CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODELS SR22 AND SR22T
INDICATING/RECORDING SYSTEMS
1. DESCRIPTION
This section describes the Indicating/Recording Systems which consists of an Annunciator Panel and
related sensors and switches.
A. Annunciator Panel - Serials w/o Perspective Avionics
The annunciator assembly is mounted on the flight instrument panel and contains six annunciators.
Each annunciator has two individual LEDs as light sources. The annunciator panel has bright, dim,
and test modes, which are activated by a toggle switch mounted next to the annunciator panel. In test
mode all annunciators illuminate in the bright mode, allowing the pilot to verify that all LEDs are functional. The entire annunciator assembly is mounted on a printed circuit board, which decodes information from the individual sensors and illuminates the necessary annunciator. 28 VDC for annunciator
operation is supplied through the 2-amp ANNUNCIATOR POWER circuit breaker on the Essential
Bus.
The OIL annunciator will illuminate if the oil temperature is greater than 240°F or if the oil pressure is
less than 10 PSI. The oil pressure/oil temperature gage provides a logic low signal if either the oil pressure or oil temperature meets the above temperature or pressure criteria. The OIL annunciator illuminates red.
The FUEL annunciator will illuminate if the fuel quantity is less than approximately 14 gallons in both
tanks. The fuel quantity gage provides a logic low signal when each tank is below approximately 14
gallons. The annunciator decodes these two signals and illuminates when both signals are low. The
FUEL annunciator illuminates amber.
The LOW VOLTS annunciator will illuminate if the system voltage falls below 24.5 ± 0.35 volts. The
MCU provides a logic low signal when the voltage is low. The LOW VOLTS annunciator illuminates
red.
The ALT 1 annunciator provides two indications. During an overload condition, when alternator 1 is
generating more than maximum rated alternator amperage, the light will flash approximately 40 times
per minute. When the alternator is generating less than 2.0 ± 2.0 amps, the ALT 1 annunciator will illuminate steady, notifying the pilot that the alternator is not generating power. The ALT 1 annunciator illuminates amber.
The ALT 2 annunciator also provides two indications. During an overload condition, where alternator 2
is generating more than maximum rated alternator amperage, the light will flash approximately 40
times per minute. When the alternator is generating less than 2.0 ± 2.0 amps, the ALT 2 annunciator
will illuminate steady, notifying the pilot that the alternator is not generating power. The ALT 2 annunciator illuminates amber.
The PITOT HEAT annunciator will illuminate if the pitot heat is inoperative. If the Pitot Heat switch is
“ON” and there is no current in the line, indicating a circuit malfunction, the PITOT HEAT annunciator
will illuminate. A current sensor provides a logic low signal to the annunciator when current is absent in
the pitot heat circuit and the pitot heat switch is “ON”. The PITOT HEAT annunciator illuminates amber.
Serials 22-1036 thru 22-3025 w/ TAWS, 22-3026 & subs w/ TAWS and w/o Perspective Avionics:
TAWS terrain annunciations and control functions are incorporated into the Annunciator Panel. The
panel consists of a momentary push button switch (SELF TEST), an illuminated push button switch
(TERR INHIBIT), and three LEDS for Terrain Warning (TERR WARN), Terrain Caution (TERR CAUT),
and Terrain Inoperative (TERR INOP). The annunciators are dimmed via the instrument panel lighting
bus. The TAWS annunciator panel is powered by 28 VDC through the 2-amp ANNUN circuit breaker
on the Essential Bus.
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AIRPLANE MAINTENANCE MANUAL
MODELS SR22 AND SR22T
B. Crew Alerting System - Serials w/ Perspective Avionics
Aircraft annunciations and alerts are displayed in the Crew Alerting System (CAS) window located to
the right of the altimeter and VSI. Aircraft annunciations are grouped by criticality and sorted by order
of appearance with the most recent message on top. The color of the message text is based on its
urgency and required action:
•
Warning (red) – Immediate crew awareness and action required.
•
Caution (yellow) – Immediate crew awareness and future corrective action required.
•
Advisory (white) – Crew awareness required and subsequent action may be required.
In combination with the CAS window, the system issues an audio alert when specific system conditions are met and an expanded description of the condition is displayed in the Alerts Window located in
the lower RH corner of the PFD.
For additional Crew Alerting System information for the Perspective Integrated Avionics System refer
to the latest revision of Cirrus Perspective Line Maintenance Manual, Garmin publication number 19000920-00.
Refer to the following Figures for detailed descriptions of CAS messages. (See Figure 31-501),(See
Figure 31-502),(See Figure 31-503),(See Figure 31-504),(See Figure 31-505), (See Figure 31-506)
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EFFECTIVITY:
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CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODELS SR22 AND SR22T
2. CIRRUS PERSPECTIVE ANNUNCIATIONS AND ALERTS
CAS Warning Text
Alerts Window Text
Definition
ANTI ICE CTL
Serials w/ FIKI: Tank valves cannot
be controlled (closed) (TKS).
There is no control over the 3-way valve in
AUTO or Manual, typical of GIA failure.
ANTI ICE FLOW
Serials w/ FIKI: Flow rate is low
(TKS).
The flow meter is not sensing adequate flow
rate;
• *NORM: Flow rate < 10.24 gph
(616.8 mL/min);
• HIGH/PUMP BKUP: Flow rate < 5.12 gph
(308.8 mL/min);
• MAX: Flow rate < 10.24 gph
(616.8 mL/min);
* The required flow rate only applies to NORM
during the ON cycle.
ANTI ICE QTY
Serials w/ FIKI: Left and right fluid
quantities are unknown (TKS)
Left and Right tank QTY is INVALID causing the
3-way valve to close both Left and Right supply
lines, typical of GIA failure.
ANTI ICE QTY
Serials w/ Ice Protection: Fluid quan- In NORM/HIGH/MAX/PUMP BKUP mode the
tity is low (TKS).
total QTY < 0.5 gal.
AOA OVERHEAT
Serials w/ FIKI: AOA probe is overheated.
The Lift Transducer heater thermocouple
senses a temperature > 255ºF (124C).
AUTO DESCENT
Aircraft descent to 14,000 feet in 60
seconds.
Emergency descent warning.
AUTO DESCENT
Aircraft descent to 14,000 feet.
Emergency descent in progress (initial descent)
AUTO DESCENT
Aircraft descent to 12,500 feet.
Emergency descent in progress (secondary
descent)
BRAKE TEMP
Brake temperature is high.
Brake temperature > 293°F.
CHT
Cylinder head temperature is high.
Temperature of one or more cylinder heads >
460°F.
CO LVL HIGH
Carbon monoxide level is too high.
Carbon monoxide level is too high.
ESS BUS
Check essential power bus voltage.
Voltage output for Alternator 1 or Alternator 2 <
24.5v for more than 20 seconds or > 32.0v. This
is usually associated with an Alternator 1 or
Alternator 2 failure and will be displayed in combination with a M BUS 1 or M BUS 2 voltage
annunciation for the corresponding Alternator.
FUEL FLOW
Check fuel flow.
Fuel flow > 30 GPH.
FUEL QTY
Check fuel tank levels.
Fuel Totalizer quantity < 9 gallons.
Figure 31-501
CAS Warning Messages
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AIRPLANE MAINTENANCE MANUAL
CAS Warning Text
Alerts Window Text
MODELS SR22 AND SR22T
Definition
M BUS 1
Check main power bus 1 voltage.
Alternator voltage output > 32.0v. This is usually
associated with an alternator failure
M BUS 2
Check main power bus 2 voltage.
Alternator voltage output > 32.0v. This is usually
associated with an alternator failure
MAN PRESSURE
SR22T Serials: Check manifold pres- Manifold pressure > 38.0 inHg for 30 seconds
sure.
OR > 38.5 inHg.
OIL PRESSURE
Oil pressure is out of range.
Oil pressure < 10 psi or > 100 psi. If low oil pressure is low, the engine has probably lost a significant amount of its oil and engine failure may
be imminent.
If low oil pressure is accompanied by normal oil
temperature, it is possible that the oil pressure
sensor, gage, or relief valve is malfunctioning.
OIL TEMP
Oil temperature is high.
Oil temperature > 240°F.
OXYGEN FAULT
Serials w/ Oxygen: Oxygen system
fault.
Tank solenoid has failed (open or closed) or flow
rate is low. If flow is checked and confirmed
present, solenoid has failed open.
OXYGEN QTY
Serials w/ Oxygen: Oxygen quantity is Altitude > 10,000 ft and tank pressure < 400 psi.
low.
RPM
Check engine RPM.
Engine speed is between 2710 RPM and 2730
RPM for 10 seconds or more, OR engine speed
> 2730 RPM for 5 seconds or more.
STALL
Stall warning.
Impending stall.
START ENGAGED
Starter is engaged.
Starter stuck engaged. MCU detects 24 VDC to
Starter 30 seconds after initial engagement.
TIT
SR22T Serials: TIT temperature is
high.
LH or RH TIT > 1750°
UNDERSPEED
PROTECT ACTIVE
None
Underspeed Protection (USP) is active.
Figure 31-501
CAS Warning Messages (Continued)
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CIRRUS
CAS Caution Text
AIRPLANE MAINTENANCE MANUAL
Alerts Window Text
MODELS SR22 AND SR22T
Definition
ALT 1
Check alternator 1 current.
Illumination of ALT 1 indicates that the ampere
output < 2 amps for 20 seconds or more.
ALT 2
Check alternator 2 current.
Illumination of ALT 2 indicates that the ampere
output < 2 amps for 20 seconds or more.
ALT AIR OPEN
Alternate air door is open.
Alternate air door is open.
ANTI ICE HEAT
Serials w/ FIKI: Stall warning/AoA
heater has failed.
With the Pitot Heat switch is ON, the lift transducer heater current sensor does not sense
adequate current.
ANTI ICE LEVEL
Serials w/ FIKI: Left tank fluid quantity There is a conflict between the level sender and
is unreliable (TKS).
the level switch:
Quantity > 0.25 gal and Switch is Empty, OR
Quantity = Out Of Range
ANTI ICE LEVEL
Serials w/ FIKI: Right tank fluid quan- There is a conflict between the level sender and
tity is unreliable (TKS).
the level switch:
Quantity > 0.25 gal & Switch is Empty, OR
Quantity = Out Of Range
ANTI ICE PRESS
Serials w/ FIKI: Tail pressure is low
(TKS).
In NORM mode, one or more horizontal and/or
elevator tip panels is not receiving adequate
pressure.
• Horizontal Pressure < 2.0 psi
• Elevator Tip Pressure < 1.5 psi
In HIGH/MAX/PUMP BKUP mode, one or more
horizontal and/or elevator tip panels is not
receiving adequate pressure.
• Horizontal Pressure < 2.0 psi
• Elevator Tip Pressure < 1.5 psi
ANTI ICE PRESS
Serials w/ FIKI: Pressure is high
(TKS).
In NORM/HIGH/PUMP BKUP mode, the high
pressure switch between the filter and metering
pumps senses excessive pressure Sensed
Pressure > 150 psi.
ANTI ICE QTY
Serials w/ FIKI: Fluid quantity imbalance has been detected (TKS)
LH/RH fluid quantity imbalance > 1.0 gal.
ANTI ICE QTY
Serials w/ Ice Protection: Fluid quan- In NORM/HIGH/MAX/PUMP BKUP mode the
tity is low (TKS)
total QTY < 1.0 gal.
ANTI ICE SPEED
Serials w/ FIKI: Airspeed is too low for With the system ON and Flaps at 0%, the indiice protection (TKS).
cated airspeed < 95 KIAS
ANTI ICE SPEED
Serials w/ FIKI: Airspeed is to high for With the system ON, indicated airspeed > 177
ice protection (TKS).
KIAS, OR true airspeed > 204 KTAS.
AP MISCOMPARE
Autopilot miscompare, autopilot is not Autopilot miscompare, autopilot is not available.
available.
Figure 31-502
CAS Caution Messages
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CIRRUS
CAS Caution Text
AIRPLANE MAINTENANCE MANUAL
Alerts Window Text
MODELS SR22 AND SR22T
Definition
AP/PFD DIF ADC
Autopilot and PFD are using different Autopilot and PFD are using different ADCs.
ADCs.
AP/PFD DIF AHRS
Autopilot and PFD are using different Autopilot and PFD are using different AHRSs.
AHRSs.
AVIONICS OFF
Avionics master switch is off.
Avionics master switch is off.
BATT 1
Check battery 1 current.
Battery 1 current is discharging at a rate > 4
amps for 30 seconds or more.
BRAKE TEMP
Brake temperature is high.
Brake temperature is between 270°F and 293°F
for more than 5 seconds.
CHT
Cylinder head temperature is high.
Temperature of one or more cylinder heads has
exceeded 420°F.
FLAP OVERSPEED Flaps are extended beyond airspeed Flaps at 100%, airspeed > 109 KIAS for 5
limitations.
seconds or more, OR Flaps at 50%, airspeed >
124 KIAS for 5 seconds or more.
FUEL FILTER
Fuel filter in bypass
The fuel filter is in bypass mode. The fuel filter
element must be replaced.
FUEL QTY
Check fuel tank levels.
Check fuel tank levels.
M BUS 1
Check main power bus 1.
Illumination of M BUS 1 indicates that the
alternator voltage output < 24.5v. This is usually
associated with an alternator failure.
M BUS 2
Check main power bus 2.
Illumination of M BUS 2 indicates that the
alternator voltage output < 24.5v. This is usually
associated with an alternator failure.
MAN PRESSURE
SR22T Serials: Check manifold pres- Manifold pressure > 36.5 inHg for 5 minutes OR
sure.
> 37.0 inHg for 2 minutes.
NO ADC MODES
Autopilot air data modes are not avail- Autopilot air data modes are not available.
able.
NO VERT MODES
Autopilot vertical modes are not avail- Autopilot vertical modes are not available.
able.
OIL PRESSURE
Oil pressure is out of range.
Oil pressure between 10 psi and 30 psi at or
above 1000 RPM. This message will appear
prior to engine start and should clear after
engine start.
OIL TEMP
Oil temperature is high.
Oil temperature > 235°F.
OXYGEN QTY
Serials w/ Oxygen: Oxygen quantity is Altitude > 10,000 ft and tank pressure < 800 psi.
low.
OXYGEN RQD
Serials w/ Oxygen: Oxygen is
required.
Oxygen is required.
Figure 31-502
CAS Caution Messages (Continued)
31-50
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CIRRUS
CAS Caution Text
AIRPLANE MAINTENANCE MANUAL
MODELS SR22 AND SR22T
Alerts Window Text
Definition
PARK BRAKE
Parking break is set.
Parking break is set.
PITOT HEAT FAIL
Pitot heat failure.
Pitot heat failure. Displayed when Pitot heat
switch is ON and Pitot heat current is not
detected.
PITOT HEAT REQD Pitot heat is required.
Displayed 20 seconds after system detects OAT
< 41°F (5°C) and Pitot Heat Switch is OFF.
START ENGAGED
Starter stuck engaged. MCU detects 24 VDC to
Starter 15 seconds after initial engagement.
Starter is engaged.
Figure 31-502
CAS Caution Messages (Continued)
CAS Advisory Text
Alerts Window Text
Definition
ALTITUDE SEL
Climbing away from selected altitude.
Climbing away from selected altitude for more
than 5 seconds.
ALTITUDE SEL
Descending away from selected altitude.
Descending away from selected altitude for
more than 5 seconds.
AOA FAIL
Serials w/ FIKI: Dynamic stall speed
band is not available.
The red airspeed tape on the PFD is no longer
dynamically adjusted by the lift transducer
and reverts to published stall speeds.
ARE YOU ALERT?
Are you alert?
No pilot interaction within a reasonable time
period.
COURSE SEL
Current track will not intercept selected Current track will not intercept selected
course.
course.
HIGH MP FF
Avoid fuel flow 18 to 30 GPH and MP
above 26”.
Avoid fuel flow 18 to 30 GPH and MP above
26”.
L FUEL QTY
Check left fuel tank level.
Left fuel quantity < 18 gallons.
OXYGEN LEFT ON
Serials w/ Oxygen: Oxygen system is
left on after shutdown.
Oxygen system is left on after shutdown.
OXYGEN QTY
Serials w/ Oxygen: Oxygen quantity is
low.
Altitude < 10,000 ft and tank pressure < 800
psi.
PUMP BACKUP
Serials w/ FIKI: Anti-ice backup pump
mode has been selected (TKS).
The system may be operating in two system
modes simultaneously.
R FUEL QTY
Check right fuel tank level.
Right fuel quantity < 18 gallons.
Figure 31-503
CAS Advisory Messages
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AIRPLANE MAINTENANCE MANUAL
Comparator Window Text
MODELS SR22 AND SR22T
Condition
ALT MISCOMP
Difference in altitude sensors > 200 ft. If both airspeed sensors
detect < 35 knots, this is inhibited.
IAS MISCOMP
If either airspeed sensor detects > 35 knots, and the difference in
sensors > 10 kts. If either airspeed sensor detects > 80 knots, and
the difference in sensors > 7 knots.
HDG MISCOMP
Difference in heading sensors > 6 degrees.
PIT MISCOMP
Difference in pitch sensors > 5 degrees.
ROL MISCOMP
Difference in roll sensors > 6 degrees.
ALT NO COMP
No data from one or both altitude sensors.
IAS NO COMP
No data from one or both airspeed sensors.
HDG NO COMP
No data from one or both heading sensors.
PIT NO COMP
No data from one or both pitch sensors.
ROL NO COMP
No data from one or both roll sensors.
Figure 31-504
CAS Comparator Window Messages
Reversionary Sensor Window Text
Condition
USING ADC2
The PFD is displaying data from the #2 Air Data Computer.
USING AHRS2
The PFD is displaying data from the #2 AHRS.
Figure 31-505
CAS Reversionary Sensor Messages
Alerts Window Message
Condition
ANTI ICE QTY – Fluid quantity is low
(TKS).
Serials w/ Ice Protection: While system is OFF, the total QTY < 1.0
gal.
CO DET FAIL – The carbon monoxide
detector is inoperative.
Carbon monoxide detector fault.
CO DET SRVC – The carbon monoxide
detector needs service.
Carbon monoxide detector fault.
ESP CONFIG – ESP config error. Config ENABLE / unlock mis-match for ESP. Software for ESP option was
service required.
not installed as specified in Service Bulletin 2X-22-07.
ESP FAIL – ESP is inoperative.
GFC 700 is unavailable.
ESP OFF – ESP selected off.
Pilot DISABLED ESP.
ESP DEGRADE – ESP IAS mode is inop- ADC failure, limited GFC availability.
erative.
Figure 31-506
CAS Alerts Messages
31-50
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CIRRUS
AIRPLANE MAINTENANCE MANUAL
Alerts Window Message
MODELS SR22 AND SR22T
Condition
EXIT ICING – Exit icing conditions.
Serials w/ Ice Protection: The system has been operating for 30
min continuously.
FAILED PATH – An autopilot servo data
path has failed.
Servo or servo wiring fault.
MFD FAN FAIL – The cooling fan for the
MFD is inoperative.
PFD FAN FAIL – The cooling fan for PFD
is inoperative.
Figure 31-506
CAS Alerts Messages (Continued)
EFFECTIVITY:
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CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODELS SR22 AND SR22T
3. MAINTENANCE PRACTICES
A. Annunciator Panel - Serials w/o Perspective Avionics (See Figure 31-507)
(1)
Removal - Annunciator Panel
(a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.
(b) Pull ANNUNCIATOR PANEL circuit breaker.
(c)
Remove glareshield. (Refer to 25-10)
(d) Remove dress nut and washers securing annunciator toggle switch to instrument panel.
(e) Disconnect electrical connector from annunciator.
(f)
Serials 22-1036 thru 22-3025 w/ TAWS, 22-3026 & subs w/ TAWS and w/o Perspective
Avionics: Disconnect LED wire harness.
Note:
(2)
(3)
Label all wires and pins before disconnecting to facilitate re-installation.
1
Disconnect J703 connector from wire harness.
2
At S500 connector, depin LED wires at pin locations 1 and 3.
(g) Remove screws, washers, and nuts securing annunciator to instrument panel. Remove
annunciator from airplane.
Installation - Annunciator Panel
(a) Position annunciator to instrument panel and secure with screws, washers, and nuts.
(b) Serials 22-1036 thru 22-3025 w/ TAWS, 22-3026 & subs w/ TAWS and w/o Perspective
Avionics: Connect LED wire harness.
1
At S500 connector, pin LED wires at pin locations 1 and 3.
2
Connect J703 connector to wire harness.
(c)
Connect electrical connector to annunciator.
(d) Install washer on toggle switch and position on instrument panel so keyway on switch
faces down. Install washer and dress nut.
(e) Install glareshield. (Refer to 25-10)
(f)
Reset ANNUNCIATOR PANEL circuit breaker.
(g) Perform Functional Test - Annunciator Panel. (Refer to 31-50)
Functional Test - Annunciator Panel
(a) Ensure that all flight controls are clear.
(b) Connect 28 ±1 VDC external power to external power receptacle.
(c)
Pull STARTER RELAY and FUEL PUMP RELAY circuit breaker.
(d) Set BAT 1, BAT 2, and AVIONICS switches to ON positions.
(e) Set annunciator switch to center BRIGHT position.
(f)
If each tank has less than 14 gallons, ensure FUEL annunciator light is on.
(g) Ensure OIL annunciator light is on.
(h) Check functionality of LOW VOLTS annunciator.
1
Turn off external power supply.
Note:
2
(i)
(j)
(k)
31-50
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If system voltage is less than 24.5 ±2.0 VDC, the LOW VOLTS
annunciator light is on.
Turn on large electrical loads (landing light, nav lights, pitot heat, etc.) until the LOW
VOLTS annunciator light is on.
3
Turn off loads and turn on external power supply.
Ensure ALT 1 annunciator light is on.
Ensure ALT 2 annunciator light is on.
Ensure PITOT HEAT annunciator light is off.
EFFECTIVITY:
Serials w/o Perspective Avionics
CIRRUS
AIRPLANE MAINTENANCE MANUAL
(l)
Set annunciator switch to DIM position.
Annunciator lights will dim.
(m)
Set annunciator switch to TEST position.
Annunciator lights will brighten.
(n)
Ensure annunciator legends and colors are correct.
(o)
OIL
Red
LOW VOLTS
Red
FUEL
Amber
PITOT HEAT
Amber
ALT 1
Amber
ALT 2
Amber
MODELS SR22 AND SR22T
Disconnect 28 ±1 VDC external power from external power receptacle.
EFFECTIVITY:
Serials w/o Perspective Avionics
31-50
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AIRPLANE MAINTENANCE MANUAL
MODELS SR22 AND SR22T
2
5
4
2
6
7
1
2
2
3
INSTRUMENT PANEL (REF)
LEGEND
1. Dress Nut
2. Washer
3. Screw
4. Toggle Switch
5. Nut
6. Electrical Connector
7. Annunciator
NOTE
Keyway on toggle switch faces down.
Serials 22-0002 thru 22-0434, 22-0435 thru 22-0820 w/o PFD.
SR22_MM31_2001B
Figure 31-507
Annunciator Panel - Serials 22-0002 thru 22-0820 w/o PFD (Sheet 1 of 2)
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CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODELS SR22 AND SR22T
2
5
P703
(REF)
J703
(REF)
6
7
4
2
3
2
2
1
4
INSTRUMENT PANEL
(REF)
NOTE
Keyway on toggle switch faces down.
At S500 connector, depin wires at pin locations 1 and 3.
LEGEND
1. Dress Nut
2. Washer
3. Screw
4. Toggle Switch, (S500)
5. Nut
6. Electrical Connector
7. Annunciator
8. Push Button Switch
SR22_MM31_1622B
Figure 31-507
Annunciator Panel - Serials 22-0435-0820 w/ PFD, 22-0821-3026 & subs w/o Perspective Avionics (Sheet 2 of 2)
EFFECTIVITY:
Serials 22-0435-0820 w/ PFD, 22-0821-3026 & subs
w/o Perspective Avionics
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AIRPLANE MAINTENANCE MANUAL
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MODELS SR22 AND SR22T
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