曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

needle deviation of localizer centerline.
3. Select ALT mode. Airplane must be 60% or more below the
glideslope centerline during the approach to the intercept point. If
the above conditions have existed for 10 seconds, GS mode will
arm, the GS annunciator will come on and the ALT annunciator will
remain illuminated. When glideslope intercept occurs, the ALT
annunciator will go out and the system will track the glideslope.
• Note •
If approach vectoring locates the airplane too near the
glideslope at the intercept point (usually the outer marker), the
GS mode can be manually armed by pressing the ALT button
once. Once capture is achieved, GS annunciator will come on
and ALT annunciator will go out.
Section 5 - Performance
There is no change to the airplane performance when the S-Tec
System 55 autopilot is installed.
Section 6 - Weight & Balance
There is no change to the airplane weight & balance when the S-Tec
System 55 autopilot is installed.
Section 7 - Systems Description
Autopilot
The airplane is equipped with an S-Tec System 55 two-axis Automatic
Flight Control System (Autopilot). The autopilot programmer/computer
is installed in the center console radio stack.
The autopilot roll axis uses an inclined gyro in the turn coordinator
case as the primary turn and roll rate sensor. In addition to the turn
coordinator instrument, the roll axis computer receives signals from
the HSI and the #1 NAV radio. The roll computer computes roll
steering commands for turns, radio intercepts, and tracking. Roll axis
Revision 3: 07-18-05
14 of 16 P/N 11934-S08
Section 9 Cirrus Design
Supplements SR20
steering is accomplished by autopilot steering commands to the
aileron trim motor and spring cartridge.
The pitch computer receives altitude data from an altitude pressure
transducer plumbed into the static system, an accelerometer, and
glideslope information from the HSI and #1 NAV radio. Pitch axis
command for altitude hold, vertical speed hold, and glideslope tracking
is accomplished by pitch computer commands to the elevator trim
motor and trim cartridge.
28 VDC for autopilot and turn coordinator operation is supplied
through the 5-amp AUTOPILOT circuit breaker on the Main Bus 1.
Turn Coordinator instrument dimming is controlled through the INST
light dimmer on the bolster switch panel.
All Autopilot mode selection is performed by using the mode select
buttons and VS knob on the autopilot programmer/computer in the
center console. Annunciators in the programmer/computer display
window annunciate modes. Refer to Figure 1 for an illustration of the
programmer/computer.
RDY (Ready)– Illuminates when autopilot is ready for engagement.
When the airplane’s Battery Master switch is turned on and the rate
gyro RPM is correct, the RDY annunciator will come on indicating the
autopilot is ready for the functional check and operation. The autopilot
cannot be engaged unless the RDY light is illuminated.
HDG (Heading) Mode – When HDG is selected, the autopilot will
engage the HDG mode, fly the airplane to, and hold the heading set on
the HSI. Subsequent heading changes are made using the HDG knob
on the HSI. For smoothest transition to HDG mode, it is recommended
that the airplane be aligned to within 10° of the selected heading
before engaging HDG. The HDG mode is also used in combination
with the NAV mode to set up a pilot selected intercept angle to a
course.
NAV (Navigation) Mode - When NAV is selected, the autopilot will
provide intercept and tracking of GPS, VOR, and Localizer courses.
For course intercept with full-scale deviation, the autopilot
automatically sets up a 45° intercept angle at maximum gain and
sensitivity (turn is limited to 90% of standard rate). The point at which
the turn to capture the course begins is dependent upon closure rate
and airplane position. When the course is intercepted and the HSI
Revision 3: 07-18-05
P/N 11934-S08 15 of 16
Cirrus Design Section 9
SR20 Supplements
course deviation needle centered (indicating course capture), the
autopilot automatically initiates a tracking gain program to reduce turn
rate to 45% standard rate, and then 15% standard rate.
REV (Reverse Course) – When REV is selected, the autopilot will
automatically execute high sensitivity gain for an approach where
tracking the front course outbound or tracking the back course inbound
is required. The APR and REV annunciators will illuminate when REV
is selected.
APR (Approach) – When APR is selected, the autopilot provides
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：Cirrus Design SR20西銳20飛行員操作手冊和飛機飛行手冊附錄(21)