737 AQP MAX DIFFERENCES

Air System. If smoke is detected within the equipment cooling system, what amber caution light illuminates?. SMOKE. EQUIP SMOKE. ELEC EQUIP SMOKE.

Air System.How is the operation of the bleed air system controlled?. Electronically controlled. Pneumatically controlled. Electro-pneumatic controlled.

Air System.Where are the RAM DOOR FULL OPEN lights located on the 737 MAX?. These lights are not on the MAX. Two lights located on Trim Air control Panel. Only one light split in two located on Pneumatic panel.

Air System. What causes both of the BLEED lights to illuminate at the same time?. If the thrust lever is moved forward more then 30%. Both Bleed switches in the OFF position after takeoff or go-around. 5 minuted after take off with both bleeds switches in OFF position.

Air System. Engine bleed air is extracted from what stages of the compressor on 737 Max?. 5th and 9th. 4th and 10th. Depend of the temperature.

Air System. How many air conditioning packs is one engine bleed capable of supplying in flight on the 737 MAX?. 2. 1. Depend of the power and temperature.

Air System. What causes both PACK lights to illuminate at the same time?. Both PACK switches in the OFF position after takeoff. If the thrust lever is moved forward more then 30%. 5 minuted after take off with both bleeds switches in OFF position.

Anti-Ice. Which of the following causes the ENG Anti-Ice light to illuminate?. If both valves are in transit. When the cowl thermal anti-ice system has been inhibited due to a system failure. If a valve is open and the other in transit.

Anti-Ice. After selecting the ENG Anti-Ice switches to ON in flight, the following indication is observed in steady state. What is true concerning the engine anti-ice system?. The left engine anti-ice valve disagrees with the ENG Anti-ice switch. The right engine anti-ice valve disagrees with the ENG Anti-ice switch. Both valves are not in selected position.

Anti-Ice. What is the indication when the wing anti-ice VALVE light momentarily illuminates amber?. Valve is in transit. Valve is Open. Valve is Close.

APU. Which of the following causes the APU door (DOOR) light to illuminate while on the ground?. The APU door is open and APU is running. The APU door is open and APU is shut down. The APU door is closed APU shut down.

Engine. What is indicated when the REVERSER COMMAND light illuminates?. No reverser in use. Reverser is commanded in flight.

Engine. What causes the REVERSER AIR/GRD light to illuminate?. The System is inoperative. Loss of the Reverser air/ground protection.

Engine. During engine start the start levers are moved to the idle detent when the MOTORING indication blanks and N1 rotation is seen, and the N2 reaches what percent?. 25%. 15%. 20%.

Engine. When conducting extended engine motoring, what is the starter usage time limit?. 10 minutes. 15 minutes. 5 minutes.

Engine. What mode of idle is selected by the EEC if the aircraft is inflight below 30,400 feet, the flaps are not extended, the main gear is not down and locked, and the engine anti-ice is on?. Icing idle. Stand by idle. Steep descent.

Flight Controls. Which statement below correctly describes a function of the Landing Attitude Modifier (LAM)?. Designed to maintain acceptable nose landing gear contact margins for landing. The pilots are in more confortable position. Is the same than NGs.

Flight Controls. What is the purpose of the Maneuver Load Alleviation (MLA) system?. Help to the airplane to keep on path app. Decreases structural loads by partially retracting the speedbrakes. Help to reduce the speed during the approaches.

Flight Controls. What can cause the SPEEDBRAKES EXTENDED light to illuminate in flight?. Speedbrake lever is beyond the ARMED position and a thrust lever is in idle. Speedbrake lever is beyond the ARMED position and a thrust lever is above idle for at least 15 seconds. Speedbrake lever is beyond the ARMED position and 30 degrees of bank.

Flight Controls. When activated, what does the Emergency Descent Speedbrakes (EDS) system do?. Raises the Speedbrakes to a higher than normal position during the emergency descent maneuver. Nothing, the descent is the same but more stable. Calculate the path to descent.

Flight Controls. What is required to activate the Elevator Jam Landing Assist system?. The Elevator Jam Landing Assist switch must be selected ON, the flap position must be 1 or greater and the autopilot must be disconnected. The Elevator Jam Landing Assist switch must be selected ON, the flap position must be 15 or greater and the autopilot must be ON. The Elevator Jam Landing Assist switch must be selected AUTO, the flap position must be 20 or greater and the autopilot must be disconnected.

Flight Controls. What does illumination of the ASSIST ON light indicate?. The Elevator Jam Landing Assist system is activated. Autopilot ON and flaps more than 1. Autopilot OFF and flaps more than 1.

Flight Controls. What causes the SPOILERS light to illuminate on the Flight Control Panel?. Minimum three spoiler pairs are inoperative. One or more spoiler pairs are inoperative. The spoilers are operative and extended.

Flight Instruments. Select the location of the Captain’s Display Select Switches. Located to the left of Captain's panels. Located under the Captain’s outboard DU. Located in the middle of Captain's and FO's panels.

Flight Instruments. How many large format Display Units (DU’s) are located on the flight deck?. 2. 4. 5.

Flight Instruments. Push the switch that allows the crew to manually enter the N1 Targets and V-speed bus on the Airspeed indicator. ENG. INFO. SYS.

Flight Instruments. On which display are all of the following located: flight number, SELCAL, transponder code, airplane tail number, and date?. INFO. AUX. ENG.

Flight Instruments. Select where the Multi-Function Display (MFD) switches are located?. Adjacent to the right MCDU. Below Captain's panels.

Flight Instruments. Where are the engine indications normally displayed?. First Officer’s Inboard display unit. Captain’s or First Officer’s Inboard display unit. Captain’s Inboard display unit.

Flight Instruments. When an outboard Display Unit (DU) failure is sensed, the displays automatically reconfigure, what happen to the AUX display?. The info is moved to Pilot flying DU automatically. Half-sized display moves to the inboard DU, and goes above the PF.

Flight Instruments. Where is the hydraulic systems information normally shown after selecting the SYS switch on the Engine Display Control Panel?. The inboard display unit opposite the engine display. The outboard display left corner. Below of the ENG info in the middle of panel.

Flight Instruments. Where is the clock switch located?. On the Glareshield panel. Central panel. Below of Captain and FO displays.

Flight Instruments. Which switch selects the Vertical Situation Display (VSD) inset on the Expanded MAP and Center Map modes on the Navigation Display (ND). VSD (in the center). The VSD is shown in the opposite panel of pilot flying.

Flight Instruments. Select the switch that moves the engine indications to either the Captain’s or the First Officer’s inboard display unit?. ENG TFR R. ENG TFR (center). ENG TFR L.

Fuel, FMC. What messages shows on the CDU scratch pad and appears on the Engine Display as amber alerts?. FUEL DISAGREE, INSUFFICIENT FUEL, and USING RSV FUEL. RESERVE FUEL DISAGREE and INSUFFICIENT FUEL. TOTAL FUEL DISAGREE, and USING RSV FUEL.

Fuel, FMC. On the FUEL PROGRESS page 5/5 the TOTALIZER fuel value is computed from what?. FQIS gauge readings. Left fuel tank. Total fuel less fuel burning to the destination and alternate.

Fuel, FMC. Where is the fuel quantity source selected on the FMC?. Fuel Progress page 5/5. Pressing FUEL bottom. Perf INIT, FUEL quantity.

Fuel, FMC. When is it possible for the fuel FILTER BYPASS lights to extinguish, if both have illuminated at any time during flight?. If the reset fuel switch activated. After engine shutdown on the ground. Before the next flight when programs the next zero fuel on FMC.

Fuel, FMC. What Engine Display alert displays if the FMC determines a difference between the total sensed fuel quantity and the calculated fuel quantity values?. FUEL DISAGREE. FUEL RESERVE. MINIMUM FUEL.

Landing Gear. Select the location of the BRAKE PRESS Accumulator Indicator. Forward Aisle stand. Below Captain's panel. Above of Landing gear lever.

Landing Gear. When pushed, what does the LOCK OVRD switch do?. Releases the landing gear lever lock. Turn off the Landing gear lights. Reset the system in case if position disagreement.

Landing Gear. Select the location of the Auto Brake switch. Above of Landing gear lever. Forward Aisle stand. Below FO's panel.

Landing Gear. Following a takeoff or a go around, check that the LANDING GEAR lever is in what position?. UP. OFF. Neutral.

Landing Gear. Where is the NOSE WHEEL STEER switch located?. Center forward panel. Pilot site. FO site.

RCAS. Select the bank pointer and slip/skid indication, with ROLL/YAW ASYMMETRY alert active, and the aircraft at 10° of bank. Red pointer with no fill. Amber outlined pointer with no fill. White outlined pointer filled.

RCAS. With a single autopilot engaged, when does the ROLL/YAW ASYMMETERY alert appear?. When the autopilot is at 75% of roll authority for more than 20 seconds. When the autopilot is at 75% of roll authority for more than 10 seconds. When the autopilot is at 80% of roll authority for more than 10 seconds.

RCAS. When the airplane is significantly out of trim (control column is deflected in the roll axis) return the airplane to coordinated flight by doing the following order: 1) Trim the rudder in the direction of the down side of the control wheel 2) Apply ruder to maintain flight path 3) Verify or set symmetrical thrust 4) Accomplish the primary rudder trim technique. 1) Verify or set symmetrical thrust 2) Accomplish the primary rudder trim technique 3) Apply ruder to maintain flight path 4) Trim the rudder in the direction of the down side of the control wheel. 1) Apply ruder to maintain flight path 2) Accomplish the primary rudder trim technique 3) Verify or set symmetrical thrust 4) Trim the rudder in the direction of the down side of the control wheel.

RCAS. Select the item(s) that are an indication of an autopilot saturation event?. Unusual control wheel deflection, ROLL/YAW ASYMMETRY alert, and the ROLL AUTHORITY. ROLL ASYMMETRY alert, and the ROLL AUTHORITY. ROLL/YAW ASYMMETRY alert, and the AUTOPILOT disconnected.

RCAS. What is the purpose of the pitch attitude latch?. Enable the use of high bank angles in recovering from a nose high upset without setting off the alerts. Max bank 30 degrees to recover a nose up upset. Permit the use of aggressive attitudes to upset recovery.

RCAS. Select the bank pointer and slip/skid Indication, in a roll upset condition, indicating that the bank angle is excessive. Solid red pointer and red outlined slip skid. AA.

RCAS. This question require picture. What should be done when you see this on your PFD?. Roll left. Roll Right. Level wings.

Runaway Stabilizer. When performing the Runaway Stabilizer Non-Normal Checklist, how should thrust be controlled after the autothrottle is disengaged?. Thrust should be controlled manually so that airspeed remains within the range appropriate for the phase of flight. Auto throttle is available. Max power in case of stall.

Runaway Stabilizer. When performing the Runaway Stabilizer Non-Normal Checklist, what can the pilot do to reduce control column forces?. Read check list. Use main electric stabilizer trim. Use the power.

Runaway Stabilizer. During a runaway stabilizer condition, which of the following actions should be taken if the runaway continues after the autopilot has been disengaged?. Move first one STAB TRIM cutout switch to CUTOUT, then the other. Move both STAB TRIM cutout switches to CUTOUT. Increase power to induce pith up.

Runaway Stabilizer. During a runaway stabilizer condition, after the pilot flying disengages the autopilot and autothrottle, Control Column and Thrust Levers are used to control what?. Airplane Pitch Attitude and Airspeed. Bank angle and speed. Avoid VNE speed limit.

Manual Trim. When the autopilot automatically disengages after 1 second of stick shaker activation, what happens to the flight director?. The flight director is temporarily removed from the PFD until airspeed increases above the amber bar. The flight director turned red color. The flight director disappear until the next flight.

Manual Trim. On the 737 MAX, when does FCC logic inhibit autopilot nose up stabilizer trim commands?. If the back angle is more than 35. When the trailing edge flaps are extended and airspeed is 3 knots or more into the amber bar. 5 knows before stall.

Speed Unreliable. Which of the following does not provide inputs for airspeed indications?. Pitot tubes. Speed Trim System. ACARS sensors.

Speed Unreliable. This question require picture. Which of the following may be an indication of an unreliable airspeed condition?. Left photo. All of the above. Right Photo.

STS. On the 737NG and 737 MAX, what condition is necessary for the Speed Trim System to operate?. FD and AP engaged. Autopilot not engaged. Autopilot engaged.

STS. On the 737 MAX what does illumination of the SPEED TRIM FAIL light indicate?. If two function fails (the Speed Trim function and MCAS function) are inoperative for the remainder of the flight. Failure of the Speed Trim System (Speed Trim function or MCAS function). If one function fails, both functions (the Speed Trim function and MCAS function) are inoperative for the remainder of the flight.

STS. On the 737 MAX which of the following is true regarding the STAB TRIM PRI and STAB TRIM B/U cutout switches on the control stand?. When either switch is placed in the CUTOUT position, stabilizer trim inputs from the main electric, autopilot, and Speed Trim System (which includes the Speed Trim function and MCAS function) are stopped. When one switch is placed in the CUTOUT position, stabilizer trim inputs from the main electric, autopilot, and Speed Trim System (which includes the Speed Trim function and MCAS function) are stopped.

STS. When the Speed Trim System is active on the 737NG or the 737 MAX, what happens when the pilot uses the main electric stabilizer trim switches on the control wheel?. The Speed Trim System is overridden. The Speed Trim System is disconnected until the next flight. The Autopilot is disconnected.

STS. What is the purpose of the MCAS function on the 737 MAX?. The autopilot is disconnected. To increase control column forces by commanding the stabilizer in the nose down direction at elevated angles of attack (AOAs). Aural alert PITCH UP, and UPSET.

STS. During which of the following conditions will the MCAS function not operate on the 737 MAX?. Flaps extended. Flaps retracted. Speed brakes deployed.