Boeing 737 Classic Flashcards
Vfe flaps 2
230 kts.
Vfe flaps 1
230 kts.
Vfe flaps 5
225 kts.
Vfe flaps 10
210 kts.
Vfe flaps 15
195 kts.
Vfe flaps 25
190 kts.
Vfe flaps 30
185 kts.
Vfe flaps 40
158 kts.
V Approach flaps 1
190 kts.
V Approach flaps 5
170 kts.
V Approach flaps 10
160 kts.
V Approach flaps 15
150 kts.
V Approach flaps 25
140 kts.
V Approach flaps 30/40
Vref + 5 kts.
VMO (max. operating speed)
340 kts.
MMO (max. Mach speed)
0.82 Mach
VA (PA 0’) (max. Airspeed full control deflection)
277 kts.
Vlo retract
235 kts.
Vlo extend
270 kts.
Vle
320 kts.
Mle
0.82 Mach
Limits below 10.000’
- Speed 300 kts.
- max. V/S 3000’
Rough airspeed
280 kts. / 0.73 Mach
V window heat inop.
250 kts. below 10.000’
Max. Operating altitude
37.000’ P.A.
Max. Take-off and landing altitude
8.400’
Max. Operating latitudes
- 73 degrees North
* 60 degrees South
Min. ambient temperature
- 73 C
Do not reduced thrust for take-off if (5 items)
- contaminated runway or low friction coefficient < 0,4
- wind shear conditions exist
- anti-skid inoperative
- PMC is off
- low visibility take-off
Altimeters requirements RVSM Airspace
- difference on ground between capt. and F/O: 40’
- difference on ground between any altimeter and A/P elev.: 75’
- difference in flight between capt. and F/O: 200’
Max. N1 RPM
106 %
Max. N2 RPM
105%
Max take-off EGT
930 C
Max. Continuous EGT
895 C
Max. Start EGT
725 C
Max. Oil temperature
165 C
Min. Oil pressure
13 PSI
Minimum oil quantity
- dep. from base: 75%
- dep. out station: 60 %
APU Versions
- GTCP 85-129: green/red marking EGT indicator
- GTCP 36-280(B): APS 2000 indicator without colored marking
APU max. EGT temperature
GTCP 85-129
- max. Start EGT: 760 C
- max. Cont. EGT: 710 C
APU start attempts are not recommended above:
25.000’
No APU use for both:
- Bleed air
- Electrical load
Above:
10.000’
No APU bleed above
17.000’
No APU start above
35.000’
Max. APU altitude
37.000’
Automatic landing limitations (4 items)
- max. Allowable wind speeds
- max./min. glide slope of 3.25 respectively 2.5 degrees
- only flaps 30 or 40 and both engines operative
- both hydraulic and both electrical systems operative
Electrical power: max. generator drive oil temperature
157 C (in)
Rise difference: 20 C
Min. hydraulic fluid quantity
88 %
Min. Fuel for ground operation of elec. hydraulic pump cooling
760 kg.
No speed brake extension when (2 items)
- below 1000’ R.A.
- flaps 15 or greater
Max. Flap operating altitude
20.000’
Max. Differential pressure
8.65 psi
Max. Cabin pressure differential for take-off and landing
0.125 psi
Engine anti-ice on when:
- Ground/flight operations: when icing conditions exist (OAT/TAT below 10 C)
- Except in climb and cruise when SAT is -40 C
Min. Time window heat operative prior take-off
10 minutes
Left annunciator panel
FLT CONT ELEC
IRS APU
FUEL OVHT DET
Right annunciator panel
ANTI ICE ENG
HYD OVERHEAD
DOORS AIR COND
Max. tire speed
190 kts.
Hydraulic system A (PLINGA)
- Auto Pilot A
- ailerons
- rudder
- elevator (feel)
- thrust reverser eng. # 1
- Power Transfer Unit
- Landing gear
- Inboard spoilers
- Nose wheel steering
- Ground Spoilers
- Alternate Brake
Hydraulic system B ( LANAL TOY)
- Auto Pilot B
- Ailerons
- Rudder
- Elevator (feel)
- Thrust reverser eng. #2
- Landing Gear Transfer Unit
- Auto slats
- Normal and auto brake
- Alternate Nose Wheel Steering
- Leading edge flaps & slats
- Trailing edge flaps
- Outboard Spoilers
- Yaw Damper
Standby hydraulic systems provides back-up for (RET):
- Rudder
- Extension of Leading edge devices
- Thrust reversers
- Yaw Damper ( NG)
Landing Gear Transfer Unit activates when (4 items):
- Airborne
- # 1 engine drops below limit value
- Landing gear lever is in UP position
- Either main landing gear is NOT up and locked
Power Transfer Unit activates when (3 items)
- Airborne
- System B Engine driven pump hydraulic pressure drops below limits
- Flaps 15 or less but not up
Min. Flight crew oxygen pressure
1200 PSI
Volume fresh potable water tanks
30 US Gallons ( installed in aft. Cargo compartment)
Fresh water can be pressurized by:
- Bleed air engine #1 or APU
- 115 V AC air compressor
Emergency exit light battery packs operating time
20 minutes
To recharge:
- AC power must be available
- Switch must be in OFF or Armed position
Passenger Oxygen mask automatically deploys when:
- Cabin altitude exceeds 14.000’
- PASS OXYGEN switch must be ON
Passenger oxygen duration
12 minutes
Power Transfer Unit purpose
Supplies additional hydraulic fluid needed to operated the:
- Autoslats
- leading edge flaps and slats
When system B engine driven hydraulic pump is lost
Landing Gear Transfer Unit purpose
Supplies volume of hydraulic fluid to raise the landing gear when system A eng. driven pump volume is lost
Hydraulic leak system A:
- leak in engine-driven pump
The reservoir quantity displayed indicates approximately 20 % full.
System A hydraulic pressure is maintained by the electrical- driven pump
Hydraulic leak system A:
- leak in electrical-driven pump (or both pumps)
Quantity in the reservoirs steadily decreases to zero and all system pressure is lost.
Hydraulic leak system B:
- Leak in engine-driven pump and/ or electrical-driven pump
- If a leak develops in either pump, line or component of system B, the quantity decreases until it indicates approximately zero and system B pressure is lost.
- Fluid remaining in system B reservoir is sufficient for Power Transfer Unit
- A leak in system B does not affect the operation of the stand-by hydraulic system.
Hydraulic leak standby system
- If a leak occurs in the standby system, the standby reservoir decreases to zero.
- System B reservoir fluid level indication decreases and stabilizes at approximately 72 % full.
Changeover (C/O) switch
- Changes IAS/MACH display (MCP)
- Automatic changeover occurs at +/- FL 260
Normal hydraulic pressure (all systems)
3000 PSI
Normal brake pressure
3000 PSI
What does the hydraulic quantity indications show if hydraulic fluid quantity is too low?
RF (refill)
Automatic operation hydraulic standby system during take-off and landing (3 items)
- airborne or wheel spees >60 kts
- hydraulic pressure system A or system B is low
- flaps are NOT up
(Standby system operates until flaps are up)
CAT I minima
DH: not lower than 200 ft.
RVR: not less than 550 m.
Visibility: not less than 800 m
CAT II minima
DH: between 100 ft. and 200 ft.
RVR: not less than 350 m.
CAT IIIA minima
DH: between 0 ft. and 100 ft.
RVR: not less than 200 m
CAT IIIB minima
DH: between 0 ft. and 50 ft.
RVR: between 50 m. and 200 m.
CAT IIIC minima
DH: no DH
RVR: no RVR limitation
FMA Annunciator modes (4 items):
A/T PITCH ROLL A/P
FMA engaged modes A/T (7 items)
- N1
- GA
- RETARD
- FMC SPD
- MCP SPD
- THR HLD
- ARM
FMA engaged modes PITCH (9 items)
- TO / GA
- V/S
- ALT ACQ
- ALT HOLD
- VNAV SPD
- VNAV PTH
- MCP SPD
- G/S
- FLARE
FMA engaged modes ROLL (3 items)
- HDG SEL
- VOR/ LOC
- LNAV
FMA engaged modes A/P (4 items)
- CMD
- FD
- CWS P
- CWS R
Max. Fuel imbalance
453 kg.
Max. Fuel quantity
- each wing main tank: 4.827 kg (2x)
- centre tank: 7.448 kg
- total: 17.102 kg
Max. Fuel temperature
+ 49 C
Min. Fuel temperature
- fuel freezing point + 3 C
- -47 C
Whichever is higher
Do not engage A/P during take-off below:
1000’ AGL
Lowest height for single channel ILS app. A/P engaged
50’ AGL
Lowest height A/P engaged in V/S mode
300’ AGL
(TMD) Thrust Mode Display annunciations
- TO
- R-TO
- CLB
- R-CLB
- CRZ
- G/A
- CON
EADI
Electronic Attitude Director Indicator (artificial horizon display)
Illuminated switch at MCP means:
Mode can be deselected by pushing switch again
When FMA shows N1…
A/T sets power according Thrust Mode Display
At 64 kts (or 84 kts?) N1 (in FMA) change into
THR HLD (Throttle Hold)
A/T servomotor disconnects so A/T cannot change THR positions. However manual adjustment is possible.
After 60 kts g/s F/D will point how many degrees nose up?
15 degrees nose up
until a v/s of 600’ p/m is obtained
Thereafter climb rate between 600 and 1200 fpm
(Pitch command is pitch/speed function)
Max. Roll limitations until 400’ RA
4 degrees bank angle
Above v/s of 1200 fpm the F/D command bar sets pitch to obtain:
V2 speed + 20 kts.
With maximum of 25 degrees nose up
THR HLD changes in ARM (FMA) when:
- 18 seconds after liftoff
And
- above 400’ RA
At 1500’ after T/O, A/T will change “ARM” into
- Thrust reduction to N1 climb limit
- N1 in FMA
- CLB in TMD
Vertical speed range (MCP)
+ 6000 fpm
- 7900 fpm
FD TO/GA mode on ground is only available if
Both F/D switches are in “on” position
LNAV engage mode criteria
- less than 3 NM off track
OR (!)
- Intercept angle less than 90 degrees
RTO active above:
90 kts.
A/T does not arm when which FMC related item is missing
OAT (Outside Air Temperature)
N1 in FMA means:
A/T have set the maximum possible power as indicated in the TMD (thrust mode display)
When FMC commands speed, the IAS/Mach display is:
Blank
You loose 1 generator (blue GEN OFF BUS light and amber (BUS OFF) light, in APP mode ABOVE 800’ RA. The F/D bar at the effected will disappear.
How can you recover the F/D guidance bar?
Switch of the F/D switch at the unaffected side and F/D will appear again.
Above 800’ RA: 1 GEN = only 1 F/D
You loose 1 generator (blue GEN OFF BUS light and amber (BUS OFF) light, below 800’ RA. What is the effect on your F/D (bar) guidance?
No effect. Below 800’ RA all F/D modes are available on both sides in case you loose a generator.
Go Around mode is available between which altitudes?
Between 2000’ RA and touchdown.
Activated by TO/GA switches
With or without F/D switches in on position
Difference between pressing 1 and 2 time(s) TO/GA switch
Once –> Reduced GA power (A/T FMA = GA)
Twice –> Full GA power (A/T FMA = N1)
(Available till 2000’ RA)
By pressing TO/GA switch for GA, the FD bar initiates 15 degrees nose up, thereafter FD will pitch for go around target speed. This speeds depends on:
Actual flap setting
How can you deselect the APP mode at the MCP?
- Both F/D switches to off
- Change ILS frequency
- Press TO/GA and perform a Go Around
- disengaging A/P
- overriding the control wheel column
In APP mode:
- F/D “V” bar disappear and;
- No guidance will be available for flare/landing
Passing which altitude?
Passing 50’ RA
G/A mode:
When can you select any other pitch or roll mode?
After passing…
400’ RA
Below this altitude TO/GA mode maintains:
- last (ground) track when G/A was initiated
- pitch for 15 degrees nose-up
G/A mode:
When reached G/A altitude, which roll mode will automatically appear on MCP and in FMA
HDG SEL
Standard bank angle airBaltic
25 degrees
CWS Pitch (P)
Pitch is set manually by yoke and pitch will be maintained when yoke is released
CWS Roll (R)
Roll is initiated manually by yoke and bank angle will be maintained when yoke is released.
Only available when roll is greater than 6 degrees
