# TCDS A00067IB: Costruzioni Aeronautiche Tecnam S.p.A - Type: Type certificate data sheet - Status: Current - Holder: Costruzioni Aeronautiche Tecnam S.p.A - Revision: 1 - Revised: May 24, 2024 - Product: Aircraft, Small Airplane - Certification basis: Part 23 - Registered aircraft: 73, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/ec/c4/ecc46a8bb6e2b607dd6a0aa2670125cfc8c31cb4e0d581eb474633900c3d993c - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID186849713220240528213922.0001 - Page: https://openairdocs.org/tcds/A00067IB ## Models (1) As the data sheet lists them. - P-Mentor ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 Rev. No. 1 1 - - DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A00067IB Revision 1 Costruzioni Aeronautiche TECNAM S.p.A. P-Mentor May 24, 2024 TYPE CERTIFICATE DATA SHEET No. A00067IB This Data Sheet, which is part of Type Certificate No. A00067IB, 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 Costruzioni Aeronautiche Tecnam S.p.A. Via S. D’acquisto 62 80042 Boscotrecase (NA) Italy I - Model P-Mentor (Normal Category), Approved May 07, 2024 Engine One Rotax 912 iSc3 Sport Engine (TC E00051EN) Fuel AVGAS 100LL (ASTM D910) MOGAS ASTM D4814 (Min RON 95) Engine Limits For Rotax 912 iSc3 Sport Engine: Maximum Power, 98.6 hp @ 5,800 rpm (5 min) Maximum Continuous Power, 96.6 hp @ 5,500 rpm Propeller and Propeller Limits MT Propeller MT MTV-21-A/180-51 (TC P16BO) Two blades, constant speed, variable pitch, wood composite Diameter: 70.9 in (1800 mm) Clockwise rotation (pilot’s view) Oil Use only oil with RON 424 or RON 451 classification For additional info, refer to “Operator manual for Rotax Engine Type 912 i Series,” latest issue Airspeed Limits KIAS KCAS VO (Operating Manoeuvring Speed) 102 103 VA (Design Manoeuvring Speed) 102 103 VFE (Maximum Flap Extended Speed) 106 105 Flap T/O 96 95 Flap LAND VNO (Maximum Structural Cruising Speed) 107 108 VNE (Never Exceed Speed) 135 136 Center of Gravity (C.G.) Range Mean Aerodynamic Chord (MAC) = 53.4 in (1.357 m) Forward limit: 69 in (1.753 m) (23% MAC) aft of datum up to 1,213 lb (550 kg) 70.1 in (1.780 m) (25% MAC) aft of datum for MTOW Aft Limit: 74.4 in (1.889 m) (33% MAC) aft of datum for all weights A00067IB Page 2 of 4 Empty Weight C.G. Range None Datum Propeller support flange without spacer (the aircraft must be levelled in the longitudinal plane) Levelling Means Refer to the seat track supporting beams (See Aircraft Flight Manual (AFM), Document No. 2002/1032, Section 6 for the procedure) Maximum Weight Take-off 1587 lbs (720 kg) Landing 1587 lbs (720 kg) Minimum Crew 1 Pilot Number of Seats 2 Baggage/Cargo Compartments Weight Maximum 66 lbs (30 kg) Fuel Capacity Total (2 tanks): Useable (total): 37 U.S. Gal. (140 L) 35 U.S. Gal. (131.6 L) Oil Capacity Maximum: 3.17 U.S. Qts (3 L) plus the volume in the pipe Minimum: 2.64 U.S. Qts. (2.5 L) plus the volume in the pipe Maximum Operating Altitude 13000 ft (3962 m) Control Surface Movements (*) Ailerons 25°±2° TEU (**); 20°±2° TED (***) Stabilator 12°±2° TEU; 2°±2° TED Stabilator trim tab (****) 0°±2° TEU; 11°±2° TED Rudder 30°±2° RH; 30°±2° LH Flaps 15°±2° TED (Take-off position) 30°±2° TED (Landing position) (*) Nominal Values (**) Trailing Edge Up (***) Trailing Edge Down (****) with Stabilator set 0° Manufacturer’s Serial Numbers S/N 1001/US and subsequent Import Requirements A U.S. airworthiness certificate may be issued on the basis of an NAA Export Certificate of Airworthiness (Export of C of A) signed by a representative of the Ente Nazionale per l'Aviazione Civile (ENAC) 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 U.S. Type Certificate No. A00067IB and to be in a condition for safe operation." Title 14 CFR § 21.183 (c) is the U.S. airworthiness certification basis for an aircraft type certificated under 14 CFR § 21.29 and imported from the country of manufacture. Each P-Mentor aircraft should have the modification: MOD2002/320 (or SB-745- CS) “P-Mentor USA Configuration.” Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate A00067IB Page 3 of 4 of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. Certification Basis Type Certification under 14 CFR Section 21.29 including the following requirements: 1. 14 CFR Part 23 effective February 1, 1965, including amdt 23-1 through 23-64, “Airworthiness Standards: Normal Category Airplanes.” 2. The detailed design standards used as a means of compliance in accordance with § 23.2010 are documented in 2002/1265, Model P- Mentor Detailed Design Standard Summary. 3. 14 CFR Part 36 effective December 1, 1969, including amdt 36-1 through 36-28 4. Equivalent levels of safety (ELOS): None 5. Approved Kinds of Operation: Day and Night, Visual Flight Rules (VFR) and Instrument Flight Rules (IFR) 6. Prohibited Kinds of Operation: Flight into known icing conditions Type Certificate No. A00067IB issued May 07, 2024. Date of Application for FAA Type Certificate was August 12, 2022. The European Aviation Safety Agency (EASA) originally type certified this aircraft under its type certificate number EASA.A.006. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the airplane for certification. In addition, the following item of equipment is required: • AFM, Document No. 2002/1032 Ed. 1, Rev 9, dated March 06, 2024, or later approved revision, for the Model P-Mentor. Service Information Each of the documents listed below must state that it is approved by EASA: • 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 for type design data only unless one of the following conditions 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. A00067IB Page 4 of 4 Available documents for the Model P-Mentor: • AFM, Document No. 2002/1032 Ed. 1, Rev 9, dated March 06, 2024, or later approved revision. • Airplane Maintenance Manual (AMM) doc. 2002/1033 Ed. 1, Rev. 3, dated July 17, 2023, or later FAA approved revision. • The appropriate Rotax 912 iSc3 Sport Engine maintenance manuals. • The appropriate MT Propellers Instruction Manual. NOTES NOTE 1 Current weight and balance report, including list of equipment included in 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: Unusable fuel: 13.3 lbs at 84.2 aft of datum Unusable oil: 4.7 lbs at 31.5 in fwd of datum NOTE 2 Airplane operation must be in accordance with the FAA approved AFM listed above. All placards listed in Section 2 Limitations must installed as specified. The AFM Limitations are EASA and FAA approved and may not be revised without EASA and FAA approval. NOTE 3 Airworthiness Limitations are specified in the Section 2 LIMITATIONS of the AFM and Chapter 4 of the AMM and are approved by EASA and the FAA. These LIMITATIONS specify mandatory replacement times, and operating limitations, and may not be changed without EASA and FAA approval. NOTE 4 Information essential for the proper operation, maintenance and inspection of the airplane is contained in the Tecnam P-Mentor AFM and AMM. --- END --- ``` ## ADs (1, in force first) - [AD 2025-17-13](https://openairdocs.org/ad/2025-17-13): Cabin Equipment/Furnishings · Costruzioni Aeronautiche Tecnam P-Mentor. Effective Sep 26, 2025 ## Registered aircraft by registry model (OpenAirDocs) - [Costruzioni Aeronautiche Tecna P-MENTOR](https://openairdocs.org/model/costruzioni-aeronautiche-tecna-p-mentor): 73 aircraft (registry codes 0330565, 05641YQ) --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.