TCDS A-723

Page No. 1 2 3 4 5 6 7 8 9 10 11 Rev. No. 23 22 22 22 22 22 22 22 22 22 22 Reformatted 5/95. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A-723 Revision 23 LOCKHEED 18 July 23, 2012 AIRCRAFT SPECIFICATION NO. A-723 This aircraft specification which is part of Type Certificate No. 723 prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations. Type Certificate Holder Lockheed Martin Aeronautics Company 86 South Cobb Drive Marietta, GA 30063 Type Certificate Holder Record Lockheed Aircraft Corporation Burbank, California I - Model 18 (See NOTE 11 for original civil and military designations and dates of approval and NOTE 12 for "Learstar" modification) Engines (1) 2 P&W Hornets S1E2-G, with 3:2 reduction gearing and two 4 1/2N dampers. (2) 2 P&W Hornets S1E3-G, with 3:2 reduction gearing and two 4 1/2N dampers. (3) 2 P&W Twin Wasps SC3-G, with 3:2 reduction gearing and one 3 1/2N damper. (4) 2 P&W Twin Wasps S1C3-G, with 3:2 reduction gearing or 16.9 spline coupled reduction gearing and one 3 1/2N damper. (5) 2 P&W Military R-1830-75 or -94, with 16:9 spline coupled reduction gearing and one 3 1/2N damper. (6) 2 P&W Twin Wasps S4C4-G, with 3:2 reduction gearing and one 3 1/2N damper. (7) 2 Wright Cyclones GR1820G-102A, with 16:11 reduction gearing and two 4 1/2N dampers. (8) 2 Wright Cyclones GR1820-G202A, 702C9GC1 or 2, with 3:2 reduction gearing and two 4 1/2N dampers. (9) 2 Wright Military R1820-56, -66, -72 or -72A with 3:2 reduction gearing and two 4 1/2N dampers. (Mixed engines permissible) (10) 2 Wright Cyclones 730C9GD1, 2, 3 or 4, with 3:2 reduction gearing and two 4 1/2N dampers. (11) 2 Wright Cyclones 704C9GC1, 2, 3 or 4, with 3:2 reduction gearing and two 4 1/2N dampers. (12) 2 Wright Military R1820-40, -60, -87 or -95, with 3:2 reduction gearing and two 4 1/2N dampers. Engine limits Engines (1) & (2) Fuel 87 Min. Grade Engine (3) Fuel 87 Min. grade Takeoff Maximum Continuous Takeoff Maximum Continuous (1 Min.) S.L. 5500 ft. (1 Min.) S.L. 12000 ft. In. Hg. 41.0/39.5 36.5 34.5 In.Hg. 42.0 36.0 34.0 RPM 2300/2500 2250 2250 RPM 2700 2550 2550 HP 900/885 800 800 HP 1050 900 900 Engines (4) Fuel 91 Min. Grade Engine (5) Fuel 100 Min. grade Takeoff Maximum Continuous Takeoff Maximum Continuous (1 Min.) S.L. 5500 ft. (1 Min.) S.L. 12000 ft. In. Hg. 48.0 41.5 39.5 In.Hg. 52.0 41.5 41.0 RPM 2700 2550 2550 RPM 2800 2550 2550 HP 1200 1050 1050 HP 1350* 1050 1050 *Ref NOTE 9(b) for requirements for aircraft w ith engine takeoff ratings in excess of 1200 R.H.P. Engine (6) Fuel 91 Min. grade Low Ratio Supercharger High Ratio Supercharger A-723 2 Takeoff Maximum Continuous Maximum Continuous (1 Min.) S.L. 7500 ft. 15,400 ft. In. Hg. 48.0 41.5 39.0 35.5 RPM 2700 2550 2550 2550 HP 1200 1050 1050 900 Engines (7) Fuel 91 Min. Grade Engine (8) Fuel 91 Min. grade Takeoff Maximum Continuous Takeoff Maximum Continuous (1 Min.) S.L. 5500 ft. (1 Min.) S.L. 6900 ft. In. Hg. 43.5 37.5 35.4 In.Hg. 45.5 39.5 37.2 RPM 2300 2300 2300 RPM 2500 2300 2300 HP 1100 900 900 HP 1200 1000 1000 Engine (9) *Fuel 91 & 100 Min. grade Low Ratio Supercharger High Ratio Supercharger Takeoff Maximum Continuous Maximum Continuous (1 Min.) S.L. 7500 ft. 11,100 ft. 17,000 ft. In. Hg. 44.0 (S.L.) 39.0 38.50 42.0 40.0 RPM 2500 2400 2400 2500 2500 HP 1200 1050 1050 900 900 *The above limits are applicable for both 91 and 100 mi n. grade fuel with appropriate carburetor adjustments in accordance with Wright Aeronautical Company instructions. Engine (10) Fuel 91 Min. Grade Engine (11) Fuel 91 Min. Grade Low Ratio High Ratio Supercharger Supercharger Takeoff Maximum Continuous Takeoff Maximum Continuous Max Cont (1 min.) S.L. 6900 Ft. (1 min.) S.L. 6900 ft. 15,200 ft. In. Hg. 45.0 39.0 36.7 In. Hg. 45.5 39.5 37.2 40.0 RPM 2500 2300 2300 RPM 2500 2300 2300 2300 HP 1200 1000 1000 HP 1200 1000 1000 900 Engine (12) *Fuel 91 & 100 Min. grade Low Ratio Supercharger High Ratio Supercharger Takeoff Maximum Continuous Maximum Continuous (1 Min.) S.L. 6900 ft. 15,200 ft. In. Hg. 45.5 39.5 37.2 40.0 RPM 2500 2300 2300 2300 HP 1200 1000 1000 900 *The above limits are applicable for both 91 and 100 min. grade fuel with appropriate carburetor adjustments in accordance with Wright Aeronautical Company instructions. Airspeed limits Vl (Level flight or climb) 238 mph (207 knots) True Ind. Vne (Never exceed) 279 mph (243 knots) True Ind. Vf (Flaps extended) 115 mph (100 knots) True Ind. Usable ceilings Engines (1) & (2) Ceiling Weight TIAS Propeller Deicers (Ft.) (lbs.) MPH (Knots) (Item) Prop Wing 6400 17500 122 (106) 1(c) No No 4800 17500 122 (106) 1(c) No Yes Engines (3) & (4) Ceiling Weight TIAS Prop. (Items) Fuel De-Icers (Ft.) (Lbs.) MPH (Knots) Eng (3) Eng (4) Grade Prop Wing 11800 17500 127 (110) 1(c) 1(c) 87 or 91 No Yes 9600 18500 128 (111) 1(c) 1(c) 91 No Yes 9100 18500 126 (110) 1(c) 1(c) 91 Yes (See Note 11) Yes 8300 18500 128 (111) - 1(a) 91 No Yes 3 A-723 6900 18500 127 (110) 1(c) 1(c) 87 No Yes Engine (5) Ceiling Weight TIAS Propeller Deicers (Ft.) (lbs.) MPH (Knots) (Item) Prop Wing 11300 17500 127 1(b) No No 10300 18500 127 1(b) No Yes Engine (6) Ceiling Weight TIAS Propelle r Deicers Supercharger (Ft.) (lbs.) MPH (Knots) (Item) Prop Wing Ratio 13750 17500 123 (107) 1(c) No No High 11800 18500 123 (107) 1(c) No No Low Engine (7) Ceiling Weight TIAS Propeller Deicers (Ft.) (lbs.) MPH (Knots) (Item) Prop Wing 10000 17500 123 (107) 1(c) No Yes 8900 18500 124 (108) 1(c) No No Engines (8) & (10) Ceiling Weight TIAS Propeller Deicers (Ft.) (lbs.) MPH (Knots) (Item) Prop Wing 12700 17500 121 (105) 1(c) or (d) No No 12200 17500 124 (105) 1(c) Yes (See Note 11) No 10800 18500 124 (108) 1(c) or (d) No No 10300 18500 124 (108) 1(c) Yes (See Note 11) No Engines (9), (11), & (12) (Supercharger Ratio High) Ceiling Weight TIAS Propeller Fuel Grade De-icers (Ft.) (lbs.) MPH (Knots) (Item) Eng. (9), (11), (12) Eng. (9) (12) Prop Wing 15100 17500 120 (104) 1(c) or (d) 91 100 No Yes 14600 17500 120 (104) 1(c) 91 100 Yes (See Note 11) Yes 13350 18500 120 (104) 1(c) or (d) 91 100 No Yes 12850 18500 120 (104) 1(c) 91 100 Yes (See Note 11) Yes Conditions for Usable Ceilings: (1) Standard Air (2) Either engine inoperative (3) Inoperative propeller fully feathered (4) Carburetor air intake on "cold air" and carburetor air filter in "off" position. (5) Operative engine at maximum conti nuous power at altitudes below the engine critical altitude and at rated rpm and full throttle at altitudes above the engine critical altitude. C.G. range Forward limit (28.1% MAC) (+0.3) (Gear down) Aft limit (37.2% MAC) (+10.8) Moment change due to landing gear retraction +30050 in.lbs. A-723 4 Maximum weights (Airplanes incor porating engines (1) or (2) and which have not been modified in accordance with NOTE 5 are limited to a landing and takeoff weight of 17,500 lbs.) Landing 17,500 lbs. Landing as cargo carrier 18,500 lbs. Takeoff 18,500 lbs. (See NOTE 3 for dump valve requireme nts, NOTE 4 for weight increase when de-icers are installed, NOTE 5 for modifi cations required for 18,500 lb. takeoff weight, NOTE 7 for modifications for 18,500 lb. landing weight and NOTE 9 for requirements for certification at or in excess of 19, 500 lbs. takeoff and 18,500 lbs. landing weights.) Number of seats 17 (Crew 2, 3 or 4 including 2 p ilots (-52.5), stewardess (+242.5) and radio operator (-21.5)). Maximum baggage Maximum capacity of compartments: No. 1 (nose) 1500 lbs. (- 133.5) No. 2 (fwd. belly) 800 lbs. (- 68.5) No. 3 (mid belly) 400 lbs. (- 20.5) No. 4 (rear belly) 700 lbs. (+ 30.5) Buffet 50 lbs. (+184.5) Fuel capacity 644 gals. (4 tanks in center section wing: 2 front tanks 150 gals. each (- 20.5) 2 rear tanks 172 gals. each (+22.5)) Oil capacity 40 gals. (1 tank in each nacelle 20 gals. each (-15)) or 44 gals. (1 tank in each nacelle 22 gals. each (-52.5)) Control surface movements Elevators 34° up 23.5° down Elevator trim tab 25° up and down Elevator anti-servo tab 12° elev. up 6.5° elev. down Ailerons 25° up 9° down Aileron trim tab 20° up 26° down (L.H. tab only) Aileron servo tab 3° up 14.5° down Rudders 31° right and left Rudder trim tabs 25° right and left Rudder servo tabs 6° right and left Serial Nos. eligible 2001 and up 2626, 6124, 6333, 6378, 6608, 7419, manufact ured by Gordon S. Hamilton Co. as Lockheed licensee. Required equipment In addition to the pertinent require d basic equipment specified in CAR 4a, the following items of equipment must be installed: Items 1(a), (b), (c), or (d), 101(a) or (b), 201(a), 202(a), 203(a), 204(a), 205(a), 206(a), 207(a) or (b), 601, 602(a) and (b). Specifications Pertinent to All Models Datum Spar centerline on underside of wing (fuse. sta. 188) MAC 115.84 in. L.E. MAC fuse. sta. 155.75 Leveling means Cabin window base line Certification basis Type Certificate No. 723 (CAR 4a) Production basis None. After February 1, 1944, prio r to original certification, a CAA agent must perform a detailed inspection for workmans hip, materials, and conformity with the approved technical data, and a check of the flight characteristics. Export eligibility Eligible for export to all countries subject to the provisions of MOP 2-4 except as follows: Canada: Landplane -eligible Skiplane - not eligible 5 A-723 Equipment: Approval for the installation of all items of equi pment listed herein has been obtained by the aircraft manufacturer except those items preceded by an asterisk (*). The asterisk denotes that approval has been obtained by other than the aircraft manufacturer. An item marked with an asterisk may not have been manufactured under a CAA monitored or approved quality control system, and therefore attention should be paid to workmanship and conformity with pertinent data called for in this specification. Propellers and Propeller Accessories 1. (a) (1) 2 propellers - Ham. Std., hubs 23E50, blades 6179A-0. 706 lbs. (-110) For interchangeable blade mode ls see Prop. Spec. No. 603 (NOTE 6). Dia.: Max. 10' 6-3/8", min. allowable for repairs 10' 3-5/8". No further reduction permitted. Low pitch setting 24° at 42 in. sta. (Eligible only with S1C3G engi nes having 16:9 spline-coupled reduction gearing and one 3 1/2N damper.) Placarded required: "Avoid continuous operation between 1200 and 1400 RPM and between 1940 and 2050 RPM." (b) (2) 2 propellers - Ham. Std., hubs 23E50, blades 6353-30. 790 lbs. (-105) For interchangeable blade mode ls see Prop. Spec. No. 603 (NOTE 6). Round or square tipped blades eligible. Dia.: Max. 10' 6-3/8", min. allowable for repairs 10' 3-5/8". No further reduction permitted. Low pitch setting 21° at 42 in. sta. for 1200 hp T.O. rating and 17° at 42 in. sta. for 1350 hp T.O. rating. (Eligible with "(5)" engines ha ving spline-coupled 16:9 reduction gears.) (c)(101) 2 propellers - Ham. Std., hubs 23E50, blades 6139-12. 758 lbs. (-110) For interchangeable blade mode ls see Prop. Spec. No. 603 (NOTE 6). Dia.: Max. 10' 6-3/8", min. allowable for repairs 10' 3-5/8". No further reduction permitted. Low pitch setting at 42 in. sta.: 17° for engines "(3), (4) and (7)"; 18° for engines "(1), (2), (8), (11) and (12)"; 20° for engine "(6)". 21° for engines "(9) and (10)". (Eligible for all engines except those having 16:9 reduction gearing). (d)(203) 2 propellers - Ham. Std., hubs 33D50, blades 6259-12, 6459-12, 610 lbs. (-106) 6505-12, 6511-12 or 6529-12. Dia.: Max. 10' 7", min. allowable for repairs 10' 4-1/4". No further reduction permitted. Low pitch setting at 42 in. sta.: 20° for engines "(8), (11) and (12"; 21° for engines "(9) and (10)". With blades model 6511-12 or 6529-12, following placard required: "Avoid continuous operation in flight below 1450 RPM and between 1650 and 1850 RPM." *(e) 2 propellers - Ham. Std., hubs 33D 50, blades 6511-12S or 6529-12S. 630 lbs. (-106) Dia.: Max. 10' 7", min. allowable for repairs 10' 4-1/4". No further reduction permitted. Low pitch setting at 42 in. sta.: 21.5° Feathered pitch setting at 42 in. sta.: 88.5°. (For engines listed in "Learstar" Modification in NOTE 12.) Placard required: "Avoid c ontinuous operation in flight below 1450 RPM and between 1650 and 1850 RPM." Engine and Engine Accessories - Fuel and Oil System 101. (a) (102 a) Residual fuel and oil for m odels with single row engines 35 lbs. (-79) (b) (102 b) Residual fuel and oil for models with P&W Twin Wasp engines 45 lbs. (-79.5) *(c) System fuel and oil ("Learstar" modification) 48 lbs. (-79) 102. (a)(201) Fuel dump valve installati on (Lockheed Dwg. No. 54418) 53 lbs. (+8) (See NOTE 3 for restrictions) *(b) 2 fuel dump valves, General Controls AV16B1165 6 lbs. (+5) A-723 6 Landing Gear 201. Main Wheel and Brake Assemblies (a) (15.00-16) 2 Goodyear wheels (No. 530161) 161 lbs. (-29) 2 Goodyear brakes (No. 510967-2) *(b) (12.50-16) 2 Goodyear wheels (No. 9540512) 196 lbs. (-29) 2 Goodyear brakes (No. 9540622) (Eligible for use on Model 18 when modified in accordance with Lear Dwg. 6048190. Eligible for use on "Learstar" when modified in accordance with Lear Dwg. 6048179.) (c) (15.00-16) Goodrich wheel-brake assembly (Dwg. No. H-14-957) 2 Goodrich wheels (No. H-3-857) 2 Goodrich brakes (No. G-2-626) 202. Main gear Tires and Tubes (a) 2 Firestone 10-ply HD, 15.00-16, with regular tubes 225 lbs. (-29) *(b) 2 Goodyear 10-ply type III, 15.00-16, with regular tubes 240 lbs. (-29) 203. Tail Wheel Assembly (a) 18 in. Hayes (Lockheed Dwg. 660058) (swiveling) 5 lbs. (+395) *(b) 17 in. Hayes D254A (swiveling) 5 lbs. (+395) 204. Tail Wheel Tire and Tube (a) 18 in. Firestone 6-ply with cactus-proof tube 19 lbs. (+395) *(b) 17 in. Goodyear 8-ply with regular tube 14 lbs. (+395) 205. Main Gear Shock Struts (a) 2 Aerol XY-450 LB 454 lbs. (-29) *(b) 2 Aerol XY-450 LB (Eligible for use on M odel 18 with Item 201(b) when 454 lbs. (-29) modified in accordance with Lear Dwg . 6048190. Eligible for use on "Learstar" with Item 201(b) when modified in accordance with Lear Dwgs. 6048179 and 6048201). 206. Tail Gear Shock Strut (a) Aerol 7976 27 lbs. (+382) *(b) Aerol 7976 per Lear Dwg. 6048189 27 lbs. (+382) (c) Aerol B-250 LA 27 lbs. (+382) 207. Main Gear Emergency Extension System (a) Independent oil-draulic system , manually operated 8 lbs. (0) (b) Nitrogen (Lockheed Dwg. 75346) 15 lbs. (-58) *(c) Nitrogen (Lear Dwg. 603625) 15 lbs. (-95) Interior Equipment 401. CAA Approved Airplane Flight Manual (Learstar modification) (The manual may be carried as part of, or bound with, the operator's "Operations Manual", but must remain in the airplane and must retain its identity as an individual manual.) 402. (401) Automatic pilot *(a) Lear Model L-5 (3 servos Model 118, 1 elevator tab servo Model 866 or 2204, and 1 rudder servo (optional) Model 2204B). Installation per Lear Dwg. 82525 (with installation of rudder tab servo per Lear Dwg. 700211) 77 lbs. (+23) (without installation of r udder tab servo) 75 lbs. (+13.5) Installation per Lear Dwg. 82825F with servo in wing 93 lbs. (+67) Main servo slip clutch torques: 175 (+ 10) in. lbs. 7 A-723 402. (401) Automatic pilot (cont'd) (a) Lear L-5 autopilot for installation Learstar modification of NOTE 12 this specification, with following servo stall torques in inch pounds measured at servos: rudder 70-90, aileron 135-165, elevator 80-100. Satisfactory for automatic approach with above values. Servos are: 118 AB, main , and 2218C-1, rudder and elevator tabs. Placards required in full view of automatic pilot controller: "Caution - when approach c oupler is engaged, elevator trim must be checked by momentarily disengaging the auto-pilot by means of the quick-disconnect button." (Note: This placard may be deleted if trim indicators for both pitch and yaw axes are installed.) "When using autopilot in crui se configuration, minimum terrain clearance is 250 ft. When using autopilot during approach, minimum altitude is 200 ft." (Minimum altitude for each case does not override any higher minimum operational altitude.) *(b) Lear Model L-2C installation in accordance with Lear Dwg. 91350A 60 lbs. (+103) Main servo Model 118K and trim tab servo Model 868G. Main servo slip clutch torques: 175 in. lbs. Placards required in full view of automatic pilot controller: "When using autopilot for cruising operations the minimum terrain clearance is 250 ft. When using autopilot during approach, minimum altitude is 200 ft., pilot's seat belt fastened and hand on control wheel." (Minimum altitude for each case does not override any higher minimum operational altitude.) "Do not override autopilot to increase angle of bank." *(c) Pioneer PB-10, 3 main servos 15601-1A, elevator tab servo 207 lbs. (-23) 15602-1B, throttle servo 15620-2A. Installation per Grand Central Aircraft, Glendale, California Dwgs. 20493, 20495, 20497, 20499, 20536, 20537 and photos 1 through 6. Airplane Flight Manual Revision dated 4-11-55 required. Servo stall torque inch pounds measured @ servos are satisfactory for FPC: Aileron 372 - 480, Elevator 325 - 400, Rudder 272 - 413. Miscellaneous 601. (103) Fixed wing slot in stallation 25 lbs. (-7) 602. (a)(104a) Wing trailing edge extensi on (Lockheed Dwg. 74349 or 79310) 35 lbs. (+94) (b)(104b) Elevator control system damping unit (Lockheed Dwg. 12 lbs. (-16) No. 73975) (When complete automatic pilot is installed, or when changes described in Lockheed Service Bulletin Bo. 18-44 are incorporated, this item may be omitted.) NOTE 1. (a) An approved Lockheed weight and balance report including list of equipment included in certificated weight empty, and loading instructions when necessary, must be in each aircraft at the time of original certification and at all times thereafter, except in the case of air ca rrier operators having an approved weight control system. (b) Lear Report No. 17 "Weight and Balance and Equipmen t List" showing interior arrangement and locations and capacities of cargo and luggage compartments shall be in each "Learstar" modification of the Lockheed Model 18 at the time of original approval and at all times thereafter. NOTE 2. (a) Placard lavatory door as follows: "This room not to be occupied during takeoff and landing." (b) A placard which states the order in which the fuel tanks are to be used must be installed at the fuel selector valve. The order of using fuel shall be the same as i ndicated in the loading instructions. (In lieu of posting such a placard in air carrier airplanes, and subject to the a pproval of the Chief, Air Carrier Safety Division, definite instructions must be issued by the operator to the e ffect that fuel tanks should be filled and used in order indicated in their approved loading instructions.) A-723 8 NOTE 2. (cont'd) (c) For those airplanes requiring an "Airplane Flight Manual", the following placard shall be placed on the instrument panel in full view of the pilot, and wh en appropriate, the instruments should be properly marked: "This airplane shall be operated in compliance with the operating limitations specified in the CAA Approved Airplane Flight Manual." (d) The following propeller placards shall be placed on the instrument panel in full view of the pilot and the tachometer appropriately marked for those airplane s on which the propellers listed below are installed. (1) Item 1(a): "Avoid continuous operation be tween 1200 and 1400 RPM and between 1944 and 2050 RPM. (2) Item 1(d) with blades Model 6511-12 or 6529-12 a nd Item 1(e): "Avoid continuous operation in flight below 1450 RPM and between 1650 and 1850 RPM." NOTE 3. Fuel jettisoning provisions are not required for aircraft having not more than 1000 lbs. spread between maximum takeoff and maximum landing weight. If dump valves other than Item 102(a) are installed, the former shall be removed or made positively inoperative. NOTE 4. Maximum landing or takeoff weight may be increased 105 lbs. when complete de-icer system is installed. Applicable to aircraft up to 19,500 lbs. takeoff weight only. NOTE 5. For certification at 18,500 lbs. take off weight (or landing weight as cargo carrier) Model 18 airplanes of Serial Nos. 2001 to 2024, inclusive, must be modified structurally to conform with drawing changes and new drawings listed on Lockheed Service Project Drawing No. 1037. Airplanes of Serial Nos. 2025 and up have had the structural revisions necessary for eligibility at 18,500 lbs. takeoff weight (or landing weight as cargo carrier) incorporated in the airplanes at the factory. NOTE 6. Replacement surfaces which incorporate flush type riveti ng may be substituted for surfaces having external head type rivets except that in the event that an outer wing panel or wing tip (with external head rivet) is being replaced by a flush type rivet panel, both left and right surfaces must be replaced. NOTE 7. All Model 18 aircraft which have been modified in accordance with NOTE 5 are eligible as cargo carriers with a maximum landing weight of 18,500 lbs. when the passenger seats are removed and the cabin is revised in accordance with Lockheed Service Project Dwgs. 1221A and 1222. Wh en airplanes of these models are certificated as cargo carriers, no passengers may be carried and satis factory loading instructions must be provided. NOTE 8. The various Air Force and Navy models were originally built as commercial aircraft but the cabins were converted for Military use by removal of seats and the installati on of troop benches or cargo provisions. Also, the military models differed from the Model 18 for certain powerplant in stallation details, minor structural differences and were equipped with a 12-volt electrical system. Prior to cer tification as a civil aircraft, the following must be accomplished in addition to compliance with Lockh eed Service Technical Report No. 1 and applicable AIRWORTHINESS DIRECTIVES: (a) Each airplane must satisfactorily pass an insp ection for conformity, possible hidden damage, and for workmanship and materials used in making any repairs and/or alternations. Particular attention should be paid to placards, instrument markings and windshield equipment. (b) The following military equipment should be removed: Propane priming, auxiliary fuel tanks and supporting structure. Such brackets and supporting structure as w ill not interfere with the safe operation of the aircraft may, at the operator's discretion, be left in the airc raft as long as the equipment has been rendered inoperative. Operators may retain the oil dilution system and hopper type oil tank upon compliance with paragraph 1 of Airworthiness Directive 46-13-3. Otherwise the inst allation of a conventional oil tank and rework of the standpipe will be required in accordance with paragr aphs 2 and 3 of Airworthiness Directive 46-13-3. (c) If the Jack & Heintz automatic pilot directional gyro control unit, Part No. JH5000 and climb and turn control unit, Part No. JH6000, are installed, they should be of the modified version identified by a yellow "M" adjacent to name plate, as covered in Jack & Heintz Service Bu lletin No. P-1. If the Jack & Heintz A-3A autopilot servo