Bombardier-Challenger_01-Ice_and_Rain_Protection庞巴迪挑战者防冰和防雨

航空发表于 2010-5-9 09:08:57

Bombardier-Challenger_01-Ice_and_Rain_Protection
 
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航空发表于 2010-5-9 09:09:11

canaaair cftanencjer OPERATING MANUAL PSP 601A-6 SECTION 14 ICE/RAIN PROTECTION TABLE OF CONTENTS 1. GENERAL 2. ICE DETECTION 3. WING ANTI-ICING A. General B. Operating Modes 4. ENGINE ANTI-ICING 5. WINDSHIELD AND SIDE WINDOW ANTI-ICING 6. ADS SENSOR ANTI-ICING Page 1 1 1 1 2 LIST OF ILLUSTRATIONS Figure Number Title 1 Anti-Iced Areas 2 Ice Detector Panel 3 Anti-Icing Ducts and Components 4 Wing and Engine Anti-Icing - Schematic 5 Anti-Icing Controls and Indicators 6 ADS Anti-Icing Controls and Indicators Page 3 4 5 6 7 8 14- Page 1 Apr
OPERATING MMUAL PS? 6Q1A-6 SECTION 14 ICE/RAIN PROTECTION 1. GENERAL (Figures 1 and 3) Ice and rain protection is provided by thermal and electrical anti-icing systems. Thermal anti-icing, using 14th stage engine bleed a i r , protects the wing leading edges and the engine cowlings- Electrical anti-icing is provided for the windshield and the various sensors of the air data system (ADS), including the stall protection system angle-of-attack sensors. 2. ICE DETECTION (Figure 2) Icing conditions are detected by two externally mounted ice detectors. The ice detectors consist of aerodynamic struts which hold sensing probes into the airstream. The sensing probe vibrates at a set frequency until ice accumulates to a point where the frequency starts to decrease. When the frequency decreases to a value which indicates the ice has reached a certain thickness, the ice detector sends a signal to the ice detector panel in the flight compartment. 3. WING ANTI-ICING (Figures 4 and 5) A. General The wing anti-icing system monitors the temperature of the wing leading edges and automatically controls, through an electronic wing anti-icing controller, the flow of engine bleed air to the wing leading edges to prevent icing. Left and right wing anti-icing modulating/shutoff valves direct 14th stage bleed air into wing anti-icing ducts running along each side of the underfloor area of the fuselage to the wing leading edges. Piccolo tubes, running the full length of each leading edge, discharge the air against the inside of the leading edge skin. The air then exhausts through louvers along the underside of the wing leading edge. The left and right sides of the wing anti-icing system are separated by a normally closed isolation valve. A control temperature sensor, a standby temperature switch and a sufficient heat/overheat sensor are fitted to the inside of each wing leading edge. These sensors monitor the leading edge skin temperature as required for automatic or standby control as well as for sufficient heat and overheat indications. SECTION 14 Page 1 Apr 02/87 cttaaienQer OPERATING MANUAL PSP 601A-6 B. Operating Modes In the NORMAL mode, the wing anti-icing controller uses the higher of the two temperatures sensed by the control temperature sensors and modulates both wing anti-icing valves to maintain the leading edge temperature at its optimum value for anti-icing. In the STANDBY mode, each standby temperature switch cycles its respective wing anti-icing valve open or closed to maintain the leading edge temperature within the maximum and minimum limits for anti-icing. ENGINE ANTI-ICING (Figures 4 and 5) Engine anti-icing is obtained by heating the leading edge of the nacelle nose cowl with 14th stage bleed air. The bleed air is ducted to each engine via l e f t and right pressure regulating/shutoff valves and enters a ring-shaped piccolo tube inside the nacelle nose cowl. The air discharges from the piccolo tube against the inside surface of the nose cowl leading edge, then exhausts through a louver in the nose cowl lower access panel. A pressure relief valve protects the engine cowl against bleed air overpressure. An engine anti-ice blowout plug, which is normally flush with the engine nacelle skin, extends when the valve operates to indicate that an overpressure relief has occurred and that maintenance action is required before the next flight. (Refer to Volume 1, WALKAROUND CHECK LIST for location.) The pressure regulating/shutoff valves are de-energized open. This feature causes the valves to fail open following an electrical failure. WINDSHIELD AND SIDE WINDOW ANTI-ICING (Figure 5) The windshields and side windows are of laminated construction and each has a thin heating element between the two outer laminations. The windshield and side window anti-icing system consists of the heating elements, temperature sensors, dual-channel temperature control units, and controls and indicators on the ANTI-ICE panel. The left and right sides of the system operate independently. Each side of the system has a dual-channel temperature control unit. Each unit monitors temperature signals from the same side windshield and side window. Two temperature sensors are provided for each windshield and side window, one for normal operation and one spare. ADS SENSOR ANTI-ICING (Figure 6) The ADS sensor anti-icing consists of heating elements in the left and right pi tot heads, left and right static ports, left and right angle-of-attack (AOA) vanes, and in the total air temperature (TAT) probe. Power to the elements is controlled by the ADS HEATER CONT panel in the flight compartment. SECTION 14 Page 2 Apr 02/87 canaaair ciianencier OPERATING MANUAL PSP 601A-6 TAT PROBE (RIGHT SIDE ONLY) PILOT STATIC HEADS AOA VANES STATIC PORTS WINDSHIELDS SIDE WINDOWS AIR INTAKES WING LEADING EDGES Anti-Iced Areas Figure 1 SECTION 14 Page 3 Apr 02/87 OPERATING MANUAL PSP 601A-6 SYS 1 AND SYS 2 FAIL LIGHTS Steady amber FAIL lights come on when built-in-test circuit detects fault in ice detection system 1 and/or 2. FAIL ights are also used K a press-to-test indication. ICE DETECTOR PUSH TO TEST FAIL FAIL EFFECTIVITY: NO 5001 TO 5134 ICE ACCUMULATION WARNING LIGHTS When ice detector sensor probe senses ice accumulation, SYS 1 and SYS 2 ember ICE fights flash. Lights go out when wing and engine entMcmg is selected on. ICE MONITOR LIGHTS Steady white ICE lights come on when wing ana engine anti-icing cs selected and remain on until ice detector fails to detect ice for 60 seconds. CENTRE INSTRUMENT PANEL Ice Detector Panel SECTION 14 Figure 2 Page 4 Apr 10/95 cacntiaaauaeirn Qer OPERATING MANUAL PSP 601A-6 Anti-Icing Ducts and Components Figure 3 SECTION 14 Page 5 Apr 02/87 challenger OPERATING MANUAL PSP 601A-6 STANDBY TEMP SWITCH (TYPICAL) CONTROL TEMP SENSOR (TYPICAL) SUFFICIENT HEAT/ OVERHEAT SENSOR (TYPICAL) OPEN/CLOSE SIGNAL WING ANTI-ICING MODULATING/I SHUTOFF VALVE (TYPICAL) ISOLATION VALVE TO ENGINE - COWL (TYPICAL) ENGINE ANTI-ICING REGULATING/SHUTOFF VALVE (TYPICAL) TO THRUST REVERSER (TYPICAL) HTH STAGE BLEED SHUTOFF VALVE (TYPICAL) A NOTE If open, valves are closed by thrust reverser operation infer to Section 17). Wing and Engine Anti-Icing - Schematic Figure 4 SECTION 14 Page 6 Apr 02/87 WING SWITCH Three-position switch controls mode of operation of left and right wing anti-icing modulatmg/shutoff valves. STANDBY - Moduiating/shutotf valves cycle open or dose to maintain wing leading edge within the minimum and maximum allowable temperatures. OFF - Modulating/srurtoff valves dosed. NORMAL - Anti-icing controller operates modulating/shutoff valves to maintain a constant wing leading edge temperature. L FAIL AND R FAIL LIGHTS Amber L FAIL or R FAIL light comes on if WING switch is set to STANDBY or NORMAL and tow pressure condition is detected in the associated wing anti-icing manifolds. Each light is inhibited when its associated HEAT light is on. L HEAT AND R HEAT SWITCH LIGHTS White L HEAT or R HEAT light comes on to indicate that temperature of associated leading edge is sufficient for effective anti-icing. When switch/light is pressed to test, correct operation of system control and monrtonng circuits is indicated when flashing WING ANTi- ICE. OVHT »tght on centre ^istrument panel and L HEAT. R HEAT. L FAIL. R FAIL and OVHT iights on ANTI-ICE panel ail come on. DUCT FAIL AND SENSOR FAIL LIGHTS Red DUCT FAIL light Refer :c Section 16 Amber SENSOR FAIL light comes on when controller detects an open temperature sensor in one of the overheat detection circuits. canaeSair ctiauencjer OPERATING MANUAL PSP 601A-6 COWL-LEFT AND RIGHT SWITCH/LIGHTS (2) Control operation of pressure regulating/shutof? valves of engine anti-icing system. When switch/lights are pressed in. valves deenergize and open. When pressed out. valves are energized and close. ON light - white light comes on when switch/light is pressed in or when associated pressure regulating/shutoff valve fails open FAIL light amber light comes on when switch/iight is pressed m and bleed air pressure is low or when switch/light is pressed out and associated pressure regulating/shutoff vaive fails open. WSHLD SWITCHES (2) Three-posit ion switches control same side wmoshteid and side window heating elements HIGH or LOW - Temperature control units maintain windshield and side window at constant temperature. At HIGH setting, controlled temperature of windshield is higher tharn controlled temperature at LOW setting Controlled temperature of side window >s the same at HIGH or LOW. OVERHEAD PANEL BUTTON WSHLD switches are set to HIGH, all four ircuits are tested when outton is Correct operation of the system is if an four green TEST lights come on s: one second. OVHT AND ISOL OPEN SWITCH/LIGHTS When pressed »n. anti-ice isolation valve opens and white ISOL OPEN light comes on. When pressed out. valve closes and light goes out. Red OVHT lignt comes on when an overheat condition is detected in the left or ngnt wing leading edge. NO HT LIGHTS 14) Amber NO HT hght comes on if associated temperature control unit detects an electrical fault m heating circuit. TEST LIGHTS t4) Green TEST itgnts come on during system test to tnoicated correct operation of associated heating circuit. WING ANTl-lCE.-OVHT LIGHT Flashing reC OVHT light comes on with OVHT light on ANTl-ICT panel when overheat condition exists on left or right leading eoge. When pushed to test, light comes on flashing. DUCT FAIL LIGHT Refer to Section 17. CENTRE INSTRUMENT PANEL Anti-Icing Controls and Indicators Figure 5 SECTION 14 Page 7 Apr 02/87 OPERATING MANUAL PSP 601A-6 HTR FAIL SWITCH/LIGHT Amber HTR FAIL light comes on if a heater fails in the left or right AOA vane, left or right static port, or the TAT probe. When pressed in, light goes out and system is reset to receive arty further failures. PWR fcr METER SELECT SWITCH Controls power to heating elements in the left and right pitot heads, left and right static ports, left and right AOA vanes, and the TAT probe. When set away from HTRS OFF, all heating elements are supplied. Also used to test individual heater elements. OVERHEAD PANEL HTR FAIL PUSH TO RESET % HTR CURRENT INDICATOR Indicates heater current in terms of percentage. Red zone indicates faBed system. PITOT HEAT LtGHTS (2) Amber PITOT HEAT tights come on to indicate failure of associated pitot static head heater. Pilot's light signals failure of left heater: copBot's light signals failure of right heater. PILOTS AND COPILOT'S INSTRUMENT PANELS ADS Anti-Icing Controls and Indicators Figure 6 SECTION 14 Page 8 Apr 02/87

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Bombardier-Challenger_01-Ice_and_Rain_Protection庞巴迪挑战者防冰和防雨

MANUAL 8