Exam Flashcards
(83 cards)
1
Q
Rotors turning, the overall length of the AS350 is approximately:
A
42.5 feet
2
Q
The AS350’s rotor disk diameter is approximately:
A
35 feet
3
Q
The high skid gear on an AS350 is approximately ___ feet wide and ___ feet long.
A
8, 11
4
Q
True or false?
GLYV’s engine is controlled by a FADEC?
A
False
5
Q
The engine in GLYV is an:
A
Arriel 1D1
6
Q
The capacity of the fuel tank is ___ liters or approximately ___ pounds.
A
540, 1000
7
Q
Maximum internal gross weight is:
A
4961 lbs
8
Q
Maximum all up weight with an external load is ___ lbs and the maximum authorized swing load weight is ___ lbs.
A
5512, 2557
9
Q
Vne power on is?
A
155 kts - 3 kts/1000ft
10
Q
Vne power off is?
A
125 kts - 3 kts/1000ft
11
Q
The Vne with the pilot’s door removed is:
A
70 kts with the sliding door closed, 100 kts with the sliding door locked open
12
Q
Normal operating range for Nr is:
A
375 to 394 rpm
13
Q
The FLI maximum takeoff rating is:
A
10 and there may be a time limitation depending on which parameter is within the takeoff rating range
14
Q
The FLI maximum transient rating is:
A
10.4 for 5 seconds maximum
15
Q
The maximum continuous rating for torque is:
A
94%
16
Q
The maximum torque takeoff rating is ___ and is limited to an airspeed of ___. There ____ time limit for the use of the takeoff torque range.
A
100%, 40 kts or less, is no
17
Q
The maximum transient torque limitation is:
A
107% for 5 seconds
18
Q
The “delta” Ng takeoff rating range is ___ and is limited to ___.
A
-4 to 0%, 5 minutes
19
Q
The maximum transient “delta” Ng is:
A
+1% for 5 seconds
20
Q
The T4 takeoff rating range is:
A
795 to 845 degrees C and there is no time limit
21
Q
Maximum load in the tail boom compartment is:
A
176 lbs @ 30 lbs/sq.ft
22
Q
True or false?
A minimum of two serviceable headsets (one of which may be the pilot’s helmet) shall be onboard the aircraft at all times. This is because many of the aircraft’s audio warnings are delivered through the intercom system?
A
True
23
Q
What are some points with regards to the starter limitations?
A
- If the first start attempt is aborted, a cooling time of 60 seconds shall be observed, followed by an engine crank of 30 seconds. Both FUEL PUMPs shall be on for an engine crank
- A maximum of two start attempts may be performed before a 30 minute cooling time must be initiated
24
Q
With battery power on, how many lights should illuminate on the caution and warning panel?
A
7 lights
25
Battery voltage must be __ and the bleed valve flag should ___ prior to starting the engine.
>22V, be visible
26
True or false?
Despite it not being mentioned in the flight manual, it is recommended by Airbus to preset the forward end of the FFCL to the near (aft) end of the middle notch (anti flame-out position notch) prior to hitting the starter button?
True
27
True or false?
When winds are above 30 kts, the pre-flight hydraulic checks and post-flight engine cool down should be performed with the FFCL in the FLIGHT detent?
True
28
True or false?
The pilot's right hand should be on the cyclic for engine start?
True
29
During the start procedure, the starter shall be released at:
40-45% Ng
30
Ng rpm should be set at ___ during ground idle.
67-70%
31
True or false?
The hydraulic checks shall be done at ground idle (67-70% Ng)?
True
32
What are some points with regards to the accumulator check, while the ACCU TST switch is depressed?
- The collective shall be down and locked
- The FFCL shall be at ground idle (67-70% Ng)
- The HYDR light flashes
- There should be no control loads felt on the cyclic
- Forces should be felt on the pedals
33
What are some points with regards to the hydraulic pressure isolation check, while the hydraulic cutoff switch is OFF:
- The collective shall be down and locked
- The FFCL shall be at ground idle (67-70% Ng)
- The hydraulic light is on
- Control loads should be felt immediately on the cyclic
- Control loads on the pedals should stay low (yaw load compensator effect)
- It should take 3 to 4 seconds for the HYDR to extinguish once the switch is reset to the normal position
34
True or false?
During the hydraulic pressure isolation check, maintenance action must be performed prior to flight if, upon reinstatement of the hydraulic cutoff switch, it takes one second or less, or more than 4 seconds for the HYDR light to extinguish
True
35
True or false?
CAUTION: If not locked, the collective will come up when the accumulators are depleted or when the hydraulic cut-off switch is set to OFF?
True
36
True or false?
It is imperative to not allow the Nr to remain steady between 300 and 320 rpm during the engine acceleration as this can set up a damaging harmonic vibration in the tail rotor drive shaft. If the pilot is inattentive and allows the engine to idle above 70% Ng, the Nr could enter this range?
True
37
True or false?
The cranking procedure can be carried out after an aborted start or during maintenance operations. Both fuel pumps shall be on and the crank button depressed for 30 seconds maximum?
True
38
Which components assist in dampening ground resonance?
- The steel springs attached to the aft end of the skids
- Flex in the cross tubes
- The oleos
39
Which components assist in dampening main rotor vibration?
- The 'China hat'
- The 'dogbone' mount on the bottom of the MGB
- The hammers
40
Vy (best rate of climb speed) for the AS350 B2 is?
55 kts
41
True or false?
Airbus recommends that cyclic and collective friction be adjusted so that friction loads are felt by the pilot when moving the flight controls?
True
42
What are some points with regards to the generator?
- GENE switch shall be ON prior to hitting the starter
- GENE switch shall be turned OFF upon engine shutdown
- In the event of a faulty hall effect loop, leaving the GENE switch on could cause starter to motor if battery power is on
- The generator comes online when the generator voltage exceeds battery voltage
- If an AS350 is started with a battery cart/APU and the aircraft's battery is completely dead, it will be impossible to bring the generator online
43
What are some points with regard to the rotor brake?
- Shall be applied at a max Nr or 170 rpm, but at less than or equal to 140 rpm for normal use
- The minimum time between two consecutive applications is 5 minutes
- Shall be used judiciously by the pilot as its replacement is expensive and a severe pain in the rear end to your friendly engineer
44
True or false?
When the rotors have stopped after engine shutdown, the ACCU TST button shall be depressed for 2 seconds and the pedals re-centered, if necessary?
True
45
True or false?
In order to avoid excessive partial NF cycles, Ng rpm should be maintained on the higher side of the 67-70% ground idle range?
True
46
How do you manually record Nf cycles for GLYV?
- One start = 1 cycle
- one power reduction from flight idle to ground idle then back up to flight idle = 0.5 cycles
47
True or false?
After the last flight of the day, the pilot shall record both the Ng and Nf cycles from the VEMD flight report page into the aircrafts journey log book?
False
48
What are some points with regards to the audio warnings of GLYV?
- There are 4 different audio warnings that can be broadcasted through the ICS
- a gong is heard each time a red light appears on the CWP
- The low rotor horn is a continuous 310 Hz tone that sounds when Nr <360 rpm
- A continuous 285 Hz tone sounds when power remains in the transient range longer than 1.5 seconds
- A continuous 285 Hz tone sounds when transient power limitations are exceeded
- A continuous 285 Hz tone sounds when transient power limitations may be exceeded during a fast power increase
- The high rotor horn is an intermittent 310 Hz tone that sounds when Nr >410 rpm
49
Recommended airspeed during an autorotation is:
65 kts
50
In the event of an engine failure and time premitting:
- Aviate, navigate, communicate
- Trim aircraft to 65 kts
- FFCL to OFF position
- Emergency fuel shutoff to OFF position
- FUEL PUMP switches OFF
- BATT to EMER SHED
51
True or false?
In the event of a low side governor failure, the red emergency sector guard needs to be lifted out of the wat and the black tab on top of the FFCL needs to be depressed to move the FFCL into the emergency sector, all while maintaining your Nr with collective?
True
52
True or false?
If you experience a complete loss of tail rotor thrust while hovering in ground effect, the FFCL shall be retarded and the collective increased to cushion touch down?
True
53
If you experience a loss of tail rotor control in flight:
- Set airspeed to 70 kts
- If you allow your airspeed to drop below 20 kts, a go-around may be impossible
- The ACCU TST button shall be depressed for 5 seconds to depressurize the load compensator and then reset to OFF
- Landing will be made easier with a RH wind component
- A shallow approach with a left sideslip is recommended
54
With the BATT switch in the EMER SHED position, all DC power is switched off except for:
- Nr/Nf gauge
- Crew reading lights
- VHF/NAV1/GPS
- Transponder
- ICS
- Instrument lighting (circuit #2)
55
If you lose both VEMD screens due to a complete electrical failure, you elect to ___ using a ___ landing. The maximum power/collective setting authorized is that which keeps the aircraft flying at ___.
Land as soon as practical, no hover
100 kts - 2kts/1000ft
56
The FUEL P light comes on in flight:
- One or both fuel pumps are faulty
- Cross referencing with the fuel pressure gauge should indicate if one or both pumps are faulty
- If both are faulty, you may continue flight at Hp < 5000' asl
57
If the FUEL FILT light comes on in-flight:
- The problem is significantly more serious than a FUEL P light and should be treated as such
- If after reducing power the light remains on, land as soon as possible
- If after reducing power the light goes out, establish flight at reduced power and land as soon as practicable
- If Ng oscillations occur, land immediately
58
If the A/F FUEL FILTER light comes on in flight:
- If after reducing power the light remains on, land as soon as possible
- If after reducing power the light goes out, establish flight at reduced power and land as soon as practicable
- Illumination of the A/F FUEL FILTER light should be treated with the same degree of seriousness as illumination of the FUEL FILTER light
59
If the FUEL light comes on:
- Land as soon as possible
- Avoid large attitude changes (fuel sloshing could lead to a flame out)
- 18 minutes of flight time remain at MCP
60
With regards to the DC electrical system:
- Maximum permissible generator voltage is 31.5V
- The generator will come offline automatically if it exceeds its maximum voltage
- The generator will stay online whether the battery switch is on or off
- Maximum continuous current output is 150 A
61
If you lose the torque parameter on the VEMD, reference the ___ instead with the value shown on the ___. You should land as soon as ___.
Ng, table, practicable
62
With regards to a hydraulic emergency:
- The hydraulic failure safety speed is 40-60 kts
- Accumulator assistance allows you to slow down or speed up to the hydraulic failure safety speed from various flight regimes
- The hydraulics must be shutoff via the collective HYD switch as soon as the safety speed is reached
- With hydraulics off, airspeed may be increased above the hydraulic failure safety speed as conditions warrant but control loads will increase
63
True or false?
Servo-transparency or 'jack-stall' is encountered when the aerodynamic forces acting in the main rotor blades (referred to as the 'load factor' by airbus) exceed the hydraulic forces generated by the main rotor servos?
True
64
An increase in the following will increase the load factor and the likelihood of encountering servo transparency:
- Airspeed
- Gross weight
- Density altitude
- Collective setting
- Severity of maneuver
65
True or false?
If the HYDR light illuminates during HIGE, takeoff or final and landing within 30 seconds is possible, then you should land normally, leaving the hydraulic cut-off switch in the ON position?
True
66
Servo transparency results in:
- An un-commanded right cyclic load
- A collective down reaction
67
If servo transparency is encountered, the following actions should be taken immediately to relieve the feedback loads:
- Reduce the severity of the maneuver
- Follow the aircrafts natural reaction
- let the collective decrease naturally (avoid low pitch)
- Smoothly counteract the right cyclic motion
68
With regards to the bleed valve:
-A green and white flag appears on the VEMD when the bleed valve is open
- If the bleed valve fails to close, the maximum power available will be reduced
- If the bleed valve fails to open, engine surging may occur
69
Were is the longline/remote hook release button located on GLYV?
On the collective and the LONGLINE button on the Load Cell must be armed
70
The following are part of the preflight checks that must be carried out prior to a flight involving external loads:
- function check both the electrical and manual release mechanisms
- Ensure the hook lock indicators are aligned when the hook is closed after each function check
- Swing the cargo hook and swing assembly to their full extremes to verify that they do not reach the limits of the range of motion of the electrical or hydraulic hose
- Visually check all readily visible major components of the cargo hook and suspension assembly for damage and security
- Check fluid level in the master cylinder reservoir for the hydraulic release system
- Check for excess air in the lines of the hydraulic release system
71
True or false?
All of Airspan's AStars have the manual cargo hook release located on the collective?
True
72
True or false?
The baskets found on all of Airspan's Astars are made by Aero Design and are good for a maximum load of 250 lbs?
True
73
74
What should be checked on the basket as part of a preflight?
- Ensure the basket lid is fully closed and locked
- Ensure the basket is locked into position on the mounting beams by pulling up on the front of the basket
- Ensure the a/c c of g calculation incorporates any load in the basket
75
Where can you find information on how to use the Performance page on the VEMD?
Section 7 of the RFM (system description)
76
How do you change between Celsius/Fahrenheit, kilograms/pounds and meters/feet on the Performance page of the VEMD?
In CONFIG mode on the VEMD
77
Where can you find information regarding the resetting of tripped circuit breakers?
COM
78
True or false?
The resetting of fuel boost pump and/or fuel quantity indicating system circuit breakers in flight is not recommended unless authorized by the a/c manufacturer and then only when authorized by the PIC?
True
79
True or false?
If it is determined that in-flight resetting of a circuit breaker is necessary for the safe completion of a flight, then no attempt should be made to reset the circuit breaker if it trips a second time?
True
80
In regards to a power check using supplement 14 to Engine Power Checks in an AS350 B2:
- Supplement 14 (Sand Filter) shall be used for all power check and performance charts only after it has been determined that the IBF is the sole reason for the engine not passing power checks using the basic RFM
- Power checks are performed in stabilized cruise flight at or near MCP
- OAT must be reduced by 4 degrees C when plotting
81
True or false?
The engine passes the power check using the basic RFM charts?
False
82
True or false?
The engine passes the power check using Supplement 14?
True
83
True or false?
You should use the HOGE and HIGE performance charts located in Supplement 14, providing all the conditions in the FDC Aerofilter Supplement have been met?
True
