TCDS 1A18

Page No. 1 2 Rev. No. 5 5 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 1A18 Revision 5 BOEING (NORTH AMERICAN) NOMAD NA-260 (T-28A) November 18, 2009 TYPE CERTIFICATE DATA SHEET NO. 1A18 This data sheet which is a part of Type Certificate No. 1A 18 prescribes conditions and limita tions under which the product for which the Type Certificate was issued meets the requirements of the Civil Air Regulations. Type Certificate Holder The Boeing Company 4000 Lakewood Blvd. Long Beach, California 90846 Aircraft Specification Holder Rockwell International tran sferred ownership to The Boeing Company on July 23, 2009 Record North American Aviation transferred ow nership to Rockwell International Corp. on February 20, 1996 I - Model NA-260 (Normal Category), Approved July 29, 1960 (Conversion of USAF Model T-28A. See NOTE 2 regarding modifications required for conversion.) Engine Wright R1820-56S Fuel 100/130 minimum grade aviation gasoline Engine limits M.P. Alt. HP R.P.M. In.Hg. Ft. Low Impeller Ratio Takeoff (five minutes) 1300 2600 47.0 S.L. Maximum continuous 1200 2500 44.0 S.L. Maximum continuous 1200 2500 43.5 2500 High Impeller Ratio Maximum continuous 900 2500 42.0 11100 Maximum continuous 900 2500 40.0 17000 Propeller and Either of the following propellers may be used: propeller limits 1. Hamilton Standard constant-speed propeller installation (a) 33D50 hub with 6951A-18 blades 340 lb. (-8) Maximum diameter 121" Minimum diameter 118-3/4" Pitch settings at 42-in. station: Low 21°, High 55° (b) Hamilton Standard governor 4G10-3 6 lb. (+4) 2. Hamilton Standard cons tant-speed propeller installation (a) 43D50 hub with 6951A-18 blades 340 lb. (-8) Maximum diameter 121" Minimum diameter 118-3/4" Pitch settings at 42-in. station: Low 20 1/2°, High 54 1/2° (b) Hamilton Standard governor 4G10-3 6 lb. (+4) Airspeed limits Never exceed 343 m.p.h. (298 knots) Maximum structural cr uising 278 m.p.h. (241 knots) Maneuvering 185 m.p.h. (161 knots) Flaps extended 161 m.p.h. (140 knots) Landing gear extended 161 m.p.h. (140 knots) C.G. range (+95.1) at 7630 lb. (landing gear extended) (+100.4) at 8350 lb. Straight-line variation between these points Empty weight C.G. range None Datum Fuselage Station 0 (49. 5 inches forward of firewall) Leveling means Lugs in nose-wheel well on aft bulkhead and side beam Maximum weight Takeoff 8350 lb. Landing 7940 lb. No. seats 2 (1 at +95, 1 at +148) Maximum baggage 90 lb. (+153) Fuel capacity 170 gal. (2 66-gal. main wing tanks at +114, 2 19-gal. aux. wing tanks at +110) Oil capacity 8.8 gal. (+43) Control surface movements Wing flaps Down 37.5° Aileron tabs Up 12° Down 3° Aileron Up 15.5° Down 10° Elevator tabs Up 15° Down 15° Elevator Up 24° Down 16° Rudder tab Left 19° Right 11° Rudder Left 25.5° Right 24.5° Serial Nos. eligible U. S. Air Force 48-1371, 48-1372, 49-1492 through 49-1756 & 50-195 thru 50-319. Certification basis CAR 3 as amended to May 15, 1956 and amendments 3-1 and 3-2. Type Certificate No. 1A18 issued July 29, 1960. Date of Application for type certificate February 28, 1958. Production basis None. Before certification and presen tation to the FAA, the military version shall be inspected and found airworthy in acco rdance with CAR 1.67(d) amended to December 8, 1959. Prior to original certification of each aircraft, an FAA representative must perform a detailed inspection for workmanship, mate rials, and conformity with the approved technical data for the modifications from the military to the civil version; and also a check of the flight characteristics. Equipment The basic required equipm ent as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the following item of equipment is required: (a) FAA Approved Airplane Fli ght Manual, dated July 29, 1960. (North American Aviation, Inc. Report NA 58H-551) NOTE 1. Current weight and balance report, including list of e quipment included in certificated empty weight, and loading instructions when necessary, must be in each aircraft at the time of original certification and at all times thereafter. The certificated empty weight and corresponding center of gr avity locations must include system oil of 62 lb. at (+20) and unusable fuel of 21 lb. at (+108) with standard wing fuel tanks. NOTE 2. Prior to civil certification, military Model T-28A must be modified in accordance with North American Drawing No. 260-00002. .....END.....