Hawker Beechcraft Hawker 800XP, Руководство по эксплуатации для пилотов, Страница: 667 / 923

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Section IV Sub-section 6
SINGLE ENGINE
P/N 140-590032-0007
Revision A4: Sep, 2010
Pilot’s Operating Manual
SINGLE ENGINE CRUISE
This Sub-section contains data tables for (SINGLE ENGINE LONG RANGE CRUISE).
If an engine fails, the cruise altitude is reduced, with a subsequent reduction in air miles per lb. To
minimize the loss of range, the thrust on the operative engine should be increased to maximum
continuous thrust and the speed reduced to the recommended single engine cruise speed (refer to the
table for Long Range Cruise Speed) and allow the airplane to drift down to its new cruise altitude.
The increase in fuel required is substantial and the possibility of engine failure must be considered when
planning a long flight with no en-route alternates, since this case may determine the fuel reserve
required.
Fuel required may be calculated on the assumption of an instantaneous loss of height from two-engine
to single engine altitude. If in the particular case it is practicable to do the gradual drift down mentioned
above, there will be a savings of approximately 150 lb of fuel compared with the instantaneous loss of
height.
Figure 1 - Range After Engine Failure shows the effect on range of the loss of altitude associated with
an engine failure.
Single Engine Holding Fuel Flows are also provided in this Sub-section.
SINGLE ENGINE MAXIMUM CONTINUOUS THRUST FOR DESCENT AND CRUISE
This Sub-section provides single engine maximum continuous thrust data for descent and cruise.
The descent data is presented for daylight operations at ISA. An altitude range from the top of the
descent down to 14,000 feet is provided for a range of weights. Maximum descent speed is 0.70 Mach/
300 KIAS.
The cruise data is provided as a function of cruise altitudes, weights and temperatures for daylight
operations at ISA. Speed is listed in both Knots True Airspeed (KTAS) and Knots Indicated Airspeed
(KIAS). Total fuel flow is given in pounds per hour.