曝光臺 注意防騙 網(wǎng)曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

symbol is adjustable through 5° of pitch trim in both CLIMBand DIVE
directions using the PULL TO CAGE knob. Rotating the knob moves
the symbol and a pointer that indicates symbol pitch trim displacement
on a scale marked in 1° increments. The knob is slowly pulled out and
rotated clockwise to cage the gyro. When released, the knob will remain
in the extended position.Ared OFFflag will appear if the gyro is caged,
power is not applied or waslost, or the gyrobecomes inoperative. The
standby attitude indicator is powered by 28 VDC supplied by EMER
BAT 1. The standby attitude indicator is used to cross check the pilot
and copilot EADIs and serves as a back up unit in the event both pilot
and copilot EADIs become inoperative.
STANDBY ATTITUDE INDICATOR
Figure 5-16
PM-121
5-39 Change 3
Pilot's Manual
Learjet 31A
STANDBY HORIZONTAL SITUATION INDICATOR (HSD
The standby HSI is installed on the pilot's instrument panel. The
standby HSI provides the pilot with an additional indicator to display
thefollowing data:
" Compass Heading (AHS 2)
" VOR 1 Course Deviation
" VOR 1 Bearing Pointer
" LOC 1 Course Deviation
" ADF1 Bearing Pointer
" Glideslope Deviation
Pilot's controls consist of an FISI/RMI selector switch and course select
knob. In theFM mode, VOR 1 bearing pointer and ADF 1 bearing
pointer are provided. In the HSI mode VOR/LOC 1 course deviation
and ADF 1 bearing pointer are provided . In both modes, heading
data from AHS2 is presented. Failure flags will drop into view if the
associated data is invalid. The ADF bearing pointer will park at the
3:00 o'clock position with the loss of the ADF signal . With the loss of
ADF receiver or DC power, the pointer will park at either the 1:30
o'clock position or its last position. The standby HSI is used to cross
check the EHSIs and serves as a back up unit in the event all EHSIs
become inoperative. The standby HSI is operative during EMER BUS
mode.
VOR 1 CDVBearing Pointer
A ADF 1 Bearing Pointer
STANDBY HORIZONTAL SITUATION INDICATOR
Figure S-17
Learjet 31A
Pilot's Manual
PITOT-STATIC SYSTEM
Pitot and static pressure for the standby instruments, air data computers
and other using systems is obtained from two pitot-static probes.
One probe is located on each side of the nose compartment. Each
probe contains a pitot (impact pressure) port and two static pressure
ports. The probes also contain electrical heating elements controlled
by the Land R PITOTHEAT switches (Refer to PITOR'-STATIC AND
STALL WARNING ANTI-ICE, Section VI). Five drain valves, located
near the nose gear doors, are installed at the system low spots to
drain moisture from the system. Thepilot's pitot system is completely
independent of the copilot's pitot system and utilizes the left pitotstatic
probe as the source of pitot pressure. The copilot's system utilizes
the right pitot-static probe to obtain pitot pressure. The pilots and
copilot's systems each utilize a separate static source on each of the
probes. A solenoid-operated shutoff valve is installed in each static
source line to assure accurate static pressure in the event one probe
becomes clogged or unreliable. The shutoff valves are controlled
through the STATIC SOURCE switch on the pilot's switch panel and
operate on 28 VDC supplied through the 7.5-amp STATIC SOURCE
circuit breaker on the pilot's circuit breaker panel.
The pilot's pitot source supplies pitot pressure for ADC 1 air data
computer. The copilot's pitot source supplies pitot pressure for ADC
2 air data computer, standby airspeed indicator and optional equipment
requiring pitot pressure input.
Each pitot-static probe contains two static sources. One static source
on each probe is interconnected with a static source on the opposite
probe to supply static pressure to ADC 1. The other static source on
each probe is interconnected with a static source on the opposite
probe to supply static pressure to the standby airspeed indicator,
standby altimeter, ADC 2, and optional equipment requiring static
pressure input. In the event a static source becomes dogged or unreliable,
the affected pitot-static probe's static sources can be isolated, allowing
all equipment to be operated from static sources on the opposite
probe.
STATIC SOURCE SWITCH
The STATIC SOURCE switch controls solenoid-operated shutoff
valves, in the static plumbing, to assure accurate static pressure sensing
in the event one of the pitot-static probes become inoperable or
unreliable. The STATIC SOURCE switch, located on the pilot's switch
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：龐巴迪挑戰(zhàn)者手冊9(73)