PIPER AIRCRAFT CORPORATION
SECTION 9
PA-28-236, DAKOTA
SUPPLEMENT 9
ISSUED: JULY 23, 1982
REPORT: VB-910
9-61
Figure 7-1 (cont)
1. KFC 150 SYSTEM KC 192 AUTOPILOT COMPUTER -
Complete Flight Director and Autopilot computer to include
system mode annunciators and system controls.
2. MODE ANNUNCIATORS - Illuminates when a mode is selected
by the corresponding mode selector button (PUSH ON- PUSH
OFF) or when the glide slope (GS) mode is automatically
engaged.
3. GLIDE SLOPE (GS) ANNUNCIATOR- Illuminates continuously
whenever the autopilot is coupled to the glide slope signal.
The GS annunciator will flash if the glide slope signal is lost
(GS flag in CD or absence of glide slope pointers in KI 525A).
The autopilot reverts to pitch attitude hold operation. If a valid
glide slope signal returns within six seconds, the autopilot will
automatically recouple in the GS mode. If the valid signal does
not return within six seconds, the autopilot will remain in pitch
attitude hold mode until such time that a valid glide slope returns
and the aircraft passes thru the glide slope. At that point GS
couple will re-occur.
4. TRIM WARNING LIGHT (TRIM) - Illuminates continuously
whenever trim power is not on or the system has not been preflight
tested. Flashes and is accompanied by an audible warning
whenever a manual trim fault is detected. The TRIM warning light
will illuminate steady and be accompanied by a steady audible
tone whenever an autotrim failure occurs. The autotrim system is
monitored for the following failures: trim servo running without
a command; trim servo not running when commanded to run;
trim servo running in the wrong direction. The trim power switch
may be cycled ·off to silence the continuous tope but the trim fail
light will remain on. The manual electric trim may be used but the
autopilot should not be engaged.
5. AUTOPILOT ANNUNCIATOR (AP) - Illuminates continuously
whenever the autopilot is engaged. Flashes approximately 12
times whenever the autopilot is disengaged (an aural alert will also
sound for 2 seconds).
6. AUTOPILOT ENGAGE (AP ENG) BUTTON - When pushed,
engages autopilot if all logic conditions are met.
7. PREFLIGHT TEST (TEST) BUTTON - When momentarily
pushed, initiates preflight test sequence which automatically turns
on all annunciator lights, tests the roll and pitch rate monitors,
tests the autotrim fault monitor, checks the manual trim drive
voltage and tests all autopilot valid and dump logic. If the
preflight is successfully passed, the AP annunciator light will
flash for approximately 6 seconds (an aural tone will also sound
simultaneously with the annunciator flashes). The autopilot cannot
be engaged until the preflight test is successfully passed.
Summary of Contents for PA-28-236 DAKOTA
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