Cirrus SR-20 N699YZ User manual

CIRRUS SR-20
N699YZ, Serial No. SR-20-2448
(revised 09/11/2018)
General, POH Section 1
1. Engine Model: Lycoming 10-390-C3136
2. Engine Horsepower rating: 215hp @ 2700 rpm
3. Propellor type: Three-blade, constant-speed Hartzell
4. Fuel capacity: 58.5 gallons total, 56.0 gallons useable
5. Fuel type: 100 LL (blue), 100 (green)
6. Oil capacity: 7 quarts (note; min. Quantity, 6 qts.)
7. Oil grades: Above 40℉ - SAE 40, all temps SAE 15W-50 or SAE 20W-50
8. Maximum gross weight for takeoff: 3,150 lbs.
9. Maximum gross weight for landing: 3,150 lbs.
10.N699YZ empty weight (see book at dispatch counter): 2145 lbs.
11.N699YZ payload with full fuel (book on dispatch counter): 668 lbs.
12.N699YZ useful load: 849 lbs.
13. Wing loading: 22 lbs per square foot. (A 182 is 17 lbs/ft )²
14.Power loading: 15 lbs. per hp.(A 182 is 13 lbs/hp)
15. V₀: Operating Maneuvering Speed- maximum speed at which application of full
control movement will not overstress the airplane. 113 KIAS.
16.Vpd: Maximum parachute deployment speed. 135 KIAS
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17.VS50% and VSO: Stall speed with 50% and 100% flaps extended.
LIMITATIONS, POH Section 2
18.VNE, VNO, VO, VPD: 201 KIAS, 164, 133, 15050%/110100%, 135
19.Zero fuel weight: 2,814 lbs.
20.Maximum weight in baggage compartment: 130 lbs.
21.Center of gravity reference datum: 100 inches forward of firewall
22.Flap limitations: Takeoff- 0% or 50%. Landing- 100%, however 0% or 50% can
be used if malfunction or other conditions deem it appropriate.
23.Allow flight load factors: Flaps up -+3.8g, -1.9g. Flaps extended-+1.9g, -0g.
24.Maximum fuel imbalance limit: 7.5 gallons (¼ tank)
25.Maximum operating altitude: 17,500 ft. MSL
26.Temperature limit and paint limitations: 150℉ (66℃), approved white paint.
27.Runway surface and smoking limitations: Smooth runway surface, no smoking
28.Maximum demonstrated parachute deployment speed: 135 KIAS
29.Multi-function display limitation: Not approved as a primary navigation instrument.
Information may be used for advisory purposes only.
30.Flight into known icing conditions: Prohibited.
31.Battery requirements: Battery 1-IFR and VFR. Battery 2- IFR.
32.Alternator requirements: Alternator 1- IFR and VFR. Alternator 2- IFR.
33.List remaining equipment that’s required for all operations: Ammeter, low volts,
and alternator annunciators; ELT; fire extinguisher; flaps system and flap position
lights; pitch and bank trim systems and indicators; fuel boost pump, quantity
indicator, and selector valve; alternate engine-air induction system; alternate
static source; anti-collision lights; standby altimeter and airspeed indicators;
magnetic compass; pitot system, static system (normal); fuel flow, manifold
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pressure, oil pressure, and oil temperature gauges; tachometer; airframe
parachute, and airplane flight manual.
34.When is the vertical speed indicator, multi-function display, and cylinder head
temperature gauge required? Never.
EMERGENCY PROCEDURES, POH Section 3
35.Maneuvering speed: 3,150 lbs-133, 2700 lbs-123, 2,300 lbs- 114 KIAS.
36.Best glide speeds: 3,150 lbs- 100, 2,600 lbs- 92 KIAS.
37.Emergency landing speeds: flaps up- 89, flaps 50%- 83, flaps 100%- 78 KIAS.
38.Engine induction-system fire during start procedure: Mixture cutoff, fuel pump off,
fuel selector off, power lever full forward, engage starter.
39. Engine failure in flight procedure: Establish best glide, mixture full rich, switch
fuel tanks, fuel pump on boost, alternate induction air on, ignition switch check
both.
40.Engine airstart procedure: Battery master switches on, power level ½” open,
mixture rich, switch fuel tanks, ignition switch on both, fuel pump onboost,
alternate induction air on, alternator master switches off, engage starter if prop
not windmilling, slowly increase power lever, alternator master switches on when
engine starts.
41.If a partial power loss occurs or the engine starts running rough, what initial
action should be performed: Fuel pump on BOOST.
42.If the engine fuel pump fails completely, will the fuel pump’s boost position
provide enough fuel to keep the engine running? No, but it will keep the engine
running of the engine pump has a partial failure.
43.Propellor governor failure procedure: If RPM will not increase, check oil pressure
and land as soon as practical. If RPM overspeeds or will not decrease, adjust
power lever to keep RPM within limits, reduce to 80 knots, and land as soon as
practial.
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44.Engine fire in flight procedure: Mixture cutoff, fuel pump off, power level idle, fuel
selector off ignition switch off.
45.Wing fire in flight procedure: Pitot heat, navigation lights and strobe lights off.
Land as soon as possible.
46.Emergency descent procedure: POwer lever idle, mixture full rich, and airspeed
at VNE (201 kts).
47.Door open in flight procedure: Reduce airspeed to 80 to 90 knots and land as
soon as practical. If not latched, door will remain 1 to 3 inches open in flight.
48.CAPS deployment procedure: Airspeed as slow as possible (max demonstrated
was 135 kts.) mixture cutoff is possible, cover removed, pull activation handle
from its holder and then clasp handle with both hands and pull straight down in a
strong, steady and continuous motion. Maintain pull force until rocket activates.
Bending of the handle-housing mount is to be expected.
49.CAPS after-deployment procedure: Mixture check cutoff, fuel selector off, bat-alt
master switches off, ignition switch off, fuel pump off, ELT on (located below CB
panel), seat belts and harnesses tightened, loose items secure, and assume
emergency landing body position.
50.Describe the emergency landing body position: Cross your arms across your
chest, firmly grasp the shoulder harness, and hold your upper torso erect. The
landing force is equivalent to a drop from 10 feet above the ground.
51.An alternator malfunctions. What indication would occur? The ALT caution light
would illuminate in the annunciator panel, and the ammeter would probably
indicate an excessive charge or discharge rate.
52.What does the term “self-exciting” alternator mean? The alternator requires
battery voltage only for starting. Once started, it provides self-generated field
power to continue operation in case of battery failure.
53.If electrical loads must be reduced due to alternator failure, should you switch off
electrical components that are not essential to flight or pull circuit breakers? Wy?
Switch off electrical components in order to prevent accidental circuit breaker
disconnection and loss of power to flight-critical systems.
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54.ALT 1 light in steady. The cause and procedure is: Cause: Wiring fault or
malfunctioning alternator or control unit. Procedure: ALT 1 master switch off, ALT
1CB checked and reset, ALT 1 master switch on. If alternator does not reset,
reduce loads on main buses 1 and 2 and on the non-essential buses, and
monitor voltage, turn the ALT 1 master switch off, and land as soon as practical.
55.ALT1 light flashing. The cause and procedure is: Cause: A severely discharged
battery, which causes an excessive charging rate, along with heavy equipment
loads. Procedure: Ammeter switch on BATT. If charging rate is greater than 30
amps, reduce load on main busses 1 and 2 and on the non-essential bses.
Monitor ammeter until battery charge rate is less than 15 amps. When charge
rate is within limits, add loads as necessary for flight conditions.
56.ALT 2 light steady. The cause and procedure is: Cause: Failure of ALT 2 or rpm
below 1,700 to 2,200. Procedure: ALT 2 master switch off, ALT 2 CB checked
and reset, ALT 2 master switch on. If alternator does not reset, reduce loads on
main buses 1 and 2 and on the non-essential buses, turn the ALT 2 master
switch off, and land as soon as practical. (Essential bus loads will now be
powered from ALT 1, BAT 1, and BAT 2.)
57.LOW VOLTS warning light illuminated procedure: Cause: Voltage is 24.5 volts or
less and you are on battery power only because both alternators have failed or
are off. Procedure: If both alternators have failed, land as soon as possible.
58.Communications failure procedure: Check switches and controls, change
frequency, check, circuit breakers, change headset, and connect the hand-held
microphone. (Note: if the audio panel power fails, the audio panel power fails, the
audio panel connects COM 1 to the pilot’s headset and speakers. The same
thing will happen if you turn the audio panel off.)
59.Power level linkage failure: Use available power and flaps as required to safely
land the airplane. If power is stuck at or near full power, use the mixture control
to control power for descent. Plan a power-off approach and landing. If power is
such that you cannot maintain straight and level flight, plan a forced landing.
60.Electric trim/autopilot failure: Maintain airplane control manually (override the
autopilot or trim) and disengage the autopilot if it was engaged. Pull the PITCH
TRIM, ROLL TRIM, or AUTOPILOT CB as required. Land as soon as practical.
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NORMAL PROCEDURES, POH Section 4
61.Normal Vy, and Vx climb speeds at sea level: 96, 96 and 81 KIAS.
62.Landing approach speeds, flaps up, 50% and 100%: 89, 84, and 78 KIAS
63.Maximum demonstrated crosswind velocity, takeoff or landing: 20 knots
64.During the cabin inspection before the walk-around, what is the first thing you do
after you turn on the BAT 2 master switch? Check the avionics cooling fan.
65.How is the fuel pump used for starting? PRIME for 2 seconds then BOOST
66.What is starter motor’s duty time? Intervals of 20 seconds on, 20 seconds off in
order to improve battery and contractor life.
67.When should the fuel pump be on BOOST? Engine start, takeoff, and landing;
and whenever hot fuel conditions exist, fuel pressure fluctuates, or switching fuel
tanks.
68.When are the ALT master switches turned on? After engine start.
69.How do you start a flooded engine? Turn fuel pump off, allow fuel to drain from
the intake tubes, mixture full lean, power lever full open, crank the engine
through several revolutions. When it starts, retard the power lever and slowly
advance the mixture to full rich.
70.How do you maintain directional control when taxiing? With rudder and
differential braking. In crosswind conditions, some continual brake force may be
required.
71.How do you check the autopilot disconnect be checked before takeoff? Even
though it’s not a Cirrus checklist item, this action should always occur: Press the
HDG button to engage the autopilot. Check control forces. Now, press the yoke’s
autopilot disconnect button (the coolie hat) to ensure autopilot disconnect.
72.How do you check the propeller operation during the runup? Move the power
lever up to the detent. Approximately 2,000 rpm should occur, and it should drop
about 100 rpm as the power lever is set in the detent.
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73.What is the rpm tolerance during the mag check? 175 rpm max drop and both
drops must be within 50 rpm of each other.
74.Is an idle check required before takeoff? It’s not on Cirrus’s checklist, but that’s
not good. At the conclusion of an engine runup, particularly with a fuel injected
engine, an idle check is mandatory.
75.What flap setting is used for short- and soft-field takeoffs? 50%
76.Should the mixture be leaned during climb? As required.
77.During cruise flight when and how do you lean for best power or best economy?
When at 75% power or less, use the MFD’s lean assist or manually lean to 100°
rich of peak EGT for best power or peak EGT for best economy.
78.When can you land with less than full flaps? Only when the flaps fail to deploy or
when it’s necessary to extend glide distance due to an engine malfunction.
79.What is the short-field approach speed and the restriction that applies to braking?
78 KIAS. Apply normal brake pressure and announce “simulating max braking”.
80.What is the crosswind landing technique? Use full flaps and avoid prolonged
slips.
81.If the ELT activates after a hard landing, how do you turn it off? Press the reset
button on the ELT control panel that’s located below the circuit breaker panel.
PERFORMANCE DATA, POH Section 5
82.When determining airplane performance, what should you do if the ambient
temperature is less than or greater than the chart value? Less than: Use the
lowest published temperature, which will result in a more conservative
performance calculation. More than: Use extreme caution as performance
degrades rapidly at higher temperatures.
83.Are performance figures always reliable? No. Range and endurance variations of
10% or more can occur due to variations in fuel metering, mixture leaning
technique, engine and propellor condition, and air turbulence.
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84.Refer to Flight Planning on page 5-14 of the POH. Using the Sample Problem’s
configuration and conditions, confirm the answers given for takeoff, climb, cruise,
fuel required, and landing by using figures 5-15 through 5-32. (This is a practical
exercise to ensure your understanding of the performance charts).
85.When using the alternate static air system and flying at 80 KIAS, what is the
KCAS with 100% flaps? 72 KCAS.
86.When using the alternate static air system and flying at 80 KIAS at sea level,
what is the altitude correction with 50% flaps? Subtract 7 feet.
WEIGHT AND BALANCE, POH Section 6
87.Is OCFC’s N699YZ legal to fly based on the following information? Yes, but the
airplane is at its forward CG limit.
Basic empty weight: 2145 lbs.
Empty moment/1,000: 306.211
Fuel: 56 gallons useable
Pilot: 210 lbs.
Front seat passenger: 170 lbs.
Rear seat passenger: 140 lbs.
88.Just after takeoff in the previous problem, the pilot realizes that his wallet (pilot
certificate and medical) is in his car. Is he legal to immediately return and land?
Yes, the maximum landing weight is 3,150 lbs.
AIRPLANE AND SYSTEMS DESCRIPTION, POH Section 7
89. The airplane is made from composite materials for aerodynamic efficiency. What
material is used for the rudder, elevator, ailerons, and wing flaps? Aluminum.
90.What is the rudder-aileron interconnect? It provides a maximum of 8° down
aileron with full rudder deflection. Right rudder will cause right roll input and left
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rudder input will cause left roll input. (This may be why the airplane roll is
sensitive. Aileron input coupled with rudder input compounds the aileron input.)
91.The airplane does not have a flight-control gust lock, and you are not required to
secure the control yoke with a seat belt when the airplane is tied down. Why not?
Because the rudder, aileron and elevator trim spring cartridges have sufficient
power to act as a gust damper.
92.What are the small tabs on the elevator, rudder and right aileron? Ground
adjustable trim tabs that are factory set and do not normally require adjustment.
93.A conical trim button (called a “coolie hat”) activates the aileron and elevator trim
motors when moved left or right or up or down. When pushed down, it?
Disconnects the autopilot if engaged.
94.How do you position the elevator trim and the aileron trim to the neutral position?
Elevator: Align the yoke’s reference ,arl with the metal tab that’s attached to the
instrument panel bolster- the rounded portion that extends across the cockpit
beneath the instrument panel. Aileron: Align the force-and-aft line that’s etched
on the control yoke with the centering indication that’s marked on the bolster.
95.If the elevator control system or aileron control system failed due to something
other than a jammed elevator or a jammed aileron, how could you control the
airplane? Use the elevator or the aileron trim control system.
96.What is the yaw trim system? A spring cartridge attach to the rudder control
system that provides a centering force whenever the rudder is deflected. It is
ground adjustable only.
97.What backup flight instruments are available if the PFD fails? Altimeter, airspeed,
attitude indicator, and magnetic compass.
98.Does the airplane have a traditional turn coordinator? Yes, but it’s out of view
behind the right instrument panel bolster and it’s only used by the autopilot.
99.What is the primary heading source for the multifunction display? The PFD.
100. What adjustments can be made for the front seats? Fore and aft and
seat-back tilt.
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101. Why can’t you kneel or stand on the pilot and passenger seats? Because
you’ll crush the seat bottom’s integral aluminum honeycomb core, which is
designed to crush under impact and absorb downward loads that would occur
during a parachute landing.
102. How can you carry bulky cargo that exceeds the baggage compartment’s
length? Unlatch the rear seat backs from within the baggage compartment and
fold the seat backs down.
103. When the shoulder harnesses are attached you have complete freedom of
movement. How, then, are you protected in the event of a crash? The harnesses
are attached to inertial reels which automatically lock during sudden deceleration.
104. How could you evacuate the airplane if the cabin doors were jammed shut?
Use the ball-peen type hammer that’s located in the center armrest to break the
acrylic windows and form an escape path.
105. You are required to visually inspect the fire extinguisher before each flight.
What must you ensure? The nozzle is unobstructed, the pin has not been pulled,
and the canister has not been damaged.
106. Are the rudder pedals connected to the nose gear for steering? No.
107. So how do you steer the airplane? Differential braking.
108. Describe the brake system: A master cylinder for each rudder pedal, one
hydraulic fluid reservoir, a parking brake valve, and a single disc brake on each
main wheel.
109. How do you set the parking brake? Apply the rudder-pedal toe brakes, and
while set, pull the PARK BRAKE knob aft. It’s located near the pilot’s right ankle
on the left side of the console.
110. What is the minimum quantity for engine oil? 6 quarts.
111. Describe the fuel injection system: It’s a continuous-flow system. The engine
driven fuel pump draws fuel from the selected wing tank and sends it to the fuel
pump’s integral mixture control valve. This valve proportions fuel in response to
the pilot operated mixture control lever position and automatically provides
altitude compensation to supply the proper full rich mixture at any altitude. Fuel is
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