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
9-94
HDG mode annunciator. Selected angle intercepts of over 60°
are not recommended.
NOTE
If radio information becomes invalid (Flag)
after initiation of a selected angle intercept the
applicable navigation mode annunciator will
flash and the autopilot will remain in HDG
mode. The automatic mode shift to the invalid
radio mode will not occur.
(3) CWS Mode - The system is equipped with a control wheel
steering switch on the pilot’s control wheel. When depressed
and held, this switch will disengage the autopilot roll and
pitch servos to allow manual aircraft maneuvering. When
released, the servos will re-engage with the lateral (roll)
mode previously in use activated. The pitch mode previously
engaged will remain programmed in the following condition:
(a.) ALT Mode - If ALT mode had been in use, the ALT
mode will synchronize at the new pressure altitude
existing at release of the CWS switch.
(b.) ATT Mode - If the ATT mode had been in use, the
system will synchronize with the aircraft attitude existing
at release of the switch.
(4) System Test (Ground operations only) -The system is
equipped with a comprehensive test circuit which, when
activated, will test the failure monitor circuits and all the
annunciator lamps. Activation of the TEST switch will initiate
the system test only when the autopilot is not engaged. When
autopilot is engaged, activation of the TEST switch will test
the annunciator lamps. If the autopilot is engaged during the
test sequence, the sequence will terminate immediately. Refer
to Section 4 for tests required before the first flight of each
day.
(5) Warning System and Interlocks - The Century 31 system
includes a number of automatic interlocks that will prevent
system operation or individual mode operation if the input
information is not valid or if other prerequisite conditions
do not exist. In addition to the interlocks, the system will
annunciate various failure ·conditions as advisory information
for the pilot. Following is a brief description of the interlocks
and warnings provided.