Bombardier-Challenger_00-Flight_Instruments庞巴迪挑战者飞行仪表

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Bombardier-Challenger_00-Flight_Instruments庞巴迪挑战者飞行仪表

 

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canadair
ctiaiienqer
OPERATING MANUAL
SECTION 11
FLIGHT INSTRUMENTS
TABLE OF CONTENTS
Subject page
GENERAL 1
PITOT-STATIC SYSTEM AND TEMPERATURE SENSING SYSTEM 1
ADS Heater Control Panel
Static Pressure Selector Valve 4
Stall Protect Valve
Pitot Heat Failure Indicator
ATTITUDE REFERENCE SYSTEM 5
Gyro Fast Erect
Flight Director Switching Panel
HEADING REFERENCE SYSTEM 5
Compass Control Panels
INSTRUMENT COMPARATOR 9
PRIMARY FLIGHT INSTRUMENTS 11
Electrically Operated Flight Instruments
Pneumatically Operated Flight Instruments
STANDBY FLIGHT INSTRUMENTS 11
Artificial Horizon
Standby Magnetic Compass 12
LIST OF ILLUSTRATIONS
Figure
Number Title Page
1 Pitot-Static System - Components (2 sheets) 2
2 Flight Director Switching Panel 6
3 Compass Control Panel (2 Sheets) 7
4 Instrument Comparator 10
5 Pilot's Mach/Airspeed Indicator 13
11 -CONTENTS
Page 1
Oct 03/83
cacnhaatiiiaeinr Qer
OPERATING MANUAL
Figure
Number Title pa ge
6 Pilot's Altimeter 14
7 Pilot's Vertical Speed Indicator 15
8 Radio Altimeter 16
9 Horizontal Situation Indicator (2 Sheets) 17
10 Attitude Director Indicator (2 Sheets) 19
11 Copilot's Mach/Airspeed Indicator 21
12 Copilot's Altimeter 22
13 Copilot's Vertical Speed Indicator 23
14 Standby Artificial Horizon 24
15 Standby Magnetic Compass 25
11 -
Paae
Oct
cacnhaadllaeinr ger
OPERATING MANUAL
SECTION 71
FLIGHT INSTRUMENTS
1. GENERAL
The primary flight instruments, which are mounted on each pilot's instrument
panel, are either electrically or pneumatically operated and are integrally
illuminated. Where applicable, display functions are displaced out of view
when not in use, and a warning flag covers a display in the event of a
malfunction* Each pilot has an alternative source of information for each
primary flight instrument. The course and heading controls and AFCS controls
are located on the centre pedestal for easy access by both pilots. For further
information about these controls, refer to SECTION 4, AUTOMATIC FLIGHT CONTROL
SYSTEM. A standby magnetic compass and an artificial horizon are also provided.
2. PITOT-STATIC SYSTEM AND TEMPERATURE SENSING SYSTEM (Figure 1)
The pitot-static system provides the pitot and static pressures required to
operate the pneumatic flight instruments, the air data computer (ADC) and the
cabin pressure indicator. The system consists of the pilot's and copilot's
pitot-static tubes, left and right static ports, A.D.S. HEATER CONT. panel,
pilot's and copilot's PITOT HEAT fail annunciators and pilot's and copilot's
STATIC PRESSURE SELECTOR VALVES. A temperature-sensing probe located on the
right side of the forward fuselage provides a total-air-temperature input to
the air data computer. The pitot tubes, the static ports and the temperature
probe contain anti-icing heater elements which are controlled from the A.D.S.
(air data sensors) HEATER CONT. panel.
On aircraft with STC No. SA99NE incorporated,
the pitot-static system is also equipped with pilot's and copilot's STALL
PROTECT valves.
The copilot's mach/airspeed, altimeter and vertical speed indicators are
connected directly to the pitot-static system. The corresponding instruments
on the pilot's side are connected to the air data computer. The controls
associated with the pitot-static system are the A.D.S. HEATER CONT. panel and
the STATIC PRESSURE SELECTOR VALVES.
On aircraft with STC No. SA99NE incorporated,
the controls associated with the pitot-static system are the A.D.S. HEATER
CONT. panel, the STATIC PRESSURE SELECTOR VALVES and the STALL PROTECT valves.
A. ADS Heater Control Panel
The A.D.S. HEATER CONT. panel contains the switches and indicators for the
pitot-static anti-icing system. The application of power to the heating
elements in the pitot-static tubes, the static ports and the temperature
SECTION 11
Page 1
Oct 03/83
canadair
ctiaiienQer
OPERATING MANUAL
HTR II ALL
FAIL II ON
A.D.S. HEATER CONT. k
PUSH TO
RESET
f / R T A T . / \ \
;wic\ I > A / OA
W/ D PWR &
r METER
I SELECT
HTRS % HTR CURRENT
OFF
AIR DATA SENSORS
f*M HEATER CONTROL
PANEL
AP
FAIL
AP
FAIL
AFCS PITOT
HEAT
GYRO
FAST 1
ERECT
TAT PROBE
0
STATIC PORT
(LEFT AND
RIGHT SIDES)
PITOT HEAT FAIL
ANNUNCIATOR
EFFECTIVITY: A/C WITHOUT STC NO
SA99NE INCORPORATED
Pitot-Static System - Components
Figure 1 (Sheet 1)
STATIC PRESSURE
SELECTOR VALVE
SECTION 11
Page 2
Oct 03/83
canadair
chanencfer
OPERATING MANUAL
o,
HTR
FAIL
A.D.S. HEATER CONT.
/ / A T.A.T. / \ \
/ S W I C \ I / L
A ; o . A \
PUSH TO
RESET
ALL
VP-TOT/ T
^ HTRS
OFF
PWR
&
METER
SELECT
AIR DATA SENSORS
UM HEATER CONTROL
PANEL
AP
PAIL
AP
FAtL
AFCS PITOT
HEAT
GYRO
FAST
ERECT
TAT PROBE
© ^
0 0
0 0
O STATIC PORT
•M (LEFT AND
RIGHT SIDES)
© PiTOT-STATIC TUBE
PITOT HEAT FAIL
ANNUNCIATOR
STATIC
>RE£f\UF*E
PROTECT f.f
STATIC
NOJP^AL
EFFECTIVITY: A/C WITH STC NO. SA99NE
INCORPORATED
PILOTS STATIC
PRESSURE SELECTOR
VALVE AND STALL PROTECT
STATIC PRESSURE SELECTOR
VALVE (SAFETY GUARD
REMOVED FOR CLARITY)
COPILOTS STALL
PROTECT STATIC
PRESSURE SELECTOR VALVE
AND STATIC PRESSURE
SELECTOR VALVE
Pitot-Static System - Components
Figure 1 (Sheet 2)
SECTION 11
Page 3
Oct 03/83
canadair
ctianencjer
OPERATING MANUAL
sensing probe is controlled by the PWR & METER SELECT switch. Power is
applied when the switch is set to any position except HTRS OFF*
If the amber HTR FAIL warning light on the control panel comes on, the
failure of one of the static port heaters is indicated. To determine which
heater has failed, rotate the PWR & METER SELECT switch through the
STATIC L and STATIC R positions. The defective heater is indicated by a
reading in the red zone on the % HTR CURRENT meter. After the defective
heater is determined, pressing the HTR FAIL switch/light causes the warning
light to go out and resets the fault detection circuits.
When the PWR & METER SELECT switch is set to HTRS OFF, the HTR FAIL light
comes on and the % HTR CURRENT meter gives a red zone reading. Although
power is applied to the two pitot-static tube heaters via the A.D.S. HEATER
CONT. panel, a pitot-static tube heater failure is not indicated by the HTR
FAIL warning light.
Static Pressure Selector Valve
The pilot's and copilot's STATIC PRESSURE SELECTOR VALVES each have two
positions - STATIC TUBE and ALTERNATE SOURCE. The STATIC TUBE position is
the normal (guarded) position. In normal operation, the static ports are
used only to operate the cabin pressure indicator. When the pilot's STATIC
PRESSURE SELECTOR VALVE is set to the ALTERNATE SOURCE position, static
port pressure is also supplied to the air data computer instead of static
pressure from the pitot-static tubes. When the copilot's STATIC PRESSURE
SELECTOR VALVE is set to ALTERNATE SOURCE, the copilot's pneumatic flight
instruments receive static pressure inputs from the static ports instead of
the pitot-static tubes. The setting of the STATIC PRESSURE SELECTOR VALVE
does not affect the cabin pressure indicator, which always operates on
static port pressure.
Stall Protect Valve
The pilot's and copilot's STALL PROTECT valves each have STATIC NORMAL and
CLOSED positions. When a valve is in the STATIC NORMAL position, the
selected static source is directed to the stall transducer. When a valve
is set to CLOSED position, the selected static source is shut off from the
stall transducer.
Pitot Heat Failure Indicator
The pilot's and copilot's instrument panels each contain an amber PITOT
HEAT warning light. If the heater element in the pilot's or copilot's
pitot-static tube becomes defective, the associated PITOT HEAT warning
light comes on. The pitot-static tube warning circuits cannot be reset.
The PITOT HEAT warning lights also come on when the PWR & METER SELECT
switch on the A.D.S. HEATER CONT. panel is set to HTRS OFF.
SECTION 11
Page 4
Oct 03/83
canadair
chaiiencjer
OPERATING MANUAL
ATTITUDE REFERENCE SYSTEM (Figure 2)
Primary attitude reference is provided by two, electrically driven vertical
gyros. Gyro VG-1 supplies pitch and roll attitude data to the pilot's ADI and
flight director computer. VG-2 supplies pitch and roll attitude data to the
copilot's ADI and flight director computer. Each vertical gyro also produces a
validity signal which, if lost, causes the red ATT flag to come into view on
the associated ADI.
A. Gyro Fast Erect
The pilot and copilot each have a GYRO FAST ERECT switch/light for use when
a gyro is suspected of toppling or drifting. When the switch/light is
pressed, and the aircraft is within 6 degrees of level flight, the gyro
erects in 3 minutes.
B. Flight Director Switching Panel
The flight director switching panel has a CAPT FLT DIR switch with two
positions - NORM and NAV 2:
(1) NORM Position
Navigational information for the pilot's flight director is supplied
from the NAV 1 receiver.
(2) NAV 2 Position
Navigational information for the pilot's flight director is supplied
from the NAV 2 receiver.
HEADING REFERENCE SYSTEM (Figure 3)
The compass system provides primary heading data to the horizontal situation
indicators (HSIs), the radio magnetic indicators (RMIs), and the automatic
flight control system (AFCS). The data is provided by two flux
valve/directional gyro systems, corrected for the aircraft magnetic fields.
The output of gyro DG-1 supplies the pilot's HSI and the copilot's RMI, and
gyro DG-2 supplies the pilot's RMI and the copilot's HSI. This arrangement
ensures that both pilots receive heading information, even if one gyro system
in inoperative.
A. Compass Control Panels
Two compass control panels are provided, one for each system. Each panel
contains a mode switch and a slew switch. The compass control panel is
shown in Figure 3 (Sheet 1).
For aircraft 1021 and subs,
the compass control panel is shown in Figure 3 (Sheet 2 ).
SECTION 11
Page 5
Oct 03/83
cacnhaadiiaeinr tjer
OPERATING MANUAL
GYRO
FAST
ERECT
GYRO
FAST
ERECT
PILOT'S SWITCH/LIGHT
When pressed, erects gyro within 3 minutes,
if aircraft is within 6-degree level flight.
©
COPILOT'S SWITCH LIGHT
When pressed, wicn gvo within 3 minutes,
if aircraft is with»n 6 O0gr«e level flight. o
o5l
C A P T V §
FLT DIR
NORM
NAV 2
CAPT FLT r>* SWITCH
NORMAL
received fro**- * *
NAV 2
received fro^> NAV 2
^formation
rttcmation
Flight Director Switching Panel
Figure 2
SECTION 11
Page 6
Oct 03/83
canaaair
ctiaiienQer
OPERATING MANUAL
MODE SWITCH
Controls mode of operation of the system.
DG—Directional gyro in free mode.
SLAVED—Directional gyro controlled by flux
valve.
Displays synchronization error between the
flux valve heading and the gyro heading.
When system is synchronized, the pointer is
in the central position.
EFFECTIVITY: A/C 1004 TO 1020
SYNCH SWITCH
Switch is slewed to synchronize gyro with the flux valve.
Compass Control Panel
Figure 3 (Sheet 1)
SECTION 11
Page 7
Oct 03/83
cacnhaadiiaeinr qer
OPERATING MANUAL
MODE SWITCH
Controls mode of operation of the system.
DG - Directional gyro in free mode.
SLAVED - Directional gyro controlled by flux valve.
® COMPASS CONTROLS ®
DG
+ 11 i l l l )#
SLAVED
SYNCH SWITCH
Switch is slewed to synchronize gyro
with the flux valve.
EFFECTIVITY : A/C 1021

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CRJ200 Flight Deck Book

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庞巴迪挑战者飞行仪表