3.
If autobrakes do not function, operate brakes manually.
Flaps, Slats.....................................C+F...............................28° / 40°
, LAND
The use of 40° of flaps is recommended for most situations. A flaps 28°
landing should be considered for the following situations.
.
Gusty wind conditions
.
Possibility of windshear exists
.
Occational proficiency practice
Annunciator Panel, Cabin PA ........................CHECKED, COMPLETED
Verify the annunciator panel displays only the lights appropriate for the landing configuration. Special attention should be given to the following:
.
The RUDDER TRAVEL UNRESTRICTED light should be on. This indicates maximum rudder travel is available if required. If the light is not on, maintain at least 135 KIAS until landing. Crosswind is limited to 12 knots.
.
All anti-skid lights should be out.
.
The AUTO-SPOILER-DO NOT USE light should be out.
.
The ENGINE SYNC light should be out.
.
The SPOILER/FLAP EXTENDED light should be out.
The PM will announce on the P.A., “FLIGHT ATTENDANTS, PLEASE BE SEATED FOR ARRIVAL.”
INTENTIONALLY LEFT BLANK MISSED APPROACH / GO-AROUND PROCEDURE
A missed approach / go-around will be initiated if continuation to a safe landing in the touchdown zone is not possible at DA(H) on a precision approach, at the MAP on a non-precision approach, or at any point when the pilot feels that safety may be compromised if the approach is continued. ATC may also direct the pilot to “GO-AROUND” if some conflict exists.
To execute the missed approach / go around, the pilot flying will simultaneously:
.
Advance throttles positively to go-around thrust while activating the TOGA buttons.
.
Call for “FLAPS 15°, CHECK MAX POWER.”
.
If the autopilot is engaged, ensure that the autopilot rotates the aircraft to go around attitude (15°-20°). If the autopilot is not engaged, rotate the aircraft to go around attitude using the command bars.
.
With a positive rate of climb, call “POSITIVE RATE, GEAR UP, ALTITUDE ARM.”
.
Climb at the Go-Around speed printed on the Landing Speed Card (The flight director should provide this guidance).
.
Call for “HEADING SELECT” (when required).
Turns after go-around should normally be delayed until 400 feet AGL.
However, a turn may be initiated as low as 50 feet AGL. Bank angle must be limited to 15° until maneuvering speed for the configuration is attained. If the decision has been made to depart the local area, upon reaching flap
retraction altitude (normally 1000 feet AGL) reduce pitch, accelerate, and
retract the flaps and slats on schedule as during a normal takeoff. If returning for another approach, climb to the missed approach altitude at the go-around speed and consider maintaining a normal traffic pattern configuration and speed (slats extended/flaps 15 and speed 170). Use of the autopilot and autothrottles is recommended to reduce the workload and to allow both pilots to concentrate on flying the missed approach procedure or complying with ATC directives.
Accomplish the AFTER TAKEOFF CHECKLIST. Note: A rejected landing will be accomplished using the same procedure as a missed approach / go-around. Special care should be taken not to raise the landing gear until a positive rate of climb is confirmed by reference to the IVSI and altimeter to ensure that an inadvertent touchdown is no longer a factor.
Autopilot Missed Approach
An autopilot go-around is initiated when either throttle TO/GA button is depressed with the autopilot engaged, the aircraft in flight, and the flaps extended beyond the 26 degree position. Activation of the go-around mode is indicated by annunciation on the flight mode annunciator G/A in both the roll and pitch mode annunciators.
The selection of any pitch mode during autopilot go-around will result in disengagement of the autopilot go-around mode and the autopilot reverts to the selected pitch mode and heading hold mode. However, altitude preselect mode, if armed, will automatically cancel the go-around mode or the selected pitch mode at altitude capture.
During autopilot go-around, any roll mode may be selected without subsequent disruption of pitch axis control.
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本文鏈接地址：MD-80 Flight Manual 麥道80飛行手冊 2(27)
