1.) What is the Height of the tail (700W, 800W & 800S)?
(FRM-700/800, 1-1 to 1-5 )
2.) What is the Length of the B-737-700?
-700 = 110’-4”
-800 = 129’-6”
(FRM-700/800; 1-1 to 1-3)
3.) What is the Wing Span of the B-737-700?
117’-5” (-700W & -800W)
(FRM-700/800; 1-1 to 1-3)
4.) What is the Height of the Winglets?
21’-1” (-700W & -800W)
(FRM-700/800; 1-1 to 1-3)
5.) What type of engines do the -700, -800 & Max have?
CFM 56-7B24 (-700)
CFM 56-7B27 (-800)
CFM Leap-1B (MAX)
(Dual-rotor, axial-flow, turbofans.)
(FRM-700/800; 220.127.116.11, pg 7-19 to 7-21)
(Leap-1B CFM Expanded Brief)
6.) When does the Isolation VALVE open when selected to Auto?
The VALVE opens whenever:
- one of the Pack SWITCHES or - #1 or #2 bleed SWITCHES is in the OFF position.
“4 corners switch”
7.) When does the DUAL BLEED light illuminate?
Anytime the APU bleed VALVE is open & either:
- the #1 bleed SWITCH is Open,
- or the #2 bleed SWITCH&
IsolationVALVE are Open.
8.) When will a pack automatically go into High?
1.) Pack switch in High,
2.) In flight; w/ flaps up and one pack not operating.
3.) Anytime both eng. bleed switches OFF and APU bleed switch ON.
9.) When will the “APU High Air Flow” mode, engage?
On ground with, APU bleed Switch ON, and either or both pack switches placed to High.
(FRM-700/800, 18.104.22.168, pg 2-22 & 2-13)
(FRM MAX, 22.214.171.124, pg 2-13)
10.) When is the equipment cooling Exhaust OFF light inhibited?
In the event of a FORWARD cargo fire warning, the equipment cooling EXHAUST fan is shut off and the associated light is inhibited.
(FRM-700/800; 2-25 & 2-30))
11.) When will the Emergency Exit Lights illuminate?
A.) Our switch to ON
B.) Or automatically when in ARMED, and power to DC bus #1 or if AC power has been lost.
C.) Switch on aft FA’s panel to ON, and their switch overrides Auto.
12.) What lights in the cockpit illuminate on emergency lighting?
Flt. deck dome light has a second bulb that is lit by the Emergency lighting system.
13.) When do the overwing Type III doors lock?
- When either engine is running, and three of the four Entry/Service doors are closed, and A/G logic says A/C is in air or both thrust levers are advanced.
- Doors will unlock when any one of the above conditions is not met or with the loss of DC power.
14.) When will you get an amber LEFT OVERWING or RIGHT OVERWING warning light?
Along with the Master Caution lt, either of these lights will illuminate when their respective door(s) is not fully closed and locked or when the flight lock is not fully engaged, either during the TO roll or in flight.
15.) If an overwing door lock fails in the locked pos. or a fault is detected, how will it be annunciated?
The PSEU, and Master Caution lights will illuminate, but these lights are inhibited from TO until 30 sec. after touchdown.
16.) When does the Recirculation Fan work?
-700: Anytime the fan switch is in AUTO, except with both packs on “and” one or both in HIGH.
-800 & Max:
● In flight –
– The Lft recirc. fan operates if both packs are operating unless either PACK switch is in HIGH.
– The Rt recirc. fan operates if both packs are operating unless both PACK switches are in HIGH.
● On the ground –
– The Lft recirc. fan operates unless both PACK switches are in HIGH.
– The Rt recirc. fan operates even if both PACK switches are in HIGH.
(FRM MAX, 2.1.2, pg 2-4)
17.) Where does the Recirculation fan take air from and move it to?
It takes air from the pax cabin and E and E bay and runs it around the lining of the forward cargo bay, and through a filter before dumping it in the Mix Manifold.
18.) If an Equip. Cooling OFF light illuminates, when will the light go out?
After the alternate associated ALTN Supply or Exhaust fan is selected, the light should go out within 5 seconds.
19.) What other warning is given with an Equip. Cooling OFF light?
The Crew Call horn in the nose wheel well will sound if the a/c is on the ground. .
20.) Where does the Equip. Cooling sys. take air from and move it to?
It takes air from the pax cabin and routes it over the flight deck displays, overhead and aft electronic panels, flt. deck CB panels, and E and E bay before dumping it overboard, or into the lining of the forward cargo bay if in flight.
21.) On the -800, what condition will cause the PACK, Master C. and AIR COND lts to illuminate?
A primary “or” standby Pack Control fails, the pack is controlled by the other one, and the lights illuminate during RECALL, but if both controllers fail, the lights automatically illuminate, and the pack continues to operate without control, unless it overtemps and trips off.
22.) On the -800, what is unique about the equipment cooling fan system?
In the event of a forward cargo fire warning, the equipment cooling Exhaust fan is shut off and the equip. cooling exhaust OFF light is inhibited.
23.) On the -800, what happens when a ZONE TEMP lt. illuminates?
An over temp in the associated zone supply duct has occurred and the respective trim air modulating valve has been closed.
24.) How does the -800 Recirculation Fan system differ from the -700?
There are 2 fans, instead of 1, and they are air/ground dependent in their modes of operation.
25.) What is the Electrical Source of power for the outflow valve in all three pressurization modes?
The outflow valve is controlled by DC Motor(s), and the MAN mode uses a separate (slower) motor powered by the DC Standby Bus.
26.) When will the Overboard Exhaust Valve for the Equip. Cooling system be driven full open?
A.) -700, when either pack is in High and the recirc. fan is off.
B.) -800 when either pack switch is in high and the right recirc. fan is Off.
C.) On B737-700W aircraft (as installed) & all B737-800W aircraft, during pressurized flight, the overboard exhaust valve will be commanded to a smoke mode upon a Forward Cargo Fire Alarm.
D.) The valve is always open on the ground.
27.) How can you open the Overboard Exhaust Valve in flight manually?
Turn off the recirc fan (Rt. fan in -800) and move one of the pack switches to HIGH.
28.) When is the Flight Recorder powered?
A.) In the air, it operates any time elec. power is available.
B.) On the ground, either engine must also be running.
C.) TEST – also powers the system on the ground.
(Additionally, it records data for at least the last 25 hrs of operation.)
(FRM-700/800; 10-81 & 102)
29.) When is the Cockpit Voice Recorder (CVR) powered and when can it be erased?
The CVR is powered anytime AC power is applied to the airplane.
It records 4 independent channels of the last 120 minutes of audio, and can only be erasedon the ground, with the parking brake set.
(As Installed B737-700W, B737-800W) the cockpit voice recorder backup power source shall continue to provide power to the CVR for 10 minutes after primary power is interrupted either by normal shutdown or for any other reason.
(FRM-700/800; 5-25 & 34)
30.) During an Engine battery start with no power on the airplane, what engine indications will you have?
Only N1, N2 and oil quantity, until 15% N2 when the EEC is powered and then you will get all engine parameters.
31.) When will the EEC switch to the Approach Idle mode?
In flight, when flaps in landing config. or Engine anti-ice is ON for either eng. or if a fault in the EEC prevents it from receiving either of those signals, it begins below 15000’.
32.) When does the Auto-Relight system activate?
During an Auto-Relight condition (uncommanded rapid decrease in N2, or N2 below idle RPM, [triggered by a flame out]) BOTH igniters are activated.
33.) What do the CONT, and FLT positions of the engine start switches do with regard to the igniters?
- The CONT position provides ignition to the SELECTED igniters when engine running
- FLT provides it to BOTH igniters with or without engine running.
- In CONT the Auto-Relight function will provide power to both igniters if it engages.
34.) What things will cause the amber pressurization AUTO FAIL light to illuminate?
1.) Loss of DC power
2.) Controller fault
3.) Outflow valve control fault
4.) Excessive differential pressure >8.75 psi (if controller is not responding properly)
5.) Excessive rate of cabin change +/- 2000 fpm
6.) High cabin altitude >15800’
35.) What is indicated if the FAULT lt. fails to illuminate when performing the Fault/Inop Detection test?
It indicates that the fault MONITORING system is inop.
36.) What is indicated if an engine fire warning switch and an ENG OVERHEAT lt. fail to illuminate when performing the Fire/Overheat Warning test?
This is an indication that a detection loop is inop.
37.) What is the normal IRS alignment time?
38.) When will the Packs automatically switch from normal flow to High flow?
With Eng bleeds open, in the air, flaps up and the packs in AUTO, the operating pack will automatically switch to High flow if the other pack stops operating.
It also occurs if both eng. bleed switches are OFF and the APU bleed switch is ON, regardless of flap setting, air/ground status or # of packs operating.
39.) Where is the LRBL on the B737?
The Least Risk Bomb Location is at the center of the aft galley service door.
(Ops Binder, pg. 4-21)
40.) What do the DISPLAYS Source and Control Panel switches control?
The Source knob selects which DEU controls which set of DU’s, and the Control Panel switch provides a means of manually switching control of the Capts and FOs displays to a single EFIS control panel.
41.) When are the secondary engine indications displayed?
1.) Selected by the Multi-Function Display (MFD) Engine (ENG) key,
2.) In flight when start lever moved to CUTOFF,
3.) In flight when an engine fails,
4.) A secondary engine parameter exceeds normal operating range.
42.) How many packs are we authorized to run off the APU?
-700/800, Two on the ground and one in the air.
43.) How many packs are we authorized to run off of one engine?
One pack, regardless of air/ground position.
44.) When do the Ram Air doors automatically drive full Open?
On the ground, or during flight with the flaps not up?
45.) When are the Deflector Doors extended?
On the ground when activated electronically by the air-ground safety sensor.
46.) When is automatic pack switching to High Air Flow inhibited?
When the airplane is on the ground, or in flight with the flaps extended, to insure adequate engine power for single engine operation.
47.) Are Autobrakes, Parking brake and Anti-skid available on the Alternate brake system?
The Autobrakes are not, but the Parking brake is and the Anti-skid is available on wheel pairs.
48.) How is an APU Fire indication fundamentally different than an Engine or Cargo Fire indication?
The Fire indication on the APU, automatically triggers an APU shut-down, without any action from the crew.
49.) Why does the Cargo Fire Fault light illuminate after the battery has been turned on but before AC power has been applied to the aircraft?
Because the Cargo fire DETECTION system is powered from DC bus 1 and 2.
50.) Why does the Wheel Well fire light not test on battery power alone?
Because the WW fire detection system is powered by the No. 2 AC Transfer Bus.
51.) What causes the Stab trim speed to change from High to Low?
It works faster with flaps out, and there are four speeds dependent on flap position or whether you are using main or autopilot trim.
Autopilot trim is slower than main electric trim for the given flap condition (up or not up).
52.) At 135 kts. and above, what happens to the rudder?
A and B pressure are reduced within its PCU by approx. 25% to reduce full rudder authority after TO and before Landing.
53.) What conditions have to be present for the Speed Brake Load Alleviation system to work?
1.) Under high gross weight & airspeed combinations, if the speed brakes are deployed to the FLT DETENT, they automatically retract to 50%.
- The SPEED BRAKE lever moves to reflect the position of the speed brakes.
- Manual override is available.
1.) Flaps Up.
2. GW > 143000 lbs.
3. IAS > 320 KIAS, if all these conditions are present, 50% is the new somewhat flexible limit.
(AOM, 3-23) (AT,AOM, FLT-13)
54) When you move the APU switch to OFF, what happens?
1.) Trips the APU Generator,
2.) Closes the APU bleed valve,
3.) Extinguishes the APU GEN OFF BUS lt.
4.) Starts 60 count to shut down.
55.) Where are the Left and Right eng. Igniters powered from?
Left ign. – Associated AC transfer bus,
Right ign.– AC Standby bus.
56.) What does a CDS Fault mean in the lower L. corner of the PFD?
A CDS (Common Display System) fault has occurred.
It is displayed on the ground only, and prior to the start of the second engine.
(White – Dispatchable, Amber – Non-dispatchable)
57.) What does an amber DSPLY SOURCE Fault mean in the lower L. corner of the PFD?
A single DEU has been selected, either manually or automatically(due to a DEU failure), to drive all six display units.
(FRM-700/800; 10-91 & 10-25)
58.) What will cause an amber fuel LOW indication on the upper DU?
- Quantity less than 2000 in related main tank,
- Displayed until quantity is increased to 2500.
(The fuel quantity arc and digits on tank(s) with low fuel quantity turn amber.)
(FRM -700/-800, 12-4)
59.) What will cause an amber fuel CONFIG indication on the upper DU?
- Center tank qty. > 1600lbs, both center pumps are producing low or no pressure, and either engine is running.
- Will remain illuminated until center tank quantity is < 800lbs, one center pump is producing high pressure or both engines are off.
(FRM -700/-800, 12-5)
60.) What will cause an amber fuel IMBAL indication on the upper DU?
- Main tanks differ by more than 1000lbs, inhibited on ground, inhibited by LOW indication when both conditions exist.
- Displayed until imbalance is reduced to 200lb
(FRM -700/-800, 12-5)
61.) What is the min pressure that should be indicated on the brake accumulator gage in the right wheel well?
62.) What indication will you have on your post flight, if you forget to turn off your IRS’, before you shut off all AC power?
The On DC lt. in the cockpit illuminates, and the Ground-Call horn in the nose wheel well will be on, indicating that the left IRS is using, back up, DC power from the Switched Hot Battery Bus.
(FRM -700/-800, 11-27)
63.) Minimum fuel for ground operation of an electric hydraulic pump is?
1675 lbs in the related main tank.
(FRM -700/-800, 13-6)
64.) Which Leading Edge devices are heated when using the Wing Anti-Ice System?
The wing anti–ice system provides protection for the three inboard leading edge slats by using bleed air.
The system does not include the leading edge flaps or the outboard leading edge slats.
The wing anti–ice control valves are AC motor–operated, and the system is effective with the slats in any position.
(FRM -700/-800, 3-10)
65.) What happens when the FLAP lever is moved from the UP position to the 1, 2, or 5 position?
TE flaps always extend to the commanded position
LE Flaps extend to the full extended position and
LE Slats extend to the “extend” position & don’t travel to the “Full Extended” position, until the flap lever is positioned beyond the 5 position.
66.) With respect to APU fueling, what is significant about ships N798SW, N270WN & N271LV?
- A DC-operated APU fuel boost pump is installed to ensure positive fuel pressure to the APU fuel control unit.
- During APU start and operation, the pump operates automatically when the APU fuel control unit senses low fuel pressure.
- The pump shuts off automatically when an AC fuel pump pressurizes the fuel manifold.
- (FRM -700-800 , 12.2.4, pg 12-10)
67.). What conditions are required for speed trim(STS) operation?
- STS Mach Gain is fully enabled between 100 KIAS & Mach .60 with a fade out to zero by Mach .68
- 10 seconds after takeoff
- 5 seconds following release of trim switches
- Autopilot not engaged
- Sensing of trim requirement
(The system is a speed stability augmentation system designed to improve flight characteristics during ops with a low G. wt, aft CG, and high thrust when the AP is not engaged. The STS returns the aircraft to a trimmed speed by commanding the stabilizer (using the autopilot stabilizer trim), in a direction opposite the speed change.)
(FRM -700/-800, 9-18)
68.) How are the Emergency Exit Lights powered & how long will they last?
Individual emergency exit light batteries will supply a minimum of 10 minutes of lighting.
(QRH -700, E-2)
69.) After landing, autobrake application begins when?
- Both forward thrust levers are retarded to IDLE.
- The main wheels spin-up.
Note:Landing autobrake settings may be selected after touchdown prior to decelerating through 30 kt of ground speed.Braking initiates immediately if the above conditions are met.
(Next Gen FRM, 14-10)
70.) After braking has started, what pilot actions will disarm the Autobrake system immediately and illuminate the AUTO BRAKE DISARM light?
1 - Moving the SPEED BRAKE lever to the down detent.
2 - Advancing the forward thrust lever(s), except during the first
3 seconds after touchdown for landing.
3 - Applying manual brakes.
4 - Moving the selector switch to the OFF position also disarms the system, but this action does not cause the AUTO BRAKE DISARM light to illuminate.
(Next Gen FRM, 14-10)
71.) What is the minimum pressure for the engine fire bottles in the left main wheel well?
Verify the pressure gauge reads 600 psi per placard (as installed).