TCDS 4A20

Page No. 1 2 Rev. No. - - U. S. DEPARTMENT OF COMMERCE CIVIL AERONAUTICS ADMINISTRATION 4A20 TRANSLAND Ag-2 October 10, 1958 TYPE CERTIFICATE DATA SHEET NO. 4A20 This data sheet which is a part of type certificate No. 4A20 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 Transland Aircraft Company 2600 West 247th Street Torrance, California I - Model Ag-2, 2 PCLM (Normal Category), Approved June 24, 1958 Engine Pratt & Whitney Wasp S3H1 (R-1340-AN-1, R-1340-36, -47 or -49) Fuel 80/87 min. grade aviation gasoline Engine limits Takeoff (one minute), 36.0 in.Hg., 2250 r.p.m. (600 hp.) All other operations, (Sea level) 34.0 in.Hg., 2200 r.p.m. (550 hp.) (5000 ft.) 32.5 in.Hg., 2200 r.p.m. (550 hp.) Propeller and 1. Propeller - Hamilton Standard, constant speed, propeller limits hub 12D40, blades 6101-12 175 lb. (-57.5) Diameter: Maximum 9'1", min. allowable for repairs 8'10-5/8". No further reduction permitted Pitch settings at 42 in. sta.: Low 10°, high 26° Placard required: "Avoid continuous ground operation between 1280 and 1800 R.P.M. unless the aircraft is headed into the wind." 2. Constant speed governor, Model 1M12A 4.5 lb. (-49) Airspeed limits Never exceed Vne 165 m.p.h. (143 knots) Normal operating Vno 131 m.p.h. (114 knots) Maneuvering Va 129 m.p.h. (112 knots) Flap extended speed Vfe 106 m.p.h. ( 92 knots) C.G. range (+24.5) to (+29.3) at 6000 lb. (+24.2) to (+31.0) at 4510 lb. (+24.0) to (+31.0) at 3000 lb. or less Empty weight C.G. range None Datum Leading edge of wing (fuselage station 81.00) Leveling means Fuselage upper longeron (cockpit rail) Maximum weight 6000 lb. (takeoff and landing) No. seats 2 (one at +87 and one at +119) Maximum cargo 2000 lb. either as liquid load in tanks (+26) or dry load in fuselage hopper (+25.25) Fuel capacity Two wing tanks 63.0 gal. each (+26) Total usable fuel 126 gal. Unusable fuel 1 gal. each tank (+26) 4A20 2 Oil capacity 10 gal. (-7) Control surface movements (Movements measured from neutral position of surface) Down Up Tolerance Flap 20.0° 0.0° +1° Aileron 5.5° 6.5° +1° Slot lip 11.5° 24.0° +3° Elevator 19.0° 26.5° +1° Horizontal Stabilizer 4° 30' 6° 45' +20' Rudder 25° right 25° left +1° Serial Nos. eligible 1 and up Certification basis CAR 3, November 1, 1949, amendments 3-1 through 3-12. Type Certificate No. 4A20 issued June 24, 1958 Date of Application for Type Certificate March 23, 1955. Production basis None. Prior to original certification of each aircraft, a CAA representative must perform a detailed inspection for workmanship, materials, and conformity with approved technical data, and a check of the flight characteristics. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. NOTE 1. (a) 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 certif ication and at all times thereafter. (b) The airplane must be loaded so that the C.G. is within the specified limits at all times taking into consideration the effect of fuel and cargo released overboard. NOTE 2. The following placards or markings must be displayed in the locations noted: (a) In front of and in clear view of the pilot: (1) "This airplane must be operated as a normal category airplane in compliance with the operating limitations stated in the CAA Approved Flight Manual. All acrobatic maneuvers, including spins, are prohibited." (2) "Avoid continuous ground operation between 1280 & 1800 R.P.M. unless the aircraft is headed into the wind." ....END....