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

PM-121
5-41
Original
Pilot's Manual
Learjet 31A
Panel, has three positions: L, BOTH, and R. When the switch is in the
BOTH position all four shutoff valves are deenergized open and static
pressure for the air data instruments and equipment is available from
static ports, in both pitot-static probes. Normally, the switch is in the
BOTH position for all operations. When the switch is set to Lor R, the
shutoff valves for the opposite pitot-static probe are energized dosed,
and static pressure will be supplied by the selected pitot-static probe
only.
PITOT-STATIC SYSTEM
Rgtxe 5-18
5-42
PM-121
Original
Learjet 31A
Pilot's Manual
AIR DATA SYSTEM (ADC 1 ANDADC2)
A dual air data system is installed to provide flight environment air
data to instruments and equipment requiring the data for display or
operation. The system consists of two air data computers (ADC 1 and
ADC 2), pilot's and copilot's airspeed/Mach indicators, pilot's and
copilot's altitude/vertical speed indicators, speed/temperature
(SAT/TAS) indicator and reversionary mode switch/annunciators.
During ground operations, the system can be tested through the SYSTEM
TEST switch on the pilot's instrument panel. ADC 1 and ADC 2
operate on 28 VDC supplied through the 3-amp ADC 1 and ADC 2
circuit breakers on the pilot's and copilot's circuit breaker panels respectively.
ADC1 is operative during EMER BUSmode.
The air data computers receive pitot and static pressures from the pitot-
static probes and temperature data from the total temperature
probe for computation of the flight environment. The computed results
of the sensor inputs are converted to electrical signals and transmitted
to the associated cockpit displays. Additional outputs from the
air data computers are transmitted to the attitude heading system
(AHS), EFIS, stall warning system, overspeed warning system, flight
management system (FMS), Mach trim system, and autopilot/flight
guidance system. The following table summarizes the various computer
outputs.
PM-121
5- 43
Change l
ADC 1
Normal (non-reversionary mode)
ADC 2
Normal (non-reversionary mode)
" Pilot's Instruments " Copilots Instruments
Airspeed/Mach Airspeed/Mach
Altitude/Vertical Speed Altitude/Vertical Speed
SAT/TAS " Altitude Alert
" Altitude Alert " RStall Warming
" LStall Warning " Gear Warning
" Gear Warning " Overspeed profile
" Overspeed profile " AHS 2 (TAS)
" AHS 1(TAS) " Copilot's EFIS
" Pilots EFIS " RFlight Guidance
" LFlight Guidance " ATC2 (encoded altitude)
" Mach Trim " FMS2
" ATC 1 (encoded altitude)
" FMS 1
Pilot's Manual
Learjet 31A
Refer to FLIGHT INSTRUMENTS for a description of air data instruments.
The reversionary mode switch/annunciators (ADC 1/ADC2)
are used to select the desired air data computer as the source for the
on-side instruments and systems. Refer to the FAA Approved AFM
for a description and use of the reversionary function.
SYSTEM TEST SWRCH - ADC FUNCT10N
During ground operations, the ADC system and instruments are tested
through the rotary-type SYSTEM TEST switch on the pilot's instrument
panel. With the SYSTEM TEST switch set to ADC, the air data
system test is initiated by depressing the TEST button in the center of
the switch. Thetest sequence will test the overspeed warning system,
both air data computers, and the air data system instruments. The test
sequence is fully described in the Berkdix/King KFC 3100 pilot's
guide.
TAKEOFF CONFIGURATION MONITOR SYSTEM
The takeoff configuration monitor system consists of a monitor box,
throttle quadrant switch, various system switches (provide the input
signals to the monitor box), and a T.O. TRIM annunciator. The system
is active when the aircraft is on the ground (right squat switch in
ground mode). The T-O. TRIM annunciator, located on the glareshield
annunciator panel, will illuminate when the pitch trim is not in a safe
position for takeoff and the aircraft is on the ground. The annunciator
is disabled during flight operations. A takeoff monitor aural warning
will sound during ground operations when the right thrust lever is
advanced above the 82°6 NI position and one or more of the following
conditions exist:
1.
Flapsnote for takeoff.
2. Spoilers not retracted.
3.
Pitch trim not in a safe position for takeoff.
4. Parking brake not released.
5.
Thrust reverser unlocked (if applicable).
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：龐巴迪挑戰者手冊9(74)