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(fèi)者

BOOSTSwitch located on the pilot's switch panel. When the switch is
set to ON, the system will be armed. Setting the switch to OFF will
disarm the system and the rudder control system will not be assisted
by the yaw servo.
CONTROL WHEEL MASTER SWITCHES - RUDDER BOOST FUNCTION
The Control Wheel Master Switches (MSW), located on the outboard
horn of the pilot's and copilot's control wheels, may be used to interrupt
operation of the rudder boost system . Depressing either the pilot's
or copilot's Control Wheel Master Switch (MSW) will disable the
rudder boost system while the switch is held.
PM-121
5- 27
Change 1
Pilot's Manual
Learjet 31A
RUDDER
PEDALS
LH YAW
FORCE
SENSOR
-------W MECHANICAL
-I" ELECTRICAL
GREEN &
AMBERORB'
ANNUNCIATORS
RUDDER BOOST BLOCK DIAGRAM
Figure 5-8
RUDDER
PEDALS
RH YAW
FORCE
SENSOR
RUDDER
5-29
PM-121
Original
Learjet 31A
Pilot's Manual
ATTITUDE HEADING SYSTEM (AHS 1 AND AHS 2)
Aircraft avionics displays and equipment requiring attitude or heading
information are supplied attitude and heading information from dual,
independentAttitude Heading Reference Systems (AHS 1 and AHS 2).
Each system consists of an attitude heading reference unit computer,
magnetic slaving unit (flux valve), HEADING control switches, AHS
annunciator light and associated aircraft wiring. The attitude heading
reference unit computer is composed of inertial instruments, electronics,
interface hardware, processing and memory circuits to provide attitude
and heading information to other aircraft systems. Onemagnetic
slaving unit is located in each wing tip and is used to sense the earth's
magnetic field. The magnetic slaving unit can thus correct the AHS for
precession error. The HEADING SLAVE-FREE switch allows the crew
to select either Free orSlaved Magnetic Headingmode. The system has
two operating modes, normal and basic. During normal operation, a
true airspeed input is supplied by the air data system to improve accuracy.
If the true airspeed input is lost, the system will continue to operate
in the basic mode. AHS, operation is automatic and both systems
will energize when battery power is applied to the aircraft. Within 60
seconds of power application, the system determines its orientation
with the local vertical and magneticNorth and performs a series of selftest
and calibration functions. TheAHS1 and 2systemsare powered by
28 VDC, 7-5-ampAHS 1 andAHS2 circuit breakers and 26 VAC, 5-amp
AHS 1 and 1-ampAHS 2 circuit breakers located on the pilot's and copilot's
circuit breaker panels . AHS 2 is operative during EMER BUS
mode. In the event of a power loss, 2 to 11 minutes of back-up power
(28 VDC) will be supplied to AHS 1 and AHS2by EMER BAT 2. This
feature makes it unnecessary to reinitialize the system should a momentary
power loss be experienced. Should one of the systems fail, the
functions of the failed system may be assumed by the remaining system
using theAHS1/AHS 2 reversionary mode. Standby HSI heading
data and weather radar antenna stabilization functions are provided by
AHS2 and cannot be assumed by AHS 1.
Attitude/heading data is provided for the following using systems:
EFIS Displays -attitude and heading displays
Autopilot/Flight Director-attitude, heading and acceleration
data
Standby HSI - heading display (heading data provided by
AHS2 at all times)
Weather Radar-pitch and roll data provided by AHS 2 for
antenna stabilization
Flight Management System-heading data
PM-121
5-29
Change 4
Pilot's Manual
Learjet 31A
HEADING CONTROL SWITCHES
The HEADING control switches, located in the AVIONICS group on
the pilot's and copilot's switch panels, are used to control the heading
output of the associated AHS. The switches on the pilot's side control
AHS 1 while the switches on the copilot's side control AHS 2. The
SLAVE-FREE switch provides slaving mode selection for the associated
AHSheading output. When the switch is set to SLAVE, the associated
AHSheadingoutput will be referenced to its magnetic slaving unit and
the associated compass cards will reflect this "slaved" alignment.
When the switch isset toFREE, the associatedAHSheading output will
not be referenced to its magnetic slaving unit. The SLAVE L-R switch
provides for manual slewmg of the associated compass cards. Small
heading splits can usually be cleared by cycling the SLAVE-FREE
switch toFREE and thenback to SLAVEwhile theaircraft is not turning
or accelerating.
　
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(69)