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1
Q

The engine in FFKA is an:

A

Arriel 2B1

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2
Q

True or false?
FFKA’s engine is controlled by a FADEC?

A

True

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3
Q

Maximum internal gross weight or FFKA is:

A

5225 lbs

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4
Q

The increased maximum gross weight of FFKA is possible because the a/c is equipped with:

A
  • High skid gear
  • Dual Hydraulics
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5
Q

Maximum all up weight with an external load is ___ lbs and the maximum authorized swing load weight is ___ lbs.

A

6173, 3086

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6
Q

True or false?
Flying with an external load is prohibited if the a/c internal gross weight exceeds 4961 lbs?

A

True

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7
Q

True or false?
Just like a BA and a B2, the lateral C of G limits remain the same for all internal gross weights for FFKA?

A

False

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8
Q

The Vne with the pilots door removed is:

A

N/A. This configuration is prohibited.

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9
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

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10
Q

The FLI maximum transient rating is:

A

10.4 for 5 seconds maximum

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11
Q

The maximum continuous rating for torque is:

A

92.7%

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12
Q

The maximum torque takeoff rating is ___ and is limited to an airspeed or ___. There ___ time limit for the use of the takeoff torque range.

A

100%, 40 kts or less, is no

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13
Q

The maximum transient torque limitation is:

A

104% for 5 seconds

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14
Q

The delta Ng takeoff rating range is ___ and is limited to ___ continuous minutes.

A

-4 to 0%, 5

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15
Q

The maximum transient delta Ng is:

A

+1 for 5 seconds

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16
Q

The T4 takeoff rating range is:

A

849 to 915 degrees C for 5 minutes

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17
Q

True or false?
Use of heating and demisting is forbidden above either the Ng or T4 maximum continuous rating. This restriction does not apply to the torque takeoff rating alone?

A

True

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18
Q

True or false?
Prior to engine start, the SERVO TEST switch shall be actuated and the SERVO light should go out on the CWP?

A

True

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19
Q

Battery voltage must be ___ and the bleed valve flag should ___ prior to starting the engine.

A

> 22 V, be visible

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20
Q

True or false?
Prior to engine start, the pedals shall be checked for freedom of control and then returned to neutral.

A

False

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21
Q

True or false?
Prior to engine start, the CWP must be checked to ensure there are no GOV lights?

A

True

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22
Q

True or false?
If the start-up procedure needs to be aborted, the starting selector must be switched off?

A

True

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23
Q

True or false?
Illumination of either the yellow or red GOV light during the start procedure calls for the start to be aborted?

A

True

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24
Q

True or false?
With the yaw servo hydraulic switch (collective mounted) in the off position a yellow HYD1 light will be displayed in the CWP?

A

False

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25
Q

True or false?
Modification 07-4622 (yaw servo test light modification on dual hydraulic helicopters) has been applied to FFKA?

A

True

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26
Q

True or false?
Neither the yaw servo hydraulic switch nor the ACCU TST switch is to be actuated during the run up hydraulic checks?

A

True

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27
Q

In FFKA, how do you ensure that the yaw load compensator is functioning properly?

A
  • Upon engine and rotor shutdown, the RIGHT pedal should move forward on its own or with a little applied force
  • Maintenance action is required if this is not the case
  • Upon engine and rotor shutdown, the pedals can be re-centered and remain centered after engaging the HYD TEST switch for 2 seconds
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28
Q

How do you perform a hydraulic pressure isolation check in FFKA?

A

There is no hydraulic pressure isolation check on the AS350 B3 w/ dual hydraulics.

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29
Q

True or false?
The FUEL PUMP shall remain on for all normal operations?

A

False

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30
Q

True or false?
The cranking procedure can be carried out after an aborted start or during maintenance operations. The FUEL PUMP shall be on and the crank button depressed for 20 seconds maximum?

A

True

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31
Q

Explain the starter limits for FFKA:

A
  • Starter limits are: 30 sec ON, 60 sec OFF, 30 sec ON, 60 sec ON, 30 sec ON, 30 min OFF
  • Crank time limit is 20 seconds
  • In case of a failed engine start, return the engine starting selector to OFF, wait for at least 60 seconds then perform an engine crank before next start attempt
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32
Q

True or false?
The 30 second N1 stabilization period must be adhered to every time the twist grip is positioned to FLIGHT?

A

False

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33
Q

True or false?
The recommended takeoff profile and height velocity diagram for FFKA are both amended from the basic RFM due to the allowance for increased internal gross weight?

34
Q

Vy (best rate of climb speed) for the AS350 B3 is ___ at 0 Hp - 1 kt/1000ft:

35
Q

True or false?
When the rotors have stopped after engine shutdown, the ACCU TST button shall be depressed for 2 seconds to depressurize the tail rotor accumulator and yaw load compensator and reduce wear on the laminated half bearings?

36
Q

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?

37
Q

True or false?
The audio warnings generated through the ICS by FFKA are identical to those in GLYV?

38
Q

Recommended airspeed during autorotation is:

39
Q

If attempting an engine relight after a flameout, what should be done?

A
  • Starting selector must be placed in the off position prior to attempting the restart
  • The fuel pump shall be on
  • The starting selector shall be reinstated to the ON position
  • At least 1000’ are required to successfully restart the engine after a flameout
40
Q

If you experience a loss of tail rotor control in flight (jamming of pedals or loss of effectiveness of the pedals), what should be done?

A
  • Landing will be made easier with a RH wind component
  • If you allow your airspeed to drop below 20 kts, a go-around may be impossible
  • The yaw servo hydraulic switch (collective mounted) shall be turned OFF
  • The ACCU TST button shall be pressed on for two seconds to depressurize the load compensator
  • A shallow approach with left sideslip is recommended
41
Q

True or false?
If you experience a complete loss of tail rotor thrust while hovering in ground effect, the twist grip should immediately be positioned to IDLE and the collective increased to cushion touch-down?

42
Q

In cruise flight, the left pedal deflects nearly full scale on its own (‘runaway yaw servo’ or yaw servo slide-valve seizure), you should elect to:

A
  • Reduce airspeed to 40 to 60 kts
  • Turn the collective mounted yaw servo hydraulic switch OFF
43
Q

True or false?
If the HYD2 and SERVO lights illuminate in flight and stiffness is felt in the pedals, the ACCU TST switch should be turned ON to depressurize the yaw load compensator?

44
Q

If the SERVO light and either the HYD1 or HYD2 lights illuminate in flight the pilot should:

A
  • Keep the a/c in a more or less level attitude and maintain angle of bank less than 30 degrees
  • Avoid abrupt maneuvers
  • Maintain IAS below 110 kts
  • Land as soon as practical
45
Q

Illumination of the LIMIT light could occur in conjunction with the following:

A
  • Maneuvering near Vne
  • Steep or aggressive maneuvers
  • LH hydraulic circuit failure
  • Moderate to severe turbulence
46
Q

True or false?
If the LIMIT light illuminates in flight, the pilot should reduce the load factor by slowing down and reducing power?

47
Q

True or false?
If electrical power is switched off and on in flight (via either the EMER.SW switch or BAT-EXT POWER switch) then a yellow GOV light will illuminate on the CWP until the next complete shutdown?

48
Q

If you lose both VEMD screens due to a complete electrical failure, you elect to ___ and perform a ___. The maximum power setting is determined by the formula:

A

Land as soon as practical, no hover landing
100 kts - 2 kts/1000 ft

49
Q

True or false?
The EBCAU provides engine governing following a complete FADEC failure?

50
Q

True or false?
If you lose the Nf indicator in flight, the EBCAU may not be available?

51
Q

True or false?
The actual Nf value can be displayed on the bottom of the FLI or 3-data screen by pressing ‘SELECT’ and then ‘+’ on the VEMD?

52
Q

The engine oil temperature exceeds 115C in flight. You elect to:

A
  • Set airspeed to 80 kts
  • Land as soon as practical if the engine oil temperature drops to within limits
  • Land as soon as possible if the engine oil temperature remains too high
53
Q

True or false?
The ENG P light and engine oil pressure gauge receive their data from different sensors and can thus be treated as separate indicating systems?

54
Q

If the ENG FIRE light illuminates during start-up, you should:

A
  • The start selector, emergency fuel valve and booster pump shall be shut off
  • CRANK the engine for 10 seconds
  • Engage the MASTER CUTOFF switch
  • APPLY rotor brake and fight fire from outside the aircraft
55
Q

What are some points regarding the main gearbox (MGB) emergencies in the AS350 B3?

A
  • There are three lights on the CWP
  • Illumination of any MGB light calls for the pilot to land as soon as possible
  • Minimum power required to fly the AS350 B3 is achieved at 65 kts (altitude depending)
56
Q

Illumination of the FUEL light means:

A
  • Fuel quantity is below 106 lbs
  • Approximately 15 minutes of flight time remains at MCP
  • Large attitude changes shall be avoided
  • land as soon as possible
57
Q

The FUEL P light comes on in flight, the pilot should:

A
  • Reduce power
  • Turn the booster pump ON
  • Conduct a low power approach and landing
  • Land as soon as possible
58
Q

The FUEL FILT light comes on in flight, the pilot should:

A
  • Reduce power
  • If the FUEL FILT light remains on, land as soon as possible
  • If the FUEL FILT light goes out, establish flight at reduced power and land as soon as practicable
  • If Ng oscillations occur, land immediately
59
Q

The A/F FUEL FILTER light illuminates in flight, the pilot should:

A
  • Reduce power
  • If the A/F FUEL FILTER light remains on, land as soon as possible
  • If the A/F FUEL FILTER light goes out, establish flight at a reduced power and land as soon as practicable
  • If the FUEL FILT light illuminates as well, land as soon as possible
  • If Ng oscillations occur, land immediately
60
Q

An erroneous collective anticipator signal could cause abnormally low Nr and Nf (Nr may go as low as 360 rpm). What are some considerations when dealing with this malfunction?

A
  • The yellow GOV light may come on depending on how low Nr goes
  • Tail rotor control margins are reduced due to decreased tail rotor efficiency at lower Nr
  • Hovering should be avoided, particularly with a left crosswind
  • A no hover landing should be made as soon as practicable
61
Q

True or false?
The ‘END’ timer on the VEMD displays time remaining until all usable fuel is consumed. This time varies with the fuel flow (‘FF’) which is dependent on your power setting, cruise altitude, OAT etc.?

62
Q

Where is the longline/remote hook release button located on FFKA?

A

On the collective and the LONGLINE button on the Load Cell must be armed

63
Q

Where is the cargo hook (belly hook) release button located on FFKA?

A

On the top right of the cyclic and the SLING switch must be armed

64
Q

True or false?
When the Cargo Swing with the manual hydraulic release is installed, the manual release should be used first to release an external load in the event of a snagged load or engine failure. If the manual release option fails, NEXT try the electrical release?

65
Q

Where in the RFM do you find the longline attachment ring size restrictions for the cargo hook?

A

Section 9, Operational equipment

66
Q

True or false?
Maximum gross weight for HIGE and HOGE must be reduced by 66 lbs due to the LH and RH cargo pods (Squirrel Cheeks) installed on FFKA?

67
Q

What are some points in regards to the FDC Aerofilter installed on FFKA:

A

-Operation of the Alternate Air Doors in falling and/or blowing snow is prohibited
- Takeoff with the LOW INLET PRESSURE light illuminated is prohibited
- If the LOW INLET PRESSURE light illuminates while flying in falling snow and remains lit even after reducing power, then land as soon as possible

68
Q

With the battery power on, how many lights should illuminate on the caution and warning panel of FFKA?

69
Q

In regards to the hydraulic system on FFKA what are some points:

A
  • The LH hydraulic circuit is powered by a pump mounted on the front of the MGB
  • The RH hydraulic circuit is powered by a belt driven pump at the MGB power input
  • Depending in which circuit fails, either a yellow HYD1 light or a yellow HYD2 light will illuminate if pressure drops below 20 +/- 2 bar
  • Only the RH circuit powers the yaw servo and associated accumulator and load compensator
  • The SERVO caution light warns of a servo distributor seizure
  • The LIMIT caution light warns of a maximum lateral servo load being reached
70
Q

Following an engine start-up and with the twist grip in the FLIGHT position, the following should be performed prior to increasing collective:

A
  • Check Nr in lower normal operating range
  • Check engine oil pressure and temperature
  • Wait for 30 seconds once the N1 has stabilized
  • Check electrical system voltage and current
  • Check CWP for no lights
71
Q

If the hydraulic pressure in the LH circuit drops below 20 bar in flight, you could expect the following indications:

A
  • Illumination of the HYD1 light
  • Illumination of the SERVO light
  • Illumination of the LIMIT light
72
Q

If the hydraulic pressure in the RH circuit drops below 20 bar in flight, you could expect the following indications:

A
  • Illumination of the HYD2 light
  • Illumination of the SERVO light
  • Stiffness in the pedals
73
Q

With the EMER.SW switch in the OFF position, all DC power is switched off except for the following:

A
  • Nr/Nf guage
  • Crew adjustable spot light
  • Start- Stop engine switch
74
Q

You are flying along and smoke starts to billow out of the instrument panel. You elect to:

A
  • Slow down, start down, left pedal crab, ventilate the cockpit
  • Brief passengers not to use the fire extinguisher, issue mayday, press ELT
  • Engage the MASTER CUTOFF switch
  • Shut off the BAT-EXT POWER and DIRECT BATTERY switches
  • Shut off the GENERATOR and AVIANOCS MASTER switches
  • Land as soon as possible if the smoke does not clear
75
Q

Regards to loss of Ng, torque and T4 parameters on the VEMD:

A
  • The FLI is automatically replaced by the 3-data page and a failure message is displayed
  • The failed parameters displayed will be yellow instead of white
  • For an Ng/deltaNg indication failure, T4 limits displayed will be starting parameters
  • For an Ng/deltaNg indication failure, the T4 limit becomes 810 degrees C
  • For a delta Ng and torquemeter indication failure, comply with the numeric Ng limits displayed in section 3.5, page 5 of the RFM and replace the delta Ng = -4 limit by a T4 limit of 810 degrees C
  • For a T4 indication failure, heating and demisting shall be shutoff
  • Land as soon as practicable
76
Q

What should you do if a red GOV light illuminates in flight:

A
  • The yellow GOV light will illuminate when emergency mode engages
  • Abrupt power changes must be avoided
  • A slow, powered approach must be made avoiding a steep angle
  • You may lose delta Ng and torque parameters on the VEMD
77
Q

What are some points in regards to the bleed valve:

A
  • A green and white flag may appear 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 blee valve fails to open, engine surging may occur
  • If the bleed valve fails, the yellow GOV light will illuminate
78
Q

As part of the daily check for the manual cargo hook release on FFKA, you should check:

A
  • With the release lever pulled all the way in, at least some of the green ring on the push rod must be visible
  • Hydraulic fluid must be visible over the baffle surface in the master cylinder reservoir
79
Q

What are some points in regards to power checks in an AS350 B3 like FFKA?

A
  • Power checks are performed in stabilized flight at or near MCP with heating and demisting off
  • The power check page is accessed on the VEMD by using the collective mounted toggle switch
  • Turbulence can cause invalid power check results
  • If the engine passes the power check torque and T4 margins, the a/c shall be operated in accordance with the basic RFM performance data
  • The HIGE and HOGE correction factors in the FDC RFM supplement need not be applied provided that the engine passes the power check using the VEMD without applying corrections to the torque and T4 margins
80
Q

Provided the helicopter is passing its power checks, which performance charts should be consulted to obtain HOGE data for external load operations?

AS350B3 DH (4 decks)

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