THE NEW PIPER AIRCRAFT, INC.
PA-32-301FT / 301XTC
MAINTENANCE MANUAL
PAGE 5
Feb 19/04
1K11
APPENDIX 1
4. GPSS
In the Global Positioning System Steering (GPSS) mode, the converter receives ground speed and bank
angle digital signals that are calculated and converted to a commanded turn rate. The turn rate is then
scaled and converted to a DC heading error signal that is compatible with S-TEC autopilots. The end
result is an autopilot that can be directly coupled to the roll steering commands produced by the GPS
Navigator, eliminating the need for the pilot to make any further adjustments to the HSI course arrow or
the DG's heading bug.
5. System Operation
Operation of the autopilot and other systems is described in the FAA-approved Airplane Flight Manual
Supplement (AFMS) - see airplane Pilot‘s Operating Handbook (POH), Section 9. Specialized controls,
annunciation, operation and interpretation are covered in this supplement and in the S-TEC Autopilot
POH that supplements the approved AFMS.
6. Maintenance
Except as provided in 5-20-00, servicing and/or maintenance of the autopilot system is On-Condition.
NOTE: Servicing of S-TEC System 55X Autopilot installations is best accomplished by approved
S-TEC dealers holding the appropriate FAA-certification. Locations of and access to the
components installed are described and depicted individually below. Removal and replacement
of components is generally indicated by functional checks provided in the AFM Supplement,
S-TEC Autopilot POH and/or below.
7. P
ost-Maintenance Operational Chec
kout (Ref. S-TEC Report No. 81191, Rev. 1.)
Complete the following checkout procedure after any maintenance to the system is performed.
NO
TE: The System 55X incorporates a SELF-TEST that requires a 100% pass rate before the autopilot
can be engaged.
NO
TE: For airplanes equipped with the optional Avidyne Entegra Electronic Flight Display System,
(see 34-20-00) references below to the remote annunciator, flight director, and HSI are to those
functions in the Primary Flight Display (PFD).
A. Apply aircraft power.
B. Avionics Master Switch ON
C. Autopilot Master Switch Set to FD / AP
NOTE: Observe that all segments of the Programmer / Computer display and annunciators
illuminate for five (5) seconds during test. Satisfactory completion of the SELF-TEST is
indicated when the Ready (RDY) annunciator remains on at the end of the five (5) second
self-test. Should a fault be detected, the FAIL annunciator will remain on at the conclusion
of the self-test and the autopilot will not operate.
D. Trim Master (ON / OFF) Switch ON
E. HDG and VS switches PRESS / RELEASE
Ensure that HDG and VS illuminate on the Fifty Five X annunciator.
F. VS Knob ROTATE CW
Pitch control (i.e. - the control yoke) should move slowly out (pilot may have to assist a heavy yoke).
G. VS Knob ROTATE CCW
Pitch control should move slowly in.
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