Hawker Beechcraft Hawker 800XP, Руководство по эксплуатации для пилотов

Страница: 334 / 923

Page 17-7
Pilot’s Operating Manual
P/N 140-590032-0007
Revision A4: Sep, 2010 Section III Sub-section 17
AVIONICS
FLIGHT GUIDANCE SYSTEM (FGS)
The FGS provides autopilot and dual flight guidance functions by utilizing two identical computers, three
primary servos, a pitch trim servo and a flight guidance panel.
The Flight Guidance Computers (FGC) receive Attitude Heading System (AHS) data directly from the
Attitude Heading Computer (AHC) to provide independent flight guidance computation while operating
together to provide 3-axis autopilot, pitch trim, Mach trim and yaw damper functions.
The two FGCs apply differential autopilot command drive to each primary servo to move the airplane
elevator, aileron and rudder control surfaces.
ATTITUDE HEADING SYSTEM (AHS)
The AHS is a dual reference system consisting of two AHC-3000 Attitude Heading Computers (AHC),
two FDU-3000 Flux Detector Units (FDU) and two External Compensation Units (ECU).
The AHS supplies attitude, stabilized magnetic or free gyro heading and linear acceleration data to the
Flight Guidance System, Electronic Flight Instrument System, Integrated Avionics Processor System
and Weather Radar System.
The AHCs are functionally and physically isolated from each other and replace the conventional vertical
gyro, directional gyro, three rate gyros, and three linear accelerometers. The AHS has two operational
modes, slaved and Directional Gyro (DG) mode.
FLIGHT MANAGEMENT SYSTEM (FMS)
The Flight Management System provides flight plan management, multisensor navigation, and radio
tuning. The FMS consists of two Flight Management Computers (FMC), two Control Display Units
(CDU) used to control the FMS and a Data Base Unit.
The FMC is a lateral and vertical navigator used by the autopilot to fly a programmed flight plan and
provides coupled VNAV, NAV-to-NAV capture, navaid data base storage and several control/planning
functions.
The Data Base Unit is a data loader used primarily to load monthly data base updates to the FMC and
to load and download maintenance data from the MDC maintenance computer.
AIR DATA SYSTEM (ADS)
Dual ADSs sense and process data obtained from the air mass around the airplane. The two Air Data
Computers (ADC) connect to the pitot/static air input ports and to a temperature sensor. The ADCs
process air data and provide output parameters to the AFDs, AHCs and the IAPS concentrators.
ENGINE INDICATING SYSTEM (EIS)
The EIS digitizes airplane engine data for input to the avionics system while converting avionics digital
data into outputs that drive airplane annunciators and aural horns.
The EIS consists of four Data Concentration Units (DCUs). Two units are wired as DCUs and two units
are wired as Engine Data Concentrators (EDCs).
The DCUs transfer airplane sensor information (analog fuel flow, strut status, etc.) to the IAPS
concentrators while transferring caution/warning advisory information from the Flight Control
Computers to the annunciators. The EDUs also provide redundant engine data to the displays.