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C-5 Eval Guide > Flight Controls > Flashcards

Flight Controls Flashcards

1
Q

How are the ailerons powered?

A

 Each aileron is powered by two hydraulic actuators (utilizing two separate hydraulic systems) served by a dual hydraulic servo control assembly.
 The left aileron is powered by hydraulic systems 1 & 2, the right aileron is powered by systems 2 & 4.

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2
Q

If the pilot control wheel jams and he cannot roll the aircraft, what must be done?

A

 The sheer pin between the two control wheels must be sheared allowing use of the right aileron. Should a jam occur in either system, an excessive control wheel force will shear both interconnect rod pins and permit use of the operating aileron

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3
Q

What does a SYSTEM 1 Light for the left aileron on the overhead panel indicate?

A

There is no hydraulic pressure from system #1 to the left aileron

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4
Q

What does an AILERON POWER Advisory indicate?

A

Hydraulic pressure has been lost (< 1450 ± 250 PSI) to either actuator in either aileron

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5
Q

Which spoilers are flight spoilers and which are ground only?

A

The 5 outboard spoilers are flight spoilers and the inboard 4 spoilers are for ground use only

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6
Q

How many hydraulic systems power each spoiler?

A

Two: Each flight spoiler panel is powered by a tandem hydraulic actuator which utilizes hydraulic pressure from two separate hydraulic systems.

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7
Q

What does the SPOILER POWER Advisory indicate?

A

Comes on when the pressure of either hydraulic system in any spoiler actuator drops below a set value.

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8
Q

What does the spoiler ratio shifter switch do?

A

 In AUTO, when flaps are up, spoiler deflection is limited to 22.5 degrees. When flaps are extended beyond 80%, spoiler deflection is 60 degrees.
 The ratio shifter allows you to select full (FLAPS DOWN) or partial (FLAPS UP) spoiler deflection regardless of flap setting.
 It is used if the ratio shifter actuator fails or for partial flap crosswind landings.
 It has three positions:
 Auto (spoilers deflect 22.5 degrees with flaps <80%, 60 degrees with flaps =>80%)
 Flaps Up (max spoiler deflection is 22.5 degrees)
 Flaps Down (max spoiler deflection is 60 degrees)

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9
Q

What is max deflection of the flight spoilers when flaps are UP?

A

22.5°

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10
Q

What is max deflection of the flight spoilers, using control wheel inputs when flaps are extended past 80%?

A

60°

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11
Q

When the flaps are extended past approximately 80%, the ratio shifter automatically extends all flight spoilers to?

A

3°

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12
Q

Full elevator authority is?

A

25 degrees up and 15 degrees down

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13
Q

Due to interconnecting rods and elevator cable system, both pilot and copilot have control of the inboard and outboard elevators. Should an elevator jam occur, in one elevator surface or a pair of elevator surfaces, how do the pilots regain control of the elevators?

A

A 180 lb force on the control wheel will shear both interconnect rod pins, permitting use of the operating elevators.

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14
Q

Which hydraulic systems power the elevators?

A

 Systems 2 & 3 power the inboard elevators

 Systems 1 & 3 power the outboard elevators

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15
Q

How is normal pitch trim powered? Controlled?

A

2 hydraulic system powers nut drive motor (faster); controlled by trim switches on yoke or manual pitch trim levers through a cable system

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16
Q

How is alternate pitch trim powered? Controlled?

A

1 hydraulic system powers screw drive motor (slow); controlled by alternate pitch trim switches (center console) or autopilot

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17
Q

What is NORMAL pitch trim authority, condition and rate using NORMAL pitch trim switches?

A
  1. 5° nose DOWN, 6.0° nose UP; flaps UP or AR door closed; 0.3°/sec
  2. 8° nose DOWN, 12.0° nose UP; flaps not UP or AR door open; 0.5°/sec
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18
Q

What is ALTERNATE pitch trim authority, condition and rate using NORMAL pitch trim switches?

A
  1. 5° nose DOWN, 6.0° nose UP; flaps UP or AR door closed; 0.15°/sec
  2. 8° nose DOWN, 12.0° nose UP; flaps not UP or AR door open; 0.15°/sec
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19
Q

In flight, the manual pitch trim levers can move the horizontal stab to a max of ___ down or ___up (mechanical limits)?

A

4.11°; 12.11°

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20
Q

In flight, do not trim the horizontal stab more than ___ nose down (except for AR) or it may result in an uncontrollable pitch down.

A

1.5°

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21
Q

What does the ELEVATOR FEEL FAIL Caution indicate?

A

 20% difference between the outputs of the elevator variable feel unit assembly
 Note that annunciation of the CWA not accompanied by the illumination of one of the two VFU system lights on the overhead panel indicates a fault not basically hydraulically oriented. Such a fault may be intermittent, and on correction the CWA will extinguish.

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22
Q

What is full rudder authority?

A

35°

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23
Q

Which hydraulic systems power the rudder?

A

 Upper rudder – Systems 1 & 3

 Lower rudder – Systems 2 & 3

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24
Q

What does the Rudder Limiter do?

A

 Prevent excessive vertical stabilizer loads resulting from excessive rudder deflection at high airspeeds
 Limits deflection as a function of airspeed and Mach and is continuously variable
 Below approx. 150 KCAS, the actuator is at one extreme position and the quadrant may rotate the full amount in either direction to provide full rudder deflection of 35 degrees either side of center
 When airspeed reaches approx. 150 KCAS, the VIAs provide a signal through the RIUs to the actuator causing it to schedule rudder limiter position with airspeed
 As dynamic pressure is increased, the actuator further reduces rudder quadrant rotation limiting rudder authority to a maximum of 4 degrees
 The rudder is also limited to 4 degrees at greater than Mach 0.77
 As airspeed decreases, the reverse actions occur.

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25
What does the rudder limiter switch do?
 In the AUTO position, the rudder limiter actuator automatically moves in response to VIA signals to control rudder authority  MIN Q position is used to override the VIA signals and cause the actuator to move to the low-speed stop permitting full rudder control at any airspeed
26
When airspeed reaches approximately _____ KCAS, the VIAs provide a signal through the RIUs to the actuator causing it to schedule rudder limiter position with airspeed
150
27
As dynamic pressure is increased, the rudder limiter actuator further reduces rudder quadrant rotation limiting rudder authority to a maximum of _____degrees. The rudder is also limited to ____ degrees at greater than Mach 0.77.
4; 4
28
What is the maximum flight control travel authority through the flight aug system?
 Elevator +/- 10°  Ailerons +/- 15°  Rudder +/- 20°
29
The yaw augmentation system receives hydraulic pressure from systems _____, ____ and _____.
1; 2; 3
30
How much additional rudder trim does the Yaw Aug Manual Trim system (emergency rudder control) provide?
+/- 20° (1° per second)
31
The lateral augmentation system receives hydraulic pressure from hydraulic systems _____, ____ and _____.
1; 2; 4
32
The pitch augmentation system receives hydraulic pressure from hydraulic systems _____ and _____.
2; 3
33
What is the ALDCS and what does it do for us?
The Active Lift Distribution Control Subsystem (ALDCS) is installed to increase fatigue life of the airplane wing by reducing maneuver and gust wing loads.
34
How does the ALDCS system work?
 Two independent AFCS partitions are provided to control ALDCS operation: AFCS partition No. 1 in VIA/AIU No. 1 (the pilot partition) and AFCS partition No. 2 in VIA/AIU No. 2 (the copilot partition)  The ALDCS utilizes control inputs to the ailerons and inboard elevators, through the pitch and lateral flight augmentation system, as a function of pitch rate, vertical acceleration at one fuselage location and four wing locations, and a pitch control column input.  It uses the flight aug system to control the inboard elevators and ailerons to move the flight controls to reduce stress on the wing during flight.  If airspeed is above 350 KCAS or 0.83M, it will move the ailerons 6 degrees wing down (6 degree uprig) and turn on the 6 DEGREE UPRIG Advisory panel.  When the airspeed is reduced below 350 KCAS or Mach 0.825, the 6-degree uprig command is removed, the 6 DEGREE UPRIG advisory message is removed, and the automatic positioning feature is reactivated.
35
If the airspeed exceeds ____ KCAS or 0.825 mach with the ALDCS engaged, the ALDCS positions the ailerons to a fixed 6 degrees wing down (UPRIG) and the 6 DEGREE UPRIG advisory message appears on the CWA display.
350
36
Is the PACS pitch system working with the autopilot engaged normally?
No, PACS functionality is only available in CWS, or when the autopilot LAT or PITCH axis is selected to OFF. In all other modes, the applicable autopilot axis is disengaged.
37
What is the PACS system?
 The Pilot Assist Cable Servo (PACS) provides assistance in overcoming the control wheel breakout force in roll and pitch.  Consists of two electromechanical torque motors, one attached to the pilot rear aileron quadrant (roll) and the other attached to the pilot rear elevator quadrant (pitch).  Electrical sensors in each control wheel detect the initial pilot effort in either roll or pitch and send a signal to the respective roll or pitch PACS.  PACS control for both roll and pitch is provided by the same VIA/AIU selected for AFCS control; VIA/AIU No. 1 with PLT CNTL (pilot control) selected and VIA/AIU No. 2 with COPLT CNTL (copilot control) selected.
38
PACS Roll reduces breakout force by approximately ____%.
40
39
PACS Roll breakout force is approximately _____ pounds with PACS on.
8.1
40
PACS Pitch reduces breakout force by approximately ____%.
35
41
PACS Pitch breakout force is approximately _____ pounds with PACS on.
12
42
The basic AP roll axis modes are the ____ mode and ____ mode.
Heading hold; Roll attitude
43
Basic AP pitch axis modes are the ____ mode and ____ mode.
Altitude hold (ALT HLD); Vertical Speed (VERT SPD)
44
The basic FD roll axis mode is:
Heading Hold
45
The basic FD pitch mode is:
Altitude hold (ALT HLD) or Vertical Speed (VERT SPD); same as autopilot
46
If airplane vertical speed is 250 fpm or less, ______ mode is engaged. If vertical speed is greater than 250 fpm, vertical speed at the time of engagement is maintained and _____mode is engaged.
ALT HLD; VERT SPD
47
The HDG HLD, HDG SEL, LNAV, VERT NAV, VERT SPD, FLCH and ALT HLD modes are disabled below _____ ft AGL when the dual approach mode is engaged.
500
48
Which VNAV mode is used for all climbs and for speed on pitch descents?
VNAVFLCH
49
Which VNAV mode is engaged for defined path descents to FMS programmed altitudes?
VNAV PATH
50
Which VNAV mode engages when the airplane reaches an altitude set in the altitude select window or programmed by the FMS?
VNAV ALC
51
Which VNAV mode is engaged for for VNAV level off at altitudes set in the Altitude select window or as programmed by the FMS, whichever occurs first?
VNAV ALT
52
The ALTITUDE INV (altitude intervene) is enabled only when the ____ mode is engaged.
VNAV
53
Which autopilot switch is used to alternately turn off and turn on the roll axis of the AP?
LAT DISABLE switch
54
Which autopilot switch is used to alternately turn off and turn on the pitch axis of the AP?
PITCH DISABLE switch
55
If 10 feet is selected, the 100/10 switch on the AFCS panel reverts to the 100-foot mode when:
Weight on wheels (touch-n-go) or TOGA selected (go around)
56
The ATS (autothrottles) will disengage and disarm for any of the following conditions:
 Failure in the VIA ATS servo interface  AFCS control changed by pressing P/CP switch on the AFCS panel  P or CP ATS disconnect switch pressed  AUTOTHROTTLE ARM switch is disarmed  System detects an incompatible ATS condition (TR not locked or less than 3 engines running)
57
With the airplane stabilized, the ATS will maintain speed within ± _____ knots of the selected airspeed throughout the recommended flight envelope.
5
58
The autothrottles will not command a speed lower than _____ or an airspeed/Mach greater than the upper limit of the recommended flight envelope.
1.2 Vstall
59
How do the flaps and slats work?
 Flaps: A flap and slat drive gearbox, located on the aft center wing beam is powered by two separate hydraulic motors, and is used to drive a single flap torque tube system in each wing. Each flap segment is extended and retracted by two torque limited ballscrew actuators which are connected through gearboxes to the torque tube system. The torque limiting function will engage and stall the flap/slat drive gearbox during excessive load conditions. The torque limiters should reset upon reversing flap movement.  Slats: Each slat section is attached to two curved tracks which move on rollers in the wing structure. Each slat section is extended and retracted by two telescoping ballscrew actuators which are torque limited during excessive load conditions. They are connected to a single slat torque tube system in the wing. Power for operation of the slats is provided by the flap and slat drive gearbox. Power output from the gearbox is transmitted by torque tubes through a decoupler unit and then to a clutch and brake assembly. From there, the power output is transmitted by torque tubes to the slat drive actuators in the wings. The slat decoupler unit is designed to disengage the flap and slat drive gearbox from the slat system in the event an excessive load occurs in the slat drive system.
60
What is the extension/retraction time for flaps with both #1 and #4 hydraulic systems operational? Only 1 system?
29 seconds / 58 seconds
61
What are the indications of a flap asymmetry?
 Flaps stop before reaching the commanded position  TE FLAP BRAKE ON Caution  TE FLAP ASYMMETRY Caution
62
What are the indications of a slat asymmetry?
 Slats stop before reaching the commanded position  LE SLAT BRAKE ON Caution  LE SLAT ASYMMETRY Caution
63
If the flaps stop the slats will ____. If the slats stop, the flaps will ____.
Stop; continue to commanded position
64
How is the flap handle connected to the flap/slat actuator?
Mechanically to the flap/slat drive gearbox
65
Does the Slat Drive Disconnect switch decouple the slats?
No - it simply disconnects the slats from the flap drive system
66
When do you get the LE SLAT BRAKE ON Caution CWA?
Whenever a slat torque tube brake is applied
67
What may a LE SLAT BRAKE ON Caution CWA indicate?
Torque tube overspeed; slat asymmetry; slat torque tube decoupled from the gearbox
68
When do you get the TE FLAP BRAKE ON Caution CWA?
Whenever a flap torque tube brake is applied
69
What may a TE FLAP BRAKE ON Caution CWA indicate?
Torque tube overspeed OR flap asymmetry
70
When do you get the TE FLAP ASYMMETRY Caution CWA?
Whenever the flap asymmetry system has generated an asymmetry signal
71
When do you get the LE SLAT ASYMMETRY Caution CWA?
Whenever the slat asymmetry system has generated an asymmetry signal
72
What does the SLAT FLAP NOT SYNC Caution CWA mean?
The flaps reached 40% before the slats fully extended or; | 10 seconds after the flaps are fully retracted, the slats are not fully retracted
73
To obtain a spin-up signal and/or touchdown signal for ground spoiler deployment, any one the following signals must be present:
 Spin up signal from L FWD and R AFT wheels  Spin up signal from R FWD and L AFT wheels  Touchdown signal from both FWD gears  Touchdown signal from both AFT gears
74
Ground spoilers get their hydraulic power from systems _____.
1 and 4
75
A mechanical spoiler interlock moves which throttle(s) to the idle position when either spoiler handle is moved to the open position?
#1 throttle
76
Where do you find guidance for flight augmentation problems after engine start but prior to takeoff?
Dash 1, Section 2, AFSC Normal Procedures
77
If uncommanded flight control inputs are experienced, immediately disengage the _____ and _____ switches on the AFCS panel.
AUG PWR; AFCS PWR
78
Where do you find guidance for flight augmentation problems after takeoff?
Dash 1, Section 3
79
A single fault in the augmentation system is indicated by a _____ or _____advisory message, or _____caution message.
PITCH AUG FAULT; LATERAL AUG FAULT; YAW AUG FAULT
80
Complete failure of a subsystem or a dual fault in the augmentation system is indicated by a _____ or _____advisory message, or _____caution message.
PITCH AUG INOP; LATERAL AUG INOP; YAW AUG INOP
81
Airspeed is restricted to ____ KCAS or ____ Mach if the yaw augmentation system remains faulted or inoperative.
300; 0.825
82
With YAW AUGMENTATION INOP, conditions permitting, reduce altitude to approximately _______ or lower and establish a cruise airspeed range of _____ to _____ Mach.
31,000 feet; 0.70; 0.75
83
What are the Flap / Slat Failure General Procedures?
 Turn off autopilot  Uncommanded rolling moment? Place flap handle to previous position  NO uncommanded rolling moment? Place flap handle to corresponding flap position  Scan affected system
84
What are the three types of mechanical failures in the flaps?
 Broken flap cable: no physical connection to desired flap position  Flap cable tension detector switch: shuts off hyd pressure to flaps  Torque limiter lockout
85
What happens if an ASYMMETRIC FLAP condition occurs?
 Flaps stop moving before reaching selected position  TE FLAP BRAKE ON light ON  TE FLAP ASYMMETRY light ON  SLATS will also stop if FLAPS stop
86
What is the problem if only the TE FLAP BRAKE light is on (no asymmetry light)?
Indicates flap overspeed or brake system malfunction
87
What happens if an ASYMMETRIC SLAT condition occurs?
 Slats stop before reaching commanded position  LE SLAT BRAKE light ON  LE SLAT ASYMMETRY light ON  SLAT FLAP SYNC light On  Slats did not fully extend before flaps reach 40%  Flaps retracted fully with slats not fully retracted within 10 seconds  Resynch flaps & slats if required
88
What is the problem if only the LE SLAT BRAKE light is on (no asymmetry light)?
Indicates slat torque tube brake engaged due to either slat decouple, LE SLAT torque tube overspeed, slat brake system malfunction or slat drive disc switch engaged (prior to slat actuation)
89
What do you do for a slat drive decouple?
Observe speed limits; visually inspect to confirm decouple; do not attempt to reset; place SLAT DRIVE DISC switch to DISC
90
What are the 3 conditions where you will have to re-sync flaps and slats?
 Slats fail to indicate extend (slats appear fully extended)  Slats fail to indicate extend (slats appear not fully extended)  Slats fail to indicate retracted (on retraction cycle)
91
Spoiler ratio shifter failure is indicated when RATIO SHIFT CWA comes on and the shifter is not in the right position with respect to the flaps. What do you have to do to correct the situation?
a. Failure in FLAPS DOWN configuration (Flaps are UP but ratio shifter thinks they are DOWN) 1) 60 spoiler capability & 3 uprig with flaps UP 2) Slight roll into failed shifter 3) Place BOTH Spoiler Ratio shifter switches to FLAPS UP position 4) If spoilers don’t move to flaps UP position (lights go out), place both switches to DOWN and limit roll control 5) After extending flaps for landing, place both Spoiler Ratio Shift switches to FLAPS DOWN position 6) Spoiler deflection of 60 at high speed could cause structural damage b. Failure in FLAPS UP configuration (Flaps are DOWN but ratio shifter thinks they are UP) 1) 22.5 spoiler capability & 0 uprig with flaps UP 2) Slight roll away from failed shifter 3) Place BOTH Spoiler Ratio shifter switches to FLAPS DOWN position 4) If spoilers don’t move to flaps DOWN position (lights go out), place both switches to UP and expect reduced roll capability during landing
92
What are maximum flap/slats speeds for the following?
 40% flaps, slats retracted - 215 KCAS / .45M  40% flaps, slats extended - 215 KCAS / .45M  62.5% flaps, slats retracted - 185 KCAS / .45M  62.5% flaps, slats extended - 195 KCAS / .45M  100% flaps, slats retracted - 175 KCAS / .45M  100% flaps, slats extended - 180 KCAS / .45M

C-5 Eval Guide (17 decks)

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