737 Flight Crew Operations Manual
Performance Dispatch
Text
737-800WSFP1/CFM56-7B26
FAA
Category C/N Brakes
Boeing Proprietary. Copyright © Boeing. May be subject to export restrictions under EAR. See title page for details.
D6-27370-866-EGP PD.14.5
Landing Climb Limit Weight
Enter the table with airport OAT and pressure altitude to read landing
climb limit weight. Apply the noted adjustments as required.
Go-Around Climb Gradient
Enter the Reference Go-Around Gradient table with airport OAT and
pressure altitude to determine the reference go-around gradient. Then
adjust the reference gradient for airplane weight and speed using the tables
provided to determine the weight and speed adjusted go-around gradient.
Apply the necessary corrections for engine bleed configuration and icing
conditions as noted.
Quick Turnaround Limit Weight
Enter the appropriate table (Steel or Carbon Brakes) with airport pressure
altitude and OAT to read maximum quick turnaround weight. Apply the
noted adjustments as required.
If the landing weight exceeds the maximum quick turnaround weight, wait
the specified time and then check that the wheel thermal plugs have not
melted before executing a subsequent takeoff. For Steel Brakes, the
alternate procedures on the charts can be used to ensure the brake
temperature is within limits. These procedures cannot be used for carbon
brakes.
Gear Down
This section provides flight planning data for revenue operation with gear
down. Unless otherwise noted, the gear down tables in this section are
identical in format and usage to the corresponding gear up tables
previously described.
To eliminate erroneous displays the flight crew should enter only gross
weight data on the PERF INIT page of the Control Display Unit (CDU).
Omission of the cost index and cruise altitude entries on the PERF INIT
page will render the VNAV function unavailable during flight. As a result,
the following information will not be provided: VNAV guidance and speed
schedules, trip fuel and ETA predictions, optimum and maximum altitude
data, step climb and top of descent predictions, and the VNAV descent
guidance path.
The gross weight entry allows the FMCS takeoff and approach speed
schedules to be generated. In addition, the flap maneuver speed and VREF
speed bugs will be available for display on the primary flight display speed
tape. Except for VNAV, normal autopilot and autothrottle modes will
remain available for use during the flight, as will the LNAV mode.
September 15, 2016
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