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

航空发表于 2010-5-8 08:01:11

Bombardier-Challenger_00-Flight_Instruments庞巴迪挑战者飞行仪表
 
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航空发表于 2010-5-8 08:01:22

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

dul 发表于 2011-2-11 15:21:31

MANUAL 8 MANUAL 8 MANUAL 8 MANUAL 8 MANUAL 8 MANUAL 8

ericgyf 发表于 2011-6-28 20:23:57

CRJ200 Flight Deck Book

bocome 发表于 2011-7-31 07:41:11

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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