Questions YANGO-ng2025

The Crew fails to properly accomplish normal procedures and takes off with the APU powering both Transfer busses. The generators will come on line automatically if the APU is either shut down or Fails. One Transfer bus will disconnect automatically after lift-off. During climb, the galleys may become inoperative.

What is the maximum takeoff and landing altitude for the B737NG?. 15000Ft. 14000Ft. 13500Ft.

The maximum aircraft altitude for electrical use of the APU is?. 37.000Ft. 41.000Ft. 35.000Ft.

The TAI Green (thermal Anti-Ice Indication) is shown in which dial?. N1. EGT. N2.

The New Generation Aircraft is designed to be fueled through the wing tanks with gravity. True. False.

The high altitude landing switch when on: Reprograms cabin altitude warning annunciation to 15.000 feet. Reprograms cabin pressurization from high altitude to normal operation. Reprograms cabin altitude warning annunciation from 10.000 to 14.000 feet.

When are the GPWS windshear warnings available?. Below 1500 feet AGL. Below 2500 feet AGL. Below 800 feet AGL.

What component controls and monitors the B737NG APU?. FADEC. FCU. ECU.

On the 737 NG, The APU can power both Generator Busses. On the ground or in flight. On the ground only. In flight only.

What is the normal Psid that you could expect when cruising at FL370. 8.05. 8.35. 7.8.

Wich Aircraft are equipped with a Tail Skid. B737-200. B737-100. B737-800-900.

What is the purpose of the PSEU. Monitors the takeoff configuration warning. Monitors the landing configuration warning. Monitors the landing gear. All of the above.

What is the APU starter duty cycle?. 2 consecutive aborted starts attempts, a 15 minute cooling period is required. 3 consecutive aborted starts attempts, a 15 minute cooling period is required. 3 consecutive aborted starts attempts, a 30 minute cooling period is required.

Inflight and imbalance of more than_____ between the main tanks will cause the display of IMBAL to appear. 902 Kgs. 453 Kgs. 760 Kgs.

The automatic flight system (AFS) consists of: AFDS; A/T; MCP; FMC. AFDS; A/T; MCP. AFDS; A/T.

La maximum flight operational Altitude of the B737NG is. 41000 Ft. 42000 Ft. 37000 Ft.

What temperature is mantained in each zone if the temperature Selectors are in AUTO. 80 Degrees Farenheit. 60 Degrees Farenheit. 70 Degrees Farenheit.

Either generator or the APU can power both transfer buses. In the event a power source fails, what is required for that transfer bus to be powered by the opposite transfer bus power source. The BUS TRANS switch must be in the AUTO position. The battery switch must be ON. The generator switch must be OFF.

With all fuel pumps operating, why should the center tank empty first. The center tank pumps have a higher output capacity than the wing tank pumps. The center tank check valves operate at a lower pressure. The center tank pumps have a lower output capacity than the wing tank pumps.

A magenta bug on the vertical speed indicator in the PFD indicates. Actual vertical Speed. Indicates vertical speed in VNAV mode. Selected vertical speed on the MCP panel with V/S pitch mode selected.

For wich modes can TCAS be displayed?. MAP (EXP or CTR) and CTR VOR and CRT APP. MAP, PLAN, VOR, APP. MAP (EXP or CTR) and EXP VOR and EXP APP.

What is the source of power for TR2?. Transfer bus 1. Transfer bus 2. AC Stby Bus.

For a 737NG the automatic landing the head and crosswind limits are. Headwind limit is 25 kts and the crosswind limit is 20 kts. Headwind limit is 20 kts and the crosswind limit is 15 kts. Headwind limit is 25 kts and the crosswind limit is 15 kts.

How are the Engine Bleed Air valves powered?. They are DC activated and pneumatically operated. They are pneumatically activated and AC operated. They are AC activated and pneumatically operated.

When you have a N1 exceedance what is the first action. Thust Lever close. Start Lever Cutoff. A/T Disconect.

What structure of the B737NG swings the largest arc while turning?. Wingtip. Nose. Tail.

What is indicated with the ELEC light illuminated. Ac transfer bus inoperative. DC Stby Bus Inoperative. Failure on the DC power system or standby power system.

Illumination of the PSEU light on the aft overhead panel will actívate the MASTER CAUTION system. False. True.

Where are the Logo lights located on the New Generation aircraft?. The Logo lights have moved to the vertical Stabilizer. The Logo lights have moved to the top of the horizontal stabilizer. The Logo lights have moved to the top of the fuselaje.

Where are the REVERSER Lights ?. Aft Overhead Panel. Glareshield. Overhead Panel.

The APU start cycle may take up to. 60 seconds. 135 seconds. 120 seconds.

On Take Off the Crew Alerts are inhibited: From 80 kts to 400 feet RA, or 30 seconds after reaching 80 Kts whichever occurs first. From 84 kts to 400 feet RA or 30 seconds after reaching 84 kts whichever occurs first. From 60 Kts to 400 feet RA or 30 seconds after reaching 60 kts whichever occurs first.

Illumination of the DRIVE light indicates. Any of the above. IDG disconnected through the drive disconnect switch. IDG failure. IDG automatic disconnect due to high oil temperatura.

What will happen on the on the new generation aircraft if a tire is flailing while the gear retract?. The tire will be fully braked before it enters the Wheel well. The maing landing gear weel has a sensor that detects flailing tires. The gear with a flailing tire will not retract.

The Crossbleed Start Indication (X-BLD) is shown on which dial?. N2. EGT. N1.

The maximum demonstrated 737NG crosswind component for take-off and landing is?. 36Kts. 34Kts. 35Kts.

Of the four lights located on the APU control panel, wich light will not cause an automatic shutdown of the APUwhen it illuminates?. Low oil quantity/Maint. High Oil Temp/Fault. Low Oil Pressure.

In which position must the Disengage bar be placed to allow AP engagement?. UP. CMD. CWS.

The EGT display, both box and dial, turn red and the EEC automatically turns off ignition and shutoff fuel to the engine if. The EGT excedes the star limit during ground starts. An impending hot start is detected during ground starts or in flight starts. An impending hot start is detected during infight starts.

Engine ignition must be on for?. Landing. Take Off. Operation in heavy rain. Anti ice Operation. All of the above.

Upon departure from a high altitude airport, the High Altitude Landing System returns to normal operation as thecabin altitude descends through?. 8000 Feet. 8500 Feet. 9000 Feet.

Upon departure from a high altitude airport, the High Altitude Landing System returns to normal operation as thecabin altitude descends through?. 8000 Feet. 8500 Feet. 9000 Feet.

The minimum tank fuel temperature prior to takeoff and inflight is?. -43 C. -47 C. -45 C.

The EEC depending on the phase of flight selects: Ground Idle; Flight Idle; Approach Idle. Ground Minimum Idle; Flight Minimum Idle; Approach Idle. Low Idle; High Idle.

What is the recommended turbulent penetration airspeed for the B737NG?. 280 Kts/0.78M. 280 Kts/0.72M. 280 Kts/0.76M.

On the ground or in flight with at least one engine running CONFIG is displayed if the center tank quantity is morethan_______ and the center tank pumps are producing no or low pressure. 453 Kgs. 760 Kgs. 726 Kgs.

The Air Data Inertial Reference Unit ADIRU, is limited to operate from. 82 North, 60 South. 80 North, 80 South. 82 North, 82 South.

What is the purpose of the new Trim Air Modulating Valves. With trim air operating, they provide warm air to the zone that needs Warming. With trim air On, packs maintain an average temperature of 24 Celcius. With Trim Air Off, they provide heat exchanger cooling.

Why don’t the new generation aircraft have viewers to determine the position of the landing gear?. Because they have a complete set of independent Gear Position Indicators. Because the gear operation is more reliable. Because downlocks are electrically operated through the hot battery bus.

What is the maximum differential pressure for take off & LDG on the B737NG?. 0.125 PSI. 0.175 PSI. 0.200 PSI.

The ENG FAIL alert is shown on wich dial?. N2. EGT. N1.

With the Control Panel select switch on the Displays source panel in the BOTH ON 2 position: Both pilots displays are using the No.2 symbol generator. DEU 2 controls all six display units. The First Officer’s EFIS Control Panel is supplying identical inputs to the captain’s and First Officer’s displays.

The APU may be used as a Pneumatic and Electric source on the ground up to. 17000 ft. 15000 ft. 10000 ft.

What configuration below causes the overboard exhaust valve to be open in flight?. One pack switch High and recirculation fan off. Both pack switches High and recirculation fan off. Both pack switches off and recirculation fan off.

What is indicated by the IMBAL light on the #1 or #2 Fuel Quantity Indicator?. There is more than 453 Kgs difference between the main tank quantities. The is more than 907 Kgs difference between the main tank quantities. There is less than 453 Kgs difference between the main tank quantities.

The AUTO ON position for the PROBE Heat Switches work: Automatically supplying power to both A and B probe heat systems when either engine is running. Automatically supplying power to both A and B probe heat systems when Take Off power is applied. Automatically supplying power to both A and B probe heat systems when AC electrical power is applied.

What is the number of ground spoilers on each wing. 2. 1. 3.

On the NG AFDS until what event after takeoff does the THR HOLD mode remain in effect?. Until climbing through 400’ RA. Until Climbing through 800’ RA. Until 18 Seg after Takeoff and 800’ RA.

The dimensions of the B737 -700 are. Wingspan 37.80m, Length 32,60m. Wingspan 35.79m, Length 33.60m. Wingspan 36.79m, Length 33,50m.

On the NG aircraft, the Outboard Landing Lights are now located. On the LEading edge of the Wing. They are on the same position as the 737CL. On the lower fuselaje, adjacent to the Ram Air Inlets.

The Flap/Slat Electronics Unit (FSEU) provides. LE skew detection for slats 2 through 7 except during autoslat operation. Uncommanded motion protection for LE devides and TE flaps. TE asymetry protection by removing hydraulic pressure to the TE flaps i fan asymetry is detected. All of the above are correct.

When is the proximity switch Electronic Unit light inhibited?. from takeoff thrust until 30 seconds after landing. For 1 minute after Landing. All of the Above.

The EEC drives all Engine indication except. Oil quantity and engine vibration. Oil temperatura, pressure and quantity indications. Fuel flow and Oil Pressure.

Where is the Hydraulic pressure and quantity displayed on the NG aircraft?. Upper DU, just above the fuel quantity displays. Lower DU selection of Display sourse of the mfds. Lower DU, Displayed by use of the MFD “SYS” switch.

The EEC becomes energized anytime the engine accelerates. N1 more than 20%. N2 more than 15%. N1 more than 18%.

With CWS engaged, the A/P rolls the wings level and holds existing heading if aileron pressure is released with. 15 degrees. 12 degrees. 6 degrees.

With the STBY switch in the AUTO position, the loss of all engine or APU electrical power results in the automaticswitching from the normal power source to the alternate source for standby power. On the ground only. Either inflight or on the ground. Inflight.

The Maximum angle of the Nose Wheel Steering controlled by the Tiller is. 78 Degrees. 7 Degrees. 88 Degrees.

The AC STBY BUS comes from. TR1. AC Transfer Bus #1. Main Bus #1.

When on the ground during taxi or when both engines are shutdown, what symbol appears by the hydraulic quantity reservoir is low on fluid and needs to be refilled?. RF. REF. LOW.

What is the maximum differential pressure for the B737NG?. 9.1PSI. 8.35PSI. 7.8 PSI.

How many leading edge devices in each wing are protected by the wing anti ice system?. 9. 3. 6.

With the Mail Panel DU switch set to ENG PRI, the______displays on the Outboard DU, and the _______ displays on the Inboard DU. Upper Center, Primary Engine Indications. PFD, Primary Engine Indications. ND, Primary Engine Indications.

The maximum difference on the ground between the captain & FO altimeters at 8000Ft is?. 75 feet. 50 feet. 60 feet.

Serviceability of the tailskid cartridge is shown by. A Green decal. A Green and red decal. Wear dimples.

Wich of the DU’s is normally blank?. PND. Lower Center. Upper Center.

In MANUAL pressurization mode the outflow valve is driven by. A motor supplied from DC bus 2. A motor supplied from the DC standby bus. A motor supplied from DC bus 1.

The TRIP RESET switch resets BLEED TRIP OFF, PACK TRIP OFF, DUCT OVERHEAT AND WING BODY OVERHEAT lights. Verdadero. Falso.

The autopilot can not be engaged for take off below?. 200 Feet. 600 Feet. 400 Feet.

Los Flight Spoilers raise on the upper wing to augment roll control with the control column displaced more than. 13 Degrees. 10 Degrees. 1 Degree.

In Flight the Recirculation Fan operates with the switch in the AUTO position execpt: When both packs are on unless either pack switch are selected to HIGH. When one pack is off. Anytime the forward outflow valve is open. When both pack switches are selector to AUTO.

At what cabin altitude is the Altitude Warning Horn automatically horn automatically activated?. 9,500 feet. 10,000 feet. 14,000 feet. 13,875 feet.

When does croos bus tie relay automatically open. When on ILS approach with dual channel autopilot engaged when APP is armed. When on ILS approach with FD or autopilot couple at glide slope capture. When on ILS approach with single channel autopilot engaged when VOR/LOC is armed. When on ILS approach with FD or autopilot coupled at localizer capture.

What will cause the APU to automatically shut down?. Senses a fire. Low Oil Pressure; Fault; Overspeed; Fire; Fuel control unit failure. Overspeed; Maintenance; Fire; Battery switch off in flight. Fire; Pulling the Fire handle; silencing the bell.

The OFF SCHED DESCENT light illuminates if: The aircraft descanded before reaching the planed cruise altitude set in the FLT ALT indicator. The aircraft has climbed above the selected flight altitudes (as set in the FLT ALT indicator). The aircraft has temporarily leveled off before reaching the planed cruise altitude set in the FLT ALT indicator. The aircraft has landed before reaching the selected flight altitude set in the FLT ALT indicator.

The EEC provides: Thrust lever inputs to automatically control forward and reverse thrust. A variable thrust climb feature once the thrust lever is set at the beginning of the climb. A vaiable thrust take-off and climb ance the thrust lever is set at the beginning of takeoof roll. A constant EGT and Fuel flow feature once the thrust lever is set at the beginning of the climb.

The EGPWS provides alerts based on radio altitude and combinations of barometric altitude, airspeed, glide slopedeviation, and airplane configuration for: Excessive deviation below an ILS glide slope or altitude loss after take off or go-around. Unsafe terrain clearance when nt in the landing configuration. Any of the above. Excessive descent rate or excessive terrain clousure rate.

An A/T LIM indication when illuminated indicates: The A/T is positioned at their normal operating limit as calculated by the FMC. The A/T LIM has been exeeded and manual inputs are now required for the affected engine(s). The A/T is using a degraded N1 thrust limit from the related EEC. The A/T computer is calcilating a N1 limit for the affected engine or engines.

The ENG OVERHEAT light and: MASTER CAUTION and OVHT/DET system annunciator illuminate. If both loops sense a fault with OVHT DET switch in the NORMAL position. MASTER CAUTION and OVHT/DETc) system annunciator lights illuminate. Illuminate if either fire loop senses a fire. MASTER CAUTION and OVT/DET system annunciator lights do not illuminate.

The Engine Fire Extinguisher system contains: One bottles in each engine nacelle to either engine or APU. Four bottles in the main wheel well, two for each engine. Two bottles in the main wheel well to their respective engine and the APU. Two bottles in the main wheel well to both engines.

The TOTAL Air Temperature provides independent temperature data to each ADIRU: Data derived from the left ADIRU is used by the left IRS and the left FMC. Answer A. and B: are correct. Data derived from the right the right ADIRU is used by the left IRS and the right FMC. Data derived from the right ADIRU is used by the right the right IRS and the right FMC.

The Alternate Flaps Position switch when selected to the UP position will: Hydraulically retract the trailing edge flaps. Electrically retract the leading edge slats and flaps and trailing edge flaps. Electrically retract the trailing edge flaps. Hydraulically retract the leading edge flaps and slats and electrically retract the trailing edge flaps.

Which part of the engine is heated by engine anti-ice system?. Pt2 probes. The bullet. Fan blades. Engine cowl lip.

Illumination of the CONT CAB ZONE TEMP light: The control cabin air mix valves drive to full cold. Nothing happens automatically with DUCT OVERHEAT, refer to QRH. Indicates duct temperatures overheat or failure of the flight deck primary and stanby temperature control. The cargo compartment air mix valves drive to full hot.

The STAB OUT OF TRIM light operates: Only when the autopilot is engaged. Only when the stabilizer trim failed. Only when the speed trim system is activated. Anytime it senses additional trim is needed.

The conditions for speed trim operation are: All answer is correct. Most frequently during takeoffs and go-around. Autopilot not engaged, Sensing of trim requiremnt. Airspeed 100 KIAS-Mach 0.5, 10 seconds after takeoff, 5 seconds after release of trim switches.

The Landing Gear Tranfer Unit provides for gear retraction when: Airborne, No.1 engine RPM drops below a limit value, either mIN Lnding gear is not up. Airborne, No.2 engine RPM drops below a limit value, either main landing gear is not up. Airborne, No.2 engine fail, LANDING GEAR lever is positined UP. Airborne, No.1 engine RPM drops below a limit value Hydraulic System B fail.

How do you connect the external Service Interphone to the Service Interphone System?. Automatically by connecting any headset or hand Microphone into a jack. It is always connected. By selecting Service Interphone Switch to On position.

When EEC is in Hard Alternate mode, what parameters are used to control engine thrust? Seleccione una: There is a standard performance table to recalculate EEC parameters according to flight condition. The EEC reverts to an alternate mode thrust Schedule predetermined by the manufacturer. Parameters are drawn from ADC to be calculated by FMC.

While on the ground, what is indicated by the TR UNIT light being illuminated on the AC and DC Metering Panel?. Any TR unit has failed. The only souse of power is the Battery. No answer is correct.

What is the maximum takeoff altitude on NG aircraft?. 14.000’. 10.000’. 13.500’.

What causes the ENG FAIL alert to display on the engine EGT indicator?. Engine start lever in idle and operating below sustained idle (less than 40% N2). Engine start lever in idle and operating below sustained idle (less than 50% N2). Engine start lever in idle and operating below sustained idle (less than 60% N2).

When will the Dual Bleed light illuminate on the Air Systems Panel?. When the APU Bleed Air Valve is closed and either engine N°1 Bleed Air Switch is ON or engine N°2 Bleed Air Switch is ON with the Isolation Valve is Open. When the APU Bleed Air Valve is closed and either engine N°1 Bleed Air Switch is ON or engine N°2 Bleed Air Switch is ON with the Isolation Valve is closed. When the APU Bleed Air Valve is open and either engine N°1 Bleed Air Switch is ON or engine N°2 Bleed Air Switch is ON with the Isolation Valve is Open.

What is indicated by the illumination of the ENGINE CONTROL light on the Engine Panel?. A fault is detected in the normal system and the system is in the alternate mode. No answer is correct. A fault is detected in the system and the aircraft is not able to be dispatched.

What occurs when the Engine Bleed Air Switch is selected to the ON position?. Opens the Engine Bleed Air Valve when the respective engine is operating. Closes the Engine Bleed Air Valve when the respective engine is operating. Dual Bleed light illuminate if the APU Bleed Air Valve is closed.

Which igniter works on battery power?. Left ignitor. It is powered by the AC Standby Bus which is powered by the battery when the battery is the onlypower. Right ignitor. It is powered by the AC Standby Bus which is powered by the battery when the battery is the only power. No answer is correct.

If all AC power is lost, for how long does right IRS remain on?. 10 minutes. 15 minutes. 5 minutes.

What LE devices are not Skew protected?. 1 and 8. 2 and 7. All are skew protected.

What is the maximum operating altitude for the APU while supplying both bleed air and electrical power to the aircraft?. 41000 ft. 10000 ft. 17000 ft.

How Much Rudder and Nose Wheel deflection is controlled by full rudder pedal input?. 9° on Nose Wheel and 27° on Rudder. 5° on Nose Wheel and 30° on Rudder. 7° on Nose Wheel and 29° on Rudder.

What is indicated by the COWL VALVE OPEN light being illuminated Dim on the Engine Anti-ice Panel?. Related Engine Cowl Anti-ice Valve is in transit (switch on). All the answers are correct. Related Engine Cowl Anti-ice Valve is open (switch on).

What hydraulic system normally powers the auto-slat operation?. Hydraulic System B. Hydraulic System A. Hydraulic System Standby.

What is indicated by the DC FAIL light being illuminated on the IRS Panel?. The AC power source for the related IRS is not normal. The DC power source for the related IRS is not normal. The stanby power source for the related IRS is not normal.

What occurs by moving and holding alternate flap position switch to the up position?. Only leading edge flaps retract. Both LE Flaps and TE flaps are electrically retracted. Only trailing edge flaps retract.

What is indicated by the LOW QUANTITY light on Flight control panel indicate?. Low standby Hydraulic system quantity (Approximately 22% Full). Low Standby Hydraulic system quantity. (Approx 50 % Full). Low Quantity in Hydraulic system in general (Averaging 70%).

What is the the highest altitude recommended for starting the APU on battery power only. 25000 feet. 20000 feet. 41000 feet.

When EEC is operating in soft alternate mode, what parameters are used to control engine thrust?. Values preset for ISA conditions according to flight altitude that allow for better engine protection. Degraded FMC N1 precalculated parameters. Last valid flight conditions sensed which allow the mode change to occur without an immediate change.

When the Mach Trim System is automatically engaged?. At speeds below Mach 0.615. At speeds above Mach 0.615. At speeds above Mach 0.655.

How many hours does the FDR Records?. The last 30 hours. The last 25 hours. The last 120 minutes.

What is the normal cabin differential pressure when flying above 37.000 ft. 8.35 psid. 7.80 psid. 7.45psid.

If the Audio Control Panel is operating in the degraded mode, how do you make PA´s and communicate on the interphone system?. Through the Audio Control Panel. All the answers are correct. Only the service interphone handset works because it bypasses the Audio Control Panel.

What is indicated by ON DC light on IRS Panel?. IRS on DC Power and performing alignment Self Test. Only dc buses available for IRSs. c) DC power is powering IRS and corres.

When is LOW QUANTITY LIGHT on Flight Control Panel Armed?. Light is armed only when Standby hydraulic system is operating. Light is always armed. Light is armed when hydraulic system B is below a fixed value.

When will the radio altitude display on the Primary Flight Display?. Below 2000 feet AGL. Below 2500 feet AGL. Below 1500 feet AGL.

How long can a start cycle take for the APU?. 180 seconds. 135 seconds. 120 Seconds.

What causes the DRIVE light on the Generator Drive and Standby Power Panel to illuminate?. When low oil pressure is sensed in the IDG. When the IDG is connected to the Transfer Bus. When over speed is sensed in the IDG.

Can one transfer bus be powered by the APU and the other by External Power?. Yes. No answer is correct. No.

What significant equipment operates in the Air System when the only source of power is the battery?. Manual pressurization control, Altitude warning horn and Pack lights. All the answers are correct. Air conditioning Pack Valves, Bleed Trip Off Lights.

During a normal APU shutdown cycle, what does the illumination of the FAULT light indicate?. The APU Fuel Shutoff Valve has not closed after 30 seconds. The APU Fuel Shutoff Valve is in transit. No answer is correct.

When does the source off light illuminates?. When transfer bus is not energized form selected power source. When transfer bus is energized by power source but generator not online. When generator is online but bus is not yet energized.

How many minutes does it take to align an IRS?. 8 to 10 minutes depending or airplane location. 5 to 17 minutes, depending on airplane latitude. 5 minutes because GPS signals quick align airplane position.

What is indicated by the three landing gear indicator lights on the aft overhead panel?. Landing gear positions, as indicated by the landing gear position lights on the landing gear panel. Works as a backup in case landing gear indicator lights are inoperative. Actual landing gear position, replacing landing gear visors.

On upper display panel, when will low alert in fuel quantity indicator be indicated?. Whenever respective wing tank has less than 680KG (1500 lbs) of fuel. Whenever respective wing tank has less than 906 KG (2000 lbs) of fuel. Whenever respective wing tank has less than 226 KG (500 lbs) of fuel.

When will config alert on Upper Display Unit appear?. When either engine is running but not all main wing fuel tanks are on. When not enough fuel pressure is delivered to fuel inlet. When either engine is running and center tank pump switches are off.

When is the IMBAL alert inhibited on the fuel quantity indicator?. When the airplane is on the ground or when the fuel LOW alert is displayed on the same main tank. When the airplane is on the air or when the fuel LOW alert is displayed on the same main tank. All the answers are correct.

Does the EEC provide overspeed protection for N1 or N2 in both the normal and alternate modes?. No, protection is only in normal mode. Yes, protection is always available. No, protection is only in alternate mode.

If a primary fcontrol fails, affected pack is controlled by. Standby pack control in affected pack. Standby pack control in opposite controller. Primary pack control in opposite controller.

Do all bulbs in the cockpit dome light illuminate when the Dome Light Switch is turned on?. Yes, all bulbs in the cockpit dome light illuminate when the Dome Light Switch is turned on. No answer is correct. No, one bulb is controlled by the Emergency Lighting System.

On IRS panel what is indicated by the align light (Steady). IRS alignment information invalid. IRS alignment modem, Initial ATT and Shutdown mode is processing. IRS in Disagreement with GPS position.

When will the IDG Automatically disconnect?. When a high oil temperature is sensed in the IDG. When an overcurrent or overtorque condition is sensed. When oil pressure has dropped below limits.

What does moving “ALTERNATE FLAPS” Switch to “ARM” accomplish?. Closes TE Flap Bypass valve. Activates stby pump. Arms alternate flap position switch. All of the above.

What causes a Zone Temp Light on FWD CAB or AFT CAB Selector?. Zone Temperature too cold. Zone Temperature too hot. Duct temperature overheat.

What is the maximum cabin differential pressure on NG Aircraft?. 8.65 psid. 9.1 psid. 7.8 psid.

Can you regain IRS heading information after IRS is lost inflight?. No, until aircraft is in ground and realigned. No, there is no ATT selection and realignment procedures. Yes, after selectin ATT following manual realignment procedures using compass heading information.

What is the max altitude APU can support both generators?. 41.000’. 37.000’. 17.000’.

When does the mach trim begin to opérate. At .615 M. At .715 M. At .605 M.

The Ground Conditioned air is Plugged Directly into the. Left pack. Right pack. Mix manifold.