Structures Flashcards
(159 cards)
1
Q
Where is o2 botttle and charging
A
Left aft side of aircraft
2
Q
Airstairs door, eddy current damper, where is it and what does it do, avionics batt disconnected can freefall
A
It’s based in door, controlled by ? LGECU i think
3
Q
Where is door switch and what bus battery
A
Door switch l/h of door outside and r/h of door inside, powered up only, uses current to motor to slow door on extension,got to be battery bus or external
The actuator uses a brushless DC motor which is connected to a planetary gearbox and slip clutch and to the output shaft. The motor is energized during the door close sequence which takes 18 seconds maximum.
4
Q
How many times to open/close door in 5 mins
A
3
5
Q
Sensor on door for for open closed- does this effect steering
A
Yes cancels steering,through LGECU
6
Q
How does door interact with steering
A
Through sensor to the computer-not sure what, THROUGH LGECU, has 3 prox switches
7
Q
Ems cdu what is it and what does it do
A
Pilots heater mats
8
Q
What is OMS onboard Maint system
A
It’s the EICAS
9
Q
What power and charges ELT and buzzer
A
Has internal battery and buzzer will sound when its selected on
10
Q
Where is electric actuator for door and how is it powered
A
Electric motor is sited in door, maybe apu battery powers it ,switch is used to close the passenger door with electrical power, when DC or AC is available.but is a dc brushless motor
11
Q
How does damper work on door as its opened
A
When the door is opened and the motor is not energized, an eddy current damper controls the speed. The door opening time is 7.0/8.5 seconds (10 seconds maximum). Before full open, the proximity switch energizes the slowdown circuit, which decreases speed to 12.5 degrees/second maximum. The slip clutch prevents the output shaft from being overdriven. A thermal switch is attached to the motor to remove voltage if the motor becomes too hot.
12
Q
What is vent flap used for in door
A
When handle is moved springs help to open flap The flap is held open by four tension springs and is driven shut by a cam face on the aft G-latch via a series of levers during the final locking sequence. The design is such that only two springs are required to retain the vent flap in the open position. In the event of residual cabin pressure or icing conditions, during door deployment, the vent flap is pulled open by a direct link to the torque tube prior to full door lift, via a cable assembly.
13
Q
How does tensator drum work on door
A
The tensator assembly comprises a single torque drum mounted to the airstairs middle shaft and four tensator springs each housed in a tensator drum. The springs are made of steel and measure over 15 ft (4.57 m) in length when fully extended. As the door is lowered, the airstairs middle shaft, under action of the two fuselage mounted cables, rotates. It causes the torque drum to draw each of the four tensator springs out of their respective drums and around the larger drum. The uncoiling of the tensator springs creates both a resistance of the falling door and a reserve of potential energy to assist in door closing.
14
Q
What type of door is overwing exit
A
There is one emergency exit on the right side of the fuselage. This is a plug-type door that you can open from the inner or outer side of the fuselage.
15
Q
Are prox sensors on top of emergency exit door
A
A proximity sensor is installed in the top center of the overwing emergency exit opening. An EICAS caution message R EMER EXIT will be displayed if the exit is open.
16
Q
28 secs after t/o brakes ,gear symbology in ECAM are removed
A
Yes is disabled on EICAS
17
Q
What is fuse skin made out of
A
The fuselage is a semimonocoque assembly. It has five sections connected together with butt straps, doublers and stringer splices. The fuselage skin is made of chemically milled aluminum alloy with aluminum alloy frames and stringers. The fuselage has attachments for the empennage/tail, the engine support structure and pylons, and the nose landing gear. The wings attach to a wing box at the bottom of the center fuselage. The forward fuselage and the center fuselage have a constant diameter of 106 in. (2.69 m). Aerodynamic fairings for the nose and tail complete the fuselage.
18
Q
What is press diff
A
3500 ft at 51000
19
Q
What station is aft press bulkhead
A
Sta 861;00
20
Q
Is fwd press b/h fs; 202;75
A
Yes
21
Q
Difference between a door and a panel
A
Door has handle
22
Q
Fuselage barrels
A
Transition barrel with door, constant barrel 5 windows after
23
Q
What material is nacelle and pylon made from
A
The primary structure includes the nose, the middle, the rear structure and the engine mount support spars. The nose and middle structures are made from aluminum alloy. All the connections from the aircraft to the engine pass through the firewall. The rear structure is made of a set of Kevlar ribs held together with rivets.
The intake cowl, upper and lower cowl doors and exhaust unit are mostly carbon fiber composite structures. The fixed cowl is titanium. All of the nacelle outer surface carbon fiber composite parts have a preimpregnated copper mesh outer lamination to shield electronic system against high intensity radiated fields (HIRFs) interference during lightning strike.
24
Q
What is minimum fuel for tow
A
5000lbs
25
What type of hf is it
Shunt type coupler
26
Do you tow aircraft if window is removed
No-its part of structure
27
Is the wing primary structure
Yes it carries the load of the aircraft
The outer wing is attached to the center wing box with the attachment fittings at the chords of the root ribs. The wing structure holds the auxiliary structure, the attachment fittings, and the flight control surfaces. The wing is divided into three zones: inboard, midwing, and outboard.
28
What are window properties
The windows in the aircraft include the flight compartment and passenger compartment windows. The windows are resistant to ambient pressure conditions. These conditions relate to a range of altitudes from 1000 ft below sea level to 51,000 ft above sea level. The windows have pressure seals to keep cabin pressurization, and they also have moisture seals to give protection to the crew compartment and the cabin from weather elements. The moisture seal also protects internal components in the transparent plies. The left and right side windshields and windows in the flight compartment give the crew sufficient forward and side vision. These windows have an anti-ice, defog, and demist system. There are 13 passenger compartment windows on each side of the fuselage. The passenger compartment windows are equal in dimension, shape, and material.
29
How many bushings does window have
The inboard retainer is a ring with retained nuts. The nuts align with the inner row of holes in the outboard retainer. The bolts that attach the plies to the outboard retainer go into the nuts in the inboard retainer. There are two sets of bushings. One set of 51 bushings go into the attachment holes that include the three sides of the outer frame. Face Ply Main Ply (inner) Interlayer Conductive Coating Windows The other set goes into the attachment holes where there is no outer frame. The bushing assembly is a metal bushing with a rubber insert. The side strap makes the splice between the windshield and the aircraft structure along the aft edge (this strap also attaches to the side window
30
Flight deck side windows
The side window assembly is a bonded structure which includes an outer frame, outer and inner main plies, an interlayer, an edge attachment set, an inboard retainer, bushing assemblies, and a side strap.
31
Why are winglets fitted
The winglets are installed at each wingtip. They are used to decrease wingtip vortices.
32
What type of spoilers are fitted
There are ground spoilers and multifunction spoilers on the upper trailing edge of the wings. The multifunction spoilers are used to remove lift when the aircraft is in flight. The ground spoilers are used to remove lift when the aircraft is on the ground.
33
How many flaps on each wing
Each wing has three fowler type flaps. The flaps are installed on the wing trailing edge and travel on four tracks.
34
How is the wing Center box made
The center wing box structure is made of a primary frame with skin panels on the top and bottom. The center wing box structure is sealed between the front and rear bulkheads and the root rib at BL47.610. This compartment is sealed for the integral fuel tank of the center wing box. The front bulkhead is a one-piece assembly. The rear bulkhead is made from aluminum alloy and made stronger with stiffeners and caps. The rear bulkhead is a support for the attachment fittings for the main landing gear (MLG) side brace. The keel beam assembly transmits the forward and aft wing loads to the fuselage structure. This assembly is installed at the centerline of the center wing box. The top and bottom skin panels are made from aluminum alloy plate. These skin panels have two access panels for the servicing of the fuel and hydraulic systems. These access panels are made from laminated graphite. The MLG side stay attachment fittings are made from aluminum alloy. They are installed on the rear bulkhead of the center wing box.
35
Where are root wing ribs sealed
Ribs are installed between the front and rear spars. These ribs are made from aluminum alloy. The root rib and the ribs at WS178.00 and WS287.00 in each outer wing are sealed to divide the fuel tanks into three compartments.
36
How many passenger windows
Each side of the fuselage has 13 passenger compartment windows. One of the 13 windows on the right side of the fuselage is in the overwing emergency door. Because the other windows have equal dimensions and the same shape they are interchangeable.
37
What material is the rudder made of
The rudder is installed on the rear of the vertical stabilizer at four hinge points. The rudder is made of composite material. The structure of the rudder includes a spar assembly, rib assemblies (installed aft of the spar assembly), nose ribs (installed forward of the spar assembly), and skins with doublers. Drain openings are installed.
38
Where is elevator pcu installed
Two attachment fittings for the power control unit (PCU) are installed in the inboard end of each elevator between hinge 1 and hinge 2. An attachment bracket for the elevator position transmitter is installed on the front spar of each elevator inboard of hinge 1.
39
What material are the elevator skin panels made from
The skin panels are made of laminations of graphite.
40
What fs is vertical stab
The vertical stabilizer holds the horizontal stabilizer and the rudder. The vertical stabilizer is installed on the empennage/tail, which connects with the aft fuselage at FS861.00.
41
What is primary structure on horizontal stab
The primary structure of the horizontal stabilizer is a torque box which has a center box structure and left and right stabilizer structures. This box is attached to the vertical stabilizer at its rear end by a hinge and at its forward end by an electric screw jack, which rotates the horizontal stabilizer to provide pitch trim.
42
What structure is pylon made of
The primary structure includes the nose, the middle, the rear structure, and the engine mount support spars. The nose and middle structures are made from aluminum alloy. All the connections from the aircraft to the engine pass through the firewall. The rear structure is made of a set of Kevlar ribs held together with rivets.
43
How is fuselage constructed
The forward fuselage is designed and manufactured by Shorts Brothers of Belfast, Northern Ireland. It is transported to Bombardier in Montreal for mating with the cockpit section before being transported to deHavilland in Toronto for final assembly. The forward fuselage is manufactured in two sections, the transition barrel from station FS281.00 to FS381.00, and the constant barrel from station FS381.00 to FS557.00. The skins, stringers, and frames of the fuselage are manufactured from aluminum.
44
Is the fuselage semi monocoque
The fuselage is a semimonocoque assembly. It has five sections connected together with butt straps, doublers and stringer splices. The fuselage skin is made of chemically milled aluminum alloy with aluminum alloy frames and stringers.
45
Where is the overwing exit
There is one overwing emergency exit. The overwing emergency exit is found on the right side of the passenger compartment over the wing. The overwing emergency exit gives the passengers and the crew one more exit during an emergency.
46
Where is the cargo door
Access to the cargo area is by the baggage compartment door. The baggage compartment door is found on the left side of the rear fuselage forward of the rear pressure bulkhead.
47
How many doors
The following components make up the doors and exits of the aircraft:
Passenger door
Overwing emergency exit • Baggage door •
Aft equipment bay door • Service doors and access panels
48
Does the pax door have a switch
Passenger Door Internal Switch Figure A2 The internal switch (identified DOOR) is installed at the passenger door opening in the passenger compartment. The switch is used to close the passenger door with electrical power.
49
Does door have external switch
Passenger Door External Switch Figure A2 The external switch is installed in the fuselage, aft of the passenger door, behind an access panel. The switch is used to close the passenger door with electrical power, when DC or AC is available.
50
Where is the door actuator fitted and powered
Passenger Door Actuator Figures A2 and A3 The actuator is installed adjacent to the middle shaft in the airstairs. The actuator turns the middle shaft with a single row chain and sprockets, to close the passenger door. The passenger door actuator is operated by a switch in the passenger compartment or an external switch, aft of the passenger door. The actuator uses a brushless DC motor which is connected to a planetary gearbox and slip clutch and to the output shaft. The motor is energized during the door close sequence, which takes 18 seconds maximum.
51
How is the door motor controlled
The proximity switch (internal of the actuator circuit card) energizes a slowdown circuit. This decreases shaft rotation to approximately 1 RPM (6°/seconds) before the door reaches the close position. When the door is opened and the motor is not energized, an eddy current damper controls the speed. The door opening time is 7.0/8.5 seconds (10 seconds maximum). Before full open, the proximity switch energizes the slowdown circuit, which decreases speed to 12.5°/second maximum. The slip clutch prevents the output shaft from being overdriven. A thermal switch is attached to the motor to remove voltage if the motor becomes too hot.
52
Does the door have a tensator assy
The Tensator assembly comprises a single torque drum mounted to the airstairs middle shaft and four Tensator springs each housed in a Tensator drum. The springs are made of steel and measure over 15 ft (4.57 m) in length when fully extended. As the door is lowered, the airstairs middle shaft, under action of the two fuselage mounted cables, rotates. It causes the torque drum to draw each of the four Tensator springs out of their respective drums and around the larger drum. The uncoiling of the Tensator springs creates both a resistance of the falling door and a reserve of potential energy to assist in door closing.
53
Does the pax door have a vent flap
On door closure, pressurization of the aircraft is prevented by the installation of a vent flap in the door structure unless the door is correctly closed and locked. The flap is held open by four tension springs and is driven shut by a cam face on the aft G-latch via a series of levers during the final locking sequence. The design is such that only two springs are required to retain the vent flap in the open position. In the event of residual cabin pressure or icing conditions, during door deployment, the vent flap is pulled open by a direct link to the torque tube prior to full door lift, via a cable assembly.
54
Does the pax door have prox sensors
There are three proximity sensors installed in the passenger door. Two are located inside the airstairs and sense G lock position. The third senses the outer handle position. The proximity sensors provide indication to the crew via EICAS displaying a caution Passenger Door (amber) when the door is not properly locked. The sensors confirm that the G-latches have fully engaged on the airstairs pin when the door is fully locked and the external handle is closed. This electrical indication system defaults to failsafe (i.e. caution Passenger Door) when a sensor or interface electronics fails. The proximity sensors are monitored by the (landing gear electronic control unit) LGECU. There is also a mechanical indication pointer to indicate that the door is locked.
55
How is door closed manually
A rope wound around a pulley on the aft end of the middle shaft must be unwound sufficiently to be brought up into the cabin. The rope can be pulled, rotating the middle shaft and raising the door via the normal cables. The rope pulley is much larger than the cable pulleys, thereby reducing the pulling force necessary. Once the door is raised, it may be lowered into the frame and locked by the normal method with the lock handle.
56
Does the door latch need resetting
If the door handle is unlocked, and the operator wishes to lock it again without fully opening the door, the torque tube latch release mechanism must be reset. It can be reset by moving the door partly out and then pulling it back in and then moving the handle to the locked position.
57
Does the emergency exit door have sensor
A single proximity sensor installed at the top center of the overwing emergency exit door opening. This sensor is monitored by the LGECU (Landing Gear Electronic Control Unit) to give an EICAS caution message, R EMER EXIT, once the door is open.
58
Can emergency exit be locked out
Overwing Exit Lockpin For added security, a GSE (Ground Support Equipment) lockpin can be installed from the inside to prevent unwanted entry from the outside. This pin must be removed before flight.
59
Does cargo door have a latching mechanism
Baggage Door Latch Mechanism The baggage door latch mechanism holds the baggage door in the closed position. Two bolt assemblies extend from the forward and aft edges of the door structure into fittings on the adjacent fuselage frames. Pushrods connect the shoot bolt assemblies to the handles. A pushrod opens and closes the vent door assembly as the handle operates.
60
Does cargo door have balance springs
There are two balance springs, which attach to the fuselage structure above the baggage door. Each balance spring has a spring wound to help lift the baggage door. A cable from each balance spring is attached to the door at a lower roller assembly. The cables wind on pulleys when the door opens and lifts.
61
Does cargo door have prox sensors
Baggage Door Proximity Sensors There are two proximity sensors. They monitor door closed and locked condition, and provide through the LGECU a visual caution on EICAS (cargo door) to the flight crew, if the door is not fully closed and locked.
62
Does aft equipment bay door have prox sensor
The aft equipment bay door has a single proximity sensor on the door frame to provide warning when the door is open. A caution message LARGE SERV DOORS will be displayed on the EICAS page.
63
Does hyd service access panel have a prox switch
There is one proximity sensor at the hydraulic system no. 3 servicing access panel. A LARGE SERV DOORS CAS message is displayed when the door is open.
64
What does the LGECU monitor
The proximity sensors are monitored by the landing gear electronic control unit (LGECU) and the microswitches are monitored by the data concentrator modular cabinets (DMCs). The LGECU monitors the doors that follow: • Passenger door •
Baggage door •
Overwing emergency exit •
Large service doors •
Aft equipment compartment door •
Refuel/defuel door •
Hydraulic system no. 3 servicing door
65
Does the DMC monitor small service doors
The DMCs monitor the small service doors.
66
What does LGECU sense
All doors excluding small service doors which are monitored by the DMC
67
Does symbol generator report back to iac
Yes it does , to satisfy the correct data has been observed and compares, its a wraparound circuit
68
Where does dau get its info from
Left and right primary ACSB, there are 4 dau,s
Left primary, right primary
Plus left and right backup
4 total,always talking to iac,s
69
How many iac,s
3 total but # 3 has 7 cards, rest have 8 cards
70
What does iac mean
Integrated avionic computer
71
Internal fuel panel where is it
Behind captain in cabin and r/h wing near trailing edge
72
Refuel system is master first panel selected
So its wise to select outside panel r/h side first as this will be master
73
Is fire panel live all the time
The system will inform if there is a fire, otherwise is switched off
74
Does pilots clock feed gps
Yes, non dispatchable otherwise, and has a battery
75
What is audio panel 3 used for
Data only
76
Area light switch always check
Can drain battery -hard wired to battery
77
Data loader do i use any usb stick
Always use approved usb stick
It’s on captains side panel by o2 mask
78
Where is cockpit printer
Co pilots side panel behind o2 panel
79
Where is pax o2 panel
Co pilots side panel
80
What are the data busses
Most information transfer between systems is accomplished by digital data buses. The data buses in the Global Express include: •
Avionics standard communications bus (ASCB) •4 off left primary, right primary, rh & r/h backup, 4 total
Radio system bus (RSB) •connects lru,s to
Digital audio bus (DAB) •
High-level data link control bus (HDLC) •
ARINC 429 data bus • standard bus
RS-232 data bus •
RS-422 data bus •
ARINC 453 data bus •
Weather radar picture data bus (WXPD) •
ARINC 717 data bus-dau 4 to fdr
81
What is rsb
Honeywell radio system bus (RSB) is the principal communications network, interconnecting the LRUs in the PRIMUS® II integrated radio subsystem. It is a fail-operational data bus system (if any device connected to the bus fails, the bus remains operational). The data traffic flow on RSB does not require a bus controller. It consists of three data buses: • Primary bus • Left side backup bus • Right side backup bus
82
Arnic 717
CVr !!!
ARINC 717 Data Bus DAU 4 transmits parameters to be recorded in the FDR via ARINC 717.
83
What does bus controller do, the aircraft has 3 using 4 ascb,s
IAC 1 = #1 BUS CONTROLLER
IAC 2 = #2 BUS CONTROLLER
IAC 3 = # 3 BUS CONTROLLER
Each bus controller is connected to three of the four data buses. Each bus controller simultaneously outputs request messages on both primary buses and on the onside backup bus. Only one bus controller is in control at any given time. The other bus controllers remain in standby status, ready to assume control automatically in the event the active bus controller becomes inoperative. Each subsystem is connected to and can receive data from three of the four data buses. This provides each subsystem with dual-path access to its onside data and single-path access to all crossside data.
84
What is HDLC control bus
High level data link, connects IAC to du,s
High-Level Data Link Control Bus Structure
There are six high-level data link control (HDLC) buses used on Global Express aircraft to provide display formats to DUs from IACs. Each IAC has two display processors (DPs) to generate the HDLC buses. The HDLC bus is a high-speed serial data link bus operating at 1 MHz. Each DP can output a unique display format every 25 milliseconds
85
What is RSB
Radio systems bus
Honeywell radio system bus (RSB) is the principal communications network, interconnecting the LRUs in the PRIMUS® II integrated radio subsystem. It is a fail-operational data bus system (if any device connected to the bus fails, the bus remains operational). The data traffic flow on RSB does not require a bus controller. It consists of three data buses: •
Primary bus •
Left side backup bus •
Right side backup bus
Data flow on RSB is bidirectional with a bit transmission rate of 667 kHz. Each subsystem outputs its message on the primary and its onside backup buses simultaneously and can receive data from the primary and onside backup buses. The input/output configuration makes it impossible for any single-point fault to disable all three data buses.
86
DAB bus
Changes analogue into audio
The PRIMUS®II system uses a digital audio bus to carry digital audio information from the remote radio system line replaceable units to the flight crew audio panels. The digital audio bus offers the advantage of complete independence from grounding problems within the aircraft and the absolute elimination of ground noise pickup, whine and crosstalk. The interconnect structure provides superior RF emissions characteristics, ensuring that the digital bus does not interfere with sensitive receivers on the aircraft. The buses are designated left/pilot (bus 1) and right/copilot (bus 2). The left COM and NAV radios only transmit on the left audio bus while the right COM and NAV radios only transmit on the right audio bus.
87
Arnic 717
DAU 4 to FDR, if it fails no flight data
ARINC 717 issues result in an FDR FAIL message.
FDR only supplied from DAU 4
Via ASCB
88
What bus does digital clock use
A dual clock system is supplied with the aircraft avionics equipment to provide the current time and date in local or Greenwich mean time (GMT), chronometer functions and elapsed time (ET). The digital clock system also transmits time-related information to other aircraft systems that require a time reference. This information is transmitted via an ARINC 429 data bus to integrated avionics computers (IACs). One digital clock is located on the pilot instrument panel and the other is located on the copilot instrument panel.
89
What does digital clock do
Digital Clocks The two digital clocks use inputs from the GPS to automatically set and synchronize time settings. The pilot clock is powered by the battery bus and the copilot clock by the DC bus 1. These clocks do not have an internal backup battery. When the aircraft is powered up outside the hangar and a valid GPS signal is available, the clocks will display the correct time and transmit time data to the IACs. If the aircraft receives an invalid GPS signal upon power up, the clocks will enter the time data setting mode and will not transmit time data. However, if the clocks are set manually, the time data will be transmitted. The local time needs to be set each time the aircraft is powered up. The clock has two LCD displays that show digits in white on a black background. There is no analog sweep. The upper six-digit LCD readout displays date (DT), GPS, internal (INT) or local time (LT). The lower four-digit LCD readout displays elapsed time (ET) or chronometer (CHR).
90
What is the FDR
The flight data recorder (FDR) system consists of the flight data recorder, a three-axis high-G accelerometer, data acquisition unit (DAU 4), underwater locating device and the pilot event marker (PEM). The flight data recorder (FDR) is a crashsurvivable data recorder that retains the last 25 hours of flight data. An underwater locating device (ULD) is attached to the FDR to locate it under water. All stored information is retained after removal of electrical power. Data can be recovered from the memory via the front panel of the FDR.
91
FDR data retrieval;
Flight Data Recorder The FDR is located in the aft equipment compartment. The FDR memory is enclosed in a heat shield and stainless steel package, which protects it from shock and thermal damage. It records all mandatory and additional optional parameters. The majority of data is recorded from the following systems: • ATA 34 (navigation) • ATA 72 (power plant) • ATA 22 (auto flight) • ATA 27 (flight control) • ATA 31 (indicating and recording) The data may be retrieved for analysis, using a hand-held download unit, via an RS-422 serial interface through the front panel connector.
92
What is Pilot event marker, clear every 30 calendar days, from Pmat
Pilot Event Marker The pilot event marker (PEM) pushbutton is located on the landing gear panel. When the PEM is pressed, two events are initiated simultaneously as follows: • An event signal is sent to the FDR to allow quick data retrieval • CAIMS initiates a recording of data in all member systems with non-volatile memory (NVM)
93
Where is FDR located
Aft equipment compartment
94
When does FDR start recording
The FDR system is automatically started when aircraft power is turned on and starts receiving data when DAU 4 receives an engine running or PEM discrete. The FDR records the data from DAU 4 channel B, via an ARINC 717 data bus at the rate of 128 words per second. Program pins on the rear connector are used to identify the data rate expected from DAU 4. If no data is present for more than 5 seconds, the FDR activates the system status flag and stops the recording process. When the FDR fails, a ground (FDR STATUS) is supplied to the DAU and the FDR FAIL advisory CAS message will be displayed on the EICAS page. The FDR records data in solid-state memory, which has a capacity of 25 hours. When the memory is full, the oldest data is overwritten. An event marker can be added to the FDR memory by pushing PEM on the landing gear panel. Flight data can be retrieved from the FDR via an RS-422 serial link, using a hand-held data download unit through the front panel connector. The high-G accelerometer provides normal acceleration data over a range of +3G to –6G. If the accelerometer is out of limits or the signal is invalid, an FDR ACCEL FAIL advisory CAS message is displayed when the aircraft is on the ground, with the parking brake set.
95
FDR where is power from
ASCB and info from DAU 4 via Arnic 717 bus
96
What g does accelerometer trigger
Plus 3 g
97
What is CFMS
Crew force monitoring system
Global series aircraft operating under FAR 135 (air carriers and operators for hire) and manufactured after Aug. 19 2002, require further additional parameters to be recorded by the flight data recorder (FDR):
1. Flight crew input force data to the control columns and control handwheels
2. Flight crew input force data to the rudder pedals The crew force measurement system (CFMS) implements these flight control inputs that are distributed to the FDR.
The crew force measurement system (CFMS) also requires the flight data recorder (FDR) to be upgraded from 58 recorded parameters to 88 recorded parameters and the four data acquisition units (DAU) to be upgraded. The CFMS consists of the following components: • Control column force transducer • Rudder pedal force transducer • Control wheel force transducer
98
What is DU 3
EICAS primary, and DU 4 is Synoptics
99
What is the DU
The display unit (DU) is a 16-color, highresolution cathode ray tube (CRT) and symbol generator contained in a single LRU. The six DUs which are installed on the main instrument panel, are identical and interchangeable. The DU presents dynamic displays as part of the EDS. The DU symbol generator uses two modes to make the displays: stroke and raster. The stroke mode provides the symbology and characters, and the raster mode provides background shades (i.e., the blue/brown sphere) and weather radar information. After the DU has converted the input data for the CRT circuits, those commands are reported back on an ARINC 429 bus to the IAC as wraparound data. The fault warning computer (FWC) portion of the IAC compares the wraparound data with the ADC, IRS, radio altimeter and the engine electronic controller (EEC) sensor input data, thereby verifying all critical display data.
100
WHAT ARE du allocations
In default configuration, each DU is dedicated for its own function: •
DU 1 = pilot PFD •
DU 2 = pilot MFD •
DU 3 = EICAS display •
DU 4 = system synoptic display •
DU 5 = copilot MFD •
DU 6 = copilot PFD
The intensity of the DUs display brightness is controlled by an automatic dimming system. In the automatic dimming system, the display intensity is manually set, using the cockpit lights flood/display control panel (figure E3). This intensity is modulated by a signal generated from the ambient light sensors (photosensors).
101
What are warning messages for EICAS
COLOR TYPE OF MESSAGE
Red; Warnings (including CAS messages)
Amber; Cautions (including CAS messages) Invalid data Failed (icons on synoptic displays)
Green ; Normal data On/Operating (synoptic displays)
Cyan; Pilot selectable/selected Advisory (including CAS messages) Static symbols (e.g., wing outlines on synoptic displays)
Magenta ; FMS generated data Status invalid/unavailable (synoptic displays)
White Warnings; Labels Scales Flow tube outlines (synoptic displays) Off/Standby (synoptic displays) Status (including CAS messages)
102
IAC how many cards
Integrated Avionics Computer The integrated avionics computers (IACs) are located in the main avionics bay on the Global Express and Global Express XRS. The IACs are installed in the above floor avionics rack on the Global 5000. IAC 1 and 2 contain eight plug-in circuit card assemblies (CCAs) and a power supply assembly. In the baseline aircraft configuration, IAC 3 contains seven CCAs and a power supply assembly. If the 3rd FMS option is selected, IAC 3 is the same as 1 and 2. An enclosure, mounted on the back of the IACs, holds a cooling fan and a battery assembly. The fan cools the IAC by drawing air from the front of the unit. The battery assembly supplies 3-V backup voltage to the internal random access memory (RAM) and an internal clock when the unit is removed from the aircraft or when the aircraft battery power fails. The internal clock is normally synced to Greenwich mean time (GMT) when the aircraft clocks are powered and transmitting time to the IACs.
103
How many du,s are iac,s connected to
Physically 6
Normally 2
Emergency 4
Switches in norm;
IAC 1 drives 1 & 2 du
IAC 2 drives 5 & 6 du
IAC 3 drives 3 & 4 du
104
Do i just swap the IAC
Power up other IACS first, by pulling CB on swapped IAC, OTHERWISE IT WILL REPROGRAMMED others, it what becomes master, tray 3 gets powered first the that becomes master, IAC 3 does most of monitoring
If an IAC configuration module is removed from the aircraft and is replaced with a configuration module from shelf stock, the configuration straps have to be cut (example table E2), in accordance with the procedures in Aircraft Maintenance Manual (AMM). The strap settings will be dependant on the A/C configuration.
105
IAC 3 does this monitor system
The integrated avionics computers (IACs) are located in the main avionics bay on the Global Express and Global Express XRS. The IACs are installed in the above floor avionics rack on the Global 5000. IAC 1 and 2 contain eight plug-in circuit card assemblies (CCAs) and a power supply assembly. In the baseline aircraft configuration, IAC 3 contains seven CCAs and a power supply assembly. If the 3rd FMS option is selected, IAC 3 is the same as 1 and 2.
106
EICAS controller what du
The EICAS controller provides pushbutton switches for selection of the appropriate systems synoptic display which can be displayed on DU 2, DU 4 and/or DU 5. The system synoptic displays are as follows:
Status display is the default display and includes: •
Cabin pressurization data •
Cabin temperature •
Oxygen data •
APU indications •
Brake temperature data •
Aircraft doors status •
Oil quantity for engines, APU and reservoir
107
How many computers does the CWS
Central warning system have
The central warning system (CWS) consists of three integrated avionics computers (IACs), junction box no. 4, two master warning/caution pushbutton annunciators (PBAs), an aural warning disable panel and three lamp dimmer power supplies (LDPSs).
108
How are the master caution lights enabled
The master warning/caution lights are enabled by the integrated avionics computers (IACs) through the contacts of the master warning and master caution relays located in junction box no. 4. The master warning light will flash to alert the flight crew anytime a warning message is displayed on EICAS. The master caution light will flash to alert the flight crew anytime a caution message is displayed on EICAS. Pressing the master warning or caution light will cancel the flashing light but the message will remain on the EICAS display.
109
What bus do the IAC,s use
Each IAC contains two display processors (DPs) which interface to the HDLC buses (figure E6). Each display processor has the ability to generate two independent formats and output them on the HDLC buses. PFD controller information, along with reversion controller switch positions, is used by the display processors to determine what display format is transmitted on which bus. If one IAC fails, the remaining two lACs can support all six DUs, and a single IAC can support up to four DUs.
110
Where does captains clock get its power from
SPDA 1,WOW sends info to 1 and 2 clocks , captains clock out to IAC 1 and 2
F/O,s clock to IAC 2
All get their power supply from SPDA 1
111
What is an SPDA and what does it do
SPDA = secondary power distribution assembly
The TRUs receive power from the AC system, which is transformed and rectified into DC power. The TRUs DC output is supplied to the DC power center (DCPC), which distributes the power to four secondary power distribution assemblies (SPDAs). The SPDAs distribute power to the aircraft subsystems.
112
What does the electronic display system consist of EDS
The electronic display system (EDS) consists of six display units (DUs), three integrated avionics computers (IACs) and configuration modules, two primary flight display (PFD) controllers, two multifunction display (MFD) controllers, an EICAS controller and a reversion controller.
The electronic display system consists of the following components: • Display units (DUs) • Integrated avionics computers (IACs) • IAC configuration modules • Primary flight display (PFD) controllers • Multifunction display (MFD) controllers • EICAS controller • Reversion controller • Cockpit flood/display lights control panel
113
What info is on PFD
Primary Flight Display
The primary flight displays (PFDs) provide all information for control of the aircraft throughout the flight envelope. In normal operation, the pilot PFD is displayed on DU 1, and the copilot PFD is displayed on DU 6. All information combined in this display represents information normally displayed in a conventional nonelectronic display cockpit, on the attitude director indicator (ADI), horizontal situation indicator (HSI), vertical speed indicator (VSI), altimeter, airspeed indicator and mode annunciator in the same T-configuration.
114
What info is on a MFD
The MFD is primarily a navigation display. In normal operation, the pilot MFD format is displayed on DU 2, and the copilot MFD format is displayed on DU 5. FMS lateral flight plan is displayed in either the map format (aircraft heading reference) or plan format (true North reference). The FMS vertical profile of the aircraft may also be displayed. Displays from the following subsystems are also selectable for display on the MFDs: • Weather radar (WXR) • Lightning sensor system (LSS) • Traffic alert and collision avoidance system (TCAS) • Enhanced ground proximity warning system (EGPWS) Additionally, the following information is selectable on the MFD: • Electronic checklists (if installed) • Pop-up menu selections
115
What info is on the EICAS display
EICAS Primary Display The EICAS primary display (DU 3) provides primary engine parameters (N1, EPR, ITT) and secondary engine parameters (N2, fuel flow, oil temperature and oil pressure). Other parameters provided by the EICAS display include fuel quantity, gear position, flap/slat/spoiler positions, and control surface trim indication (stabilizer, ailerons, and rudder). Crew alerting system (CAS) messages are also displayed. On the ground, the CAS window displays up to 14 messages. While in flight, after the gear, flaps and slats are retracted, their indications are removed and the CAS window expands to display up to 24 messages.
116
What info is on a system SYNOPTIC display
System Synoptic Displays The system synoptic display (DU 4) provides system synoptic information in a “flow tube” graphical format for each of the following aircraft systems: • Bleed/anti-ice air • Air conditioning • Hydraulics • Electrical AC • Electrical DC •Fuel • Flight controls • Status (default position)
117
What does the IAC do
Three integrated avionics computers (IACs) are located in the main avionics bay on the Global Express and Global Express XRS or in the above floor avionics rack on the Global 5000. Each IAC has the capability to support the following functions: • Input/output processor • ASCB controller • Electronic display system (EDS)- Electronic flight instrument system (EFIS)- Engine indicating and crew alerting system (EICAS)- Fault warning computer (FWC)- Central aircraft information management system (CAIMS) • Flight management system (FMS) • Autothrottle (AT) • Flight guidance computer (FGC)- Flight director system (FDS)- Autopilot (AP)- Yaw damper The IAC allows each of these functions to remain independent of each other while using a common input/output subsystem and power supply. Each IAC contains two display processors (DPs) that perform symbol generation. All inputs to the IAC DPs are via the ASCB and RS-422 buses. The RS-422 bus inputs are from the MFD controller. The IAC DPs collect and process data from various sources, and output data to the six display units via high-level data link control (HDLC) buses.
118
What are the IAC configuration modes
IAC Configuration Modules There are three IAC configuration modules. The IAC has a number of options which are identified by configuration straps. These straps are located in the IAC configuration module, which is a standalone unit mounted next to each IAC.
119
Are the DU,s auto-dimmed
The intensity of the DUs display brightness is controlled by an automatic dimming system. In the automatic dimming system, the display intensity is manually set, using the cockpit lights flood/display control panel (figure E3). This intensity is modulated by a signal generated from the ambient light sensors (photosensors).
120
Does the IAC have a battery
An enclosure, mounted on the back of the IACs, holds a cooling fan and a battery assembly. The fan cools the IAC by drawing air from the front of the unit. The battery assembly supplies 3-V backup voltage to the internal random access memory (RAM) and an internal clock when the unit is removed from the aircraft or when the aircraft battery power fails. The internal clock is normally synced to Greenwich mean time (GMT) when the aircraft clocks are powered and transmitting time to the IACs.
121
Where does the clock get its backup from if main battery disconnected
An enclosure, mounted on the back of the IACs, holds a cooling fan and a battery assembly. The fan cools the IAC by drawing air from the front of the unit. The battery assembly supplies 3-V backup voltage to the internal random access memory (RAM) and an internal clock when the unit is removed from the aircraft or when the aircraft battery power fails. The internal clock is normally synced to Greenwich mean time (GMT) when the aircraft clocks are powered and transmitting time to the IACs.
122
What happens if a. IAC fails
Each IAC contains two display processors (DPs) which interface to the HDLC buses (figure E6). Each display processor has the ability to generate two independent formats and output them on the HDLC buses. PFD controller information, along with reversion controller switch positions, is used by the display processors to determine what display format is transmitted on which bus. If one IAC fails, the remaining two lACs can support all six DUs, and a single IAC can support up to four DUs.
123
Reversion controller function
Reversion Controller Figure E11 The reversion controller allows manual selection of various display sources, and display options to maintain cockpit functionality in the event of a sensor, display, or IAC symbol generator failure. PFD 1 Switch Figure E12 When the rotary switch is in the NORM position, the PFD format is displayed on DU 1. When the rotary switch is in the ALTN position, the PFD format is displayed on DU 2. When the PFD and EICAS are switched to the same DU, the PFD takes priority. PFD 2 Switch Figure E12 When the rotary switch is in the NORM position, the PFD format is displayed on DU 6. When the rotary switch is in the ALTN position, the PFD format is displayed on DU 5. When the PFD and EICAS are switched to the same DU, the PFD takes priority. EICAS Switch Figure E13 When the switch is in NORM position, the EICAS primary format is displayed on DU 3. When the switch is in ALTN 1 position, the EICAS primary format is displayed on DU 4. When the switch is in ALTN 2 or ALTN 3 position, the EICAS primary format is displayed on DU 2 or DU 5 as long as the PFD is not displayed on the selected DU.
124
What is PFD alternate source
Alternate moves screen 1 screen in -same source
125
EICAS and PFD are primary screens
EICAS selected to alt1, it moves 1 to right, leaving #3 screen blank
126
IAC can control max of 4 screens
Connected to 6 though, normally 2
127
What happens when sg 1 fails
Select to alternate, sg 2 drives du3 and 6
Sg3 drives du1, du2 and du4
Advisory in WHITE
128
What happens if sg2 fails
Select sg2 to alternate sg1 drives du1, and du2
Sg3 drives du3, du5, du6
129
Sg1 and sg3 fail
Sg3 drives du1,du3,du5,du6
IAC can only run 4 but connected to 6
Page E25
130
What is SPDA powered by
Generator, battery, rat, each SPDA 80 power outlets,
E26
131
What happens on start up
E27
Power-On Built-In Test The EDS processors (DP1 and DP2) are required to perform extensive power-up testing to ensure correct operation of the hardware. This is needed to reduce exposure periods of faulty hardware, which could result in misleading data to the flight crew. The testing will be different, depending upon a warm or cold start. The following tests are performed: • All tests during a cold start • Only a subset of the tests during a warm start
132
Q iac mem full
E28
Clear the non volatile memory,over 80 per cent full, will give probs
133
What is PMAT
Portable Maint
Claims and Pmat, laptop
Clears nvm,s
134
What does EFIS system consist of
F1
The electronic flight instrument system (EFIS) consists of two primary flight displays (PFDs), two multifunction displays (MFDs), two primary flight display (PFD) controllers, two multifunction display (MFD) controllers, a reversion controller, three integrated avionics computers (IACs), three IAC configuration modules and a cockpit flood/ display lights control panel. Flight Deck Controls The EFIS provides the flight crew with all the necessary display information for aircraft control and navigation. Data from various subsystems are used by the EFIS to generate the appropriate formats on the display units. In normal operation, the EFIS system displays this information on the primary flight display (PFD) and multifunction display (MFD) of the pilot and the PFD and MFD of the copilot.
135
What does PFD controller 1 control
F3
DU 1 and 2
136
On PFD if using another source any indications
F5
Yes will be at to amber caution
137
Cyan
138
What colour is fms info
CYAN is active state
139
What does rad alt display
2500 feet in green on PFD on figure f5 it displays 1300ft
F5
140
What is amber
F7
Acceptable but out of limit- boxed- caution
141
What does MFD show
F8
The MFD format display map mode can be divided into nine sections: • Upper display annunciation area • Center display annunciation • FMS navigation display • Vertical profile window • WX/LSS data window 6 • TCAS zoom window 3 • Pop-up menu • Electronic checklist
142
What is pop up display
F9
If more than one selection is active from display controller, the priority to determine which window is active is as follows: • TCAS zoom window (highest) • POP-UP menu window • Vertical profile window (lowest) The pop-up menu allows the flight crew to change information displayed on PFD and navigation display, source selection preference, and to view engine exceedance information.
143
What happens 3rd press of menu
F9
Exceedencies, will bring up cas message
EXCEEDENCE Displays any given exceedence transmitted by the engine electronic controller (EEC). Only displayed when the airplane is on the ground.
144
Q , the pop up menu is only valid for that power cycle
F10
145
What is ABN button
Abnormal procedures on Synoptics panel, MFC (multifunctional controller) panel 1 per side
F12
146
What du,s are EICAS
G3
Du 2,3,4,5
147
What is lamp test
G8
The LDPS system consists of three power supplies that receive 28 VDC and output 28/9 VDC, depending on the PBA BRT/DIM switch selection. Each supply is capable of 28 VDC at 3.7 amps. The BRT setting provides 28 volts for daytime viewing, and the DIM setting provides 9 volts for nighttime use. Through EMS CDU,both sides
148
What happens 28 secs after gear up
G11
Dark cockpit, all messages are out, except
149
Where does EPR get its info from
G11
Fms on EICAS screen 3
150
What colour are advisories
G12
Warning (red) immediate recognition
Amber) Immediate recognition Immediate crew awareness Advisory
(cyan) Status
(white) Minor system failures or significant crew reminders Non-normal pilot selections
151
What is outside dial for o2, the o2 system is temp compensated by volume
G14
Only o2 to be used for dispatch -status page in flight deck,
Comes up as a percentage
152
EICAS controller what is it
G14
Selects Synoptics
153
How many computers in CWS central warning system
H1
The central warning system (CWS) consists of three integrated avionics computers (IACs), junction box no. 4, two master warning/caution pushbutton annunciators (PBAs), an aural warning disable panel and three lamp dimmer power supplies (LDPSs).
154
Does aircraft mute warnings on take off
H4
Yes
The crew alert system (CAS) display is controlled by the priority FWC. Messages are prioritized by the FWC. The FWC also provides the pilot with a selectable checklist. The checklist has stored text for normal, abnormal and emergency pages.
155
Does aural warning feed all iacs
H7
Yes
156
Can aural warning be muted
H10
Can be overridden-stall is highest level
By iacs 1 and 2
157
Where do i test the aircraft systems
h12
Ems-cdu
Integrated built in test
158
What’s the main difference between the vision and 5000
Avionics cabinet not inside, less screens, Dont need a plug in to download FDR ,
159
What is ASCB bus
Avionics Standard Communications Bus Figure B1 Honeywell avionics standard communications bus (ASCB) is the principal communications network interconnecting the PRIMUS® 2000XP system and is a fail-operational data bus system. If any device connected to the bus fails, the bus remains operational. ASCB consists of four data buses: • Left side primary bus • Right side primary bus • Left side backup bus • Right side backup bus Bidirectional data flow with a bit transmission rate of 667 kHz. Data flow on the ASCB is managed by three fail-passive bus controllers inside the IACs.
Each bus controller is connected to three of the four data buses. Each bus controller simultaneously outputs request messages on both primary buses and on the onside backup bus. Only one bus controller is in control at any given time. The other bus controllers remain in standby status, ready to assume control automatically in the event the active bus controller becomes inoperative. Each subsystem is connected to and can receive data from three of the four data buses. This provides each subsystem with dual-path access to its onside data and single-path access to all crossside data. Each subsystem outputs its reply data simultaneously on its onside primary and onside backup buses only. This input/output configuration makes it impossible for any single-point fault to disable all four data buses. Each subsystem responds to its own uniquely defined address transmitted by the active bus controller. By design, the ASCB interfaces are virtually immune to lightning-induced transients, hot shorts, ground shorts, and RF threats. ASCB status is monitored by the FWC.
