TCDS A-783

Page No. 1 2 3 4 Rev. No. 10 8 8 8 Rev 10: Added Type Certificate holder record and reformatted all pages. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A-783 Revision 10 Frakes Aviation G-73 June 11, 2012 AIRCRAFT SPECIFICATION NO. A-783 Type Certificate Holder Frakes Aviation Claburne Airport Route 3, Box 229-B Cleburne, Texas 76031 Type Certificate Holder Record Grumman Aircra ft Engineering Corp. transferred TC A-783 to Grumman American Aviation Corporation on April 1, 1975 Grumman American Corporation transferred TC A-783 to Gulfstream American Corporation on June 1, 1979 Gulfstream American Corporation transferred TC A-783 to Frakes Aviation on April 1, 1981 I. Model G-73, 12 PCAmM, Mallard, approved September 8, 1947 Engines 2 P & W Wasps S3H1 or Milita ry R-1340-36, -47, -49, -51 or -AN-1 (See also Item 109 for optional engines.) Fuel 91 min. octane aviation gasoline Engine limits MP HP RPM In.Hg . ALT Takeoff (1 minute) 600 2,250 36.0 - Max. continuous 550 2,200 34.0 S.L. 550 2,200 32.5 5,000' (Straight line manifold pressure variation with altitude shown) Airspeed limits (CAS) Level fli ght or climb 220 mph (191 knots) Glide or dive 270 mph (235 knots) Flaps extended 125 mph (109 knots) C.G. range (-17.3) to (-7.4). Moment change due to retraction of landing gear (nose and main) is +1,032 in. lb. Datum Rear face of main wing beam (Sta. 233.65). Leveling means Fore and aft leveling lugs located in left or right wheel pocket. Maximum weight 12,750 lbs. No. seats Two cockpit (-108.65); 10 cabin . (See Approved Airplane Flight Manual for arrangement.) Maximum baggage Forward compartment 460 lb. (Sta. 53 to 93, max. floor loading 50 lb./sq. ft.). Aft compartment 540 lbs. (Sta. 384 to 428, max. floor loading 75 lb./sq.ft.) Model G-73, 12 PCAmM, Mallard, approved September 8, 1947 (Continued) Fuel capacity 360 gal. (180 gal. in 7 cells in ri ght and left wing at (-14) for airplane serial nos. J-49 and up. Original fuel capacity for airplane serial nos. J-1 through J-4 and J-9, J-10 and J-11 is 330 gal. consisting of 165 gal. in one integral tank in each wing. Original fuel capacity for airplanes J-8, J-12 through J-48 is 380 gal. consisting of 190 gallons in one integral tank in each wing. J-1 through J-48 also eligible for bladder-type fuel cell installation in accordance with Grumman data. See Notes 1B a nd 1C regarding "System Fuel and Oil." Oil capacity 20 gal. (Two tanks, 10 gal. each in nacelles) (-16) Control surface movements Wing flaps Up - Down 45° Elevator trim tab Up 70° Down 25° Elevator Up 30° Down 10° Aileron Up 21° Down 18° Rudder trim tab Right 20° Left 20° Rudder Right 25° Left 25° Serial nos. eligible J-1 and up Required equipment Items 1, 102, 103, 104(a) or (b), 201, 202, 302 and 401. Item 302, battery required since electrical power is required for auxiliary electric fuel pumps. Specifications Pertinent to All Models Certification basis Type Certificat e No. 783 (Transport Category, CAR 4a). Production basis None Equipment A plus (+) or minus (-) sign preceding the weight of an item indicates net weight change when that item is installed. Propellers and Propeller Accessories, except De-Icing Equipment 1. Two Hamilton Standard propellers, hubs 23 D40- 51, blades 6533A-18 or 6533A-18S. 252 lb. each (-79) Diameter: 8'6-5/16" max., 8'4-5/16" min. allowable for repairs. For interchangeable blade models see Propeller spec. no. 719 (Note 6). Low pitch setting 12° at 42 in. sta. Provision is made in the propeller hub for a positive high pitch stop in order to meet flight performance requirements. This is indicated by the dash number (-51) on the propeller hub. 2. Hamilton Standard Propeller Governor 4K11. 6 lb. each (071) Engine and Engine Accessories - Fuel and Oil System 101. Two starters, Eclipse Type 1416-15 27 lb. each (-42) 102. Two oil coolers, Clifford Mfg. Co. 10" Diamond X 18 lb. each (-49) 9 in. Long No. B-36690 with UAP 4 port valve UD-4785. 103. System fuel and oil (see Note 1A for definition). (a) Unusable fuel and oil is 15 lb./engine and 42 lb./engine respectively. 114 lb. (-39) (b) On J-8 and J-12 through J-26 unusable fuel and oil/engine is 27 lb. and 42 lb. respectively. 138 lb. (-39) (c) On J-27 and subsequent usable fuel and oil/e ngine is 9 lb. and 42 lb. respectively. 102 lb. (-39) 104. Fuel pumps (a) Pesco 2E-207, electric-driven fuel booster pump (Serial Nos. J-1, J-2, and J-3) 6 lb. each (-29) (b) Thompson Product TFD-10300, el ectric-driven fuel booster pump (Serial No. J-4 and up) 7 lb. each (-29) 105. Surface combustion heater ADS-100N-041G 90 lb. each (+206) 106. Integral auxiliary fuel tanks (50 gal. each) in wing tip float, including pump and line 19 lb. each (+10) 107. Two vacuum pumps, Type B-2B or Aero Model A 505-DD, for de-icer installation only. 4 lb. each (-49) 108. Oil dilution system. 3 lb. (-39) 109. Engine - Pratt and Whitney WASP S1H1 Use actual weight increase A-783 3 of 4 Model G-73, 12 PCAmM, Mallard, approved September 8, 1947 (Continued) LIMITS HP RPM HP In.Hg. ALT Takeoff (1 minute) 600 2,250 36.5 - Maximum continuous 550 2,200 35.0 S.L. 550 2,200 33.0 8,000' (Straight line MP variation with altitude) In order to provide adequate engine cooling, when P & W S1H1 engine is installed, cowling and intercylinder duct must be modified per Grumman Drawings 108335B, 108344, 109050B, and 109051C. Flight Manual revised pages 1, 2, 5, 6, 9, 11, 26, 30, and 35, approved May 18, 1950, required. Landing Gear and Floats 201. Two 9.50-16 main wheels, Goody ear L 9.50-16HBA, with brakes and 9.50-16 6-ply nylon tires 120 lb. each (+4) 202. 19x6.89-10 nose wheel, Bendix Type B-1, Assembly No. 145308A and 19x6.80-10 6-ply rayon tire (tire to be placarded fo r 80 psi inflation pressure). 37 lb. each (-174) Electric Equipment 301. Two generators, Eclipse Type 1273-3, insta lled on J-1, J-2, and J-3. 32 lb. each (-58) Leece & Neville 2471-G12, installed on J-4 through J-9 Leece & Neville 2473-G12, installed on J-10 and subsequent 302. Battery, Exide 12-TS-9L 73 lb. (-4) 303. Two landing lights, Grimes G-3801-1 or G-3801-3 7 lb. each ((+18) Interior Equipment 401. CAA Approved Airplane Fli ght Manual revised June 30, 1947. (The manual may be carried as part of or bound with the operator's "Approved Operations Manual" but must remain in the airplane and must retain its identity as an individual manual. 402. Two 3- minute parachute flares, International 23 lb. each (+221) 403. Two windshield wipers, Kearfoot Type 2 lb. each (-134) 404. Safety belt and harness asse mbly, NAF 1201-1 (cockpit) 405. Sperry Model A-12 automatic pilot installation 194 lb. (-144) 406. Lear L-2C automatic pilot To be installed in accordance with Lear Draw ing No. 95600. 62 lb. (- 7) The following placards to be installed: (1) On autopilot master switch, "AUTOPILOT MASTER SWITCH ON," (2) On quick disconnect switch, "AUTOPILOT DISCONNECT ON-OFF," (3) In plain view of the pilot, "DO NOT USE AUTOPILOT BELOW 450 FEET ABOVE TERRAIN IN CRUISE CONFIGURAT ION," "DO OT USE AUTOPILOT BELOW 300 FEET ABOVE TERRAIN IN APPROACH CONFIGURATION." Servo slipclutch settings measured on th e ground: rudder 175 lb., aileron 50" lb., elevator 75" lb. (Approach coupler not investigated; therefore, not eligible.) Airplane Flight Manual Supplement date d January 14, 1952, is required equipment. De-Icing Equipment (Propellers, Wing and Windshield) 501. Surface de-icers, Goodrich Type II, Model 705 (a) Two wing boots (removable) 24 lb. each ( -23) (b) Stabilizer boot (removable) 8 lb. each (+272) (c) Fin boot (removable) 7 lb. (+300) (d) De-icer installation ge neral equipment (fixed portion) (1) Mechanically cycled installation 60 lb. (+17) (2) Electronically cycled installation 74 lb. (+37) 502. Propeller anti-icer (a) Propeller lines and Hamilton Standard s linger rings 4 lb. (- 79) (b) 7.5 gal. alcohol tank, pump and accessories (flui d weight 50 lb.) 62 lb. (+ 7) 503. Windshield anti-icer (Utilizes fluid from propeller anti-icer tank) 2 lb. (- 19) Model G-73, 12 PCAmM, Mallard, approved September 8, 1947 (Continued) Miscellaneous (not listed above) 601. Installation of revised wing leading edge in accordance with Grumman Drawing No. 106930. (Not eligible with Item 501 in stalled.) 30 lb. (- 19) NOTE 1. A. Current weight and balance repor t including list of equipment included in certificated empty weight, and loading instructions when necessary, must be in each aircraft at the time of orig inal certification and at all times thereafter (except in the case of air carrier operato rs having an approved weight control system). B. "System Fuel and Oil" is that amount required to fill both systems and the tanks up to the tank outlets to the engines, when the airplane is in the level attitude. "System Fuel and Oil" and all hydraulic fluid must be included in the certificated weight empty. C. Fuel and oil tank capacities do not include any "System Fuel and Oil." NOTE 2. The following placard shall be placed in the instrument panel in full view of the pilot. "THIS AIRPLANE SHALL BE OPERATED IN ACCORDANCE WITH SECTION 1 'OPERATING LIMITATIONS' OF FLIGHT MANUAL WHICH SHALL BE CARRIED IN THE PILOT'S COMPARTMENT AT ALL TIMES." .....END.....