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DELTA > 717 SYSTEMS > Flashcards

717 SYSTEMS Flashcards

1
Q

RECOMMENDED WIDTH FOR 180 TURN
VOL 2 1.2.2

A

81 FT

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2
Q

OXY QTY FOR DISPATCH
VOL 1 3.4.1

A

1000 PSI AND TANK GAUGE ON THE GREEN

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3
Q

OIL QTY FOR DISPATCH
VOL 1 3.4.1

A

9QRTS MAINTAINANCE STATION
7QRTS NON-MAINT STATION

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4
Q

MIN HYD QTY FOR DISPATCH
VOL 1 3.4.1

A

7 QRTS

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5
Q

EMER LT Switch
VOL 2 1.4.3

A

OFF – Extinguishes emergency lights
(emergency battery packs are being charged)
ARM - Normal position (emergency battery
packs are armed)
ON - Activates emergency battery packs to
illuminate emergency lights

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6
Q

LANDING LIGHTS SWITCHES
VOL 2 1.4.2

A

Lim: cool 1 ½ minutes after the initial
extension or retraction and 3 ½ minutes
after each subsequent extension or
retraction
not be operated in
still air for more than 10 minutes

Auto retract if eng fail
auto re-extend flaps=>25

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7
Q

PREFLIGHT considerations for center tank fuel pumps
vol 1 2.1.11.6

A

Prior to engine start on any flight where center tank fuel is present and will be needed
for that route segment, the center tank pumps must be individually checked to verify pump
operation

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8
Q

AIR CONDITIONING PACK INDICATION
VOL 2 2.1.5

A

White – Commanded OFF, no air flow
Green (vaned) - Commanded ON, normal air flow
Amber – Commanded OFF, normal air flow
Amber (vaned) - Commanded ON with no air flow

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9
Q

AVIONICS COOLING Switch
VOL 2 2.1.1

A

The AVIONICS COOLING Switch is operative in flight only and is used to control radio rack cooling:
FAN - the primary fan cools the radios; if the primary fails, the backup fan comes on automatically
OVRD - the radio rack fans are off, the venturi valve is commanded open and venturi airflow cools the radios

NOTE: On the ground, both fans stay on all the time and the venturi valve is
commanded closed

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10
Q

RAM AIR SWITCH
VOL 2 2.1.1

A

OFF - Ram air valve commanded closed
ON - Ram air valve commanded open, allowing ram air to enter the air conditioning ducts

In flight, the system provides ventilation for the cabin and the cockpit when air conditioning is not available

Do not use the ON position to ventilate the aircraft on the ground

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11
Q

PACK SHUTDOWN Switch
VOL 2 2.1.1

A

AUTO - Allows automatic pack shutdown in the event of an engine failure
OVRD – Overrides the auto pack shutdown for an engine failure OR when the packs are selected OFF on the FMC

  • Both AC packs will automatically shut down if either engine fails during takeoff OR if selected OFF through the FMS
  • The auto pack shutdown feature is disarmed above 3000’ AGL
    NOTE: A pack will also auto shutdown if a high supply duct temperature is sensed. This cannot be overridden with the PACK SHUTDOWN switch.
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12
Q

FLOW Switch
VOL 2 2.1.1

A

NORM – The flow control valve solenoid is energized to provide a lower airflow rate
HIGH - The flow control valve solenoid is de-energized to provide a higher airflow rate

must be in NORM for takeoff

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13
Q

ISOL Switch
VOL 2 2.1.1

A

CLSD - The isolation valve is commanded closed
OPEN - The isolation valve is commanded open
AUTO - The isolation valve is controlled by the pneumatic system controller. Allows automatic crossfeed of left and right pneumatic systems during one bleed
source operation with airfoil ice protection selected ON

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14
Q

Instrument Panel Flow Indicator
VOL 2.1.2

A

ON – On the ground, with air conditioning off, indicates instrument panel cooling fan airflow
OFF – On the ground, with air conditioning off, indicates the absence of airflow and cooling fan failure

1 only during ground and flight operations with both air conditioning packs off
2 ground operations, one pack selected AUTO, the instrument cooling fan operating. With both packs selected AUTO, the instrument panel cooling fan is not operating – instrument cooling provided by aircraft air conditioning system
3 ground operations, if the APU is required for cooling and both pilots must leave
the cockpit, one AC pack should be selected OFF. This will preclude possible Display
Unit overheats caused by an inadvertent APU shutdown with both packs selected on
4 flight operations, BOTH AC packs must be OFF for the instrument panel
cooling fan to operate

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15
Q

Gasper Booster Fan switch
VOL 2 2.1.3

A

ON (Push) – Provides supplemental airplane ventilation when the left pack is
operating
OFF – booster fan is not operating; switch is extinguished
NOTE : The fan increases cold air ventilation through the eyeball outlets. In flight with both packs off, the ram air valve should be manually selected to ON (open).

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16
Q

CAB PRESS SYSTEM INDICATOR
VOL 2 2.1.4

A

SELECT - Illuminates to indicate failure of both automatic cabin pressure controllers.
MANUAL - When switchlight is pushed, MANUAL illuminates and the cabin pressurization system operates in manual mode. Also used to alternate control between cabin pressure controllers (Auto 1 and Auto 2)

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17
Q

Air Conditioning T/O Packs Off procedure
VOL 1 5.2.2

A

TO/APPR page PACKS – Line select ON to OFF PACKS ALL OFF alert message on EAD
NOTE: With the air conditioning pack switches in AUTO, the packs will automatically shut off at
throttle advance and will automatically come back on at 3,000 feet AGL

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18
Q

How forward and aft cargo bins are heated and where live animals must be
transported
VOL 2 2.2.17

A

-In flight, if the primary fan is operating, the forward cargo compartment is electrically
heated to a temperature range between 60° and 75°F
- Live animals must be transported only in the forward cargo compartment
- The aft cargo compartment is heated with cabin exhaust air

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19
Q

Recall the function of the Pneumatic Overheat Detection System (PODS)
VOL 2 2.2.6

A
  • Detects overheat conditions in the tail compartment AND along the wing and tail ice protection manifolds
  • If a failure is detected in the anti-ice manifolds, PODS automatically closes the respective anti-ice valve and alerts the flight crew
  • PODS is automatically tested when the engine fire test is performed
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20
Q

WING/TAIL A/I BLEED AIR INDICATIONS
VOL

A

Blank – Anti-Ice off
White – On the ground, anti-ice is
commanded on or anti-ice is commanded off with system pressurized
Green – Anti-ice commanded on in flight
Amber – Anti-ice bleed air temp out of limits

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21
Q

Recall conditions which require the use of engine anti-ice
VOL 1 5.16.2

A

OAT is 6ºC or below (10ºC TAT or below in flight) and any of the following conditions exist:
1- Visible moisture (clouds, rain, snow, sleet, ice crystals, fog when visibility is 1 mile or
less, etc) is present, or
2- 3ºC or less temperature/dew point spread, or
3- Ice, snow, slush or standing water is present on the ramps, taxiways or runways

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22
Q

Recall engine run-up requirements during icing conditions
VOL 1 5.16.2.5

A

Run the engines to a minimum of 40% N1 for approximately 10 seconds at intervals
no greater than 60 minutes

Additionally, a standing takeoff is required during icing conditions and is
accomplished by holding the brakes while in position on the assigned runway until
the engines are stabilized at, or above, 50% N1 before the start of the takeoff roll

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23
Q

AIR DATA Heat pushbutton
VOL 2 3.1.2

A

OFF (amber light) – all air data system heaters are off
Dark when all heater circuits for pitots, rudder limiter, stall probes, static ports,
and RAT probes are energized
NOTE: RAT probe heat is inhibited during ground operations

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24
Q

WING ICE DET switch
VOL 2 3.1.2

A

RESET – resets system and removes WING ICE DETECTED alert from the EAD. System will not reset if ice remains on the sensors
TEST – tests the wing ice detection system

Wing ice detection system functions on the ground only and alerts the pilots to the presence of wing upper surface ice. It is
inhibited during takeoff, landing and in flight

Do not takeoff with WING ICE DETECTED alert displayed

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25
Q

Recall which cockpit windows are electrically heated and/or anti-fogged
VOL 2 3.2.6

A
  • The three pilot windshields are electrically anti-iced and electrically anti-fogged
  • The clearview windows are also electrically anti-fogged
  • The eyebrow windows are not anti-iced or anti-fogged
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26
Q

Recall which control surfaces are anti-iced with engine bleed air
VOL 2 3.2.2

A

Wing slats and horizontal stab leading edge—from either or both engines

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27
Q

WINDSHIELD ANTI-FOG switch
VOL 2 3.1.2

A

OFF – Turns off windshield and clearview anti-fog
ON – Turns on windshield and clearview anti-fog

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28
Q

Recall how to activate/deactivate the oxygen mask microphone
VOL 2 5.2.5

A
  • When the mask is removed from the oxygen mask compartment, the mask
    microphone is activated
    -To deactivate the mask microphone, close the storage box doors and push the
    TEST/RESET button
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29
Q

Recall degraded cabin communications considerations
QRH 6.19

A

When Operating GEN L OFF or Complete loss AC PWR
No FA CHIME capability.
The CABIN INTERPHONE must
be selected ON to enable flight attendant communication with the cockpit ( CAB
pushbutton on ACP is in the “up” position and volume adjusted to hear any
potential FA calls)

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30
Q

BATTERY SWITCH
VOL 2 6.1.1

A

OFF – battery connected to the battery direct bus only(battery charging not affected)
ON - Connects battery to the DC transfer bus and the battery direct bus (adds DC transfer bus)

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31
Q

EMER PWR Selector
VOL 2 6.1.1

A

OFF - Emergency power is off. Resets the automatic emergency power system
ARM – Supplies emergency power automatically when power loss
to the EMER AC or DC bus is detected
ON - Emergency power is on. The battery supplies power for AC EMER bus (through the static inverter) and DC EMER bus

can only be tested on the ground with both engines shut down

Turn EMER PWR selector OFF if both pilots leave the aircraft and the APU is shut
down

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32
Q

Recall which buses are powered on EMER PWR

VOL 2 6.2.10

A
  • Battery direct bus
  • DC transfer bus
  • Emergency AC bus (through emergency inverter)
  • Emergency DC bus

60 MINUTES BATT

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33
Q

Explain the function of the L/R BUS TIE Switches
VOL 2 6.1.1

A

Open – Respective generator cannot power the tie bus. Can also be used to reset a bus tie lockout on the ground
AUTO – Generator bus to tie bus connection is controlled automatically to meet aircraft power requirements

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34
Q

DC BUS TIE Switch
VOL 2 6.1.1

A

OPEN - Opens all three DC bus tie relays
AUTO - DC bus tie relays are automatically controlled to ensure all DC buses are powered

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35
Q

L/R GEN Switches
VOL 2 6.1.1

A

RESET – Resets the generator
OFF – Disconnects the generator from the respective bus
ON – Allows an operating generator to supply power to its respective bus

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36
Q

GND SERVICE ELEC PWR Switch
VOL 2 6.1.2

A

OFF - Neutral position for ground service power
ON - Connects external power to the AC ground service bus and powers the
DC ground service bus. EXT power switch is OFF. ON light illuminates blue.

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37
Q

TGT INDICATIONS
VOL 2 7.1.2

A

White – Normally white, however, pointer
and digits will turn amber if TGT
amberline limits are exceeded for more
than 5 minutes – and will turn red if
redline limits are exceeded
Cyan Lightning Bolt – indicates ignition
is requested on
Red Start Limit – displayed during
engine ground start (removed at idle)

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38
Q

Recall the rated thrust of the BR715 engine
VOL 2 7.3.1

A

21,000 LBS

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39
Q

Recall the requirements for a ground, engine AUTO START
VOL 2 7.3.6.3

A
  • EEC controls all fuel metering and ignition to the respective engine once the ENG START Switch is pulled and the FUEL Switch selected ON. includes an automatic 30 second engine motoring delay before fuel
    is introduced
  • Auto-Start also includes a TGT protection threshold and will not allow fuel introduction if TGT is below 150ºC

IGNITION Switch – AUTO
ENG START Switch—Pulled
FUEL Switch – ON

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40
Q

Auto Abort during a ground engine Auto Start
VOL 2 3.6.3

A
  • Hung Start
  • Starter duty timer is exceeded (3 minutes)
  • Hot Start (or impending hot start) - 700ºC
  • Fuel On condition not satisfied (TGT is above 150ºC)
  • Loss of valid N2 input
  • Certain failures of both channels of EEC

ENG L/R START ABORT

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41
Q

engine warm up and cool down times
VOL 2 7.3.6.5

A
  • No minimum warm up time required following an engine shutdown of two hours or less
  • A warm up of at least 3 minutes is required following shutdown periods exceeding two hours
  • Engines require a 3 minute cool down prior to shutdown. Verify ENGINE COOL alert message illuminated on EAD
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42
Q

Recall approximate STD day, sea level, engine indications after a stabilized start
FCTM 2.3.1.1

A

EPR 1.0
N1 20%
TGT 400
N2 60%
FF 600-700
OIL PRESS 45

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43
Q

FADEC function and its main components
VOL 2 7.3.1

A

FADEC control engine functions from start
to shutdown
three main components: throttle, throttle
module, and Electronic Engine Control (EEC)

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44
Q

Recall when the EEC will provide automatic ignition activation (auto-relight)
VOL 7.3.6.6

A

Auto-relight armed from engine start to
shutdown
Automatic activation of BOTH ignition systems if:
-Combustor instability
- Significant water ingestion
- Significant ice ingestion
- Flameout
NOTE: Additionally, the ignition system unit will be automatically energized for 60
seconds after either ENG anti-ice switch has been selected on

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45
Q

Recall how to select EMERGENCY thrust
VOL 2 7.3.5

A

Push T/L through a mechanical gate
thrust management based on N1
ATS will disconnect and QRH to re-connect

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46
Q

RED REV INDICATION
VOL 2 7.3.7

A

Uncommanded deployment inflight
EEC will reduce to Idle

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47
Q

EMERGENCY REVERSE power
VOL 2 7.3.7

A
  • pulling the reverse thrust levers through a
    mechanical gate (and holding them in position)
  • engine damage can occur, maintenance inspection required
  • Amber REV alerts will appear on the EAD in the EPR exceedance position while
    green REV remains inside
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48
Q

Recall the normal and back-up fuel supply for the APU
VOL 2 7.4.3

A
  • APU fuel is normally supplied from the right main tank
  • Using crossfeed, fuel can be supplied from the left tank
  • When center tank pumps are used to supply fuel to the APU (both pumps ON), a right main tank fuel boost pump should also be operating
  • When center tank fuel value is less than 800 pounds, using center tank pumps alone
    can force air into the APU fuel line and cause APU flameout or prevent APU start
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49
Q

APU start automatic delay
VOL 2 7.4.2

A

40” FOR INLET DOOR TO OPEN

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50
Q

APU bleed air is inhibited for… minutes after an APU start
VOL 2 7.2.1

A

2’ after APU start initiated

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51
Q

how the APU shutdown cycle is verified complete
VOL 1 5.7.2

A

Absence of APU info on SD ENG display
1’ after APU RPM decrease

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52
Q

Recall considerations for shutting down the APU both with and without External Power
available
vol 1 5.7.2

A
  • With no external power, the BATT switch and EMER PWR selector must remain on
    until APU shutdown is complete (absence of the APU information block on the SD
    ENG display)
  • With external power connected, the EXT power switch must remain ON until APU
    shutdown is complete (absence of the APU information block on the SD ENG display)
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53
Q

APU continues to run for approximately …seconds while a No Power Break
Transfer is performed
VOL 2 7.4.4

A
  • At normal shutdown, APU runs 17 seconds while the elec sys do No Break Power Transfer (NBPT)
  • This delay is bypassed when APU FIRE CONT toggle switch OFF & AGENT ARM position OR when the exterior ground APU toggle switch is SHUT OFF position
  • It is also bypassed if an APU fire is detected
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54
Q

Shutdown features of the APU for both ground and in flight faults
VOL 2 7.4.4

A
  • On the ground conditions could damage the APU automatically shuts down and the amber APU AUTO SHUTDOWN alert is displayed
    -In flight, only for APU OVERSPEED or an APU COMPARTMENT FIRE. If an APU FAULT in flight, automatically shuts down 10 minutes after landing
55
Q

FIRE WARNING test using BATTERY POWER only
VOL 1 5.8.1

A

First Officer’s MASTER WARNING light will not illuminate and the cyan PODS TEST PASS alert message on the EAD will not be displayed

Fire Warning test must be re-accomplished after APU start

56
Q

ENGINE FIRE INDICATIONS
VOL 8.2.2.1

A

L/R ENG FIRE handle light(s) illuminate
FUEL switch light(s) illuminate
Aural/vocal warnings sound
ENGINE L/R FIRE alert(s) displayed on EAD
MASTER WARNING lights flash

57
Q

APU FIRE INDICATIONS
VOL 2 8.2.2.2

A

APU automatically shuts down
APU FIRE alert displayed on the EAD
MASTER WARNING lights flash
FIRE light on external APU ground control panel illuminates
Aural/vocal warnings sound (flight deck – 3 cycles; exterior – horn will remain audible until the fire is extinguished.)

58
Q

CARGO SMOKE or FIRE INDICATIONS

A

MASTER WARNING lights flash
MASTER CAUTION lights illuminate
CARGO SMOKE aural
CARGO SMOKE FWD (AFT) level 3 alert on EAD and AIR SD
“Land at Nearest Suitable Airport” – on CONSEQUENCE Page
DISCH CARGO AGENT – on EAD and AIR SD
AIR SD will display RED triangles
AFT/FWD CARGO SMOKE AGENT DISCH switchlight will flash “PUSH”

  • 1’ after first bottle discharged, the illuminated amber AFT/FWD CARGO SMOKE AGENT DISCH “PUSH” switchlight will
    extinguish and be replaced by an amber “LOW” light indicating the first Halon bottle
    has discharged. CARGO AGENT 1 LO displayed on the EAD
  • Approx 6’ later, direct the crew to discharge the second bottle; much slower rate ; CARGO AGENT 2 LO alert will
    illuminate after about 2 hours
  • The red triangles displayed on the AIR synoptic are activated cargo smoke detectors
59
Q

LAVATORY FIRE indications
VOL 2 8.2.2.3

A

MASTER CAUTION light illuminate
LAVATORY SMOKE alert on EAD

60
Q

ENGINE FIRE HANDLE what happens when pulled
VOL 2 8.1.2

A

FUEL SOV CLOSES
HYD SOV CLOSES
GEN TRIP OFF
SILENCE AURAL WARNINGS

61
Q

CARGO FIRE EXTINGUISHERS how long can suppress fire for
VOL 2 8.2.4

A

APPROX 80’

62
Q

RUDDER OPERATIONS
VOL 2 9.1.3

A

powered OR manual
Normally, right hydraulic system

If right system hydraulic pressure is too low, or manual mode is selected ( HYD CONT RUDDER switch OFF ), the rudder control
tab unlocks
In manual mode, the rudder pedals move the control tab on the rudder and
aerodynamic forces on the control tab move the rudder

63
Q

Recall features of the aircraft rudder limiting systems
VOL 2 9.2.4

A

primary rudder limiter protects the empennage from excessive loads by
restricting rudder travel as airspeed increases. mechanical system operated by ram air pressure from a pitot tube on the leading edge of the vertical stabilizer

A second rudder restricting system provides rudder limiting in the event the primary
system fails. The system has two positions, restricted and unrestricted, controlled by
the Flight Control Computer (FCC), as a function of airspeed.

64
Q

T/L advanced while speed brakes out
VOL 2 9.2.7.1

A

speed brake handle remains in position, but the speed brakes automatically
retract – confirmation can be seen on the CONFIGURATION SD

65
Q

SLATS positions and operations
VOL 2 9.2.8

A

Five individual Slat sections on each wing
operates as single unit
powered by both HYD systems, but either HYD system can fully operate slats

66
Q

Stabilizer movement warning horn
VOL 2 9.2.9

A

Warning horn and voice when stab moves more than 1 degree
inhibited on ground

67
Q

STABILIZER TRIM Brake Switch
VOL 2 9.1.2

A

OFF – (switch is pushed) amber OFF illuminates and electrical power to the brake is removed, setting the brake to prevent stabilizer movement

68
Q

Recall how the elevators are normally positioned for pitch control
VOL 2 9.2.6

A

-aerodynamically positioned by control tabs, mechanically connected to the control columns
-A variable load feel mechanism simulates aerodynamic forces and returns the
control columns to an artificial center position when they are released

69
Q

Recall each elevator has two tabs
VOL 2 9.2.6

A

-Control Tabs: Operated by the control columns, which then aerodynamically
position the elevators
- Geared Tabs: As each elevator is moved, geared tabs are deflected, providing
aerodynamic assistance in moving the elevators
- A total of four tabs aerodynamically position the elevators (two each side)

70
Q

Recall how pitch control is maintained if either control column jams
VOL 2 9.2.6

A
  • An override mechanism, installed on the torque tube connecting the two control
    columns, about 130 pounds disconnects columns
  • Once disconnected, maintenance is required
71
Q

Recall the function of the elevator augmentation system
VOL 2 9.2.6

A

-two hydraulic boost cylinders that augment elevator control during a deep stall recovery, elevators move to full deflection for additional nose down capability
-powered by the left hydraulic system with an accumulator backup if system pressure is lost.

72
Q

SPOILERS power/control
VOL 2 9.2.7

A

Spoilers are electrically controlled by the Spoiler Electronic Control Unit
(SECU) and hydraulically powered

73
Q

HOW BANK IS ACCOMPLISHED
VOL 2 9.1.3

A

Ailerons are aerodynamically positioned by control tabs mechanically connected to
the control wheels, aerodynamic position ailerons
>5 deg ctrl wheel flight spoilers extend proportionally to input on downward wing

74
Q

How spoilers deploy on grnd
VOL 2 9.2.7.1

A

RTO when reversers selected
when Landing main wheel spin or nose gear down

75
Q

STICK PUSHER
VOL 2 9.1.5

A

imminent stall condition
-STICK PUSHER PUSH TO INHIBIT
-autopilot disconnects
-Abrupt fwd mov of columns
-stick shaker deactivation

Until
- angle-of-attack is reduced below stick shaker
- the gravity force is sufficiently reduced
-STICK PUSHER PUSH TO INHIBIT switchlight is pushed

TO OVERRIDE:
-STICK PUSH TO INHIBIT pushed
-Pull control column (if stall persist and aft pressure released stick pusher will come back)

76
Q

Flight instruments components
VOL 2 10.2.2

A

EIS: ELECTRONIC INSTRUMENT SYS
6 DU’s
2 ECP (EIS CONTROL PANELS)
1 SDCP (SYS DISPL CTRL PNL)

SUPPORTED BY 2 VIAs (VERSATILE INTEGRATED AVIONICS units) IN THE E/E COMP

77
Q

Recall the function of the two aircraft Versatile Integrated Avionics units (VIAs)
VOL 2 10.2.2.3

A

data display, flight management computing, central aural warning, master warn/caution, and flight data acquisition

Normally VIA-1 provides data for the DUs 1 – 3 and VIA-2 provides data for the DUs 4 - 6

If fail, either VIA unit will automatically provide data for all DUs

78
Q

AIRSPEED BUGS INDICATIONS
VOL 2 10.1.2.3

A

Withe solid bowtie- selected airspeed
White outline bowtie- preselected airspeed
Solid Magenta circle- FMS commanded spd
Open Magenta cirlce- FMS spd not selected

79
Q

SISP
VOL 2 10.1.6.1

A

SOURCE INPUT SELECT PANEL
- EIS SOURCE SEL: CPT ON 2 USES VIA-2 FOR CAPT INSTRUMENTS
-AIR DATA :Sel off-side ADIRU src for DUs
-IRS : Sel off-side IRS
-FLT MGT:Sel off-side FMS src for DUs
- VOR/APP: Sel off-side radio sys

80
Q

IRS control panel and system
VOL 2 10.1.5

A

ADIRU-1 pwrd by EMER AC and backed up by BATT if AC lost
ADIRU-2 pwrd by R AC and backed up by independent battery 30’

Normal align 10’ , Fast 3’

NAV OFF LIGHT IF ADIRU:
- OFF
- ALGNING
- FAILURE

NAV OFF FLASHING IF:
- No pres pos received while aligning(5-10’)
- Pres pos entry wrong

81
Q

FLIGHT DATA RECORDER
VOL 2 10.2.6

A

-25 hrs ops
-Parking brk release+either fuel swtch on
- EVENT swtch ovhd to mark an event

82
Q

WHEN PROF ACTIVATE IF SEL ON GRD
FCTM 3.10.3.1

A

400 AGL

83
Q

WHEN NAV ACTIVATE IF SEL ON GRD
FCTM 3.10.2.1

A

100 AGL

84
Q

CLB/CLB1/CLB2 WHEN
VOL 1 3.4.3

A

CLB-1 TOGW>100K
CLB-2 TOGW<100K

When clmb less 1000fpm sel CLB on PERF page

85
Q

FMS SPEED 12000MSL IN DESC…
FCTM 4.3.3.1

A

PLANE SLOW DOWN TO 245 NO MATTER WHAT. IF HIGHER SPEED NEEDED MANUAL SPEED HAS TO BE CONSIDERED

86
Q

FUEL CAPACITIES
VOL 2 12.2.2

A

MAIN 9,266lbs each
CENTER 6,077lbs
TOTAL 24,609lbs

87
Q

NUMBER OF FUEL PUMPS
VOL 2 12.2.6

A

EACH MAIN 2 AC BOOST PUMPS
CTR TANK 2 AC BOOST PUMPS

CTR HAS HIGHER HEAD PRESSURE

88
Q

FUEL VENTING SYSTEM
VOL 2 12.2.3

A

-Allow equalization of pressure between tanks , prevents spilling
-Right and left main vented to the center tank. overflow from main tanks to drain into the center tank
- Center tank fuel is vented to the wingtip vent boxes

89
Q

APU is supplied fuel
VOL 2 12.2.6

A

Normally from right main tank.
center tank may be used if pumps on

90
Q

APU fuel usage on ground
VOL 2 12.2.6

A

350 lbs/hours

91
Q

AUX hydraulic switch
VOL 2 13.1.1

A

Located right wheel well 2 purposes:
1- back up right eng driven pump (if Right pump or Right engine fail, it provides hyd press to operate right system includ. Land gear)
2- Press Right hyd syst on ground when eng off

Thermal protection, shuts down if overheat

92
Q

HYD CONT RUDDER switch
VOL 2 13.1.1

A
  • Manual Rudder Ops
  • Hyd pwr to rudder shuts off and rudder operates manually
93
Q

TRANS pump switch
VOL 2 13.1.1

A

Located Left wheel well
allow pressurized system to power an un-pressurized system if both reserve qty ok

94
Q

Recall the effect of electrical failure on the Engine Driven Hydraulic Pumps
VOL 2 13.2.5

A

If elect pwr removed from eng driven pump it will default to ON

95
Q

LG warning horn and will sound if:
VOL 2 14.2.6

A

LG not down and flaps in landing conf (no silence)
LG not down, TL retarded, <210kias, <1200 agl (ok silence)

96
Q

LG is down and lock as long as
VOL 2 14.2.2

A

three green gear light either the gear position lights or the CONFIGURATION
synoptic constitute a gear down and locked confirmation

97
Q

Max brakes temp for take off
VOL 1 3.4.2

A

115C or less for airport <2200 msl

based on 120K and V1 140kts

98
Q

Recall indications of a Brake Overheat
VOL 2 14.1.4

A

-MASTER CAUTION
-CONFIG SD
-EAD

After Landing OK brake temp differential 60C on same gear

99
Q

Nose gear steering max degrees
VOL 2 14.1.2

A

Tiller 82 deg
Rudder 17 deg

100
Q

Ground Shift Sensing system
VOL 2 14.1.1

A

Located Nose gear. Senses plane on grd.
If Landing gear lever stuck GEAR HANDLE RELEASE button will override the shift sensor system

101
Q

Emergency Gear Extension Lever
VOL 2 14.1.1

A

Located right to pedestal
when pulled LG free falls

102
Q

Cautions on ground when Emergency
Gear Extension
VOL 2 14.2.5

A

Nose gear deflection limited to the LEFT(Right hyd is isloated from LG)

-stop on rwy
-close and latch main gear door manually
-LG Pins installed before taxi/tow

103
Q

Recall how braking is effected with a loss of both hydraulic systems
VOL 2 14.2.7

A

Each main gear wheel has disk type brakes indipendently operated by both hyd sys

if both fails , each syst has an accumulator provid enough brake pressure to stop plane

104
Q

Recall features of the antiskid system
VOL 2 14.2.7

A

-Max brake without skidding
- no brake until wheels spinup
- disabled at low taxi speed
-autotest when pwr applied

105
Q

ANTISKID switch
VOL 2 14.1.3

A

OFF Deactivates antiskid sys
doesnt mean a failure

106
Q

CAWS Meaning and components
VOL 2 15.2.2.2

A

CENTRAL AURAL WARNING SYSTEM
TONE+VOICE

107
Q

When Take Off Warning occur
VOL 2 15.2.3.11

A

ON ground with Throttles advanced and:
BRAKES Parking Brakes on
FLAPS not agree with FMS
SLATS not in takeoff
SPOILERS panels >2 degr
STABILIZER not in green
RUDDER TRIM not centered

108
Q

Predictive Windshear features
VOL 2 15.2.7.1

A

Detect Microburst/WS on TO/LNDG

Auto activate in flight <2300’RA
During TO activate when RDR on

Aural Alerts <1200’ and microburst detected

109
Q

Predictive Windshear WARNING Alerts
VOL 2 15.2.7.1.1

A

WARNING
T/O
Inhibited from 100 kts to 50’AGL
-Max 3NM range
-WS icon on ND
-Red WS on PFD
- Aural WS Ahead Ws Ahead

LANDING
Inhibited below 50’AGL
-Max Range 1.5NM
-WS on ND
-WS on PFD
-Aural “Go Around WS ahead”

110
Q

Predictive Windshear CAUTION/ADVISORY Alert
VOL 2 15.2.7.1.2

A

Same inhibit as Warning
- WS event outside warning area
- Max range 3NM
-WS on ND
- Amber WS AHEAD on PFD
- Aural “Monitor Radar Display”

-WS event outside Caution area
-Max 5NM
-WS only on ND

111
Q

EIS ALERTING AND SDCP
VOL 2 15.2.4

A

ELECTRONIC INSTRUMENT SYSTEM
SYSTEM DISPLAY CONTROL PANEL

112
Q

EIS ALERTING LEVELS
VOL 2 15.2.4.1

A

LVL 3 - RED BOXED
Emergency Immediate crew action
-RED MASTER WARNING
-Boxed RED alert on EAD, red triangle
-Cue light on SDCP

LVL 2 - AMBER BOXED
Abnormal Immediate crew attention
-AMBER MASTER CAUTION
- BOX AMBER on EAD or STATUS page
-Cue light on SDCP

LVL 1 - AMBER
May require Maintenance before TO
-AMBER MASTER CAUTION may illuminate
-AMBER on EAD,SD, or STATUS page
- Cue light on SDCP may illuminate

LVL 0 - CYAN
Operational or AC status info
-CYAN alert on EAD

113
Q

Inhibit of Alert System on TO
VOL 2 15.2.4.7.1

A

MASTER WARNING/MASTER CAUTION from V1 to 400’RA no longer than 25” in flight
MASTER CAUTION LESS SEVERE throttle advance to >1000’AFE or 120”

114
Q

Green box on EAD before landing
VOL 2 15.2.4.9

A

-Landing gear down
-Flaps in landing range
-Spoilers armed

115
Q

TERRAIN OVRD SWITCH AND FLAPS OVRD SWITCH
VOL 2 15.1.2

A

TERRAIN OVRRIDE : Inhibits enhanced EGPWS features
FLAPS OVRRIDE: Inhibits warning with flaps less than 25/40

116
Q

BELOW G/S SWITCH
VOL 2 15.2.5

A

-Indicate excess deviation blw GS
-Push blw 1000’ RA cancel warning
-effective blw 2500’ AGL

117
Q

Reactive WAGS
VOL 2 15.2.7.2

A

WINDSHEAR ALERT AND GUIDANCE SYST
TAKE OFF (grd-to 1500’AGL),APP, GA Provides visual/aural warning and AP/FD guidance through WS event
-RED decreasing performances
-AMBER increasing performances
-ON TAKEOFF WS on PFD and FMA follow by aural “TAILWIND SHEAR” or “HEADWIND SHEAR”
-ON APP/GA Same as TO but NO GUIDANCE unless a GA is button press or TL >95%
if ATS and/or FD or, they will reactivate once TL advanced to GA

GPWS AND TCAS ARE INHIBITED WHILE ON WS GUIDANCE MODE

118
Q

FMA COLORS

A

ACTIVE MODE COLOR
NUMBERS COLOR BASE OF WHERE IS THE NUMBER COMING FROM (FMS, PRESELECTED..)

119
Q

ATS OFF COLORS

A

WHITE: OFF BUT CAN BE ENGAGED
AMBER: OFF NO RE-ENGAGE
RED(FLASH): OFF NEED A/T OFF PRESS AGAIN

120
Q

ATS OFF PLACEMENT ON FMA

A

IF SPEED ON THRUST “” UNDER SPEED BOX
IF SPEED ON PITCH “” UNDER ALTITUDE BOX

121
Q

AP OFF PLACEMENT ON FMA

A

IF SPEED ON THRUST “” UNDER ROLL BOX
IF SPEED ON PITCH “” UNDER SPEED BOX

122
Q

WHEN NAV AND PROF CAN BE ARMED AND ACTIVE

A

AT LEAST ONE ENGINE RUNNING

USUALLY DURING NAV BRIEFING

NAV ACTIVE AT 100 AGL
PROF ACTIVE AT 400 AGL

123
Q

WICH A/P MODE CAN BE ACTIVATED AT 200’ AGL

A

HDG ONLY

124
Q

WHEN SPEED WHITE

A

+/- 4 KNOTS TO FMS PLANNED SPEED

125
Q

A/P ENGAGEMENT WHEN NAV ARMED ON GROUND

A

NOT POSSIBLE TO ENGAGE BELOW 400’AGL

126
Q

SPEED CHANGES ON T/O

A

LIFTOFF FD V2
AT V2 FD V2+10
AT ACCEL ALT SPEED ON CLIMB PAGE

127
Q

PARALLEL RUDDER
FCTM 5.1.15

A

Function of FCC to manage asymmetries

SERIES or PARALLEL

Series : like a YD no feedback to pedals authority limited 2 degrees

Parallel: when AP during TO GA or AUTOLAND on . Motion fedback to pedals authority 27 degrees. When engaged bank angle Limiter on PFD shows 10 degree or less
Disconnects when new lateral mode selected or when clean configuration

128
Q

EMERGENCY PWR ITEMS AVAILABLE

A

FAME FADES
Fire det\prot
Apu start
Manual pressurization
Engine Fuel Pump

Fadec\EEC
Adiru 1
DU 1-3
Engine Ign 2
Skid (Antiskid)

129
Q

PCDU

A

Power Conversion Distribution Unit
PEAS
Protection Ext Pwr
Emerg Pwr auto activ
Auto Pwr Transf (NBPT)
Shedding Galley

130
Q

Go Around when activated

Flight Instruments

A

FD’s displayed
ATS go around Thrust
Parallel Ruddr active
GOAROUND 3rd col

131
Q

Return to Tank

Fuel

A

Avoid ice formation
in wing root
Cycle warm fuel from Eng back to inbd main tank
Inhibited:
-TO\LDG
- Main tank fuel temp high
-Main tank fuel qty low

132
Q

Lateral fuel imbalance qty EAS message

Fuel

A

1400 lbs

133
Q

FUEL LEVL LOW

Fuel

A

CTR <1000lbs and
either Main < 2000lbs x 2 mins

134
Q

Cabin Stby emergency lights powered by

A

DC Emergency bus

DELTA (8 decks)

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