for malfunctioning. ‘The inspection requirements in the handbook are stated in such a manner as to establish what equipment is to be inspected, when it is to be in- spected, and what conditions are to be sought. Ap- plicable portions of the appropriate maintenance hand- books should be consulted to obtain maintenance in- structions that are beyond the scope of this handbook. ‘The inspections prescribed by this handbook will be accomplished at specified periods of Air Force organizational or Navy Class D maintenance activities, with aasistance provided by Air Force field maintenance or Navy Class C activities when required, and by De- partment of Army activities as authorized by Army directives. Compliance with the provisions of this handbook is required to assure that latent defects are discovered and corrected before malfunctioning or serious trouble results. ‘This handbook is divided into six sections. Sec- tions I, 1, and IV comprise the basic inspection re- quirements for Preflight, Postflight, and Periodic Inspections. Section V contains inspection require- ‘ments that supplement the requirements of one of the above sections at specific periods or upon occurrence of specific conditions. Section VI contains require- ments for replacing specific accessories or compon- ents at prescribed periods. Section VII contains test ‘ight inspection requirements. In order to arrange inspection and replacement requirements as nearly as possible according to the manner in which work ‘will be divided and assigned, the requirements in each section of the handbook are divided into groups under "system" headings. A system title indicates either a functional system or a group of related components. Requirements shown in Sections I, I and IV are basic requirements of the inspection. It may be nec- ssary to obtain additional requirements from Section V or Section VI to complete the inspection; for example, Af the 4th periodic is to be accomplished, any require- ‘ments that fall due at every 2nd or 4th periodic inspec- tion are to be included with the basic requirements of the periodic inspection. Discrepancies appearing on "Aircraft Flight Report and Maintenance Record” become a part of the requirements of appropriate post- {ight or periodic inspection in order that the number of delayed discrepancies may be held to an absolute minimum. No attempt is made to sequence the order of per- formance of inspection requirements. The inspection methods employed, the availability of specialists at specific times, and the facilities utilized are too vari- able to establish standardized sequencing. The inspection intervals designated to accomplish the requirements are the maximums, and are prepared from factual operating data for the primary use of the aircraft by type designation and will be revised as, tIntroduction ‘experience dictates. These inspection intervals should never be exceeded. Due to local conditions (types of ‘missions, special utilization, geographical locations, etc.), commands, local commanders, and their main- tenance officers, who not only have the prerogative but are expected to exercise it, should increase the fr uency or scope of any inspection as required. The times in man-minutes for accomplishment of inspection requirements reflect only the time re- quired for inspection, plus normal maintenance and adjustment and are to be utilized by maintenance of- ficers for planning and scheduling. Those factors (personnel and equipment shortages, lack of parts, unpredictable maintenance, unscheduled replacements, adverse working conditions, and qualifications of per- sonnel) which will directly affect the length of time for a scheduled maintenance inspection are not re- flected, because they cannot be accurately predicted for any particular inspection. This handbook pertains to all of a model or cer- ‘usin series of aircraft and may, therefore, contain in- i T.O. 1L-19A-6 ‘spection requirements applicable to specific equipment that is not installed on individual aircraft. When this situation is encountered, those requirements that are ‘not applicable should be disregarded. Additional information relative to recording of inspections and the use of this handbook may be ob- tained by consulting applicable technical directives. Revisions to this handbook will be published when necessary to add, delete, revise, or change frequency of requirements.’ Such revisions will be based on fac- tual data accumulated as a result of maintenance ex- perienced with the aircraft concerned. Data will be gathered by field studies, from Unsatisfactory Reports or reports on unsatisfactory or defective material, and from other communications perta'riag to the handbook and its requirements. Recom:: dations proposing changes to this handbook shou > submitted to the Maintenance Engineering Service” ision of the AMA or AF Depot having prime engin: ag responsibility for the aircraft, to the Bureau o. -2ronautics, or to the Transportation Corps, Army Av.acion Field Service Office.‘T.O, 1L-19A-6 Preflight Power Off ‘System 3 SECTION I PREFLIGHT INSPECTION 1-1. This inspection will be accomplished prior to the first flight of the day. ‘The inspection consists of checking the aircraft for flight preparedness by performing visual examination and operational tests to discover defects and maladjustments that, Lf not corrected, could cause accidents or aborted missions. Requirements preceeded by an asterisk are applicable only when use of the equipment concerned {s contemplated. Requirements preceeded by a double asterisk will be accomplished prior to each flight when more than one {ight is made In the same day. Additfonal information pertaining to the application of the preflight inspection and exceptions thereto are contained in applicable technical directives. BLECTRICAL POWER OFF PREPARATION MAN-MINS 1. Wheels chocked. 1 2. All fuselage, engine and pitot tube covers removed. 3 3. Fire extinguisher provided. 1 4, Auxiliary ground wire installed. 1 5. DD Form 781 checked, control locks disengaged, all a switches OFF, fuel selector ON. AIRFRAME (System No. 3) 1. Alreraft fatrings, panels and doors for breaks, tears 3 ‘and loose fasteners. 2. Wings, fuselage and control surfaces for dents, punctures 3 and abrasions. Windshield, rear view mirror and windows for cleanlin¢ **4, All loose equipment in cabin stored and secure. 1 5. First ald kit for availability and broken seal. 1 Emergency door release mechanism visually for defects 1 ‘which may render the door inoperative. Changed 1 April 1959 atPreflight Power Off T.0. 1L-19A-6 Systems 3 (Cont), 4,6,7 AIRFRAME (System No. 3)(Cont) 7. Check list and ash trays for availability. 8. Shoulder harness inertia ree! manual and automatic locks for positive locking and releasing. **9. Wings, flight control surfaces, and hinge points for frost, ‘Ice and snow. LANDING GEAR (System No. 4) +1, Tires for blisters, bruises, deep cuts and inflation. +2, Brakes for sponginess. 3. Brake Lines for leakage. UTILITY (System No. 6) 1. Portable A-20 fire extinguisher for dents, broken indicator Glass, low pressure, broken seals and loose fastener. 2. Cabin heater controls for ease of adjustment, pilot's and observer's seat outlets for obstructions. 3. Cabin ventilators for binding and obstructions. 4. Windshield defroster opening for obstructions. POWER PLANT (System No. 7) ‘**1. Cowling and panels for loose fasteners. 2. Engine controls for full travel and unrestricted movement. 12TO. 1-146 POWER PLANT (System No. 7) (Cont) 3. Exterior of engine for fuel and oll leaks. FUEL (System No. 8) ‘**1. Fuel tanks for servicing and filler caps for tightnes * plroraft Refeled. Verify fuel quantity indicating system to aseure complete servicing by adding indicated quantity Of fel owetnng in tanks. Wr fo sevice ane amet of fuel serviced. **2. Fuel tank drain valves and fuel filter drain valve for ‘water and sediment. #3. Exterlor of aircraft for fuel leakage; fuel vent outlets for obstruction. 4. Fuel selector valves for leaks, binding, and erratic detent action. #95. Fuel quantity gages for readings comparable with known contents in tanks. (OTL (System No. 9) **1. Ot sump for servicing; dip stlek and filler cap for tightness; drain valve for leakage. "2. Ol cooler for obstructed alr passage. ‘AIR INDUCTION (System No. 11) ‘°*1, Carburetor alr filter opening for obstructed alr passage. Preflight Power Off Systems 7 (Cont) 8, 9, 11 MAN-MINS 10 Changed 6 Februcry 1967 1-3Preflight Power Off TO. 1L-19A-6 Systems 12, 15, 16, 17 PROPELLER (System No. 12) ‘MAN-MINS s*1, Propeller blades for dirt, dents and gouges. 1 2. Propeller control for full travel and unrestricted 1 ‘movement. INSTRUMENTS (System No. 15) 1. Pitot static and port openings for obstructions. 1 2. Instrument cover glasses for cleanliness 1 3. Compass correction cards for availability. 1 RADIO (System No. 16) ‘**1, External antennas for cracked or broken insulators 1 and loose attaching screws. ARMAMENT (System No. 17) ‘*1, Bomb rack adapters and bomb racks for loose attaching a bolts; parts for scores, burrs and sharp edges; ‘electrical connections for looseness. ELECTRICAL POWER ON PREPARATION ‘MAN-MINS. 1. External power source available. 5 17.0, 1L-19A-6 AIRFRAME (System No. 3) 1, Landing Maps for unrestricted range of travel; flap position indicator consistent with flap position. FUEL (System No. 8) 1, Fuel pressure warning light for illumination. ELECTRICAL (System No. 14) Instrument lights for illumination. "2. Cabin lights for illumination. *3. Position and navigation Lights for illumination in flash and steady position. “4. Landing lights for illumination. *5. Rotating warning Nght for illumination and rotation. Preflight Power On Systems 3, 4 1-57.0. 1L-194-6 Postflight Power Off system 3 SECTION POSTFLIGHT INSPECTION ‘This inspection is, basically, a combination of requirements for checking equip- ment that requires daily or frequent verification of satisfactory functioning, plus requirements that prescribe searching for defects that become apparent after the aircraft is flown. It is intended that evidence of chafing, leaks, and similar con- ditions be discovered and corrected during the postflight inspection to preclude pro- gression of a relatively minor problem to a state that would require major main- tenance to remedy the diffciency. The postflight inspection is, therefore, an im- portant function that should be performed with care. Requirements preceded by an asterisk are applicable when the equipment concerned has been used. This inspection will normally be accomplished after the last flight of the day's operation or more frequently if local conditions warrant, however, since accom- plishment intervals will vary based on aircraft utilization, applicable aircraft in- spection systems directives should be consulted for additional information on hourly and calendar intervals of accomplishment. ‘This alrcraft will be operated under the tailored inspection concept. The scope of the inspection depends on the "class of operation" in which the aircraft is utilized and is reflected in the columns to the right of the requirements. Items identified with an "X" will be accomplished at each postflight inspection. Items identified by hour or calendar periods will be accomplished at the postflight inspections nearest to the hourly or calendar Interval indicated for that item. ELECTRICAL POWER OFF AT ‘ACCOMPLISi r PREPARATION ‘MAN-MINS 1. Portable fire extinguishers provided. 1 x 2. Wheels chocked. 1 x 3. All necessary cowling and inspection doors 2 x ‘or panels opened. 4. DD Form 781 for discrepancies, flight control 2 x lock disengaged, all switches OFF. 5. Auxillary ground wire installed. 1 x AIRFRAME (System No. 3) 1. Cockpit and ash trays for cleanliness. 1 x aPostflight Power Off T.O. 1L-19A- ‘Systems 3 (Cont), 4 AIRFRAME (System No. 3) (Cont) 10. ‘Wings, fuselage and flight control surfaces for loose rivets, dents, cracks, oll, dirt and corrosion, Windshield and windows for loose screws, cracks, leaks, smears, streaks and dirt. Cabin door and window latching mechanisms for erratic latching. Seats for breaks, grease, oll, corrosion and loose attaching bolts. ‘Seats for binding and erratic locking in all positions; seat tracks for cracks. First ald kits for availability, broken seals, correct identification markings, and serviceable tags. Safety belts and shoulder harness for soiled fabric and leather, cuts or fraying; attaching parts for binding and insecure locking; date of last weight test; insecure attachment. Static ground wire for contact with ground. curity and positive Flight control locks engaged. LANDING GEAR (System No. 4) . Tall gear for broken steering chains. ‘Tires for deep cuts, blisters, skid spots, inflation, and misaligned slippage marks. ‘Accessible brake lines, hoses and connections for leakage with parking brakes in ON position. Brakes for sponginess. Wheels and brakes for cracks, oil, grease, dirt and corrosion. ‘ACCOMPLISH AT [ccass[ 1 [mr MAN-MINS 15 x |x 8 x |x 1 x |x 4 x |x a x | x 1 x |x 3 x |x 1 ea 1 x |x 1 |e 3 x | x 2 x | x 1 x |x 3 im‘T.0. 1L-14-6 UTILITY (System No. 6) 1, Portable A-20 fire extinguisher for dents, broken indicator glass, low pressure, broken seals and loose fastener; mounting brackets for cracks and loose attaching scre POWER PLANT (System No. 7) 1. Cowling for cracks, loo fasteners. , broken or missing 2, Bxposed area of engine and accessories for loose attaching screws, bolts, clamps, and nuts. 3. Engine mount and supports for loose attaching bolts. 4. Cooling battles for cracks. FUEL (Gystem No. 8) **1, Fuel tanks for servicing and filler cape for tightness. 4. Aircraft Refueled. Verify fuel quantity indi ting ‘system {2 teu complete vervicing by aiding indicated quonity {Kel roneiniae in tanks, er to wottice, end De amount of fuel serviced. 2. Exterior of aircraft for fuel leakage; fuel vent outlets for obstruction. 3. Fuel quantity gages for readings comparable with known contents of tanks. OIL (System No. 9) 1. O11 sump for servicing dip stick and and filler cap for tightness; drain valve for leakage, cracks or breaks; cam handle and shaft for loosnes Postflight Power Off Systems 6, 7, 8, 9 ‘ACCOMPLISH AT Tass |r ‘MAN-MINS 1 x |x ‘ x] « 3 a] 2 le 2 5 lhe 10 x |x 2 x] 1 «| * 3 x | Changed 6 February 1967 2-3Postflight Power Of! TO. 1L-194-6 Systems 9 (Cont) 10, 11 OIL (System No. 9) (Cont) 2. Oli Lines and hose connections for leakage and chafing. 3. Oll cooler for loose attaching bolts, leaks and obstructions in the air passa IGNITION (System No. 10) 1. Ignition harness for burns, breaks, chafing, oll, dirt, and loose clamps; magneto and spark plug terminals for looseness. 2, Magneto and distributor for cracks and loos attaching bolts, AIR INDUCTION, EXHAUST (System No. 11) 1, Exhaust and intake manifold system: a, Exhaust system for cracks, leakage, loose clamps, bolts, and spring. b. Intake manifolds for cracks, leakage, loose attaching screws and clamps. 2. Intake ducts for obstructions and cracks. 3. Carburetor air filters for obstructed air passages and dryness. 24 ‘ACCOMPLISH AT. [CLASS | MAN-MINS 1 BG 1 x |x 10 as | a5 hrs. | hrs 5 x |x 2 z [x 3 x |x 1 x | x 1 x | xT.O. 1L-194-6 PROPELLER (System No. 12) 1. Propeller for cracks and nicks or dents beyond permissible limits: 2. Propeller hub and governor for oil Leaks ELECTRICAL (System No. 14) 1. Battery for leakage or overflow of electrolyte. 2. Battery and installation: a. Cells for electrolyte level and leakage. b. Electrolyte for specific gravity. Battery leads, connectors and vicinity of battery for corrosion. 4. Connectors for tightne: Drains and vents for restriction and loose clamps; jar for loose clamps. {. Battery container and cover for loose hold-down clamps. g. Battery sump jar pad for saturation with sodium bicarbonate and water. INSTRUMENTS (System No. 15) 1. Compass correction cards available, 2. Instrument indication pointers for indications in- consistent with existing temperature, pressure, direction and altitude; cover glasses for cracks and looseness; slippage, range and limit markings for deterioration. Pitot head drain holes for obstruction. Postflight Power Off Systems 12, 14, 15 "ACCOMPLISH AT Crass[ 1 | ur ‘MAN-MINS 1 x | «x 1 x |x 1 x | x “4 Every | Every 711 days | days 1 x |x 2 x |x 1 x |x 25Postflight Power Off T.0. 1L-198-6 System 16 Power On, Systems 8, 15 RADIO (System No. 16) 1. Mast type and loop antennas for loose mountings; ‘fixed wire antenna for cracked insulators, broken ‘tension units and loose connections. 2, Headsets and microphone plugs for insertion into Jack boxes and cordage for stowage. 3. Flexible shafts for broken or crushed casings. 4. Communication equipment for dents, structural fallure and loose attaching parts. ELECTRICAL POWER ON PREPARATION 1. External power source provided. Fire extinguisher provided. 3. Fuel selector valve ON (all switches and fuel selector valve turned off at completion of inspection). FUEL (System No. 8) 1. Fuel lines, hoses and connections for leaks and loose clamps (auxiliary fuel pump operating). 2. Fuel pressure warning light for illumination. INSTRUMENTS (System No. 15) 1. Pitot head heating element for temperature. 28 x |x x | x LISH AT. r ie AerTO. 1L-194-6 Postflight Power On System 17 ‘ACCOMPLISH AT. ekass] I | ur ARMAMENT (System No. 17) MAN-BINS. 1. Bomb racks for electrical release and manual cocking. 2 xTO. 1L-19A-6 Intermediate SECTION I INTERMEDIATE INSPECTION ‘This section is not being used at the present time due to the conversion to the periodic inspection which is a single inspection concept. However, utilization of this section may be re-established at a later date. The requirements for the peri- odie inspection are contained in Section IV.PREPARATION MAN: . Wheels chocked. 1 x 7.0. 1L-19A-6 Periodic Power Off System 3 SECTION IV ‘PERIODIC INSPECTION ‘The periodic inspection is a thorough and searching inspection of the entire aircraft. The inspection includes certain requirements that are also applicable to the preflight and postflight inspections. The thoroughness of the check and special tools or test equipment, if required, are indicated in the statement of the require- ment. ‘This aircraft will be operated under the tailored inspection concept. The hourly intervals at which this inspection will be accomplished by each "class of operation” are indicated below. Calendar intervals for accomplishing this inspection are speci- fied in applicable aircraft inspection system directives. The scope of the inspec tion depends on the "class of operation” in which the aircraft is utilized and is re- flected in the columns to the right of the requirements. Items identified with an "X" will be accomplished at each periodle inspection. Items identified by numbers will be accomplished at the numbered periodic inspection indicated. Ttems identi~ fied by calendar periods will be accomplished at the periodic inspection nearest the due date for that item. CLASSE: Atthe expiration of 100 flying hours after the preceding perio- dic inspection. CLASS II: At the expiration of 100 flying hours after the preceding perio- dic inspection. ELECTRICAL POWER OFF ‘ACCOMPLISH AT. 1 CLASS | T Engine cowling, baffles and shrouds; fuselage, 120 x ‘wing and empennage inspection doors, panels, plates, fairings and pitot cover opened or removed. Reinstalled after completion of inspection. Fire extinguishers provided. 1 DD Form 781 for discrepancies. 3 Auxiliary ground wire installed. 1 Flight controls lock released. Switches OFF. 1 AIRFRAME (System No. 3) 1 Aircraft (cabin, fuselage, exterior, wings, oI and empennage) for cleanline:Periodic Power Off T.O. 1L-19A-6 System 3 AIRFRAME (System No. 3)(Cont) Emergency door controls and locking mechanism for positive release and engagement, hinge pins free of corrosion. Wings, fuselage and empennage for loose or missing rivets, screws, nuts, bolts, skin punctures, cracks, buckles, corrosion, abrasion and cracked or buckled structure; fillets for cracks, loose rivets and corrosion. Firewall for cracks and loose or pulled rivets. Windshield, windows and rear view mtrror for cracks, crazing, loose retainer and attaching screws, and leaks, smears, streaks and dirt. ‘Flight control surfaces (allerons, elevators, rudder, trim tab and flaps) for the following: ‘&. Loose or missing rivets, skin punctures, cracks, buckled or wrinkled skin, abrasions, cracked or buckled structure and corrosion. b, Attachment fittings and brackets for looseness and cracks; bolt holes for elongation. . Bolts and pins for looseness. 4. Flaps for chafing trailing edge of wing. €. Counterweights for looseness. {. Hinges for cracks and looseness. & Controls for erratic range of travel. Cabin door, windows, hinges and latching mechanism for binding and corrosion. Flight control mechanisms for the following: a, Rudder, elevator and flap bearings for excessive radial and axial play, and binding. b. Elevator tab actuator for binding, and rod end bearing hole for elongation. ‘c. Control tube for loose or missing rivets, cracks, dents, gouges, and corrosion; brackets for cracks or breaks; bearings for binding, radial and axial play, loos in castings; broken dust seals. 4. Blevators, ailerons, flap and trim tab sn- pull rods and/or tubes for cracks, cor breaks and bolt holes for elongation; ro: end bearings for binding, radial and axial play; broken dust seal e. Elevator trim tab position indicators for restricted movement and bent pointers. Ar or 4 x | x 18 ial 1 x |x 5 ile 20 miler 2 Bia 60 x | x Changed 1 April 1959T.O. 1L-19A-6 AIRFRAME (System No. 3)(Cont) {Cables for dirt, corrosion, and fraying beyond permissible limits, particularly at pulleys, fairleads and cable guides. g Pulleys and fairleads for cracks, binding and misalignment; pulley bearings for excessive radial and axial play. hh, Elevator trim tab cable stop blocks for slippage. i, Turnbuckles for cracks, corrosion and loos safety wire J. Redder, aileron, elevator and flap bellcrank assembly for cracks, leaks, and loose attaching bolts. k. Flap flexible drive shafts for kinks, chafing, crushed casings, and attaching supports for cracks, loose grommets and clamps. 1. Serew jack mounting brackets for cracks, corrosion and loose rivets. ‘m, Wing flap motor for loose attaching screw: electric connections for loase wires. ‘n, Flap indicator sending unit for loose attaching screws, corrosion and electrical leads for looseness. 9. Wings, wing struts, horizontal and vertical stabilizer attaching bolts for looseness. 10. Seats, lock linkage and tracks for breaks or cracks; ‘seats for binding and erratic locking in all positions, torn or-solled fabric; rollers for binding or wear. 11, Safety belts and shoulder harness for bent or corroded metal parts; soiled fabric and leather, cuts or fraying, latching parts for binding and insecure locking, date of last weight test; insecure attachment. 12. Inertia reel manual and automatic locks for security and positive locking and releasing. 13. First ald kit for availability, completeness of contents in side compartments, serviceable tag attached, date of seal and specified indentification markings. 14, Check lists and ash trays for availability. 15. Upholstery and blind flight curtains for soiled and torn fabric. 16. Aircraft technical publications file current and complete. 17, Stencils, decals and insignia for legibility. Periodic Power ort System 3 (Cont) “ACCOMPLISH AT Class{ 1 |i ‘MAN-MINS 5 x] x 4 ee) 5 x |x 1 x | x 2 Lela 1 x |x 5 x |x a x |xPeriodic Power Off 7.0. 1L-1A-6 Systems 4, 6 LANDING GEAR (System No. 4) 1 10. a. ‘Tail gear spring assembly for cracked, broken, misaligned or vent leaves (Dy Chek or Magnetic Particle); broken or loose U bolt. ‘Tail whee! fork assembly for corrosion, cracks and broken coil springs; bearing cone and rollers, for pits, flakes, smears, cracks, breaks and over- heating: bearing cups for looseness; bearing cage for bends and cracks; bushing for wear beyond ma) imum tolerance; steering mechanism for broken chains ‘and bent arms. Movement of rudder and tail wheel coincide in each direction. ‘Tires for uneven tread wear, cuts, blisters, grease or oll, misalignment of slippage marks, and inflation. Wheels for corrosion, cracks and distortion, dust covers for cracks, corrosion, and looseness; overheating adjacent to brakes; bearing inclosure rings for bends and distortion; bearing cones, cups and rollers for, flakes, smears, cracks, breaks and overheating; bearing cups for looseness; bearing cage for bends and cracks; drive keys for looseness; wheels for misalign- ‘ment; tail wheel felt grease retainers for deterioration. Master brake cylinders for correct fuld level, positive full return and binding. Brake pedals for correct adjustment, bind Ing, cracks, bends; linkage bolt Roles for elongation and looseness of bolts and pins. Brakes for spongin« Brake assembly for cracks at mounting holes and anvil side brake lining lower cavity. (Dye pene- trant inspect every 2nd Periodic; loose bolts; linings for minimum thickness. ‘Axles for nicks, deep scratches, bends and corrosion, bearing surfaces for galls and pits; threaded portions for crazed or stripped threads. Main landing gear struts and supporting structure for cracks, distortion buckling, loose bolts, shims and wedges. UTILITY (System No. 6) 1 Portable A-20 fire extinguisher low pressure, broken seals, dents, gouges, leakage, broken Indicator glass, and loose fasteners; mounting brackets for cracks. 4-4 Changed 25 November 1968 “ACCOMPLISH AT CrAss| 1 | ur ‘MAN-MINS 128, x | x 32 x |x 1 fz |e) 6 xl | 80 x |x 4 x |x 10 x |x 1 x |x 3 x |x 3 x |x 15 mes 1 x |xT. 0, IL-1A-6 UTILITY (System No. 6) (Cont) Cabin heating and windshield defroster ducts for holes, tears, collapsed tubes, loose connections and chafing. Cabin heater valves for cracks, warpage and loose attaching bolts; controls for loose wire and erratic range of travel. Cabin ventilators for foreign matter, and binding; ducts for holes, tears and collapsed tubes; air POWER PLANT (System No. 7) tb 2. 10. 12. Engine for cleanliness. Cowling for cracks, defective, missing and loo: fasteners. Lord mounts for insecure attachment, loose or broken safetying, and deterioration of rubber core assemblies. Engine mounts for cracks, corrosion and loose attaching bolts. Air deflectors and baffles for cracks, loose attaching screws and bolts, and chafing against cylinder fins. Crankease breathers for obstructions. Engine for fuel and oll leaks; loose, broken or ‘missing nuts, bolts, studs, clamps and safetying. Valve springs, retainers, keys and rocker arms for cracks, breaks and dryness. Cylinders for broken fins; loose hold-down pal nuts. Push rod housings for severe dents, cracks, leakage and loose safetying. Carburetor seals, plugs and nipples for leakage; screens for breaks, tears and contamination. ‘Engine controls, bellcranks, rod end fittings, and links for wear, cracks, ‘misalignment and loose or broken safetying; brackets for cracks, ‘corrosion and loose attaching bolts; controls for binding and restricted travel. Periodic Power Ott Systems 8, (Cont), 7 2 20 40 10 x |x x] x x | x 4-5Periodic Power Off ‘T. O, 1L-1A-6 Systems 7(Cont), 8 POWER PLANT (System No. 7) (Cont) 13 4 15. Starter for cracked or broken mounting flange and loose attaching bolts; electrical connections for looser Cylinders for specified compression values. Starter brushes for wear (11/32 inch or more in length remaining) and freedom of movement in brush holder; brush leads for deterioration or evidence of chafing: commutator for evidence of arcing and presence of oil or metal particles; electrical connections for tightnes: FUEL (System No. 8) 1 10. a. 12, 13 Fuel tank filler cap gaskets for deterioration, breaks and tears. Exterior of aircraft for fuel leakage. Fuel tank vent lines for obstruction and chafing. Fuel lines for pitting, scratches and dents beyond Permissible limits, chafing and loose attaching clamps; hoses for cuts, cracks and deterioration ‘Micronic filter element for breaks, tears and contamination; strainer housing for loose attaching bolts, cracks, corrosion and pits. Fuel tank and fuel filter drain valves for erratic action and leakage. Fuel selector valve for leaks, binding, erratic detent action, and loose attaching screw: Fuel quantity gages for readings comparable with Imown contents in tanks; gages for leaks and loose attaching screws. ‘Auxiliary fuel pump drain for obstruction and seal for leakage Auxiliary fuel pump for loose attaching bolts; connections for leakage; electrical connections including bonding jumpers for looseness. Auxiliary fuel pump brushes for chips, cracks, and wear beyond minimum length; leads for fraying; binding in brush holders. Fuel pressure warning light electrical connections for loose wires, Primer and primer lines for leakage; loose attaching screws and clamps. Fuel pump for loose mounting nuts, and corrosion; ‘mounting flange for cracks or breaks; seal for seepage and drain for obstruction; pressure relief chamber vent plug for obstructions. 4-6 Changed 25 November 1968 ACCOMPLISH AT Lass 1 | or ‘MAN-MINS 4 ae 36 a} 2 20 Bell a 10 x |x 10 x | x 10 x |x 5 telex 2 Bele 1 ces 2 tle 2 x |x 2 x |x 5 3s |o3T. 0, 1L-1A-6 UTILITY (System No. 6) (Cont) 2. Cabin heating and windshield defroster ducts for holes, tears, collapsed tubes, loose connections, and chafing. Cabin heater valves for cracks, warpage and loose attaching bolts; controls for loose wire and erratic range of travel Cabin ventilators for foreign matter, and binding; ducts for holes, tears and collapsed tubes; air inlets for obstruction. POWER PLANT (System No. 7) 12, Engine for cleanliness. Cowling for cracks, defective, missing and loose fasteners. Lord mounts for insecure attachment, loose or broken safetying, and deterioration of rubber core assemblies. Engine mounts for cracks, corrosion and loose attaching bolts. ‘Air deflectors and baffles for cracks, loose attaching screws and bolts, and chafing against cylinder fins. Crankcase breathers for obstructions. Engine for fuel and oil leaks; loose, broken or missing nuts, bolts, studs, clamps and safetying. Valve springs, retainers, keys and rocker arms for cracks, breaks and dryness. Cylinders for broken fins; loose hold~down pal nuts. Push rod housings for severe dents, cracks, leakage and loose safetying. Carburetor seals, plugs and nipples for leakage; screens for breaks, tears and contamination. Engine controls, bellcranks, rod end fittings, and links for wear, cracks, ‘misalignment and loose or broken safetying; brackets for cracks, corrosion and loose attaching bolts; controls for binding and restricted travel. Periodic Power Off Systems 6, (Cont), 7 ‘ACCOMPLISH AT ekass[ | ur ‘MAN-MINS 2 x |x 12 ea 2 x |x 20 x |x 3 ales 5 x |x 2 la 4 x | x 1 x |x 1 le 40 Apa 10 x | x 5 x | x 9 x | x 4 x | x 4-5Periodic Power Off O, 1L-1A-6 Systems 7 (Cont), 8 POWER PLANT (System No. 7) (Cont) 13. 4, Starter for cracked or broken mounting flange and loose attaching bolts; electrical connections for looseness. Cylinders for specified compression valuc 15, Starter brushes for wear (11/92 inch or more in length remaining) and freedom of movement in brush holder; brush leads for deterioration or evidence of chafing: commutator for evidence of arcing and presence of oi! ‘or metal particles; electrical connections for tightness. FUEL (System No. 8) 1 10 a. 12, 13 46 Fuel tank filler cap gaskets for deterioration, breaks and tears. Exterior of aircraft for fuel leakage. Fuel tank vent lines for obstruction and chafing. Fuel lines for pitting, scratches and dents beyond permissible limits, chafing and loose attaching clamps; hoses for cuts, cracks and deterioration |. Micronic filter element for breaks, tears and contamination; strainer housing for loose attaching bolts, cracks, corrosion and pits. Fuel tank and fuel filter drain valvé erratic action and leakage. for Fuel selector valve for leaks, binding, erratic detent action, and loose attaching screws. Fuel quantity gages for readings comparable with known contents in tanks; gages for leaks and loose attaching screw: ‘Auxiliary fuel pump drain for obstruction and ‘seal for leakage Auxiliary fuel pump for loose attaching bolts; connections for leakage; electrical connections including bonding jumpers for loosene: ‘Auxiliary fuel pump brushes for chips, cracks, and wear beyond minimum length; leads for fraying; binding in brush holders. Fuel pressure warning light electrical connections for loose wires, Primer and primer lines for leakage; loose attaching screws and clamps Fuel pump for loose mounting nuts, and corrosion; ‘mounting flange for cracks or breaks; seal for ‘seepage and drain for obstruction; pressure rellef ‘chamber vent plug for obstructions. Changed 25 November 1968 AG aT CLASS TL (-MINS 4 x 36 2 20 2 10 x 10 x 10 x 5 x 2 x 1 x 2 x a x 2 x 5 3 1 x a xT.O. 1L-19A-6 OM (system No. 9) 1. Oil sump serviced, filler cap secured. 2. Engine main oll screen for metallic particles on the screen or in the screen housing. 3. Oil system for leakage; lines for dents, cracks and chafing; flexible connections for deterioration; loose hose clamps; oil drain valve for leakage, cracks or breaks, loose cam handle and shaft; outlet tube dented or cracked, and weak spring. 4. Oil cooler for leaks, loose attaching bolts, foreign matter in the air passage, welled tubes, corrosion, dents, scratches and cracks. IGNITION (System No. 10) Ignition harness assemblies for loose clamps; brackets for cracks; condults for chafing or overheating. 2, Ignition harness for loose terminal connections. Magnetos: a. Breaker compartments for oil and dirt. b. Breaker pointé for pitting Cam followers for adequate lubrication. d. Ventilator screens and plugs for contamination and loose attaching nuts. AIR INDUCTION, EXHAUST (System No. 11) 1. Exhaust System: a, Exhaust port studs for loose or missing nuts. b. Clamps for looseness, cracks, misalignment, and leakage. Periodic Power Systems 9, 10, on ry MAN-1 10 20 10 8 18 ‘ACCOMPLISH AT ccass [Tt [ur “MINS x |x mex x |x 41Periodic Power Off T.O. 1L-19A-6 Systems 11 (Cont), 12 AIR INDUCTION, EXHAUST (System No. 11) (Cont) c. Exhaust muffler and cabin heat muffler for cracks, burning, distortion and loose attaching screws and bolts. 4. Exhaust stacks for cracks, burns and loose clamps and bolts. ¢. Tail pipe for misalignment, cracks, and loose clamps and bolts. 2. Carburetor air filter for obstructed air passage; and filter material for dryness, channels, breaks and tears; filter frame for cracks, vreaks and bends. 3. Carburetor air intake box for broken valve spring, and loose screws and bolts. 4. Intake system: a, Intake port studs for loose or missing nuts and leakage. b. Intake manifolds for cracks, leaks and loose clamps and attaching bolts. . Intake pipe connecting hoses for deterioration. PROPELLER (System No. 12) 1. Propeller for corrosion, cracks and nicks. 2. Propeller retaining nuts for torque and safety. (65-65 foot pounds). 3. Propeller blades for track. 4, Propeller hub for oll leaks. 5. Propeller governor for loose attaching nuts, and oil leakage. Propeller control bellcranks, rod end fittings and links for wear, cracks, misalignment and safetying. Brackets for cracks, corrosion, loose screws and broken safety wire. ‘1. Propeller control for unrestricted movement and full range of travel 4-8 OMPLISH AT cass[ 1 [nr ‘MAN-MINS 3 x |x 2 x | x 15 za | 2 x |x 2 x | x 3 aedles| 1 x |x 2 eal 3 x 1 x7.0. 1L-19A-6 ELECTRICAL (System No. 14) 1 10. Reverse current relays for loose attaching screws, grease, oll, or dirt; case for cracks, dents and breaks’ Flasher for loose attaching screw: cracks, breaks and distortion. cover for Voltage regulators for loot grease, oil or dirt. attaching clips, Navigation, position, landing and cabin lights for broken lenses and bulbs, and corrosion. Battery for leakage, overflow of electrolyte, specific gravity and water level. Electrical systems from the generating source to each electrical component (excluding radio, instrument and armament wiring from main power buses to operating units) for the following: a. Wiring for deterioration, chafing, traying, loose support clamps, and overheating. b. Generator plug exteriors for corrosion, cracks, overheating, loose wire connections. ©. Wire shielding for fraying, crimping and corrosion. 4. Junction boxes for cracks, and loose attaching screws; drain holes for obstructions. e. Plastic tubing for security and adequate drainage provision {Terminal strips, connections, bonding jumpers land ground connections for corrosion, and loose attaching parts. Generator for loose attaching nuts, cracked or broken mounting flange and end housing; electrical connections for loosenes: Generator blast tube for loose connections and anchorage clamps. Shock mounts for cracks, corrosion, loose bolts or rivets, vibration absorbers for deterioration of rubber parts, and loose or missing bonding. Generator brushes for wear beyond specified ‘minimum length, even wear, and binding in brush holders; insulation on brush leads for deterioration or chafing; commutators for arcing and presence of oil or metal particles; electrical connections for looseness. Periodic Power Off System 14 "ACCOMPLISH AT CLass[ | ir MAN-MINS 33 x | x 1 x |x 1 x | x 1 x | x 2 x |x 18 x |x 2 x |x 1 ae a =e 26 x] xPeriodic Power Off T.0. 1L-19A-6 Systems 14 (Cont), 15 ELECTRICAL (System No. 14) (Cont) aL 12. Rotating warning light lens for cracks and dis lens drain hole for obstructions; lens retaining ring screws for loose or broken safetying. Battery for capacity check. INSTRUMENTS (System No. 15) 4-10 1 Pitot port, static sources, and drain holes for obstructions; pitot head for loose attaching Instruments for security of mounting. Compass correction cards for availability. Magnetic compasses for discoloration of Liquid, leakage and air bubbles. Instrument indicating pointers for indications inconsistent with existing temperature, pressure, direction, and altitude; cover glasses for cracks, and looseness; slippage; range, and limit markings for deterioration; luminescent paint for chips dirt and fading. All pressure indicating instruments and corresponding connections at the instrument panel for leakage. Engine thermocouple and terminal for looseness harness leads for overheating and chafing. Directional gyros and artificial horizon caging ‘mechanisms for positive caging and uncaging. Instrument systems for the following (from each electrical component to, but not including, Junction boxes containing main power buses): a. Wiring for deterioration, chafing, fraying loose support clamps, and overheating. . Connector plug exteriors for corrosion, cracks, overheating, and loose wire connections. c. Wire shielding for fraying, crimping, and corrosion. d. Junction boxes for cracks, and loose attaching ‘screws; drain holes for obstructions. OMPLISH AT focass[ [ur MAN-MINS 1 x 10 Every | Every| 4 4 1 x |x 4 x] x 1 x | x 1 x |x 3 x |x 5 x |x 1 x | x 1 x |x 10 x | x1.0, 1L-194-6 INSTRUMENTS (System No. 15) (Cont) 10. ML. 12 13, 4. 15. 18. e. Plastic tubing for security and adequate drainage provisions. £, Terminal strips, connections, bonding jumpers and ground connections for fraying, corrosion, and loose attaching parts. contamination, leaks and erratic calibration of airspeed indicators at all major graduations. ‘Shock mounts for cracks, corrosion, loose attaching bolts or rivets; deterioration of rubber and loose or missing bonding. Altimeter for reading within tolerance; pointers for friction. Tester MB-1, TCAD-807695. ‘Tachometer generator for loose attaching bolts, and corrosion; mounting flanges for cracks or breaks; electrical connection for looseness, and loose or broken safetying. ‘Vacuum pump for loose attaching nuts, and corrosion; mounting flange for cracks and breaks: relief valve for loose fittings, clamps, and safetying; screen for contamination; body for cracks and corrosion. Connections for looseness and leakage. ‘Vacuum pump air filter for contaminati element for cracks and breaks; body for cracks, corrosion and loose attaching screws; connections for looseness. ‘Vacuum pump oil separator for leaks; screen for obstructions; mounting lugs for cracks, loose attaching bolts and-cage for cracks, breaks and collapsing. RADIO (System No. 16) 1 ‘Mast type and loop antenna for loose mounting; fixed wire antenna for cracked insulator: bbroken tension units, loose connections and ‘mounting; lead-ins for specified spacing trom surrounding objects. ‘Shock mounts for cracks, corrosion, loose attaching bolts or rivets, deterioration of rubber, and loose or missing bonding. Periodic Power Otf Systems 15 (Cont), 16 ACCOMPLISH AT Grass [ft | am MAN-MINS 20 Biba 6 x | x 30 x | x 2 x | x 2 x |x 5 x | x 15 x |x a x | ox a x | x gelPeriodic Power Off 7.0. 1L-19A-6 Systems 16 (Cont), 17 RADIO (System No. 16) (Cont) 3. Headsets and microphone plugs for insertion into Jack boxes and receptacles; cordage for stowage. 4. Flexible shafts for broken or crushed casings. 5. Communications equipment for dents, structural failure, and loose attaching parts. 6. Radio systems for the following (from each electrical component to, but not includin junetion boxes containing main power buses): &. Wiring for deterioration, chafing, fraying, loose support clamps, and overheating. . Connector plug exteriors for corrosion, cracks, overheating, and loose wire connections. cc. Wire shielding for fraying, crimping and corrosion. 4. Junction boxes for cracks, and loose attaching ‘Screws; drain holes for obstructions. e. Plastic tubing for security and adequate drainage provisions. {, Terminal strips, connections, bonding jumpers and ground connections for fraying, corrosion, and loose attaching parts. ‘1. ADF loop antenna dehydrator crystals for discoloration beyond serviceability. ARMAMENT (System No. 17) 41 1. Bomb racks and bomb rack adapters for corrosion and loose attaching bolts; mechanism for distortion oF binding. 2, Armament systems for the following (from each electrical component to, but not including, junction boxes containing main power buses): ‘a. Wiring for deterioration, chafing, fraying, loose support clamps, and overheating. b. Connector plug exteriors for corrosion, cracks, overheating, and loose wire connections. ‘ACCOMPLISH AT fecass| | mm MAN-MINS 1 x |x 2 x |x a x |x 15 ze 4 x 5 x 18 xT.0. 1L-19A-6 Periodic Power Off System 17 (Cont), Power On Systems 3, 8 ‘ACCOMPLISH AT (CEAss[ Tor ARMAMENT (System No. 17)(Cont) MAN-MINS c. Wire shielding for fraying, crimping and corrosion. d. Junction boxes for cracks, and loose attaching Screws; drain holes for obstructions. Plastic tubing for security and adequate drainage provisions. {Terminal strips, connections, bonding jumpers and ground connections for fraying, corrosion and loose attaching parts. ELECTRICAL POWER ON ‘ACCOMPLISH AT Chass] 1 | or PREPARATION ‘MAN-MINS, 1. External power source provided. 5 elas) 2, Fire extinguisher provided. 1 x] x AIRFRAME (System No. 3) Landing flaps for unrestricted range of 1 x | x travel; flap position indicator consistent with flap position. FUEL (System No. 8) 1. All fuel system components, lines, hoses 10 led and connections for leakage, (fuel selector ON, auxiliary fuel pump ON. 2. Fuel pressure warning light for illumination 1 x | x and correct cut-in and cut-out pressures.Periodic Power On T.O, 1L-19A-6 Systems 14, 15, 16, 17 ELECTRICAL (System No. 14) 1. Instrument lights for {lumination. 2. Cabin Lights for illumination. 3. Position and navigation Lights for iLlumination in flash and steady position. Landing lights for illumination. 5. Rotating warning light for illumination. INSTRUMENTS (System No. 15) Pitot head heating element for temperature RADIO (System No. 16) . Radio receivers for sensitivity, adequate volume, clarity of tone and dial calibration on all channels 2. Radio transmitters for frequency, power output and clarity of side tone. 3. Radio range receiver for dial calibration, clarity of tone, adequate volume, functioning on applicable antenna and ease of rotation of dial tuning control. 4. ADF receiver for dial calibration and antenna coordination. 5. Interphone system for clarity of tone on all positions. ARMAMENT (System No. 17) 1. Bomb racks for electrical release and manual cocking. “ACCOMPLISH AT Ckass| 1] ar ‘MAN-MINS 1 x |x 1 x | x 2 x] x 1 x |x 1 x a x | x 2 x |x 2 x] x 2 eel) 2 x] ox 2 x] ox 2 x | xT.O. 1L-19A-6 ENGINE OPERATION PREPARATION 1 Portable fire extinguisher provided. Pull propeller through a minimum of two complete turns. OPERATION A Accomplish engine operation in accordance with applicable directives. a. Pre-engine start. b. Engine start. Engine warm-up. 4. Complete cockpit check. ©. Pre-shut-down. {. Stopping engine. & After engine shut-down, Perform the following operational checks during engine operation: ‘a. Engine for operation on all sources of alr. b. Engine instruments for correct response to ‘engine power application and freedom from excessive fluctuation. ¢. Availability of fuel from each fuel tank selector positio 4. Generator and voltage regulator for output; reverse current relays for cut-in and cut-out. e. Voltage regulator for correct bus voltage; check with voltmeter for known accuracy. Carburetor heat system for operation by observing engine operation variation when controls are actuated. . Propeller for correct response to actuation of propeller control. Accomplish test fight. Periodic Engine Operation “ACCOMPLISH AT (ELAS, mT ‘MAN-MINS As Req.T. O, 1L-1A-6 Spectal System 3 SECTION V SPECIAL INSPECTION REQUIREMENTS ‘This section contains inspection requirements that supplement the basic require- ‘ments of preflight, postflight and periodic inspections. The requirements contained in this section are only those which require accomplishment due to specific circum= stances or upon occurrence of specific conditions. When accomplishment of any one of the items is required, it is to be added to the basic requirements of the inspection to be performed, The IRAN requirements are integrated into this section and are intended to be over and above those items specified at numbered periodies that only depot level facilities are equipped to do, and those that have broad frequency of accomplish- ment tolerances. ACCOMPLISH SYSTEM AND ITEM ‘MAN-MINS, AIRFRAME (System No. 3) After cleaning or 1. Safety belts and shoulder harness, 60 repair. ‘weight tested. Every IRAN 2. Landing flap screw jacks for loose bolts and bushings, ‘corrosion, cracks, breaks and loose flexible drive shafts; torque tube for bends and binding; dust shields for dents, gouges, nicks and breaks; dust seal for deterioration; rod-end bearing hole for elongation, cracks and corrosion. Every IRAN 3. Elevator tab actuator for loose or broken attaching clamps; sprocket for cracks, breaks, broken teeth and looseness on shaft; housing for cracks, corrosion, dents and gouges; rod-end bearing holes for elongation, cracks and corroston. Every IRAN 4, Flight control system anti-friction bearings for axial and radial play, binding, inadequate lubrication, missing dust shields and loosenes: 1m castings. Eve-y IRAN, 5. Elevator tab control chains for cracked and/or broken links, loo Unk pins, and binding Links and rollers; sprocket for cracks, breaks, and worn or missing teeth. Cuangeu 49 wuveMver L900 9-4Special Systems 3 (Cont) 4 ACCOMPLISH Every IRAN Every IRAN ‘At 8th periodic and every periodic thereafter until replaced. Every tire change and wheel removal. Whenever wheel is removed. When circumstances which could result in possible Yanding gear damage are reported by pilot. Every IRAN Every IRAN 5-2 Changed 7 April 1967 7.0, 1L-1A-6 SYSTEM AND ITEM ‘MAN-MINS AIRFRAME (System No. 3) (Cont) 6. Inertia reel case for cracks, breaks, ‘and dents; dust cover for distortion, cracks, and breaks, especially where cable end rests; harness cable for corrosion and broken strands; torsion spring for tension, distortion and ‘breaks; clutch and base for chipped, cracked and broken or missing teeth; base pin for being perpendicular to the teeth, J. Interior of fuselage for corrosion. LANDING GEAR (System No. 4) 1, Tail wheel fork spindle grease 30 groove for cracks. (Dy-Chek or Magnetic Particle.) 2. Main wheel for corrosion, cracks, and 22 distortion; bearings and bearing surfaces for pits, flakes, brinells, cracks, corrosion, breaks and everheating. 3. Brakes for cracks at mounting and at the inside 3 radii of brake housing between piston and anvil. 4, Tire interior for breaks, wheels for 120 cracks and warpage; struts for cracks, distortion and loose or broken attaching bolts; supporting structure ‘wedges and shims for cracks, buckling, loose or broken bolts. 5. Brake housing for cracks, scores, gouges, deep scratches and leaka rotating disc for scores, warpin ‘wear beyond minimum thickness, and key slots for wear beyond maximum length; bolts and screws for crossed or stripped threads and heads for rounded corners or burrs. 6. Main landing gear springs for cracks, (Dy-Chek or Magnetic Particle {fillet plate for cracks; support assembly for pulled rivets; attaching bolts for cracks, bends and torque.ACCOMPLISH After ground run and first flight following cylinder change After ground run and test flight following engine change. Overspeed, but not in excess of limits. ‘Overspeed in excess of mits At the 10th hour of engine operation after inspection of the engine due to overspeed. Whenever any component ‘which would affect cali- bration is replaced. Whenever aircraft has been in storage exceeding 30 days T.O, 1L-19A. SYSTEM AND ITEM POWER PLANT (System No. 7) 1 5. Engine for the following: a, Oil leakage at cylinder mounting flange. b. Intake and exhaust manifolds, push rod housings, rocker box covers and lines on replaced cylinders for dents, cracks, chafing, loose attaching clamps, and leakage. ¢. Removable oil strainers and sump plugs for metal particles. Engine for the following: a, Accessible areas of engine for dents, cracks, warpage, chafing, leakage, safetying, and loose or missing nuts, bolts, studs and clamps. . Oil and fuet lines, manifolds, and accessories for cracks, chafing and loose attaching clamps, ¢. Removable oll strainers and sump plugs for metal particles. Engine for cracked or broken cylinder heads or barrels; sump oll and oil screens for metal particl Engine change. ‘Sump oll and oll screens for metal particles. FUEL (System No. 8) 1 Fuel quantity system for specified calibration with tanks empty and with tanks full. Relief valve body on engine driven fuel pump for specified torque value. Special Systems 7, 8 ‘MAN-MINS: 10 10 35 130 20 10Special Systems 8 (Cont), 9, 10, 11, 12 ACCOMPLISH Every IRAN Every IRAN Every engine change as a result of internal engine failure. ‘At each spark plug change, and whenever any spark plug terminal is dis connected. Every IRAN, Bvery Postflight when dusty atmospheric conditions exist. Engine change resulting from overspeed in excess of limits. 54 7.0. 1L-19A-6 SYSTEM AND ITEM FUEL (System No. 8) (Cont) Fuel pressure gage for accuracy and calibration (C-1 Portable Field Instrument Test Set 3715800) Fuel tank for corrosion, breaks and cracks; retaining straps for cracks breaks, corrosion and tension. Turn- buckles for corrosion, cracks, stripped threads and safety wiring. OL (System No. 9) 1 Oil cooler and regulator replaced; hoses cleaned and flushed. IGNITION (System No. 10) L ‘Spark plug elbows for distortion; Insulators for cleanliness, missing or distorted contact springs, cracks, and secure attachment to ignition leads. Ignition switch for cossinuity in all ‘positions; terminal sc-ews for looseness; lever and contact post pins and plate for looseness; contacts for pits and corrosion. AIR INDUCTION, EXHAUST (System No. 11) 1 Carburetor air filter for contamination. PROPELLER (System No. 12) 1 Propeller retaining bolts magnetically inspected. Propeller given a close Visual inspection for cracks, breaks, and nicks. 10 15ACCOMPLISH Every IRAN, Every IRAN Every IRAN Every 180 hours or every three months, whichever comes first and anytime that equipment replace- ment, modification or Telocation might cause ‘compass deviation. Every IRAN Every IRAN ‘Bvery IRAN SYSTEM AND ITEM -MAN-MINS ELECTRICAL (System No. 14) 1. Position light flasher chassis for breaks and cracks; contact points for pits, arcing, and sticking; cartridge for continuity and ‘burning; frequency of cycling. 2. Interior of cannon plugs for corrosion; electrical wiring for corrosion and looseness in pin receptacles. 3. Voltage regulator base for loose, bent, corroded, pitted, discolored contacts, and worn silver plating; terminal lugs for breaks and corrosion; insulators for cracks and burning. INSTRUMENTS (System No. 15) Compass for correct reading on all cardinal headings. Recompensate if necessary. 2. Instruments for calibration. (C-1 Portable Instrument Field Test Set 3785800). 3. Interior of cannon plugs for corrosion; electric wiring for corrosion and looseness in pin receptacles. RADIO (System No. 16) 1. Cannon plug interior for corrosion; ‘wiring for corrosion and looseness in pin receptacles. 5-5Special System 17 ACCOMPLISH ‘Every IRAN Every IRAN 5-6 T.O, 1L-19A-6 SYSTEM AND ITEM ‘MAN-MINS ARMAMENT (System No. 17) 1. Bomb racks for bends and warps; latch for scored parts; mechanism for dirt, metal chips, solder, or scored surfaces; pins and holes {for dirt, binding and loose parts; hhook, link, and locking cam for cracks (magnetic particle); release spring for breaks, distortion, and resiliency; electric contact points for dirt and pits; electrical ‘wires for loose or frayed ends and insulation for deterioration. 2. Interior of cannon plugs for corrosion; wiring for corrosion and looseness in pin receptacles0, 1L-1A-6 Replacement systems 3, 4, 7, 8 SECTION VI REPLACEMENT SCHEDULE This section lists units of operating equipment that are to be replaced at the periods specified. Replacement means removal of the equipment and installation of a serviceable item in its place. Replacement of equipment will be indicated in flying hours or calendar time and will be accomplished at the Periodic Inspection nearest the time when the replacement is due. Applicable technical directives should be consulted for information pertaining to authorized extensions of the specified periods REPLACE SYSTEM AND ITEM. AIRFRAME (System No. 3) 1, Deleted, LANDING GEAR (System No. 4) 1. Deleted. 2, Deleted. POWER PLANT (System No. 1) Expiration of maximum 1. Engine. 0-470-11 permissible operating 0-470-118 time. 0-470-118 0-470-15 FUEL (System No. 8) 1. Deleted. 2. Deleted. Changed 25 November 1968 6-1Replacement Systems 9, 10, 12, 14 REPLACE JEvery 1300 hours, 8-2 Changed 25,November 1968, T. 0. 1L-1A-6 SYSTEM AND ITEM OIL (System No. 9) 1, Deleted. IGNITION (System No. 10) 1. Deleted. PROPELLER (System No. 12) 1, Deleted, 2, Deleted. 3. Propeller (0-1D, TO-1D and O-1F Aireraft) ELECTRICAL (System No. 14) 1, Deleted. 2. Deleted, 3. Deleted. ‘MAN-MINS 48T.O. LL-19A-6 SECTION v—. ‘TEST FLIGHT INSPECTION REQUIREMENTS ‘This section lists all conditions under which test flights are required and com- plete inspection requirements for accomplishment of prescribed test flights. In- spection requirements in this section are established to assure a thorough inspec~ ton of the aircraft before flight, during fight, and upon completion of the test fight. When a test flight is performed for purposes of determining that specific equipment or systems are in proper operating condition, requirements not related to such equip- ment or systems should be disregarded. This section is divided into four separate parts. Part I contains all conditions and circumstances under which test Gights are required. Part II contains inspection requirements to be accomplished prior to a test flight. Part IT contains inspection requirements to be accomplished during a test flight. Part IV contains only direct post-test-flight inspection requirements to be accomplished upon completion of a test flight. Items of Part IV to be accom- plished by the air crew, upon completion of the test flight are listed first and ap- ropriately identified followed by ground crew and special post-test-flight require- ments. PARTI ‘The conditions required to accomplish a test flight are listed below. Under cir- ‘cumstances other than those listed, the need for an aircraft to be test flown follow- ing maintenance or repairs is an engineering decision to be exercised by Commanders through their Maintenance Officers. 1, To complete a Periodic Inspection. 2. When new or newly overhauled engine is installed. (A test flight for a ‘minimum duration of one hour is required). 3. When replacement or removal and reinstallation of a propeller and propeller governor is accomplished. 4. Whén-fixed flight control surfac reinstalled. have been replaced, or removed and 5. When moveable flight control surfaces have been replaced, or removed for major repair and reinstalled. 6. When flight control cables and rods have been replaced, rerouted, rerigged, or flight control mechaniam has been adjusted. 7. When major structural repair or modification 1s accomplished. ‘Test Flight tl‘Téist Flight T.0. 1L-19A-6 PART Il - PRIOR TO TEST FLIGHT REQUIREMENTS 1, Ground Crew Responsibilities. a. Complete preflight inspection performed in accordance with Section I of this handbook. Only double asterisk items need be accomplished, if test Might is not the first fight of the day. 2, Flight Crew Responsibilities. Complete preflight inspection requirements in accordance with applicable -1 Flight Handbook and Test Flight Worksheet, including the following: (2) Exterior and interior checks. (2) Before starting engines. (3) Starting engines. (4) Engine ground operation. (8) Ground test. (6) Taxting. (1) Before take-otf. (8) Preflight aircraft check. PART. - IN FLIGHT REQUIREMENTS 1, The following requirements to be accomplished by the pilot. b. 1 ‘Take-off. (1) Engine. (a) Maximum RPM. (b) Maximum cylinder temperature. (c) Ol pressure. (d) Fuel pressure. Cruise (1) Engine. (a) Oll pressure. (b) Fuel pressure.T.O. 1L-19A-6 ‘Test Flight (©) Oil temperature. (d) Cylinder head temperature. (e) Generator amperage. () Magneto drop in RPM. (g) Heating, defrosting and ventilation: (2) Instruments. (a) Air speec (b) Flight gyro. (©) Directional gyro. (@) Turn and bank indicator (e) Free air temperature gage. () Compasses. (@) Heating, defrosting and ventilatio (8) Radto. (a) VHF operation. 1. Transmitters, 2. Receivers. 3 Interphone. (b) FM operation. 1. BC-1335-A. 2. SCR-300-A. (©) Low frequency. 1, BC-1000-A. (4) Airplane Characteristics. (a) Aileron. (b) Rudder. (©) Elevators. (@) Alleron Trim, (e) Rudder Trim. (0) Elevator Trim. (@) Electric Flaps. c. Landing. (1) Brake.‘Test Flight T.0. 1L-19A-6 PART IV - POST TEST FLIGHT REQUIREMENTS 1... Flight Crew Responsibilities a. Postflight inspection accomplished in accordance with applicable -1 Flight Handbook. (1) Postflight engine check. 2) stopping engine. (8) Before leaving airpiane. b. Test flight discrepancies entered in the Te Flight Worksheets. 2. Ground Crew Responsibilities. a. After test flight following engine change. (1) Engines. {a) Proper safetying of cylinder hold down nuts and cap screws, () Oil and fuel lines, manifold, and accessories fo1 damage, evidence of leakage and security. (©). Removable oll screens and sump plugs for ‘metal particles and foreign material. T4.