TCDS A57CE

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 Rev. No. 34 24 30 31 30 23 28 30 31 34 28 28 30 31 30 34 18 33 18 31 33 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A57CE Revision 34 DIAMOND DA 42 DA 42 NG DA 42 M-NG DA 62 July 8, 2025 TYPE CERTIFICATE DATA SHEET NO. A57CE This data sheet which is part of Type Certificate No. A57CE 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: Diamond Aircraft Industries GmbH N.A. Otto-Str.5 A-2700 Wiener Neustadt Austria I. Model DA 42 (Normal Category), approved July 22, 2005 Engine 2 Technify Motors GmbH (formerly Thielert) TAE 125-01 or TAE 125-02-99 or TAE 125-02-114, see Note 1 FAA Type Certification Data Sheet No. E00069EN Fuel Jet A, Jet A-1 (ASTM 1655) Engine Limits Maximum Take-Off, 2300 rpm Continuous Operation, 2300 rpm (Propeller shaft RPM) Propeller 2 MT Propeller Co. MTV-6-A-C-F/CF187-129 FAA Type Certification Data Sheet No. P19NE Propeller Limits Diameter 74.0 in., +0.0 in., -2.0 in; (1870 mm, +0.0mm, -50mm) Low Pitch Setting 12° Feather Position 81º Start Lock 15° Airspeed Limits Maximum Never Exceed Speed VNE 192 KCAS, 220 mph Maximum Structural Cruising Speed VNO 155 KEAS, 178 mph Design Cruising Speed VC 155 KEAS, 178 mph Maneuvering Speed if MAM 42-088 and/or OAM 42-054 incorporated VA (up to 3400 lbs / 1542 kg) 119 KEAS, 137 mph VA (above 3400 lbs / 1542 kg) 125 KEAS, 144 mph if neither MAM 42-088 nor OAM 42-054 incorporated VA (up to 3236 lbs / 1468 kg) 119 KEAS, 137 mph VA (above 3236 lbs / 1468 kg) 122 KEAS, 140 mph Maximum Flap Extending Speed VFE Full Flaps 110 KEAS, 127 mph VFE Approach Flaps 135 KEAS, 155 mph Maximum Landing Gear Operation Speed VLO 155 KEAS, 178 mph Maximum Landing Gear Extended Speed VLE 192 KCAS, 220 mph A57CE Page 2 of 21 C.G. Range Forward c/g position (aft of datum): up to 3236 lbs. (1468 kg) 92.5 in. (2.35 meter) at 3935 lbs. (1785 kg) 94.5 in. (2.40 meter) Varying Linearly with weight in between Rearward c/g position (aft of datum): At 2756 lbs. (1250 kg) 95.3 in. (2.42 meter) At 3527 lbs. (1600 kg) and above 98.0 in (2.49 meter) Varying Linearly with weight in between Empty Wt. C.G. Range None Reference Datum 86.5 in. (2.196 meter) in front of leading edge of stub-wing at the wing joint Leveling Means Floor of front baggage compartment levelled. Maximum Weight Takeoff (Normal Category) 3748 lbs. (1700 kgs) 3935 lbs. (1785kgs), see Note 9 Landing 3748 lbs. (1700 kgs) Zero Fuel weight 3638 lbs. (1650 kg) Minimum Crew 1 No. of Seats 4 Maximum Baggage Front Baggage Compartment 66 lbs (30 kgs) Behind Rear Seats 100 lbs (45 kgs) Aft part of Baggage Extension 40 lbs (18 kgs) Whole aft baggage compartment together 100 lbs (45 kg) Fuel Capacity With Standard Fuel Tank 52 gallons (196.8 liters) total. 50 gallons (189.2 liters) usable. With Auxiliary Tank additional 27.4 gallons (104 liters) total 26.4 gallons (100 liters) usable Oil Capacity Each engine Maximum – 6.3 qts (6.0 liters). Minimum – 4.8 qts (4.5 liters) See Note 2 For specification of engine and gearbox oil see AFM Coolant Distilled water / Cooler Protection For more details see applicable AFM, Section 2 Maximum Operating Altitude 18,000 feet. (5486 meters) Control Surface Movements Aileron trailing edge up 25º, ± 2º, trailing edge down 15º, +2/-0º Elevator trailing edge up 15.5º, ± 0.5º, trailing edge down 13º, ± 1º Elevator Trim Tab: 28º, ± 5º (nose up at elevator neutral) 25º, ± 5º (nose down at elevator neutral) Rudder: left 27º, ± 1º / right 29º, ± 1º Rudder Trim Tab: 30º, +5/-0º (trim RH at rudder neutral) 29º, +5/-0º (trim LH at rudder neutral) With OÄM 42-252 installed: 45º ± 3º (trim RH at rudder neutral) 41º ± 3º (trim LH at rudder neutral) Page 3 of 21 A57CE Flaps: Cruise flap setting 0°, + 2°- 0° Approach flap setting 20º, + 4º - 2° Landing flap setting 42º, +3º - 1º Manufacturer’s Serial Numbers a) For aircraft produced at Diamond Aircraft Industries GmbH, N.A. Otto-Str. 5, A-2700 Wiener-Neustadt Austria, eligible serial numbers are 42.004 and subsequent b) For aircraft produced at Diamond Aircraft Industries Inc., 1560 Crumlin Sideroad, London Ontario N5v 1S2, Canada, eligible serial numbers are 42.AC001 and subsequent Certification Basis Type Certification under 14 CFR Section 21.29 including the following requirements: - Joint Aviation Requirements (JAR) 23, Amdt. 1, dated February 01, 2001. - NOTE: The DA 42 was certificated using the FAA/JAA validation certification procedures. A list of Significant Regulatory Differences was addressed. Therefore, the certification basis is equivalent to 14 CFR Part 23 effective February 1, 1965, including Amendments 23-1 through Amendment 23-55. - 14 CFR Part 36 effective December 1, 1969, including Amendments 36-1 through Amendment 36-24. - Special Conditions: - 23-167-SC applicable to the Model DA 42 for Protection of Systems for High Intensity Radiated Fields. - 23-169-SC applicable to the Model DA 42 for Diesel Cycle Engine Using Turbine (Jet) Fuel. Equivalent safety Items: Equivalent Levels of Safety findings made per the provisions of 14 CFR 21.21(b)(1) for: - Equivalent level of safety ACE-05-05 applicable to the Model DA 42 for Ignition Switches with the TAE-125-01 or TAE 125-02-99 or TAE 125-02-114 Diesel Engines. - Equivalent level of safety ACE-05-06 applicable to the Model DA 42 for Cockpit Controls and Motion and Effect of Cockpit Controls with the TAE-125-01 or TAE 125- 02-99 or TAE 125-02-114 Diesel Engines. - Equivalent level of safety ACE-05-07 applicable to the Model DA 42 for Liquid Cooling with the TAE-125-01 or TAE 125-02-99 or TAE 125-02-114 Diesel Engines. - The Austro Control group (ACG) originally type certificated this aircraft. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product under their Type certificate Number A.005 on behalf of Austria. - DAI elected to comply with the following requirements: With OÄM 42-324 installed: 14 CFR 23.2270 (a) – (d), Amendment 23-64 Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) is listed in the Airplane Flight Manual and must be installed in the airplane for certification. In addition, the following items of equipment are required: Airplane Flight Manual, Document No. 7.01.05-E, dated 29-April-2004. For GFC 700 equipped DA 42, Airplane Flight Manual, Document No. 7.01.06-E, dated 20- December-2007. For TAE 125-02-114 equipped DA 42 (OÄM 42-252) AFM Supplement S07 applies. Maintenance Manual (including Airworthiness Limitation), Document No. 7.02.01, dated 01-Dec-2004. A57CE Page 4 of 21 Import requirements a) For aircraft produced in Austria, 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 Austro Control Group (ACG) 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 Part 23 approved under U.S. Type Certificate No. A57CE and to be in a condition for safe operation”. b) For aircraft produced in Canada, a United States airworthiness certificate may be issued on the basis of a Canadian Certificate of Airworthiness for Export signed by a representative of the Transport Canada Civil Aviation (TCCA), containing the following statement (in the English language): ‘The aircraft covered by this certificate has been examined, tested, and found to comply with U.S. type certificate No. A57CE and to be in a condition for safe operation.’ c) The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 and exported by the country of manufacture is FAR Sections 21.183(c) or 21.185(c). d) The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 exported from countries other than the country of manufacture (e.g., third party country) is FAR Section 21.183(b) or 21.183(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. 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 Austro Control Group. · 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: Engine part number of TAE 125-01 approved for installation in the DA 42 is 125-01-(017)-(), engine part number of TAE 125-02-99 aproved for installation in the DA 42 is 125-02-99-(0003)-(), engine part number of TAE 125- 02-114 aproved for installation in the DA 42 is 125-02-114-(0006)-(), with approved firmware and mapping according to DAI MSB 42-007, always latest issue. Page 5 of 21 A57CE NOTE 2: Weight and Balance: A current weight and balance report including 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 full oil, coolant and unusable fuel. NOTE 3: The placards specified in the EASA approved Airplane Flight Manual must be displayed. NOTE 4: "Compliance with requirements of 14 CFR § 23.1419 as amended by Amendment 23-43 effective May 10, 1993, has been established by the Exemption Number 9623 granted to Diamond Aircraft Industries, Austria, dated February 22, 2008, provided required ice protection systems are installed and functioning properly, and the airplane and the ice protections system are operated in accordance with Airplane Flight Manual Supplement S03, "Ice Protection System," dated February 10, 2007, or later approved revision." NOTE 5: For approved software versions of Garmin G1000 Integrated Avionics System, see DAI MSB 42-008, always latest version. NOTE 6: Instructions for Continued Airworthiness and Service Life Limited components is included in the Maintenance Manual Document No. 7.02.01. (Revisions to Airworthiness Limitations must be approved by the FAA) NOTE 7: Exterior color is limited to that specified in Diamond Document No. 7.02.01. NOTE 8: Major structural repair must be accomplished at a FAA certified repair stations rated for composite aircraft structure work, in accordance with Diamond repair methods approved by ACG and accepted by FAA. NOTE 9: The maximum takeoff mass of 3935 lbs. (1785 kgs) is approved if major Change MAM 42-088 is installed. NOTE 10: Approved major changes on Diamond DA-42 are: MÄM 42-007 AFM Revision 5, part of initial type design MÄM 42-031 Increase of the initial Major Inspection Interval, part of initial type design MAM 42-046 Rough field Operations MAM 42-088 Increased gross weight MAM 42-101 New engine instrument marking MÄM 42-102 Increase of the cont. major inspection interval, part of initial type design MÄM 42-111/b, New ROC for Single Engine Operation MAM 42-198 Engine change to TAE 125-02-99 MÄM 42-361/c DA 42 Installation NG Safety Walk Strips OÄM 42-051, Autopilot, part of initial type design OÄM 42-052 IFR Operation, part of initial type design OÄM 42-054 Known Icing OAM 42-056 Auxilliary tank OÄM 42-067 Adjustable back rest for front seats OAM 42-102 Installation of Garmin GFC 700 Autopilot OÄM 42-146 Garmin Synthetic Vision (SVT) OÄM 42-188 Increase of Maximum Zero Fuel Weight OÄM 42-195 DA 42 NG Landing Gear for DA 42 OÄM 42-252 Installation of TAE 125-02-114 Engine OÄM 42-324 AmSafe V23 AAIR Aviation Inflatable Restraint System NOTE 11: For Airplanes registered in the United States of America, an ECU Backup Battery must be installed. The ECU Backup Battery may be installed during production per the requirements of OAM 42-129, or in compliance with FAA Airworthiness Directive 2007-23-14 per the requirements of OSB 42-050/1. A57CE Page 6 of 21 II. Model DA 42 NG (Normal Category), approved April 02, 2010 Engine 2 Austro Engine E4, see Note 1 FAA Type Certification Data Sheet No. E00081EN Fuel Jet A, Jet A-1 (ASTM 1655) Engine Limits Maximum Take-Off (5 min), 2300 rpm Maximum Continuous Operation, 2100 rpm With MÄM 42-600 installed, 2300 rpm see note 12 (Propeller shaft RPM) Max T/O Power (5min) 100%(123,5 kW) Max. Continous Power 92% (114 kW) Propeller 2 MT Propeller Co. MTV-6-R-C-F/CF187-129 or 2 MT Propeller Co. MTV-6-R-C-F/CF190-69 see Note 12 FAA Type Certification Data Sheet No. P19NE Propeller Limits Diameter 74.0 in., +0.0 in., -2.0 in; (1870 mm, +0.0mm, -50mm) or 75.0 in., +0.0 in., -2.0 in; (1900 mm, +0.0mm, -50mm) (MÄM 42-600) Low Pitch Setting 12° 13° (MÄM 42-600) see Note 12 Feather Position 81º 80° (MÄM 42-600) see Note 12 Start Lock 15° Airspeed Limits Maximum Never Exceed Speed VNE 192 KCAS, 220 mph Maximum Structural Cruising Speed VNO 155 KEAS, 178 mph Design Cruising Speed VC 155 KEAS, 178 mph Operating Maneuvering Speed VO (up to 3748 lbs / 1700 kg) 114 KEAS, 131 mph VO (3748 lbs / 1701 kg through 3968 lbs / 1800kg) 121 KEAS, 139 mph VO (above 3968 lbs / 1800 kg) 125 KEAS, 144 mph Maximum Flap Extending Speed VFE Full Flaps 110 KEAS, 127 mph VFE Approach Flaps 135 KEAS, 155 mph Maximum Landing Gear Operation Speed VLO 155 KEAS, 178 mph Maximum Landing Gear Extended Speed VLE 192 KCAS, 220 mph C.G. Range Forward c/g position (aft of datum): Forward limit at 3197 lbs. (1450 kgs) 92.5 in. (2.350 meters) at 3236 lbs. (1468 kgs) 92.5 in. (2.350 meters) at 4189 lbs. (1900 kgs) 95.2 in. (2.418 meters) If MÄM 42-678 is installed: at 4407 lbs. (1999 kgs) 95.8 in. (2.434 meters) Varying Linearly with weight in between Rearward c/g position (aft of datum): at 3197 lbs. (1450 kgs) 96.6 in. (2.454 meters) at 3748 lbs. (1700 kgs) and above 97.6 in. (2.480 meters) Varying Linearly with weight in between If OÄM 42-199 is installed (see note 13): For all weights 96.5 in. (2.450 meters) If OÄM 42-199 and MÄM 42-600 are installed (see note 13): at 3197 lbs. (1450 kgs) 96.6 in. (2.454 meters) at 3329 lbs. (1510 kgs) and above 96.9 in. (2.460 meters) Page 7 of 21 A57CE Empty Wt. C.G. Range None Reference Datum 86.5 in. (2.196 meter) in front of leading edge of stub-wing at the wing joint Leveling Means Floor of front baggage compartment levelled. Maximum Weight (see note 14) Takeoff (Normal Category) 4189 lbs. (1900 kgs) If MÄM 42-678 is installed 4407 lbs. (1999 kgs) Landing 3979 lbs. (1805 kgs) If MÄM 42-659 is installed 4407 lbs. (1999 kgs) Zero Fuel weight 3891 lbs. (1765 kgs) If MÄM 42-659 is installed 4045 lbs. (1835 kgs) Minimum Crew 1 No. of Seats 4 Maximum Baggage Front Baggage Compartment 66 lbs (30 kgs) Behind Rear Seats 100 lbs (45 kgs) Aft part of Baggage Extension 40 lbs (18 kgs) Whole aft baggage compartment together 100 lbs (45 kg) Fuel Capacity With Standard Fuel Tank 52 gallons (196.8 liters) total. 50 gallons (189.2 liters) usable. With Auxiliary Tank additional 27.4 gallons (104 liters) total 26.4 gallons (100 liters) usable Oil Capacity Each engine Maximum – 7,4 qts (7.0 liters). Minimum – 5,3 qts (5.0 liters) See Note 2 For specification of engine and gearbox oil see AFM, 7.01.15, Section 2 Coolant Water / Cooler Protection For more details see AFM, Section 2 Maximum Operating Altitude 18,000 feet. (5486 meters) Control Surface Movements Aileron trailing edge up 25º, ± 2º, trailing edge down 15º, +2/-0º Elevator trailing edge up 15.5º, ± 0.5º, trailing edge down 13º, ± 1º Elevator Trim Tab: 28º, ± 5º (nose up at elevator neutral) 25º, ± 5º (nose down at elevator neutral) Rudder: left 27º, ± 1º / right 29º, ± 1º Rudder Trim Tab: 45º, ± 3º (trim RH at rudder neutral) 41º, ± 3º (trim LH at rudder neutral) MÄM 42-600 43°, ± 3º (trim RH at rudder neutral) MÄM 42-600 39º, ± 5º (trim LH at rudder neutral) MÄM 42-600 and MÄM 42-885: 48º, ± 3º (trim RH at rudder neutral) 36°, ± 5º (trim LH at rudder neutral) Flaps: Cruise flap setting 0°, + 2°/- 0° Approach flap setting 20º, + 4º/ - 2° Landing flap setting 42º, +3º - 1º A57CE Page 8 of 21 Manufacturer’s Serial Numbers a) For aircraft produced at Diamond Aircraft Industries GmbH, N.A. Otto-Str. 5, A-2700 Wiener-Neustadt Austria, eligible serial numbers are 42.N001 and subsequent See Note 10. b) For aircraft produced at Diamond Aircraft Industries Inc., 1560 Crumlin Sideroad, London Ontario N5v 1S2, Canada, eligible serial numbers are 42.NC001 and subsequent See Note 10. Certification Basis Type Certification under 14 CFR Section 21.29 including the following requirements: - Joint Aviation Requirements (JAR) 23, Amdt. 1, dated February 01, 2001. NOTE: The DA 42 NG was certificated using the FAA/EASA interim validation certification procedures. A list of Significant Regulatory Differences was addressed. Therefore, the certification basis is equivalent to 14 CFR Part 23 effective February 1, 1965, including Amendments 23-1 through Amendment 23-55. - 14 CFR Part 36 effective December 1, 1969, including Amendments 36-1through Amendment 36-24. - Special Conditions: - 23-167-SC applicable to the Model DA 42 for Protection of Systems for High Intensity Radiated Fields. - 23-169-SC applicable to the Model DA 42 for Diesel Cycle Engine Using Turbine (Jet) Fuel. Equivalent safety Items: Equivalent Levels of Safety findings made per the provisions of 14 CFR 21.21(b)(1) for: - Equivalent level of safety ACE-05-05A: Extension of Equivalent Level of Safety (ELOS) to 14 CFR part 23, §23.1145, Motion and Effect of Cockpit Controls for the Diamond Aircraft Industries Model DA-42NG Airplane. - Equivalent level of safety ACE-05-06A: Extension of Equivalent Level of Safety (ELOS) to 14 CFR part 23, §23.777(d), Ignition Switches, for the Diamond Aircraft Industries for the DA-42NG Airplane. - Equivalent level of safety ACE-05-07A: Extension of Equivalent Level of Safety (ELOS) to 14 CFR part 23, §23.1061, Liquid Cooling – Installation, and §23.1063 Liquid Cooling – Coolant tank tests for the Diamond Aircraft Industries DA-42NG Airplane - Equivalent level of safety ACE-10-07: Equivalent level of safety (ELOS) to 14 CFR part 23, § 23.991(a)(1) and §23.991(b), Fuel pumps for the Diamond Aircraft Industries DA 42 NG airplane - The European Aviation Safety Agency (EASA) certificated this aircraft under their Type certificate Number A.005. - DAI elected to comply with the following requirements: With OÄM 42-324 installed: 14 CFR 23.2270 (a) – (d), Amendment 23-64 Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) is listed in the Airplane Flight Manual and must be installed in the airplane for certification. In addition, the following items of equipment are required: Airplane Flight Manual, Document No. 7.01.15-E, Rev. 2, dated 30-Nov-2009, or a later approved revision or if MÄM 42-600 is installed, Airplane Flight Manual, Document Number 7.01.16-E, Rev. 0, dated 01-Apr-2012 or a later approved revision. Page 9 of 21 A57CE Maintenance Manual (including Airworthiness Limitation), Document No. 7.02.15, Rev. 1, dated 15-Oct-2009, or a later approved revision. Import requirements a) For aircraft produced in Austria, 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 Austro Control (ACG) 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 Part 23 approved under U.S. Type Certificate No. A57CE and to be in a condition for safe operation”. b) For aircraft produced in Canada, a United States airworthiness certificate may be issued on the basis of a Canadian Certificate of Airworthiness for Export signed by a representative of the Transport Canada Civil Aviation (TCCA), containing the following statement (in the English language): ‘The aircraft covered by this certificate has been examined, tested, and found to comply with U.S. type certificate No. A57CE and to be in a condition for safe operation.’ c) The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 and exported by the country of manufacture is FAR Sections 21.183(c) or 21.185(c). d) The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 exported from countries other than the country of manufacture (e.g., third party country) is FAR Section 21.183(b) or 21.183(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. Service Information Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or Diamond Aircraft DOA No. EASA.21J.052: · 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.