DA-2000

• - 36,700 Lb
• - 36,500 Lb
• - 33,000 Lb
• - 28,660 Lb
• - Refer to Center of gravity limits chart

1,600 Lb / 61.4 lb/sq.ft

5,990 Lb

81.9 lb/sq.ft

198 KIAS

Full application of rudder or aileron controls, as well as maneuvers that involve angles-of-attack near the stall must be confined to speeds below VA. Rapidly alternating large rudder applications in combination with large sideslip angles may result in structural failure at any speed.

VFE Slats extended + flaps 10° .............200 KIAS - VFE Slats extended + flaps 20° ......................160 KIAS - VFE Slats extended + flaps 40° ......................160 KIAS

20,000 ft

• 190 KIAS
• MI 0.70

• 245 KIAD
• MI 0.75

90 KIAS

90 KIAS

98 KIAS

215 KIAS

215 KIAS

195 KIAS

• - Flaps up ..........................+2.64 to -1.00
• - Flaps down......................+2.00 to 0.00

198 KIAS

-1,000 ft / +10,000 ft

±2.0 %

10 kt

47,000 ft

• - Maximum differential pressure.............................9.3 psi
• - Maximum negative differential pressure.............-0.3 psi

• The autopilot is certified to the minimum height as follows:
• - Coupled ILS approach:
• - Radioaltimeter operative.................70 ft
• - Radioaltimeter inoperative............160 ft
• - Cruise.........................................1,000 ft
• - Non precision approach................250 ft

• Maximum engine generator output in flight:
• - Stabilized ...................................400 A
• - Transient (5 sec.)........................800 A
• - Transient (40 sec.)......................600 A
• - Transient (160 sec.)....................500 A
• Maximum engine generator output on ground:
• - Basic generators.... .....................300 A

• - Amber light (WARM) at or above.......120 °F
• - Red light (HOT) at or above................160 °F

260 KIAS or MI 0.76

20,000 ft

Above 20,000 ft, do not establish or maintain a configuration with the flaps or the slats extended

• - JET A
• - JET A-1 - Type JP-8
• - JP B
• - JP-4
• - JP-5

In flight, tank fuel temperature must be maintained at least 3 °C above the freezing point of fuel being used.

2,200 lb

50 psi / 3.5 bars

The Fuel Quantity Management Computer (FQMC) must be operative for take-off.

• - LH wing + half center wing box........906 Lb
•                                                               6,070 Gal
• - RH wing + half center wing box........908 Lb
•                                                               6,085 Gal
• - Airplane total capacity........................1,814 Lb 
•                                                               12,155 Gal

AIR 3520 or MIL-H-5606

Brake kinetic energy limit.................15,000 kJ per brake

The wing anti-ice should not be used with a Total Air Temperature (TAT) above 10 °C (50 °F).

between 78°15’ North and 78°15’ South latitude.

If the APPR or GPS APPR annunciation in the PFD is not green 2 NM before the FAF.

above 14,500 ft ± 500 ft

35,000 ft

35,000 ft

110 %

974 °C

746 °C

• Transient:
• - 40 seconds ...................................450 A
• - 180 seconds .................................375 A
• Stabilized:
• - 0 to 10,000 ft................................300 A
• - 10,000 to 25,000 ft........................250 A
• - 25,000 to 35,000 ft........................200 A

• - Take-off............................................ 5,888 lb
• - Maximum continuous ...................... 5,613 lb

• - Maximum Take-off............N1: 96.7 %  N2: 106%
• - Maximum continuous........N1: 96.7 %  N2: 104.9%

• - N1 .............................1.0 in./sec.
• - N2 ..............................1.5 in./sec.

• - Ground start.................................815 °C
•  -Airstart.........................................890 °C
•  -Restart max. temperature.............150 °C

• - Max. take-off (APR).......890 °C (5 minutes max.)
• - Normal take-off .............864 °C (5 minutes max.)
• - Max. continuous.............861 °C

• 970 °C........10 seconds max.
• 1,000 °C.......2 seconds max.

• Ground start:
• - start to light-off.....10 seconds max. after reaching 22 % N2
• - light-off to idle......60 seconds max.

• - Assisted...................90 seconds
• - Windmilling...........180 seconds

Starter cutout N2: 53.6 %

• - Operating range.........................................60 to 85 psi
• - Transient (3 min. max.)............................85 to 100 psi
• - Minimum (at IDLE)............................................30 psi
• - Cold start: oil T° < 0 °C (2.5 min. max.)...........135 psi

• - Maximum..........................................138 °C
• - Minimum for take-off..........................30 °C
• - Transient: for 3 min................138 to 155 °C
• - Cold start...........................................- 40 °C

- 280 KIAS max / MI 0.76 max

- Decrease altitude to increase buffet boundary margin.

• With the autopilot disengaged:
• - Fly attitude,
• - Avoid using the stabilizer trim,
• - Do not chase altitude and speed.

climb or cruise when the TAT is below -40 °C (-40 °F).

• more than 25 % of the surface is covered by either:
• - 3 mm (0.12 in) of standing water, or
• - Slush or loose snow, equivalent to more than 3 mm of water
• - Compacted snow, any depth, or - Ice, any depth.

• - Slats-flaps must be in 20° position.
• - If runway contaminated by ice: both reversers must be operative.

• - Landing gear retraction ................Delayed 15 seconds
• - IAS < 190 KIAS)........................ Recycle landing gear

• - Landing gear...............................Down
• - PARK BRAKE..............Pull to second detent for 5 seconds  Several times

• After V1:
• - Check maximum take-off thrust
• - At VR: Perform normal rotation at 3°/sec (maximum 20° pitch angle)
• - Keep take-off configuration, do not retract landing gear, - Fly at stall onset (top of red tape on airspeed indicator)  
• - PNF monitors radio-altimeter and announces readings -  - Attempt to fly a positive radio-altimeter trend,
• - Allow pitch to increase up to 30° (airspeed / stall onset permitting),
• - When exiting windshear, resume normal operation.

• - Disconnect autopilot
• - Level wings
• - Fly pitch angle up to stall onset.
• - Set maximum take-off thrust
• - Retract AIRBRAKES
• - Retract SLATS + FLAPS to 20°.
• At pilot's discretion (considering radio altimeter trend)
• - Retract landing gear.

• - Maximum pitch........................20°
• - Speed........................................At or above V2 + 10 kt

• - Take-off with slats/flaps 20°
• - Rotate at 3° per second,
• - Increase the pitch angle up to 20° maximum
• - V2+10.
• - The take-off thrust is maintained up to 1,500 ft AAL, then the thrust is reduced to the MAX CLIMB thrust.