TCDS A00076CE

Page No. 1 2 3 4 5 6 7 8 Rev. No. 13 11 11 1 6 11 13 12 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A00076CE Revision 13 Costruzioni Aeronautiche Tecnam S.P.A. P2012 Traveller Septermber 09, 2025 TYPE CERTIFICATE DATA SHEET No. A00076CE This Data Sheet, which is part of Type Certificate No. A00076CE 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 P2012 Traveller (Normal Category), Approved July 11, 2019 Engines 2 Lycoming TEO-540-C1A (TC E00009NY) OR 2 GTSIO-520-S (TC E7CE), see NOTE 16 Fuel AVGAS 100LL (ASTM D910) – see Lycoming SI-1070 AVGAS 100/100LL (ASTM D910) – see Continental Publication OI-34 Engine Limits For Lycoming TEO-540-C1A: aximum Power, 375 hp @ 2575 r.p.m. Maximum Continuous Power, 375 hp @ 2575 r.p.m. For Continental GTSIO-520-S: Maximum Power, 375 hp @ 2233 r.p.m. Maximum Continuous Power, 375 hp @ 2233 r.p.m. Propeller and For Lycoming TEO-540-C1A: Propeller Limits 2 MT Propeller MTV-14-B-C-F/CF195-30 (TC P3BO) Four blades, constant speed, variable pitch with feathering capability, wood construction. Diameter: 76.77 in (1950 mm) Clockwise rotation (pilot’s view) For Continental GTSIO-520-S: 2 MT Propeller MTV-9-E-C-F/CF226-37b (TC P24NE) Three blades, constant speed, variable pitch with feathering capability, wood construction. Diameter: 88.98 in (2260 mm) Clockwise rotation (pilot’s view) Oil For Lycoming TEO-540-C1A: Average MIL-L-22851 or Ambient SAEJ1899 Spec. Temperature Ashless Dispersant Grades All Temperatures SAE15W-50 or SAE20W-50 Above 80°F (27°C) SAE60 A00076CE Page 2 of 8 Above 60°F (16°C) SAE40 or SAE50 30°F to 90°F (-1°C to 32°C) SAE40 0°F to 70°F (-18°C to 21°C) SAE30, SAE40, SAE20W-40 Below 10°F (-12°C) SAE30 or SAE20W-30 For additional info, refer to “TEO-540-C1A Operation and Installation Manual", latest issue, “Operating Instruction” Section and Lycoming Service Instruction No. 1014 (latest issue). For Continental GTSIO-520-S: Average MIL-C-6526 or Ambient SAEJ1899 and SAEJ1966 Spec. Temperature Ashless Dispersant Grades Above 40°F (4.5°C)* SAE50 or multi-viscosity Below 40°F (4.5°C)* SAE30 or multi-viscosity For additional info, refer to Continental Aerospace Technologies “Publication OI-34, GTSIO-520-S Installation and Operation Manual,” (latest issue). * Ambient air, sea level Airspeed Limits For Lycoming TEO-540-C1A: KIAS KCAS VA (Design Manoeuvring Speed) 141 142 VFE (Flap Extended Speed) 124 125 Take off 119 119 Landing VMC (Minimum Control Speed – One Engine Inop) 70 76 Flap T/O 67 73 Flap LAND VO (Operating Manoeuvring Speed) 141 142 VNO (Maximum Structural Cruising Speed) 176 175 VNE (Never Exceed Speed) 223 219 For Continental GTSIO-520-S: KIAS KCAS VA (Design Manoeuvring Speed) 145 143 VFE (Flap Extended Speed) 129 127 Take off 119 120 Landing VMC (Minimum Control Speed – One Engine Inop) 73 77 Flap T/O 64 68 Flap LAND VO (Operating Manoeuvring Speed) 145 143 VNO (Maximum Structural Cruising Speed) 181 177 up to 15000 ft 164 161 at 19500 ft VNE (Never Exceed Speed) 228 222 up to 15000 ft 207 202 at 19500 ft For MTOW of 8113 lbs, see NOTE 6 KIAS KCAS VA (Design Manoeuvring Speed) 143 143 VFE (Flap Extended Speed) 126 127 Take off 120 120 Landing VMC (Minimum Control Speed – One Engine Inop) 71 77 Flap T/O 68 74 Flap LAND VO (Operating Manoeuvring Speed) 143 143 VNO (Maximum Structural Cruising Speed) 178 177 VNE (Never Exceed Speed) 226 222 Center of Gravity (C.G.) Range Forward limit: 14.44 in (0.367 m) (18.0 % MAC) aft of datum up to 6613.9 lbs (3000 kg) A00076CE Page 3 of 8 17.36 in (0.441 m) (22.0 % MAC) aft of datum at Maximum Take-off Weight (MTOW) 17.7 in (0.450 m) (22.5 % MAC) aft of datum at Maximum Take-off Weight (MTOW of 8113 lbs), see NOTE 6. Straight line variation between indicated points Aft limit: 23.86 in (0.606 m) (31.0 % MAC) aft of datum MAC = 72.4 in (1.839 m) Empty Weight C.G. Range None Datum: Vertical plane tangent to wing leading edge Leveling Means Seat support tracks (see Aircraft Flight Manual (AFM), Document No. 2012/391, Section 6 for the procedure). Maximum Weights Take-off 7937 lbs (3600 kg) 8113 lbs (3680 kg), see NOTE 6. Landing 7937 lbs (3600 kg) 8003 lbs (3630 kg), see NOTE 6. Zero Fuel 7673 lbs (3480 kg), for Lycoming TEO-540-C1A 7848 lbs (3560 kg), for Continental GTSIO-520-S Minimum Crew 1 pilot Number of Seats Maximum 11 occupants (9 passengers and 2 crew) Maximum Compartments Weights Nose 227 lbs (103 kg) at 10.88 ft (3.316 m) forward of datum Rear 527 lbs (239 kg) at 11.54 ft (3.518 m) aft of datum Fuel Capacity Total (2 tanks): 198 US gal (750 l) at 33.7 in aft of datum Useable (total): 192 US gal (728 l) Oil Capacity For Lycoming TEO-540-C1A: Maximum (each engine): 12.0 US qts (11.3 l) Minimum (each engine): 4.0 US qts (3.8 l) For Continental GTSIO-520-S: Maximum (each engine): 13.0 US qts (12.3 l) Minimum (each engine): 7.0 US qts (6.5 l) Maximum Operating Altitude 13000 ft 19500 ft if suitable supplementary oxygen dispensing unit is provided, see NOTE 13. Control Surface Movements (*) Ailerons 20° ± 2° TEU (**); 15 ° ± 2° TED (***) Aileron tab 30° ± 2° TEU; 28° ± 2° TED Elevator 23° ± 2° TEU; 13° ± 2° TED Elevator trim tab -8° ± 2° TEU;-21° ± 2° TED -6° ± 4° TEU,-23° ± 4° TED, see NOTE 6. Rudder 22° ± 2° Left / 22° ± 2° Right Rudder trim tab 6° ± 2° Left / 6° ± 2° Right Flaps 0° (Retracted) 15° ± 2° (Take-off) 30° ± 2° (Landing) (*) Nominal Values (**) Trailing Edge Up (***) Trailing Edge Down A00076CE Page 4 of 8 Manufacturer’s Serial Numbers S/N 002/U.S. and subsequent Import Requirements A U.S. standard 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. A00076CE 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. 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 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. Each P2012 Traveller aircraft should have the following modification installed: • MOD2012/016, “Aircraft configuration registered in USA”, It must be identified with a “Steel identification plate” showing USA S/N (xxx/U.S.) and TCDS references. Tecnam can incorporate these modifications using Tecnam Service Bulletin No. SB 316-CS. Certification Basis Type Certification based on the provisions of 14 CFR § 21.29, including the following requirements: 1. 14 CFR Part 23 effective February 1, 1965, including Amendments 23-1 through Amendment 23-62, “Airworthiness Standards for Normal Category Airplanes”. In addition, the following 14 CFR Part 23 regulations at Amendment 23-62 for commuter category: §783(d) – Doors §803(a) – Emergency evacuation §807(d) – Emergency exits §811(b) – Emergency exit marking §813(a) – Emergency exit access §853(d) – Passenger and crew compartment interiors 2. 14 CFR Part 36 effective December 1, 1969, including Amendments 36-1 through Amendment 36-30. (SEE NOTE 14) 3. Special Conditions per 14 CFR 21.16 as follows: a) 23-292-SC: Electronic Engine Control System Installation b) 23-293-SC: Installation of Rechargeable Lithium Batteries 4. Equivalent Level of Safety (ELOS) findings per 14 CFR 21.21(b)(1) as follows: a) TC00988CE-A-G-9-PSPM: 14 CFR §§ 23.45, 23.51, 23.63, 23.67, 23.73, 23.77, 23.161, 23.181, 23.221, 23.251, 23.253, 23.571, 23.785, 23.831, 23.1195, 23.1197, 23.1199, 23.1201, 23.1445, 23.1527, 23.1545, and 23.1583, Amendment 62 Errors. 5. Approved Kinds of Operation: A00076CE Page 5 of 8 Day and Night, Visual Flight Rules (VFR) and Instrument Flight Rules (IFR) . Flight into forecast and known icing conditions is approved in accordance with 14 CFR § 23.1419 when properly equipped, see NOTE 5. 6. Not approved for ditching; compliance with the provisions for ditching equipment in accordance with 14 CFR § 23.1415(a)(b) has not been demonstrated. Type Certificate No. A00076CE issued July 11, 2019. Application for FAA type certificate dated February 28, 2018. The European Aviation Safety Agency (EASA) originally type certified this aircraft under its Type Certificate No. EASA.A.637. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the following item of equipment is required: • AFM, Document No. 2012/100 Ed. 1, Rev. 1, dated June 28, 2019, or later approved revision, for the Model P2012 Traveller. 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. Available documents for the Model P2012 Traveller: • AFM, Document No. 2012/100 Ed. 1, Rev. 1, dated June 28, 2019, or later approved revision. • Aircraft Maintenance Manual (AMM), Document No. 2012/101 Ed. 1 , Rev. 1, dated August 13, 2019, or later approved revision. • Aircraft Illustrated Parts Catalogue (AIPC), Doc ument No. 2012/103 Issue 00, dated May 30, 2019, or later revision. • Lycoming TEO-540 series Engine Maintenance Manual. • MT Propeller Instruction Manual A00076CE Page 6 of 8 NOTES NOTE 1. 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 the weight of the unusable fuel and unusable oil: Unusable fuel: 35 lbs at 33.7 in aft of datum Unusable oil: 5.1 lbs at 14.1 in forward of datum NOTE 2. Airplane operation must be in accordance with the approved AFM listed above. All placards required by the AFM Section 2 Limitations must be installed as specified. The AFM Limitations are EASA and FAA approved and may not be revised without EASA and FAA approval. NOTE 3. Airplane inspections, maintenance, repair, and painting must be accomplished according to the approved AMM listed above or other procedures acceptable to the FAA. The AMM Chapter 4 Airworthiness Limitations Section specifies mandatory replacement times. These Airworthiness Limitations are EASA and FAA approved and may not be revised without EASA and FAA approval. NOTE 4. Information essential for the proper operation, maintenance and inspection of the airplane is contained in the Model P2012 Traveller AFM and AMM. NOTE 5. Stall Warning Device for FIKI Operations Tecnam Modification No. MOD2012/030 (Stall Warning Device for FIKI Operations). Airplanes with this modification must have AFM Document No. 2012/100, Ed. 1, Rev. 3, which includes revised Supplement No. S02, Ed. 1, Rev. 3, or later FAA/EASA approved revisions and Tecnam P2012 AMM Supplement No. S16, Ed. 1, Rev. 0, or later FAA/EASA approved revisions. Aircraft in service can incorporate this modification using Tecnam Service Bulletin SB-332-CS. In addition, modified pitot probes must be installed in accordance with Tecnam Modification No. MOD2012/049 or Tecnam Service Bulletin SB-335-CS. When this change is combined with Tecnam Modification No. MOD2012/023 (GTSIO-520-S Engine), the aircraft must have Tecnam P2012 AFM Document No. 2012/391, Ed. 1, Rev. 1, and related Supplement S02 or later FAA/EASA approved revisions. NOTE 6. Maximum Take-off Weight Increase Up To 8113 lbs (3680 kg) Tecnam Modification No. MOD2012/017 (MTOW increment up to 3680kg). Airplanes with this modification must have AFM Document No. 2012/100, Ed. 1, Rev. 4, or later FAA/EASA approved revisions and Tecnam P2012 Aircraft Maintenance Manual (AMM), Document No. 2012/101 Ed. 2, Rev. 1, dated July 1, 2020, or later FAA/EASA approved revision. Aircraft in service can incorporate this modification using Tecnam Service Bulletin SB-376-CS. When this change is combined with Tecnam Modification No. MOD2012/023 (GTSIO-520-S Engine), the aircraft must have Tecnam P2012 AFM Document No. 2012/391, Ed. 1, Rev. 1, or later FAA/EASA approved revisions. NOTE 7. Engine Limitations Update and Time Limited Dispatch (TLD) Management Tecnam Modification No. MOD2012/081 (Engine limitations update and TLD management). Airplanes with this modification must have AFM Document No. 2012/100, Ed. 1, Rev. 5 , which includes revised Supplement No. S11, Ed. 1, Rev. 2, or later FAA/EASA approved revisions. Aircraft in service can incorporate this modification using Tecnam Service Bulletin SB -385-CS. NOTE 8. FDR and CVR Installation Tecnam Modification No. MOD2012/174 (FDR and CVR installation). Airplanes with this modification must have AFM Supplement No. S21, Ed. 1, Rev. 1, or later FAA/EASA approved revision and Tecnam P2012 AMM Supplement No. S27, Ed. 5, Rev. 0, or later FAA/EASA approved revision. Aircraft in service can incorporate this modification using Tecnam Service Bulletin No. SB - 521-CS. When this change is combined with Tecnam Modification No. MOD2012/023 (GTSIO -520-S Engine), the aircraft must have Tecnam P2012 AFM Document No. 2012/391, Ed. 1, Rev. 1, and related Supplement S21 or later FAA/EASA approved revisions. NOTE 9. Medical Evacuation Configuration (MedEvac) Tecnam Modification No. MOD2012/027 (MedEvac). Airplanes with this modification must have AFM Supplement No. S14, Ed. 1, Rev. 2, or later FAA/EASA approved revision, and Tecnam P2012 A00076CE Page 7 of 8 AMM Supplement No. S21, Ed. 5, Rev. 1, or later FAA/EASA approved revision. Aircraft in service can incorporate this modification using Tecnam Service Bulletin No. SB 441- CS. When this change is combined with Tecnam Modification No. MOD2012/023 (GTSIO-520-S Engine), the aircraft must have Tecnam P2012 AFM Document No. 2012/391, Ed. 1, Rev. 1, and related Supplement S14 or later FAA/EASA approved revisions. NOTE 10. Special Mission Platform Configuration Tecnam Modification No. MOD2012/098 (Special Mission Platform Configuration). Airplanes can be modified by Tecnam at the factory under their major level 1 type design change approval. Airplanes with this modification must have AFM Supplement No. S15, Ed. 1, Rev. 4, or later FAA/EASA approved revision and Tecnam P2012 AMM Supplement No. S23, Ed. 5, Rev. 0, or later FAA/EASA approved revision. Aircraft in service can incorporate this modification using Tecnam Service Bulletin SB 932-CS. NOTE 11. Synthetic Vision System (SVS) Enablement Tecnam Modification No. MOD2012/191 (SVS Enablement). Airplanes with this modification must have AFM Supplement No. S23, Ed. 1, Rev. 0, or later FAA/EASA approved revision, and Tecnam P2012 AMM Temporary Revision No. TR-AMM-212-015, Rev. 0, or later FAA/EASA approved revision. Aircraft in service can incorporate this modification using Tecnam Service Bulletin No. SB 502-CS. When this change is combined with Tecnam Modification No. MOD2012/023 (GTSIO -520-S Engine), the aircraft must have Tecnam P2012 AFM Document No. 2012/391, Ed. 1, Rev. 1, and related Supplement S23 or later FAA/EASA approved revisions. NOTE 12. Wing and Landing Gear Fatigue Life Extension Tecnam Modification No. MOD2012/036 (Extension of wing and landing gear fatigue life). Airplanes with this modification must have Tecnam P2012 AMM Temporary Revision No. TR -AMM-212-025, Rev. 0, or later FAA/EASA approved revision. Aircraft in service can incorporate this modification using Tecnam Service Bulletin SB 551 CS. NOTE 13. Maximum Operating Altitude increase Tecnam Modification No. MOD2012/020 (Max operating altitude at 19500ft). For Flight operation above 13000ft the maximum seating capacity is reduced to four (4) occupants and oxygen operational requirements must be met by operators. Refer to details reported in Tecnam P2012 AFM Supplement No. S20, Ed. 1, Rev. 0 or later FAA/EASA approved revision and Tecnam P2012 AMM Supplement No. S15, Ed. 5, Rev 0, or later FAA/EASA approved revision. Aircraft in service can incorporate this modification using Tecnam Service Bulletin SB 501-CS. When this change is combined with Tecnam Modification No. MOD2012/023 (GTSIO-520-S Engine), the aircraft must have Tecnam P2012 AFM Document No. 2012/391, Ed. 1, Rev. 1, and related Supplement S20 or later FAA/EASA approved revisions. NOTE 14. Noise Reduction System Tecnam Modification No. MOD2012/119 (Noise Reduction system). Airplanes with this modification must have AFM Document No. 2012/100, Ed. 1, Rev. 6, or later FAA/EASA approved revisions. Additionally, CFR Part 36 effective December 1, 1969, including Amendments 36- 1 through Amendment 36-31 is applicable for this modification. Aircraft in service can incorporate this modification using Tecnam Service Bulletin SB 416-CS. This Tecnam modification (MOD2012/119) cannot be installed on aircrafts incorporated with Tecnam Modification No. MOD2012/023 (Alternative Continental Engine). NOTE 15. Alternative passenger-cargo door Tecnam Modification No. MOD2012/162 (Alternative passenger-cargo door). Airplanes with this modification must have Tecnam P2012 AFM Document No. 2012/100, Ed. 1, Rev. 13, or later FAA/EASA approved revisions and Tecnam P2012 AMM Supplement No. S24, Ed. 5, Rev. 1, or later FAA/EASA approved revision. Aircraft in service can incorporate this modification using Tecnam Service Bulletin SB 785-CS. When this change is combined with Tecnam Modification No. MOD2012/023 (GTSIO-520-S Engine), the aircraft must have Tecnam P2012 AFM Document No. 2012/391, Ed. 1, Rev. 1, or later FAA/EASA approved revisions. A00076CE Page 8 of 8 NOTE 16. Alternative Engine Tecnam Modification No. MOD2012/023 (GTSIO-520-S Engine). Airplanes with this modification must have Tecnam P2012 AFM Document No. 2012/391, Ed. 1, Rev. 1, or later FAA/EASA approved revisions and Tecnam P2012 AMM Supplement No. S25, Ed. 5, Rev. 1, or later FAA/EASA approved revision. This Tecnam modification (MOD2012/023) must have the following Tecnam Modification No. MOD2012/017 (MTOW increment up to 3680kg) installed as a prerequisite. NOTE 17. Cold Weather Operations for Outside Air Temperature (OAT) down to -40°C Tecnam Modification No. MOD2012/248 (Cold Weather Operations for OAT down to -40°C). Airplanes with this modification must have Tecnam P2012 AFM Document No. 2012/ 100, Ed. 1, Rev. 14, or later FAA/EASA approved revisions and Tecnam P2012 AMM Supplement No. S 31, Ed. 1, Rev. 0, or later FAA/EASA approved revision. - END -