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MH-60R HAC HSM-50 > NATOPS Chapter 2: AFCS HSM-50 > Flashcards

NATOPS Chapter 2: AFCS HSM-50 Flashcards

1
Q

What does SAS do?

What is the difference between SAS 1 and 2?

What percent control do they have?

A

Senses acceleration and applies control to reduce the rate.

SAS 1 is Analog, SAS 2 is Digital. They are identical except for the hover aug/ gust alleviation and alt hold/ hover coupler provided by SAS 2.

They have 10% authority With each providing 5%.

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2
Q

SAS 2 commands the collective inner-loop actuator by operating with what engaged?

A

RADALT, BARALT, APP/HVR and DEPART MODES ENGAGED.

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3
Q

Which SAS must be manually disengaged by the pilot if it has failed?

A

SAS 1

SAS 2 will be turned off by the AFCC.

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4
Q

Which trim servos are electric?

Hydraulic?

A

Yaw, collective

Pitch, roll

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5
Q

Trim is limited in movement by _________

A

10% percent per second

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6
Q

To disengage yaw trim above 50 kias the pilot must _________

Below 50 kias?

A

Push the cyclic button and the trim micro switches

Just the pedal micro switches

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7
Q

Auto pilot does what?

A

Maintains pitch and roll attitude, airspeed, heading during cruise

And

Provides a coordinated turn above 50 kias.

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8
Q

Attitude hold is engaged below _______, and using the 4-way trim switch will adjust pitch attitude at a rate of _________.

A

50 kias

5* per second

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9
Q

Airspeed hold is engaged ___________. The 4-way trim switch will adjust the airspeed by ___________. The lateral trim roll rate is _________. It resets to __________ when you ___________.

A

Above 50 KIAS and AOB less than 30*

6 KIAS per second

6* per second

Wings level

Accelerate through 50 kias

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10
Q

Heading hold is slewed at ____ below 50 kias and _______ above 50 kias.

A

3* per second

1* per click or 1* per second

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11
Q

Heading hold is re-engaged when what 2 conditions are met?

A

Roll attitude is within 2* of wings level

Yaw rate is less than 2* per second

Disengaged by WOW switch.

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12
Q

Altitude hold: The AFCC commands both the ____ and the ____ to maintain the reference altitude.

It will stop increasing power if torque hits _______ above 80 kias or ________ below 80 kias.

A

Collective SAS actuator and collective trim actuator

106%

120%

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13
Q

Altitude that RADALT will work?

A

0 to 5000ft AGL.

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14
Q

RADALT and BAR ALT require what push buttons to be engaged?

A

SAS 2, TRIM, and AUTOPILOT

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15
Q

RADALT climb and descent rates?

A

1000 ft per minute

200 ft per minute

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16
Q

What does hover augmentation/gust alleviation do?

A

Improves aircraft stability at low airspeeds by using attitude retention, longitudinal acceleration, and lateral acceleration to eliminate drift.

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17
Q

Turn coordination is provided ______. It will engage when _________ and any of what 3 conditions exist?

A

Above 50 KIAS

Roll attitude is greater than 1*

And either:

1) lateral cyclic displacement is greater than 3%
2) Cyclic TRIM REL is pressed
3) roll attitude is more than 2.5* using 4-way trim

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18
Q

The purpose of Maneuvering stability is to __________. It is provided by _________ between _______.

The ___________ push button must be engaged for it to function.

A

Increase pilot effort to maintain pitch rate at greater than 30* AOB

Pushing the cyclic forward by 1% for every 1.5* AOB. Between 30* and 75* AOB.

Autopilot

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19
Q

Automatic approach assumes _______ when engaged and again at ________.

A

Wings level

80 KIAS

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20
Q

The 4-way trim switch changes the deceleration rate by ________ during the automatic approach.

It will reset the deceleration profile at _____________. Pressing the ________ will reset the profile.

A

+- 1kt per second, 2 seconds for a full knot.

40KGS

TRIM REL

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21
Q

Automatic approach profile numbers?

ON (above 40KGS and below 40KGS)

Below-

Above-

A

Above 40: 2.5kt/sec 215 ft/min

Below 40: 1.5kt/sec 130 ft/min

Below profile: 2.5 kt/sec w/RADALT hold

Above profile: 360 ft/min w/airspeed hold

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22
Q

What is the Warning associated with an automatic approach?

A

If auto approach is turned on while in a trimmed turn it will spiral downward past the selected altitude and crash.

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23
Q

Hover coupler speeds can be varied by ________ with the 4-way trim switch.

Hover coupler will automatically engage after an automatic approach when __________ and manually when within ________

A

+- 10

Within 2 ft and 1KGS
Or
5KGS

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24
Q

The hover coupler will stop increasing the _______ at ________.

A

Collective torque

116%

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25
Q

During couple hover if winds are greater than 50KIAS and the cyclic trim is depressed the ____________

A

Heading hold will be disabled. This could cause rapid deviation from the desired helicopter heading.

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26
Q

Automatic depart, if not interrupted, will reach _____ and ______.

A

150ft and 120kias

27
Q

Automatic depart assumes __________ at _______ if bank angle is ________.

If bank angle is greater than ____.

Automatic departure will limit power at __________.

A

Wings level attitude, 50KIAS

Less than 5*

5* it will maintain a coordinated turn.

106 and 120% dependent on airspeed.

28
Q

Automatic departure profile?

A

240ft/min climb
3kt/sec below 85 kts

1kt/sec above 100 kts

29
Q

Crew hover control authority?

A

+- 5 KGS

30
Q

Cable angle is decoupled from the AFCS for ____ when dome raising/lowering is stopped or started in the water.

Disengaged for ____ if flight control trim inputs are made

A

9 seconds

20 seconds (must be manually controlled)

31
Q

Scale on the cable angle display is _________. The rings are at _____ and ______.

A

2 degrees per tick

  1. 25 degrees
    8.5 degrees
32
Q

CABLE ANGLE AT LIMIT caution appears when ___.

A

cable angle has exceeded 7.5 degrees total deflection.

33
Q

The helicopter will default to HVR mode at _________ during cable angle hover.

If either axis is failed it must be _________.

What should you not continue if both axis are failed?

A

27+- 12 ft water depth.

Manually controlled

Dipping operations.

34
Q

What is required for Cable Angle Hover Mode?

A

KADADA

KGS of +-5

Altitude hold w/in 10 ft.

Dome wet indication.

AFCS DEGRADED not illuminated

DPRT or CREW HVR not engaged

AUTO PILOT engaged

35
Q

The ______ are inoperative when CABLE ANGLE HOVER is engaged.

A

LONG VEL and LAT VEL potentiometers.

36
Q

Cable angle takes ______ to come up with a solution.

A

25 seconds. Do not make inputs during this time.

37
Q

Cable angle hover will not _________ with ____________ engaged.

A

Disengage

Cable angle override on. (Must be manually disengaged)

38
Q

To conduct AFCS preflight checks you need:

BREWS

A 
Both EGIs attitudes valid
Rotor brake ON
Engine torque below 10%
WOW
SAS 1 ON (AFCC must be on for at least 20seconds)
39
Q

If one of the SAS channels fail, what operable control authority is the operable channel limited to?

A

+-5 percent authority, but it operates at twice the normal gain to compensate for the failed SAS channel

40
Q

When does the SAS caution appear?

A

Whenever SAS 1 and SAS 2 lose electrical power or when hyd pressure is lost to the actuators.

41
Q

Is Trim an outer-loop functions, or inner-loop?

A

Outer-loop

42
Q

Cable angle is used to keep the cable ____ to the water.

A

Perpendicular

43
Q

What does the SUBM OVRD button do?

A

Provides override capability of the 27+-12 ft submerge requirement to engage cable angle hover mode. (in case you’re dipping in shallow water or don’t have the dome wet indication.)

44
Q

How do you initiate the automatic preflight check?

A

by pressing the SAS 1 pushbutton. Takes approx 10 seconds to complete.

45
Q

3 major subsystems

A

SAS
AFCC
Stab

46
Q

19 Functions of the AFCS

A

5 holds
5 hovers
3 -ations
MTDABS

Attitude hold
Airspeed hold
BARALT hold
RADALT hold
Heading hold

Automatic approach
Coupled hover
Automatic departure
Cable angle hover
Crew hover

Hover augmentation/gust alleviation
Turn coordination
Stability augmentation (SAS)

Maneuvering Stability
Trim
Diagnostics
Auto Preflight Checks
Blade Fold
Stabilator

47
Q

2 types of AFCC control

A
  1. Inner loop (SAS)

2. Outer loop (autopilot)

48
Q

Inner loop is

A

fast in response, limited in authority, and does not move the flight controls

49
Q

Outer loop provides

A

Long term input by moving flight controls through their full range of travel (100% authority) at a limited rate of 10% a second

50
Q

ATT caution cube indicates loss of pitch or roll attitude or

A

3 deg miscompare between EGIs

51
Q

AFCC uses the ___ to choose between the ___ for the best source of power

A

Voltage sensor relay

AC primary buses

52
Q

4 Inputs to the Stab

A

Collective Position
Lateral Acceleartion
Airspeed
Pitch Rate

53
Q

How is the stab positioned? What buses power its movement?

A

2 electrical jackscrews acting in series
Each jackscrew provides 1/2 the input
DC Essential & No 1 DC Primary

54
Q

Stab movement if it fails full down/up?

A

35 degrees if fails full down, 30 if full up

55
Q

Primary purpose of the stabilator

A

To eliminate undesirable nose up attitudes caused by rotor downwash on the horizontal stab during transition to a hover and low speed flight

56
Q

When is the TEST pushbutton for the stab operable?

A

Below 50 KIAS

57
Q

Range of motion for the stab

A

42* trailing edge down for hover/low speed flight (below 30 KIAS) to 10* trailing edge up for cruise and maneuvering flight

58
Q

AFCS is what type of system?

A

Electrohydromechanical

59
Q

What must be done during the auto depart profile if dome at trail?

A

Profile must be overridden (double depart or cyclic trim release) to prevent exceeding 70 KIAS (TA trail/below trail airspeed limit)

60
Q

What happens to CABLE ANGLE if both lat/long axes fail?

What should you do?

A

CABLE ANGLE HOVER will be disengaged/blocked (CABLE ANGLE INACTIVE advisory). Reverts to normal hover mode and pots are active

Continued dipping ops not recommended

61
Q

Cable angle hover performance is primarily affected by __________

Additional inputs?

A

Cable angle sensors in ALFS
Positioning of SO LAT/LONG pots

Pitch/roll/horizontal ground speed signals from EGI
Horizontal and vertical acceleration of AFCS accelerometers
Pitch/roll signals from AFCS rate gyros
Pitch/Roll/Collective signals from SAS/Trim servos
RAD ALT altitude

62
Q

Cable angle hover mode disengagement occurs:

A

Dome raised through 27+-12 ft (if subm ovrd not engaged)

Manually disengaged (pushbutton)

Difference between radar alt and selected alt greater than 10 ft

Both LAT/LONG sensor channels fail

HVR pushbutton manually disengaged

63
Q

AFCS NOT IN ALT CONTROL Caution Cause/Corrective Action

A

Cause: RADALT invalid/disengaged (AFCS not controlling altitude)

Maintain 70’ AGL hover (cross check RADALT/BARALT)

Recover TA

Depart

64
Q

If both LAT and LONG cubes appear what should you do?

A

Control aircraft manually (pots are active)

Continued dipping ops not recommended (recover dome)

MH-60R HAC HSM-50 (73 decks)

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