TCDS A11WE

Page No. 1 2 3 4 Rev. No. 4 - 3 - DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A11WE Revision 4 Aerostar 360 400 October 22, 1992 TYPE CERTIFICATE DATA SHEET NO. A11WE This data sheet which is a part of type certificate No. A11WE prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder Aerostar Aircraft Corporation South 3608 Davison Blvd Spokane, Washington 99204-5799 I - Model 360 (Normal Category) Approved May 1, 1967 Engine 2 Lycoming IO-360-E1A Fuel 100/130 minimum grade aviation gasoline Engine limits 2700 r.p.m. (180 hp) for all operations Propeller and 1. Two Hartzell full-feathering propeller installations: propeller limits (a) Propellers - Hartzell HC-92WK-2B/W8447-12R Pitch setting at 30 in. station: Low 14°, High 84° Diameter: not over 72 in., not under 71 in. (b) Spinners - Hartzell 835-30 (c) Propeller Governor - Woodward #210485 (d) Unfeathering Accumulator installation - Woodward #986250 Airspeed limits Vne - Never exceed 280 mph (243 knots) EAS Vno - Maximum structural cruising 250 mph (217 knots) EAS Vp - Maneuvering 162 mph (141 knots) EAS Vfe - Flaps extended 150 mph (130 knots) EAS Vle = Vlo = Max. Landing Gear Operation 180 mph (156 knots) EAS C.G. range +162.1 to +167.9 (19% MAC to 28% MAC) Empty weight C.G. range None Datum F.S. 0.00 @ 150.00 in. forward of wing L.E. Leveling means Across cabin floor seat tracks. (Use bubble scale) Maximum weight 4100 lbs. No. of seats 5 (2 @ +98, 1 @ +132, 2 @ +165) Maximum baggage Rear compartment 240 lbs. @ +245 Fuel capacity 111 gal. total (one center fuselage tank +214) (109 gal. usable) See Note 1 for data on system fuel A11WE 2 I - Model 360 (cont'd) Oil capacity 8 qt. each engine (+141), usable 6 qt. ea. engine; total capacity 16 qt. See Note 1 for data on system oil Control surface movements Wing Flaps Down 42° + 1° Main surfaces Aileron Up 25° + 1° Down 15° + 1° Elevator Up 30° + 1° Down 10° + 1° Rudder Right 30° + 1° Left 30° + 1° Tabs (main surface in neutral) Elevator Up 5° + 1° Down 25° + 1° Rudder Right 15° + 1° Left 15° + 1° Serial Nos. eligible 36-0002 and subsequent II - Model 400 (Normal Category) Approved October 4, 1967 Engines 2 Lycoming IO-360-D1A Fuel 100/130 minimum grade aviation gasoline Engine limits 2700 r.p.m. (200 hp) for all operations Propeller and 1. Two Hartzell full-feathering propeller installations: propeller limits (a) Propellers - Hartzell HC-C3YR-2/C7663-6 Pitch setting at 30 in. station: Low 10.5°, High 79° Diameter: not over 72 in., not under 71 in. (b) Spinners - Hartzell C-3258 (c) Propeller Governor - Woodward #210485 (d) Unfeathering Accumulator installation - Woodward #986250 Airspeed limits Vne - Never exceed 280 mph (243 knots) EAS Vno - Maximum structural cruising 250 mph (217 knots) EAS Vp - Maneuvering 169 mph (147 knots) EAS Vfe - Flaps extended 150 mph (130 knots) EAS Vle = Vlo = Max. Landing Gear Operation 180 mph (156 knots) EAS C.G. range At 4500 lbs. 16% MAC to 28% MAC (+160.2 to +167.9) At 4100 lbs. 13% MAC to 28% MAC (+158.3 to +167.9) Empty weight C.G. range None Datum F.S. 0.00 @ 150.00 in. forward of wing L.E. Leveling means Across cabin floor seat tracks. (Use bubble scale) Maximum weight 4500 lbs. No. of seats 5 (2 @ +98, 1 @ +132, 2 @ +165) Maximum baggage Rear compartment 240 lbs. @ +245 Fuel capacity 111 gal. total (one center fuselage tank +214) (109 gal. usable) See Note 1 for data on system fuel 3 A11WE II - Model 400 (cont'd) Oil capacity 8 qt. each engine (+141), usable 6 qt. ea. engine; total capacity 16 qt. See Note 1 for data on system oil Control surface movements Wing Flaps Down 42° + 1° Main surfaces Aileron Up 25° + 1° Down 15° + 1° Elevator Up 30° + 1° Down 10° + 1° Rudder Right 30° + 1° Left 30° + 1° Tabs (main surface in neutral) Elevator Up 5° + 1° Down 30° + 1° Rudder Right 15° + 1° Left 15° + 1° Serial Nos. eligible 40-0001 and subsequent DATA PERTINENT TO ALL MODELS Certification basis FAR 23 effective February 1, 1965 and Amendments 23-1, 23-2 and 23-3. No exceptions Type Certificate No. A11WE issued May 1, 1967 Application for Type Certificate dated December 6, 1965. Production basis None. Prior to original certification of each aircraft an FAA representative must perform a detailed inspection for workmanship, materials, and conformity with the approved technical data, and a check of the flight characteristics. Export eligibility Aircraft will be eligible for issuance of an Export Certificate of Airworthiness subject to compliance with Federal Aviation Regulation Part 21, Subpart L, Sections 21.321 thru 21.339. The applicable procedures are contained in Advisor Circular 21-2. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. Additional required items of equipment are listed in the FAA Approved Equipment List No. 360-1 for Model 360 and Equipment List No. 400-2 for Model 400. NOTE 1. Current weight and balance report including list of equipment included in certificated empty weight, and loading instructions when necessary, must be in each aircraft at the time of original certification. The certificated empty weight and corresponding center of gravity locations must include system oil of 7.5 lb. at (+141) and unusable fuel of 12 lb. at (+214) for Model 360 and Model 400. NOTE 2. The following placards must be displayed: (a) L. H. side adjacent to pilots: (1) "This airplane must be operated as a normal category airplane in compliance with the operating limitations stated in the form of placards, markings and manuals. No acrobatic maneuvers, including spins, approved." (2) "This aircraft is limited to day and night VFR non-icing flight." for Model 360 and "This aircraft approved for day/night VFR/IFR non-icing flight when equipped in accordance with the airplane flight manual" for the Model 400. A11WE 4 (b) On instrument panel above Airspeed Indicator: (1) "Maximum gear down and operating speed 180 mph" (2) "Design maneuvering speed 162 mph" for Model 360 and "Design maneuvering speed 169 mph" for the Model 400. (3) "Demonstrated cross-wind velocity 17 mph" for Model 360 and Model 400. (c) Above upper door handle on inside: "Shut off left engine before entering or leaving cabin." (d) In the center above emergency exit quick release mechanism: (1) "Emergency exit" (2) "Pull to release" (e) On aft baggage floor near lower door jam: (1) "Maximum capacity 240 lbs." (2) "Load in accordance with flight manual" (f) On center line of airplane on contoured (facing aft) edge of glare shield in full view of occupants and on right side of cabin between +111.0 and +118.5 on window molding, lower edge: "No Smoking" (g) On + 176 bulkhead behind electrical equipment cover: "Notice: Electrical system has been substantiated for a maximum load of 50 amps only." .....END.....