TCDS A00064CE

Page No. 1 2 3 4 Rev. No. 0 0 0 0 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A00064CE Revision 0 XtremeAir XA42 November 5, 2012 TYPE CERTIFICATE DATA SHEET NO. A00064CE This data sheet which is part of Type Certificate No. A00064CE prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of Title 14 of the Code of Federal Regulations. Type Certificate Holder XtremeAir GmbH Harzstrasse 2 39444 Cochstedt Germany I. Model XA42, (Acrobatic Category), Approved November 5, 2012 Engine One Lycoming AEIO-580-B1A, TCDS E00004NY Fuel 100/100LL minimum grade aviation gasoline Engine Limits Maximum Take-Off, 2700 rpm (315 hp) Continuous Operation, 2700 rpm (315 hp) Propeller (a) MT Propeller Co. MTV-9-B-C/C203-20d, TCDS P24NE (b) Spinner: Dwg No. P-1010(3R) Propeller Limits Diameter 79.92 in (2030 mm ± 5 mm) Low Pitch 9 º± 0.2º High Pitch 30 º± 1º Pitch Radius at 29.92 in (760 mm) Airspeed Limits V NE 225 KIAS, 259 mph V NO 185 KIAS, 213 mph V O 174 KIAS, 200 mph C.G. Range Takeoff, flight and landing: 137.0 to 145.8 (550 mm (25% MAC) to 700 mm (33% MAC)) aft of datum (at all weights) Empty Wt. C.G. Range None Reference Datum Forward face of firewall Leveling Means Horizontal frame of cockpit canopy cut-out. A00064CE Page 2 of 4 Revision 0 Maximum Weight Maximum Empty Weight 1477 lbs (670 kg) Maximum Take-off Weight 1874 lbs. (850 kg) full acro 2200 lbs. (999 kg) limited acro Maximum Landing Weight 1874 lbs. (850 kg) full acro 2200 lbs. (999 kg) limited acro Minimum Crew 1 pilot (rear seat) No. of Seats 2 (front seat) fixed seat at 33.86 (860 mm) aft of datum. (rear seat) fixed seat at 68.1 (1730 mm) aft of datum. Maximum Baggage 22 pounds (10 kg) total in baggage area behind pilot’s seat at 103.15 inches (2620 mm) aft of the datum. Carriage of baggage prohibited during acrobatic maneuvers. Fuel Capacity 72.6 gallons (275 liters) tota l, (two 27.7 gallon tanks at 13.38 in (340 mm) aft of the datum, one 17.2 gallon tank at 11.22 in. (285 mm) aft of datum). 72.1 gallons (273 liters) usable See Note 1. Oil Capacity 16 qt (15.15 liters). See Note 1. Smoke Oil Capacity 7.4 gallons (28 liters) at 103.15 inches (2620 mm) aft of the datum. (optional system) See Note 1. Maximum Operating Altitude 15,000 feet. Control Surface Movements Aileron ± 30º +0°, -5° Elevator ± 27º +3°, -5° Trim tab (on RH elevator) ± 3° Rudder ± 30º ±0.66° Manufacturer’s Serial Numbers Serial numbers 101, 102, 103, 106 and on. See Note 4. Import Requirements A U.S. airworthiness certificate may be issued on the basis of a German Certificate of Airworthiness for Export signed by a representative of the Luftfahrt Bundesamt on behalf of EASA containing the following statement: “The aircraft covered by this certificate has been examined and found to comply with the type design of Type Certificate A00064CE approved under U.S. Type Certificate Number A00064CE and to be in a condition for safe operation.” A00064CE Page 3 of 4 Revision 0 Certification Basis (1) Part 23 of Title 14 of the Code of Federal Regulations effective February 1, 1965, as amended by Amendments 23-1 through 23-59; (2) Part 36 of Title 14 of the Code of Federal Regulations effective December 1, 1969, as amended by Amendments 36-1 through 36-28 (3) Special Conditions as follows: (a) Special Conditions No. 23-256-SC: Acrobatic Category and Aerodynamic Stability; SC23.171 Flight – General, SC23.173 Static longitudinal stability, SC23.175 Demonstration of static longitudinal stability, SC23.177 Static directional and lateral stability. (4) Equivalent levels of safety as follows: (a) ACE-11-12: 14 CFR §23.207 Stall warning. (b) ACE-11-16: 14 CFR §23.777(d) Cockpit controls and §23.781(b), Powerplant control knobs Type Certificate A00064CE issued November 5, 2012. Application for type certificate dated May 3, 2011. Not approved for ditching; compliance with the provisions for ditching equipment in accordance with 14 CFR § 23.1415(a)(b) has not been demonstrated. Approved for VFR-day only. Flight in known icing prohibited. Equipment The basic required equipmen t as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the airplane for certification. In addition, the following items of equipment are required: EASA approved Airplane Flight Manual dated October 16, 2012, XtremeAir document number AFM-XA42-0040-002-C.01, or later EASA approved revision. A parachute as specified in the Airplane Flight Manual. Service Information Service bulletins, structural repair manuals, vendor manuals, AFMs, and overhaul and maintenance manuals, which contain a statement that the document is approved by EASA, are accepted by the FAA and are considered FAA approved. (These approvals pertain to design data only.) NOTE 1: Weight and Balance: A current weight and balance report, including a list of equipment included in the certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. The certificated empty weight and corresponding center of gravity location must include full oil and unusable fuel. A00064CE Page 4 of 4 Revision 0 NOTE 2: The placards specified in the EASA approved Airplane Flight Manual must be displayed. NOTE 3: Instructions for Continued Airworthiness and Service Life Limited components is included in the Maintenance Manual Document No. AMM-XA42-0040-001-B03. Revisions to Airworthiness Limitations must be EASA approved for the FAA. NOTE 4: Airplanes with serial numbers 101, 102, 103, and 106 through 114 may be imported if modified per XtremeAir SB-2012-006. END