# TCDS A57CE: Diamond Aircraft Industries GmbH - Type: Type certificate data sheet - Status: Current - Holder: Diamond Aircraft Industries GmbH - Revision: 34 - Revised: July 8, 2025 - Product: Aircraft, Small Airplane - Certification basis: Part 23, Part 21 - Registered aircraft: 284, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/01/3f/013f4d1aa66ac0f0370bf67ab93860f77ae69ab62cb129b91f6e58a7d9447800 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID158115701820250709134158.0001 - Page: https://openairdocs.org/tcds/A57CE ## Models (4) As the data sheet lists them. - DA 42 NG - DA 62 - DA 42 - DA 42 M-NG ## 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 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. 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. A57CE Page 10 of 21 NOTE 1: Approved engine configuration for installation in the DA 42 NG: E4-B With MÄM 42-600: E4-C With approved engine software according to DAI MSB 42NG-002/3 or later issue. 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 10036 granted to Diamond Aircraft Industries, Austria, dated March 23, 2010, 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 28-May-2009, or later approved revision. NOTE 5: For approved software versions of Garmin G1000 Integrated Avionics System, see DAI MSB 42NG-003, always latest version. NOTE 6: Instructions for Continued Airworthiness and Service Life Limited components is included in the Maintenance Manual Document No. 7.02.15. (Revisions to Airworthiness Limitations must be approved by the FAA) NOTE 7: Exterior color is limited to that specified in Diamond Document No. 7.02.15. 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 EASA or Diamond Aircraft DOA No. EASA.21J.052 and accepted by FAA. NOTE 10: Aircraft Model DA-42 converted to DA42-NG via Diamond Aircraft Industries Service Bulletin OSB 42-068 are also eligible for this TCDS. Necessary design changes to be incorporated in the Diamond DA-42 NG (factory installed or via service bulletin) are: MÄM 42-403 Modification of the electrical system MÄM 42-415 DA 42 NG Sealing of center wing push-rod cutout NOTE 11: Approved major changes on Diamond DA-42 NG are: MÄM 42-325 DA 42 NG Exhaust shielding, part of initial type design OAM 42-160 Flight into known icing conditions, part of initial type design OÄM 42-179 SBAS and P-RNAV Operation OÄM 42-193 Recirculating Air Cabin Cooling OÄM 42-204 Additional Alternator OÄM 42-207 Short Baggage Compartment OÄM 42-173 On Top Exhaust System MÄM 42-600 Performance Enhancement OÄM 42-199 Removal of Variable Elevator Stop MÄM 42-659 Maximum Landing Weight 1999 kg MÄM 42-678 Maximum Take-Off Weight 1999 kg, Maximum Zero Fuel Weight 1835 kg MÄM 42-885 Improved Rudder and Rudder Trim Tab Installation MÄM 42-1114 Use of Portable Electronic Device OÄM 42-337 Gamin Flight Stream 510 OÄM 42-324 AmSafe V23 AAIR Aviation Inflatable Restraint System MÄM 42-1312 Operational Fluids Update NOTE 12: The installation of Propeller MTV-6-R-C-F/CF190-69 is only approved by complete instellation of design change MÄM 42-600 which includes a number of different modifications. NOTE 13: The Variable Elevator Stop is removed with OÄM 42-199 installed. Page 11 of 21 A57CE NOTE 14: The following Design Weight Configurations are approved: Design Changes installed Standard MÄM 42-659 MÄM 42-659 and MÄM 42-678 MTOW 1900 kgs (4189 Ibs.) 1900 kgs (4189 Ibs.) 1999 kgs (4407 Ibs.) MZFW 1765 kgs (3891 Ibs.) 1835 kgs (4045 Ibs.) 1835 kgs (4045 Ibs.) MLW 1805 kgs (3979 Ibs.) 1900 kgs (4189 Ibs.) 1999 kgs (4407 Ibs.) MTOW – maximum take-off weight; MZFW – maximum zero fuel weight; MLW – maximum landing weight The retrofit installation of the design changes is only approved per TC Holder Service Bulletins. III. Model DA 42 M-NG (Normal Category), 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 (Propeller shaft RPM) With MÄM 42-600 installed, 2300 rpm (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 15 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) Feather Position 81º 80º (MÄM 42-600) 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): at 3197 lbs. (1450 kgs) 92.5 in. (2.350 meters) A57CE Page 12 of 21 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 meterss) 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 12): For all weights 96.5 in. (2.450 meters) 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 kg) 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 Distilled water / Cooler Protection For more details see AFM, 7.01.15, 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) Page 13 of 21 A57CE 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 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 Manufacturer’s Serial Numbers For aircraft produced at Diamond Aircraft Industries GmbH, N.A. Otto-Str. 5, A-2700 Wiener-Neustadt Austria, eligible serial numbers are 42.339, 42.379, 42.MN001 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 36-1 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-05-05B: 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-42 M-NG Airplane. - Equivalent level of safety ACE-05-06B: 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-42 M-NG Airplane. - Equivalent level of safety ACE-05-07B: 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-42 M-NG 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 A57CE Page 14 of 21 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 appoved revision including Supplement M00, dated 01-Jun-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 including Supplement M00 Revision 2 dated 28-Oct-2019. Maintenance Manual (including Airworthiness Limitation), Document No. 7.02.15, Rev. 1, dated 15-Oct-2009, or a later approved revision and Supplemental AMM Doc. No. 7.02.15- M00, date 01-Jun-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 Page 15 of 21 A57CE · 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: Approved engine configuration for installation in the DA 42 NG: E4-B With MÄM 42-600 installed: E4-C With approved engine software according to DAI MSB 42NG-002/3 or later issue. 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 10037 granted to Diamond Aircraft Industries, Austria, dated March 29, 2010, 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 28-May-2009, or later approved revision." NOTE 5: For approved software versions of Garmin G1000 Integrated Avionics System, see DAI MSB 42NG-003, always latest version. NOTE 6: Instructions for Continued Airworthiness and Service Life Limited components is included in the Maintenance Manual Document No. 7.02.15. (Revisions to Airworthiness Limitations must be approved by the FAA) NOTE 7: Exterior color is limited to that specified in Diamond Document No. 7.02.15. 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 EASA or Diamond Aircraft DOA No. EASA.21J.052 and accepted by FAA. NOTE 10: Aircraft Model DA-42 converted to DA42 M-NG via Diamond Aircraft Industries Service Bulletin OSB 42-081 are also eligible for this TCDS. Necessary design changes to be incorporated in the Diamond DA-42 NG (factory installed or via service bulletin) are: MÄM 42-403 Modification of the electrical system MÄM 42-415 DA 42 NG Sealing of center wing push-rod cutout NOTE 11: Approved major changes on Diamond DA-42 M-NG: MÄM 42-325 DA 42 NG Exhaust shielding, part of initial type design OAM 42-160 Flight into known icing conditions, part of initial type design OÄM 42-179 SBAS and P-RNAV Operation OÄM 42-173 On Top Exhaust System OÄM 42-199 Removal of Variable Elevator Stop MÄM 42-659 Maximum Landing Weight 1999 kg MÄM 42-678 Maximum Take-Off Weight 1999 kg, Maximum Zero Fuel Weight 1835 kg MÄM 42-600/c Performance Enhancement MÄM 42-600/e Performance Enhancement MÄM 42-885 Improved Rudder and Rudder Trim Tab Installation MÄM 42-1114 Use of Portable Electronic Device A57CE Page 16 of 21 OÄM 42-228/e Universal Nose OÄM 42-240/c Nose Pod OÄM 42-337 Gamin Flight Stream 510 OÄM 42-342 GeoStar Pod OÄM 42-324 AmSafe V23 AAIR Aviation Inflatable Restraint System MÄM 42-1312 Operational Fluids Update NOTE 12: The Variable Elevator Stop is removed with OÄM 42-199 installed. NOTE 13: For the purpose of a later on STC or installation of mission equipment that can fully comply with the standard TC Basis the following Modifications are approved for installation: OÄM 42-241 Belly Pod (Std. TC) The following additional Limitations apply: • Flights into known or forecast icing conditions prohibited • AFM and AMM Supplement M07 must be furnished OÄM 42-228 Nose with Hard Points The following additional Limitations apply: • Flights into known or forecast icing conditions prohibited • Most rearward flight CG: 2,45 m aft of Datum at 1510 kg 2,47 m aft of Datum at 1700 kg 2,47 m aft of Datum at 1900 kg Linear variation in between If OÄM 42-199 is installed (see note 09): for all weights 2,45 m aft of Datum • AFM and AMM Supplement M05 must be furnished • Maximum operating speed with Equipment installed 156 KIAS OÄM 42-240 Nose Pod (Std. TC) The following additional Limitations apply: • Flights into known or forecast icing conditions prohibited • Most rearward flight CG: 2,44 m aft of Datum at 1510 kg 2,46 m aft of Datum at 1700 kg 2,46 m aft of Datum at 1900 kg Linear variation in between If OÄM 42-199 is installed (see note 09): 2,44 m aft of Datum at 1510 kg 2,45 m aft of Datum at 1605 kg 2,45 m aft of Datum at 1900 kg Linear variation in between • AFM and AMM Supplement M06 must be furnished • Maximum operating speed with Equipment installed 156 KIAS OÄM 42-242 GeoStar Pod (Std. TC) The following additional Limitations apply: • Flights into known or forecast icing conditions prohibited • AFM and AMM Supplement M09 must be furnished NOTE 14: The following Design Weight Configurations are approved: Design Changes installed Standard MÄM 42-659 MÄM 42-659 and MÄM 42-678 MTOW 1900 kgs (4189 lbs.) 1900 kgs (4189 lbs.) 1999 kgs (4407 lbs.) MZFW 1765 kgs (3891 lbs.) 1835 kgs (4045 lbs.) 1835 kgs (4045 lbs.) Page 17 of 21 A57CE MLW 1805 kgs (3979 lbs.) 1900 kgs (4189 lbs.) 1999 kgs (4407 lbs.) MTOW – maximum take-off weight; MZFW – maximum zero fuel weight; MLW – maximum landing weight The retrofit installation of the design changes is only approved per TC Holder Service Bulletins. NOTE 15: The installation of Propeller MTV-6-R-C-F/CF 190-69 is only approved by complete installation of design change MÄM 42-600 which includes a number of different modifications. IV. Model DA 62 (Normal Category), approved February 22, 2016 Engine 2 Austro Engine E4P, 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 2200 rpm (Propeller shaft RPM) Max T/O Power (5min) 100% (132 kW) Max. Continous Power 95% (126 kW) Propeller 2 MT Propeller Co. MTV-6-R-C-F/CF194-80 FAA Type Certification Data Sheet No. P19NE Propeller Limits Diameter 76.4 in., +0.0 in., -2.0 in.; (1940 mm, +0.0mm, -50mm) Low Pitch Setting 11° Feather Position 80º Start Lock 15° Airspeed Limits Maximum Never Exceed Speed VNE 201 KEAS, 231 mph Maximum Structural Cruising Speed VNO 160 KEAS, 184 mph Design Cruising Speed VC 160 KEAS, 184 mph Operating Maneuvering Speed VO (up to 3968 lbs / 1800 kg) 119 KEAS, 137 mph VO (3969 lbs / 1801 kg through 4189 lbs / 1900 kg) 126 KEAS, 145 mph VO (4190 lbs / 1901 kg through 4407 lbs / 1999 kg) 130 KEAS, 149 mph VO (4408 lbs / 2000 kg through 4630 lbs / 2100 kg) 133 KEAS, 153 mph VO (4631 lbs / 2101 kg through 4850 lbs / 2200 kg) 136 KEAS, 156 mph VO (above 4851 lbs / 2201 kg through 5071 lbs / 2300 kg) 140 KEAS, 161 mph Maximum Flap Extending Speed VFE Full Flaps 118 KEAS, 136 mph VFE Approach Flaps 135 KEAS, 155 mph Maximum Landing Gear Operation Speed VLO 160 KEAS, 184 mph Maximum Landing Gear Extended Speed VLE 201 KCAS, 231 mph C.G. Range Forward c/g position (aft of datum): Forward limit Between 3527 lbs. (1600 kg) and 3968 lbs. (1800 kgs) 92.1 in. (2.340 meters) at 5071 lbs. (2300 kgs) 96.9 in. (2.460 meters) Varying Linearly with weight in between Rearward c/g position (aft of datum): at 3527 lbs. (1600 kgs) 96.9 in. (2.460 meters) Between 4189 lbs. (1900 kg) and 4407 lbs. (1999 kgs) 98.8 in. (2.510 meters) at 5071 lbs. (2300 kgs) and above 99.6 in. (2.530 meters) Varying Linearly with weight in between A57CE Page 18 of 21 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) 4407 lbs. (1999 kgs) If MÄM 62-001 is installed 5071lbs. (2300 kgs) Landing 5071 lbs. (2300 kgs) Zero Fuel weight 4489 lbs. (2036 kgs) If MÄM 62-063 is installed 4850 lbs. (2200 kgs) Minimum Crew 1 No. of Seats 5, If OÄM 62-019 is installed 7 Maximum Baggage LH Front Baggage Compartment 66 lbs (30 kgs) RH Front Baggage Compartment 66 lbs (30 kgs) Rear Baggage Compartment 265 lbs (120 kgs) If OÄM 62-019 is installed 101 lbs (46 kgs) Fuel Capacity With Standard Fuel Tank 52 gallons (196.8 liters) total. 50 gallons (189.2 liters) usable. With Auxiliary Tank additional 37 gallons (140 liters) total 36.4 gallons (137.8 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, 7.01.25, Section 2 Coolant Water / Cooler Protection For more details see AFM, Section 2 Maximum Operating Altitude 20,000 feet. (6096 meters) Control Surface Movements Aileron trailing edge up 25º, ± 2º, trailing edge down 15º, +2/-0º Elevator trailing edge up 18º, ± 0.5º, trailing edge down 15º, ± 1º Elevator Trim Tab: + 17º, ± 5º (nose up at elevator 10° up) - 35º, ± 5º (nose down at elevator 10° up) Rudder: left 30º, ± 1º / right 30º, ± 1º Rudder Trim Tab: + 45º, ± 5º (trim RH at rudder 20° LH) + 28º, ± 3º (trim LH at rudder 20° LH) Flaps: Cruise flap setting 0°, + 2° / - 0° Approach flap setting 20º, + 4º / - 2° Landing flap setting 42º, + 3º / - 1º Manufacturer’s Serial Numbers None. See Note 10. Page 19 of 21 A57CE 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. - A list of Significant Regulatory Differences was addressed using 14 CFR Part 23 amendment compared to CS-23, Original Issue. The certification basis is equivalent to 14 CFR Part 23 effective February 1, 1965, including Amendments 23-1 through Amendment 23-55. - §23.1306 Electrical and electronic system lightning protection. - §23.1308 High-intensity Radiated Fields (HIRF) Protection. [please add] - 14 CFR Part 36, effective December, 1969, including Amendments 36-1 through Amendments 36-28. - Special Conditions: - 23-169-SC applicable to the derivative model DA-62 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: - ACE-05-05 - Ignition Switches with the Austro AE300 Diesel Engine. - ACE-05-06C - Cockpit Controls and Motion and Effect of Cockpit Controls with the Austro AE300 Diesel Engine. - ACE-05-07 - Liquid Cooling with the Austro AE300 Diesel Engine. - ACE-10-07 - Fuel Pump Installations with the Austro AE300 Diesel Engine. FAA agrees with the EASA assessment for the changed product rule regarding the changes for this derivative model. The following are required regulations determined by the EASA that applicable due to the significantly changed areas: - CS 23.573 Damage tolerance and fatigue evaluation of structures (CS 23, amendment 2) - CS 23.603 Materials and workmanship (CS 23, amendment 2) - CS 23.613 Material strength and properties and design values (CS 23, amendment 2) - CS 23.629 Flutter (CS 23, amendment 2) - CS 23.775 Windshields and windows (CS 23, amendment 4) - CS 23.1419 Ice protection (CS 23, amendment 4) Based on editorial changes or references to guidance material the following later amendments apply: - CS 23.851 Fire extinguishers (CS 23, amendment 2) - CS 23.909 Turbo charger system (CS 23, amendment 2) DAI elected to comply with the following requirements: - CS 23.0049 Stalling Speed (CS 23, amendment 1) - CS 23.149(d) Vsse (CS 23 Initial issue) - CS 23.562 Emergency landing dynamic conditions (CS 23, amendment 1) - CS 23.807 Emergency Exits (CS 23, Initial issue) - CS 23.1093 Induction system icing protection (CS 23, Initial issue) - CS 23.1326 Pitot heat indication system (CS 23, amendment 3) - CS 23.1431 Electronic equipment (CS 23, amendment 3) - CS 23.1507 Maneuvering speed (CS 23, Initial issue) - CS 23.1563 Airspeed placards (CS 23, Initial issue) - The European Aviation Safety Agency (EASA) certificated this aircraft under their Type certificate Number A.005. A57CE Page 20 of 21 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. 7.01.25-E, Rev. 3, dated 15-Nov-2015, or a later approved revision. Maintenance Manual (including Airworthiness Limitation), Document No. 7.02.25, Rev. 0, dated 01-Apr-2015, 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. 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. Page 21 of 21 A57CE NOTE 1: Approved engine configuration for installation in the DA 62: E4P-C With approved engine software according to DAI MSB 62-002, always latest version. 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 17118 granted to Diamond Aircraft Industries, Austria, dated Oct 03, 2016, 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 For Flight Into Known Icing Rev. 1," dated 14-Oct-2016, or later approved revision." NOTE 5: For approved software versions of Garmin G1000 Integrated Avionics System, see DAI MSB 62-003, always latest version. NOTE 6: Instructions for Continued Airworthiness and Service Life Limited components is included in the Maintenance Manual Document No. 7.02.25. (Revisions to Airworthiness Limitations must be approved by the FAA) NOTE 7: Exterior color is limited to that specified in Diamond Document No. 7.02.25. 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 EASA or Diamond Aircraft DOA ref. EASA.21J.052 and accepted by FAA. NOTE 9: Approved major changes on Diamond DA 62 are: MÄM 62-001 2300 kg MTOM MÄM 62-003 Rear Baggage Compartment (5 seater) MÄM 62-006 2300 kg MLM MÄM 62-007 Colors other than white MÄM 62-008 Nose Baggage Compartment MÄM 62-063 Maximum Zero Fuel Mass 2200 kg OÄM 62-001 Aux Fuel Tank Installation OÄM 62-002 TKS System (non FIKI) OÄM 62-003 Flights into Known Icing Conditions OÄM 62-004 Oxygen System OÄM 62-019 7 Seat Configuration NOTE 10: Following the completion of Diamond Aircraft Factory Campaign No. 62-010 on March 14, 2023, the state of design of the DA 62 has transferred from EASA to Transport Canada Civil Aviation (TCCA). Diamond Aircraft Industries Inc. has taken over TC-holder responsibility for all DA 62 aircraft. DA 62 eligible serial numbers are listed on FAA TCDS A00012NY. .....END..... ``` ## ADs (27, in force first) - [AD 2026-14-08](https://openairdocs.org/ad/2026-14-08): Landing Gear Actuator · Diamond Aircraft Industries DA 42, DA 42 M-NG and DA 42 NG. Effective Jul 20, 2026 - [AD 2025-24-07](https://openairdocs.org/ad/2025-24-07): Passenger/Crew Doors · Diamond Aircraft Industries DA 42, DA 42 M-NG and DA 42 NG. Effective Feb 12, 2026 - [AD 2024-06-13](https://openairdocs.org/ad/2024-06-13): Flight Control System · Diamond Aircraft Industries DA 42, DA 42 NG and DA 42 M-NG. Effective May 28, 2024 - [AD 2022-06-08](https://openairdocs.org/ad/2022-06-08): Flight Control System · Diamond Aircraft Industries DA 42, DA 42 M-NG and DA 42 NG. Effective May 9, 2022 - [AD 2022-03-01](https://openairdocs.org/ad/2022-03-01): Fuel Storage · Diamond Aircraft Industries DA 42, DA 42 M-NG and DA 42 NG. Effective Mar 17, 2022 - [AD 2021-22-03](https://openairdocs.org/ad/2021-22-03): Nose/Tail Landing Gear Attach Section · Diamond Aircraft Industries DA 42, DA 42 M-NG and DA 42 NG. Effective Dec 21, 2021 - [AD 2019-14-11](https://openairdocs.org/ad/2019-14-11): Flight Controls · Diamond Aircraft Industries DA 42 NG and DA 42 M-NG. Effective Sep 9, 2019 - [AD 2018-10-10](https://openairdocs.org/ad/2018-10-10): Engine Exhaust · Diamond Aircraft Industries DA 42. Effective Jun 12, 2018 - [AD 2016-22-06](https://openairdocs.org/ad/2016-22-06): Autopilot · Diamond Aircraft Industries DA 40 NG, DA 42 NG and DA 42 M-NG. Effective Nov 16, 2016 - [AD 2014-04-04](https://openairdocs.org/ad/2014-04-04): Electric Power · Diamond Aircraft Industries DA 42 NG and DA 42 M-NG. Effective Apr 7, 2014 - [AD 2013-19-11](https://openairdocs.org/ad/2013-19-11): Landing Gear · Diamond Aircraft Industries DA 42, DA 42 M-NG and DA 42 NG. Effective Oct 31, 2013 - [AD 2013-07-01](https://openairdocs.org/ad/2013-07-01): Landing Gear · Diamond Aircraft Industries DA 42, DA 42 M-NG and DA 42 NG. Effective May 20, 2013 - [AD 2013-06-02](https://openairdocs.org/ad/2013-06-02): Power Plant · Diamond Aircraft Industries DA 42 M-NG and DA 42 NG. Effective Apr 8, 2013 - [AD 2012-17-07](https://openairdocs.org/ad/2012-17-07): Wings · Diamond Aircraft Industries DA 42, DA 42 M-NG and DA 42 NG. Effective Oct 11, 2012 - [AD 2011-11-07](https://openairdocs.org/ad/2011-11-07): Landing Gear · Diamond Aircraft Industries DA 42. Effective Jul 6, 2011 - [AD 2011-10-13](https://openairdocs.org/ad/2011-10-13): Doors · Diamond Aircraft Industries DA 42, DA 42 M-NG and DA 42 NG. Effective Jun 17, 2011 - [AD 2008-23-08](https://openairdocs.org/ad/2008-23-08): Right hand engine support bracket · Diamond Aircraft Industries DA 42. Effective Dec 22, 2008 - [AD 2008-16-20](https://openairdocs.org/ad/2008-16-20): Aileron control system · Diamond Aircraft Industries DA 42. Effective Sep 17, 2008 - [AD 2007-23-14](https://openairdocs.org/ad/2007-23-14): Main aircraft battery · Diamond Aircraft Industries DA 42. Effective Dec 26, 2007 - [AD 2007-13-16](https://openairdocs.org/ad/2007-13-16): Surface roughness · Diamond Aircraft Industries DA 42. Effective Aug 10, 2007 - [AD 2007-12-24](https://openairdocs.org/ad/2007-12-24): Engine gearbox holding lines · Diamond Aircraft Industries DA 42. Effective Jul 19, 2007 - [AD 2007-12-05](https://openairdocs.org/ad/2007-12-05): Auxiliary fuel tank · Diamond Aircraft Industries DA 42. Effective Jul 16, 2007 - [AD 2022-21-15](https://openairdocs.org/ad/2022-21-15) (historical): Fuselage Miscellaneous Structure · Diamond Aircraft Industries DA 42, DA 42 NG and DA 42 M-NG. Effective Dec 14, 2022 - [AD 2017-18-10](https://openairdocs.org/ad/2017-18-10) (historical): Flight Controls · Diamond Aircraft Industries DA-42-M-NG, DA-42-NG and DA 42. Effective Oct 11, 2017 - [AD 2017-15-09](https://openairdocs.org/ad/2017-15-09) (historical): Engine Exhaust · Diamond Aircraft Industries DA 42. Effective Aug 1, 2017 - [AD 2017-11-08](https://openairdocs.org/ad/2017-11-08) (historical): Engine Exhaust · Diamond Aircraft Industries DA 42. Effective May 31, 2017 - [AD 2017-01-12](https://openairdocs.org/ad/2017-01-12) (historical): Engine Exhaust · Diamond Aircraft Industries DA 42. Effective Feb 22, 2017 ## Registered aircraft by registry model (OpenAirDocs) - [Diamond Aircraft Ind DA 42 NG](https://openairdocs.org/model/diamond-aircraft-ind-da-42-ng): 149 aircraft (registry codes 2990105, 2990205) - [Diamond Aircraft Ind DA 42](https://openairdocs.org/model/diamond-aircraft-ind-da-42): 114 aircraft (registry codes 2990104, 2990004) - [Diamond Aircraft Ind DA 62](https://openairdocs.org/model/diamond-aircraft-ind-da-62): 18 aircraft (registry code 2990103) - [Diamond Aircraft Ind DA42MNG](https://openairdocs.org/model/diamond-aircraft-ind-da42mng): 3 aircraft (registry code 2990009) ## STCs approved under this data sheet (31) - [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC - [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc. - [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC - [STC SA04681NY](https://openairdocs.org/stc/SA04681NY): Installation of MT-Propeller Entwicklung GmbH model MTV-6-( )-C-F/CF190-69( ) 3-blade, constant speed, full feathering propellers and spinners. MT- Propeller Entwicklung GmbH - [STC SA11174SC PAGE 1](https://openairdocs.org/stc/SA11174SC%20PAGE%201): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King) - [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation - [STC SA00344BO PAGE 1](https://openairdocs.org/stc/SA00344BO%20PAGE%201): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies - [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation - [STC SA02153LA-D PAGE 1](https://openairdocs.org/stc/SA02153LA-D%20PAGE%201): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc. - [STC SA02013CH](https://openairdocs.org/stc/SA02013CH): Installation of Avidyne Corporation Traffic Advisory System (TAS). Avidyne Corporation - [STC SA01828SE](https://openairdocs.org/stc/SA01828SE): Installation of J.P. Instruments (JPI) EDM-960 Primary Engine Data Management System. J. P. Instruments - [STC SA02212AK](https://openairdocs.org/stc/SA02212AK): Replacement of existing landing and/or taxi light reflector and bulbs with high intensity discharge (HID) lighting systems. Seaplanes North LLC - [STC SA03804NY](https://openairdocs.org/stc/SA03804NY): Engine Refit: The presently installed versions of the TAE 125-01 or TAE 125-02-99 engine are replaced by the TAE 125-02-114 engine. This STC includes two propeller configurations: 1) MTV-6-A-C-F / CF187-129 without noise suppressor or 2) MTV-6-A-C-F / CF190-69 with noise suppressor;. Crosby Aviation (Jersey) Ltd. - [STC SA03701NY](https://openairdocs.org/stc/SA03701NY): Installation of RF-006(A) Main Wheel and RA-002(B) Nose Wheel with EA-003.7N(A) Brake System. Beringer Aero - [STC SA11172SC](https://openairdocs.org/stc/SA11172SC): Installation of an ADS600-B Automatic Dependent Surveillance-Broadcast (ADS-B) Universal Access Transceiver (UAT) and Global Positioning System (GPS) antenna. NavWorx Inc - [STC SA01969SE](https://openairdocs.org/stc/SA01969SE): Installation of a Mid-Continent MD302 Standby Attitude Module. Mid-Continent Instruments and Avionics - [STC SA02442AK PAGE 1](https://openairdocs.org/stc/SA02442AK%20PAGE%201): Approval of the L-3 Communications NGT 2000/2500 ADS-B system. ADS-B Technologies, LLC - [STC SA02121SE](https://openairdocs.org/stc/SA02121SE): Installation of Garmin GTS 825 (TAS) or GTS 855 (TCAS I) Traffic System. Garmin International Inc - [STC SA00269BO](https://openairdocs.org/stc/SA00269BO): Installation of Avidyne Corporation TWX 670 Tactical Weather Detection System P/N 850-00026-000-( ) consisting of Avidyne Processor P/N 700-00033-000-( ), Sensor Systems Inc. Antenna P/N S72-1715-1 with doubler plate P/N S72-171530-1, and Avidyne Mounting Tray P/N 700-00034-000.. Avidyne Corporation - [STC SA02717NY PAGE 1](https://openairdocs.org/stc/SA02717NY%20PAGE%201): Installation of VoiceFlight Systems LLC VFS101 Speech Recognition Module. VoiceFlight Systems LLC - [STC SA02015SE-D](https://openairdocs.org/stc/SA02015SE-D): Installation of Garmin G500 Primary Flight Display (PFD) and Multifunction Display (MFD) System.. Garmin International Inc - [STC SA00432SE](https://openairdocs.org/stc/SA00432SE): Installation of EGT 701 series fuel flow instrument.. J P Instruments - [STC SA00861SE](https://openairdocs.org/stc/SA00861SE): Installation of J.P. Instruments (JPI) fuel flow indicating system. J P Instruments - [STC SA02226SE](https://openairdocs.org/stc/SA02226SE): Installation of vortex generators on the wings and tail surfaces. Micro AeroDynamics Inc - [STC SA00281BO](https://openairdocs.org/stc/SA00281BO): Installation of Avidyne Corporation MLX770 MultiLink Broadcast Transceiver P/N 700-00163-( ), Sensor Systems Inc. Antenna P/N S67-1575-109, or equivalent, and optional Avidyne Mounting Tray P/N 700-00165-000. Avidyne Corporation - [STC SA01918LA](https://openairdocs.org/stc/SA01918LA): Installation of AmSafe Inflatable Restraint System on the pilot and passenger seats.. AMSAFE Inc. - [STC SA00290BO](https://openairdocs.org/stc/SA00290BO): Installation of Avidyne Corporation Part Number 700-00167-XXX Multi-Function Display and Mounting Tray Assembly Part Number 700-00168-XXX. Avidyne Corporation - [STC SA02725NY](https://openairdocs.org/stc/SA02725NY): Installation of Lycoming IO-360 M1A series engines with MTV-12-B-C-F series propellers. Diamond Aircraft Industries Inc. - [STC SA03254CH](https://openairdocs.org/stc/SA03254CH) (historical): Installation of an Electric Vapor Air Cycle System. Standard Aero Business Aviation Services LLC - [STC SA02153LA-D](https://openairdocs.org/stc/SA02153LA-D) (historical): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc - [STC SA02717NY](https://openairdocs.org/stc/SA02717NY) (historical): Installation of VoiceFlight Systems LLC VFS101 Speech Recognition Module. VoiceFlight Systems LLC --- 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.