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Cirrus > POH Operating Limitations > Flashcards

POH Operating Limitations Flashcards

1
Q

Maximum gallons usable fuel

A

56

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2
Q

Horsepower

A

200@2700 RPM

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3
Q

Propellor type

A

Constant speed

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4
Q

Oil level quarts

A

6 - 8 quarts

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5
Q

Max gross wt at take off

A

3050

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6
Q

Max baggage compartment weight

A

130

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7
Q

Standard empty weight

A

2050

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8
Q

Max useful load wt

A

950

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9
Q

Full fuel payload wt

A

622 (max allowable combined wt of pilot, passengers, baggage) with full fuel

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10
Q

Vne (never exceed)

A

200 KIAS, 204 KCAS

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11
Q

Vno (max structural cruising speed - smooth air)

A

163 KIAS, 166 KCAS

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12
Q

Vo at 3050lbs and 2,600lbs (Operating maneuvering speed, max speed with full control)

A 
3050 = 130 KIAS
2600 = 120 KIAS
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13
Q

Vfe at 50% flaps (Max flap extend)

A

119 KIAS, 120 KCAS

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14
Q

Vfe at 100% flaps (Max flap extend)

A

104 KIAS, 104 KCAS

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15
Q

Vpd (Max parachute deployment speed)

A

133 KIAS, 135 KCAS

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16
Q

Fuel grade

A

100 LL (Blue)

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17
Q

Max allowable fuel imbalance between tanks?

A

7.5 gallons (1/4 tank)

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18
Q

How do you quickly tune the emergency frequency (121.5)

A

Press and hold comm transfer key for 2 seconds.

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19
Q

Vg at 3,050lbs and 2,600lbs (Best glide)

A 
3,050 = 99
2,600 = 95

At 8,000ft, best glide with no wind will yield approx 12nm distance

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20
Q

Emergency landing speeds (flaps up, 50%, and 100%)

A

Flaps Up……87 KIAS
Flaps 50% ………82 KIAS
Flaps 100% …..76 KIAS

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21
Q

Emergency procedure: Engine failure on takeoff

A
  1. Best Glide or Landing Speed (as appropriate) ……….. ESTABLISH
  2. Mixture ……………………………………………………………………CUTOFF
  3. Fuel Selector………………………………………………………………….OFF
  4. Ignition Switch………………………………………………………………..OFF
  5. Flaps ……………………………………………………………. AS REQUIRED
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22
Q

Emergency procedure: Engine failure during flight

A
  1. Best Glide Speed ……………………………………………….. ESTABLISH
  2. Mixture …………………………………………………………. AS REQUIRED
  3. Fuel Selector……………………………………………….. SWITCH TANKS
  4. Fuel Pump……………………………………………………………….. BOOST
  5. Alternate Induction Air……………………………………………………… ON
  6. Ignition Switch……………………………………………….. CHECK, BOTH
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23
Q

Emergency procedure: Emergency engine airstart

A
  1. Bat Master Switches …………………………………………………………ON
  2. Power Lever ……………………………………………………………½” OPEN
  3. Mixture ………………………………………………………. RICH, AS REQ’D
  4. Fuel Selector……………………………………………….. SWITCH TANKS
  5. Ignition Switch…………………………………………………………….. BOTH
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24
Q

Emergency procedure: Engine fire inflight

A
  1. Mixture ………………………………………………………………….. CUTOFF
  2. Fuel Pump……………………………………………………………………..OFF
  3. Fuel Selector………………………………………………………………….OFF
  4. Airflow Selector ………………………………………………………………OFF
  5. Power Lever …………………………………………………………………IDLE
  6. Ignition Switch………………………………………………………………..OFF
  7. Cabin Doors ……………………………………………… PARTIALLY OPEN
    Airspeed may need to be reduced to partially open door in flight.
  8. Land as soon as possible.
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25
Q

Emergency procedure: Cabin fire in flight

A
  1. Bat-Alt Master Switches…………………………………. OFF , AS REQ’D
  2. Fire Extinguisher…………………………………………………… ACTIVATE
    If airflow is not sufficient to clear smoke or fumes from cabin: 3. Cabin Doors……………………………………………….PARTIALLY OPEN

•• WARNING •• Halon gas used in the fire extinguisher can be toxic, especially in a closed area. After extinguishing fire, ventilate cabin by and unlatching door (if required).

If the airplane is in IMC conditions, turn ALT 1, ALT 2, and BAT 1 switches OFF . Power from battery 2 will keep the Primary Flight Display operational for approximately 30 minutes.

• Note • With Bat-Alt Master Switches OFF , engine will continue to run. However, no electrical power will be available

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26
Q

Emergency procedure: Wing fire in flight

A
  1. Pitot Heat Switch…………………………………………………………….OFF
  2. Navigation Light Switch……………………………………………………OFF
  3. Landing Light …………………………………………………………………OFF
  4. Strobe Light Switch …………………………………………………………OFF
  5. If possible, side slip to keep flames away from fuel tank and cabin.
  6. Land as soon as possible.

• Note • Putting the airplane into a dive may blow out the fire. Do not exceed VNE during the dive.

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27
Q

Emergency procedure: Engine fire during start

A
  1. Mixture ………………………………………………………………….. CUTOFF
  2. Fuel Pump……………………………………………………………………..OFF
  3. Fuel Selector………………………………………………………………….OFF
  4. Power Lever …………………………………………………………FORWARD
  5. Starter …………………………………………………………………….. CRANK
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28
Q

Emergency procedures: Emergency descent

A
  1. Power Lever ………………………………………………………………….IDLE
  2. Mixture …………………………………………………………. AS REQUIRED

• Caution • If significant turbulence is expected do not descend at indicated airspeeds greater than VNO (163 KIAS).

  1. Airspeed………………………………………………………..VNE (200 KIAS)
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29
Q

Emergency procedure: Emergency landing without power

A
  1. Best Glide Speed……………………………………………….. ESTABLISH
  2. Radio …………………………………….. Transmit (121.5 MHz) MAYDAY giving location and intentions
  3. Transponder………………………………………………….. SQUAWK 7700
  4. If off airport, ELT ………………………………………………….. ACTIVATE
  5. Power Lever …………………………………………………………………. IDLE
  6. Mixture ……………………………………………………………………CUTOFF
  7. Fuel Selector………………………………………………………………….OFF
  8. Ignition Switch………………………………………………………………..OFF
  9. Fuel Pump …………………………………………………………………….OFF
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30
Q

Which annunciator message is more critical: Caution or Warning?

A

Warning

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31
Q

Emergency procedures: AHRS Failure

A
  1. Verify Avionics System has switched to functioning AHRS If not, manually switch to functioning AHRS and attempt to bring failed AHRS back on-line:
  2. Failed AHRS Circuit Breaker……………………………………………. SET
    If open, reset (close) circuit breaker. If circuit breaker opens again, do not reset.
  3. Be prepared to revert to Standby Instruments (Altitude, Heading).
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32
Q

Emergency procedures: ADC (Air data computer) Failure

A
  1. ADC Circuit Breaker……………………………………………………….. SET
    If open, reset (close) circuit breaker. If circuit breaker opens again, do not reset.
  2. Revert to Standby Instruments (Altitude, Airspeed).
  3. Land as soon as practical.
33
Q

Emergency procedures: Emergency ground egress

A
  1. Engine………………………………………………………………SHUTDOWN

• Note • If the engine is left running, set the Parking Brake prior to evacuating the airplane.

  1. Seat belts …………………………………………………………….. RELEASE
  2. Airplane………………………………………………………………………..EXIT

• Note • If the doors cannot be opened, break out the windows with egress hammer, located in the console between the front seats, and crawl through the opening.

34
Q

Emergency procedures: Inadvertent spin entry

A

Inadvertent Spin Entry 1. CAPS ………………………………………………………………….. ACTIVATE

In all cases, if the aircraft enters an unusual attitude from which recovery is not expected before ground impact, immediate deployment of the CAPS is required.

The minimum demonstrated altitude loss for a CAPS deployment from a one-turn spin is 920 feet. Activation at higher altitudes provides enhanced safety margins for parachute recoveries. Do not waste time and altitude trying to recover from a spiral/spin before activating CAPS.

35
Q

Emergency procedures: Inadvertent spiral dive in IMC

A
  1. Power Lever ………………………………………………………………….IDLE
  2. Stop the spiral dive by using coordinated aileron and rudder control while referring to the attitude indicator and turn coordinator to level the wings.
  3. Cautiously apply elevator back pressure to bring airplane to level flight attitude.

In all cases, if the aircraft enters an unusual attitude from which recovery is not assured, immediately deploy CAPS. Refer to Section 10, Safety Information, for CAPS deployment information

36
Q

Emergency procedures: Emergency engine shutdown on ground

A
  1. Power Lever …………………………………………………………………. IDLE
  2. Fuel Pump (if used) ………………………………………………………..OFF
  3. Mixture ……………………………………………………………………CUTOFF
  4. Fuel Selector………………………………………………………………….OFF
  5. Ignition Switch………………………………………………………………..OFF
37
Q

Emergency procedure: Deploying CAPS

A
  1. Airspeed………………………………………………. MINIMUM POSSIBLE
    The maximum demonstrated deployment speed is 133 KIAS.
    Reducing airspeed allows minimum parachute loads and prevents structural overload and possible parachute failure.
  2. Mixture (If time and altitude permit) …………………………… CUTOFF
    Generally, a distressed airplane will be safer for its occupants if the engine is not running.
  3. Activation Handle Cover………………………………………….. REMOVE
    The cover has a handle located at the forward edge. Pull cover down to expose activation T-handle.
  4. Activation Handle (Both Hands)…………. PULL STRAIGHT DOWN
    Pull the activation T-handle from its holder. Clasp both hands around the handle and pull straight down in a strong, steady, and continuous motion. Maintain maximum pull force until the rocket activates. Pull forces up to, or exceeding, 45 pounds may be required. Bending of the handle-housing mount is to be expected.

•• WARNING •• Jerking or rapidly pulling the activation T-handle will greatly increase the pull forces required to activate the rocket. Use a firm and steady pulling motion – a “chin-up” type pull enhances successful activation.

38
Q

What is the best way to maximize braking?

A

0% flaps

39
Q

It is hot outside, what should the fuel boost be set at?

A

Fuel boost should be on to prevent vapor lock.

40
Q

On an alternate static source, will KIAS be higher or lower than KCAS?

A

Higher, because the cabin pressure is lower than outside ambient air pressure.

41
Q

Vs (0%)

A

69 KIAS

42
Q

Vs (100%)?

A

61 KIAS

43
Q

Take off distance (1,000ft pressure alt, 20C, 3,050lbs)?

A

1,700 ft

no obstacle clearance. see section 5 of POH for more variables.

44
Q

Amount of fuel consumed for start, taxi, and takeoff?

A

1.5 gallons

45
Q

Typical fuel consumption rate?

A

10-14 gph

POH section 5

46
Q

Landing distance (1000ft pressure alt, 20C, 3,050lbs, full flaps)

A

1,000ft

Section 5 POH

47
Q

How often should tanks be switched?

A

30 minutes

Actually 37 minutes assuming 7.5 gallons maximum difference between tanks, assumes 12 gallons/hour

48
Q

How is a standard rate turn indicated?

A

By the magenta trend vector holding steady on the 2’nd tick mark. (the first tick mark is a half-rate turn… a 2 minute turn)

49
Q

What does the HSI course pointer look like if it is displaying VOR2/LOC2?

A

It is a double line. VOR1/LOC1 is a single line.

50
Q

How do you know a navaid is being received?

A

The to/from indicator will be present. The station tuned to will show in the nav frequency box.

51
Q

How do you set the parking brake?

A

To apply the parking brake, set the brakes with the rudder-pedal toe brakes, and then pull the PARK BRAKE handle aft. This properly sets the hydraulics

52
Q

What type of engine is in the SR20?

A

Teledyne Continental IO-360-ES, six-cylinder, normally aspirated, fuel-injected engine de-rated to 200 hp at 2,700 RPM.

53
Q

Amount of fuel if filled to the tabs?

A

13 gallons each tank, total of 26.

(vs 28/56 for full fuel).

54
Q

Describe how the fuel pump works in “Prime” position?

A

It is a momentary switch that allows the fuel pump to run at high speed (PRIME) when the engine oil pressure is less than 10 PSI.

55
Q

Describe the fuel pump operation in “Boost” position.

A

Selecting BOOST energizes the fuel pump in low-speed mode regardless of oil pressure to deliver a continuous 4-6 psi boost to the fuel flow for vapor suppression in a hot fuel condition.

56
Q

Battery 2 is dedicated to…

A

Essential bus #1 and #2.

57
Q

Component on essential bus #1 are:

A

ADC, AHRS1, GPS NAV 1, COM1, PFD1, Standby attitude instrument,

58
Q

Besides the Essential Bus, ALT 1 powers which busses?

A
  • A/C BUS 1,
    • A/C BUS 2,
    • MAIN BUS 3.
59
Q

Besides the Essential busses, ALT 2 powers which busses?

A
  • NON ESS BUS,
    • MAIN BUS 1,
    • MAIN BUS 2
60
Q

Describe the various ways power is delivered to the Essential busses?

A

The circuit breaker panel ESS BUS 1 and ESS BUS 2 are powered directly by ALT 1 and ALT 2 from the MCU Essential Distribution Bus through 30-amp fuses inside the MCU and also by BAT 2 through the 20-amp BAT 2 circuit breaker. In the event of ALT 1 or ALT 2 failure, the Essential Buses in the circuit breaker panel will be powered by the remaining alternator through the Main Distribution Bus 1 or Main Distribution Bus 2 in the MCU. In the case of both alternators failing, BAT 1 is connected directly to the Essential Distribution Bus in the MCU and will power ESS BUS 1 and ESS BUS 2. In the event of both alternators and BAT 1 failing, BAT 2 is connected directly to ESS BUS 1.

61
Q

Describe how Main Bus 1 and 2 receive their power.

A

The circuit breaker panel MAIN BUS 1 and MAIN BUS 2 are powered by ALT 2 from the MCU Main Distribution Bus 2 and - in the event of ALT 2 failure - by ALT 1 and BAT 1 from the Main Distribution Bus 2.

62
Q

Describe how Main Bus 3 receives it’s power.

A

The circuit breaker panel MAIN BUS 3 is powered by ALT 1 and BAT 1 from the MCU Main Distribution Bus 1. In the event of ALT 1 failure, BAT 1 will power MAIN BUS 3. ALT 2 is prevented from powering MAIN BUS 3.

63
Q

Describe how the non-Essential bus is powered.

A

The circuit breaker panel NON ESS BUS is powered by ALT 2 from the MCU Main Distribution Bus 2 and - in the event of ALT 2 failure - by ALT 1 and BAT 1 from the Main Distribution Bus 2.

64
Q

Describe how the AC (aircraft) busses are powered.

A

The circuit breaker panel A/C BUS 1 and A/C BUS 2, is powered by ALT 1 and BAT 1 from the MCU Main Distribution Bus 1. In the event of ALT 1 failure, BAT 1 will power A/C BUS 1 and A/C BUS 2. ALT 2 is prevented from powering A/C BUS 1 and A/C BUS 2

65
Q

Describe what happens when you turn on BAT1.

A

Setting the BAT 1 switch ‘on’ energizes a relay connecting BAT 1 to the MCU Distribution Buses (also energizing the circuit breaker panel buses) and the open contacts of the starter relay.

66
Q

Describe what happens when you turn on BAT 2.

A

Setting the BAT 2 switch ‘on’ energizes a relay connecting BAT 2 to the circuit breaker panel ESS BUS 1.

67
Q

Which battery switch must be on to enable ALT 1?

A

BAT1

68
Q

Which battery switch must be on to enable ALT2?

A

BAT1 or BAT2.

69
Q

What is the purpose of the Avionics switch?

A

Typically, the switch is used to energize or de-energize all non-essential avionics on the AVIONICS bus simultaneously. With the switch in the OFF position, no electrical power will be applied to the non-essential avionics equipment, regardless of the position of the MASTER switch or the individual equipment switches. For normal operations, the AVIONICS switch should be placed in the OFF position prior to activating the MASTER switches, starting the engine, or applying an external power source.

70
Q

Recite the sample take off briefing.

A

This will be a __________ (normal, short, soft) takeoff from RWY _________ with a takeoff distance of _______ feet and ________ feet of runway available. Rotation speed is ______ KIAS. Initial heading after takeoff is _______ degrees to an altitude of _______ feet. Abort the takeoff for any engine failures/abnormalities prior to rotation. If the engine fails after rotation I will ______________.

71
Q

Vr

A

65-70

72
Q

Describe the pattern speeds and flap configurations.

A

Downwind: 100KIAS, 0 flaps, approx 50% power
Abeam: 100KIAS, 50% flaps, approx 25% power
Base: 90KIAS, 100% flaps, approx 25% power
Final: 78KIAS, 100% flaps, power as required
Land: Stalling speed

73
Q

Typical fuel flow

A

Green arc >14. Yellow arc 7-14

74
Q

Vs 50%

A

66KIAS (stall speed with 50% flaps)

75
Q

Vs

A

69KIAS (mimimum speed in cruise configuration)

76
Q

Vx

A

77KIAS (best angle of climb)

77
Q

Vy

A

85 KIAS (best rate of climb)

78
Q

When should the “Boost” pump be used?

A

Takeoff, landing, and switching tanks

79
Q

Do a passenger briefing.

A
  • CAPS
  • Smoking
  • Seatbelts
  • Doors
  • Emergency exit/Egress hammer
  • ELT

Cirrus (3 decks)

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