TCDS A1WE

Page No. 1 2 3 Rev. No. 2 2 2 FEDERAL AVIATION AGENCY A1WE Revision 2 HAMILTON T-28R-1 T-28R-2 October 1, 1963 TYPE CERTIFICATE DATA SHEET NO. A1WE This data sheet which is a part of type certificate No. A1WE 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 Hamilton Aircraft Company, Inc. 6501 South Park Avenue Tucson, Arizona I - Model Hamilton T28R-2 (Normal Category), approved January 31, 1962 (see NOTE 2 regarding modifications required for conversion from Military T-28-A) Engine (1) Wright R-1820-56A, -66, -72A (with 3:2 reduction gear ratio) See NOTE 5 or (2) Wright 704C9GC1 (with 3:2 reduction gear ratio) Fuel 100/130 minimum grade aviation fuel Engine limits M.P. Alt. Engine (1) HP. R.P.M. In.Hg. Ft. Low Impeller Ratio Takeoff (five min.) 1350 2700 48.0 S.L. Maximum continuous 1200 2500 44.0 S.L. Maximum continuous 1200 2500 43.5 2500 High Impeller Ratio Takeoff (five min.) 1000 2600 44.5 14500 Maximum continuous 900 2500 42.0 11000 Maximum continuous 900 2500 40.0 17000 Engine (2) Low Impeller Ratio Takeoff (five min.) 1200 2500 45.5 S.L. Takeoff (five min.) 1200 2500 43.0 4300 Maximum continuous 1000 2300 39.5 S.L. Maximum continuous 1000 2300 37.2 6900 High Impeller Ratio Takeoff (five min.) 1000 2500 44.5 14200 Maximum continuous 900 2300 40.0 15200 Maximum continuous 900 2300 42.5 9700 Propeller and propeller limits Hamilton Standard, constant speed, 33D50 or 43D50 hub with 6601-17S blades Diameter: Max. 121-7/8", min. allowable for repairs 120" (See NOTE 4) Pitch setting at 42 in. station: Engine (1) Low 20.0°, high 57° Engine (2) Low 20.5°, high 57° Airspeed limits Never exceed 307 m.p.h. (266 knots) CAS Maximum structural cruising 236 m.p.h. (205 knots) CAS Maneuvering 180 m.p.h. (156 knots) CAS Flaps extended 160 m.p.h. (139 knots) CAS Landing gear extended 160 m.p.h. (139 knots) CAS C.G. range (+144.6) to (+150.2) (effect of landing gear extension - 2700 in.-lb.) Empty weight C.G. range None A1WE 2 Maximum weight Takeoff 7600 lb., Landing 7600 lb. No. seats 5(1 at 138.5) (2 at +171.5) (2 at +200.5) Baggage None Fuel capacity 170 gal. with 4 cells (two 66 gal. main wing tanks at +114 and two 19 gal. aux. wing tanks at +110) or 125 gal. with 2 cells (two 62.5 gal. main tanks at +164) See NOTE 3 Oil capacity 10 gal. (+65.2) Control surface movements Wing flaps Down 36.5° Aileron tab Up 12.0° Down 3° Aileron Up 15.5° Down 10° Elevator tab Up 15.0° Down 15° Elevator Up 24.0° Down 16.0° Rudder tab Left 19.0° Right 11.0° Rudder Left 25.5° Right 24.5° (Allowable limits plus or minus 1/2°) Serial Nos. eligible All UASF serial Nos. II - Model Hamilton T28R-1 (Normal Category), approved March 26, 1962 (see NOTE 2 regarding modifications required for conversion from Military T-28-A) Same as Model T28R-2 except for tandem cockpits, interior arragement, and flight controls Engine (1) Wright 1820-56A, -66, -72A (with 3:2 reduction gear ratio) See NOTE 5 (2) Wright 704C9GC1 (with 3:2 reduction gear ratio) Augmenters per Hamilton Dwg. 674-51 optional with 704C9GC1 engine. Fuel 100/130 minimum grade aviation fuel Engine limits M.P. Alt. Engine (1) HP. R.P.M. In.Hg. Ft. Low Impeller Ratio Takeoff (five min.) 1350 2700 48.0 S.L. Takeoff (five min.) 1350 2700 47.0 1300 Maximum continuous 1200 2500 44.0 S.L. Maximum continuous 1200 2500 43.5 2500 High Impeller Ratio Takeoff (five min.) 1000 2600 44.5 14500 Maximum continuous 900 2500 42.0 11000 Maximum continuous 900 2500 40.0 17000 Engine (2) Low Impeller Ratio Takeoff (five min.) 1200 2500 45.5 S.L. Takeoff (five min.) 1200 2500 43.0 4300 Maximum continuous 1000 2300 39.5 S.L. Maximum continuous 1000 2300 37.2 6900 High Impeller Ratio Takeoff (five min.) 1000 2500 44.5 14200 Maximum continuous 900 2300 40.0 15200 Maximum continuous 900 2300 42.5 9700 Propeller and propeller limits Hamilton Standard, constant speed, 33D50 or 43D50 hub with 6601-17S blades Diameter: Max. 121-7/8", min. allowable for repairs 120" (See NOTE 4) Pitch setting at 42 in. station: Engine (1) Low 20.0°, high 57° Engine (2) Low 20.5°, high 57° Airspeed limits Never exceed 307 m.p.h. (266 knots) CAS Maximum structural cruising 236 m.p.h. (205 knots) CAS Maneuvering 180 m.p.h. (157 knots) CAS Flaps extended 160 m.p.h. (139 knots) CAS Landing gear extended 160 m.p.h. (139 knots) CAS C.G. range (+144.6) to (+150.2) (effect of landing gear extension - 2700 in.-lb.) Empty weight C.G. range None 3 A1WE Maximum weight Takeoff 7600 lb., Landing 7600 lb. No. seats 2 (1 at 145) (1 at +198) Baggage None Fuel capacity 170 gal. with 4 cells (two 66 gal. main wing tanks at +114 and two 19 gal. aux. wing tanks at +110) or 125 gal. with 2 cells (two 62.5 gal. main tanks at +164) See NOTE 3 Oil capacity 10 gal. (+65.2) Control surface movements Wing flaps Down 36.5° Aileron tab Up 12.0° Down 3.0° Aileron Up 15.5° Down 10.0° Elevator tab Up 15.0° Down 15.0° Elevator Up 24.0° Down 16.0° Rudder tab Left 19.0° Right 11.0° Rudder Left 25.5° Right 24.5° (Allowable limits plus or minus 1/2°) Serial Nos. eligible All UASF serial Nos. Data Pertinent to All Models Datum 100.5 in. forward of fuselage nose jacking fitting (fitting located at Fuselage Station 50.5 right side of firewall) Leveling means Lugs in nose wheel well on aft bulkhead and side beams Certification basis CAR 3 as amended to May 15, 1956, and Amendments 3-1 thru 3-5. Type Certificate No. A1WE issued January 31, 1962. Date of Application for Type Certificate November 16, 1959 Production basis None. Prior to original certification of each aircraft, an FAA representative must perform an inspection for workmanship, material and conformity with the approved technical data for the modification from military to civil version; 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 certifcation. In addition, the following items of equipment are required: (a) FAA Approved Airplane Flight Manual, dated January 31, 1962, for Model T28R-2, and March 26, 1962, for Model T28R-1. NOTE 1. Current weight and balance report, including list of equipment included in certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at time of original certification. The certificated empty weight and corresponding center of gravity locations must include system oil of 41 lb. at (+65.2) and unusable fuel of 72 lb. at (+164) with standard two-cell installation with or without integral wing tip tanks and unusable fuel of 44 lb. at (+151.5) with four-cell installation. NOTE 2. Prior to civil certification, military model T-28A aircraft must be modified in accordance with Hamilaton Aircraft Dwg. List No. 674 to become Model T28R-2 aircraft or Dwg. List No. 674-1000 to become Model T28R-1 aircraft. NOTE 3. Integral wing tip tanks (42 gal. each wing) are approved for the 2 cell (125 gal.) fuel system only in accordance with Hamilton Aircraft Dwg. No. 674-56. NOTE 4. Placard on Instrument Panel in full view of the pilot: "Avoid continuous engine operation between 1850 and 2200 rpm during ground operation and in flight with landing gear or flaps extended. NOTE 5. The Wright 1820-56A, -66 and -72A engines are not approved for use on aircraft equipped with the 4 cell (170 gal.) fuel system. - END -