bgu
問題一覧
1
Only if the aircraft is in on the ground, and the internal pressure is below a predetermined value.
2
Display Unit 2 removed
3
Helicopter on ground
4
Inside the CMC (Central Maintenance Computer) and Data Base modules
5
Inside both NIC/PROC (Network Interface Controller with Processor) and the Data Base modules
6
Set the electrical power off to reset the module
7
Upload database files and software
8
Show a selection of current or historical message data
9
Show a selection of current or historical message data
10
Make a selection of a specific test
11
Load the Flight Software and the Loadable Diagnostic Information (LDI) Software
12
MAU 2
13
In the rear avionics bay
14
MAU 1
15
MAU 2
16
ASCB-D Right Primary and Right Backup
17
Left Primary, Right Primary and Right Backup
18
ASCB-D
19
It is used to interface the MAU modules to the backplane bus (VbPCI)
20
Standard precautions for handling electrical components must be applied
21
Both pointer and digital readout turn red
22
Control Area Network (CAN)
23
ASCB-D Data Bus
24
On the on-side primary and backup ASCB-D buses
25
On the on-side ASCB-D buses and from the cross-side ASCB-D primary bus
26
To all the MAU Modules except the Power Supply and the GPS Module
27
It transfers maintenance data, test functions and software loading data loading
28
MAU Modules on the VbPCI Data Bus
29
MAU 1
30
By first pressing the release button
31
IM-950 (APM)
32
Serial and Parallel Data Bus
33
To store a backup of the CMS (Central Maintenance System) and FMS (Flight Management System) software
34
It is a digital bi-directional bus for the dual Linear Actuators
35
Four minimum
36
Kevlar
37
Kevlar
38
Six bolts
39
The torque loading is the same for all bolts
40
It is fixed to the Tail Unit
41
Through any of the Cabin Windows
42
Tension link and elastomeric bearing
43
By the top and bottom conical rings
44
Hydraulic damper provided with internal fluid reservoir chamber
45
Hydraulic
46
Damper reservoir need to be serviced with fluid
47
Triple-coil magnetic pickup
48
Discrepancy between digital NR data from EEC and analog backup NR data from the sensor
49
Composite material
50
Solid film lubricant
51
By adjusting the length of the Pitch Links and adjusting the Outer and Inner Trim Tabs
52
It is a fully-articulated Main Rotor Head
53
In the Blade Bolts
54
Visually through a Sight Glass
55
A method using a special tool
56
The Support Plates
57
The same length of the pitch link replaced
58
Above 110%
59
Via an NR Sensor
60
The Mast must be aligned vertically
61
Centrifugally-activated sprag type
62
Wet-sump type
63
Gerotor type
64
It is provided with a thermostatic bypass valve
65
Steel shaft connected by a spline to the engine output shaft and by a flexible coupling to the MGB Input flange
66
At the end of each oil pressure distribution side
67
On each MGB Input modules
68
One in the Mast and two in the Sump
69
Land as soon as practicable
70
Reduce power and land as soon as practicable
71
To test, troubleshoot and check the continuity of the cabling to each individual sensor
72
Only on the ground, with both engines off
73
When the aircraft is on the ground and both Engines are in the OFF position
74
Fiber glass
75
Nickel alloy
76
Tha tail rotor blade may be replaced individually
77
The yellow marks located on the hub arm must be aligned with those on the blade
78
By rotating the main rotor blade
79
Forged titanium
80
By two conical rings
81
Elastomeric
82
The elastomeric material of the damper is worn beyond limits; replace the damper
83
A new Shim between the Tail Rotor Blade Pitch Change Arm and the Bearing must be calculated
84
Damper Attachment Plate
85
one
86
With a top conical ring and two bottom conical half rings
87
By using a special tool
88
On condition
89
After replacement of the Bearing or the Cover or the Spider Assembly
90
The Slider Assembly slides inside the Slider Bushing
91
The Tail Rotor Servoactuator Pitch Control Rod is installed with a nut on the duplex bearing
92
3 sections, one is made of steel alloy and two are made of aluminum
93
1st Steel, 2nd Aluminium, 3rd Aluminium
94
A Temperature Sensor, a Chip Detector, an Oil Low Level Sensor
95
A temperature sensor, a chip detector, an oil low level sensor
96
Chip Detector, Temperature Sensor, Oil Level Sensor
97
Land as soon as possible
98
No emergency landing is required
問題一覧
1
Only if the aircraft is in on the ground, and the internal pressure is below a predetermined value.
2
Display Unit 2 removed
3
Helicopter on ground
4
Inside the CMC (Central Maintenance Computer) and Data Base modules
5
Inside both NIC/PROC (Network Interface Controller with Processor) and the Data Base modules
6
Set the electrical power off to reset the module
7
Upload database files and software
8
Show a selection of current or historical message data
9
Show a selection of current or historical message data
10
Make a selection of a specific test
11
Load the Flight Software and the Loadable Diagnostic Information (LDI) Software
12
MAU 2
13
In the rear avionics bay
14
MAU 1
15
MAU 2
16
ASCB-D Right Primary and Right Backup
17
Left Primary, Right Primary and Right Backup
18
ASCB-D
19
It is used to interface the MAU modules to the backplane bus (VbPCI)
20
Standard precautions for handling electrical components must be applied
21
Both pointer and digital readout turn red
22
Control Area Network (CAN)
23
ASCB-D Data Bus
24
On the on-side primary and backup ASCB-D buses
25
On the on-side ASCB-D buses and from the cross-side ASCB-D primary bus
26
To all the MAU Modules except the Power Supply and the GPS Module
27
It transfers maintenance data, test functions and software loading data loading
28
MAU Modules on the VbPCI Data Bus
29
MAU 1
30
By first pressing the release button
31
IM-950 (APM)
32
Serial and Parallel Data Bus
33
To store a backup of the CMS (Central Maintenance System) and FMS (Flight Management System) software
34
It is a digital bi-directional bus for the dual Linear Actuators
35
Four minimum
36
Kevlar
37
Kevlar
38
Six bolts
39
The torque loading is the same for all bolts
40
It is fixed to the Tail Unit
41
Through any of the Cabin Windows
42
Tension link and elastomeric bearing
43
By the top and bottom conical rings
44
Hydraulic damper provided with internal fluid reservoir chamber
45
Hydraulic
46
Damper reservoir need to be serviced with fluid
47
Triple-coil magnetic pickup
48
Discrepancy between digital NR data from EEC and analog backup NR data from the sensor
49
Composite material
50
Solid film lubricant
51
By adjusting the length of the Pitch Links and adjusting the Outer and Inner Trim Tabs
52
It is a fully-articulated Main Rotor Head
53
In the Blade Bolts
54
Visually through a Sight Glass
55
A method using a special tool
56
The Support Plates
57
The same length of the pitch link replaced
58
Above 110%
59
Via an NR Sensor
60
The Mast must be aligned vertically
61
Centrifugally-activated sprag type
62
Wet-sump type
63
Gerotor type
64
It is provided with a thermostatic bypass valve
65
Steel shaft connected by a spline to the engine output shaft and by a flexible coupling to the MGB Input flange
66
At the end of each oil pressure distribution side
67
On each MGB Input modules
68
One in the Mast and two in the Sump
69
Land as soon as practicable
70
Reduce power and land as soon as practicable
71
To test, troubleshoot and check the continuity of the cabling to each individual sensor
72
Only on the ground, with both engines off
73
When the aircraft is on the ground and both Engines are in the OFF position
74
Fiber glass
75
Nickel alloy
76
Tha tail rotor blade may be replaced individually
77
The yellow marks located on the hub arm must be aligned with those on the blade
78
By rotating the main rotor blade
79
Forged titanium
80
By two conical rings
81
Elastomeric
82
The elastomeric material of the damper is worn beyond limits; replace the damper
83
A new Shim between the Tail Rotor Blade Pitch Change Arm and the Bearing must be calculated
84
Damper Attachment Plate
85
one
86
With a top conical ring and two bottom conical half rings
87
By using a special tool
88
On condition
89
After replacement of the Bearing or the Cover or the Spider Assembly
90
The Slider Assembly slides inside the Slider Bushing
91
The Tail Rotor Servoactuator Pitch Control Rod is installed with a nut on the duplex bearing
92
3 sections, one is made of steel alloy and two are made of aluminum
93
1st Steel, 2nd Aluminium, 3rd Aluminium
94
A Temperature Sensor, a Chip Detector, an Oil Low Level Sensor
95
A temperature sensor, a chip detector, an oil low level sensor
96
Chip Detector, Temperature Sensor, Oil Level Sensor
97
Land as soon as possible
98
No emergency landing is required