TCDS A-2-599

Page No. 1 2 Rev. No. - - DEPARTMENT OF COMMERCE CIVIL AERONAUTICS ADMINISTRATION A-2-599 FAIRCHILD M-84-C December 19, 1949 AIRCRAFT SPECIFICATION NO. A-2-599 Manufacturer Fairchild Engine and Airplane Corporation Hagerstown, Maryland I - Model M-84-C, 4 PCLM, Approved September 12, 1949 Engine Continental W-670-6N Fuel 80 minimum octane aviation gasoline Engine limits For all operations, 2075 rpm (220 hp) Airspeed limits Level flight or climb 150 mph True Ind. Glide or dive 202 mph True Ind. Flaps extended 106 mph True Ind. C.G. range (+18.1) to (+25.2) at 2900 lbs. (+21.1) to (+25.2) at 3300 lbs. Straight line variation between points given. Effect of retracting landing gear 0 in, lbs. 3300 3100 2900 18 20 22 24 26 Inches Aft of Datum Gross Wt. in Lbs. Forw'd Limit Aft Limit Empty weight C.G. range None Datum Leading edge of wing at root section Leveling means Lugs on front and rear stabilizer attachment belts, left side. Maximum weight 3300 lbs. No. seats 4 (2 at +12, 2 at +62) Maximum baggage 50 lbs. (+86) Fuel capacity 48 gals. (+39) Oil capacity 4.1 gals. (-26) Control surface movements Aileron 34° up 25.5° down Flaps 55° down Elevator 26° up 25° down Elevator trim tabs 3° up 26° down Rudder 34° left 31° right Serial Nos. eligible 6200 only Required equipment Items 1, 2, 201, 202, 204, 301, 302, 303 A-2-599 Page 2 Specifications Pertinent to All Models Certification basis Airworthiness Certificate only (CAR 4a.031) Export eligibility Eligible for export to all countries except as follows, subject to the provisions of ASR No. 312 (MOP 2-4 contains same information): Canada - landplane - eligible skiplane - not eligible. Equipment: A Plus (+) or minus (-) preceding an item of equipment indicates net weight change when that item is installed. Propellers and Propeller Accessories 1. Propeller-Beech Controllable, Hub Model R201-100, Blades Model R201-211 Diameter: Not over 88 in., not under 86 in. High pitch setting 20.5°, Low pitch setting 8.0° Blade angle determined at 30 in. radius Propeller must be indexed in the zero position on the crankshaft. 56 lbs. (-62) 2. Propeller controls Electric Motor, Control and Installation 6 lbs. (-28) Landing Gear 201. Two main wheel-brake assemblies, 7.50-10, Type III. (a) Goodrich Model 752M Wheel Assembly No. G-3-73M Brake Assembly No. G-2-122 26 lbs. (+9) 202. Main wheel 4-ply-rating tires, 6.50-10, Type III with tubes 32 lbs. (+9) 204. Tail wheel assembly, 10 in. Type I (a) Variety Model VGC-10-10, full swiveling steerable, with 6-ply-rating tire and tube 6 lbs. (+216) Electrical Equipment 301. Generator-Eclipse Type 308, Model 4 16 lbs. (-34) 302. Battery-Reading Model R-24-L 25 lbs. (+85) 303. Starter-Eclipse Model E-801 8 lbs. (-33) NOTE 1. Current weight and balance report including list of equipment included in certificated weight empty, and loading instructions when necessary, must be in the aircraft at the time of original certification and at all times thereafter. NOTE 2. The following placards must be displayed in front of and in clear view of the pilots: "Intentional spinning prohibited." "Use 80 minimum octane aviation gasoline." - END -