# TCDS A-724: Fairchild Hiller Corporation - Type: Type certificate data sheet - Status: Current - Holder: Fairchild Hiller Corporation - Revision: 7 - Revised: January 31, 1966 - Product: Aircraft, Small Airplane - Certification basis: CAR 4a - Registered aircraft: 219, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/d2/58/d25821fe54bc43e821f0b52bb4225027ebdc2a4379b8e4661979915d868f4655 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/22F74A08921CDA19852567350067B05A.0001 - Page: https://openairdocs.org/tcds/A-724 ## Models (5) As the data sheet lists them. - M-62B - M-62A - M-62A-4 - M-62A-3 - M-62C ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 5 6 7 8 9 Rev. No. 7 - 7 7 - - - - - FEDERAL AVIATION AGENCY A-724 Revision 7 FAIRCHILD M62A (Army PT-19, -19A, -19A-AE, -19A-SL, -19B, -19B-AE) M62A-3 or M62A-4 (Army PT-26, -26A, -26B) M62B M62C (Army PT-23, -23-AE, -23-HO, -23-SL, -23A, -23A-SL) January 31, 1966 AICRAFT SPECIFICATION NO. A-724 Type Certificate Holder Fairchild Hiller Corporation Hagerstown, Maryland I - Model M-62A (Army PT-19, -19A, -19A-AE, -19A-SL, -19B, -19B-AE), 2 PO-CLM, Approved April 3, 1940 See NOTE 4(a) and (b) regarding modifications required for conversion of military models. See NOTE 5 regarding airplanes manufactured by other than Fairchild. Engine Ranger 6-440-C2. See Item 301(a) for optional engines. Fuel 65 minimum grade aviation gasoline. Engine limits For all operations, 2450 r.p.m. (175 hp.) Airspeed limits (CAS) Level flight or climb 130 m.p.h. (113 knots) Glide or dive 187 m.p.h. (163 knots) Flaps extended 95 m.p.h. ( 83 knots) See NOTE 3(a) for different values when rudder and elevator control system springs (Item 602) are not installed. Propeller Limits Refer to pertinent item of equipment except for limits when rudder and elevator control system springs (Item 602) are not installed, see Note 3(a). C.G. range (+18.6) to (+28.4). See NOTE 3(a) for different range when rudder and elevator control system springs (Item 602) are not installed. Empty weight C.G. range (+20.4) to (+23.0). When empty weight C.G. falls within this range, computation of critical fore and aft C.G. positions is unnecessary. Range is not valid when Buddy seat (Item 607) is installed or for any other non-standard arrangement. Maximum weight 2800 lb. At weights over 2450 lb., placard as follows is required: "INTENTIONAL SPINNING WITH FLAPS EXTENDED IS PROHIBITED." Maximum weight restricted to 2450 lb. when rudder and elevator control system springs (Item 302) are not installed. No. of seats 2 (One at +12 and one at +62) Maximum baggage 50 lb. (+98) Fuel capacity 49 gal. (One 24 1/2 gal. tank in each wing) (+39) Usable capacity 45 gal. (22 1/2 gal. in each tank) Oil capacity 4 gal. (-26) Control surface movements Ailerons 28° Up 16° Down Elevators 33° Up 25° Down Rudder 30° Right 30° Left Elevator trim tab 0° Up 25° Down Flaps 55° Down Serial Nos. eligible T40-101 to T40-428 inclusive; T41-429 to T41-1312 inclusive; T42-1313 to T42-1999 inclusive; T42-3000 to T42-3989 inclusive; T43-3990 to T43-3999 inclusive; T43-5000 to T43-5999 inclusive; T43-7000 to T43-7429 inclusive; and all AAF Nos. Use manufacturer's No. when available. See NOTE 5 regarding airplanes manufactured by other than Fairchild. Required equipment In addition to the pertinent required basic equipment specified in CAR 4a, the following items of equipment must be installed: 1, 102, 103, 104, 105, 106, 109, 602. See NOTE 3(a) regarding restrictions applicable when Item 602 is not installed. A-724 2 II - Model M-62A-3 and M-62A-4 (Army PT-26, -26A, -26B), 2 PO-CLM, Approved April 9, 1942 and February 19, 1947, respectively. See NOTE 4(a) and (c) for modifications required for conversion of military models. See NOTE 5 regarding airplanes manufactured by other than Fairchild. The M-62A-4 is identical to the M-62A-3 and both are the same as model M-62A except for engine. Engine Ranger 6-440-C5 Fuel 87 minimum grade aviation gasoline. Engine limits For all operations, 2450 r.p.m. (200 hp.) Airspeed limits (CAS) Level flight or climb 130 m.p.h. (113 knots) Glide or dive 187 m.p.h. (163 knots) Flaps extended 95 m.p.h. ( 83 knots) See NOTE 3(b) for other limits when rudder and elevator control system springs (Item 602) are not installed. Propeller Limits Refer to pertinent item of equipment except for limits when rudder and elevator control system springs (Item 602) are not installed, see Note 3(b). C.G. range (+18.6) to (+28.4). See NOTE 3(b) for different range when rudder and elevator control system springs (Item 602) are not installed. Empty weight C.G. range (+20.4) to (+23.0). When empty weight C.G. falls within this range, computation of critical fore and aft C.G. positions is unnecessary. Range is not valid when Buddy seat (Item 607) is installed or for any other non-standard arrangement. Maximum weight 2800 lb. At weights over 2450 lb., placard as follows is required: "INTENTIONAL SPINNING WITH FLAPS EXTENDED IS PROHIBITED." Maximum weight restricted to 2450 lb. when rudder and elevator control system springs (Item 602) are not installed. No. of seats 2 (One at +12 and one at +62) Maximum baggage 50 lb. (+98) Fuel capacity 49 gal. (One 24 1/2 gal. tank in each wing) (+39) Usable capacity 45 gal. (22 1/2 gal. in each tank) Oil capacity 4 gal. (-26) Control surface movements Ailerons 28° Up 16° Down Elevators 33° Up 25° Down Rudder 30° Right 30° Left Elevator trim tab 0° Up 25° Down Flaps 55° Down Serial Nos. eligible T42-4000 to T42-4334 inclusive (M-62A-3 or M-62A-4); T43-4335 to T43-4669 inclusive (M-62A-3 or M-62A-4); and all AAF Nos. Use manufacturer's No. when available. See NOTES 5 and 6 regarding airplanes manufactured by other than Fairchild. Required equipment In addition to the pertinent required basic equipment specified in CAR 4a, the following items of equipment must be installed: 1, 102, 103, 104, 105, 106, 602. See NOTE 3(b) regarding restrictions applicable when Item 602 is not installed. 3 A-724 III - Model M-62B, 2 PO-CLM, Approved May 14, 1941 Engine Warner Super Scarab 165 (Suffix "E") Fuel 73 minimum grade aviation gasoline. Engine limits Maximum continuous, 2100 r.P.M. (165 hp.) Take-off (one minute), 2250 r.p.m. (175 hp.) Airspeed limits (CAS) Level flight or climb 142 m.p.h. (124 knots) Glide or dive 203 m.p.h. (176 knots) Flaps extended 93 m.p.h. ( 81 knots) Propeller Limits Refer to pertinent item of equipment C.G. range (+19.8) to (+27.6). Empty weight C.G. range (+20.4) to (+22.7). When empty weight C.G. falls within this range, computation of critical fore and aft C.G. positions is unnecessary. Range is not valid when Buddy seat (Item 607) is installed or for any other non-standard arrangement. Maximum weight 2450 lb. No. of seats 2 (One at +12 and one at +62) Maximum baggage 50 lb. (+98) Fuel capacity 49 gal. (24 1/2 gal. tank in each wing) (+39) Usable capacity 45 gal. (22 1/2 gal. in each tank) Oil capacity 4 gal. (-26) Control surface movements Ailerons 28° Up 16° Down Elevators 33° Up 25° Down Rudder 30° Left 30° Right Elevator trim tab 0° Up 25° Down Flaps 55° Down Serial Nos. eligible T41-2000 to T41-2046 inclusive Required equipment In addition to the pertinent required basic equipment specified in CAR 4a, the following items of equipment must be installed: 2, 102, 103, 104, 105, 107, 108, 109, 110, 602. IV - Model M-62C (Army PT-23-, -23-AE, -23-HO, -23SL, -23A, -23A-SL), 2 PO-CLM, Approved March 26, 1945. See NOTE 4(a) and (d) regarding modifications required for conversion of military models. [ See NOTES 5, 6 and 8 regarding airplanes manufactured by other than Fairchild. Engine Continental W-670-6N. See Item 301(b) for optional engine. Fuel 65 minimum grade aviation gasoline. Engine limits For all operations, 2075 r.p.m. (220 hp.) A-724 4 Airspeed limits (CAS) Level flight or climb 130 m.p.h. (113 knots) Glide or dive 187 m.p.h. (163 knots) Flaps extended 95 m.p.h. ( 83 knots) Propeller Limits Refer to pertinent item of equipment. C.G. range (+18.6) to (+28.4). Empty weight C.G. range (+20.4) to (+23.0). When empty weight C.G. falls within this range, computation of critical fore and aft C.G. positions is unnecessary. Range is not valid when Buddy seat (Item 607) is installed or for any other non-standard arrangement. Maximum weight 2900 lb. At weights over 2450 lb., placard as follows is required: "INTENTIONAL SPINNING WITH FLAPS EXTENDED IS PROHIBITED." No. of seats 2 (One at +12 and one at +62) Maximum baggage 50 lb. (+98) Fuel capacity 49 gal. (One 24 1/2 gal. tank in each wing) (+39) Usable capacity 45 gal. (22 1/2 gal. in each tank) Oil capacity 4 gal. (-26) Control surface movements Aileron 28° Up 16° Down Elevators 33° Up 25° Down Rudder 30° Right 30° Left Elevator trim tab 0° Up 25° Down Flaps 55° Down Serial Nos. eligible All AAF Nos. Use manufacturer's No. when available. ¦ See NOTES 5, 6 and 8 regarding airplanes manufactured by other than Fairchild. Required equipment In addition to the pertinent required basic equipment specified in CAR 4a, the following items of equipment must be installed: 3, 102, 103, 105(b), 109, 111, 112(a), 113, 602. Specifications Pertinent to All Models Datum Wing leading edge at root section. Leveling means Leveling blocks welded on fuselage in rear cockpit Certification basis Type Certificate No. 724 (CAR 4a) Production basis None. Prior to original certification an FAA agent must perform a detailed inspection for workmanship, 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 Equipment: A Plus (+) or minus (-) sign preceding the weight of an item indicates net weight change when that item is installed. 5 A-724 Propellers and Propeller Accessories Superseded Item No. Current Item No. M-62A M-62A-3 M-62A-4 M-62B M-62C 101(a). 1. Propeller - fixed pitch wood (incl. hub) with following limits: (Model M-62A) Static r.p.m. at max. permissible throttle setting: Not over 2075, not under 1900. No additional tolerance permitted. Diameter: Not over 86 in., not under 83 in. 40 lb. (-77) --- --- (Model M-62A-3 and M62A-4) Static r.p.m. at max. permissible throttle setting: Not over 2190, not under 1925. No additional tolerance permitted. Diameter: Not over 86 in., not under 83 in. 101(b). 2. Propeller - fixed pitch metal, Curtiss 55518-4, with following limits: Static r.p.m. at max. permissible throttle setting: Not over 1810, not under 1710. No additional tolerance permitted. Diameter: Not over 86 in., not under 83 in. --- 48 lb. (-67) --- 1. 3. Propeller - fixed pitch wood (incl. hub) with following limits: Static r.p.m. at max. permissible throttle setting. Not over 1850, not under 1750.. No additional tolerance permitted. Diameter: Not over 90 in., not under 87 in. Must be in the 90º position (blades at right angles to the crank throw) when installed on Continental W-670-6A or -6N engines. --- --- 50 lb. (-59) 101(c). 4. Propeller - fixed pitch metal, Curtiss 55518-10 (Models M-62A-3 and M-62A-4 only) 50 lb. (-77) --- --- 201. 5. Propeller - fixed pitch wood (incl. hub) with following limits: Static r.p.m. at max. permissible throttle setting: Not over 1920, not under 1750. No additional tolerance permitted. Diameter: Not over 86 in., not under 83 in. --- 48 lb. (-67) --- 3. 6. Propeller - fixed pitch wood (less hub) Canadian built S&S, designation 220 issue "D" or Issue "E". 30 lb. (-77) --- --- 4. 7. Propeller - Beech controllable, R203 with R203-100 hub and R201-211-88 or R201-237-88 blades With mechanical control With electrically operated mech. control 60 lb. (-78) 66 lb. (-75) --- --- --- --- Pitch setting at 33 in. sta. for M-62A: Low 9º, high 22º Static r.p.m. at low pitch setting for M-62A, M-62A-3, M-62A-4: Not over 2210, not uner 2110. No additional tolerance permitted. Diameter: Not over 88 in., not under 86 in. Index propeller in 0 degree position. 5. 8. Propeller - Hartzell controllable, HC-12x20-1 with 8428-2 (formerly 8628) blades (for M-62A only) 60 lb. --- --- Pitch setting at 30 in. sta.: Low 11.3º, high 20.1º. Static r.p.m. at max. permissible throttle setting (low pitch): Not over 2190, not under 2090. No additional tolerance permitted. Diameter: Not over 86 in., not under 84 in. A-724 6 Superseded Item No. Current Item No. M-62A M-62A-3 M-62A-4 M-62B M-62C 9. Propeller - fixed pitch wood (less hub), Sensenich 82RS72 or any other fixed pitch wood propeller eligible for the engine power and speed which meets the following limits: (Models M-62A-3 and M-62A-4) Static r.p.m. at max. permissible throttle setting: Not over 2190, not under 2050. No additional tolerance permitted. Diameter: Not over 86 in., not under 82 in. 30 lb. (-77) --- --- Engines and Engine Accessories - Fuel and Oil System 104. Starter (Manual) Eclipse 4H-6) 15 lb. (-30) 15 lb. (-39) --- 105. Fuel pumps (a) Engine-driven (Pesco 227-D) (B) Wobble (U.A.P. D-2) 2 lb. (-32) 3 lb. (+18) 2 lb. ( -41) 3 lb. (+18) --- 3 lb. (+18) 106. Oil cooler (U.A.P. U-3150-D5) 12 lb. (-44) --- --- 107. NACA type ring cowl (Dwg. 684100) --- 24 lb. (-51) --- 108. Exhaust manifold with itensifier tube (Dwg. 641115-A) --- 27 lb. (-45) --- 110. Carburetor air maze (Dwg. 641147-1) --- 8 lb. (-40) --- 111. Starter (manual) - Fairchild Dwg. 64100 --- --- 29 lb. (-23) 112. Fuel pump (a) Engine-driven (Type F-10) --- --- 2 lb. (-31) 113. Carburetor air filter (air maze) --- --- 12 lb. (-30) 114. Starter (electric) (Bendix EF-80) (M-62A-3 and M-62A-4 only) 19 lb. (-30) --- --- 115. Rawdon cabin heater, installation and control (M-62A only) 7 lb. (-33) --- --- 202. Carburetor air maze (Dwg. 68633-E) 5 lb. (-58) --- --- 301. Engines (a) Ranger 6-440-C3 (M-62A only) Engine limits (73 min. grade fuel) For all operations, 2450 r.p.m. (180 hp.) (b) Continental W-670-6A No wt. change --- --- --- --- -5 lb. (-45) 303. Starter (electric) (Eclipse Y-150) 21 lb. (-30) --- --- 308. Oil cooper (U.A.P. U-3160-D5) +6 lb. (-44) --- --- Landing Gear and Floats 102. 7.50-10 wheels (Hayes 752M) with brakes and 6.50-10 tires 55 lb. ( + 9) 55 lb. (+ 9) 55 lb. (+ 9) 103. 8 in. streamline tail wheel and 6-ply cotton fabric tire 4 lb. (+216) 4 lb.(+216) 4 lb.(+216) 209. 10 in. smooth contour tail wheel and 6-ply tire +2 lb. (+216) +2 lb. (+216) +2 lb. (+216) 210. 7.50-10 wheels (Hayes 752A) with brakes and 6.50-10 cactus-proof tires +11 lb. (+9) +11lb, (+9) +11 lb. (+9) 211. 8 in. smooth contour tail wheel with 6-ply cotton fabric tire (a 4-ply cotton fabric tire may be used when airplane maximum weight is not over 2450 lb.) Neglect Wt. Change 212. Skis (eligible on any airplane of these models provided the propeller installation meets the minimum 9 in. ground clearance. The maximum weight for the skiplane will be the same as for the corresponding landplane or that shown in parenthesis after each ski model, whichever is (less) (a) Federal SC-4 (Maximum 2850 lb.) (b) Federal A-2500 (Maximum 2500 lb.), Federal Installation Dwg. 11G264 (c) Federal A-2500A (Maximum 2500 lb.) Federal Installation Dwg. 11G264 (d) Federal A-3500 (maximum 3500 lb.), Federal Installation Dwg. 11G264 (e) Federal A-3500A (maximum 3500 lb.), Federal Installation Dwg. 11G264 213. 8 in. smooth contour or streamline tail wheel and 4-ply smooth contour or nylon fabric tire. 7 A-724 Superseded Item No. Current Item No. M-62A M-62A-3 M-62A-4 M-62B M-62C Electrical Equipment 204. Six volt position light installation (reading 324L battery and box 15 lb. (- 16), Dwg. 68676) 22 lb. (0) 22 lb. (0) --- Following placard required in rear cockpit: "NIGHT SOLO FLYING FROM FRONT SEAT ONLY." 205. Twelve volt position light installation Dwg. 68650-3. 10 lb. (+39) 10 lb. (+39) --- Following placard required in rear cockpit: "NIGHT SOLO FLYING FROM FRONT SEAT ONLY." 206. Battery and box (Reading R-24) 28 lb. (+31) 28 lb. (+31) --- 208. Landing lights (a) One Grimes ST-250 (Dwg. 68650-1) +6 lb. (+25) +6 lb. (+25) --- (b) Two Grimes ST-250 (Dwg. 68650-2) +12 lb. (+25) +12 lb. (+25) --- 302. Generator (Elec. Spec. Co NA-1) 16 lb. (-27) --- --- 305. Shielding (Air Associates) +5 lb. (-50) --- --- 309. Generator (Bendix Model 8A Type 309) (M-62A-3 and M-62A-4 only) 21 lb. (-27) --- --- Miscellaneous (Not Listed Above) 109. Windshields, etc., for open cockpit (Dwg. 60574) 30 lb. (+37) 30 lb. (+37) 30 lb. (+37) 203. Cockpit enclosure (replacing item 109) (Dwg. 68400J) See Note 2(b) regarding placard required. +45 lb. (+53) --- +45 lb. (+53) 601. Irving model B acrobatic safety belt 3½ lb. ea. (+12, +62) 3½ lb. ea. (+12, +62) --- 602. Rudder and elevator control system springs (Fairchild Dwg. 62177) x x x 603. Cockpit enclosure (Radon Dwg. No. PT-1001) (Glide or dive speed limited to 187 mph CAS) +30 lb. (+49.5) +30 lb. (+49.5) +30 lb. (+49.5) 604. Cockpit enclosures, front and rear. (RAD Air Devices, Inc. drawings 24, 25, and 26) (Formerly Robertson) (Glide or dive speed limited to 187 mph CAS) 12 lb. (+12) 12 lb. (+62) 12 lb. (+12) 12 lb. (+62) 12 lb. (+12) 12 lb. (+62) 605. Top hatch cockpit enclosure (Service Equipment Co.) See Note 2(b) regarding placard required. 68 lb. (+47) 68 lb. (+47) 68 lb. (+47) 606. Cockpit enclosure, front and rear. (Holme-Shaw Products drawing D-101) (Glide or dive speed limited to 187 m.p.h. CAS) 5 lb. (+12 5 lb. (+62) 5 lb. (+12) 5 lb. (+62) 5 lb. (+12) 5 lb. (+62) 607. Buddy Seat (Service Equipment Co's dwgs. 1100, 1101, and 1102) (Not eligible unless airplane is also equipped with cockpit enclosure) 14 lb. (+45) --- 14 lb. (+45) NOTE 1. Current 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 carrier operators having an approved weight control system). NOTE 2. (a) The following placard should be added adjacent to each fuel tank filler opening: "ACTUAL CAPACITY 24 1/2 GAL. USABLE CAPACITY 22 1/2 GAL." (b) With cockpit enclosure Item 203 or 605 installed, the following placard(s) is (are) required in both cockpits: (1) On all airplanes: "COCKPIT ENCLOSURE TO BE OPEN ON ALL TAKE-OFFS AND LANDINGS." (2) On M-62A, M-62A-3 and M-62A-4 airplanes on which control system bungees have not been installed, and on all M-62B airplanes: "FLY SOLO FROM FRONT SEAT ONLY." (c) With position lights installed, the following placard is required in the rear cockpit: "NIGHT SOLO FLYING FROM FRONT SEAT ONLY." (d) The following placard is required for all models with maximum weight of more than 2450 lb.: "INTENTIONAL SPINNING WITH FLAPS EXTENDED PROHIBITED." A-724 8 NOTE 3. (a) Model M-62A and corresponding Army models are eligible without Item 602 at a maximum weight of 2450 lb. provided the C.G. range is restricted to (+19.8) to (+27.6) and a placard is installed which states, "INTENTIONAL SPINNING PROHIBITED". This spin placard may be removed provided the C.G. range is further restricted to (+19.8) to (+26.1). In either case, the following limitations apply: Airspeed limits: Level flight or climb 142 m.p.h. (CAS) Glide or dive 191 m.p.h. Flaps extended 95 m.p.h. Propeller limits: Static r.p.m. at maximum permissible throttle setting - not over 2075, not under 1900. No additional tolerance permitted. Diameter - not more than 94 in.; not less than 83 in. (b) Model M-62A-3 and M-62A-4 and corresponding Army and Canadian built models are eligible without Item 602 at a maximum weight of 2450 lb. provided the C.G. range is restricted to (+19.8) to (+27.6) and a placard is installed which states: "INTENTIONAL SPINNING PROHIBITED". This spin placard may be removed provided the C.G. range is further restricted to (+19.8) to (+26.1). In either case the following limitations apply: Airspeed limits: Level flight or climb 142 m.p.h. (CAS) Glide or dive 203 m.p.h. Flaps extended 95 m.p.h. Propeller limits: Static r.p.m. at maximum permissible throttle setting - with fixed pitch metal: not over 2080, not under 1980. With fixed pitch wood: Not over 2190, not under 1925. No additional tolerance permitted. Diameter (metal or wood): Not over 86 in.; not under 83 in. NOTE 4. (a) Prior to civil certification of Army models equivalent to all M62 series models, the following shall be accomplished in addition to requirements previously noted: (1) Rework the control sticks to safety the sticks in their sockets in accordance with Fairchild Service Bulletin No. 44-62-2. (2) Provide boots around the base of the control sticks in accordance with Fairchild Service Bulletin NO. 44-62-2. (3) Reinforce the forward attachment of vertical fin in accordance with Fairchild Service Bulletin No. 44-62-1. (b) Prior to civil certification of Army models equivalent to model M-62A, the following work must be accomplished in addition to requirements previously noted: (1) Revise airspeed pitot mast installation in accordance with Fairchild Service Bulletin NO. 45-62-9. Pitot installations emanating from the wing center section are considered satisfactory without modification. (2) In order to be eligible for night operation, any PT-19 Series airplane having uncertificated position lights should have them replaced with approved types. If Air Force Type A-9 wing tip lights are installed, they may be used provided the sand-blasted surface on the inside of the cover glass is painted black. (c) Prior to civil certification of Army models equivalent to Model M-62A-3 or M-62A-4, the following must be accomplished in addition to requirements previously noted: (1) Revise airspeed pitot mast installation in accordance with Fairchild Service Bulletin No. 45-62-9. Pitot installations emanating from the wing center section are considered satisfactory without modification. (2) Replace the aluminum alloy cockpit heat control valve box and valve with a valve and box made of ferrous metal at least .018 inch thick. If ordinary steel is used, it should be suitably protected against corrosion. In lieu of the foregoing, it will be satisfactory to remove the valve box and to seal the opening in the firewall with an overlapping sheet of ferrous metal secured with the present bolts and nuts. (3) Relocate the generator fuse and its spare so that they are accessible to the pilot. (d) Prior to civil certification of Army models equivalent to model M-62C, the following work must be accomplished in addition to requirements previously noted. (1) Carburetor hot air duct to be lagged with asbestos over entire length. (2) Revise airspeed pitot mast installation in accordance with Fairchild Service Bulletin No. 45-62-9. Pitot installations emanating from the wing center section are considered satisfactory without modification. 9 A-724 (3) Install cone type rubber engine mounts in accordance with Fairchild Aircraft Service Bulletin No. 45-62-11 dated September 4, 1945. NOTE 5. The following aircraft were fabricated by the Aeronca Aircraft Corporation, Howard Aircraft Corporation or St. Louis Aircraft Corporation as licensees and are identical to those manufactured by Fairchild Aircraft Corporation. They are distinguished by the suffix "AE", "HO" or "SL" to the model designation and serial number. AIRCRAFT FABRICATED BY AERONCA AIRCRAFT CORPORATION Model Serial Nos. PT-19A-AE 4763-AE to 4833-AE, inclusive PT-19B-AE 4843-AE to 6263-AE, inclusive PT-19A-AE 6273-AE to 10954-AE, inclusive PT-23-AE 1012-AE to 4753-AE, inclusive AIRCRAFT FABRICATED BY HOWARD AIRCRAFT CORPORATION Model Serial Nos. PT-23-HO 101-HO to 450-HO, inclusive AIRCRAFT FABRICATED BY ST. LOUIS AIRCRAFT CORPORATION Model Serial Nos. PT-19A-SL 224-SL, 235-SL, 238-SL, 251-SL, 254-SL, 280-SL, 282-SL, 284-SL, 286- SL, 288-SL, 290-SL to 304-SL, inclusive, 306-SL, 308-SL, 310-SL, 312- SL, 314-SL, 316-SL, 318-SL, 320-SL, 322-SL, 324-SL, 326-SL, 328-SL, 330-SL, 332-SL, 334-SL, 336-SL, 338-SL, 340-SL, and 342-SL. PT-23-SL 1-SL TO 200-SL, inclusive. PT-23A-SL 201-SL to 223-SL, inclusive, 225-SL to 234-SL, inclusive, 236-SL, 237- SL, 239-SL, to 250-SL, inclusive, 252-SL, 253-SL, 255-SL to 279-SL, inclusive, 281-SL, 283-SL, 285-SL, 287-SL, 289-SL, 305-SL, 307-SL, 309-SL, 311-SL, 313-SL, 315-SL, 317-SL, 319-SL, 321-SL, 323-SL, 325- SL, 327-SL, 329-SL, 331-SL, 333-SL, 335-SL, 337-SL, 339-SL, 341-SL, 343-SL to 350-SL, inclusive. NOTE 6. The following aircraft which were either fabricated or modified by Fleet Aircraft, Ltd., Fort Erie, Canada, are also eligible: Model Serial Nos. PT-23 FE-1 to FE-93, inclusive PT-26A FC-1 to FC-250, inclusive PT-26B FZ-198 to FZ-426, inclusive PT-26B FZ-699 to FZ-718, inclusive PT-26A FV-100 to FV-899, inclusive PT-26A FT-542 to FT-830, inclusive PT-26A FW-881 to FW-998, inclusive PT-26A FX-100 to FX-197, inclusive NOTE 7. It is recommended that the following limitations which were included in both AAF and RCAF operating instructions, be adhered to: MANEUVERS PROHIBITED (1) Outside loops, (2) Any maneuvers which might impose excessive negative loads on the airplane, (3) Snap rolls in excess of 100 m.p.h., (4) Immelman turns in excess of 170 m.p.h., (5) Slow rolls in excess of 150 m.p.h., (6) Indicated airspeed in excess of 191 m.p.h. NOTE 8. The following aircraft which were fabricated by D. D. Funk Aviation Company, Tulsa, Oklahoma are eligible for the model M-62C: Funk F-23A, Serial Nos. 1 and up when modified in accordance with Supplemental Type Certificate SA333SW. ......END..... ``` ## ADs (9, in force first) - [AD 43-07-01](https://openairdocs.org/ad/43-07-01): Wing Center Section Spars · Fairchild Hiller M-62A, M-62A-3 and M-62B - [AD 46-14-01](https://openairdocs.org/ad/46-14-01): Propeller Indexing · Fairchild Hiller M-62C - [AD 46-14-02](https://openairdocs.org/ad/46-14-02): Cockpit Heat Control Valve · Fairchild Hiller M-62A-3 and M-62A-4 - [AD 47-07-02](https://openairdocs.org/ad/47-07-02): Elevator Hinge Attachments · Fairchild Hiller M-62A, M-62A-3, M-62A-4 and 2 more - [AD 47-07-03](https://openairdocs.org/ad/47-07-03): Wing Inspection · Fairchild Hiller M-62A, M-62A-3, M-62A-4 and 2 more - [AD 47-07-04](https://openairdocs.org/ad/47-07-04): Control Stick Safetying · Fairchild Hiller M-62A, M-62A-3, M-62A-4 and 2 more - [AD 47-07-05](https://openairdocs.org/ad/47-07-05): Torque Tube · Fairchild Hiller M-62A, M-62A-3, M-62A-4 and 2 more - [AD 47-07-06](https://openairdocs.org/ad/47-07-06): Vertical Fin Attachment · Fairchild Hiller M-62A, M-62A-3, M-62A-4 and 2 more - [AD 48-45-01](https://openairdocs.org/ad/48-45-01): Wing Spar Inspection · Fairchild Hiller M-62A, M-62A-3, M-62A-4 and 2 more ## Registered aircraft by registry model (OpenAirDocs) - [Fairchild M-62A](https://openairdocs.org/model/fairchild-m-62a): 116 aircraft (registry code 3371604) - [Fairchild M-62A-3](https://openairdocs.org/model/fairchild-m-62a-3): 56 aircraft (registry code 3371618) - [Fairchild M-62C(PT-23A)](https://openairdocs.org/model/fairchild-m-62c-pt-23a): 32 aircraft (registry code 3371630) - [Fairchild M-62A-4](https://openairdocs.org/model/fairchild-m-62a-4): 10 aircraft (registry code 3371620) - [Fairchild Funk M62C F-23A](https://openairdocs.org/model/fairchild-funk-m62c-f-23a): 3 aircraft (registry code 3374004) - [Fairchild M-62B](https://openairdocs.org/model/fairchild-m-62b): 1 aircraft (registry code 3371628) - [Fairchild PT-26 M62A3](https://openairdocs.org/model/fairchild-pt-26-m62a3): 1 aircraft (registry code 3371603) - [Fairchild M-62C](https://openairdocs.org/model/fairchild-m-62c): 0 aircraft (registry code 3371635) - [Fairchild-Skelton M-62A](https://openairdocs.org/model/fairchild-skelton-m-62a): 0 aircraft (registry code 3371605) ## STCs approved under this data sheet (34) - [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC - [STC SA7965SW](https://openairdocs.org/stc/SA7965SW): Application of fabric and polyurethane finishing system.. Shady Aviation LLC - [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC - [STC SA03898NY](https://openairdocs.org/stc/SA03898NY): Installation and maintenance of ORATEX covering and coating material. Aircraft Design & Certification Ltd - [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc. - [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc. - [STC SA04776NY](https://openairdocs.org/stc/SA04776NY): The HIPEC Covering and Finishing System must be performed and maintained. HIPEC Aircraft Coatings Inc. - [STC SA01831WI](https://openairdocs.org/stc/SA01831WI): To allow the use of UL91 (minimum) grade aviation fuel. Petersen Aviation Inc - [STC SA01406NY](https://openairdocs.org/stc/SA01406NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K017 on single and multi-engine fixed light aircraft and rotary wing. Airwolf Filter Corporation - [STC SA02428SE](https://openairdocs.org/stc/SA02428SE): Installation of an Air Stream Switch for an electric time recording device on non-pressurized aircraft. Henry F Rogers/David E Polley - [STC SA00478CH](https://openairdocs.org/stc/SA00478CH): Installation of Cooper Superflite 102 Fabric.. Aviation Products Systems Inc. - [STC SA02283SE PAGE 2](https://openairdocs.org/stc/SA02283SE%20PAGE%202): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In Flight Data) CGR-30P. Electronics International Inc. - [STC SA02402SE PAGE 1](https://openairdocs.org/stc/SA02402SE%20PAGE%201): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) CGR-30C. Electronics International Inc. - [STC SA00068SE](https://openairdocs.org/stc/SA00068SE): Installation of fuel flow/pressure instruments. (W/TSIO-360-MB1). Electronics International Inc. - [STC SA01988SE](https://openairdocs.org/stc/SA01988SE): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) MVP-50P.. Electronics International Inc. - [STC SA02033AT](https://openairdocs.org/stc/SA02033AT): Modification to install an air-oil separator to prevent oil from being aspirated from the engine breather line.. M-20 Oil Separators LLC - [STC SA8075SW](https://openairdocs.org/stc/SA8075SW): Installation of fiberglass covering. (M-62 SERIES PT-19) (G-73 SCHWEIZER). Razorback Fabrics Inc - [STC SA1008WE](https://openairdocs.org/stc/SA1008WE): Installation of Poly-Fiber covering material.. Poly-Fiber Inc. - [STC SA489EA](https://openairdocs.org/stc/SA489EA): Installation of ARP Inc. carburetor ice detection system. Aircraft & Rotorcraft Products (ARP) Inc - [STC SA1308GL](https://openairdocs.org/stc/SA1308GL): Surrendered and incorporated into STC SA00478CH.. Cooper Aviation Supply Company, Inc. - [STC SA00068LA](https://openairdocs.org/stc/SA00068LA): Installation of tail wheel adapter ring.. R-R-R-Russ Aircraft - [STC SA00745CH](https://openairdocs.org/stc/SA00745CH): Installation of Cleveland Wheels and Brakes conversion Kit 199-167.. Kalamazoo Aviation History Museum - [STC SA2-952](https://openairdocs.org/stc/SA2-952): Installation of fiberglass covering.. Razorback Fabrics Inc - [STC SA1351WE](https://openairdocs.org/stc/SA1351WE): Replace existing fabric on wings, fuselage, empennage, and/or control surfaces, with Ceconite101 material. (262A Series -12). Ceconite Inc - [STC SA308EA](https://openairdocs.org/stc/SA308EA): Installation of carburetor ice detection system 105AP in single and twin engine aircraft and single engine helicopters powered by Continental, Franklin, and Lycoming type engines equipped with Marvel-Schebler MA-2, MA-3, MA-4, MA-4-5, MA-6 and HA-6 series carburetors. (Normal,Utility and Acrobatic Category airplanes and helicopters equipped with engines and carburetors as described.). Alfred R Puccinelli - [STC SA180SW](https://openairdocs.org/stc/SA180SW): Modification of aircraft to 1 PCLM Part 8 agricultural aircraft.. Olsen Ernest - [STC SA333SW](https://openairdocs.org/stc/SA333SW): Part 8 agricultural aircraft modification.. Olsen Ernest - [STC SA648SW](https://openairdocs.org/stc/SA648SW): Jacobs R755-9-B2M engine, propeller, revised aileron.. Olsen Ernest - [STC SA1350WE](https://openairdocs.org/stc/SA1350WE): Replace existing fabric on wings, fuselage, empennage and/or control surfaces with fiberglass cloth.. Ceconite, Inc - [STC SA4-1362](https://openairdocs.org/stc/SA4-1362): Spraying and dusting modification.. Weatherly Avn Co Inc - [STC SA4-1082](https://openairdocs.org/stc/SA4-1082): Ceconite 101 covering of fuselage, ailerons, elevators and rudder.. Cooper Engineering Corporation - [STC SA4-840](https://openairdocs.org/stc/SA4-840): Fabric replaced with glass cloth on wings, fuselage, empennage and/or control surfaces.. Air Fibre Inc - [STC SA612WE](https://openairdocs.org/stc/SA612WE): Pratt & Whitney R-985-AN1 engine.. Weatherly Avn Co Inc - [STC SH111WE](https://openairdocs.org/stc/SH111WE): Installation of step on either side or both sides of aircraft, attached to skid and torsion bar between Stations 60 and 100.. 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