TCDS No. EASA.A.005 DA 42 - Series
Diamond DA42 VI · Type Certificate
Overview
This document is the Type Certificate Data Sheet (TCDS) for the Diamond DA42 series, specifically detailing the DA42 NG and its commercial designation, the DA42 VI. It provides essential information regarding the aircraft's design, operational limitations, and certification basis. The TCDS is intended for use by aviation authorities, manufacturers, and operators to ensure compliance with safety and operational standards. It outlines the aircraft's technical characteristics, including dimensions, engine specifications, weight limits, and performance data, which are crucial for pilots and maintenance personnel.
- Maximum Take-Off Weight: 1900 kg (4189 lb)
- Maximum Operating Altitude: 5486 m (18,000 ft)
- Wingspan: 13.42 m (44 ft 0 in)
- Maximum Structural Cruising Speed: 155 KEAS
- Fuel Capacity: 196.8 liters (52 US gallons)
Document
Source
Originally published by www.ikaros.dk. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Type Certificate
- Year
- 2023
- Pages
- 8
- File size
- 150 KB
- Publisher
- www.ikaros.dk
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- Pilot's Operating Handbook / AFM
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- Service Bulletins
- Type Certificate (TCDS)
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In this document
General Information
The TCDS identifies the aircraft as a twin-engine, four-seater low-wing airplane with composite construction and retractable tricycle landing gear. It is certified under JAR 23 Normal Category and is manufactured by Diamond Aircraft Industries in Austria, Canada, and China.
Technical Characteristics
The DA42 VI features a wingspan of 13.42 m (44 ft 0 in), a length of 8.56 m (28 ft 1 in), and a height of 2.49 m (8 ft 2 in). It is powered by two Austro Engine E4 engines, with a maximum take-off power of 123.5 kW and a maximum continuous power of 114 kW. The aircraft has a maximum operating altitude of 5486 m (18,000 ft) and is capable of all-weather operations.
Weight and Balance
The maximum take-off weight (MTOW) for the DA42 VI is 1900 kg (4189 lb), with variations depending on installed modifications. The maximum landing weight is 1805 kg (3979 lb). The center of gravity limits are specified for various weights, ensuring safe operation during flight.
Performance Data
Key performance speeds include a maximum structural cruising speed (vNO) of 155 KEAS and a never exceed speed (vNE) of 192 KEAS. The aircraft has a minimum control speed airborne (vMCA) of 75 KEAS and a maximum landing gear operation speed (vLO) of 155 KEAS.
Fuel and Fluids
The DA42 VI can use Jet A-1 and Diesel fuel, with a total fuel capacity of 196.8 liters (52 US gallons) and a usable fuel capacity of 189.2 liters (50 US gallons). Oil capacity per engine is between 5 to 7 liters, and the coolant system holds approximately 7 liters.
Safety notes
- Flights into known or forecast icing conditions are approved with the appropriate ice protection system installed.
- Operation with Diesel fuel is only approved if specific modifications are installed.
Full document text
TCDS No. EASA.A.005 DA 42 - Series Page 19 of 40 Issue 43, 29 March 2023 SECTION C: DA 42 NG C.I. General 1. Data Sheet No.: EASA.A.005 2. a) Type: b) Model: c) Variant: DA 42 DA 42 NG -- 3. Airworthiness Category: JAR 23 Normal Category 4. Type Certificate Holder: DIAMOND AIRCRAFT INDUSTRIES GMBH N.A. OTTO-STR. 5 A-2700 WIENER NEUSTADT AUSTRIA 5. Manufacturer: DIAMOND AIRCRAFT INDUSTRIES GMBH N.A. OTTO-STR. 5 A-2700 WIENER NEUSTADT AUSTRIA DIAMOND AIRCRAFT INDUSTRIES INC. 1560 CRUMLIN SIDEROAD, LONDON ONTARIO N5V 1S2 CANADA CETC WUHU DIAMOND AIRCRAFT MANUFACTURE CO., LTD. ANHUI XINWU ECONOMIC DEVELOPMENT ZONE, WUHU COUNTY PEOPLE'S REPUBLIC OF CHINA 6. Certification Application Date: 17-Jan-2008 7. (Reserved) N/A 8. (Reserved) N/A C.II. EASA Certification Basis 1. Reference Date for determining the applicable requirements: 02-Apr-2002 TCDS No. EASA.A.005 DA 42 - Series Page 20 of 40 Issue 43, 29 March 2023 2. Airworthiness Requirements: JAR-23, Amendment 1, issued 01-Feb-2001 JAR-1, Change 5, issued 15-Jul-1996 3. Special Conditions: CRI D-02 Variable Elevator Stop CRI E-02 Use of Jet Fuel for Reciprocating Engines CRI E-03 Use of Diesel Fuel for Reciprocating Engines CRI E-04 Liquid Cooling – Coolant Tank CRI E-05 Electronically-controlled Reciprocating Diesel Engine CRI E-06 Engine Vibration Level CRI E-07 Engine Torque CRI F-01 Protection from the Effects of HIRF CRI F-03 Protection from the Effects of Lightning Strikes, Indirect Effects CRI F-04 Power plant Instruments CRI F-07 Human Factors in Integrated Avionic System 3. Exemptions: None 4. Deviations: None 5. Equivalent Safety Findings: CRI E-10 Electrical Fuel Pump 6. Requirements elected to comply: CS 23.1507 (CS 23/0) CS 23.49 (CS 23/1) CS 23.562 (CS 23/1) With OÄM 42-324 installed: CS 23.2270 (a)-(d), (CS23/5) 7. Environmental Standards: ICAO, Annex 16, Volume 1, Part II and as implemented in Decision No. 2003/4/RM amended by Decision 2007/007/R of The Executive Director of the Agency dated 2 April 2007, on certification specifications providing for acceptable means of compliance for aircraft noise CS-36, Amendment 1 see Note 2 8. (Reserved) N/A 9. (Reserved) N/A 10. Operational Suitability Requirements OSD MMEL: CS-GEN-MMEL, Initial Issue dated 31 January 2014 TCDS No. EASA.A.005 DA 42 - Series Page 21 of 40 Issue 43, 29 March 2023 C.III. Technical Characteristics and Operational Limitations 1. Type Design Definition: Current issue of Doc. No. 7.07.00, Chapter V004/7including Design Changes VÄM 42-004, MÄM 42-313, MÄM 42-316 to 318, 42-322, 42-325 and following 2. Description: Twin engine, four-seated cantilever low wing airplane, composite construction, retractable tricycle landing gear, T- tail 3. Equipment: Equipment list, AFM, Section 6, see Note 3 4. Dimensions: Span Length Height Wing Area 13.42 m (44 ft 0 in) 8.56 m (28 ft 1 in) 2.49 m ( 8 ft 2 in) 16.29 m² (175.3 sqft) 5. Engine: 5.1.1 Model: 2 Austro Engine E4 see Note 4 5.1.2 Type Certificate: EASA Engine Type Certificate Data Sheet E.200 5.1.3 Limitations: Max take-off rotational speed (5 min.) 2300 r.p.m. Max continuous rotational speed 2100 r.p.m (Propeller shaft r.p.m) with MÄM 42-600 installed 2300 r.p.m Max T/O Power (5min) 100% (123,5 kW) Max. continuous Power 92% (114 kW) For power-plants limits refer to AFM, Section 2 5.1.4Firmware: see DAI MSB 42NG-002 See Note 4 5.1.5Mapping: see DAI MSB 42NG-002 See Note 4 6. Load factors: at vA at vNE with flaps in T/O or LDG position Positive: 3.8 3.8 2.0 Negative -1.52 0 7. Propeller: 7.1 Model: 2 MT-Propeller MTV-6-R-C-F/CF187-129 or 2 MT-Propeller MTV-6-R-C-F/CF 190-69 see Note 8 7.2 Type Certificate: EASA Prop. Type Certificate Data Sheet P.094 See note 5 7.3 Number of blades: 3 7.4 Diameter: 1870 mm or 1900 mm (MÄM 42-600) 7.5 Sense of Rotation: CW TCDS No. EASA.A.005 DA 42 - Series Page 22 of 40 Issue 43, 29 March 2023 7.6 Settings: Low pitch setting 12 ° 13° (MÄM 42-600) Feather position: 81 ° 80° (MÄM 42-600) Start Lock: 15° 8. Fluids: 8.1 Fuel: Jet A-1 (ASTM 1655), see note 7 Diesel (EN590), see note 11 8.2 Oil: Engine: Gearbox: Shell Helix Ultra 5W30 or 5W40 or see AFM, Section 2 Shell SPIRAX GSX 75W-80 or Shell SPIRAX S6 GXME 75W-80 or see AFM, Section 2 8.3 Coolant: Water / Cooler Protection for more details see AFM, Section 2 8.4 Ice Protection Fluids: AL-5 (DTD 406B) or Aeroshell Compound 07 for more details see AFM, Suppl. S03 9. Fluid capacities: 9.1 Fuel: Standard Fuel Tank Total: 196.8 liters 52 US Gallons Usable: 189.2 liters 50 US Gallons Auxiliary Fuel Tank Total: 104 liters 27,4 US Gallons Usable: 100 liters 26,4 US Gallons 9.2 Oil: each engine Maximum: 7 liters Minimum: 5 liters 9.3 Coolant system capacity: Approx. 7 liters 10. Air Speeds: Design Manoeuvring Speed vA up to 1700 kg 114 KEAS 1701 to 1800 kg 121 KEAS above 1800 kg 125 KEAS Flap Extended Speed vFE Approach 135 KEAS Landing 110 KEAS Maximum Landing Gear Operation Speed vLO 155 KEAS TCDS No. EASA.A.005 DA 42 - Series Page 23 of 40 Issue 43, 29 March 2023 Maximum Landing Gear Extended Speed vLE 192 KEAS Minimum Control Speed Airborne vMCA 75 KEAS MÄM 42-600 70 KEAS Maximum structural cruising speed vNO (= Maximum structural design speed vC) 155 KEAS Never exceed speed vNE 192 KEAS 11. Maximum Operating Altitude: 5486 m (18 000 ft) 12. Allweather Operations Capability: Day/Night-VFR, IFR Flights into known or forecast icing conditions See Note 6 13. Maximum Weights: Take-off Zero Fuel Landing See Note 12 1900 kg (4189 lb) If MÄM 42-678 is installed 1999 kg (4407 lb) 1765 kg (3891 lb) If MÄM 42-659 is installed 1835 kg (4045 lb) 1805 kg (3979 lb) If MÄM 42-659 is installed 1999 kg (4407 lb) 14. Centre of Gravity Range: Forward limit At 1450 kg 2.350 m behind Datum At 1468 kg 2.350 m behind Datum At 1900 kg 2.418 m behind Datum If MÄM 42-678 is installed At 1999 kg 2.434 m behind Datum Varying linearly with mass in between Rear limit At 1450 kg 2.454 m behind Datum At 1700 kg and above 2.480 m behind Datum
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Varying linearly with mass in between If OÄM 42-199 is installed (see note 10): For all weights 2.450 m behind Datum If OÄM 42-199 and MÄM 42-600 are installed: (see note 10) At 1450 kg 2.454 m behind Datum At 1510 kg and above 2.460 m behind Datum TCDS No. EASA.A.005 DA 42 - Series Page 24 of 40 Issue 43, 29 March 2023 15. Datum: 2.196 m in front of leading edge of stub-wing at the wing joint 16. Control surface deflections: Aileron Elevator Elevator Trim Tab Rudder Rudder Trim Tab Flaps trailing edge up 25º ± 2º trailing edge down 15º +2/-0º trailing edge up 15.5º ± 0.5º trailing edge down 13º ± 1º nose up at elevator neutral 28º ± 5º nose down at elevator neutral 25º ± 5º left 27º ± 1º right 29º ± 1º trim RH at rudder neutral 45º ± 3º trim LH at rudder neutral 41º ± 3º with MÄM 42-600 installed: trim RH at rudder neutral 43º ± 3º trim LH at rudder neutral 39º ± 5º with MÄM 42-600 and MÄM 42-885 installed: trim RH at rudder neutral 48º ± 3º trim LH at rudder neutral 36° ± 5º Cruise flap setting 0° + 2°- 0° Approach flap setting 20º + 4º - 2° Landing flap setting 42º +3º - 1º 17. Levelling Means: floor of front baggage compartment levelled 18. Minimum Flight Crew: 1 (Pilot) 19. Maximum Passenger Seating Capacity: 3 20. Baggage/Cargo Compartments: Location max. allowable Load Front Baggage Compartment 30 kg (66 lb) Behind Rear Seats 45 kg (100 lb) Aft part of Baggage Extension 18 kg (40 lb) Whole aft Baggage Compartment together 45 kg (100 lbs) 21. Wheels and Tyres: Nose Wheel Tyre Size 5.00 – 5 Main Wheel Tyre Size 15x6.0–6 see Note 9 22. (Reserved): N/A C.IV. Operating and Service Instructions 1. Flight Manual: Document No. 7.01.15 or 7.01.16 (MÄM 42-600 installed) TCDS No. EASA.A.005 DA 42 - Series Page 25 of 40 Issue 43, 29 March 2023 2. Technical Manual: Airplane Maintenance Manual (AMM) Document No. 7.02.15 (incl. Airworthiness Limitations) Service Information and Service Bulletins 3. Spare Parts Catalogue (IPC): Document No. 7.03.15 4. Instruments and aggregates: refer to AMM Doc. No. 7.02.15 Chapter 1 C.V. Operational Suitability Data (OSD) The Operational Suitability Data elements listed below are approved by the European Union Aviation Safety Agency under the EASA Type Certificate EASA.A.005 as per Commission Regulation (EU) 748/2012 as amended by Commission Regulation (EU) No 69/2014. 1. Master Minimum Equipment List (MMEL) The MMEL is defined in the Document No: 7.11.01, Revision Original or later approved revisions. C.VI. Notes: 1. This certification applies to serial numbers 42.339, 42.379, 42.N001 and subsequent for production at Diamond-Austria, 42.NC001 and subsequent for production at Diamond-Canada. 42.NW002 and subsequent for production in Wuhu/China, see Note 14. DA42 may be converted to Model DA 42 NG by DAI approved SB OSB 42- 068. 2. Approved Noise Levels in accordance to the EASA data sheet for noise TCDSN A.005. 3. For approved software versions of Gamin G1000 Integrated Avionic System see DAI MSB 42NG-003, at latest issue. Garmin Software PNo. 010-00670-01 or later approved version is required. 4. Approved engine model for installation in the DA 42 NG: E4-B with MÄM 42-600 installed : E4-C The approved firmware and mapping is according to DAI MSB 42NG-002 at latest issue. 5. Propeller Equipment: Governor P-877-16 6. Flights into known or forecast icing conditions is approved if the liquid fluid ice protection system in accordance to Major Design Change OÄM 42-160 is installed. 7. For additional approved Jet Fuel specifications see AFM Section 2. 8. 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. 9. Only specific brand names and types of tires are allowed for installation, see AMM and IPC 10. The Variable Elevator Stop is removed with OÄM 42-199 installed. TCDS No. EASA.A.005 DA 42 - Series Page 26 of 40 Issue 43, 29 March 2023 11. Operation with Diesel fuel is only approved if OÄM 42-251. 12. The following Design Mass Configurations are approved: Design Changes installed Standard MÄM 42- 659 MÄM 42-659 and MÄM 42-678 MÄM 42-659 and MÄM 42- 678 and OÄM 42-260 MTOM 1900 kg (4189 Ib) 1900 kg (4189 Ib) 1999 kg (4407 Ib) 2001 kg (4411 Ib) MZFM 1765 kg (3891 Ib) 1835 kg (4045 Ib) 1835 kg (4045 Ib) 1835 kg (4045 Ib) MLM 1805 kg (3979 Ib) 1900 kg (4189 Ib) 1999 kg (4407 Ib) 1999 kg (4407 Ib) MTOM – maximum take-off mass; MZFM – maximum zero fuel mass; MLM – maximum landing mass The retrofit installation of the design changes is only approved per TC Holder Service Bulletins. The Maximum Take Off Mass of 2001 kg (4411 lb) per OÄM 42-260 is intended only for cases where it is operationally more suitable to have a MTOM above 2000 kg. The forward Center of Gravity Limit at MTOM 2001 kg (4407 lb) is 2.434 m (95.83 in) aft of datum plane. 13. The commercial designation of the DA 42 NG with MÄM 42-600 installed is DA42-VI. 14. For serial number 42.NW002 and subsequent produced in Wuhu/China under Chinese Production Certificate PC0030A, EASA is considered state of design. Pending a bilateral agreement between the People’s Republic of China and the European Union (EU), this aircraft serial numbers are not eligible for registration in the EU. Spareparts with a Chinese Authorized Release Certificate are not eligible for EU registered aircraft.
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