TCDS A00066CE

Page No. 1 2 3 4 5 6 7 8 9 10 Rev. No. 11 4 10 4 6 11 9 10 9 11 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A00066CE Revision 11 Costruzioni Aeronautiche Tecnam S.P.A. P2010 P2010 TDI September 08, 2026 TYPE CERTIFICATE DATA SHEET No. A00066CE This Data Sheet, which is part of Type Certificate No. A00066CE, 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 Type Certificate Holder Record Costruzioni Aeronautiche Tecnam srl transferred TC A00066CE to Costruzioni Aeronautiche Tecnam S.P.A. on March 14, 2018. I - Model P2010 (Normal Category), Approved December 4, 2015 Engine 1) Lycoming Engine IO-360-M1A (TC 1E10) 2) Lycoming Engine IO-390-C3B6 (TC E00006NY) (See Note 9) Fuel For Lycoming Engine IO-360-M1A: AVGAS Grade 91/96 or 100LL (ASTM D910) MOGAS EN 228:2008 (E) (see Note 8) For Lycoming Engine IO-390-C3B6: AVGAS 100LL Engine Limits For Lycoming Engine IO-360-M1A: Max rotational speed 2700 r.p.m. (180 hp) Cruise rotational speed (75%) 2450 r.p.m. (135 hp) (Engine shaft r.p.m.) For Lycoming Engine IO-390-C3B6: Take-Off power 2700 r.p.m. (215 hp) Max continuous power 2700 r.p.m. (215 hp) Propeller and 1) MT Propeller MT 188R145-4G (TC P19BO) Propeller Limits Two blades, constant speed, fixed pitch, wood construction. Diameter: 1880 mm (74 in) - no reduction allowed. Clockwise rotation (pilot’s view) 2) MT Propeller MTV-15-B/193-52 (TC P23BO) (See Note 5) Two blades, constant speed, variable pitch, wood construction. Diameter: 1930 mm (76 in) – No reduction allowed. Clockwise rotation (pilot’s view) A00066CE Page 2 of 10 3) MT Propeller MTV-12B/183-59 (TC P25NE) (See Note 9) Three blades, constant speed, variable pitch, wood construction. Diameter: 1830 mm (72 in) – No reduction allowed. Clockwise rotation (pilot’s view) Oil Average Ambient Temperature MIL-L-6082B or SAEJ1966 Spec. Mineral Grades MIL-L-22851 or SAEJ1899 Spec. Ashless Dispersant Grades All Temperatures SAE15W50 or SAE20W-50 Above 80°F SAE60 SAE60 Above 60°F SAE50 SAE40 or SAE50 30°F to 90°F SAE40 SAE40 0°F to 70°F SAE30 SAE40, SAE30, SAE20W40 Below 10°F SAE20 SAE30 or SAE20W30 For additional info, refer to "Lycoming Operation and Installation Manual" for the list of alternative recommended commercial brands and types KIAS KCAS Airspeed Limits VO (Operating Manoeuvring Speed) 120 119 VA (Design Manoeuvring Speed) 120 119 VFE (Maximum Flap Extended Speed) 91 92 VNO (Maximum Structural Cruising Speed) 132 130 VNE (Never Exceed Speed) 169 164 Center of Gravity (C.G.) Range Forward limit: 10.31 in (19 % MAC) behind datum Aft Limit: 17.32 in (32.0 % MAC) behind datum Mean Aerodynamic Chord is 54.2 in Empty Weight C.G. Range None Datum Vertical plane tangent to wing leading edge Levelling Means Seat track supporting beams (see Airplane Flight Manual (AFM), 2010/100, Section 6 for the procedure). Maximum Weight Take-off 2557 lbs Landing 2557 lbs Minimum Crew 1 pilot Number of Seats 4 Baggage/Cargo Maximum 88 lbs at 61.41 in aft the datum Compartments Weight Fuel Capacity 63.4 U.S. Gal. (+ 24.1 in) Usable 61 U.S. Gal. Oil Capacity (each engine) Maximum: 8 U.S. Qts. Minimum: 4 U.S. Qts. Control Surface Movements (*) Ailerons 19°±2° TEU (**) 14 ° ±2° TED (***) Stabilator 6°±2° TEU 17°±2° TED Stabilator trim tab 3°±1° TEU 15°°±1° TED 3°±1° TEU 6°±1° TED (See Note 10) Rudder 25°±2° RH 25°±2° LH Rudder trim tab 20°±2° RH 20°±2° LH A00066CE Page 3 of 10 Flaps 15°±1° TED (Take-off position) 40°±1° TED (Landing position) (*) Nominal Values (**) Trailing Edge Up (***) Trailing Edge Down Applicable Serial Numbers S/N 1/U.S. to 9999/U.S. Import Requirements a) 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. A00066CE and to be in a condition for safe operation." b) The U.S. airworthiness certification basis for aircraft type certificated under 14 CFR part 21, Section 21.29 and exported. c) Each P2010 aircraft should have the following modification installed: • MOD2010/061 “New cargo net and G1000 software configuration for USA aircraft”, 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 SB 221-CS. d) 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. 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- 61 Additional regulations at 14 CFR Part 23, Amendment 23-64 for Tecnam Modification No. MOD2010/277 (GI-275 back-up instrument): 23.2005, 23.2010, 23.2325, 23.2500, 23.2505, 23.2510, 23.2525(g), 23.2605 The detailed design standards used as a means of compliance for those regulations at amendment 23-64 or later in accordance with § 23.2010 are documented in Tecnam P2010 Detail Design Standard (DDS) Summary, Report No. 2010/998 Ed. 1, Rev 0, dated July 01, 2025. 2) 14 CFR Part 36 effective December 1, 1969 including amdt 36-1 through 36- 28 3) Equivalent levels of safety (ELOS): None 4) Approved Kinds of Operation: Day and Night, Visual Flight Rules (VFR) and Instrument Flight Rules (IFR) A00066CE Page 4 of 10 5) Prohibited Kinds of Operation: Flight into known icing conditions Type Certificate No. A00066CE was issued December 4, 2015. Date of Application for FAA Type Certificate was December 13, 2011. The European Aviation Safety Agency (EASA) originally type certified this aircraft under its type certificate number A.576. Maximum Operating Altitude 12000 ft 14000 ft (See Note 11) Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the airplane for certification. Such equipment is listed in the current FAA approved AFM: 2010/100 Ed. 2, Rev. 0, or later approved revisions. 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. Each airplane is provided with the following approved documents: a) AFM doc. 2010/100 Ed. 2, Rev. 0, or later FAA approved revision. b) Airplane Maintenance Manual (AMM) doc. 2010/101 Ed. 1, Rev. 2, or later FAA approved revision, including Chap. 4: "Airworthiness Limitations" and Chap. 5: "Time Limits/ Maintenance Check". c) The appropriate Lycoming series engine maintenance manuals. d) 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: 14.28 lbs at 24.1 in aft of datum NOTE 2 Airplane operation must be in accordance with the EASA approved AFM listed above. All placards listed in Section 2 must be displayed. A00066CE Page 5 of 10 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 FAA approval . Revisions to the Airworthiness Limitations must be approved by the FAA. The inspections, maintenance, repair and painting must be accomplished according to the Maintenance Manual or other procedures acceptable to the FAA. NOTE 4 Information essential for the proper operation, maintenance and inspection of the airplane is contained in the Tecnam P2010 AFM and AMM. NOTE 5 Optional Variable Pitch Propeller Tecnam Modification No. MOD2010-002 (Variable Pitch Propeller - MTV-15-B/193-52 (TC P23BO)). Airplanes with this modification must have at least Tecnam AFM doc. 2010/100 E d. 2, Rev. 0, Supplement No. D-2 or later FAA/EASA approved revisions and Tecnam P2010 AMM Supplement No. S-1, Ed. 1, Rev. 0, or later FAA/EASA approved revisions. NOTE 6 Optional GFC 700 Autopilot Tecnam Modification No. MOD2010-001 (Garmin GFC 700 Autopilot). Airplanes can be modified by Tecnam at the factory under their major level 1 type design change approval. Airplanes with this modification must have Tecnam AFM Section 9 Supplement No. D01, Ed. 1, Rev. 0 (Aircraft equipped with fixed pitch propeller), or AFM Section 9 Supplement No. D07, Ed. 1, Rev. 0 (Aircraft equipped variable pitch propeller), or later FAA/EASA approved revisions and Tecnam P2010 AMM Supplement No. S-3, Ed. 1, Rev. 0, or later FAA/EASA approved revisions. Aircraft in service can incorporate this modification using Tecnam Service bulletin SB -180-CS (Aircraft equipped with fixed pitch propeller) or Tecnam Service bulletin SB -220-CS(Aircraft equipped with variable pitch propeller). NOTE 7 Alternative Avionics Configuration Tecnam Modification No. MOD2010-003 (Alternative Avionics Configuration – Garmin G500). This modification cannot be installed as retrofit. Airplanes can be modified by Tecnam at the factory under their major level 1 type design change approval. Airplanes with this modification must have Tecnam AFM Section 9 Supplement No. D03, Ed.1, Rev. 0, or later FAA/EASA approved revisions and Tecnam P2010 AMM Supplement No. S-2, Ed.1, Rev. 0, or later FAA/EASA approved revisions. NOTE 8 Optional Automotive Fuel Tecnam Modification No. MOD2010-032 (Automotive Fuel-MOGAS). Airplanes can be modified by Tecnam at the factory under their major level 1 type design change approval. Airplanes with this modification must have Tecnam AFM Section 9 Supplement No. D04, Ed. 1, Rev 0, or later FAA/EASA approved revisions. Aircraft in service can incorporate this modification using Tecnam Service bulletin SB -182-CS. NOTE 9 Optional Engine and Avionic Suite Tecnam Modification No. MOD2010/078 (Lycoming IO-390 Engine and G1000Nxi avionic suite installation). This modification cannot be installed as a retrofit. Airplanes with this modification must have Tecnam AFM Supplement No. D10, Ed. 2, Rev. 1 or later FAA/EASA approved revisions and Tecnam P2010 AMM Supplement No. S6, Ed. 1, Rev. 1, or later FAA/EASA approved revisions. NOTE 10 Optional GFC 700 Autopilot for Airplanes Equipped with IO390 Engine Tecnam Modification No. MOD2010/133 (Garmin GFC 700 Autopilot for IO390-Equipped Airplanes). Airplanes with this modification must have Tecnam AFM Section 9 Supplement No. D16, Ed. 2, Rev. 0, or later FAA/EASA approved revisions and Tecnam P2010 AMM Supplement No. S12, Ed. 1, Rev. 1, or later FAA/EASA approved revisions. Aircraft in service can incorporate this modification using Tecnam Service bulletin SB -308-CS. NOTE 11 Optional Altitude Increase for Airplanes Equipped with IO390 Engine Tecnam Modification No. MOD2010/194 (Maximum operating altitude increase at 14000ft for IO-390 equipped airplanes). Airplanes with this modification must have Tecnam AFM Section 9 Supplement No. D21, Ed. 2, Rev. 2, or later FAA/EASA approved revisions and Tecnam P2010 AMM Supplement No. A00066CE Page 6 of 10 S16, Ed. 1, Rev. 1, or later FAA/EASA approved revisions. Aircraft in service can incorporate this modification using Tecnam Service bulletin SB -410-CS. NOTE 12 GI-275 Back-up Instrument Tecnam Modification No. MOD2010/277 (GI-275 back-up instrument). Airplanes with this modification must have the Tecnam P2010 AFM Doc. 2010/100, Ed. 2, Rev. 17, or later FAA/EASA approved revisions and AMM Supplement 2010/101-S18 Ed. 2, Rev 0 or later FAA/EASA approved revisions. NOTE 13 Fuselage and Wing Fatigue Life Extension Tecnam Modification No. MOD 2010/282 (Fuselage and Wing Fatigue Life Extension). Airplanes with this modification must have Tecnam P2010 AMM Temporary Revision No. TR-AMM-210-013, Rev. 0, or later FAA/EASA approved revisions or Tecnam P2010 AMM Doc.2010/101 that incorporates this Temporary Revision. Aircraft in service can incorporate this modification using Tecnam Service bulletin SB -918-CS. II - Model P2010 TDI (Normal Category), Approved October 27, 2021 Engine Continental Engine TAE 125-02-125 (TC E00069EN) Fuel JET A-1 (ASTM-D-1655) Diesel (EN 590) Engine Limits Take-Off power 2300 r.p.m. (168 hp) Max continuous power 2250 r.p.m. (153 hp) Other engine limitations listed in P2010 TDI Airplane Flight Manual (AFM), 2010/552, Section 2 Propeller and MT Propeller MTV-6-R/190-69 (TC P19NE) Propeller Limits Three blades, constant speed, variable pitch, wood construction. Diameter: 1900 mm (75 in) - no reduction allowed. Clockwise rotation (pilot’s view) Oil Engine: Aero Shell Oil Diesel Ultra; Shell Helix Ultra 5W30 Gearbox: Centurion Gearbox Oil N1 For additional info, refer to P2010 TDI AFM, 2010/552, Section 2 Coolant BASF Glysantin Protect Plus / G48; Water / Radiator protection in a ratio of 50:50 For additional info, refer to P2010 TDI AFM, 2010/552, Section 2 KIAS KCAS Airspeed Limits VO (Operating Manoeuvring Speed) 119 119 121(*) 121(*) 122(**) 122(**) VA (Design Manoeuvring Speed) 119 119 121(*) 121(*) 122(**) 122(**) VFE (Maximum Flap Extended Speed) 90 92 LND 92(*) 93(*) LND 93(**) 94(**) LND 100 101 TO 102(*) 103(*) TO 104(**) 104(**) TO A00066CE Page 7 of 10 VNO (Maximum Structural Cruising Speed) 130 130 VNE (Never Exceed Speed) 163 164 (*) See NOTE 5 (**) See NOTE 7 Center of Gravity (C.G.) Range Forward limit: 10.83 in (19 % MAC) behind datum up to 2205 lbs 12.99 in (23% MAC) behind datum up to MTOW or - 13.54 in (24% MAC) behind datum up to MTOW (See NOTE 5) - 13.82 in (24.5% MAC) behind datum up to MTOW (See NOTE 7) Aft Limit: 17.87 in (32.0 % MAC) behind datum Mean Aerodynamic Chord is 54.2 in Empty Weight C.G. Range None Datum Vertical plane tangent to wing leading edge Levelling Means Seat track supporting beams (see AFM, 2010/552, Section 6 for the procedure) Maximum Weight Take-off 2557 lbs 2645 lbs (See NOTE 5) 2690 lbs (See NOTE 7) Landing 2557 lbs 2645 lbs (See NOTE 5) 2690 lbs (See NOTE 7) Minimum Crew 1 pilot Number of Seats 4 Baggage/Cargo Maximum 88 lbs at 61.41 in from datum Compartments Weight Fuel Capacity 63.4 U.S. Gal. (+ 24.1 in) Usable 61 U.S. Gal. Oil Capacity (each engine) Maximum: 6.34 U.S. Qts. Minimum: 4.75 U.S. Qts. Control Surface Movements (*) Ailerons 19°±2° TEU (**) 14 ° ±2° TED (***) Stabilator 17°±2° TEU 6°±2° TED Stabilator trim tab 2°±2° TEU 8°±2° TED Rudder 25°±2° RH 25°±2° LH Rudder trim tab 20°±2° RH 20°±2° LH Flaps 0° (Fully Retracted) 40°±1° (Fully Extended) (*) Nominal Values (**) Trailing Edge Up (***) Trailing Edge Down Applicable Serial Numbers S/N 100/U.S. to 9999/U.S. when MOD2010/162 is installed Import Requirements a) 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 A00066CE Page 8 of 10 comply with U.S. Type Certificate No. A00066CE and to be in a condition for safe operation." b) The U.S. airworthiness certification basis for aircraft type certificated under 14 CFR part 21, Section 21.29 and exported. c) Each P2010 TDI aircraft should have the following modification installed: • MOD2010/061 “New cargo net and G1000 software configuration for USA aircraft”, 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 SB 221-CS. d) 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. Certification Basis Type Certification under 14 CFR Section 21.29 including the following requirements: 1) 14 CFR Part 23 effective February 1, 1965, including Amendments 23-1 through Amendment 23-61. a) Additional regulations at 14 CFR Part 23 regulations at Amendment 23- 64 for the installation of a diesel engine with a Full Authority Digital Engine Control (FADEC) system: §23.2010 – Accepted means of compliance, §23.2225 – Component loading conditions, §23.2400 – Powerplant installation, §23.2410 – Powerplant installation hazard assessment, §23.2425 – Powerplant operational characteristics, §23.2430 – Fuel system, §23.2510 – Equipment, systems, and installations, §23.2515 – Electrical and electronic system lightning protection, §23.2520 – High-intensity Radiated Fields (HIRF) protection, §23.2610 – Instrument markings, control markings, and placards, §23.2615 – Flight, navigation, and powerplant instruments b) Additional regulations at 14 CFR Part 23, Amendment 23-64 for Tecnam Modification No. MOD2010/277 (GI-275 back-up instrument): 23.2005, 23.2010, 23.2325, 23.2500, 23.2505, 23.2510, 23.2525(g), 23.2605 The detailed design standards used as a means of compliance for those regulations at amendment 23-64 or later in accordance with § 23.2010 are documented in Tecnam P2010 Detail Design Standard (DDS) Summary, Report No. 2010/998 Ed. 1, Rev 0, dated July 01, 2025. 2) 14 CFR Part 36 effective December 1, 1969, including Amendments 36-1 through Amendment 36-31 3) Approved Kinds of Operation: Day and Night, Visual Flight Rules (VFR) and Instrument Flight Rules (IFR) A00066CE Page 9 of 10 4) Prohibited Kinds of Operation: Flight into known icing conditions Date of Application for U.S. Amended Type Certificate for Model P2010 TDI January 28, 2021. The European Aviation Safety Agency (EASA) originally type certified this model aircraft under its type certificate number EASA.A.576. Maximum Operating Altitude 18000 ft Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the airplane for certification. Such equipment is listed in the current FAA approved AFM: 2010/552 Ed. 1, Rev. 1, or later approved revisions. 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. Each airplane is provided with the following approved documents: a) AFM doc. 2010/552 Ed. 1, Rev. 1, or later FAA approved revision. b) Airplane Maintenance Manual (AMM) doc. 2010/553 Ed. 2, Rev. 0, or later FAA approved revision, including Chap. 4: "Airworthiness Limitations" and Chap. 5: "Time Limits/ Maintenance Check". c) The appropriate Continental series engine maintenance manuals. d) 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: 16.1 lbs at 24.1 in aft of datum NOTE 2 Airplane operation must be in accordance with the FAA approved AFM listed above. All placards listed in Section 2 must be displayed. 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 FAA approval. A00066CE Page 10 of 10 Revisions to the Airworthiness Limitations must be approved by the FAA. The inspections, maintenance, repair and painting must be accomplished according to the Maintenance Manual or other procedures acceptable to the FAA. NOTE 4 Information essential for the proper operation, maintenance and inspection of the airplane is contained in the Tecnam P2010 TDI AFM and AMM. NOTE 5 Optional Weight Increase up to 1200 kg Tecnam Modification No. MOD2010/207 (P2010TDI: weight increment up to 1200kg). Airplanes with this modification must have Tecnam P2010 TDI AFM Doc. 2010/552, Ed. 2, Rev. 0, or later FAA/EASA approved revisions and Tecnam P2010 TDI AMM Doc. 2010/553, Ed. 2, Rev. 0, or later FAA/EASA approved revisions. Aircraft in service can incorporate this modification using Tecnam Service B ulletin SB 487-CS. NOTE 6 Optional Engine Upgrade for “Cold Weather Operation” Tecnam Modification No. MOD2010/240 (P2010TDI: CD-170 engine upgrade for “cold weather operation” limitation removal). Airplanes with this modification must have Tecnam P2010 TDI AFM Doc. 2010/552, Ed. 2, Rev. 4, or later FAA/EASA approved revisions. Also, must have Tecnam P2010 TDI AMM Temporary Revision No. TR-AMM-210D-009, Rev. 0, or later FAA/EASA approved revisions or Tecnam P2010 TDI AMM Doc. 2010/553 that incorporates this Temporary Revision. Aircraft in service can incorporate this modification using Tecnam Service Bulletin SB-587-CS. NOTE 7 Optional Weight Increase up to 1220 kg Tecnam Modification No. MOD2010/269 (P2010TDI: weight increment up to 1220kg). Airplanes with this modification must have Tecnam P2010 TDI AFM Doc. 2010/552, Ed. 2, Rev. 6 , or later FAA/EASA approved revisions. Also, must have Tecnam P2010 TDI AMM Temporary Revision No. TR-AMM- 210D-018, Rev. 0, or later FAA/EASA approved revisions or Tecnam P2010 TDI AMM Doc. 2010/553