Note: Flight director command bar commands fly up (maximum 20° airplane nose up).
Flight director command bar commands go-around reference speed, wings level and maintains existing heading when roll attitude is less than 3°.
FAST / SLOW indicator on each ADI will provide guidance to go-around
speed (which equals approximately 1.3 V5 + 5 knots for landing flaps).
If an immediate climbing turn is required:
HDG Select Knob..............................................................................PULL
Momentarily pull out of HDG select knob to engage heading select mode. Verify bank angle limit is set at 15°. Rotate HDG select knob until desired heading is displayed in HDG Readout. FMA’s will display EPR GA / HDG SEL / GO RND.
For all contingencies:
ALT Set Knob...................................................................................PULL
Momentarily pull out on the ALT SET knob to arm the FGS for missed
approach altitude capture. Arm mode will display ALT.
Pitch Control Wheel ...................................................................ROTATE
Rotate pitch control wheel as required to accelerate at 1,000 ft. AGL. Pitch mode changes to VERT SPD.
(Continued)
CL Mode Button ...............................................................................PUSH
Push CL mode button. EPR limit for climb thrust will be displayed in the EPR LIM Readout and EPR reference bug on EPR gage will be automatically positioned. Autothrottle mode changes from EPR GA to EPR
CL.
SPD / MACH Readout .........................................................................SET
Rotate the SPD / MACH select knob until desired speed appears in SPD /
MACH Readout.
Continental
Rev. 12/01/00 #29 Flight Manual
AUTOLAND APPROACH
1 – 2 Switch ..................................................................................... 1 OR 2
Select flight guidance computer 1 or 2.
AP Switch..............................................................................................ON
AUTO THROT Switch ......................................................................... ON
Move AUTO THROT switch to on (UP) position and observe FMA displays
SPD (plus selected value), HDG SEL, and ALT HELD.
VHP / NAV Readouts...........................................................................SET
Set the same ILS frequency in both VHF / NAV Readouts and identify.
Note: Both VHF and CRS Readouts must be set to the same ILS frequency and course before autoland logic can complete.
VHF / CRS Readouts ...........................................................................SET
Rotate VHF / CRS select knobs until required ILS front inbound course
is displayed in each Readout.
Note: If correct ILS / LOC inbound course has not been set, and a large discrepancy exists between the actual LOC inbound course and the selected course, flight guidance system will not attempt to complete the course intercept; the airplane will fly through the localizer, wings level. In that case, LOC CAP may be annunciated and G/S TRK could occur, causing the airplane to begin to descent. Upon failing to attain LOC TRK and after exiting the localizer beam, autopilot will disconnect and flight guidance will revert to HDG HLD / VERT SPD.
No Autoland Light .............................................................................. OFF
Observe that the NO AUTOLAND light is off.
Note: If the NO AUTOLAND light is on, move 1 – 2 switch to opposite position and again observe NO AUTOLAND light. If the NO AUTOLAND light is off, continue autoland operation. If the NO AUTOLAND light is on, autoland operation is not possible.
The NO AUTOLAND light can come on any time the computer is powered.
(Continued)
HDG Readout.......................................................................................SET
Rotate HDG selector knob until required localizer intercept heading
appears in HDG Readout. Verify HDG SEL mode is engaged.
AUTOLAND Button .........................................................................PUSH
Push AUTOLAND pushbutton and observe FMA’s display LND.
Note: The pitch wheel may be used to arrive at approach entry altitude.
When the localizer beam deviation reduces to the capture threshold, the airplane automatically turns as required to localizer beam centerline. LOC CAP will be annunciated in the roll FMA’s.
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