TECI GENERAL

737-800 dimensions

• wings span : 35.79m

• Lenght : 39.50m

• Height :12.50m

737-700 dimensions

• wings span : 35.79m

• Lenght : 33.60m

• Height : 12.50m

737-800 turning radius (180°)

• 24.3m

• No turn from an obstacle smaller than 5.4m wing tip and 7.4m nose

737-700 turning radius (180°)

• 20.4m

• no turn 5.4m from wing tip and 9.8m from nose

Flight crew oxygen indicator should be at ….

1850 psi

PASS OXYGEN button :

• NORM

• ON

• NORM : at 14000ft cabin altitude = masks drop

• ON : manually releases masks

ELT transmits tone and position on

• 121.5 Mhz

• 243 MHz

• 406 MHz

Takeoff and Landing tailwind limitation on 737-700 & 737-800 are :

• 737-700 : 10 kts tailwind

• 737-800 : 15 kts tailwind

CAT II & CAT III Autoland limitations for both aircraft ? Headwind, crosswind, tailwind

• 737-700 :

  • 25 kts headwind

  • 20 kts crosswind

  • 10 kts tailwind

• 737-800 :

  • 25 kts headwind

  • 20 kts crosswind

  • 15 kts tailwind FLAPS 40

  • 12 kts tailwind FLAPS 30

Max TO component

• 33 kts on dry RWY

• 25 kts on Wet RWY

Max operating altitude & Max TO / landing altitude

Max operating altitude : 41000 ft

Max TO/LDG altitude : 8400 ft

Max altimeter difference between CPT and FO :

• In flight

• On ground (0 - 5000 ft) (5001 - 10000ft)

Max altimeter difference between CPT and FO

in flight : 200 ft

On ground 0 - 5000 ft : 50ft

On ground 5001 - 10000 ft : 60 ft

Max difference of altimeter with field elevation

75 ft

Overwing exits unlock if :

• AC on ground

• One door is open

• Thrust lever are not fully advanced

APU is monitored by ….. and if an amber light related to APU lights up, what happens ?

ECU (electronic control unit)

APU will shutdown automatically

why is BAT ON needed for APU operations ?

Because ECU needs battery power

How can APU be started ?

• AC power (provided from AC TRANSFER BUS 1)

• Main battery power

with AC fuel pumps operating for the APU fuel is drawn from ….

With AC fuel pumps inoperating for the APU fuel is drawn from ….

• AC fuel pumps : left side fuel manifold

• NO AC fuel pumps : Number 1 tank

What happens when APU is shut down :

• Generator stops

• Bleed air valve closes

• Fuel valve closes

• Air inlet valve closes

• Fuel (in KG) in wing tanks

• Center tank

• 3915 KG

• 13066 KG

How is crossfeed valve operated ?

DC power

What parameters should indicate a FUEL LEAK ?

• 230 kg imbalance in 30 min

Fuel temp should be kept at …

• -3°C above freezing point

• -43°C

Whichever is higher

ENGINES :

How many fire detectors and extinguishers bottles ?

• 2 fire detectors loop per engine

• 2 fire extinguisher bottles (in total)

Main wheel well : how is fire detected and how is it extinguished ?

• 1 fire detectors loop

• No extinguisher : lower speeed, extend gears. No retraction before 20 min after WHEEL WELL FIRE light has extinguished

CARGO : fire detector and extinguisher ?

• Dual loop configuration

• 1 fire extinguisher bottle

Describe 737NG motors :

• nature

• Thrust

• What is N1

• What is N2

• CFM56-7

• Dual rotor, axial flow

• 27300 pounds of thrust

• N1 rotor : low pressure rotor & turbine

• N2 rotor : high pressure rotor and turbine, all gearboxes are powered by it, bleed air starter drives N2 rotor for engine start

What EEC (electronic engine control) modes exist ?

Each engine have EEC dual channel

• Normal mode

• Alternate : soft/hard

CPT control wheel is connected by cables to ….. through the ……

FO control wheel is connected by cables to ……. Through the …….

Both control wheels are interconnected

• CPT : Aileron power contrôle Unit (PCU) through the aileron feel and centering unit

• FO : Spoiler PCU through the Spoiler Mixer

Spoilers deflection start when control wheel is turned by more than :

10°

Mach trim system provides stability above

MACH 0.615

What is STS used for and what are the Conditions for STS (speed trim system) operation :

Stabilizes the aircraft by commanding the stabilizer in a direction opposite of speed change

• STS Mach gain is fully enabled between 100 Kias and Mach 0.60 (starts to fade-out at Mach 0.68)

• 10 sec after TO

• 5 sec following release of trim switches

• Autopilot not engaged

• Sensing of trim requirement

After take off and before landing : full rudder authority is limited above …… kts by reducing hydraulic pressure by ……

• 135 kts

• 25%

FFM Force flight monitor

Activâtes standby system for rudder in case of Jam

Flaps : no extension above ….

20 000 ft

Flaps protection 737-800 :

• flaps 40

• Flaps 30

• Flaps 25

• Flaps 10

• Flaps 40 : if speed is above 163 kts —> flaps 30. re extension at 158 kts

• Flaps 30 : 176 kts —> flaps 25. 171 kts

• Flaps 25 : 191 kts —> flaps 15. 186 kts

• Flaps 10 : 211 kts —> flaps 5. 206 kts

Flaps protection Boeing 737-700 :

• Flaps 40

• Flaps 30

• Flaps 40 : 163 kts —> flaps 30. 158 kts

• Flaps 30 : 176 kts —> flaps 25. 171 kts

What does FSEU do (flap slat electronic unit)

Monitor and control flaps and slats for asymmetry and skew conditions

In case of malfunction of system B, how can trailing edge flaps be operated ?

Electrically

What happens if the Yaw damper switch moves to OFF ? Can it work again at some point ?

If it switches to OFF, it is not possible to turn it ON again.

If Standby hydraulic system takes Over : Yaw damper switch resets to ON and it will be powered by the standby system

If System B fails, how are operated TE flaps and LE flaps ?

• TE flaps : can be extended retracted electrically thanks to alternate flaps switch

• LE flaps : can only be extended by the standby hydraulic system

What happens to flight logic if ENG ANTI ICE is ON ?

What happens to flight logic when WINGS ANTI ICE is ON ?

What happens when we turn it to OFF ?

• ENG ANTI ICE ON : stick shaker logic changes for icing conditions + airspeed limits changes. When turned off : back to normal

• WING ANTI ICE ON : stick shaker logic changes but not airspeed. If OFF : its not going back to normal

Hydraulic system A powers :

• Ailerons, rudder, elevator

• Flight spoilers

• Ground spoilers

• Alternate brakes

• Reverser 1

• Autopilot A

• Normal nose wheel steering

• Landing gear extension/retraction

• PTU

Hydraulic system B powers :

• ailerons, rudder, elevator

• Flight spoilers ONLY

• LE flaps And Slats

• Trailing edge Flaps

• Normal Brakes

• Reverser 2

• Autopilot B

• Alternate nose wheel steering

• Landing gear transfer unit (retraction is possible only)

• Autoslats

• Yaw damper

Standby hydraulic system powers :

• Thrust reversers

• Rudder

• LE flaps and slats (extension only)

• Standby yaw damper

When would standby hydraulic system operate automatically ?

If all are mets :

• Loss of syst. A and B

• Flaps not UP

• AC airborne or wheel more than 60 kts

• Flight controls A and B switch ON

Bleed air is supplied from which section of the compressor ?

5th to 9th compressor stages

From where does power come from ?

• for AC power :

• For DC power :

• AC power : Engines and APU

• DC power : 3 transformer rectifiers and 2 batteries (24v)

Battery supply standby power for (duration)

60 min

Can a single engine operate 2 packs ?

NO

APU can supply bleed air for how many packs ?

• Ground

• In flight

Ground : 2

In flight : 1

Arrêt à AUTOFLIGHT