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MH60S > FLIGHT CONTROL SYSTEM > Flashcards

FLIGHT CONTROL SYSTEM Flashcards

1
Q

The flight control system can be divided into three sections:

A
  1. Mechanical control system.
  2. Flight control servo system.
  3. Automatic flight control system.
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2
Q

Flight control flow

A

aft
out
up
trim + flight controls
PAS
mixing unit
fore, aft, lateral servos + bridge assembly
swashplate assembly

The yaw inputs to the tail rotor servo are transferred from the mixing unit aft to the tail rotor quadrant through the tail rotor cables

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3
Q

The tail rotor servo is _____ actuated, but requires _____ pressure to operate the pitch change shaft, which moves the tail rotor pitch change beam, changing blade pitch angle through the pitch-change links

A

mechanically
hydraulic

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4
Q

Two ____ ____ connected to the quadrant allow cable tension to be maintained if either tail rotor cable becomes severed

A

spring cylinders

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5
Q

The pilot-assist servo assembly contains the following:

A

boost servos
SAS actuators
hydraulic (pitch and roll) trim actuators

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6
Q

The pilot-assist servos, except ___ and ____ trim, are turned on and off by pressing the SAS/BOOST pushbutton on the AFCS CONTROL panel

A

pitch
roll

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7
Q

Hydraulic pressure to the pitch and roll trim actuators is turned on and
off by the ____ pushbutton on the AFCS CONTROL

A

TRIM

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8
Q

Boost servers and roll channel include a SAS actuator that does what?

A

rate damping

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9
Q

The cyclic, collective, and pedal controls are mechanically combined in the what?

A

mixing unit

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10
Q

electrical (collective/airspeed-to-yaw) mixing is also present when what is engaged?

A

trim

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11
Q

Three major system of AFCS

A

Stability Augmentation System (SAS)
Stabilator system
Advanced Flight Control Computer (AFCC)

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12
Q

AFCS provides the following features:

A
  1. Pitch, roll, and yaw stability augmentation.
  2. Stabilator control.
  3. Cyclic, collective, and pedal trim.
  4. Pitch and roll attitude hold.
  5. Airspeed hold.
  6. Heading hold.
  7. Barometric altitude hold.
  8. Radar altitude hold.
  9. Pitch and roll hover augmentation/gust alleviation.
  10. Turn coordination.
  11. Maneuvering stability.
  12. Automatic approach to hover.
  13. Hover coupler.
  14. Automatic depart.
  15. Crew hover.
  16. Blade-fold assist.
  17. Automatic preflight check.
  18. Diagnostics (failure advisory).
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13
Q

The AFCC commands the ____ actuators and ____ actuators in all four control channels

A

SAS
Trim

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14
Q

AFCC provides

A

self-monitoring
fault isolation
failure advisory

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15
Q

AFCC two types of control

A

inner loop
outer loop

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16
Q

The inner-loop (SAS) employs what to improve dynamic helicopter stability?

A

rate damping

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17
Q

Inner loop control and rate

A

fast in response, limited in authority, and operates without movement of the flight controls.

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18
Q

Outer-loop (autopilot) provides long-term inputs by…

A

trimming the flight controls to the position required to maintain
the selected flight regime

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19
Q

Inner loop control rates

A

move flight controls through their full range of travel, or 100 percent
authority, at a limited rate of 10 percent per second

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20
Q

The stabilator system is completely independent of the other two AFCS subsystems except for common what?

A

airspeed sensors
lateral accelerometers
collective position sensor
pitch rate gyros

21
Q

STAB primary purpose

A

provide angle of attackstability

22
Q

STAB aligns with what during low speed flight?

A

rotor downwash

23
Q

STAB test is operable under what airspeed?

A

50kias

24
Q

When the STAB programs all the way down what airspeed and angle is it at?

A

42° trailing-edge down for hover and low-speed flight (below 30 KIAS)

25
Q

STAB max angle and when is it achieved in relation to flight regime?

A

10° trailing-edge up for cruise and maneuvering flight

26
Q

Four inputs are required to position the stabilator:

A
  1. Collective position.
  2. Lateral acceleration.
  3. Airspeed.
  4. Pitch rate.
27
Q

Stabilator travel is restricted to ___° if an actuator fails in the full-down position or ___° if an actuator fails in the full-up position

A

35°
30°

28
Q

Reengagement of the automatic mode after shutdown results in the automatic mode operating for how many second(s)?

A

1 second

29
Q

SAS provides increased stability by sensing _____
rate in the ____, ____, and ____axes and applying proportionate control inputs to dampen out the sensed rate

A

acceleration
pitch, roll, and yaw

30
Q

SAS1 vs SAS2: Which is analog and which is digital?

A

SAS1 is analog
SAS2 is digital and part of AFCC

31
Q

Collective Inner-Loop Actuator (CILA) is a function of which SAS and what is it needed for?

A

SAS2

  1. hover augmentation/gust alleviation
  2. turn coordination
  3. roll attitude hold
  4. altitude hold
  5. coupler functions
32
Q

With both SAS channels engaged, actuators have ___ percent control authority with each channel providing ___ percent

A

±10
±5

33
Q

AFCC will automatically disengage the affected axis of which SAS? What about the other SAS?

A

SAS2

SAS1 was much disengaged manually if it fails

34
Q

If only one SAS remains at what authority and rate will it operate?

A

±5 percent authority, but operates at twice its normal gain

35
Q

How do you disengage yaw trim with flight controls above or below a certain airspeed? What is that airspeed?

A

Above 50kias pedal microswitches and cyclic trim (simultaneously)
Below 50kias pedal microswitches only

36
Q

The autopilot maintains helicopter what during cruise flight? What does it provide above 50 KIAS?

A

pitch and roll attitude
airspeed
heading

coordinated turn feature

37
Q

At airspeeds less than 50kias autopilot uses what hold feature? Above 50kias and below 30° AOB what hold feature is enabled?

A

attitude
airspeed

38
Q

Four way trim pitch rate

A

5° per second

39
Q

Four way trim lateral rate

A

6° per second

40
Q

Heading hold is disengaged with…

A

weight on wheels

41
Q

HDG TRIM: Below 50 KIAS, the aircraft is slewed at ___ per second. Above 50 KIAS, actuation of the switch for less than 1 second provides a ___ heading change and actuation for greater than 1 second provides a ___ per second coordinated turn

A

3°
1°
1°

42
Q

The heading hold is reengaged, following a turn, when the following conditions are maintained for 2 seconds:

A
  1. Aircraft roll attitude is within 2° of wings level.
  2. Yaw rate is less than 2° per second.
43
Q

During altitude hold the AFCC commands both the collective SAS actuator and the collective trim actuator to maintain the reference altitude, but it monitors and will not exceed what parameter?

A

Continuous Torque limits (106% and 120%)

44
Q

RAD ALT altitude range

A

0-5000ft AGL (pitch and roll angles up to 45 degrees)

45
Q

Automatic turn coordination is engaged and heading hold disengaged when roll attitude is greater than 1° and any of the following conditions exists:

A
  1. Lateral cyclic displacement is greater than 3 percent.
  2. Cyclic TRIM REL button is pressed.
  3. Roll attitude exceeds 2.5° bank angle using the four-way TRIM switch.
  4. Collective HDG TRIM switch is toggled for more than 1 second.
46
Q

During an automatic approach, the deceleration rate can
be varied up to…

A

±1 knot per second using the four-way TRIM switch

47
Q

During a coupled hover, the AFCC monitors dual-engine torque and will stop increasing collective if torque reaches or exceeds

A

116 percent

48
Q

The AFCC automatic preflight check is initiated, using the SAS 1 pushbutton, when the following conditions are present:

A
  1. Weight on wheels.
  2. Rotor brake on.
  3. Engine torques below 10 percent.
  4. Both EGI attitudes valid.
  5. SAS 1 pushbutton engaged (after AFCC on for at least 20 seconds).

The automatic preflight takes approximately 10 seconds to complete.

If the test is interrupted the AFCC CMPTR PWR/RESET button must be cycled and 20 seconds must elapse before the test will initiate

MH60S (11 decks)

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