Each IRU has 2 General Purpose input buses:

for FMF inputs, FCE inputs and data upload

The Alerting and Transponder Panel control data goes:

through the 3 Tuning Control Panels to the Common Data Network

Large information signs or "Smart Signs" are:

controlled by Passenger Service Modules

Predictive windshear alert indications show:

on the PFD mini-map and on the ND

For an APU start on the battery, the Start Power Unit changes:

28v DC from the APU battery to 115v AC

The relation between the 2 different types of ELCUs is:

ELCU C communicates with the BPCU, ELCU P Controls and protects the ELCCs

If the 3 Air Data Reference Functions fail, airspeed is:

Synthetic: based on Inertial and Angle of Attack Data

During an ILS approach when the B787 aligns with the runway:

an automatic swithing from the LOC capture to the LOC track antenna occurs

You may not be able to release the parking brake on a B787 that is not powered by EXT or APU power because:

the Main battery is not installed

The B787 electrical power buses are:

235v AC, 115v AC, +/- 270v DC and 28v DC

The Runway Turnoff Lights are located:

in the left and right wing root

A CDU NAV RADIO Page shows a VOR frequency and the letter "R" next to the frequency because:

this VOR station is autotuned by the FMF and part of a route

The Current Return Network:

is a return path for normal and fault AC and DC currents

The Flight Management Function:

provides lateral and vertical navigation

ELCUs have two different types of modules:

ELCU P (protection) and ELCU C (communication).

The Air Data Reference System has:

3 pitot probes and 3 pairs of static ports

The antenna on top of the vertical stabilizer under the vertical fin tip receives:

the VOR, Localizer or GLS/VDB signals

The BATTERY TEST switch indicator lights HIGH, MEDIUM and LOW indicate:

the minimum assumed towing time without braking

If one circuit card assembly (CCA) in the Left ISSPU fails:

The failed function is taken over by the Right ISSPU

When the TOWING POWER switch is ON:

both the APU and MAIN batteries are used

The TCAS/ATC antennas are located:

One on the top and one on the bottom of the fuselage

BPCU software can be loaded:

in the Left or Right BPCU with APU power

To reset a BPCU you must:

cycle the related EXT PWR switch ON and OFF

If the Weather Radar Receiver/Transmitter Module (RTM) does not have power:

Neither the ISSPU nor the RTM can be data loaded

The APU start contactor closes when it gets:

Both a ground from the related APU GCU and 28v DC from the CMSC

Most of the Cockpit lights get power directly from:

an analog or digital Power Control Unit

Cabin lighting control is given by:

Software configuration in cabin services system controller (CSSC)

The wing and tail position lights are:

powered if the Towing Power switch is ON

The EBPSUs are powered by:

The Hot Bat Bus and their respective TRU

WCUs having WELS antenna units are:

above Passenger Doors and Overhead Bins

The Current Return Network in the wings and in the empennage:

is only used for fault current and lightning protection

Voltage and amperage for the Main and APU batteries can be checked from:

electrical synoptic page and electrical maintenance page 1

The RAT deploys automatically in flight when:

the 2 flight instrument buses lose power

The Emergency Lights "ARMED" signal is:

28V DC from the hot battery bus (HBB)

studbud

Combined: Duplicate of ATA 34 +ATA 33 + ATA 24

92 termsStudBud Administration140 plays

Duplicate of ATA 34: Boeing 787 Navigation Systems Duplicate of ATA 33: B787 Lights Duplicate of ATA 24: B787 Electrical Systems

Flashcards92 cardsFPractice quizPHost liveL

Questions 92

Answers

1
ADMs send air pressure digital data to:
the Air Data Computers
the Common Data Network
the ACEs in the FCEs
the Earth Reference System (ERS)
2
With the 3 EXT Power sources availlable you can start:
The Left engine only
just the APU
The Right engine only
The Left or the Right engine
3
ADF data is displayed on:
the PFDs
the NDs
the MFDs
the PFDs' mini-map
4
A "Single FMC" advisory message appears in case of:
a failure of 3 FMF
the connection of a single FMF to the Autopilot
a failure of a single FMF
a dual FMF failure
5
The secondary power source for the IRUs and AHRUs is:
Their on-side DC busses
The Hot Battery Bus (HBB)
The Ram Air Turbine (RAT)
Their on-side dedicated Battery Unit.
6
Each IRU has 2 General Purpose input buses:
for GPS data
for time marks
for FMF inputs, FCE inputs and data upload
to make your life difficult
7
The Alerting and Transponder Panel control data goes:
through the 3 Tuning Control Panels to the Common Data Network
directly to the 2 Integrated Surveillance System Processor units
directly to the left Integrated Surveillance System Processor unit
to the left Tuning Control Panel and then to the right ISSPU
8
The Air Data Reference Functions are hosted in:
There are 2 copies in the right CCR cabinet and 1 in the left
the Air Data Computers
There are 2 copies in the left CCR cabinet and 1 in the right
the 3 Flight Control Modules
9
The aft external power contactor is controlled by:
the L2 GCU
by WIFI through an application on the pilots' Ipads
the Left or Right BPCU
only the left BPCU
10
Large information signs or "Smart Signs" are:
Cathode Ray Tube (CRT) displays
controlled by Passenger Service Modules
located near the smartest passengers
controlled by Cabin Zone Units
11
Predictive windshear alert indications show:
on the CBS evening news
on the PFD mini-map and on the ND
on the PFD
on the ND Vertical Situation Display
12
For an APU start on the battery, the Start Power Unit changes:
115v AC to +/- 135v DC
115v AC to +/- 270v DC
28v DC from the APU battery to 115v AC
28v DC from the APU battery to +/- 135v DC
13
A Remote Power Distribution Unit controls loads up to:
500 Amps
100 Amps
50 Amps
10 Amps
14
The relation between the 2 different types of ELCUs is:
ELCU P supplies power to ELCU C
ELCU P is the Primary controller, ELCU C is the secondary controller
ELCU C communicates with the BPCU, ELCU P Controls and protects the ELCCs
ELCU P Controls and Protects ELCU C
15
If the 3 Air Data Reference Functions fail, airspeed is:
sent by CPDLC to the airplane
given by the GPS
lost
Synthetic: based on Inertial and Angle of Attack Data
16
During an ILS approach when the B787 aligns with the runway:
an automatic swithing from the ILS capture to the ILS track antennas occurs
an automatic swithing from the LOC capture to the LOC track antenna occurs
Pilots need to switch from the ILS capture to the ILS track antennas
an automatic swithing from the G/S capture to the G/S track antenna occurs
17
You may not be able to release the parking brake on a B787 that is not powered by EXT or APU power because:
the battery switch is not set to ON
the Main battery is not installed
the APU battery is not installed
the airplane is not powered
18
The B787 electrical power buses are:
235v AC, 115v AC, +/- 270v DC and 28v DC
235v AC, 115v AC, 28v AC and 28v DC
235v AC, 115v AC, 270v AC and 28v DC
28v AC, 115v AC, +/- 270v DC and 28v DC
19
WELS Battery Units are:
lead–acid type
nickel–cadmium type
Nickel-metal hydride type
Lithium Ion Polymer type
20
The Runway Turnoff Lights are located:
on the left and right side of the fuselage forward of the wing strakelet
on the main landing gears
in the left and right wing root
on the nose landing gear
21
A CDU NAV RADIO Page shows a VOR frequency and the letter "R" next to the frequency because:
a Request has been sent to the FMF for VOR autotuning
this VOR station is manually tuned by the FMF
this VOR station is autotuned by the FMF and part of a route
this VOR station is autotuned by FMF and part of procedure
22
Emergency Light Batteries are located:
above Passenger Doors 1R, 2L, 3R and 4L
in the WELS Control Units
near the WELS Control Units
in the FWD and AFT EE bays
23
How many copies of the Flight Management Function does the B787 have:
2
3
1
4
24
The Current Return Network:
is a return path for normal and fault AC and DC currents
is a data network controlling load shedding
is a protective network against Electromagnetic Interferences
is a distribution network for AC and DC loads
25
The Flight Management Function:
manages the flight crew payroll
provides vertical navigation only
provides lateral navigation only
provides lateral and vertical navigation
26
ELCUs have two different types of modules:
ELCU C (communication) and ELCU M (monitoring).
ELCU P (protection) and ELCU T (transmission).
ELCU P (protection) and ELCU C (communication).
ELCU I (interface) and ELCU P (protection).
27
The Air Data Reference System has:
3 pitot probes and 3 pairs of static ports
3 pitot probes and 4 static ports
4 pitot probes and 3 pairs of static ports
2 pitot probes and 4 pairs of static ports
28
The antenna on top of the vertical stabilizer under the vertical fin tip receives:
the SATCOM signal
the ADF signal
the VOR, Localizer or GLS/VDB signals
the Glide Slope signal
29
The BATTERY TEST switch indicator lights HIGH, MEDIUM and LOW indicate:
the minimum assumed towing time without braking
the minimum assumed towing time with 2 heavy brakings
the time the battery can be left on the airplane without any EXT Power
the available braking force
30
If one circuit card assembly (CCA) in the Left ISSPU fails:
Another CCA in the Left ISSPU takes over the function
An ExtraVehicular Activity is programmed to fix the ISS
The failed function is taken over by the Right ISSPU
Integrated Surveillance System switches to the Right ISSPU
31
When the TOWING POWER switch is ON:
the FCE batteries are used
the APU battery is used
both the APU and MAIN batteries are used
the MAIN battery is used
32
An automatic start of the APU occurs in flight when:
3 or more VSFGs go offline
the left and right 115v AC buses lose power
the 2 flight instrument buses lose power
the IFE power demand exceeds the VFSGs power capacity
33
The TCAS/ATC antennas are located:
On the bottom of the fuselage
On the top of the fuselage
At the top of the vertical stabilizer
One on the top and one on the bottom of the fuselage
34
BPCU software can be loaded:
only in the left BPCU when you use the forward external power
only in the shop
in the left or right BPCU when you use the forward external power
in the Left or Right BPCU with APU power
35
To reset a BPCU you must:
start a Test from the CMCF ATA 24 Chapter
cycle the related EXT PWR switch ON and OFF
do a BITE TEST on the front panel of the unit
cycle the two FWD EXT PWR swiches ON and OFF
36
If the Weather Radar Receiver/Transmitter Module (RTM) does not have power:
Neither the ISSPU nor the RTM can be data loaded
The RTM can be data loaded but not the ISSPU
The ISSPU can be data loaded but not the RTM
The ISSPU and the RTM can be data loaded
37
The Common Motor Start Controllers do not control:
The NGS
The CACs
The EMPs
The EBPSUs
38
The APU start contactor closes when it gets:
an order from the captain over the Flight Interphone
A ground from the related APU GCU
Both a ground from the related APU GCU and 28v DC from the CMSC
28v DC from the CMSC
39
Most of the Cockpit lights get power directly from:
Static Electricity
an analog or digital Power Control Unit
the Hot Batt Bus
an RPDU
40
Cabin lighting control is given by:
CCR hosted applications
Software configuration in Cabin Zone Units (CZU)
sophisticated wiring interconnexions
Software configuration in cabin services system controller (CSSC)
41
The wing and tail position lights are:
always ON
powered if the Towing Power switch is ON
synchronized by a "Sync Wire"
turned on automatically when it gets dark
42
The EBPSUs are powered by:
The Hot Bat Bus and their respective TRU
The APU Hot Bat Bus and the CAPT INSTRUMENT BUS
The Hot Bat Bus and the CAPT INSTRUMENT BUS
The Hot Bat Bus and the APU Hot Bat Bus
43
Before an APU start the configuration of the contactors is checked by:
The BPCU
the Start Power Unit
The CMSC
The APU controller
44
WCUs having WELS antenna units are:
above Passenger Doors and Overhead Bins
above Passenger Doors only
above Overhead Bins only
under Passenger Seats only
45
The Current Return Network in the wings and in the empennage:
is only used for fault current and lightning protection
consists of two loops of bars, straps, tie brackets and wiring
is a single loop of wires
is similar to the one in the fuselage
46
A CDU NAV RADIO Page shows an ILS frequency and course + Park because the ILS:
is manually tuned but doesn't receive any signal.
is autotuned but not used
is not tuned
tune inhibit mode is active
47
Voltage and amperage for the Main and APU batteries can be checked from:
the ESIC page
electrical synoptic page and P5 overhead panel (voltage only)
electrical synoptic page and electrical maintenance page 1
the CBIC page
48
The RAT deploys automatically in flight when:
3 or more VSFGs go offline
the 2 flight instrument buses lose power
a FOD is detected by the predictive bird strike function of the WXR
the left and right 115v AC buses lose power
49
The Emergency Lights "ARMED" signal is:
28V DC from the hot battery bus (HBB)
11V DC from the Hot Batt Bus through a resistor
8.2V DC from the WELS battery unit (WBU).
115V AC from an RPDU
50
What type of light is used for the Anti-Collision lights?
Incandescent
Halogen
HID
LED
51
The antenna receiving position correction data from a ground station for a GLS approach is the:
VHF left antenna
Right or Center VHF antenna
VOR or Localizer antenna
Glide Slope Antenna
52
To control WXR display on a side, you use:
the on-side or the center CDU
the on-side TCP only
the on-side or the center TCP
the on-side CDU only
53
A Gateway RPDU interfaces with:
All the Standard and Gateway RPDUs
Every Standard RPDUs
3 or 4 Standard RPDUs
The other Gateway RPDUS
54
On a B787 with GE engines the thermostatic valve of the VFSG cooling system is:
a mechanical independant thermostatic valve
electrically controlled by the Engine Ice Protection system
electrically controlled by the EEC
a servo valve controlled by the Fuel Metering Unit
55
The "AC CONNECTED" light at the EXT PWR receptacles indicates that :
a good quality power source is connected
AC power is connected instead of DC power
AC power is already supplied by either a VSFG or an ASG
a power source is connected and in use
56
On a B787 with RR engines to regulate the VFSG oil temperature:
the EEC closes the AOHE valve to cool the oil through a Fuel/Oil Heat Exch
the thermostatic valve closes to cool the oil through a Fuel/Oil Heat Exch
the EEC sends a command to the BPCU to connect an ASG to the network
the EEC regulates the air flow through the AOHE via an electric valve
57
ELCC can get open/closed commands from:
ELCU P or CMSC
ELCU P, SPDU or RPDU
ELCU P only
ELCU P, GCU or BPCU
58
The load management function:
makes each load use less power
makes sure that each power source gives the same amount of power
keeps the aircraft load level below the power supply level
is an help for the Load Master to load the Cargo Compartment
59
When the nose landing gear is down and locked and the Nose Landing Light Switch is set to ON:
the nose landing lights and the turn off lights turn on
only the nose landing lights turn on
the nose and wing landing lights turn on
the nose landing and taxi lights turn on
60
The 4-digit Air Traffic Control (ATC) transponder code (Squawk) can be changed from:
the Control Display Unit (CDU)
the Miscellaneous Control pages
the Tuning Control Panel (TCP)
the Alerting and Transponder Panel (ATP).
61
On the CBIC data page the OUTPUT STATUS of a load shows OVERRIDE because:
The load is shed
There is No Computed Data for this item
The load CB is tripped
The load CB is set to OPEN
62
The ground service bus is controlled by:
software in the L2 GCU
software in the BPCU
the right CCR cabinet
the left CCR cabinet
63
When the RAT is the only source of power:
the C1 and C2 TRUs get power
the CMSCs get power
the 4 TRUs get power
2 main 235v AC busses get power
64
Airplane Personnality Modules get power from:
Nothing, they are passive modules
Their onside IRU or AHRU
Their internal battery
the Hot Batt Bus
65
Selecting "WXR" on a Navigation Display (ND) pull-down menu displays WXR data on:
the Captain and First Officer's NDs
the onside PFD and ND
the onside Primary Flight Display (PFD) mini map
the onside Navigation Display (ND).
66
For the CARGO LOAD LIGHTS to turn on, one of the conditions is to have:
the service bus powered
the cargo door unlocked
the Bulk Cargo Door unlatched
the cargo door fully open
67
The emergency lights-Wireless Control Units "Prime" are located:
Under passenger seats
above passenger doors
above overhead bins
in a safe in the flight deck
68
The Integrated Navigation Radio combines:
ILS, VOR and DME
ILS, VOR and ADF
ADF, GNSS, DME and Marker Beacon
ILS/GLS, GNSS, VOR and Marker Beacon
69
Do Ground Handling Loads lose power when an engine is started on the ground?
Yes but only GND HDLG DC loads
Yes but only GND HDLG loads that can't stand variable frequency
No all loads are kept powered
Yes the GND HDLG bus is not powered when an engine is running
70
A DME distance on a PFD is paired with:
A VOR station
An ILS or GLS station
An ADF station
the ISS (International Space Station)
71
An IRS ON/OFF switch gives power to:
its on-side IRU
its on-side IRU and AHRU
its ADIRU
its on-side AHRU
72
When a high differential pressure between the main battery enclosure and the airplane occurs:
the enclosure pressure burst disk indicator is no longer visisble
there is a Scheduled Maintenance Task on the LATCHED MSG ERASE page
the red indicator button of the pressure burst disc Indicator extends
the main bat enclosure explodes to tell you you have to replace the battery
73
On a B787 with RR engines the VFSG oil temperature is controlled by:
The Cabin Air Compressors and the A/C packs
a Fuel/Oil Heat Exchanger Valve
the EEC and an Air/Oil Heat Exchanger air control valve
a Thermostatic Bypass Valve
74
Flight Management Function Data is:
identical for the 3 FMFs
simplified for the Backup FMF
simplified for the Master FMF
different for each FMF
75
A WCU can drive up to:
10 emergency lights
8 emergency lights
6 emergency lights
4 emergency lights
76
The Integrated Surveillance System combines:
WXR, ILS, TCAS and RA
ATC, WXR, TCAS and TAWS
ATC, TCAS, RA and ILS
RA, TAWS, ATC and TCAS
77
A DME distance on an ND is paired with:
a lunar station
a VOR station
an ADF station
an ILS station
78
The Receiver Transmitter Module of the Weather Radar is located:
Behind the radome in a non-pressurized zone
Just aft the forward bulkhead
In the forward EE bay
In the flight deck aft aisle stand
79
For the FWD Cargo interior lights to turn on, one of the conditions is to have:
the FWD cargo door closed
the service bus powered
the FWD cargo door fully open
the FWD cargo door unlocked
80
The Landing light system has:
5 lights
2 lights
6 lights
4 lights
81
Conditions to manually disconnect a VFSG on the ground are:
A/C Powered-GEN DISC switch pressed-FUEL CONTROL Switch to RUN-LOW OIL Pres
A/C Powered, GEN DISC switch pressed
A/C Powered, GEN DISC switch pressed, FUEL CONTROL Switch to RUN
GEN DISC switch pressed
82
Emergency Lights are powered by:
115 VAC from RPDUs
8.2 VAC from WCUs transformers
8.2 VDC from WCU Battery Units
28 VDC from the RAT via TRU C1 and C2
83
On a B787 with GE engines the VFSG oil temperature is controlled by:
a FOEH, an AOHE and a Thermostatic bypass valve
the EEC, Air/Oil Heat Exchanger air control valve, AOHE and Fuel/Oil HE
The Cabin Air Compressors and the A/C packs
only a Fuel/Oil Heat Exchanger valve
84
Before removing the main batterie the airplane has to be powered down for at least 30 minutes:
to let the CCR Cabinets shut down properly
to prevent the WELS from activating
to let the Lithium-ion battery cool down before removal
to let the parking brake release the Electric Brake Actuators
85
The "Sync Wire" connected to the body anti-collision lights synchronises:
the body and wing anti-collision lights
the body anti-coll lights with the beating of the captain's heart
the upper and lower anti-coll lights with the navigation lights
the upper and lower anti-collision lights together
86
In case of damage to the Emergency Lights On/Off/Armed control wire:
a diode in the Master Attendant Switch Panel Emerg Light test switch blinks
the On/Off/Armed signal is sent wirelessly
the emergency lights come on
the emergency lights stay off
87
To input the ground power unit (GPU) load capacity data into the airplane you use:
The Electrical synoptic page
The MISC SYSTEM CTRLS
The ELECTRICAL Maintenence Page 1
The dedicated switch on the P5 overhead panel
88
To make the ESIC page selection active:
a CMCF Special Function has to be activated
double click on the Panel you want to activate
you must enter a 4 digit code
the GND TEST switch has to be set to Enable or Data Load Enable
89
Both the PFD and ND show Terrain data when:
there is a Predictive Windshear
"TERR" is selected on the Alerting and Transponder Panel
"TERR" is selected from the EFIS/DSP Panel
"TERR" is selected either from the EFIS/DSP Panel or ND menu
90
When the EXT Power is not ON, a BPCU is powered by the Hot Bat bus or:
the EXT PWR receptacle
its onside EXT PWR TRU
any EXT PWR TRU
the APU Hot Bat Bus
91
The primary source for the INTEGRATED SURVEILLANCE SYSTEM functions at power up is:
A random selection of left and right ISSPU circuit cards.
The left ISSPU Integrated Surveillance System Processor Unit
The right ISSPU.
A mid-value selection of the 2 ISSPUs.
92
The Master Bright switch controls:
only Integral Panel lights
the lights controlled by a white dotted switch
only Flood lights
all lights in the cockpit

Combined: Duplicate of ATA 34 +ATA 33 + ATA 24 Flashcards | StudBud