The correct statement regarding the pitot- static anti-ice system is: a) Electrical power is not required (if bleed air is available). b) The squat switch will not allow full power to the heating elements while the airplane is on the ground. c) Failure of one main system static port heater will illuminate the P/S HTR L–R annunciator. d) Electrical power is always available to the pilot’s system (fail safe operation of the emergency bus in the event of a dual generator failure).
Regarding the windshield anti-ice system: a) The W/S BLEED switch controls volume (HI or LOW). b) The W/S BLEED switch controls temperature. c) Electrical power must be available to open the solenoid control valve in the tail cone. d) Temperature is controlled by the WINDSHIELD BLEED AIR valves.
Regarding use of the W/S BLEED switch: a) HI position should be used with an OAT above –18°C. b) LOW position should be used with an OAT below –18°C. c) HI position should be used if greater airflow is desired. d) It deenergizes the solenoid control valve open when HI or LOW is selected.
If the W/S AIR O’HEAT light illuminates with the W/S BLEED switch in OFF, there is: a) 5-psi pressure sensed in the duct. b) 5-psi pressure buildup in the duct, and the light is to alert the pilot to open the WINDSHIELD BLEED AIR valve to relieve the pressure to prevent damage to the duct. c) A system malfunction; the light should never illuminate with the W/S BLEED switch in OFF. d) An overtemperature in the duct.
The W/S AIR O’HEAT light will illuminate: a) If 5-psi pressure is sensed in the duct with the W/S BLEED switch in OFF. b) If the temperature of the air going to the windshield is too hot (146°C) with the W/S BLEED switch in the HI or LOW position. c) Neither d) a and b.
In order to operate the rain removal sys-tem, the pilot should: a) Open the rain doors only. b) Open the rain doors, and turn on the W/S ALCOHOL switch. c) Open the rain doors, position the WINDSHIELD BLEED AIR knobs to MAX, and position the W/S BLEED switch to LOW. d) Open the rain doors, and position the W/S BLEED switch to LOW.
The windshield alcohol system: a) Is a back up system for the windshield anti-ice system. b) Energizes ejector swhitch apply alcohol to both the pilot’s and the copilot’s windshields. c) Utilizes a pump that supplies alcohol to the pilot’s windshield only for a maximum of 10 minutes. d) a and c.
The surface de-ice system: a) Should not be activated until ice thickness exceeds 1/2 inch. b) Should not be activated until ice thickness exceeds 1/4 inch. c) Will function during an electrical failure because it is pneumatically operated. d) Has a maximum ice accumulation limit of one inch.
Switching on both engine anti-ice systems in flight increases the reading on each of the generator ammeters by: a) 120 amps b) 300 amps c) 60 amps d) 150 amps.
Regarding the STBY P/S HTR light: a) It will illuminate if the PITOT & STATIC switch is OFF. b) Illumination of the light could mean a loss of electrical power to the standby pitot tube or a standby static port. c) If power is lost to all heated static ports on the standby system, the light will illuminate. d) A and B.
A correct statement concerning the surface deice system is: a) The SURFACE DEICE switch must be held in the SURFACE DEICE position for 12 seconds to ensure that all deice boots receive inflation pressure. b) The SURFACE DEICE switch must be cycled to RESET to reset the timer circuit after each use. c) The system should not be used below –40°C. d) Illumination of the white SURFACE DEICE annunciator after the SURFACE DEICE switch has been cycled to SURFACE DEICE indicates a lack of bleed air to the boots.
An incorrect statement regarding engine anti ice is: a) When the ENGINE ANTI ICE switches are turned on, the two green lights above the ignition switches should illuminate. b) The throttles must be above 60% N2 rpm before the wing leading edge anti- ice system is activated. c) The T1 temperature probe is anti-iced whenever the engine is operating. d) The ENG ANTI ICE LH–RH lights will illuminate steady when initially activating the system.
Switching on the engine anti ice system with the engines idling at 50% N2 causes: a) An increase in ITT, an increase in amperage, and illumination of the ENG ICE FAIL annunciators for at least five seconds. b) An increase in amperage only. c) A drop in N2 rpm and a rise in ITT. d) Illumination of the ENG ANTI ICE annunciators and an increase in amperage.
The ENG ANTICE annunciator will illuminate when: a) The wing leading edge temperature is below the low temperature switch setting (16°C/60°F). b) The nacelle temperature is too warm (above 104°C/220°F). c) The bleed-air valve to the nose cone (bullet) closes. d) The ENGINE ANTI ICE switch is in OFF.
|
