TCDS A66EU

Page No. 1 2 3 Rev. No. 5 4 5 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A66EU Revision 5 CEAPR R 3000/160 January 15, 2020 TYPE CERTIFICATE DATA SHEET NO. A66EU This data sheet which is part of Type Certificate No. A66EU prescribes conditions and limitations under which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: CEAPR 1 Route de Troyes 21121 Darois France Type Certificate Holder Record: AVIONS PIERRE ROBIN was previous holder of A66EU. Effective July 18, 2002, APEX became TC holder. APEX Aircraft transferred TC A66EU to CEAPR on May 10, 2013. Previous holders of TC A66EU include Société Avions Robin and ROBIN Aviation. (See Note 2.) I. Model R3000/160 Normal and Utility, approved November 17, 1988 Engine Lycoming O-360 A3A Fuel 100 LL minimum aviation grade gasoline Engine Limits For all operations 2600 rpm (160 hp) Propeller Sensenich 76 EM8 S5-0-64 Propeller Limits Static rpm at maximum permissible throttle setting - 2200 ± 50 Diameter 76 inches. No cutoff permitted. Spinner ROBIN 58.26.10.1.80 Airspeed Limits Never exceed 314 km/h (170 kts) Maximum structural cruising 249 km/h (134 kts) Maneuvering 213 km/h (115 kts) Flaps extended (35°) 174 km/h ( 94 kts) Cat. "U" Cat. "N" Flight Maneuvering Load Flaps Up + 4.4 + 3.8 Factors (G's) - 2.2 - 1.9 Down + 2.0 + 2.0 0 0 C.G. Range Forward limit 11.42 in. @ 1878 lbs. Intermediate limit 15.86 in @ 2205 lbs. in cat. "U" and 2536 lbs. in cat. "N". Aft limit 22.83 in. @ 2205 lbs. in cat. "U" and 2536 lbs. in cat. "N". Straight line variation between points given: 11.42 in. @ 1878 lbs. to 15.86 in. @ 2205 lbs. in cat. "U" and 2536 lbs. A66EU Page 2 of 3 in cat. "N". 15.86 in. @ 2205 lbs. to 22.83 in. @ 2205 lbs. in cat. "U". 15.86 in. @ 2536 lbs. to 22.83 in. @ 2536 lbs. in cat. "N". Datum Leading edge rectangular section. Leveling Means Upper fuselage longeron Empty Weight C.G. Range None Maximum Weight Cat. "U" Cat. "N" Takeoff 2205 lbs. 2536 lbs. Landing 2205 lbs. 2536 lbs. No. of Seats 2 front at (19.68 - 23.62), 2 rear at (52.36) Maximum Baggage 88 lbs. at (+75). None for utility category. Fuel Capacity 66.19 US gal at (+9.84) (total) 59.66 US gal at (+9.84) (usable) Oil Capacity Minimum Capacity 8 qts. Minimum 2 qts. Control Surface Movements Wing flaps 30° ± 2.0 Ailerons Up 12° ± 2.0 Down 15° ± 2.0 Rudder (L&R) 25° ± 3.0 Elevator Up 25° ± 2.0 Down 10° ± 2.0 Elevator trim tab (with elevator n neutral position) Flaps retracted Trim wheel to neutral 0° ± 3° Trim wheel full down - 12° ± 3° Trim wheel full up + 37° ± 3° Flaps extended (30°) Trim wheel to neutral + 16° ± 3° Trim wheel full down - 9° ± 3° Trim wheel full up + 40° ± 3° Serial Nos. Eligible A French "Certificat de Navigabilité pour Exportation" endorsed as noted under "Import Requirements," must be submitted for each individual aircraft for which application for U.S. certification is made. Certification Basis Part 23 of the Federal Aviation Regulations, Amendments 1 through 23, FAR 21.29; FAR 36 Amendment 36-1 through (..........) Special Certification Review: "The Canopy (forward sliding) must be jettisonable." Date of applicable for type certification: October 26, 1990. The Direction Generale de l’Aviation Civile (DGAC) originally type certificated This aircraft under its type Certificate Number TC 172. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product under their type certificate Number TC 172 on behalf of France. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for Page 3 of 3 A66EU certification. In addition, the following is required: FAA-approved Airplane Flight Manual, Model R3000/160, Edition 2, April 1990. Import Requirements For aircraft produced in France, The FAA can issue a U.S. airworthiness certificate based on an NAA Export Certificate of Airworthiness (Export C of A) signed by a representative of the Direction Generale de l’Aviation Civile (DGAC) on behalf of the European Community. The Export C of A should contain the following statement “The aircraft covered by this certificate has been examined, tested, and found to comply with Code of Federal Regulations approved under U.S. type certificate No. A 66EU and to be in a condition for safe operation”. For issuance of an airworthiness certificate in accordance with §21.183(c), the Direction Generale de l'Aviation Civile of France must certify that the aircraft conforms to the type design and is in condition for safe operation. In that regard, the Direction Generale de l'Aviation Civile of France will certify that the aircraft complies with the latest issue of Avions Pierre Robin Service Bulletins 111, 112, 114, 116, 121, 127, 132, 133, 136, 141, 146, 147, 151, 152, 153 and 176 and all other applicable mandatory continuing airworthiness information that it has issued, in addition to all other requirements of this type certificate data sheet. For issuance of an airworthiness certificate in accordance with §21.183(d), the certificating inspector, or other authorized person, must find, among other things, that the product is in a condition for safe operation. Service Information Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or – for approvals made before September 28, 2003- by the Direction Generale de l’Aviation Civile (DGAC) · Service bulletins · Structural Repair Manuals · Vendor Manuals · Aircraft Flight Manuals, and · Overhaul and Maintenance Manuals The FAA accepts such documents and considers them FAA-approved unless one of the following condition exists: · The documents change the limitations, performance, or procedures of the FAA approved manuals; or · The documents make an acoustical or emissions changes to this product’s U.S.type certificate as defined in 14 CFR § 21.93. The FAA uses the post type validation procedures to approve these documents. The FAA may delegate on case-by-case to EASA to approve on behalf of the FAA for the U.S. type certificate. If this is the case it will be noted on the document. NOTE 1. Current weight and balance report, including list of equipment in certificated empty weight, and loading instructions if applicable, must be in each aircraft at the time of original certification. Empty weight must include unusable fuel of 3.2 lbs. at (9.84). Basic empty weight includes engine oil of 16.5 lbs. NOTE 2. Some of these transfers were not notified to the FAA and so in some instances the actual type certificates were not reissued. .....END.....