TYPE-CERTIFICATE DATA SHEET EASA 005 DA 42

Flights into known or forecast icing conditions See Note 5 13. Maximum Weights: Take-off Zero Fuel Landing 1700 kg (3748 lb) 1785 kg (3935 Ib) MÄM 42-088 installed 1650 kg (3638 lb) 1674 kg (3690 Ib) OÄM 42-188 installed 1730 kg (3814 Ib) OÄM 42-188 & -195 installed 1700 kg (3748 lb) 1785 kg (3935 Ib) OÄM 42-195 installed For approved Weight Configurations see Note 6 TCDS No. EASA.A.005 DA 42 Page 7 of 30 Issue 22, 14 June 2013 14. Centre of GravityRange Forward limit Rear limit Up to 1468 kg 2.35 m behind Datum At 1785 kg 2.40 m behind Datum Varying linearly with mass in between At 1250 kg 2.42 m behind Datum At 1600 kg and above 2.49 m behind Datum Varying linearly with mass in between 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 10° up + 17º ± 5º nose down at elevator 10° up - 35º ± 5º left 27º ± 1º right 29º ± 1º trim RH at rudder 20° LH + 34º ± 5º trim LH at rudder 20° LH + 18º ± 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 22. (Reserved): N/A TCDS No. EASA.A.005 DA 42 Page 8 of 30 Issue 22, 14 June 2013 A.IV. Operating and Service Instructions 1. Flight Manual: Document No. 7.01.05 or7.01.06 (with OÄM 42- 102, GFC 700 Autopilot ) 2. Technical Manual: Airplane Maintenance Manual (AMM) Document No. 7.02.01(incl. Airworthiness Limitations) Service Information and Service Bulletins 3. Spare Parts Catalogue: Document No. 7.03.01 4. Instruments and aggregates:refer to AMM Doc. No. 7.02.01 Chapter 1 A.V. Notes: 1. This certification applies to serial numbers 42.004 and subsequent for production at Diamond-Austria, serial numbers 42.AC001 and subsequent for production at Diamond–Canada, excluding serial numbers 42L.001 and 42L.002. 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 42-008, at latest issue. If engine TAE 125-02-99 is installed (Design Change MÄM 42-198), than Garmin Software PNo. 010-00370-15 or later approved version is required. 4. Approved engine model for installation in the DA 42: TAE 125-01, 125-01- (017)-( ), TAE 125-02-99, 125-02-(0003)-( ). The approved firmware and mapping is according to DAI MSB 42-007 at latest issue. Installation of engine types in pairs only. The engine TAE 125-02-99 engine was previously approved as TAE 125-02. Engine retrofit installation from engine TAE 125-01 to TAE 125-02-99 is approved by Design Change MÄM 42-198 with OSB 42- 046. 5. Fights into known or forecast icing conditions is approved if the liquid fluid ice protection system in accordance to Major Design Change OÄM 42-054 is installed. 6. The following Design Mass Configurations are approved: Design Changes installed Standard MÄM 42-088 MÄM 42-088 and OÄM 42-188 MÄM 42-088 and OÄM 42-188 and OÄM 42-195 MTOM 1700 kg (3748 Ib) 1785 kg (3935 Ib) 1785 kg (3935 Ib) 1785 kg (3935 Ib) MZFM 1650 kg (3638 Ib) 1650 kg (3638 Ib) 1674 kg (3690 Ib) 1730 kg (3814 Ib) MLM 1700 kg (3748 Ib) 1700 kg (3748 Ib) 1700 kg (3748 Ib) 1785 kg (3935 Ib) MTOM – maximum take-off mass; MZFM – maximum zero fuel mass; MLM – maximum landing mass The retrofit installation of the design changes is approved per TC Holder Service Bulletins. TCDS No. EASA.A.005 DA 42 Page 9 of 30 Issue 22, 14 June 2013 7. The use of Diesel fuel (EN 590) is approved if Major Design Change MÄM 42- 037 is installed. 8. For additional approved Jet Fuel specifications see AFM Section 2. TCDS No. EASA.A.005 DA 42 Page 10 of 30 Issue 22, 14 June 2013 SECTION B: DA 42 M B.I. General 1. Data Sheet No.: EASA.A.005 2. a) Type: b) Model: c) Variant: DA 42 DA 42 M -- 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 6. Certification Application Date: 01-Jun-2006 7. (Reserved) N/A 8. (Reserved) N/A B.II. EASA Certification Basis 1. Reference Date for determining the applicable requirements: 02-Apr-2002 2. Airworthiness Requirements: JAR-23, Amendment 1, issued 01 February 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-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 ofLightning Strikes, Indirect Effects CRI F-07 Human Factors in Integrated Avionic TCDS No. EASA.A.005 DA 42 Page 11 of 30 Issue 22, 14 June 2013 System 3. Exemptions: None 4. Deviations: None 5. Equivalent Safety Findings: CRI D-01 Single Lever Power Control CRI E-04 Liquid Cooling – Coolant Tank CRI E-05 Electronically-controlled Reciprocating Diesel Engine CRI E-08 Fuel System – Hot Fuel Temperature CRI F-04 Power plant Instruments CRI B-03 Stall Speed in Icing Conditions 6. Requirements elected to comply: None 7. Environmental Standards: ICAO, Annex 16, Volume 1, Third Edition, 1993, Amdt. 7 JAR 36, issued 23-May-1997 CRI A-03 for additional national requirements See Note 2 8. (Reserved) N/A 9. (Reserved) N/A B.III. Technical Characteristics and Operational Limitations 1. Type Design Definition: Current issue of Doc. No. 7.07.00, Chapter 7including Design Changes MÄM 42-001 to 42-012 and following 2. Description: Twin engine, four-seated cantilever low wing airplane, composite construction, retractable tricycle landing gear, T-tail The airplane is equipped with provisions for installation of various mission options. 3. Equipment: Equipment list, AFM, Doc. No. 7.01.05, Section 6, and and AFM Supplement M00 See Note 7 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 Thielert TAE 125-02-99 5.1.2 Type Certificate: EASA Engine Type Certificate Data Sheet E.055 TCDS No. EASA.A.005 DA 42 Page 12 of 30 Issue 22, 14 June 2013 5.1.3 Limitations: Max take-off rotational speed 2300 r.p.m. Max continuous rotational speed 2300 r.p.m (Propeller shaft r.p.m) For power-plants limits refer to AFM, Doc. No. 7.01.05 or Doc. No. 7.01.06, Section 2 5.1.4Firmware: see DAI MSB 42-007 See Note 3 5.1.5Mapping: see DAI MSB 42-007 See Note 3 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-A-C-F/CF187-129 7.2 Type Certificate: EASA Prop. Type Certificate Data Sheet P.094 7.3 Number of blades: 3 7.4 Diameter: 1870 mm 7.5 Sense of Rotation: CW 7.6 Settings: Low pitch setting: 12 ° Feather position: 81 ° Start Lock: 15° 8. Fluids: 8.1 Fuel: Jet A-1 (ASTM 1655) see Note 6 Diesel (EN 590) see Note 5 8.2 Oil: Engine: Gearbox: Shell Helix Ultra 5W30 synthetic API SJ/CF or see AFM, Doc. No. 7.01.05, Section 2 Shell EP 75W90 API GL-4 or see AFM, Doc. No. 7.01.05, Section 2 8.3 Coolant: Water / Cooler Protection for more details see AFM, 7.01.05, Section 2 8.4 Ice Protection Fluids: AL-5 (DTD 406B) or Aeroshell Compound 07 for more details see AFM, 7.01.05, 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 TCDS No. EASA.A.005 DA 42 Page 13 of 30 Issue 22, 14 June 2013 9.2 Oil: each engine Maximum: 6.0 liters 6.3 qts Minimum: 4.5 liters 4.8 qts 9.3 Coolant system capacity: Approx. 7 liters 10. Air Speeds: Design Manoeuvring Speed v A up to 1542 kg 119 KEAS above 1542 kg 125 KEAS Flap Extended Speed v FE Approach 135 KEAS Landing 110 KEAS Maximum Landing Gear Operation Speed v LO 155 KEAS Maximum Landing Gear Extended Speed v LE 192 KEAS Minimum Control Speed v MC 68 KEAS Maximum structural cruising speed vNO (= Maximum structural design speed vC) 155 KEAS Never exceed speed v NE 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 4 13. Maximum Weights: Take-off Zero Fuel Landing 1785 kg (3935 Ib) 1650 kg (3638 lb) 1674 kg (3690 Ib) OÄM 42-188 installed 1730 kg (3814 Ib) OÄM 42-188 & -195 installed 1700 kg (3748 lb) 1785 kg (3935 Ib) OÄM 42-195 installed For approved Weight Configurations see Note 8 14. Centre of Gravity Range: Forward limit Up to 1468 kg 2.35 m behind Datum At 1785 kg 2.40 m behind Datum Varying linearly with mass in between Rear limit At 1250 kg 2.42 m behind Datum At 1600 kg and above 2.49 m behind Datum Varying linearly with mass in between TCDS No. EASA.A.005 DA 42 Page 14 of 30 Issue 22, 14 June 2013 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 railing edge up 15.5º ± 0.5º trailing edge down 13º ± 1º nose up at elevator 10° up + 17º ± 5º nose down at elevator 10° up - 35º ± 5º left 27º ± 1º right 29º ± 1º trim RH at rudder 20° LH + 34º ± 5º trim LH at rudder 20° LH + 18º ± 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 22. (Reserved): N/A B.IV. Operating and Service Instructions 1. Flight Manual: Document No. 7.01.05 or7.01.06 (with OÄM 42-102, GFC 700 Autopilot), including AFM Supplement M00 2. Technical Manual: Airplane Maintenance Manual (AMM) Document No. 7.02.01(incl. Airworthiness Limitations) Service Information and Service Bulletins 3. Spare Parts Catalogue: Document No. 7.03.01 TCDS No. EASA.A.005 DA 42 Page 15 of 30 Issue 22, 14 June 2013 4. Instruments and aggregates:refer to AMM Doc. No. 7.02.01 Chapter 1 B.V. Notes: 1. This certification applies to serial numbers 42.005, 42.008, 42.157, 42.177, 42.191, 42.234, 42.247, 42.255, 42.262, 42.272, 42.282, 42.286, 42.293, 42.304, 42.319, 42.328 and serial number 42.M001 and subsequent . All of these serial numbers initially delivered as a DA42 must be modified with Optional Service Bulletin OSB42-056 to comply with the DA42M type design. 2. For approved software versions of Gamin G1000 Integrated Avionic System see DAI MSB 42-008, at latest issue. Garmin Software PNo. 010-00370-15 or later approved version is required. 3. Approved engine model for installation in the DA 42 M: TAE 125-02-99 125-02-(0003)-( ) The approved firmware and mapping is according to DAI MSB 42-007 at latest issue. 4. Fights into known or forecast icing conditions is approved if the liquid fluid ice protection system in accordance to Major Design Change OÄM 42-054 is installed. 5. The use of Diesel fuel (EN 590) is approved if Major Design Change MÄM 42- 037 is installed. 6. For additional approved Jet Fuel specifications see AFM Section 2. 7. The basic DA42 M does not include provisions for specific mission purposes.The specific type design for mission equipment and its installations are not part of the DA42 M certification; this is approved only in accordance to EASA TCDS A.513 8. The following Design Mass Configurations are approved: Design Changes installed Standard MÄM 42-088 and OÄM 42-188 MÄM 42-088 and OÄM 42-188 and OÄM 42-195 MTOM 1785 kg (3935 Ib) 1785 kg (3935 Ib) 1785 kg (3935 Ib) MZFM 1650 kg (3638 Ib) 1674 kg (3690 Ib) 1730 kg (3814 Ib) MLM 1700 kg (3748 Ib) 1700 kg (3748 Ib) 1785 kg (3935 Ib) MTOM – maximum take-off mass; MZFM – maximum zero fuel mass; MLM – maximum landing mass The retrofit installation of the design changes is approved per TC Holder Service Bulletins. TCDS No. EASA.A.005 DA 42 Page 16 of 30 Issue 22, 14 June 2013 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 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 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 TCDS No. EASA.A.005 DA 42 Page 17 of 30 Issue 22, 14 June 2013 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 ofLightning 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 Manoeuvring Speed 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 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: TCDS No. EASA.A.005 DA 42 Page 18 of 30 Issue 22, 14 June 2013 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 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 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 TCDS No. EASA.A.005 DA 42 Page 19 of 30 Issue 22, 14 June 2013 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 9. Air Speeds: Design Manoeuvring Speed v A up to 1700 kg 114 KEAS 1701 to 1800 kg 121 KEAS above 1800 kg 125 KEAS Flap Extended Speed v FE Approach 135 KEAS Landing 110 KEAS Maximum Landing Gear Operation Speed v LO 155 KEAS Maximum Landing Gear Extended Speed v LE 192 KEAS Minimum Control Speed Airborne v MCA 75 KEAS MÄM 42-600 70 KEAS Maximum structural cruising speed vNO (= Maximum structural design speed vC) 155 KEAS Never exceed speed v NE 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 1900 kg (4189 lb) 1765 kg (3891 lb) 1805 kg (3979 lb) TCDS No. EASA.A.005 DA 42 Page 20 of 30 Issue 22, 14 June 2013 14. Centre of Gravity Range: Forward limit At 1510 kg 2.357 m behind Datum At 1900 kg 2.418 m behind Datum Varying linearly with mass in between Rear limit At 1510 kg 2.460 m behind Datum At 1700 kg and above 2.48 m behind Datum 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) For all weights 2.460 m behind Datum 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 10° up + 17º ± 5º nose down at elevator 10° up - 35º ± 5º left 27º ± 1º right 29º ± 1º trim RH at rudder 20° LH + 54º ± 5º trim LH at rudder 20° LH + 22º ± 5º trim RH at rudder 20° LH (MÄM 42-600) + 35º ± 5º trim LH at rudder 20° LH (MÄM 42-600) + 36º ± 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) TCDS No. EASA.A.005 DA 42 Page 21 of 30 Issue 22, 14 June 2013 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 5. Flight Manual: Document No. 7.01.15 or 7.01.16 (MÄM 42-600 installed) 6. Technical Manual: Airplane Maintenance Manual (AMM) Document No. 7.02.15 (incl. Airworthiness Limitations) Service Information and Service Bulletins 7. Spare Parts Catalogue (IPC): Document No. 7.03.15 8. Instruments and aggregates:refer to AMM Doc. No. 7.02.15 Chapter 1 C.V. 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. 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. Fights 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 Page 22 of 30 Issue 22, 14 June 2013 SECTION D: DA 42 M-NG D.I. General 1. Data Sheet No.: EASA.A.005 2. a) Type: b) Model: c) Variant: DA 42 DA 42 M-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 6. Certification Application Date: 12-Nov-2008 7. (Reserved) N/A 8. (Reserved) N/A D.II. EASA Certification Basis 1. Reference Date for determining the applicable requirements: 02-Apr-2002 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 TCDS No. EASA.A.005 DA 42 Page 23 of 30 Issue 22, 14 June 2013 CRI F-03 Protection from the Effects ofLightning 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 Manoeuvring Speed 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 D.III. Technical Characteristics and Operational Limitations 1. Type Design Definition: Current issue of Doc. No. 7.07.00, Chapter V005/7including Design Changes VÄM 42-004 and VÄM 42-005 2. Description: Twin engine, four-seated cantilever low wing airplane, composite construction, retractable tricycle landing gear, T-tail The airplane is equipped with provisions for installation of various mission options. 3. Equipment: Equipment list, AFM, Doc. No. 7.01.15, Section 6,and AFM Supplement M00 See Notes 3 and 7 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: TCDS No. EASA.A.005 DA 42 Page 24 of 30 Issue 22, 14 June 2013 5.1.1 Model: 2 AustroengineE4 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) Max T/O Power (5min) 100%(123,5 kW) Max. continuous Power 92% (114 kW) For power-plants limits refer to AFM, Doc. No. 7.01.15, 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 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 7.5 Sense of Rotation: CW 7.6 Settings: Low pitch setting: 12 ° Feather position: 81 ° Start Lock: 15° 8. Fluids: 8.1 Fuel: Jet A-1 (ASTM 1655), see note 8 8.2 Oil: Engine: Gearbox: Shell Helix Ultra 5W30 or 5W40 or see AFM, Doc. No. 7.01.15, Section 2 Shell SPIRAX GSX 75W-80 or see AFM, Doc. No. 7.01.15, Section 2 8.3 Coolant: Water / Cooler Protection for more details see AFM, 7.01.15, Section 2 8.4 Ice Protection Fluids: AL-5 (DTD 406B) or Aeroshell Compound 07 for more details see AFM, 7.01.15, Suppl. S03 9. Fluid capacities: TCDS No. EASA.A.005 DA 42 Page 25 of 30 Issue 22, 14 June 2013 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 v A up to 1700 kg 114 KEAS 1701 to 1800 kg 121 KEAS above 1800 kg 125 KEAS Flap Extended Speed v FE Approach 135 KEAS Landing 110 KEAS Maximum Landing Gear Operation Speed v LO 155 KEAS Maximum Landing Gear Extended Speed v LE 192 KEAS Minimum Control Speed Airborne v MCA 75 KEAS Maximum structural cruising speed vNO (= Maximum structural design speed vC) 155 KEAS Never exceed speed v NE 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 1900 kg (4189 lb) 1765 kg (3891 lb) 1805 kg (3979 lb) TCDS No. EASA.A.005 DA 42 Page 26 of 30 Issue 22, 14 June 2013 14. Centre of Gravity Range: Forward limit At 1510 kg 2.357 m behind Datum At 1900 kg 2.418 m behind Datum Varying linearly with mass in between Rear limit At 1510 kg 2.460 m behind Datum At 1700 kg and above 2.480 m behind Datum Varying linearly with mass in between If OÄM 42-199 is installed (see note 9): For all weights 2.450 m behind Datum 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 railing edge up 15.5º ± 0.5º trailing edge down 13º ± 1º nose up at elevator 10° up + 17º ± 5º nose down at elevator 10° up - 35º ± 5º left 27º ± 1º right 29º ± 1º trim RH at rudder 20° LH + 54º ± 5º trim LH at rudder 20° LH + 22º ± 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 22. (Reserved): N/A TCDS No. EASA.A.005 DA 42 Page 27 of 30 Issue 22, 14 June 2013 D.IV. Operating and Service Instructions 1. Flight Manual: Document No. 7.01.15 including AFM Supplement M00 2. Technical Manual: Airplane Maintenance Manual (AMM) Document No. 7.02.15 (incl. Airworthiness Limitations)including Supplement M00, Service Information and Service Bulletins 3. Spare Parts Catalogue: Document No. 7.03.15 4. Instruments and aggregates:refer to AMM Doc. No. 7.02.15 Chapter 1 D.V. Notes: 1. This certification applies to serial numbers 42.339, 42.MN001 and subsequent for production at Diamond-Austria. DA 42 M may be converted to Model DA 42 M-NG by DAI approved SB OSB 42-081. 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 The approved firmware and mapping is according to DAI MSB 42NG-002 at latest issue. 5. Propeller Equipment : Governor: P-877-16 6. Fights 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. The basic DA42 M-NG does not include provisions for specific mission purposes. The specific type design for mission equipment and its installations are not part of the DA42 M-NG certification; this is approved only in accordance to EASA TCDS A.513 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 TCDS No. EASA.A.005 DA 42 Page 28 of 30 Issue 22, 14 June 2013  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 8. For additional approved Jet Fuel specifications see AFM Section 2. 9. The Variable Elevator Stop is removed with OÄM 42-199 installed. TCDS No. EASA.A.005 DA 42 Page 29 of 30 Issue 22, 14 June 2013 ADMINISTRATIVE SECTION I. Acronyms N/A II. Type Certificate Holder Record Diamond Aircraft Industries GmbH N.A. Otto-Str. 5 A-2700 Wiener Neustadt Austria III. Change Record Issue Date Changes TC Issue No.& Date Issue 1 13-May-2004 Initial Issue 13-May-2004 Issue 2 17-Dec-2004 Changed to reflect IFR certification - Issue 3 29-Sep-2005 Page 1: Issue 3 added Page1, List of effective pages: page “9” added Page 2: Section 3 added Page 3, Section 1, I: Issue to 3 changed Page 3. Section 1, II: Exemption deleted not applicable in EASA Page 4, Section 1, II.9: CRI E-04 added Page 4, Section 1, III.5.1: reference changed from SI 42-002 to MSB 42-007 Page 4, Section 1, III.5.2: reference changed from SI 42-003 to MSB 42-008 Page 5, Section 1, III.8.3: “Distilled Water” changed to “Water” Page 7, Section 1, V.3: reference changed from SI 42-002 to MSB 42-007 Page 7, Section 1, V.4: reference changed from SI 42-003 to MSB 42-008 Page 9, Section 3: Section 3 added completely - Issue 4 16-Dec-2005 OÄM 42-056 Auxiliary fuel tank OÄM 42-054 Flights into known icing conditions MÄM 42-037 Diesel Fuel Operation MÄM 42-088 Take off mass 1785 kg Page 3, Section 1, II.7 : add CRI E-03 Page 4, Section 1, II.9 : add CRI B-03 Page 5, Section 1, III.8 : add 8.1 Diesel (EN 590) and 8.4 Ice protection fluid Page 5, Section 1, III.9.1 : add Auxiliary fuel tank Page 5, Section 1, III.10 : add and change design manoeuvring speed Page 5, Section 1, III.12 : add known icing Page 5, Section 1, III.13 : add 1785 kg Page 5, Section 1, III.14: change cg range up to 1785 kg Page 7, Section 1, V: add Notes 5,6,7, noise level in note 2 Page 7, Section 1, V: add in Notes 1, excluding Sno. 42L.001 and 42L.002 - Issue 5 24-April-2006 Canadian Production Fuel Changes from Engine Certification Misprint correction of VLO Page 3, Section 1, I.4: add Diamond CanadaPage 4, Section 1, III.5: change JAA TCDS in EASA TCDS Page 5, Section 1, III.10: VLO corrected misprint since initial version - TCDS No. EASA.A.005 DA 42 Page 30 of 30 Issue 22, 14 June 2013 Page 7. Section 1, V.8: add approved jet fuel variants Issue 6 21-Dec-2006 MÄM 42-198 Engine TAE 125-02 Page 4, Section 1, III.5 : add TAE 125-02 Page 7. Section 1, V.2 : add noise level for TAE 125-02 Page 7. Section 1, V.3 : add minimum Garmin software version for TAE 125-02 Page 7. Section 1, V.4 : add engine model for TAE 125-02 Page 7. Section 1, V.9 : add note 9 retrofit for TAE 125-02 - Issue 7 11-Jun-2007 Engine TAE 125-02 renamed TAE 125-02-99 Page 4, Section 1, III.5 Page 7. Section 1, V.2 Page 7. Section 1, V.3 Page 7. Section 1, V.4 Page 7. Section 1, V.9 - Issue 8 14-Dec-2007 DA 42 M Model Page 7, Section 1, A.V. 9: OSB 42-033 changed to OSB 42-046 14-Dec-2007 Issue 9 02-Apr-2008 OÄM 42-102 Autopilot Garmin GFC 700 Page 6. Section 1, AIV AFM Page 11.Section 2, BIV AFM - Issue 10 09-Mar-2009 VÄM 42-004 Model DA 42 NG, P-EASA.A.C.09012 Section 3 complete new 09-Mar-2009 Issue 11 09-Jun-2009 VÄM 42-005 Model DA 42 M-NG, P-EASA.A.C.11271 Section 4 complete new OÄM 42-160 “Flights into Known Icing for DA42 NG” Page 15, Section 3,C.III.12, All weather capability Page 17, Section 3,CV.6, Note 09-Jun-2009 Issue 12 09-Jul-2009 OÄM 42-175 Fuel TS-1; P-EASA.A.C.12574 BV Note 6 and AV Note 8 - Issue 13 17-Mar-2010 Administrative Changes Coverpage Page Change Record has been removed no longer required D.V. Note 1 Conversion SB added - Issue 14 16-Jul-2010 OÄM 42-188 Increase of the maximum Zero Fuel Weight , EASA Project Nr. 0010004589-001 including OÄM 42-195 maximum Landing mass 1785 kg AIII.13 weights changed AV. Note 6 changed BIII.13 weights changed BV. Note 8 added Format modified to standard EASA TCDS format. - Issue 15 13-Dec-2010 Inclusion of Production in Canada for Model DA 42 NG TS-1 fuelsformodels DA 42 NG, DA 42 M-NG Editorial Changes - Issue 16 26-April-2011 Section C.V, Note 7; D.V, Note 8: Additional Fuel Grades added, EASA Project No. 0010010748-001 - Issue 17 15-Sep-2011 Section A.V, Note 8; B.V, Note 6; C.V, Note 7; D.V, Note 8: General Ref. to AFM - Issue 18 12-April-2012 MÄM 42-600 Performance Enhancement ,EASA Project Number 0010015152 Section C.III. 16, 9,7,5; Section C.IV.5.AFM New; Section C.V. Note 4, Note 8,9 added Editorial changes Issue 19 06- December- 2012 Editorial Changes CRI F-05 deleted in accordance to CRI A-01 Issue 20 18-Dec-2012 Section C and D: OÄM 42-199 Removal of Variable Elevator Stop – aft CG Limits EASA Project No. 0010007850-001 Issue 21 06-Feb-2013 Conversion error corrected Section D.V, Note 1: S/N 42.339 included Issue 22 14-June-2013 Section D.V. Note 7 OÄM 42-240,-241,-228b Nose and Belly Container on Standard TC EASA Project 0010021849