REPUBLIC OF INDONESIA MINISTRY OF TRANSPORTATION DIRECTORATE GENERAL OF CIVIL AVIATION TYPE CERTIFICATE DATA SHEET NO. A094

Transcription

1 REPUBLIC OF INDONESIA MINISTRY OF TRANSPORTATION DIRECTORATE GENERAL OF CIVIL AVIATION A094 Revision 0 Costruzioni Aeronautiche TECNAM S.r.L P2006T 7 June 2013 TYPE CERTIFICATE DATA SHEET NO. A094 This data sheet is part of TYPE CERTIFICATE Validation No. A094 prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Civil Aviation Safety Regulations for Normal Category Airplane. Type Certificate Holder: Costruzioni Aeronautiche TECNAM S.r.L Via Tasso, Napoli Italy II. Model P2006T (Normal Category), Approved 7 June 2013 Engine Two Bombardier ROTAX 912 S3 (DGCA TC E047 revision-) Fuel MOGAS Min. RON 95 (ASTM D4814) AVGAS 100LL (ASTM D910) Engine Limits Max rotational speed (5 min) 5800 r.p.m. (98.6 hp) Max continuous rotational speed 5500 r.p.m. (92.5 hp) (Engine shaft r.p.m) Propeller and propeller limits Two MTV-21-A-C-F/CF (DGCA TC P029 revision 0) Two blades, constant speed, variable pitch with feathering capability, wood construction. Diameter : 1780 mm Oil Coolant Oil with API classification "SG" or higher. For additional info, refer to "Rotax Operators Manual" - latest issue - "Operating Media" Section. Water / Cooler Protection (see AFM,2006/044, Section 2) Page Rev. No TCDS No. A094 Page 1 of 5

2 Airspeed Limits V A V FE V MC V LO V LE V NO V NE ( Landing) 117 (Take off) The following values apply when EASA Major Change Approval No Increment of the maximum take off weight (1230 Kg) as per C.A. Tecnam MOD2006/015 is installed (Other Air Speeds remain unchanged): V A V FE V NO V NE ( Landing) (Take off) The following values apply when EASA Major Change Approval No V LE and V LO increment as per C.A.Tecnam MOD2006/033 is installed (Other Air Speeds remain unchanged): V LO V LE Center of Gravity (C.G.) Range Datum Leveling Means m (8.7 in) (16.5 % MAC) to m (16.34 in) (31.0 % MAC) Wing leading edge (MAC = m (52.72 in)) Seat support trusses (see AFM, 2006/044, Sect.6 for the procedure) Maximum Weights Takeoff : 1180 kg (2600 lb) Landing : 1180 kg (2600 lb) Zero Fuel : 1145 kg (2524 lb) The following values apply when EASA Major Change Approval n Increment of the maximum takeoff weight (1230 Kg) as per C.A. Tecnam MOD2006/015 is installed: Takeoff : 1230 kg (2712 lb) Zero Fuel : 5 kg (2635 lb) Landing : 1230 kg (2712 lb) TCDS No. A094 Page 2 of 5

3 Minimum Crew 1 Number of Seats 4 Maximum Baggage Fuel Capacity Oil Capacity (each engine) Maximum operating altitude 80 kg at m (176 lbs at in) aft the datum Total : 200 liters / 52.8 US Gal Usable : liters / 51.4 US Gal Max : 3 liters (3.2 qts) Min : 2 liters (2.1 qts) 4,267 m (14000) ft Operations Capability Day/Night-VFR, IFR (*) Flight into expected or actual icing conditions is prohibited * Airplane has been certified to operate VFR Day, VFR Night and IFR Night. Basic aircraft equipment configuration allows VFR Day operation. Additional equipment configuration are available at customer choice (see Aircraft Flight Manual Sect.6 for further information). Control Surface Movements(*) Ailerons 20 TEU(**) 17 TED(***) Stabilator 4 TEU 15 TED Stabilator trim tab 2 TEU 19 TED Rudder 26 RH 26 LH Rudder trim tab 20 RH 20 LH Flaps (*) Nominal Values (**) Trailing Edge Up (***) Trailing Edge Down 15 TED (Take-off position) 40 TED (Landing position) Manufacturer s Serial Numbers Service Information MSN 001 and subsequent Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA): Service bulletins, Structural repair manuals, Vendor manuals, Aircraft flight manuals, and Overhaul and maintenance manuals. DGCA accepts such documents and considers them DGCA approved TCDS No. A094 Page 3 of 5

4 Import Requirement To be considered eligible for operation in the Republic of Indonesia, each aircraft manufactured under this type certificate must be accompanied by a certificate of airworthiness for export*, or certifying statement endorsed by the exporting foreign civil airworthiness authority, which states (in the English language): "The aircraft covered by this certificate has been examined, tested, and found to conform to the type design approved under Indonesian Type Certificate No. A094 and to be in condition for safe operation." *See NOTE 1. The Indonesian airworthiness certification basis for aircraft type certificated under CASR Part 21 section 21.29, and exported by country of manufacture is section (c) or (c). The Indonesia airworthiness certification basis for aircraft type certificated under section and exported from countries other than the country of manufacture (e.g., third party country) is section (d). Certification Basis Model P2006T In accordance with Civil Aviation Safety Regulation (CASR) of the Republic of Indonesia, CASR 21.29(a)(ii), the Indonesia Type Certificate is issued in using the EASA certification basis as it is being stated in EASA TCDS No. A.185 Issue 03, 20 December Basic Requirement CS-23 Initial Issue (Effective 14 November 2003) CS-36 Initial Issue (Effective 17 October 2003) Special Condition Special Condition - Interim Policy for HIRF protection CRI F-1 Equivalent Level of Safety CS (b) CS (e) CS CS (b), Main Door (CRI D-02) Ditching Emergency Exits (CRI D-01) Fire protection of flight controls, engine mounts and other flight structure (CRI D-03) Liquid Cooling Coolant tank (CRI E-01) Environmental Standards: - ICAO, Annex 16, Volume I, 4th Edition, July 2005; - EASA CS-36, Decision No. 2003/4/RM, 17 October 2003 TCDS No. A094 Page 4 of 5

5 Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the airplane for certification. Notes: Note 1: Following modification can be modified by Tecnam at the factory under their major level 1 type design change approval ; 1. Tecnam Modification No. MOD2006/001 (S-TEC 55x Autopilot) EASA Major Change Approval No Issued 18 March Tecnam Modification No. MOD (Glass Cockpit Garmin G950) - EASA Major Change Approval No Issued 8 April Tecnam Modification No. MOD2006/015 (Increase Maximum Take-off Weight 2712 lb) - EASA Major Change Approval No Issued 21 December Tecnam Modification No. MOD2006/033 (V LE and V LO Increment - EASA Major Change Approval No Issued 1 October 2012 Aircraft with applicable modifications must has the appropriate Tecnam Aircraft Manual Supplement as required. Note 2: When major change, Tecnam Modification No. MOD2006/002 (EASA approval ), is installed for Optional Equipment Garmin G950, the corresponding major modification to CRI A-01 must be considered together with special condition detailed in CRI B-52 Human factor in Integrated Avionic Systems. --ooo-- TCDS No. A094 Page 5 of 5