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

autopilot/flight director system. The roll steering output limits
for both “Direct To” and normal leg-to-leg changes are
configuration specific, and are set during initial configuration of
the system. These specified limits are restricted to a
maximum roll angle of 30°. The roll rate is limited to 3° per
second in all installations. Refer to the following table for
operational roll angle limits:
HEADING CHANGE  ROLL ANGLE LIMIT
Normal Leg
Sequence/Direct To
Standard rate turn not to exceed configured limits.
Procedure Turn 27.8°
Holding 27.8°
FMS Heading Equal to heading error – not to exceed configured
limits
Procedural Headings
(SIDs, STARs)
Equal to heading error – not to exceed configured
limits
Tear-drop Procedure
Turn
10° to 20° (Refer to Tear-drop Procedure Turns in
Section V.)
 
Section I
System Description
2423sv602
Change 1
1-8
Fuel
The aircraft's engine fuel flow system provides the inputs necessary
to integrate real time fuel management information with the
navigational functions. During the predeparture phase, the pilot
inputs the fuel on board the aircraft to initialize the fuel management
functions. During flight, the FMS automatically updates the fuel on
board and gross weight as well as provides continuous estimates of
the fuel requirements for the programmed flight plan based upon fuel
flow and groundspeed. The FMS also provides specific range and
endurance data to aid the pilot in optimizing fuel consumption to
obtain maximum range or endurance.
NOTE: The Fuel Flow management information provided by the
FMS has not been evaluated to the requirements of TSO
C44a (Fuel Flowmeters).
Fuel display parameters are advisory only and do not
replace primary fuel quantity or fuel flow gauges for fuel
load and range planning.
Multiple FMSs
In dual or triple installations, each FMS outputs and makes available
to the other system initialization and flight plan information through
an interconnecting bus. While all long range navigation sensors are
interfaced with both units, each FMS acts as the "master" to the
associated sensor. Each FMS computes its own independent
position using all available navigation sensors and provides selected
information to the associated flight instruments. Each FMS also
shares its best computed position with the other system and
continuously monitors the other system's position output.
Radio Tuning
Incorporated into the FMS, an optional TUNE mode provides the
operator with a centralized means to tune the aircraft's radios, select
and store preset frequencies for each radio, and to view the selected
(preset or active) frequencies for each radio. The aircraft must be
configured with a Radio Tune Unit or Proline 4 or AN/ARN TACAN
or 709 DME & 711 VOR for this mode to be operational.
Section I
System Description
2423sv602 1-9
Change 1
Annunciations
Messages
The FMS contains an array of messages, which alert the operator to
system status and flight plan sequencing. When a message is
active, "MSG" will appear on the display, and the message can be
accessed by pressing the MSG key.
The Message function also is utilized for AFIS and UniLink
communications in applicable installations.
Remote Annunciations
Outputs are provided to drive the six external annunciators to alert
the pilot of system status or flight plan sequencing (Note: these may
be incorporated into the EFIS display):
MSG - A new message has been generated.
WPT - (Steady) Lateral waypoint alert.
(Flashing) Vertical waypoint Flight Path Angle
alert.
SXTK - FMS is in selected crosstrack mode.
FMS HDG - FMS is in Heading Mode.
FMS APPR - FMS is in Approach Mode.
GPS INTEG - RAIM is not available or a fault is detected. DME
may be still in use.
Video Interface Option
Only applicable to UNS-1B with Flat Panel CDU, or to UNS-1C, -
1Csp, or -1D. This optional feature allows interface with video
cameras and cabin display systems for viewing on the FMS color flat
panel display. NTSC RGB video format is required for input to the
FMS.
SYSTEM COMPONENTS
The basic FMS installation consists of the FMS (containing the
display, keyboard, navigation computer and a GPS sensor), a
configuration module, a Data Transfer Unit and a GPS antenna.
Section I
System Description
2423sv602
Change 1
1-10
FMS Display
The FMS utilizes a 4 or 5-inch active matrix liquid crystal color flat
　
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10(19)