Piper PA-28-236 DAKOTA, Руководство по эксплуатации для пилотов

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SECTION 9 PIPER AIRCRAFT CORPORATION
SUPPLEMENT 11 PA-28-236, DAKOTA
REPORT: VB-910 ISSUED: OCTOBER 14, 1986
9-92
Figure 7-1 (cont)
the modifier UP or DN will cause a pitch attitude change at a rate of
0. 7° per second. In ALT mode, actuation of the pitch modifier will
cause the autopilot to enter the ATT mode with subsequent operation
as described above.
8. ALT (Altitude) Mode Selector Switch
Selection of ALT mode will cause the autopilot to maintain the
pressure level (altitude) at the point of engagement. Because of them
pitch rate control provided by the autopilot, altitude mode may be
engaged from any rate of climb or descent, however, for maximum
passenger comfort, rate of climb or descent should be reduced to 1000
FPM or less prior to ALT mode engagement.
9. Test- See Section 4 for test procedure.
a. SPECIAL MODES AND OPERATIONS
(l.) Glide Slope (GS) Mode - The GS mode is fully autotic,
therefore, no GS engage switch is used. The GS mode may be
entered from either ATT mode or ALT mode, from above the
GS centerline or below the centerline.
Activation of the GS mode depends upon satisfying two sets
of conditions; completion of the ARMING sequence and the
satisfying of an equation relating to the aircraft’s position
relative to the GS centerline and the rate at which the aircraft
is approaching or departing from the GS centerline.
For GS mode arming, the following conditions must exist
simultaneously:
(a.) No. 1 NAV radio must be channeled to a localizer
frequency.
(b.) Localizer deviation must be less than 80%.
(c.) Localizer flag not extended -valid LOC signal.
(d.) GS Flag not extended- valid GS signaL
(e.) System in APR mode.
(f.) System in either ATT or ALT mode.
When the GS mode arming conditions are met, the GS mode
annunciator will illuminate in conjunction with the active
pitch mode. Loss of any arming condition prior to GS capture
will cause the GS annunciator to extinguish.