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Diamond DA42 TDI

Aircraft Specs & Performance


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Aircraft Specs
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General Info
Category Multi Engine Piston
Seating
Crew + Typical Seating / Maximum Seating. For example, 2 + 6 / 9 indicates that the aircraft requires two pilots, there are six seats in the typical cabin configuration and the aircraft is certified for up to 9 passenger seats.

A six place single or multi-engine is shown as 1 + 5 / 5 indicating that one pilot is required and there are five other seats available for passengers in a normal cabin configuration.

See Guide To Specs for more info.
1 + 3 / 3
Top Speed
The top speed as determined by the manufacturer under optimal conditions and flown by an expert test pilot.

This speed will vary from aircraft to aircraft based on equipment, flight conditions and pilot abilities.
168 kts
Max Range
Max Range as indicated by the manufacturer under optimal conditions.

See Cruise & Mission performance for examples of range capabilities.
925 NM
URL www.diamondaircraft.com
Weights & Dimensions
Weights:
Basic Operating Weight
Empty Weight (EW) is shown for Piston powered airplanes.

Basic Operating Weight (BOW) is shown for turbine powered airplanes. BOW is the empty weight of the aircraft, plus 200 lbs for each required crewmember. This does not include unusable fuel and oil.

BOW is based on the average EW for current production aircraft and is interpolated as accurate as possible for out of production aircraft. For Ultra Long Range aircraft, Crew = 3 pilots and 1 cabin attendant.

Please see the Guide To Specifications for more detail.
2,400 lbs 1,088.62 kg
Max Payload
Jet & Turboprop Aircraft - Zero fuel weight minus Basic Operating Weight (BOW).

For piston engine airplanes, weight shown here is calculated by subtracting 200 pounds from the Useful Load for the pilot and supplies. (Useful Load minus Pilot @ 200 lbs = Max Payload).
918 lbs 416.40 kg
Passenger Payload
Based on 180 pounds per occupant for Piston aircraft and 200 pounds per occupant for turbine engine airplanes.

If the passenger payload exceeds the maximum payload, we use the maximum payload weight.

Pilots and crew are not counted as occupants.
540 lbs 244.94 kg
Useful Load 1,118 lbs 507.12 kg
Avail. Payload/Max Fuel
The maximum ramp weight minus the tanks full weight, (not to exceed zero fuel weight) minus Basic Operating Weight.

For light aircraft, it is the Max Payload minus the full fuel weight.
606 lbs 274.88 kg
Avail. Fuel/Max Payload
Jet & Turboprop Aircraft - Maximum Ramp Weight minus Basic Operating Weight, not to exceed Zero Fuel Weight or maximum fuel capacity.
52.00 gal / 312 lbs 196.84 L / 141.52 kg
Max Fuel 52.00 gal / 312 lbs 196.84 L / 141.52 kg
Usable Fuel 50.00 gal / 300 lbs 189.27 L / 136.08 kg
Wing Loading
Is computed using the Max Takeoff Weight (MTOW) divided by the total wing area.
20.52 lbs / ft2 30.54 kg / m2
Power Loading
Power Loading is calculated using the Max Takeoff Weight (MTOW) divided by total rated thrust / horsepower.
13.80 lbs / hp 6.26 kg / hp
Max Ramp Weight
The maximum allowable weight of the aircraft to be considered airworthy including fuel required for taxi.

Max ramp, takeoff and landing weights may be the same for light aircraft that only have a certificated max takeoff weight.
3,935 lbs 1,784.89 kg
Max Takeoff Weight
(MTOW) The maximum weight that the aircraft has shown to meet all airworthiness requirements. MTOW is fixed and does not vary with altitude or air temperature.

Max ramp, takeoff and landing weights may be the same for light aircraft that on may only have a certificated max takeoff weight.
3,935 lbs 1,784.89 kg
Max Landing Weight
Max Landing Weight is determined by structural limits and is the maximum weight for an aircraft to land.

Max ramp, takeoff and landing weights may be the same for light aircraft that on may only have a certificated max takeoff weight.
3,748 lbs 1,700.06 kg
Max Zero Fuel Weight
(ZFW) The maximum total weight of the aircraft less the weight of fuel required to fly 1.5 hours at high-speed cruise for turbine powered aircraft.
3,638 lbs 1,650.17 kg
External Dimensions
External length, height and span dimensions are provided for use in determining hangar and or tie-down space requirements.
Length 28 ft 1 in 8.56 m
Height 8 ft 2 in 2.49 m
Wingspan 44 ft 0 in 13.41 m
Wing Area 175.30 ft2 53.43 m2
Baggage Capacity
Interior Weight 100 lbs 45.36 kg
Exterior Weight 66 lbs 29.94 kg
Propeller Info
Manufacturer MT
Model V-6-A
Pitch Constant Speed
Diameter 74.00 in 1.88 m
Number of Blades 3

Performance Specs
Speeds
Top Speed
The top speed as determined by the manufacturer under optimal conditions and flown by an expert test pilot.

This speed will vary from aircraft to aircraft based on equipment, flight conditions and pilot abilities.
168 kts
Cruise Speed
Crusie Speed as determined by the manufacturer under optimal conditions and flown by an expert test pilot.

This speed will vary from aircraft to aircraft based on equipment, flight conditions and pilot abilities.
151 kts
Max Range
Max Range as indicated by the manufacturer under optimal conditions.

See Cruise & Mission performance for examples of range capabilities.
925 NM
V Speeds:
Speed Vso 56 kts
Speed Vs 62 kts
Speed Vx 76 kts
Speed Vy 76 kts
Speed Vyse 82 kts
Speed Vsse 83 kts
Speed Vmca 68 kts
Speed Va 126 kts
Speed Vno 155 kts
Speed Vne 197 kts
Takeoff Distances
Is the shortest ground distance, measured in feet, for an aircraft to accelerate and liftoff. Where applicable, takeoff distance is computed for airplanes to clear a 50' obstruction.

Aviation regulations, (for large aircraft) require the takeoff distance to be less than, or equal to the available runway length, both with and without an engine failure assumed.
Sea Level, ISA 1,739 ft 530.05 m
5000 ft elev 25'C 3,450 ft 1,051.56 m
Landing Distances
Is the shortest distance an aircraft can descend, land and come to a complete stop. Where applicable, landing distance is computed for airplanes to clear a 50' obstruction. For larger aircraft, a mid-weight mission is used for computation.
Sea Level, ISA 2,267 ft 690.98 m
5000 ft elev 25'C 2,900 ft 883.92 m
Climb Performance / Ceilings
Climb 1,280 fpm 390.14 mpm
Min. To Altitude
Provides an indication of overall climb performance, especially if the aircraft has an all-engine service ceiling well above sample top-of-climb altitudes shown here and in the cruise section of performance specs. The all-engine time to climb to a specific altitude is shown, based on type of aircraft, departing at Max Total Operating Weight (MTOW) from a sea level, standard day airport.

We provide the all engine time to climb to specific altitudes based on the type of aircraft.

10,000 feet for normally aspirated (non turbocharged) single and multi engine piston aircraft, pressurized single engine piston and non pressurized turboprop; 25,000 feet for pressurized single and multiengine turboprops; 37,000 feet for turbofan powered aircraft.

The data is published as time-to-climb in minutes to the designated altitude. Exp: If it takes 9 minutes to climb to 10,000 feet, it will be shown as 9 / 10,000.
13 min / 10,000 ft 13 min / 3,048.00 m
Engine Out Rate
The One Engine Inoperative (OEI) rate of climb for multi-engine aircraft at Max Takeoff Weight (MTOW). OEI is derived from the Airplane Flight Manuel and is based on landing gear retracted and wing flaps in the takeoff configuration used to compute the published takeoff distance.
500 fpm 152.40 mpm
Certified Ceiling
Maximum allowable operating altitude determined by airworthiness authorities.
18,000 ft 5,486.40 m
Ceiling All Engines
Maximum altitude at which at least 100-fpm rate of climb can be attained, assuming the aircraft departed a sea-level, standard-day airport at Max Total Operating Weight (MTOW) and climbed directly to altitude.
18,000 ft 5,486.40 m
Ceiling w/Engine Out
Maximum altitude at which a 50-fpm rate of climb can be attained, assuming the aircraft departed a sea-level, standard-day airport at Max Total Operating Weight (MTOW) and climbed directly to altitude.
10,000 ft 3,048.00 m
Cruise Performance at 8,000 ft
Recommended
Speed / Power 148 kts / 60 %
Fuel Flow 8.00 gal / 48 lbs 30.28 L / 21.77 kg
Range 880 NM
Altitude 8,000 ft 2,438.40 m
Payload / Fuel
560 lbs / 254.01 kg / 0.00 lb/gal 0.00 kg/L
High Speed
Speed / Power 162 kts / 75 %
Fuel Flow 12.20 gal / 73 lbs 46.18 L / 33.20 kg
Range 790 NM
Altitude 8,000 ft 2,438.40 m
Payload / Fuel
560 lbs / 254.01 kg / 0.00 lb/gal 0.00 kg/L

ClassG and MyWings are registered
service marks of ClassG, LLC.