CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 5-30: AIRPLANE OPERATIONAL AND FUNCTIONAL TEST
VISION SF50 GENERAL
Airplane Operational and Functional Test
5-30: AIRPLANE OPERATIONAL AND FUNCTIONAL CHECK
1. General
The following test must be performed before and after the Scheduled Maintenance Inspection to
detect any airplane abnormalities or malfunctions. A portion of the test is accomplished with the
engine running and warmed up.
The technician performing these tests must initial each box in the appropriate column to indicate
completion of that step. Note any abnormalities in the notes column on the right. Spaces at the
end of the checklist are provided for recording engine parameters.
• WARNING •
In order to perform the following test the engine must be operating. Do not stand or let
anyone else stand within the danger area of the engine exhaust while conducting this
test.
Clear danger area aft of engine by 85 ft (26 m) wide and 208 ft (63 m) long during any
ground engine operation. Refer to Airplane Flight Manual, Section 2.
• CAUTION •
During all engine operations outlined in this test, use caution to avoid harm or damage to
personnel and equipment due to engine exhaust and rotating turbine blades.
Excessive engine temperatures must be avoided since run-up temperatures must closely parallel
in-flight temperatures.
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03 Dec 2018
CHAPTER 5-30: AIRPLANE OPERATIONAL AND FUNCTIONAL TEST CIRRUS AIRPLANE MAINTENANCE MANUAL
GENERAL VISION SF50
Initial Final
Operational Inspection Report Chk Chk Notes
1. Battery 2 Master Switch
When switch is toggled ON the following should occur:
a. PFD indicates at least 24 volts on Emergency Bus.
b. MAIN BUS caution message is displayed on PFD.
c. AHRS aligns and COM 1 / NAV 1 are operational.
d. Standby attitude gyro aligned within five minutes.
2. Battery 1 Master Switch
When switch is toggled ON the following should occur:
a. Engine parameters on MFD are operational, Man “Hg display should
indicate approximately the altimeter setting.
b. Turn battery 2 to OFF position and verify PFD and MFD remain functional.
c. Verify MFD indicates at least 24 volts on Main bus, Essential Bus, and
Emergency Bus.
3. Lighting
Verify lighting controls, avionics light sensors and lights operate properly:
a. Landing lights.
b. Position lights.
c. Anti-collision lights.
d. Ice detection light.
e. Panel lighting: panel and overhead, circuit breaker, and CAPS handle
lights.
f. Task lights.
g. Avionics brightness: Emergency Overhead Panel and autopilot.
h. PFD, MFD display and GTC brightness.
4. Pitot / Stall AOA Heat
Set PITOT HEAT switch to ON position. The Pitot tube and Stall Vane must
be noticeably warm within 10 seconds after the pitot heat is switched on.
5. AOA / Stall Vane
Pull “Stall Warning” circuit breaker - Verify AOA fail.
Turn on Pitot Heat switch.
Pull Stall/AOA heat circuit breaker - Verify “Stall/Anti Ice HTR”.
6. Oxygen System
Confirm Oxygen system is charged. Test system pressure. Verify flow from
pilot and passenger ports. Verify O2 flow stops when switch is shut off.
7. Ice Protection System
Momentarily press WINDSHLD IPS MAX push button and verify evidence of
IPS fluid from windshield spray bar and radome spray nozzle.
8. Flight Controls
Test for full range of travel and excessive friction. Visual Inspection for
obstructions.
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24 Mar 2023
CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 5-30: AIRPLANE OPERATIONAL AND FUNCTIONAL TEST
VISION SF50 GENERAL
Initial Final
Operational Inspection Report (Continued) Chk Chk Notes
9. Communications
a. Verify all headset jacks operate properly.
b. Music is muted during transmissions and receptions.
c. Verify communications capability on both high and low ends of VHF COM
band.
10. Environmental System
Fan operates with increasing velocity at appropriate control location.
Defog Control alters airflow appropriately.
If equipped, AC selection starts condenser fan, illuminates light.
If equipped, Verify AC recirculate position opens the evaporator doors.
All controls operate smoothly and effectively with positive detents.
11. Engine Controls
Test full range of motion without any obstruction or excessive friction to
travel. Power lever should have positive clearance to the console slot in
both the full forward and full aft positions.
12. Start Engine (Refer to AFM Section 4)
Before pressing ENGINE START/STOP button, audibly verify fuel pump
operation.
13. Ice Protection System
Set WING/STAB IPS system switch to ON position and verify LH and RH
stabilizer, LH and RH wing (lower) and LH and RH wing (upper) deice boots
inflate.
14. Flaps
Operate through full extension and retraction for steady and complete
deployment. Flap position indication on EIS corresponds to physical 50%,
and 100% flap positions.
15. Trim Controls
Aileron trim functions fully left and right without rudder movement caused
by the rudder-aileron interconnect. Test for full range of travel and
excessive friction.
16. Altimeter
Indicates within 50 feet of field elevation when set to correct barometric
pressure setting.
17. Vertical Speed Indicator
Indicates zero.
18. Starter/Generator (GEN 1) Load (Air Conditioning OFF)
The GEN 1 annunciation will appear when Main Bus voltage is below 24.5
volts and output is less than 5 amps. When GEN 1 is turned off, Main Bus
voltage will indicate battery 1 voltage.
19. Alternator (GEN 2) Load
During normal operating conditions (AC off ) GEN 2 will indicate a larger
load than GEN 1. There will be an GEN 2 annunciation when the GEN 2 load
is less than 4 amps. When GEN 2 is not operating, GEN 1 will carry the entire
electrical load.
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22 Oct 2020
CHAPTER 5-30: AIRPLANE OPERATIONAL AND FUNCTIONAL TEST CIRRUS AIRPLANE MAINTENANCE MANUAL
GENERAL VISION SF50
Initial Final
Operational Inspection Report (Continued) Chk Chk Notes
20. Fuel Selector Valve
Move selector to RIGHT and LEFT positions. Verify fuel flow.
21. Engine Full Power
Advance thrust lever to full forward. Test N1 in accordance with power
setting charts.
22. Fuel Flow
Advance thrust lever to full forward. Verify fuel flow indicates in green
range.
23. Oil Temperature
Indicates in the green range.
24. ITT (Inter Turbine Temperature)
Verify temperature indicates in green range.
25. Brakes
Rudder pedal brakes should hold airplane stationary with no slipping at full
power. Parking brake should hold airplane stationary with no slipping at
full power.
26. Engine Idle
Move thrust lever to full aft. Test N2 in accordance with power setting
charts.
27. Engine Shut Down
Allow engine to run at ground idle for 2 minutes and perform Shutdown
checklist. (Refer to AFM Section 4)
The following tables are for recording engine parameters.
Initial Operational Test Engine Parameters
N1% Engine N2% Engine ITT Full Power Oil Oil Pt2 Tt2
Full Power Idle Fuel Flow Temp Pressure
Final Operational Test Engine Parameters
N1% Engine N2% Engine ITT Full Power Oil Oil Pt2 Tt2
Full Power Idle Fuel Flow Temp Pressure
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