Brasilia Cockpit

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salisbury.r
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110277
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Brasilia Cockpit
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2012-03-18 13:23:47
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Brasilia Cockpit
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Brasilia Cockpit
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  1. Inverter INOP light
    Indicates when the respective inverter has been switched off or has failed.
  2. Number 1 inverter 115 VAC BUS OFF light
    The respective AC bus is not powered.

    If the 115 VAC output from inverter 1 fails the system automatically switches to inverter 2, which will supply all AC buses.
  3. Number 1 26 VAC BUS OFF light
    The respective AC bus is not powered.

    If the 26 VAC output from inverter 1 fails the system WILL NOT automaticly switch to inverter 2.

    Inverter 1 switch must be turned OFF to allow inverter 2 to supply all AC buses.
  4. Why must inverter 2 be turned ON and OFF before inverter 1?
    Inverter 2 must be turned ON and OFF first to ensure that it is capable of supplying the AC buses since it normally remains in powered standby.
  5. AUX GEN OFF BUS lights
    Indicates that the respective aux gen contactor is open.
  6. EMERG BUS OFF light
    Illuminates when one or both of the emergency buses are not powered.
  7. BUS 1 OFF or BUS 2 OFF light
    Illuminates when the respective DC bus is not powered.
  8. CENTRAL BUS OFF light
    Indicates that no power is being supplied to the Central DC bus.
  9. GEN OFF BUS light
    Indicates that the respective generator contactor is open and the gen is isolated form its respective bus.
  10. BATT OFF BUS light
    Indicates that the battery contactor is open and the battery is disconnected from the Central DC bus.
  11. TRANSFER FAIL light
    Indicates that the auxiliary transfer contactor failed to change position during autotransfer.

    The autotransfer sequence is not complete and the battery is being depleted and the normal buses are still shed.
  12. Which lights DONT test with the ALARM LIGHTS TEST?

    LPGAFEBBL
    • Landing Gear
    • Parking Brake "ON" light
    • GPU AVAILABLE light
    • APU fire lights
    • Flap bar indicators
    • Engine fire lights
    • Back-up battery "ON" light
    • Baggage Smoke/ Fire lights
    • Low speed alarm light
  13. Which lights WILL NOT dim with the ALARM LT switch?
    • Red alarm lights
    • Back-up battery "ON" light
    • Master WARNING and CAUTION lights
  14. FORWARD ACTUATOR light
    Illuminates when the main door solenoid fails in the open position and indicates a hydraulic lock in the main door.

    A pressure relief valve is located in the cockpit below the center pedestal in front of the jumpseat.

    A maintenance relief valve is located in the forward hydraulic compartment.
  15. SERVICE door light
    Indicates that either the avionics door, control rigging door or one or both of the fuel doors may not be closed properly.
  16. CARGO door light
    Indicates that the cargo door may not be closed properly.
  17. FORWARD door light
    Indicated that the forward main entry door may not be closed properly.
  18. EMERG LT in OFF
    The battery packs receive 28 VDC from the Emergency DC Bus 1.
  19. EMERG LT in ARM
    The battery packs charge off of Emergency DC Bus 1.

    If the Emergency DC Bus 1 fails, the emergency lights are automatically connected to the battery packs.

    The battery packs can keep the lights illuminated for 17 minutes.
  20. EMERG LT in ON
    Power form the Emergency DC Bus 1 is cut off and the lights are connected to the battery packs.

    The battery packs can keep the lights illuminated for 17 minutes.
  21. Landing lights
    The left light is powered by Emergency DC Bus 2 to ensure lighting is available during and electrical emergency condition.

    The right light is powered by DC Bus 2.
  22. Taxi lights
    One lamp is a wide beam and the other a narrow beam.

    A landing gear proximity switch provides an enable signal to respective RCCB to close and energize the taxi light circuit.

    The taxi lights are powered by DC Bus 1.
  23. Nav lights
    Powered by DC Bus 2.
  24. Rotating Beacon lights
    These 100-candle power lights and rotating platforms are powered by DC Bus 2.
  25. Strobe lights
    Should be off while on the ground as a courtesy to other aircraft.

    May be turned off while in clouds to prevent vertigo.

    Powered by DC Bus 1.
  26. Wing inspection lights
    Can also be used to inspect main landing gear at night.

    Lights are installed on either side of aircraft nose pointing rearward.

    Powered by DC Bus 2.
  27. Logo lights
    Mounted in the underside of the horizontal stabilizer to illuminate the vertical fin.

    Powered by DC Bus 3.
  28. No Smoking and Fasten Seatbelt signs
    Activation of the PAX SIGNS sounds a single chime through the PA and is powered by radio master DC Bus 1A.

    The lighted signs are powered by Emergency DC Bus 2.
  29. APU: START CONTACTOR light
    Illuminates when the APU start relay is energized.

    At 50% RPM the ECU disengages the starter and the light extinguishes.
  30. APU: oil LOW PRESS light
    Illuminates when oil pressure drops below 31 psid.

    APU will also illuminate on the MAP.
  31. APU: HIGH TEMP light
    Illuminates when the oil temp exceeds 163oC .

    A thermostat sends a signal to the light overhead and to APU on the MAP.
  32. APU: :fuel LOW PRESS light
    Illuminates when fuel in the APU fuel line drops below 9 psi.

    A pressure switch in the fuel line sends a signal to the light overhead and to APU on the MAP.
  33. APU: CLOSED fuel shutoff light
    Illuminates when the fuel shutoff valve in the right wing is fully closed.

    Verify that CLOSED light is extinguished when starting APU, otherwise, no fuel will be introduced during the starting sequence.
  34. APU: STOP button
    Shuts down the APU by sending an electronic, 110% overspeed signal to the ECU fault protection circuit.
  35. APU: START/MASTER SWITCH
    START- Initiates the automatic start cycle.

    ON- Applies power to the ECU and opens the fuel shutoff valve.

    OFF- De-energizes the ECU and APU panel. Closes the fuel shutoff valve.
  36. APU: BLEED SWITCH
    OPEN- After 95% and 4 seconds the bleed switch may be opened to allow APU bleed air to enter the pneumatic system.

    CLOSED- APU bleed air valve closed. Bleed valve will close automatically when APU falls below 95% RPM or when the APU is supplying the same pack as the engine (Priority of Air).
  37. APU: DUCT LEAK light
    Illuminates when temperature sensors located along the lines sense temperatures of 71oC or greater. Also, DUCT LEAK will illuminate on the MAP and "DUCT LEAK" will be heard.
  38. APU: GEN SWITCH
    RESET- Used to reset the generator GCU when it falls off line. Spring loaded to the ON position.

    ON- Connects the APU generator to the Central DC bus.

    OFF- Disconnects the APU generator from the Central DC bus.
  39. APU: GEN OFF BUS light
    Illuminates when the generator is disconnected from the Central DC bus.
  40. APU: SHUTOFF/EXTG switch
    EXTG- Discharges the fire extinguishing agent into the APU compartment.

    • CLOSE- BADFO
    • Bleed air valve closes
    • Arms fire extinguisher
    • De-energizes APU panel
    • Fuel shutoff valve closes
    • Opens Gen contactor

    ON- Normal operating position
  41. APU: fire det FIRE light
    Illuminates when an overheat or fire condition is sensed by the APU fire detector. Also, FIRE APU will illuminate on the MAP

    Light will remain illuminated until the condition is eliminated.

    Light will illuminate during the main fire system test.



  42. APU: fire det INOP light
    Illuminates when the inert gas is lost from the detector plumbing.

    APU will also illuminate on the MAP.

    Light will also illuminate during the main fire system test.
  43. APU: bottle ABLE light
    Will only illuminate during the main fire system test if the bottle firing circuits are intact.
  44. APU: bottle INOP light
    Illuminates when the bottle is empty or inadequately pressurized below 275 psi.

    Light will also illuminate during the main fire system test.
  45. fuel FILTER light
    Illuminates when the pressure differential has reached 1.5 psid across the low pressure filter and or 25 psid across the high pressure filter.

    The filters bypass at 3 and 50 psid respectively to allow continuous fuel flow to the HMU.

    FUEL will also illuminate on the MAP.
  46. fuel LOW TEMP light
    Will illuminate when the fuel temperature drops into the freezing range.

    FUEL will also illuminate on the MAP.
  47. fuel LOW PRESS light
    Will illuminate when the fuel pressure drops below 9psi.

    During engine starting, a relay inhibits the low pressure warning circuit due to low electrical output.
  48. fuel crossfeed OPEN light
    Illuminates when the crossfeed valve has reached the fully open position.

    When in the open position, an electric boost pump must be in the ON position because when the crossfeed valve is open the motive flow valves close.
  49. Electric fuel boost pump ON light
    Will illuminate when the pump is selected to the ON position or in AUTO position and the fuel pressure drops below 9 psi, turning on the pump momentarilty until the pressure is above 9 psi then it shuts off (pinball effect).

    Provides a flow of 1800 pph or 20 psi.
  50. ELEC FEATTHER switch
    Actuates the electric feathering solenoid and the electrical auxiliary feathering pump to feather the prop and cancel Np fuel governing.

    • For the aux pump test, FFOD;
    • Prop Aux Pump will run for 20 seconds to prevent pump overheating.

    The pump is limited to 6 consecutive cycles because the Aux Oil Tank may be empty.

    If more actuation's are required and the Aux Oil Tank is empty; dry motoring the engine may be required to replenish the tank.
  51. Auto feather ARMED light
    • Will illuminate when:
    • 1. Auto feather switch ON
    • 2. Both power levers above 62o PLA
    • 3. Both engine torque above 62%

    • Indicates that the auto feather system is ready and if the torque on either engine drops below 22%:
    • 1. ARMED light extinguish
    • Then .5 sec delay
    • 2. Operating engine auto feather will be disabled
    • 3. Failed engine prop will feather
    • 4. Failed engine Np fuel governing is canceled
  52. PROP SYNC switch
    Utilizes a microprocessor with pulse generator input to direct an increase/ decrease command to the right PCU.

    The left prop is the master and the right prop is the slave.

    The synchrophaser only operable between 80-100% Np and 2.5% Np between either prop.
  53. EEC MANUAL light
    Illuminates when power rating selector to manual position or when EEC reverts automatically to manual mode.
  54. EEC POWER RATING SELECTOR knob
    Programs the EEC, which affects the fuel flow to the engine.

    The EEC software contains reference curves for Np and Nh versus PLA. Then provides a signal to the torque motor in the HMU to vary engine fuel flow.

    Note: Since the torque bugs are disabled, there is no difference between TO, CL, CR positions.
  55. Ignition Control Switch
    ON- Ignition circuit remains energized.

    AUTO- Automatically energized when the starting cycle is initiated. Circuit automatically deenergized when Nh reaches 50% (+/- 6%) by the GCU.

    • OFF- Ignition circuit is continuously deenergized.
    • Used for:
    • 1. Dry motoring, to replenish RGB Aux Oil Tank
    • 2. Clear engine after a wet start
    • 3. Lower T6 temps after a hot start
  56. IGNITION light
    Illuminates when ever the ignition circuit is energized.
  57. Engine START switch
    ON- Signals GCU to close the start contactor and initiate the start sequence until the GCU receives a signal from the Nh sensor at 50% Nh.

    ABORT- Simulates 50% Nh signal to the GCU and canceles the start sequence.
  58. Flap Annunciator Panel
    Provides a digital indication of the actual position of the flaps and the commanded position of the flap lever.

    Each light bar represents 5.625o of flap.
  59. Flap RST button
    When pushed, resets all memories and faults, initializes all systems and restart automatic control.
  60. Flap CFD button
    Stops the flashing of the light bars during a flap malfunction.
  61. Flap BIT button
    Initiates the system self test.

    • A successful test is:
    • 1. Illumination of all light bars on the overhead annunciator panel.
    • 2. CONTROL FAULT on the supplementary flap panel.
    • 3. FLAP and ADVANCED SWS on the MAP.
    • 4. Indication on the analog position indicator above the 0o mark.
  62. Rudder INOP lights
    Illuminates to indicate a failure in the rudder hydraulic system when the airspeed is below 120kts.

    At speeds above 120kts, a single rudder failure WILL NOT trigger the INOP light. If both rudder systems fail, BOTH INOP lights will illuminate.
  63. Rudder OVERBOOST light
    Above 120kts, only one (blue) hydraulic system is powering the rudder, to prevent over-stressing of the airframe.

    OVERBOOST will illuminate to indicate a failure of the green system to shut down above 120kts.
  64. Flap Warning ASYMMETRY
    Asymmetry is defines as a different degree of extension WITHIN a flap pair.

    ASYMMETRY will illuminate when a pair of flaps position differ by more than 7o.

    The affected flap pair will be disengaged from the automatic control.

    When directed by the checklist, using the override switch, the good flap should be driven to the bad flap.
  65. Flap Warning DISAGREEMENT
    DISAGREEMENT will illuminate when a position difference exists between two or more pairs of flaps and that difference is greater than 7o.

    The system will take no automatic corrective action.
  66. Flap Warning CONTROL FAULT
    • Will illuminate when there is a failure in:
    • 1. Any of the three control unit channels
    • 2. The annunciator panel
    • 3. The selector lever

    If the CF is detected in the control unit, the affected flap pair is disengaged from automatic control.

    All three flap pairs are disengaged when the failure is detected in the annunciator panel or the selector lever (all light bars flash).
  67. Brake Line Pressure INBOARD and OUTBOARD, left and right lights
    Each light represents each main gear brake line.

    All four lights will illuminate when the TEST buttons are pressed and the toe brakes are depressed.

    The test is verifying brake line integrity and available brake line pressure is above 300psi.
  68. Anti-skid INOP lights
    • Will illuminate when:
    • 1. An anti-skid control switch is in the off position
    • 2. A servo valve or transducer failure
    • 3. Pressure to the brakes is reduced for more than 1.5 seconds.

    The INOP lights will only illuminate when the gear lever is in the DOWN position.
  69. Emerg/Parking Brake LOW PRESS light
    Illuminates when the pressure in the nitrogen side of the brake accumulator is less than 1500psi.
  70. Ice Detector INOP light
    The Ice Detection System is automatically turned on with the plane and remains on for the duration.

    The INOP light will illuminate when the Ice Detection System fails.
  71. Hydraulic Reservoir LOW PRESS light
    Illuminates when the bleed air pressure drops below 12psi in the related reservoir.
  72. Hydraulic Reservoir LOW LEVEL light
    Illuminates when the fluid level drops below .8 liters in the related reservoir.
  73. Hydraulic MAIN PUMP LOW PRESS light
    Will illuminate when the hydraulic pressure, generated by the engine-driven pump, drop s below 1500psi.

    The light will extinguish when the main pump pressure increases to 1950psi.
  74. Hydraulic ELEC PUMP light
    Will illuminate when the respective electrical hydraulic pump is operating.
  75. Hydraulic FLUID OVERHEAT light
    Illuminates when the fluid temperature in that respective side reaches 120oC.

    Light will extinguish when the temperature decreases to 110oC.
  76. Hydraulic Pump Switch
    Off- Is off

    Auto- The respective electric hydraulic pump will come on if the engine driven pump output drops below 1500psi.

    On- The respective electric hydraulic pump is turned on. The electric pump will supply working pressure but the MAIN PUMP LOW PRESS light will remain illuminated.
  77. Hydraulic FILTER light
    The engine-driven, electrical and the primary return lines each have a separate filter.

    The light will illuminate when any one of the three filters are bypassed.
  78. Leading Edge Deicer INOP lights
    Will illuminate if a boot does not inflate (less than 16psi at the pressure switch) or remains inflated beyond 6 seconds.

    The NORMAL light will extinguish and the respective INOP light will illuminate where the fault occurred.
  79. Leading Edge Deicer NORMAL light
    Indicates that the system is operating normally.
  80. Leading Edge Deice Timer Switch
    Timer 1 and 2 are the same timer, the #2 is a standby.

    The boots are actuated in a sequence to minimize bleed air losses and prevent aerodynamic asymmetry.

    • Time sequence:
    • 1. OUTBOARD wings
    • 2. MIDDLE wings
    • 3. INBOARD wings and INBOARD horizontal stabilizer
    • 4. OUTBOARD horizontal stabilizer and VERTICAL FIN

    One complete cycle of the deice system is 1 minute; 6 seconds inflated, 54 seconds deflated.
  81. Propeller Deice INOP lights
    • The respective INOP light will illuminate when:
    • 1. An under current of 35 amps occurs
    • 2. An over current of 50 amps occurs
    • 3. Prop-deice switch is on and oil pressure is below 40psid.
  82. Propeller Deice NORMAL light
    Indicates that the system is operating normally.
  83. Propeller Deice Timer Switch
    Timer 1 and 2 are the same timer, the #2 is a standby.

    When selected to either timer the brush blocks transfer electrical current to the slip rings which are connected to the propeller blades.

    Power is supplied to opposite blades to ensure propeller balance.

    • Propeller heating sequence:
    • Left propeller blades 1 and 3, Right propeller blades 1 and 3.
    • Left propeller blades 2 and 4, Right propeller blades 2 and 4.

    Over heat damage protection on the ground is provide by the 40psid engine oil low pressure switch.
  84. Propeller Deice COLD/NORM Switch
    Selects a different propeller deice duration.

    NORM- Used when the OAT is above -10oC. 10 seconds on, 60 seconds off.

    COLD- Used when the OAT is below -10oC. 20 seconds on, 60 seconds off.
  85. Eng Air Inlet Deice INOP lights
    Will illuminate when a boot does not inflate (less than 16psi at the pressure switch) or remains inflated beyond 6 seconds.
  86. Eng Air Inlet Deice NORMAL lights
    Indicates that the system is operating normally.
  87. Deice Monitor INOP light
    Will illuminate when any fault occurs in the monitor.
  88. Deice Monitor Switch
    Spring loaded to the ON position which provides a constant operational check of all the deice (leading edges, props, engine inlet, and indicator lights) systems.

    When the aircraft is energized, the monitor is on. Therefore, even when a specific deice system is not on it is still being monitored.

    The TEST position checks all the deicing system lights and the monitor.
  89. TAT INOP light
    Will illuminate when the total-air temperature (TAT) anti-icing heater element should fail.
  90. Pitot/ Static INOP lights (3).
    Are illuminated whenever the three Pitot/ Static switches are in the OFF position (required by FAR Part 25) or when a heater failure occurs.
  91. Pitot/ Static Switches
    • Controls the heating elements for:
    • 1. Pilots pitot/ static heater,
    • 2. Co-pilots pitot/ static heater and the pneumatic outflow valve static port heater,
    • 3. The auxiliary pitot/ static heater and the electro-pneumatic outflow valve static port heater
  92. Slip INOP light
    Will illuminate whenever the anti-icing heater fails.
  93. Slip Switch
    Controls the heating element for the slip/skid vane.
  94. AOA Sensor INOP lights (2).
    Will illuminate whenever its related anti-icing heater fails.
  95. AOA Sensor Switches
    The left switch controls the heating element for the pilots AOA vane and the right switch controls the heating element for the co-pilots AOA vane.
  96. Windshield Wiper Knobs
    Controls the respective windshield wiper operation.
  97. Windshield INOP lights
    Will illuminate when the respective heater fails.
  98. Windshield ON lights
    Will illuminate when the windshield heat is on and operating normally.

    Light will extinguish when the window temperature gets to 45oC with the switch in the ON position.
  99. Windshield ON/OFF Switches
    Controls the heater elements in the respective windshield.

    The window controller will maintain a temperature between 40oC and 45oC with an overheat limit of 55oC.
  100. Windshield LEFT/RIGHT TEST Switch
    When held to either side (L/R) tests the overheat circuit, basically simulating an over temp of 55oC.
  101. Pneumatic DUCT OVERHEAT light
    Will illuminate when the air coming out of the respective pack is too hot (245oC).
  102. Pneumatic Temperature Selector Knob
    Used to adjust the temperature of the cockpit or cabin trough the respective temp controllers.
  103. Cockpit Temperature Mode Selector Switch
    AUTO- This mode uses signals given the ambient, skin, and duct temperature sensor. This information is sent to the Temperature Controller which adjusts the Temp Control Valve to maintain the selected temperature.

    MAN- In this mode the ambient, skin and duct sensors are bypassed and the temperature control knob is directly connected to the Temp Control Valve. This is usually used in the event of an automatic temp controller failure.
  104. Cabin Temperature Mode Selector Switch
    AUTO- This mode uses signals given the ambient, skin, and duct temperature sensor. This information is sent to the Temperature Controller which adjusts the Temp Control Valve to maintain the selected temperature.

    MAN- In this mode the ambient, skin and duct sensors are bypassed and the temperature control knob is directly connected to the Temp Control Valve. This is usually used in the event of an automatic temp controller failure.

    CAB ATT- Same operation as AUTO mode however the FA can select the temperature from her temperature selector.
  105. W/S DEFOG Switch
    ON- Opens a diverter that directs air from the cockpit air vents to the windshield defogger ducts.

    OFF- Diverter is closed, allowing maximum airflow to the cockpit vents. If no air is coming out of the cockpit vents, the W/S DEFOG switch might be in the ON position.
  106. RECIRC Fan Switch
    HIGH- Fans operate at maximum output.

    LOW- Fans operate at a lower output.

    OFF- Fans are off.

    If a pack is inoperative select the recirc fan on operative side to HIGH or LOW and OFF on the inoperative pack side.
  107. GASPER Switch
    MIX- The shutoff valve will be open and the gasper fans will operate on low speed.

    AUTO- With a duct temp of +75oC the shutoff valve will close and the gasper fan will operate on high speed. With a duct temp of -75oC, the shutoff valve will open and the gasper fan will turn off.

    OFF- Shutoff valve will remain open, gasper fans will be off and any airflow will be from the duct only.
  108. PACK FAIL light
    Will illuminate when the temperature of the pack reaches 425oC. When this occurs, the PRSOV will automatically close illuminating PACK FAIL.

    • Possible reasons for pack failing:
    • Ground
    • Exesive temps in the pack due to high ambient temps
    • Too warm a temp selected for conditions
    • Ground cooling fan failure or air ground switch failure
    • Bleed overheat

    • In flight:
    • Too warm a temp selected for conditions
    • Heat Exchanger failure
    • HI mode selected on pack
    • RAM AIR INLET open
    • Bleed overheat
  109. Pack Control Selector Knobs
    HI- Used only in cold conditions when cabin temperatures cannot be maintained above 19oC, but only inflight. A PRSOV regulates the pack pressure to 24psi. If the engine bleed is in AUTO, it also opens up the P3 bleed to supply high temperature bleed air.

    NORM- The PRSOV regulates pressure to between 15 and 35psi depending on temperature demand.

    LOW-Used for takeoff and approach to minimize bleed air extraction to conserve engine power. The PRSOV regulates pressure to 15psi.

    OFF- The PRSOV is fully closed.
  110. RAM AIR INLET Switch
    OPEN- The NACA inlet will direct air into the cabin distribution system (for unpressurized flight only). With the packs operating and RAM AIR INLET OPEN will cause a pack fail.

    CLOSE- The NACA inlet will direct air to the pack heat exchangers.
  111. DUCT LEAK light
    Indicates a bleed air leak in the bleed air duct. Sensors are located close to each duct interconnection and are activated if the temperature reaches 71oC.

    Light indicates a possible rupture of a bleed air line. Follow QRH for procedures. Must consult with maintenance control for permission to relight an engine.
  112. BLEED OVERHEAT Light
    Will illuminate when the temperature in the bleed duct reaches 600oF and the bleed air shutoff valve automatically closes.
  113. CROSSBLEED Valve OPEN Light
    Indicates the position of the crossbleed valve. The valve allows bleed air from either engine or APU to feed either right or left pneumatic system.

    The valve is electrically controlled and pneumatically actuated. If no pneumatic air is available the crossbleed valve will not open.
  114. Engine Bleed Shutoff Switch
    This switch actuates a valve located between the engine bleed and the crossbleed manifold.

    The valve is used to isolate an engine bleed supply in the event of a malfunction or for performance reasons.

    The valve is electrically controlled and pneumatically actuated. In auto-transfer, the valve will be de-energized and closed, causing a loss of pressurization.
  115. PEDAL STEER INOP lights
    Indicates when the nosewheel steering is inoperative.

    • Will illuminate when:
    • 1. Either of the rudder pedal disengage triggers are pulled
    • 2. The nose wheel angle is greater than 9o with the tiller disengaged.
  116. Master WARNING lights
    They direct the crew attention immediately to an alarm condition and allow the degree of importance to be immediately assessed.

    Red WARNING alarm lights advise of an emergency condition or fault usually requiring immediate action.
  117. Master CAUTION lights
    They direct the crews attention immediately to an alarm condition and allow the degree of importance to be immediately assessed.

    Amber CAUTION alarm lights advise of an abnormal condition requiring attention.
  118. EEC 1 or EEC 2 lights
    Illuminates when any failure is detected on respective EEC or on HMU enrichment solenoid valve.
  119. IDLE UNLK lights
    Our planes are equipped with electrical Flight Idle stop device that prevents power levers to be moved below FLT IDLE inflight.

    Lights will illuminate when the flight idle stop device is not operational inflight. This may be caused by a failure of an air/ground switch on the main gear or failure of the solenoid itself.
  120. BETA lights
    Illuminates when the propeller pitch drops to 12.6o. The low blade angle switch senses this condition, illuminates the BETA light, and activates the electric feather solenoid to increase blade angle toward feather.

    A BETA light flashing inflight indicates that the primary low pitch stop has failed.

    BETA lights on while on the ground is acceptable because the primary and secondary low pitch stops are inhibited when power levers are below flight idle.
  121. FIRE ENG/WW or FIRE PIPE ZONE lights
    The engine and wheelwell fire detection system consists of three fire/overheat detectors for the engine, wheelwell, and pipezone along with two control modules.

    The detectors sense an increase in temperature or pressure above normal. Gas expansion inside the tube closes a pressure switch in the dual responder and sends a signal to the control module.

    The appropriate lights will illuminate when the control module receives a signal from the dual responder indicating an overheat or fire condition exists.
  122. DET INOP ENG/WW or DET INOP FIRE PIPE ZONE lights
    Will illuminate if the inert gas in the sensor tubes leaks out or if one of the detectors fails.
  123. Bottle ABEL lights
    Will illuminate only when the testing the fire system if the integrity of the extinguisher bottles and squibs are in proper firing order.
  124. Bottle INOP lights
    Each bottle is pressurized to 600psi.

    The INOP lights will illuminate when the respective bottle is empty or the pressure falls below 275psi.
  125. Fire System TEST Button
    Tests the integrity of all of the extinguisher bottles and their squibs.

    If pressed for more than 10 seconds, without canceling will shutdown the APU.
  126. FUEL and HYD CLOSED lights
    Illuminate when the respective fuel or hydraulic shutoff valves are fully closed.
  127. Fire Handel 1 or 2

    FAHEED
    • When the fire handle is pulled:
    • F- Fuel shutoff valve closes
    • A- Autofeather
    • H- Hydraulic shutoff valve closes
    • E- Engine bleed valve closes
    • E- Extinguishers arm on both sides
    • D- Deice flow control valve closes

    To discharge the extinguisher agents, rotate handle left to select Bottle A and right to select Bottle B.
  128. Baggage Smoke Fire Ext TEST 1 and 2
    TEST 1- ABLE, INOP and red WARN lights will illuminate along with 3 chimes, aural warning 'SMOKE' and SMOKE on the MAP.

    TEST 2- Red WARN light illuminates along with 3 chimes, aural warning 'SMOKE' and SMOKE on the MAP.
  129. Baggage Smoke Fire Ext ABLE light
    Indicates normal operation of the firing circuits in both bottles.

    Will only illuminate when TEST 1 is performed.
  130. Baggage Smoke Fire Ext INOP light
    Will illuminate when an extinguisher has low pressure or empty or when TEST 1 is performed.
  131. Baggage Smoke Fire Ext WARN light
    Indicates smoke in the cargo compartment. Will remain illuminated as long as smoke is present.

    When pressed, releases the extinguishing agents from both bottles into the cargo compartment.

    One bottle is a high-rate discharge and is intended to fill the cargo are immediately. The second bottle is a metered-discharge and will continue to discharge over a period of 60 minutes.
  132. Back-up Battery ON light
    Illuminates when the Back-up Battery Switch is held in the TEST position.
  133. Back-up Battery Swtich
    OFF- Off

    ARM- Must be armed for all engine and APU starts. Provides a stable power source for sensitive electronic equipment.

    TEST- Simulates that the Emerg DC Bus 1 has fallen below 19v, and the ON light illuminates.

    DO NOT hold the switch in the TEST position for more than 7 seconds or the Flight Idle Stop circuit breakers will pop.
  134. EFIS Control Panel Composite Mode Switch
    EADI- Causes the EHSI information to display compositely with the EADI on the upper CRT.

    OFF- The EADI and EHSI are displayed normally

    EHSI- Causes the EADI information to to display compositely with the EHSI on the lower CRT.
  135. EFIS Control Panel Display Source Switch
    NORM- Information to the two CRTs is provided by the respective DPU.

    XFR- If the DPU fails, this switch allows information from the MPU to be displayed on the affected CRTs.
  136. EFIS Control Panel XFR light
    Illuminates when the Display Source is in XFR mode.
  137. EFIS Control Panel AHRS ATT and HDG Switches
    NORM- Allows the attitude or heading information to be driven from the respective AHRS.

    XFR- Allows the attitude or heading information to be driven from the opposite AHRS.
  138. EFIS Control Panel VOR CRS DEV Switch
    ANG- When selected CDI deflection is 2o per 1 dot.

    LIN- CDI displacement is NOT 2o per 1 dot.
  139. GPU AVAILABLE light
    Is powered by the external power source and will illuminate when the ground power is plugged in and supplying power.
  140. PAX OXYGEN Switch on center pedestal
    OFF- Deenergizes the passenger system.

    AUTO- Automatically drops the oxygen masks when cabin altitude exceeds 14,000' and also opens the PAX OXYGEN shutoff valve allowing oxygen to flow to masks.

    MAN- Drops the masks regardless of cabin altitude and also opens the PAX OXYGEN shutoff valve allowing oxygen to flow to the masks.
  141. PAX OXYGEN ON light
    Will illuminate when the oxygen system is pressurized after the masks have dropped.
  142. PAX OXYGEN Switch on the co-pilots side panel
    OFF- Closes the oxygen shutoff valve.

    AUTO- Allows oxygen to pressurize the system automatically at cabin altitudes above 14,000'.

    MAN- Manually opens the oxygen shutoff valve regardless of cabin altitude.
  143. Pressurization Mode Selector Switch
    AUTO- Selects the automatic mode of operation via the Electronic Controller, and utilizes both electro-pneumatic and pneumatic outflow valves.

    MAN- Selects the manual mode of operation via the Manual Controller and uses only the pneumatic outflow valve.

    DUMP- Depressurizes the cabin. The cabin altitude limiter will limit the cabin altitude to 13,000' if at least one pack is operating. If no packs are operating the cabin will climb to the aircraft altitude.
  144. Presurization Manual Controller Knob
    Used in the event of an automatic mode failure or electrical power failure.

    The manual controller should be placed to the 1 o'clock position before switching from AUTO mode to allow enough time for the pneumatic outflow valve to reach the neutral position.

    The manual controller is not provided with a scale system so you must monitor the triple indicator for desired rate of climb/descent.
  145. Pressurization Electronic Controller
    Electronically controls a torque motor that opens or closes the electro-pneumatic outflow valves.
  146. Pressurization ALT SET Knob and Scale
    ALT SET Knob selects the cabin altitude versus selected flight level.

    When setting the pressurization for cruise (say FL270) on the inner scale, this will result in a cabin altitude of 5,600' on the outer scale.

    When setting the pressurization for landing, set it to 300' below field elevation on the outer scale.
  147. Pressurization RATE SET Knob
    Selects the cabin rate of climb or descent in automatic mode.

    DETENT- Sets a 650 ft/min climb and 450 ft/min descent.

    FULL CLOCKWISE- Sets a 1450 ft/min climb and 1000 ft/min descent.

    FULL COUNTERCLOCKWISE- Sets a 200 ft/min rate of climb and 150 ft/min rate of descent.
  148. Pressurization BARO SET Knob
    Allows the adjustment for varying barometric pressures. Set either the field pressure or 29.92 at cruise in the flight levels.
  149. Stall Warning SYS 1 or SYS 2 ON/OFF Switch
    The red guarded switch allows the pilot to disconnect a malfunctioning computer from its respective shaker and pusher.
  150. Stall Warning TEST Buttons
    The red TEST buttons are illuminated red whenever power was taken away from the plane and until the test is completed.

    When pressed, the fast/slow indicator will move from fast to slow, then the respective shaker will activate followed by the pusher.

    The pusher is inhibited above 173kts and reactivated below 155kts.
  151. SWC ICE MODE light
    The stall warning computer has a feature in which it will reset the shaker and pusher angles during ice conditions. The purpose is to increase the speed between stick shaker and stick pusher when in icing conditions.

    Will illuminate when ICE CONDITION is detected by the ice detector and or when the leading edge deicers are turned on.
  152. Landing Gear Electrical Override Switch
    NORMAL- Allows for normal operation of the landing gear.

    DOORS- Energizes the gear wheelwell doors solenoid valve, allowing the hydraulic circuit to open the gear doors.

    GEAR/DOORS- Energizes both the gear door solenoid valve and the landing gear actuating solenoid valve. The gear is hydraulically lowered and the doors stay open.

    In order for the Electrical Override to work, Emerg DC bus 1 must be operative and the Green hydraulic system must be available.
  153. Landing Gear Freefall Extension Valves
    There are four mechanical assemblies, the forward right valve is connected to the emergency selector valve the others are connected directly to their respective uplock hooks.

    Actuating the forward right valve essentially depressurizes the landing gear system. Then, with the gear handle in the UP position, actuating the remaining valves releases the respective uplock hooks and allows the weight of the gear to push open the gear doors.

    When each gear is down and locked the red disagreement lights will remain illuminated until the gear handle is returned to the DOWN position.
  154. Landing Gear Lever Operation
    Controls the landing gear solenoid valve which directs the hydraulic pressure to extend or retract the gear.

    When the aircraft is on the ground, an electrical solenoid mechanically locks ONLY the GEAR LEVER preventing it to be moved into the up position.
  155. Landing Gear DOWN LOCK RELAY Button
    Used in an emergency, such as an engine failure during takeoff, a failure of the solenoid or air/ground switch may prevent gear retraction.

    In this case the DOWN LOCK RELAY button should be pressed and the gear handle selected to the UP position.
  156. Landing Gear Lamps TEST
    One button for each circuit (A and B) tests the condition of the lights only.
  157. Landing Gear Position Indicating Lights
    The gear position indicating system consists of two fully independent electrical circuits (A and B). These circuits are identical and operate simultaneously.

    Red- Indicate that there is a disagreement between the landing gear position and the position of the gear lever.

    Green- Indicate that the corresponding landing gear is down and locked.

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