737 Operations Manual
Performance Inflight -
Text
737-400/CFM56-3_23.5K
Copyright © The Boeing Company. See title page for details.
D6-27370-400E-TBCE PI.26.9
Max Continuous %N1
Power setting is based on one engine operating with one A/C pack
operating and all anti-ice bleeds off. Enter the table with pressure altitude
and IAS or Mach to read %N1.
It is desirable to maintain engine thrust within the limits of the Max Cruise
thrust rating. However, where thrust in excess of Max Cruise rating is
required, such as for meeting terrain clearance, ATC altitude assignments,
or to attain maximum range capability, it is permissible to use the thrust
needed up to the Max Continuous thrust rating. The Max Continuous
thrust rating is intended primarily for emergency use at the discretion of
the pilot and is the maximum thrust that may be used continuously.
Driftdown Speed/Level Off Altitude
The table shows optimum driftdown speed as a function of cruise weight
at start of driftdown. Also shown are the approximate weight and pressure
altitude at which the airplane will level off considering 100 ft/min residual
rate of climb.
The level off altitude is dependent on air temperature (ISA deviation).
Driftdown/LRC Cruise Range Capability
This table shows the range capability from the start of driftdown.
Driftdown is continued to level off altitude. As weight decreases due to
fuel burn, the airplane is accelerated to Long Range Cruise speed. Cruise
is continued at level off altitude and Long Range Cruise speed.
To determine fuel required, enter the Ground to Air Miles Conversion table
with the desired ground distance and correct for anticipated winds to
obtain air distance to destination. Then enter the Driftdown/Cruise Fuel
and Time table with air distance and weight at start of driftdown to
determine fuel and time required. If altitudes other than the level off
altitude is used, fuel and time required may be obtained by using the
Engine Inoperative Long Range Cruise Enroute Fuel and Time Table.
Long Range Cruise Altitude Capability
The table shows the maximum altitude that can be maintained at a given
weight and air temperature (ISA deviation), based on Long Range Cruise
speed, Max Continuous thrust, and 100 ft/min residual rate of climb.
June 07, 2002
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