TECH DECK Flashcards
REfer to the RF indication to the right of the Hydraulic system quantity indication.
This indication is displayed.
Only when the hydraulic is below 76% in either system A or B and the aircraft is on the ground with both Engines shut down.
Or after Landing with flaps up during Taxi.
Cargo compartment
Smoke detection system
Powered by?
DC Bus 1 and DC Bus 2
During normal ops
Hydraulic quantity indications vary
By Raising or Lowering the Land Gear and Lead edge devices
Once Activated, the APU DC operated fuel pump operates automatically UNTIL
an AC fuel pump pressurises the manifold
Amber Display Source annunciation bellow SPEED TAPE indicates
A single DEU has been manually or automatically selected to all six display units
Which of these is indicated by the HYDRAULIC BRAKE pressure indicator
MAXIMUM pressure 3500psi in white
The flaps/spats ELECTRONIC unit (FSEU) provides
Protection for LE devices and TE flaps if two or more LE Flaps or LE slats move from commanded position.
Zone TEMP maker light illumination for CONT CAB indicates
Both a duct temp overheat, or a failure of both temperature controllers.
If all TEMP ZONE SELECTORS are positioned OFF
the LEFT PACK maintains 24 DEG, RIGHT PACK 18 DEG
If the Autopilot ALT HOLT mode is manually overridden with the control column pressure, which of the following occurs
The autopilot changes to CWS P and returns to ALT HOLD if the control pressure is released within 250ft of the elected ALT.
ILL of FAULT light with the over heat detector in NORMAL indicates
Both detector loops for and engine have FAILED
Predictive windshear warnings
will activate up to 1.5 NM ahead of the AC
In addition to HYD sys A and B, the rudder can be powered by the STBY HYD sys through the
STBY rudder PCU
Normal Brake SYS Powered by HYD
SYS A
Auto brake uses HYD SYS
SYS B
Only operates when normal brake system is operating
Landing AUTOBRAKE setting may be selected after touchdown
Prior to decelerating through 30 KTS groundspeed
When is the ENGINE ANTI-ICE turned on if icing conditions exist on the Ground
As part of the AFTER START checks.
What could cause the AMBER anti SKID light to ILLUMINATE
FAULT in the PARK BRAKE system
MIN in flight tank FUEL TEMP is
3 Degrees Above fuel freezing point or -43 DEG, whichever is higher .
The Air/ Ground system receives Logic signals from
SIX Sensors, TWO on Each Landing Gear.
Source of ELEC power for the Engine Fuel shutoff valve
The Battery Bus
Manual IRS entry of present position or magnetic heading are normally accomplished on the
POS INIT page or ISDU
The Amber LOW PRESSURE light for SYS B HYD pump illuminates what are the other indications
MASTER CAUTION, and HYD annunciation lights illuminate
*The Red Landing GEAR indication lights are illuminated under which of the following conditions
Both: Landing Gear is in disagreement with the landing gear lever position
and the Landing Gear is not down and locked (With either or both thrust levers retarded to idle, and below 800ft AGL.
on GRD,
BATT SWITCH OFF
STBY POWER SWITCH on BATT
Switched hot bat bus IS ?
NOT POWERED
If ON DC on the LEFT IRS comes on steady
it MEANS
Related IRS is operating on
DC POWER from
SWITCHED HOT BATTERY BUS
FCCs
Number of ?
2
After normal T/O. the commanded pitch command is ?
V2 + 20
Right IRS is electrically powered from
Normally AC transfer Bus 2
In an Emergency from the switched Hot bat bus
MAX 5 MINS
The ENG start Switch OFF,
Austomatic Ignition will occur
if N2 is between 57% and 50%
With AUTOBRAKE select switch to RTO,
Autobraking is initiated when?
Wheel spin 90 KTSor more from thrust levers at IDLE
With MFD system, in SYS
The LOWER DU shows
Hydraulic Pressure and quantity only
If Landing is Made with the RTO selected
AUTO BRAKE DISARM light illuminates for 2 seconds after touchdown
In AUTO, the FASTEN SEAT BELTS and return to seats signs
ILLUMINATES when the FLAP and GEAR are extended
MAX ZERO FUEL WEIGHT
(61,688 KG)
MAX LAND WEIGHT
(65,317 KG)
DEU 1
CAPTAINS
(Capt 28V DC STBY BUS) supplies data to the captains outboard, inboard and upper DUs
DEU 2
(F/O 28vV DC BUS 2 ) supplies dRa to the F/Os outboard inboard and lower DUs
GPWS (LOOKS OUT FOR )
WINDSHEAR TERRAIN OBSTACLES GLIDE SLOP DEV CONFIG ALERTS
SINGLE CHANNEL FAULTS
PSEU
AUTO SLATS
MACH TRIM
SPEED TRIM
Overspeed Clacker receives Aural warnings from
ADIRUs
Speed clacker can be operated in ON Ground or in AIR
ON ground only
ADIRU provides
P osition
A ttitude
A ltitude
S speed
TCAS Resolution Advisory generated when
The conflicting AC is 25 seconds fro the point of closest approach
Fuel for APU supplied
Left side of fuel manifold
If NOSE GEAR steering lockout pin is not installed for pushback and towing
SYSTEM A HYDRAULIC PUMPS must be switched off
TO RECIEVE NAV and ADF voice and range audio
Set the filter to BOTH
During VNAV path decent and below the speed restriction altitude
The FMC alerting message OVERSPEED DISCONNECT means
VNAV has disengaged because airspeed has exceeded FMC target speed by more than 15KTS
Autopilot Trim & MAIN Stabiliser Trim use
Single ELECTRIC TRIM MOTOR
EGT Display, both box and dial, TURN RED and the EEC automatically turns off IGNITION and shutoff fuel to the ENGINE if
The EGT EXCEEDS the starting limit during GROUND starts
No 1 DRIVE light ILLuminates AMBER. This is directly caused by
LOW OIL pressure in the IDG
With the Loss of HYD System B (System A operating Normally)
Main and STBY Yaw damper functions are lost
PTU provides alt source of power for the Autoslat System if
A loss of Hydraulic System B is sensed
APU MAINT Light means
APU can be operated
If thrust lever (s) are advanced after Touchdown
After 3 Seconds in the advanced position,
AUTOBRAKE DISARM LIGHT WILL ILLUMINATE
Predictive Wind shear alerts
Below 1200FT Rad alt
During flight with HYD system B inoperative (No Fluid in System B)
The STBY HYD System operates the leading edge slats and leading edge flaps to fully extend position only
To climb to FL280 in the shortest distance, MAX ANGLE should be selected on page?
CLB
PROXIMITY TRAFFIC SYMBOl
WHITE SOLID DIAMOND
Accessory Gearbox receives info from
N2 Rotor
BLEED TRIP OFF LIGHT
INDICATES excessive bleed air pressure or Temp
FMC Advisory message BUFFET ALERT Indicates
Current Conditions results in MANOEUVERING MARGIN less than Specified.
During primary Charge CYCLE
BAT CAN BE AS HIGH AS
30 VOLTS
When Does RAD ALT display a DIGITAL readout
Between 2500ft and 1000ft AGL
LOW PRESSURE LIGHT Main tank indicate?
Low fuel pump OUTPUT pressure
Bleed trip off light, What valve has automatically closed
ENGINE BLEED AIR VALVE
HYdraulic Pressure from System B will be used to retract the landing GEAR
After failure of No1 Engine with the Landing Gear still down and the Landing gear lever is positioned up.
Antenne Switiching from TAIL ANTENNA to NOSE ANTENNA OCCURS when
LOC frequency is selected and VOR/LOC is armed and ENGAGED
RAM AIR SYSTEM DEFLECTOR DOORS
EXTEND on the GROUND only
AC not certified above
82N and 82S
AFTER FMC CDU preflight , Flight crew notices the ACTIVE NAV DATA BASE is expired, must be changed,
WHAT will route page look like after NAV DATAbase change
BLACK, Requiring RELOADING.
TOGA Switch pressed, once bellow 2000FT RA
AUTOMATIC GO AROUND
FLARE ARMED
ILS Channel APP
Auto throttles advance thrust levers to
REDUCED go around N1
WHeel spinnup not detected on Landing
With the speed brake armed the flight spoilers will rep
Automatically when
When the Air/Ground senses the ground
any strut compresses
If the Fault light on IRS mode SELECTOR UNIT ILLUMINATES
Indicates
A system Fault affecting the respective IRS ATT and /or NAV mode has been detected
Power source for FIRE EXTINGUISHING
the HOT BATT BUS
DOTTED RED AREAS
TERAIN DISPLAY
Terrain more than 2,000ft above the airplane ALT (BARO)
Which statement is true regarding AILERON TRIM
If the autopilot is engaged
The amount of trim is not indicated on the scale.
ALL WINDOW HEATS SELECTED ON
The Green window heat ON extinguishes
WHY
System is at Correct TEMP.
MIN EQUIP for RAs to be GENERATED
The other AC needs a MODE C Transponder
When the manual gear extension access door is open
Manual landing gear extension may be accomplished with the Landing gear handle in the up position
WITH ENGINE START switches OFF, Automatic IGNITION will occur
IF N2 is between 57% and 50%
During preflight procedure the trim air switch is left in the OFF position and only one pack is selected ON for airconditioning. What is the correct consequence?
With the TRIM AIR selected OFF, the pack attempts to produce an air temperature to satisfy the average temperature demands of all three zones.
An overheat condition causes the pack valve
in the cooling cycle:
to close and the PACK
light to illuminate
On the GROUND, with both pack switches set to HIGH and both RECIRC FANs selected to AUTO:
the left recirculation
fan will shut down
With pack switches set to AUTO, if one pack fails, when does the remaining pack provide high air flow
In Flight (With Flaps UP)
The controller programs the cabin to land slightly pressurized. After landing to depressurize the aircraft
while taxiing in, the
controller slowly drives
the outflow valve fully
open
If all Temperature Zone
Selectors are positioned
OFF:
the left pack maintains 75degF,
the right 65degF
LEFT 24DEG RIGHT PACK 18 DEG C
When pressing Master Caution Recall the CONT CAB amber ZONE TEMP light illuminates. What is correct?
Due to failure of the primary flight deck temperature control, automatic switching to the backup system has occurred.
What indications can be reset with TRIP RESET (Button)
ZONE TEMP (Duct overheat) , PACK, BLEED TRIP OFF
The wing-body overheat light comes on. What is the related master caution warning?
AIR CON
ENGINE BLEED AIR VALVE
PRessure Regulator & SHUTTOFF VALVE
The bleed air pressure
indicator has L and R
pointers. These
pointers:
may indicate a L/R
duct pressure difference
which is considered
normal as long as there is sufficient air for cabin pressurisation
may indicate a L/R
duct pressure difference
which is considered
normal as long as there
the high stage valve
modulates open to
maintain adequate
bleed air pressure
From where does the
Cabin Auto Controller
get its inputs?
From the ADIRUs.
In MANUAL
pressurization mode the
outflow valve is driven
by?
a motor supplied from
DC standby bus
The cabin begins to
pressurize:
ON the ground at high power settings
During flight with Hyd SYS B inop (No FLUID in system B)
The STBY hid system operates the leading edge slats and leading edge flaps to fully extended position only
During BAT START EEC start to operate
15% N2
What is the position of the isolation Valve when the Isolation is set to AUTO
Open when any bleed air switch or air conditioning pack switch is positioned off
