Cirrus Sr22 Maintenance Manual Download
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M-6007-A50NA 5.0L Engine Assembly NO PART OF THIS DOCUMENT MAY BE REPRODUCED WITHOUT PRIOR AGREEMENT AND WRITTEN PERMISSION OF FORD RACING PERFORMANCE PARTS Techline 1-800-367-3788 Page 2 of 11 IS-1850-0377 Factory Ford shop manuals are available from Helm Publications, 1-800-782-4356. The 170/200ci engines had an orange valve cover and air cleaner, and a black block prior to 1965. From 1965 onwards the 170/200ci engines had a Ford blue valve cover, air cleaner, and block. Some early 170/200ci motors had an orange oil pan as well. The 250ci engine came with a Ford blue valve cover, air cleaner, and block. Ford mustang 170 ci engine pdf download.
CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22 24-30 Page 3 All EFFECTIVITY: A. Alternator 1 (See Figure 24-302) The front alternator (alternator 1) is. This manual reflects the operation of System Software version 0764.08 or later for the Cirrus SR20, SR22, and SR22T. Some differences in operation may be observed when comparing the information in this manual to earlier or later software versions. Garmin International, Inc., 1200 East 151st Street, Olathe, Kansas 66062, U.S.A.
Download Maintenance manual of Cirrus SR22T Aircrafts, Remote Control for Free or View it Online on All-Guides.com.
Brand: Cirrus
Category: Aircrafts , Remote Control
Type: Maintenance manual
Cirrus Sr22 Parts Manual Download
Model: Cirrus SR22T , Cirrus SR22
Pages: 6
CIRRUSAIRPLANE MAINTENANCE MANUALMODELS SR22 AND SR22T
Page 1
EFFECTIVITY:
1.DESCRIPTION
This section describes those components used for computing data from a number of different sources
without a preponderance of functions in any one system. This includes the GIA 63W integrated avionics
The airplane is equipped with two GIA 63W integrated avionics units located behind the PFD and MFD,
respectively. The GIA 63W functions as the main communications hub for the Perspective Avionics system,
linking all system components with the PFD and MFD. The main processor interfaces with all of the Per-
spective Avionics components and performs calculations for the GFC 700 autopilot. The integrated avion-
ics units are not paired together and do not communicate with each other directly.
Each GIA 63W integrated avionics unit contains the following:
•A VHF COM transceiver that provides tuning from 118.00 to 136.975 MHz in 25 kHz or 8.33 kHz spac-
ing for 760 or 3040 channel configuration respectively.
•A VOR/ILS localizer receiver that provides tuning from 108.00 to 117.95 MHz in 50 kHz increments.
•An ILS glideslope receiver that provides tuning from 328.6 to 335.4 MHz as paired with the frequency
•A flight director system if optional automatic flight control system is installed.
28 VDC for GIA 63W integrated avionics unit 1 operation is supplied through the 7.5-amp COM 1 and 5-
amp GPS NAV GIA 1 circuit breakers on Essential Bus 1. 28 VDC for GIA 63W integrated avionics unit 2
operation is supplied through the 7.5-amp COM 2 and 5-amp GPS NAV GIA 2 circuit breakers on Main Bus
The GIA 63W integrated avionics unit is integral to the Perspective Integrated Avionics system. For an
overview of the Perspective Avionics system, refer to Chapter 42, Integrated Modular Avionics. (Refer to
15 Jun 2010
Cirrus Sr22 Illustrated Parts Manual
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CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
ENGINE INDICATING 1. GENERAL This chapter describes those components which indicate engine operation. The engine indicating components include the tachometer, MAP/fuel flow gage and sensor, EGT/CHT gage and sensors, sensor interface unit (SIU), and data acquisition unit (DAU). Serials 0002 thru 1662: Engine crankshaft speed is indicated by an electrically operated tachometer which receives a speed signal from the RH magneto. Manifold pressure (MAP) is indicated by a MAP/fuel flow gage which receives a signal from a sensor mounted in the engine manifold. Exhaust gas temperature (EGT) is indicated by an EGT/CHT gage which receives a signal from a sensor mounted in cylinder #4 exhaust pipe. Cylinder head temperature (CHT) is indicated by an EGT/CHT gage which receives a signal from a sensor mounted in the #6 cylinder head. Serials 0002 thru 1662 w/ EMax™ Engine Monitoring: Engine crankshaft speed is indicated by an electrically operated tachometer and by the MFD. Both indications receive a speed signal from the RH magneto. Manifold pressure (MAP) is indicated by a MAP/fuel flow gage and by the MFD. Both indications receive a signal from a sensor mounted in the engine manifold. Exhaust gas temperature (EGT) is indicated by the MFD which receives signals from six individual sensors (one per exhaust header). Cylinder head temperature (CHT) is indicated by the MFD which receives signals from six individual sensors (one per cylinder). The Sensor Interface Unit (SIU) decodes the sensor information and transmits the data to the MFD. Serials 1663 & subs: Engine crankshaft speed is indicated by the PFD and MFD which receive a speed signal from the RH magneto. Manifold pressure (MAP) is indicated by the PFD and MFD which receive a signal from a sensor mounted in the engine manifold. Exhaust gas temperature (EGT) is indicated by the MFD which receives a signal from a sensor mounted in the #4 cylinder exhaust pipe. Cylinder head temperature (CHT) is indicated by the MFD which receives a signal from a sensor mounted in the #6 cylinder head. The Data Acquisition Unit (DAU) decodes the sensor information and transmits the data to the PFD and MFD. Serials 1663 & subs w/ EMax™ Engine Monitoring: Engine crankshaft speed is indicated by the PFD and MFD which receive a speed signal from the RH magneto. Manifold pressure (MAP) is indicated by the PFD and MFD which receive a signal from a sensor mounted in the engine manifold. Exhaust gas temperature (EGT) is indicated by the MFD which receives signals from six individual sensors (one per cylinder exhaust pipe). Cylinder head temperature (CHT) is indicated by the MFD which receives signals from six individual sensors (one per cylinder). The Data Acquisition Unit (DAU) decodes the sensor information and transmits the data to the PFD and MFD.
EFFECTIVITY: All
77-00
Page 1 15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
2. TROUBLESHOOTING Trouble No RPM indication.
Probable Cause Tachometer circuit breaker open.
Engine Monitoring System indica- OAT Sensor not properly tions disappear during flight into grounded. clouds or precipitation.
77-00
Page 2 15 Apr 2007
EFFECTIVITY: All
Remedy Check circuit breaker. Verify resistance from OAT sensor case to airplane ground is less than 2.0 ohms. If resistance is greater than 2.0 ohms, burnish OAT sensor backshell contact as required. Ensure backshell is secured tightly to sensor assembly.
CIRRUS
Tachometer
RH Magneto
AIRPLANE MAINTENANCE MANUAL
MAP/Fuel Flow GAGE
MAP Sensor
Fuel Flow Sensor
MODEL SR22
Oil Pressure/Temperature Gage
Oil Temperature Sensor
Oil Pressure Sensor
EGT/CHT Gage
EGT Sensor #4 Cylinder
CHT Sensor #6 Cylinder
Serials 0002 thru 1601, 1603 thru 1643, 1645 thru 1662, w/o EMax Engine Monitoring.
SR22_MM77_2238A
Figure 77-001 Engine Indicating Schematic - Serials 0002 thru 1662 w/o EMax Engine Monitoring (Sheet 1 of 3) EFFECTIVITY: Serials 0002 thru 1662 w/o EMax Engine Monitoring
77-00
Page 3 15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
MAP/Fuel Flow GAGE
Avidyne MFD
Oil Pressure/Temperature Gage
Tachometer
Sensor Interface Unit
EGT Sensor Cylinders 1-6
CHT Sensor Cylinders 1-6
MAP Sensor
Fuel Flow Sensor
Oil Pressure Sensor
Oil Temperature Sensor
Serials 0300 thru 1601, 1603 thru 1643, 1645 thru 1662 w/ EMax Engine Monitoring.
RH Magneto SR22_MM77_2240A
Figure 77-001 Engine Indicating Schematic - Serials 0300 thru 1662 w/ EMax Engine Monitoring (Sheet 2 of 3)
77-00
Page 4 15 Apr 2007
EFFECTIVITY: Serials 0300 thru 1662 w/ EMax Engine Monitoring
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
Avidyne PFD
Avidyne MFD
Data Aquisition Unit
RH Magneto
Oil Pressure Sensor
MAP Sensor
Fuel Flow Sensor
Oil Temperature Sensor
EGT Sensor #4 Cylinder
CHT Sensor #6 Cylinder
NOTE EMax equipped airplanes have EGT and CHT sensors mounted to all six cylinders.
SR22_MM77_2242A
Figure 77-001 Engine Indicating Schematic - Serials 1663 & subs (Sheet 3 of 3) EFFECTIVITY: Serials 1663 & subs
77-00
Page 5 15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
Intentionally Left Blank
77-00
Page 6 15 Apr 2007
EFFECTIVITY: All
MODEL SR22
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
ENGINE INDICATING 1. GENERAL This chapter describes those components which indicate engine operation. The engine indicating components include the tachometer, MAP/fuel flow gage and sensor, EGT/CHT gage and sensors, sensor interface unit (SIU), and data acquisition unit (DAU). Serials 0002 thru 1662: Engine crankshaft speed is indicated by an electrically operated tachometer which receives a speed signal from the RH magneto. Manifold pressure (MAP) is indicated by a MAP/fuel flow gage which receives a signal from a sensor mounted in the engine manifold. Exhaust gas temperature (EGT) is indicated by an EGT/CHT gage which receives a signal from a sensor mounted in cylinder #4 exhaust pipe. Cylinder head temperature (CHT) is indicated by an EGT/CHT gage which receives a signal from a sensor mounted in the #6 cylinder head. Serials 0002 thru 1662 w/ EMax™ Engine Monitoring: Engine crankshaft speed is indicated by an electrically operated tachometer and by the MFD. Both indications receive a speed signal from the RH magneto. Manifold pressure (MAP) is indicated by a MAP/fuel flow gage and by the MFD. Both indications receive a signal from a sensor mounted in the engine manifold. Exhaust gas temperature (EGT) is indicated by the MFD which receives signals from six individual sensors (one per exhaust header). Cylinder head temperature (CHT) is indicated by the MFD which receives signals from six individual sensors (one per cylinder). The Sensor Interface Unit (SIU) decodes the sensor information and transmits the data to the MFD. Serials 1663 & subs: Engine crankshaft speed is indicated by the PFD and MFD which receive a speed signal from the RH magneto. Manifold pressure (MAP) is indicated by the PFD and MFD which receive a signal from a sensor mounted in the engine manifold. Exhaust gas temperature (EGT) is indicated by the MFD which receives a signal from a sensor mounted in the #4 cylinder exhaust pipe. Cylinder head temperature (CHT) is indicated by the MFD which receives a signal from a sensor mounted in the #6 cylinder head. The Data Acquisition Unit (DAU) decodes the sensor information and transmits the data to the PFD and MFD. Serials 1663 & subs w/ EMax™ Engine Monitoring: Engine crankshaft speed is indicated by the PFD and MFD which receive a speed signal from the RH magneto. Manifold pressure (MAP) is indicated by the PFD and MFD which receive a signal from a sensor mounted in the engine manifold. Exhaust gas temperature (EGT) is indicated by the MFD which receives signals from six individual sensors (one per cylinder exhaust pipe). Cylinder head temperature (CHT) is indicated by the MFD which receives signals from six individual sensors (one per cylinder). The Data Acquisition Unit (DAU) decodes the sensor information and transmits the data to the PFD and MFD.
EFFECTIVITY: All
77-00
Page 1 15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
2. TROUBLESHOOTING Trouble No RPM indication.
Probable Cause Tachometer circuit breaker open.
Engine Monitoring System indica- OAT Sensor not properly tions disappear during flight into grounded. clouds or precipitation.
77-00
Page 2 15 Apr 2007
EFFECTIVITY: All
Remedy Check circuit breaker. Verify resistance from OAT sensor case to airplane ground is less than 2.0 ohms. If resistance is greater than 2.0 ohms, burnish OAT sensor backshell contact as required. Ensure backshell is secured tightly to sensor assembly.
CIRRUS
Tachometer
RH Magneto
AIRPLANE MAINTENANCE MANUAL
MAP/Fuel Flow GAGE
MAP Sensor
Fuel Flow Sensor
MODEL SR22
Oil Pressure/Temperature Gage
Oil Temperature Sensor
Oil Pressure Sensor
EGT/CHT Gage
EGT Sensor #4 Cylinder
CHT Sensor #6 Cylinder
Serials 0002 thru 1601, 1603 thru 1643, 1645 thru 1662, w/o EMax Engine Monitoring.
SR22_MM77_2238A
Figure 77-001 Engine Indicating Schematic - Serials 0002 thru 1662 w/o EMax Engine Monitoring (Sheet 1 of 3) EFFECTIVITY: Serials 0002 thru 1662 w/o EMax Engine Monitoring
77-00
Page 3 15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
MAP/Fuel Flow GAGE
Avidyne MFD
Oil Pressure/Temperature Gage
Tachometer
Sensor Interface Unit
EGT Sensor Cylinders 1-6
CHT Sensor Cylinders 1-6
MAP Sensor
Fuel Flow Sensor
Oil Pressure Sensor
Oil Temperature Sensor
Serials 0300 thru 1601, 1603 thru 1643, 1645 thru 1662 w/ EMax Engine Monitoring.
RH Magneto SR22_MM77_2240A
Figure 77-001 Engine Indicating Schematic - Serials 0300 thru 1662 w/ EMax Engine Monitoring (Sheet 2 of 3)
77-00
Page 4 15 Apr 2007
EFFECTIVITY: Serials 0300 thru 1662 w/ EMax Engine Monitoring
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
Avidyne PFD
Avidyne MFD
Data Aquisition Unit
RH Magneto
Oil Pressure Sensor
MAP Sensor
Fuel Flow Sensor
Oil Temperature Sensor
EGT Sensor #4 Cylinder
CHT Sensor #6 Cylinder
NOTE EMax equipped airplanes have EGT and CHT sensors mounted to all six cylinders.
SR22_MM77_2242A
Figure 77-001 Engine Indicating Schematic - Serials 1663 & subs (Sheet 3 of 3) EFFECTIVITY: Serials 1663 & subs
77-00
Page 5 15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
Intentionally Left Blank
77-00
Page 6 15 Apr 2007
EFFECTIVITY: All
MODEL SR22
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