Transcript
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
DEPENDENT POSITION DETERMINING 1. DESCRIPTION This section covers that portion of the system which provides information to determine position from sources which are mainly dependent on ground installations. This includes the GPS transceivers, transponder, course deviation indicator (CDI), VOR/LOC antenna, and HSI components. •
GPS Transceivers Two VHF communications (COM) transceivers and integrated controls are mounted in dual Garmin GNS 430 units or Garmin GNS 430/GNC 420 units to provide VHF communication. The transceivers receive all narrow- and wide-band VHF communication transmissions transmitted within range of the selected frequency. The antennas pick up the signals and route the communication signals to the transceivers, which digitize the audible communication signal. The digitized audio is then routed to the audio control unit for distribution to the speakers or headphones. The Garmin GNC 420 is an IFR certified VHF communications transceiver and GPS sensor. The transceiver incorporates a GPS sensor and includes two removable data cards, one with a Jeppesen data base, and the second being a custom data card. GPS signals are received by an antenna mounted inside the fuselage under the instrument console. The Garmin GNS 430 is an IFR certified VHF communications transceiver and Navigation Management System (NMS). The NMS includes GPS sensor, VOR/Localizer and Glideslope receivers. The GNS 430 includes two removable data cards, one with a Jeppesen data base, and the second being a custom data card. GPS signals are received by an antenna mounted inside the fuselage under the forward headliner or by an antenna mounted inside the fuselage under the instrument console. Serials w/ GNS 430/GNC 420 units: For upper GNS 430 designated as COM 1, 28 VDC is supplied through the 5-amp GPS 1 and 7.5-amp COM 1 circuit breakers on the Avionics Essential Bus. For lower GNC 420 designated as COM 2, 28 VDC is supplied through the 5-amp GPS 2 and 7.5-amp COM 2 circuit breakers on the Avionics Non-Essential Bus. Serials w/ dual GNS 430 units: For upper GNS 430 designated as COM 1, 28 VDC is supplied through the 5-amp GPS 1 and 7.5-amp COM 1 circuit breakers on the Avionics Essential Bus. For lower GNS 430 designated as COM 2, 28 VDC is supplied through the 5-amp GPS 2 and 7.5-amp COM 2 circuit breakers on the Avionics Essential Bus. Refer to the manufacturer’s approved Instructions For Continued Airworthiness and/or other service instructions.
•
Transponder The Garmin GTX 327 (Serials 0002 & subs w/o Mode S) or Garmin GTX 330 (Serials 0821 & subs w/ Mode S, Serials 0435 & subs after SB 2X-34-09) transponder is mounted in the center console. The transponder receives interrogations from a ground-based secondary radar transmitter and transmits the airplane’s identification to the Air Traffic Control Center via Mode A transmissions and altitude information via Mode C. In addition, the GTX 330 transponder and Becker Mode S also send a unique aircraft address via Mode S to enhance the tracking capabilities of ATC and other Mode S transponderequipped aircraft. 28 VDC for receiver, transmitter, and altitude encoder operation is supplied through the 2-amp ENCODER/XPONDER circuit breaker on the Avionics Non-Essential Bus. Refer to the manufacturer’s approved Instructions For Continued Airworthiness and/or other service instructions.
•
Course Deviation Indicator (CDI) Serials 0002 thru 0434, 0435 thru 0820 w/o PFD: The Garmin GI-102(A) and GI-106(A) are panelmounted Course Deviation Indicators (CDI's) with rectilinear meter movements and integral GPS, NAV, and VLOC mode annunciators. Both units provide a VOR/LOC/GPS needle, TO/FROM indicator, NAV
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AIRPLANE MAINTENANCE MANUAL
MODEL SR22
warning flag, and an integral resolver for OBS feedback. The GI-106A also provides a GS needle and flag. 28 VDC for lighting is supplied through the 2-amp INST LIGHTS circuit breaker on Main Bus 1. •
Horizontal Situation Indicator (HSI/EHSI) Serials 0002 thru 0434, 0435 thru 0820 w/o PFD: The NSD-1000 HSI, located directly below the attitude indicator, has an electrically driven gyro slaved to a flux detector mounted in the right wing and an amplifier mounted under the copilot floor for continuous compass card correction. The HSI mode switch is mounted directly beneath the HSI to allow the pilot to select either SLAVE or FREE GYRO mode. The HSI displays a stable indication of the airplane heading to the pilot. 28 VDC for the redundant power circuits is supplied through the 5-amp HSI#1 circuit breaker on the Essential Bus and 5amp HSI#2 circuit breaker on Main Bus 2. Serials 0002 thru 0434, 0435 thru 0820 w/o PFD: The SN3308 EHSI is located directly below the attitude indicator and performs the functions of a standard HSI combined with a two-pointer RMI. The instrument also displays a moving map, marker beacon, WX500 stormscope data, and GPS data. The EHSI system includes a remote gyro located under the RH passenger seat which is slaved to a flux detector mounted in the right wing. 28 VDC for the redundant power circuits is supplied through the 5amp HSI#1 circuit breaker on the Essential Bus and 5-amp HSI#2 circuit breaker on Main Bus 2.
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AIRPLANE MAINTENANCE MANUAL
MODEL SR22
2. MAINTENANCE PRACTICES A. Garmin GNS 430 GPS/COM/NAV (See Figure 34-501) (1)
Removal - Garmin GNS 430 GPS/COM/NAV (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers. (c) Insert 3/32-inch hex wrench into front panel bolt hole and engage hex bolt. (d) Rotate locking screw counter-clockwise to loosen locking cam. Cam will move the transceiver unit out 0.25 inch (0.64 cm) and disengage from the electrical connectors. CAUTION:
(2)
For dual GNS or GNS/GNC configurations, note positions for GPS 1 and GPS 2 when originally installed transceivers will be replaced.
(e) Pull transceiver from mounting tray. Installation - Garmin GNS 430 GPS/COM/NAV CAUTION:
When mounting the transceivers, do not press on display window as damage may result. For dual GNS or GNS/GNC configurations, verify when replacing originally installed transceivers that GPS 1 and GPS 2 positions are retained.
(a)
(3)
With light to medium pressure, push transceiver into mounting tray to engage electrical connectors. (b) Insert 3/32-inch hex wrench into front panel bolt hole and engage hex bolt. (c) Rotate bolt clockwise to tighten locking cam. (d) Reset ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers. (e) If transceiver is a different unit from the originally installed transceiver: 1 Perform Functional Test - Garmin GNS 430 GPS/COM/NAV Setup. (Refer to 34-50) 2 Perform Functional Test - Garmin GNS 430 GPS/COM/NAV Clock Setup. (Refer to 34-50) 3 Perform Functional Test - Dual Garmin GNS 430 GPS/COM/NAV Crossfill Setup. (Refer to 34-50) 4 Perform Operational Test - Garmin GNS 430 GPS/COM/NAV VHF COM Check. (Refer to 34-50) (f) If transceiver is the same unit as the originally installed transceiver: 1 Perform Functional Test - Dual Garmin GNS 430 GPS/COM/NAV Crossfill Setup. (Refer to 34-50) 2 Perform Operational Test - Garmin GNS 430 GPS/COM/NAV VHF COM Check. (Refer to 34-50) Operational Test - Garmin GNS 430 GPS/COM/NAV VHF COM Check A flight test is recommended after the installation to verify satisfactory performance. To check the communications transceiver: (a) (b) (c) (d)
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Maintain an appropriate altitude and contact a ground station facility at a range of at least 50 nautical miles. Contact a close ground station. Press the squelch disable button to defeat the automatic squelch feature and listen for any unusual electrical noise which would increase the squelch threshold. If possible, confirm communications capability on both high and low ends of the VHF COM band.
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MODEL SR22
Functional Test - Garmin GNS 430 GPS/COM/NAV Setup (a) Connect 28 ±1 VDC external power to external power receptacle. (b) Set BAT 1, BAT 2, and AVIONICS switches to ON positions. (c) Pull STARTER RELAY and FUEL PUMP RELAY circuit breakers. (d) On dual GNS or GNS/GNC units, rotate [C] knobs for COM power counter-clockwise to OFF positions. Note: (e) (f) (g) (h) (i) (j) (k)
Right data card slot contains blank card.
On dual GNS or GNS/GNC units, verify data cards are installed for GPS 1 and GPS 2 in left data card slot. While holding [ENT], rotate [C] knobs for COM power clockwise to ON positions. Release [ENT] after display is on. After power-up, the Self Test pages will display, followed by the Database page. On dual GNS or GNS/GNC units, verify GPS 1 and GPS 2 have the same MAIN SOFTWARE VERSION, GPS SOFTWARE VERSION, and CYCLE numbers displayed. On the Database page, press [ENT]. On the Instrument Panel Self-Test page, press [ENT]. Navigate subsequent pages by use of GNS 430 controls. Note:
Only the GPS indicated by the NAV selection on the PFD will be displayed. Not all parameters are editable.
To turn on cursor, press inner dial of [CRSR] knob. To move between data fields, rotate outer dial of [CRSR] knob. To change a field that cursor is on, rotate inner dial of [CRSR] knob. To accept entry of current selection, press [ENT]. To turn off cursor before switching pages, press inner dial of [CRSR] knob. To switch between pages, rotate inner dial of [CRSR] knob. 1
Set parameters for the Main ARINC 429 Config page for GPS 1.
IN 1 - Serials 0002 thru 0820 w/ Century HSI
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SPEED
DATA
Low
Off
IN 1 - Serials 0002 thru 0820 w/ Sandel EHSI, Low 0435 thru 0820 w/PFD, 0821 & subs
Sandel EHSI
IN 2 - Serials 0002 & subs w/o SkyWatch
Low
Off
IN 2 - Serials 0002 & subs w/ SkyWatch
Low
Traffic Advisory
OUT
Low
GAMA 429 grph w/int
SDI
LNAV 1
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Set parameters for the Main ARINC 429 Config page for GPS 2. SPEED
DATA
IN 1 - Serials 0002 thru 0434, 0435 thru 0820 w/o PFD
Low
Off
IN 1 - Serials 0435 thru 0820 w/ PFD, 0821 & subs
Low
Sandel EHSI
IN 2 - Serials 0002 & subs w/o SkyWatch
Low
Off
IN 2 - Serials 0002 & subs w/ SkyWatch
Low
Traffic Advisory
OUT
Low
GAMA 429 grph w/int
SDI
LNAV 2
Set parameters for the Main RS232 Config page for GPS 1 and GPS 2. INPUT
OUTPUT
CHAN 1
Icarus-alt
Aviation
CHAN 2 - Serials 0002 & subs w/o TAWS
Off
Off
CHAN 2 - Serials 0002 & subs w/ TAWS
Off
HW EGPWS
CHAN 3
Crossfill
Crossfill
CHAN 4 - Serials 0002 & subs w/o Stormscope
Off
Off
CHAN 4 - Serials 0002 & subs w/ Stormscope
WX 500
Off
FUEL TYPE
AV gas
The Main Inputs 1 page is not used. The Main Inputs 2 page is not used. Set parameters for the Instrument Panel Self-Test page. LCDI
Half Left
LFLG
Out of View
TO/FRM
To
RMI
135°
DTK
150°
For the Main Lighting page, cover photocell and observe that display slowly dims and lighting values decrease. Note:
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MODEL SR22
Main Lighting page values may differ from those below due to your unique lighting environment.
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8
9 10
11 12
13
Set parameters for the Main Lighting page. DISPLAY
KEY
LIGHTING
0-9999
0-9999
SOURCE
PHOTO
28VDC
RESP TIME/MIN
4
080
4
40
SLOPE/OFFSET
50
50
50
50
Set parameters for the Date/Time Setup page. Set parameters for the Main Discrete Inputs page. GRAY CODE
00000000000
DECODED ALTITUDE
_ _ _ _ _ _ ft
RMT CDI
unchecked
RMT OBS
unchecked
The Main Discrete Outputs page is not used. Serials 0002 thru 0820 w/ Century HSI: Set parameters for the Main CDI/ OBS Config page. CDI
NAV FLAG
TO-FROM
LAT
Center
Hidden
Hidden
VERT
Center
Hidden
SELECTED COURSE
148°
CDI
GPS
OBI SOURCE
Track CDI
VERT
Flag Center
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Calibrate to 150°?
Serials 0002 thru 0820 w/ Century HSI: Toggle settings to verify outputs display correctly for the corresponding indicators.
LAT
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MODEL SR22
CDI
NAV FLAG
TO-FROM
Max Left Full Left Center Full Right Max Right
Hidden In View
From Hidden To
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AIRPLANE MAINTENANCE MANUAL
VERT
14 15 16 17 18 19 20 21
22
(l)
Max Up Full Up Center Full Down Max Down
MODEL SR22
Hidden In View
Serials 0002 thru 0820 w/ Century HSI: Set OBS dial on HSI to “150°”. Serials 0002 thru 0820 w/ Century HSI: Select “Calibrate To 150°?”, then press [ENT]. Serials 0002 thru 0820 w/ Century HSI: Set OBS to other headings around dial to verify correct readings. Serials 0002 thru 0820 w/ Sandel EHSI, 0435 thru 0820 w/ PFD, 0821 & subs: The Main CDI / OBS Config page is not used. The COM Setup page is not used. The VOR Discrete Inputs page is not used. The VOR / LOC / GS CDI page is not used. Set parameters for the VOR / LOC / GS ARINC 429 Config page for GPS 1. RX
TX
SPEED
Low
Low
SDI
VOR / ILS 1
DME MODE
Directed freq 1
Set parameters for the VOR / LOC / GS ARINC 429 Config page for GPS 2. RX
TX
SPEED
Low
Low
SDI
VOR / ILS 2
DME MODE
Directed freq 2
(m) (n)
When setup is completed, on dual GNS or GNS/GNC units, rotate [C] knobs for COM power counter-clockwise to OFF positions. Allow display to blank completely. On dual GNS or GNS/GNC units, rotate [C] knobs for COM power clockwise to ON positions. The Self-Test pages will be displayed followed by the Database page.
(o) (p)
On the Database page, press [ENT]. Set parameters on the Instrument Panel Self-Test page.
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LCDI
Half Left
LFLG
Out of View
VCDI
Half Up
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(r) (s)
(t) (u) (v)
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VFLG
Out of View
CAP
81gl
FOB
0gl
FF
0.0gl
TO/FRM
To
RMI
135°
OBS
150°
ANNUN
On
DTK
150°
MODEL SR22
Verify parameters for self-test data output by GNS 430 on the displays indicated. Display
Parameter
Self-Test
VOR/HSI/PFD
Course Deviation
½ scale left deviation, TO flag, NAV flag pulled
VOR/HSI - Serials 0002 thru 0434, Glidescope/ Vertical 0435 thru 0820 w/o PFD Deviation
½ scale up deviation, GS flag pulled
MFD/EHSI/PFD
Active Waypoint (WPT)
"GARMN"
MFD/EHSI/PFD
Distance To Go (DIS)
10.0 nautical miles
MFD/EHSI/PFD
Desired Track (DTK)
150°
MFD/EHSI/PFD
Bearing to Wpt (BRG)
135°
MFD/EHSI/PFD
Groundspeed (GS)
150 knots
MFD/EHSI - Serials 0002 thru 0434, 0435 thru 0820 w/o PFD
Track (TRK)
135°
MFD/EHSI/PFD
Time to Go (ETE)
4 minutes
On dual GNS or GNS/GNC units, press [ENT]. Upon approval of the Database page, the Satellite Status page will be displayed. Serials 0435 thru 0820 w/ PFD, 0821 & subs: Verify coupling between PFD and COM/ NAVs: 1 On PFD, press [Nav1] to select "GPS1". 2 Verify Nav1 selection on PFD matches CDI setting of "GPS" on GNS 430. 3 On PFD, press [Nav1] to select "VLOC1". 4 Verify CDI setting on GNS 430 changes to "VLOC". 5 On GNS 430, press [CDI] to select "GPS". 6 On PFD, verify Nav1 selection changes back to "GPS1". 7 Repeat coupling procedure for the lower GNS 430 or GNC 420. Reset STARTER RELAY and FUEL PUMP RELAY circuit breakers. Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. Disconnect 28 ±1 VDC external power from external power receptacle. EFFECTIVITY: All
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AIRPLANE MAINTENANCE MANUAL
MODEL SR22
Functional Test - Garmin GNS 430 GPS/COM/NAV Clock Setup (a) Set BAT 1 and AVIONICS switches to ON positions. (b) On GNS unit, rotate [C] knob for COM power clockwise to ON position. (c) After power-up, the Self Test pages will display, followed by the Database page. (d) On the Database page, press [ENT]. (e) On the Instrument Panel Self-Test page, press [ENT]. (f) Rotate outer dial of [CRSR] knob to select the first Aux (Flight Planning) page. (g) Rotate inner dial of [CRSR] knob to select the third Aux (Setup 1) page. (h) Press inner dial of [CRSR] knob to activate cursor. (i) Rotate inner dial of [CRSR] knob to select “Date / Time”, then press [ENT]. (j) Rotate inner dial of [CRSR] knob to highlight TIME FORMAT. (k) Rotate inner dial of [CRSR] knob to select "Local 24hr", then press [ENT]. (l) Rotate inner dial of [CRSR] knob to highlight TIME OFFSET. (m) Rotate inner dial of [CRSR] knob to select present UTC time, then press [ENT]. (n) Rotate [C] knob for COM power counter-clockwise to OFF position. (o) Set BAT 1 and AVIONICS switches to OFF positions. Functional Test - Dual Garmin GNS 430 GPS/COM/NAV Crossfill Setup (a) Set BAT 1 and AVIONICS switches to ON positions. (b) On GNS unit, rotate [C] knob for COM power clockwise to ON position. (c) Rotate outer right dial of [CRSR] knob to select the first Aux (Flight Planning) page. (d) Press inner right dial of [CRSR] knob to highlight the cursor. (e) Rotate inner right dial of [CRSR] knob to select "Crossfill", then press [ENT]. (f) Verify that status displayed is READY. (g) Rotate [C] knob for COM power counter-clockwise to OFF position. (h) Set BAT 1 and AVIONICS switches to OFF positions.
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B. Garmin GNC 420 GPS/COM (See Figure 34-501) (1)
Removal - Garmin GNC 420 GPS/COM (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers. (c) Insert 3/32-inch hex wrench into front panel bolt hole and engage hex bolt. (d) Rotate locking screw counter-clockwise to loosen locking cam. Cam will move the transceiver unit out 1/4-inch and disengage from the electrical connectors. CAUTION:
(2)
For dual GNS or GNS/GNC configurations, note positions for GPS 1 and GPS 2 when originally installed transceivers will be replaced.
(e) Pull transceiver from mounting tray. Installation - Garmin GNC 420 GPS/COM CAUTION:
When mounting the transceivers, do not press on display window as damage may result. For dual GNS or GNS/GNC configurations, verify when replacing originally installed transceivers that GPS 1 and GPS 2 positions are retained.
(a)
(3)
With light to medium pressure, push transceiver into mounting tray to engage electrical connectors. (b) Insert 3/32-inch hex wrench into front panel bolt hole and engage hex bolt. (c) Rotate bolt clockwise to tighten locking cam. (d) Reset ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers. (e) If transceiver is a different unit from the originally installed transceiver: 1 Perform Functional Test - Garmin GNC 420 GPS/COM Setup. (Refer to 34-50) 2 Perform Functional Test - Garmin GNC 420 GPS/COM Clock Setup. (Refer to 3450) 3 Perform Operational Test - Garmin GNC 420 GPS/COM VHF COM Check. (Refer to 34-50) (f) If transceiver is the same unit as the originally installed transceiver: 1 Perform Operational Test - Garmin GNC 420 GPS/COM VHF COM Check. (Refer to 34-50) Operational Test - Garmin GNC 420 GPS/COM VHF COM Check A flight test is recommended after the installation to verify satisfactory performance. To check the communications transceiver: (a)
(4)
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Maintain an appropriate altitude and contact a ground station facility at a range of at least 50 nautical miles. (b) Contact a close ground station. (c) Press the squelch disable button to defeat the automatic squelch feature and listen for any unusual electrical noise which would increase the squelch threshold. (d) If possible, confirm communications capability on both high and low ends of the VHF COM band. Functional Test - Garmin GNC 420 GPS/COM Setup (a) Connect 28 ±1 VDC external power to external power receptacle. (b) Set BAT 1, BAT 2, and AVIONICS switches to ON positions. (c) Pull STARTER RELAY and FUEL PUMP RELAY circuit breakers. (d) On GNS 430/GNC 420, rotate [C] knobs for COM power counter-clockwise to OFF positions. EFFECTIVITY: All
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AIRPLANE MAINTENANCE MANUAL
Note: (e) (f) (g) (h) (i) (j) (k)
MODEL SR22
Right data card slot contains blank card.
Verify data cards are installed for GPS 1 and GPS 2 in left data card slot. While holding [ENT], rotate [C] knobs for COM power clockwise to ON positions. Release [ENT] after display is on. After power-up, the Self Test pages will display, followed by the Database page. Verify GPS 1 and GPS 2 have the same MAIN SOFTWARE VERSION, GPS SOFTWARE VERSION, and CYCLE numbers displayed. On the Database page, press [ENT]. On the Instrument Panel Self-Test page, press [ENT]. Navigate subsequent pages by use of GNS 430/GNC 420 controls. Note:
Only the GPS indicated by the NAV selection on the PFD will be displayed. Not all parameters are editable.
To turn on cursor, press inner dial of [CRSR] knob. To move between data fields, rotate outer dial of [CRSR] knob. To change a field that cursor is on, rotate inner dial of [CRSR] knob. To accept entry of current selection, press [ENT]. To turn off cursor before switching pages, press inner dial of [CRSR] knob. To switch between pages, rotate inner dial of [CRSR] knob. 1
Set parameters for the Main ARINC 429 Config page for GPS 1.
IN 1 - Serials 0002 thru 0820 w/ Century HSI
2
EFFECTIVITY: All
SPEED
DATA
Low
Off
IN 1 - Serials 0002 thru 0820 w/ Sandel EHSI, Low 0435 thru 0820 w/PFD, 0821 & subs
Sandel EHSI
IN 2 - Serials 0002 & subs w/o SkyWatch
Low
Off
IN 2 - Serials 0002 & subs w/ SkyWatch
Low
Traffic Advisory
OUT
Low
GAMA 429 grph w/int
SDI
LNAV 1
Set parameters for the Main ARINC 429 Config page for GPS 2. SPEED
DATA
IN 1 - Serials 0002 thru 0434, 0435 thru 0820 w/o PFD
Low
Off
IN 1 - Serials 0435 thru 0820 w/ PFD, 0821 & subs
Low
Sandel EHSI
IN 2 - Serials 0002 & subs w/o SkyWatch
Low
Off
IN 2 - Serials 0002 & subs w/ SkyWatch
Low
Traffic Advisory
OUT
Low
GAMA 429 grph w/int
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SDI 3
4 5 6
7
Set parameters for the Main RS232 Config page for GPS 1 and GPS 2. INPUT
OUTPUT
CHAN 1
Icarus-alt
Aviation
CHAN 2
Off
Off
CHAN 3
Crossfill
Crossfill
CHAN 4 - Serials 0002 & subs w/o Stormscope
Off
Off
CHAN 4 - Serials 0002 & subs w/ Stormscope
WX 500
Off
FUEL TYPE
AV gas
The Main Inputs 1 page is not used. The Main Inputs 2 page is not used. Set parameters for the Instrument Panel Self-Test page. LCDI
Half Left
LFLG
Out of View
TO/FRM
To
RMI
135°
DTK
150°
For the Main Lighting page, cover photocell and observe that display slowly dims and lighting values decrease. Note:
8
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Main Lighting page values may differ from those below due to your unique lighting environment.
Set parameters for the Main Lighting page. DISPLAY
KEY
LIGHTING
0-9999
0-9999
SOURCE
PHOTO
28VDC
RESP TIME/MIN
4
080
4
40
SLOPE/OFFSET
50
50
50
50
Set parameters for the Date/Time Setup page. Set parameters for the Main Discrete Inputs page. GRAY CODE
34-50
LNAV 2
00000000000
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13
14 15 16 17 18 19 20
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DECODED ALTITUDE
_ _ _ _ _ _ ft
RMT CDI
unchecked
RMT OBS
unchecked
MODEL SR22
The Main Discrete Outputs page is not used. Serials 0002 thru 0820 w/ Century HSI: Set parameters for the Main CDI/ OBS Config page. CDI
NAV FLAG
TO-FROM
LAT
Center
Hidden
Hidden
VERT
Center
Hidden
SELECTED COURSE
148°
CDI
GPS
OBI SOURCE
Track CDI
VERT
Flag Center
Calibrate to 150°?
Serials 0002 thru 0820 w/ Century HSI: Toggle settings to verify outputs display correctly for the corresponding indicators. CDI
NAV FLAG
TO-FROM
LAT
Max Left Full Left Center Full Right Max Right
Hidden In View
From Hidden To
VERT
Max Up Full Up Center Full Down Max Down
Hidden In View
Serials 0002 thru 0820 w/ Century HSI: Set OBS dial on HSI to “150°”. Serials 0002 thru 0820 w/ Century HSI: Select “Calibrate To 150°?”, then press [ENT]. Serials 0002 thru 0820 w/ Century HSI: Set OBS to other headings around dial to verify correct readings. Serials 0002 thru 0820 w/ Sandel EHSI, 0435 thru 0820 w/ PFD, 0821 & subs: The Main CDI / OBS Config page is not used. The COM Setup page is not used. The VOR Discrete Inputs page is not used. The VOR / LOC / GS CDI page is not used.
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22
(l) (m) (n) (o) (p)
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MODEL SR22
Set parameters for the VOR / LOC / GS ARINC 429 Config page for GPS 1. RX
TX
SPEED
Low
Low
SDI
VOR / ILS 1
DME MODE
Directed freq 1
Set parameters for the VOR / LOC / GS ARINC 429 Config page for GPS 2. RX
TX
SPEED
Low
Low
SDI
VOR / ILS 2
DME MODE
Directed freq 2
When setup is completed, on GNS 430/GNC 420, rotate [C] knobs for COM power counter-clockwise to OFF positions. Allow display to blank completely. On GNS 430/GNC 420, rotate [C] knobs for COM power clockwise to ON positions. The Self-Test pages will be displayed followed by the Database page. On the Database page, press [ENT]. Set parameters on the Instrument Panel Self-Test page. LCDI
Half Left
LFLG
Out of View
VCDI
Half Up
VFLG
Out of View
CAP
81gl
FOB
0gl
FF
0.0gl
TO/FRM
To
RMI
135°
OBS
150°M
ANNUN
On
DTK
150°M
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MODEL SR22
Verify parameters for self-test data output by GNS 430/GNC 420 on the displays indicated. Display
Parameter
Self-Test
VOR/HSI/PFD
Course Deviation
½ scale left deviation, TO flag, NAV flag pulled
VOR/HSI - Serials 0002 thru 0434, Glidescope/ Vertical 0435 thru 0820 w/o PFD Deviation
½ scale up deviation, GS flag pulled
MFD/EHSI/PFD
Active Waypoint (WPT)
"GARMN"
MFD/EHSI/PFD
Distance To Go (DIS)
10.0 nautical miles
MFD/EHSI/PFD
Desired Track (DTK)
150°
MFD/EHSI/PFD
Bearing to Wpt (BRG)
135°
MFD/EHSI/PFD
Groundspeed (GS)
150 knots
MFD/EHSI - Serials 0002 thru 0434, 0435 thru 0820 w/o PFD
Track (TRK)
135°
MFD/EHSI/PFD
Time to Go (ETE)
4 minutes
(r)
On GNS 430/GNC 420, press [ENT]. Upon approval of the Database page, the Satellite Status page will be displayed. (s) Serials 0435 thru 0820 w/ PFD, 0821 & subs: Verify coupling between PFD and COM/ NAVs: 1 On PFD, press [Nav1] to select "GPS1". 2 Verify Nav1 selection on PFD matches CDI setting of "GPS" on GNS 430. 3 On PFD, press [Nav1] to select "VLOC1". 4 Verify CDI setting on GNS 430 changes to "VLOC". 5 On GNS 430, press [CDI] to select "GPS". 6 On PFD, verify Nav1 selection changes back to "GPS1". 7 If applicable, repeat coupling procedure for the lower GNC 420. (t) Reset STARTER RELAY and FUEL PUMP RELAY circuit breakers. (u) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (v) Disconnect 28 ±1 VDC external power from external power receptacle. (5) Functional Test - Garmin GNC 420 GPS/COM Clock Setup (a) Set BAT 1 and AVIONICS switches to ON positions. (b) On GNS unit, rotate [C] knob for COM power clockwise to ON position. (c) After power-up, the Self Test pages will display, followed by the Database page. (d) On the Database page, press [ENT]. (e) On the Instrument Panel Self-Test page, press [ENT]. (f) Rotate outer dial of [CRSR] knob to select the first Aux (Flight Planning) page. (g) Rotate inner dial of [CRSR] knob to select the third Aux (Setup 1) page. (h) Press inner dial of [CRSR] knob to activate cursor. (i) Rotate inner dial of [CRSR] knob to select “Date / Time”, then press [ENT]. (j) Rotate inner dial of [CRSR] knob to highlight TIME FORMAT. (k) Rotate inner dial of [CRSR] knob to select "Local 24hr", then press [ENT]. (l) Rotate inner dial of [CRSR] knob to highlight TIME OFFSET. (m) Rotate inner dial of [CRSR] knob to select present UTC time, then press [ENT]. EFFECTIVITY: All Page 15 15 Apr 2007
34-50
CIRRUS (n) (o)
34-50
Page 16 15 Apr 2007
AIRPLANE MAINTENANCE MANUAL
Rotate [C] knob for COM power counter-clockwise to OFF position. Set BAT 1 and AVIONICS switches to OFF positions.
EFFECTIVITY: All
MODEL SR22
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
INSTRUMENT PANEL (REF)
1
3
3 1 or 2
LEGEND 1. GNC 420 Transceiver 2. GNS 430 Transceiver 3. Captive Screw
NOTE Insert 3/32 inch hex wrench into front panel bolt hole and engage hex bolt.
SR22_MM34_1477D
Figure 34-501 Transceiver Installation EFFECTIVITY: All
34-50
Page 17 15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
C. GPS 1 Antenna (See Figure 34-502) (1)
(2)
34-50
Page 18 15 Apr 2007
Removal - GPS 1 Antenna (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers. (c) Serials 0002 thru 0820: Remove cabin headliner. (Refer to 25-10) (d) Serials 0821 & subs: Remove glareshield. (Refer to 25-10) (e) Disconnect antenna cable from antenna. (f) Serials 0002 thru 0820: Pry antenna from hook and loop fastener securing antenna to fuselage. (g) Serials 0821 & subs: Pry antenna from hook and loop fastener securing antenna to glareshield. (h) Remove antenna from airplane. Installation - GPS 1 Antenna (a) Serials 0002 thru 0820: To secure antenna to fuselage, firmly press fastener strip on antenna against fastener strip fastened to the fuselage. (b) Serials 0821 & subs: To secure antenna to glareshield, firmly press hook and loop strip on antenna against hook and loop strip fastened to the glareshield. (c) Connect antenna cable. (d) Reset ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers. (e) Serials 0002 thru 0820: Install cabin headliner. (Refer to 25-10) (f) Serials 0821 & subs: Install glareshield. (Refer to 25-10)
EFFECTIVITY: All
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
D. GPS 2 Antenna (See Figure 34-502) (1)
(2)
Removal - GPS 2 Antenna (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers. (c) Remove glareshield. (Refer to 25-10) (d) Disconnect antenna cable from antenna. (e) Pry antenna from hook and loop fastener securing antenna to glareshield. (f) Remove antenna from airplane. Installation - GPS 2 Antenna (a) To secure antenna to glareshield, firmly press hook and loop strip on antenna against hook and loop strip fastened to the glareshield. (b) Connect antenna cable. (c) Install glareshield. (Refer to 25-10) (d) Reset ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers.
EFFECTIVITY: All
34-50
Page 19 15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
CABIN CEILING (REF) OR GLARESHIELD (REF)
1
3
2
4
Serials 0002 thru 0820.
LEGEND 1. GPS 1 Antenna 2. GPS 2 Antenna 3. Hook & Loop Fastener 4. Antenna Connector
NOTE GPS 1 installed on cabin ceiling. GPS 2 installed on glareshield.
SR22_MM34_1476C
Figure 34-502 GPS Antenna Installation - Serials 0002 thru 0820 (Sheet 1 of 3)
34-50
Page 20 15 Apr 2007
EFFECTIVITY: Serials 0002 thru 0820
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
GLARESHIELD (REF)
1
3
2
4
Serials 0821 & subs w/o TAWS.
NOTE GPS 1 installed on RH side of glareshield.
LEGEND 1. GPS 1 Antenna 2. GPS 2 Antenna 3. Hook & Loop Fastener 4. Antenna Connector
GPS 2 installed on LH side of glareshield.
SR22_MM34_2565
Figure 34-502 GPS Antenna Installation - Serials 0821 & subs w/o TAWS (Sheet 2 of 3) EFFECTIVITY: Serials 0821 & subs w/o TAWS
34-50
Page 21 15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
GLARESHIELD (REF)
1
3
2
4
Serials 0821 & subs w/ TAWS.
NOTE GPS 1 installed on RH outboard side of glareshield.
LEGEND 1. GPS 1 Antenna 2. GPS 2 Antenna 3. Hook & Loop Fastener 4. Antenna Connector
GPS 2 installed on RH inboard side of glareshield.
SR22_MM34_2602
Figure 34-502 GPS Antenna Installation - Serials 0821 & subs w/ TAWS (Sheet 3 of 3)
34-50
Page 22 15 Apr 2007
EFFECTIVITY: Serials 0821 & subs w/ TAWS
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
E. COM 1 Antenna - Serials 1793 & subs, 0002 thru 1792 before SB 2X-34-06 w/ combo antenna in kit, 0002 thru 1792 after SB 2X-34-06 w/o combo antenna in kit (See Figure 34-503) (1)
(2)
Removal - COM 1 Antenna (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers. (c) Remove cabin headliner. (Refer to 25-10) (d) Disconnect antenna cable from antenna. (e) Remove nuts, washers, and screws securing antenna to fuselage. (f) Remove antenna and gasket from top of fuselage. (g) Remove remaining sealant from fuselage. Installation - COM 1 Antenna (a)
Acquire necessary tools, equipment, and supplies. Description Caulk Sealant
(b) (c) (d) (e) (f) (g)
P/N or Spec.
Supplier
(Refer to 51-30)
(Refer to 51-30)
Purpose Weather sealant.
Position gasket and antenna on fuselage roof, then insert screws through mounting holes. Install washers and nuts securing antenna to fuselage. Fillet seal antenna perimeter. (Refer to 20-10) Connect antenna cable. Install cabin headliner. (Refer to 25-10) Reset ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers.
EFFECTIVITY: Serials 1793 & subs, 0002 thru 1792 before SB 2X-3406 w/ combo antenna in kit, 0002 thru 1792 after SB 2X-34-06 w/o combo antenna in kit
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Page 23 15 Apr 2007
CIRRUS F.
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
COM 1 / XM Weather Antenna - Serials 1087 thru 1643 w/ factory XM Weather, 0002 thru 1792 after SB 2X-34-06 w/ COM 1 / XM antenna in kit (See Figure 34-503) (1)
(2)
Removal - COM 1 / XM Weather Antenna (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers. (c) Remove cabin headliner. (Refer to 25-10) (d) Disconnect XM weather cable from antenna. (e) Disconnect COM 1 cable from antenna. (f) Remove nuts, washers, and screws securing antenna to fuselage. (g) Remove antenna and gasket from fuselage. (h) Remove remaining sealant from fuselage. Installation - COM 1 / XM Weather Antenna (a)
Acquire necessary tools, equipment, and supplies. Description Caulk Sealant
(b) (c) (d) (e) (f) (g) (h)
34-50
Page 24 15 Apr 2007
P/N or Spec.
Supplier
(Refer to 51-30)
(Refer to 51-30)
Purpose Weather sealant.
Position gasket and antenna to fuselage and insert screws through mounting holes. Install washers and nuts securing antenna to fuselage. Fillet seal antenna perimeter. (Refer to 20-10) Connect XM Weather cable to antenna. Connect COM 1 cable to antenna. Install cabin headliner. (Refer to 25-10) Reset ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers.
EFFECTIVITY: Serials 1087 thru 1643 w/ factory XM Weather, 0002 thru 1792 after SB 2X-34-06 w/ COM 1 / XM antenna in kit
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
G. COM 2 Antenna (See Figure 34-503) (1)
(2)
Removal - COM 2 Antenna (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers. (c) Remove baggage compartment floor access panel. (Refer to 06-00) (d) Disconnect antenna cable from antenna. (e) Remove nuts and washers securing antenna to fuselage. (f) Remove antenna and gasket from belly of fuselage. (g) Peel off remaining sealant from fuselage. Installation - COM 2 Antenna (a)
Acquire necessary tools, equipment, and supplies. Description Caulk Sealant
(b) (c) (d) (e) (f) (g)
EFFECTIVITY: All
P/N or Spec.
Supplier
(Refer to 51-30)
(Refer to 51-30)
Purpose Weather sealant.
Position gasket and antenna on fuselage belly, then insert screws through mounting holes. Install washers and nuts securing antenna to fuselage. Fillet seal antenna perimeter. (Refer to 20-10) Connect antenna cable. Install baggage compartment floor access panel. (Refer to 06-00) Reset ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers.
34-50
Page 25 15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
4
7 BAGGAGE COMPARTMENT FLOOR (REF)
6
1 5
8 8 FUSELAGE (REF)
3 5 6 7
4
Serials 1793 & subs, 0002 thru 1792 before SB 2X-34-06 w/ COM 1 / XM antenna in kit, 0002 thru 1792 after SB 2X-34-06 w/o COM 1 / XM antenna in kit.
2
5 FUSELAGE (REF)
6 7
8
4
Serials 1087 thru 1643 w/ factory XM Weather, 0002 thru 1792 after SB 2X-34-06 w/ COM 1 / XM antenna in kit.
LEGEND 1. COM 1 Antenna 2. COM 1 / XM Weather Antenna 3. COM 2 Antenna 4. Antenna Connector 5. Screw 6. Washer 7. Nut 8. Gasket
SR22_MM34_2463
Figure 34-503 COM Antenna Installation
34-50
Page 26 15 Apr 2007
EFFECTIVITY: All
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
H. Garmin GTX Transponder (See Figure 34-504) (1)
(2)
(3) (4)
Removal - Garmin GTX Transponder (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull ENCODER/TRANSPONDER circuit breaker. (c) Insert hex wrench into front panel bolt hole and engage hex bolt. (d) Turn locking screw counter-clockwise to loosen locking cam. Locking cam will move the transponder unit out 0.25 inch (0.635 cm) and disengage from the electrical connectors. (e) Pull transponder from mounting tray and remove from airplane. Installation - Garmin GTX Transponder (a) With light to medium pressure, push transponder into mounting tray to engage electrical connectors. (b) Insert hex wrench into front panel bolt hole and engage hex bolt. (c) Turn bolt clockwise to tighten locking cam. (d) Reset ENCODER/TRANSPONDER circuit breaker. (e) If transponder is a different unit from the originally installed transponder: 1 Serials 0002 & subs w/ GTX 327 Transponder: Perform Functional Test - Garmin GTX 327 Transponder Setup. (Refer to 34-50) 2 Serials 0435 & subs w/ GTX 330 Transponder: Perform Functional Test - Garmin GTX 330 Transponder Setup. (Refer to 34-50) (f) Perform Functional Test - Altitude Encoder Calibration. (Refer to 34-10) (g) Perform Operational Test - Garmin Transponder. (Refer to 34-50) Operational Test - Garmin Transponder (a) Verify transponder operation in accordance with 14 CFR 91.413. Functional Test - Garmin GTX 327 Transponder Setup (a) Pull STARTER RELAY and FUEL PUMP RELAY circuit breakers. (b) Set BAT 1, BAT 2, and AVIONICS switches to ON positions. (c) On GTX 327, press [OFF] key. (d) Hold down [FUNC] and press [ON]. Set highlighted parameters as follows: To sequence through configuration pages, press [FUNC]. To highlight selectable fields on each page, press [CRSR]. When a field is highlighted, numeric data entry is performed with 0-9 keys, and list selections with 8 or 9 keys. To accept changes, press [CRSR] key. Pressing [FUNC] key moves on to the next configuration page without saving the changes. 1
2
EFFECTIVITY: All
Set parameters for the Display Mode page. DISPLAY MODE
AUTO
LEVEL
75
Set parameters for the Display Backlight page. BKLT
AUTO
RSP TIME
4
MIN
08
BKLT SRCE
PHOTO
34-50
Page 27 15 Apr 2007
CIRRUS
3
4
AIRPLANE MAINTENANCE MANUAL
SLOPE
50
OFFSET
50
Set parameters for the Key Lighting page. KEY
AUTO
RSP TIME
4
MIN
08
KEY SRCE
28V
SLOPE
50
OFFSET
50
Set parameters for the Contrast Configuration page. CONTRAST MODE
5
6
7
8
34-50
Page 28 15 Apr 2007
AUTO
Set parameters for the RS-232 Input/Output page. INPUT
OUTPUT
CHNL 1
OFF
ICARUS ALT
CHNL 2
GPS
Set parameters for the Operation Configuration page. VS RATE
0500
FLT TMR
CLEAR
VFR ID
1200
FORMAT
FEET
Set parameters for the Squat Switch page. SQUAT SWITCH?
NO
SENSE
LOW
AUTO STANDBY?
ON
DELAY TIME
10
Set parameters for the Aircraft Type page. AC TYPE
9
MODEL SR22
<15.5K lb
Set parameters for the RS-232 INPUT VIEW page. EFFECTIVITY: All
CIRRUS
AIRPLANE MAINTENANCE MANUAL
Note:
10
12
(5)
With GPS in self-test mode, GSPD should read 150 kts. CH1
OFF
+ _ _ _ _ _ _ . _ _ n/a
CH2
GSPD
+ _ _ _ 1 5 0 . 0 0 kts
Set parameters for the Gray Code Input page. GRAY CODE
##########
DECODED ALTITUDE
#### (Field Elevation ±300 ft)
Note: 11
MODEL SR22
No external switches are used.
Set parameters for the External Switch page. IDENT
unchecked
STANDBY
unchecked
SQUAT
unchecked
Set parameters for the Analog Input page. 14/5V LTG
000
PHOTO
000
LCD TEMP
000
28V LTG
000
REPLY
000
UNIT TMP
000
Press [OFF] to exit setup. 13 (e) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (f) Reset STARTER RELAY and FUEL PUMP RELAY circuit breakers. Functional Test - Garmin GTX 330 Transponder Setup (a) Pull STARTER RELAY and FUEL PUMP RELAY circuit breakers. (b) Set BAT 1, BAT 2, and AVIONICS switches in ON positions. (c) On GTX 330, press [OFF]. (d) Hold down [FUNC] and press [ON]. Set highlighted parameters as follows: To sequence through configuration pages, press [FUNC]. To highlight selectable fields on each page, press [CRSR]. When a field is highlighted, numeric data entry is performed with 0-9 keys, and list selections with 8 or 9 keys. To accept changes, press [CRSR]. Pressing [FUNC] moves on to the next configuration page without saving changes.
EFFECTIVITY: All
34-50
Page 29 15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
Note:
1
The MODE S Address (A/C Reg) page will only be displayed on initial power-up if no address is entered.
Set parameters for the MODE S Address (A/C Reg) page. ADDRESS
2
4
6
7
34-50
Page 30 15 Apr 2007
DIAGNOSTICS
Set parameters for the Audio Mode pages. Verify audio messages by selecting 2, 3, 4, or 5 for MESSAGE. VOICE
FEMALE
MESSAGE
0 AUDIO
PAGE CHANGE
ALTITUDE MONITOR
MSG
ENABLE
COUNT DOWN TIMER
MSG
Set parameters for the Traffic Information page. TRAFFIC MESSAGES
5
US TAIL# NXXX
Set parameters for the Configuration Menu page. JUMP TO
3
MODEL SR22
TONE
Set parameters for the Display Mode page. DISPLAY MODE
AUTO
LEVEL
75
Set parameters for the Display Backlight page. BKLT
AUTO
RSP TIME
4
MIN
08
BKLT SRCE
PHOTO
SLOPE
50
OFFSET
50
Set parameters for the Key Lighting page. KEY
AUTO
RSP TIME
4 EFFECTIVITY: All
CIRRUS
AIRPLANE MAINTENANCE MANUAL
8
MIN
08
KEY SRCE
28V
SLOPE
50
OFFSET
50
Set parameters for the Contrast Configuration page. CONTRAST MODE
9
MODEL SR22
AUTO
Set parameters for the ARINC 429 Input pages. SPEED
DATA
CHANNEL 1
LOW
GPS
CHANNEL 2
LOW
OFF
SPEED
DATA
LOW
OFF
CHANNEL 3 CHANNEL 4 10
11
12
13
Set parameters for the ARINC 429 Output page. CHANNEL 1
OFF
CHANNEL 2
OFF
Set parameters for the RS-232 Input/Output page. INPUT
OUTPUT
CHNL 1
OFF
ICARUS ALT
CHNL 2
OFF
OFF
Set parameters for the Operation Configuration page. VS RATE
0500
FORMAT
FEET
VFR ID
1200
ALT ALRT DEV
200
Set parameters for the Squat Switch page. SQUAT SWITCH?
EFFECTIVITY: All
OFF
NO
34-50
Page 31 15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
14
SENSE
LOW
DELAY TIME
10
AUTO FLT TMR?
CLEAR
Set parameters for the Temperature page. SENSOR INSTALLED
15
US TAIL# NXXX
Set parameters for the Mode S Address (Flight ID) page. FLT ID
17
18
20
34-50
Page 32 15 Apr 2007
SAME AS TAIL
Set parameters for the Mode S Aircraft Type page. AC TYPE
<15.5K lb
MAX A/S
<=300 kt
Set parameters for the Gray Code Input page. GRAY CODE
##########
DECODED ALTITUDE
#### (Field Elevation ±300 feet)
Note: 19
NO
Set parameters for the Mode S Address (A/C Reg) page. ADDRESS
16
MODEL SR22
No external switches are used.
Set parameters for the External Switch page. IDENT
unchecked
STANDBY
unchecked
SQUAT
unchecked
Set parameters for the Analog Input page. 14/5V LTG
000
PHOTO
###
LCD TEMP
###
28V LTG
000
REPLY
000
UNIT TMP
### EFFECTIVITY: All
CIRRUS
AIRPLANE MAINTENANCE MANUAL
21
22
Set parameters for the RS-232 Input page. CH1
OFF
+ _ _ _ _ _ _ . _ _ n/a
CH2
OFF
+ _ _ _ _ _ _ . _ _ n/a
Set parameters for the ARINC 429 Channel pages. Note:
(e) (f)
EFFECTIVITY: All
MODEL SR22
With GPS in self-test mode, GSPD should read 150 kts. CH1
###
+ _ _ _ 1 5 0 . 0 0 kts
CH2
000
+ _ _ _ _ _ _ . _ _ n/a
CH3
000
+ _ _ _ _ _ _ . _ _ n/a
CH4
000
+ _ _ _ _ _ _ . _ _ n/a
23 Press [OFF] to exit setup. Set BAT 1, BAT 2, and AVIONICS switches in OFF positions. Reset STARTER RELAY and FUEL PUMP RELAY circuit breakers.
34-50
Page 33 15 Apr 2007
CIRRUS I.
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
Transponder Antenna (See Figure 34-504) (1)
(2)
34-50
Page 34 15 Apr 2007
Removal - Transponder Antenna (a) Remove access panel CF8. (Refer to 06-00) (b) Disconnect antenna cable from antenna. (c) Serials 0002 thru 0319 before SB 2X-34-05, 0320 & subs: Verify transponder antenna is supported and remove nut and washers securing antenna to fuselage belly. (d) Serials 0002 thru 0319 after SB 2X-34-05: Verify transponder antenna is supported and remove nut, washers, and ground plane ring securing antenna to fuselage belly. (e) Remove antenna from airplane. Installation - Transponder Antenna (a) Solvent clean installation area. (Refer to 20-30) (b) Serials 0002 thru 0319 after SB 2X-34-05: Install ground plane ring between transponder antenna gasket and fuselage belly. (c) Verify transponder antenna is inserted and supported in antenna mounting hole in fuselage belly by another aircraft technician. (d) Install washers and nut securing antenna to fuselage belly. (e) Serials 0002 thru 0319 after SB 2X-34-05, 0320 & subs: Torque nut as necessary to ensure antenna collar makes electrical contact with ground plane ring. (f) Connect antenna cable to antenna. (g) Install access cover CF8. (Refer to 06-00)
EFFECTIVITY: All
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
2
1
9
9
8 8
8
7
7
7
6
6
6
6
6
9
6 3 FUSELAGE BELLY (REF)
5
3
FUSELAGE BELLY (REF)
5
4
Serials 0002 thru 0706 before SB 2X-34-05.
FUSELAGE BELLY (REF)
4
Serials 0002 thru 0319 after SB 2X-34-05.
NOTE Typical installation shown. Avionics stackup may change based on optional equipment installation. Ensure hole in ground plane ring aligns with fuselage skin drain.
5 4
Serials 0707 & subs, Serials 0320 thru 0706 after SB 2X-34-05. LEGEND 1. GTX Transponder 2. Mounting Rack 3. Ground Plane Ring 4. Transponder Antenna 5. Gasket 6. Washer 7. Nut 8. Connector 9. Coaxial Cable SR22_MM34_1478B
Figure 34-504 Transponder and Antenna Installation EFFECTIVITY: All
34-50
Page 35 15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
J. Course Deviation Indicator - Serials 0002 thru 0434, 0435 thru 0820 w/o PFD (See Figure 34-505) (1)
(2)
34-50
Page 36 15 Apr 2007
Removal - Course Deviation Indicator (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull INSTRUMENT LIGHTS circuit breaker. (c) Remove glareshield. (Refer to 25-10) (d) Disconnect electrical connector. (e) While supporting course deviation indicator, remove screws and washers securing unit to instrument panel. Installation - Course Deviation Indicator (a) Position course deviation indicator in instrument panel and attach with screws and washers. (b) Connect electrical connector. (c) Install glareshield. (Refer to 25-10) (d) Reset INSTRUMENT LIGHTS circuit breaker.
EFFECTIVITY: Serials 0002 thru 0434, 0435 thru 0820 w/o PFD
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
INSTRUMENT PANEL (REF)
3
2 1
LEGEND 1. Screw 2. Washer 3. Course Deviation Indicator Serials 0002 thru 0434, 0435 thru 0820 w/o PFD.
SR22_MM34_1837A
Figure 34-505 Course Deviation Indicator - Serials 0002 thru 0434, 0435 thru 0820 w/o PFD EFFECTIVITY: Serials 0002 thru 0434, 0435 thru 0820 w/o PFD
34-50
Page 37 15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
K. VOR/LOC Antenna (See Figure 34-506) (1)
(2)
Removal - VOR/LOC Antenna (a) Remove screws securing antenna mounting plate to vertical stabilizer. (b) Lift antenna mounting plate assembly from vertical stabilizer recess. (c) Disconnect antenna cable from antenna. (d) Remove screws securing antenna to mounting plate and remove antenna from airplane. Installation - VOR/LOC Antenna (a)
Acquire necessary tools, equipment, and supplies. Description Caulk Sealant
(b) (c) (d) (e) (f) (g)
(i)
34-50
Page 38 15 Apr 2007
Supplier
(Refer to 51-30)
(Refer to 51-30)
Purpose Weather sealant.
Remove old sealant and solvent clean antenna mounting surfaces. (Refer to 20-30) Install screws securing antenna to antenna mounting plate. Connect antenna cable to antenna. Install antenna mounting plate assembly into vertical stabilizer recess. Install screws securing antenna mounting plate to vertical stabilizer. Solvent clean mounting plate surface. (Refer to 20-30) CAUTION:
(h)
P/N or Spec.
Do not allow tape perimeter to exceed edges of mounting plate.
Apply tape covering screw heads and 0.5 inch (1.27 cm) radius minimum around each screw head. Apply sealant around perimeter of antenna mounting plate.
EFFECTIVITY: All
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
L. VOR/LOC Diplexer (See Figure 34-506) (1)
(2)
Removal - VOR/LOC Diplexer (a) Remove radio module assembly. (Refer to 25-10) (b) Disconnect G/S 1, G/S 2, VOR 1, VOR 2, and ANT cables from diplexer. (c) Serials 0002 thru 2437: Remove screws and nuts securing diplexer to center console. (d) Serials 2438 & subs: Lift edge of diplexer and release reclosable fasteners. (e) Remove diplexer from airplane. Installation - VOR/LOC Diplexer (a) Serials 0002 thru 2437: Install screws and nuts securing diplexer to center console. (b) Serials 2438 & subs: Place diplexer into position and secure. Firmly push on diplexer in areas of reclosable fasteners. (c) Connect G/S 1, G/S 2, VOR 1, VOR 2, and ANT cables to diplexer. (d) Install radio module assembly. (Refer to 25-10)
EFFECTIVITY: All
34-50
Page 39 15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
4 3 3 2
5
1 6 CENTER CONSOLE (REF)
2 8 7
6 10
9
3
11
8
FUSELAGE (REF)
Serials 0002 thru 2333, 2335 thru 2419, 2421 thru 2437.
12 10
Serials 2334, 2420, 2438 & subs.
11
NOTE App;y tape covering screwheads and 0.5 inch (1.27 cm) radius minimum around each screw head. Do not allow tape perimeter to exceed edges of mounting plate.
Figure 34-506 VOR/LOC Antenna Installation
34-50
Page 40 15 Apr 2007
EFFECTIVITY: All
LEGEND 1. VOR/LOC Antenna 2. Washer 3. Screw 4. Tape 5 Mounting Plate 6. Grommet 7. Connector, Straight 8. Nut 9. Antenna Cable 10. Diplexer Antenna 11. Connector, Right Angle 12. Reclosable Fastener SR22_MM34_1479D
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
M. NSD-1000 HSI - Serials 0002 thru 0434, 0435 thru 0820 w/o PFD (See Figure 34-507) (1)
(2)
(3)
Removal - NSD-1000 HSI (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull HSI#1 and HSI#2 circuit breakers. (c) Remove MFD. (Refer to 31-60) (d) Disconnect cable. (e) While supporting HSI, remove screws securing unit to instrument panel. (f) Cap off fittings on back of HSI to prevent possible contamination and remove HSI from airplane. Installation - NSD-1000 HSI (a) Position HSI in instrument panel and secure with screws. (b) Connect data cable. (c) Install MFD. (Refer to 31-60) (d) Reset HSI#1 and HSI#2 circuit breakers. (e) If NSD-1000 HSI is a different unit from the originally installed NSD-1000 HSI: 1 Perform Functional Test - Flux Detector Calibration with NSD-1000 HSI Installed. (Refer to 34-50) 2 Perform Operational Test - NSD-1000 HSI Setup. (Refer to 34-50) (f) If NSD-1000 HSI is the same unit as the originally installed NSD-1000 HSI: 1 Perform Operational Test - NSD-1000 HSI Setup. (Refer to 34-50) Operational Test - NSD-1000 HSI Setup (a) Pull STARTER RELAY and FUEL PUMP RELAY circuit breakers. (b) Set BAT 1, BAT 2, and AVIONICS switches to ON positions. The NSD-1000 HSI will begin to spin-up and stabilize when battery power is initially turned on. When the gyro reaches operational speed, the HSI "HDG" flag will retract from view and the compass card will stabilize. (c) (d)
Set HSI switch to SLAVE position. Rotate compass card to approximate magnetic heading. Slaving meter will be at 45° when compass card matches heading. Verify slaving meter oscillates back and forth as compass card is rotated back and forth.
(e) (f)
Wait 5 minutes and verify the compass card remains on correct heading. To test HSI navigation, perform Functional Test - Garmin GNS 430 GPS/COM/NAV Setup. (Refer to 34-50) CAUTION:
Prior to verifying NSD-1000 HSI system, verify that doors are closed, flaps are in retracted position, engine is running, and airplane is in level flight attitude. Engine starting, taxiing, and shut-down may only be performed by authorized personnel.
Note:
If compass rose is not available, a calibrated boresight compass may be used.
EFFECTIVITY: Serials 0002 thru 0434, 0435 thru 0820 w/o PFD
34-50
Page 41 15 Apr 2007
CIRRUS (g)
AIRPLANE MAINTENANCE MANUAL
Acquire necessary tools, equipment, and supplies. Description Boresight Compass (if compass rose is unavailable)
(h) (i) (j) (k) (l) (m)
MODEL SR22
P/N or Spec.
Supplier
Purpose
±1° accuracy Any Source Verify NSD-1000 HSI system.
Set BAT 1, BAT 2, ALT 1, ALT 2, PITOT HEAT, and all radio switches to ON positions. Set all other cockpit controlled electrical switches to OFF positions. Place airplane in as realistic flight environment as possible. Taxi airplane to compass rose, if available. If using compass rose for verification: 1 Align centerline of airplane on magnetic North heading (±1°). If using boresight compass for verification: WARNING:
Use of a boresight compass requires two technicians. Do not stand or let anyone else stand close to the arc of the airplane’s propeller while conducting test.
1
(n) (o) (p) (q)
34-50
Page 42 15 Apr 2007
With outside technician standing 20-30 ft (6-9 m) in front of airplane and through the use of hand signals, have outside technician direct technician at controls to move airplane so propeller spinner and vertical stabilizer align with magnetic North. Align airplane with West and verify NSD-1000 HSI system indicates 90° turn. Align airplane with North and verify NSD-1000 HSI system indicates 90° turn. Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. Reset STARTER RELAY and FUEL PUMP RELAY circuit breakers.
EFFECTIVITY: Serials 0002 thru 0434, 0435 thru 0820 w/o PFD
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
N. SN3308 EHSI - Serials 0002 thru 0434, 0435 thru 0820 w/o PFD (See Figure 34-507) (1)
Removal - SN3308 EHSI (a)
Acquire necessary tools, equipment, and supplies. Description
P/N or Spec.
7/64-inch Hex Wrench
(b) (c) (d) (e) (f)
-
Supplier Any Source
Purpose EHSI installation and removal.
Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. Pull HSI#1 and HSI#2 circuit breakers. Loosen top two screws above EHSI to remove tension from mounting tray. Remove lower-left screw securing EHSI to mounting tray. Insert hex wrench into lower-left hole approximately 0.75 inch (1.9 cm) and engage jackscrew. CAUTION:
Do not apply excessive torque on the jackscrew. The jackscrew is used to assist in removing EHSI but cannot extract the unit alone. If EHSI is difficult to remove, verify upper two clamp screws are sufficiently loosened.
(g) (2)
To remove EHSI from instrument panel, rotate jackscrew clockwise in 1/2 turn increments while simultaneously pulling on EHSI bezel. Installation - SN3308 EHSI
(a)
Acquire necessary tools, equipment, and supplies. Description 7/64-inch Hex Wrench CAUTION:
(b) (c) (d) (e) (f) (g) (h)
-
Supplier Any Source
Purpose EHSI installation and removal.
When mounting EHSI, do not press on display window as damage may result.
Tighten lower right mounting screw Insert hex wrench into lower-left hole approximately 0.75 inch (1.9 cm) and engage jackscrew. Turn jackscrew clockwise until finger tight. Slide EHSI into mounting tray. Rotate jackscrew counter-clockwise until EHSI is fully engaged in tray connectors. Install lower-left screw. Tighten upper two screws. CAUTION:
(i) (j)
P/N or Spec.
Verify face of EHSI is flush with instrument panel. If face of EHSI protrudes more than 0.0625 inch (1.6 mm), remove unit and reinstall.
Reset HSI#1 and HSI#2 circuit breakers. If SN3308 EHSI is a different unit from the originally installed SN3308 EHSI: 1 Perform Functional Test - SN3308 EHSI Setup. (Refer to 34-50) 2 Perform Functional Test - Flux Detector Calibration with SN3308 EHSI Installed. (Refer to 34-50) 3 Perform Operational Test - SN3308 EHSI System. (Refer to 34-50)
EFFECTIVITY: Serials 0002 thru 0434, 0435 thru 0820 w/o PFD
34-50
Page 43 15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
(k)
(3)
If SN3308 EHSI is the same unit as the originally installed SN3308 EHSI: 1 Perform Operational Test - SN3308 EHSI System. (Refer to 34-50) Functional Test - SN3308 EHSI Setup (a)
Acquire necessary tools, equipment, and supplies. Description VOR Signal Generator (if steady VOR frequency is not available)
(b) (c) (d)
(e) (f) (g)
(j) (k)
34-50
Page 44 15 Apr 2007
NAV-402
Supplier Any Source
Purpose Simulate VOR bearing.
Pull STARTER RELAY and FUEL PUMP RELAY circuit breakers. Set BAT 1, BAT 2, and AVIONICS switches to ON positions. Pull circuit breakers. 1 Pull HSI#1 circuit breaker, then verify EHSI remains ON. Reset HSI#1 circuit breaker. 2 Pull HSI#2 circuit breaker, then verify EHSI remains ON. 3 Pull HSI#1 circuit breaker, then verify EHSI shuts OFF. On SN3308 EHSI, press and hold [SHFT] and [A-B]. Reset HSI#1 and HSI#2 circuit breakers. Continue to hold [SHFT] and [A-B] until the first Maintenance Menu page appears. Note:
(h) (i)
P/N or Spec.
Press [NEXT] or [LAST] to cycle the Maintenance Menu pages.Use [UP] or [DOWN] arrows to change selection, and rotate right knob to change setting for selection.
Press [LAST] key repeatedly to access 2: Compass System page. Set parameters for the 2: Compass System page. GYRO TYPE
MID-CONT DG
GYRO VALID
P1-9 LOW
SLAVING
YES
FLUX GATE
STEC 6446
QUADRANT
270°
PEAKING
6
The 3: Compass Calibration page is not used. Set parameters for the 4: BRG PTR Setup page. BRG NAV-1
429
NAV-2
COMPOSITE
BRG ADF-1
DISABLED
ADF-2
DISABLED
EFFECTIVITY: Serials 0002 thru 0434, 0435 thru 0820 w/o PFD
CIRRUS (l)
AIRPLANE MAINTENANCE MANUAL
Set parameters for the 5: DME-1 Select page. CURRENT SELECTION
(m)
(o)
(q)
NOT INSTALLED
Set parameters for the 7: DME 1 / 2 Change page. DME1:
NOT INSTALLED
DME2:
NOT INSTALLED
Set parameters for the 8: FCS Emulation page. CURRENT SELECTION
(p)
NOT INSTALLED
Set parameters for the 6: DME-2 Select page. CURRENT SELECTION
(n)
MODEL SR22
CENTURY 21/31/41 DC
Set parameters for the 9: FCS Change page. HDG DATUM - CURRENT
+RIGHT
CRS DATUM - CURRENT
+RIGHT
REF VOLTS - CURRENT
04.950
Adjust HDG Bug. On SN3308 EHSI, select CURRENT-REF VOLTS on the Maintenance Menu page. 1 2 Press [360] to select Map page. 3 Press [SYNC] to center HDG bug. 4 Press [SHFT], then [MAINT] to return to the Maintenance Menu page. 5 On System 55X A/P programmer/computer, press [HDG]. 6 Adjust CURRENT-REF VOLTS until yokes are centered, and have little or no left/ right movement. 7 On SN3308 EHSI, press [360] to confirm adjustment. 8 Press [SYNC] to center HDG bug. 9 Verify little to no yoke movement. 10 On SN3308 EHSI, rotate RH knob 1-2 degrees left of current heading. Yoke should respond accordingly. 11
On SN3308 EHSI, rotate RH knob 1-2 degrees right of current heading. Yoke should respond accordingly.
12
(r)
If necessary, press [SHFT], then [MAINT] to return to the Maintenance Menu page and re-adjust HDG bug until yokes respond correctly. 13 On LH yoke, press A/P DISC switch to disconnect autopilot. Set parameters for the 10: LNAV-1 Select page. CURRENT SELECTION
EFFECTIVITY: Serials 0002 thru 0434, 0435 thru 0820 w/o PFD
GARMIN GNS 430(ARINC)
34-50
Page 45 15 Apr 2007
CIRRUS (s)
AIRPLANE MAINTENANCE MANUAL
Set parameters for the 11: LNAV-2 Select page. CURRENT SELECTION
(t)
(u)
NONE
Set parameters for the 12: LNAV 1 / 2 Change page. LNAV 1
GARMIN GNS 430(ARINC)
ANNUN
SERIAL
COURSE
OBS/LEG
DEVIATION
SER DATA
LNAV 2
NONE
Set parameters for the 13: MKR Select page. CURRENT SELECTION
(v)
(w)
MODEL SR22
KING KMA-24
Set parameters for the 14: MKR Change page. MKR
KING KMA-24
MKR VALID
VALID HIGH
THRESH
2.0 Volts
DEVIATION
SER DATA
LNAV 2
NONE
Set parameters for the 15: NAV Change page. Note:
VHF Omni-directional Range (VOR) value for 175° is not labeled in display. NAV-1 ENABLE
YES
PORT
429 PORT-2
NAV-2 ENABLE
NO
RELAY MODE
MASTER
ILS LOCKOUT
NO
COMPOSITE-2
000.0 175°
(x)
34-50
Page 46 15 Apr 2007
Adjust NAV2 BRG PTR. 1 On SN3308 EHSI, select COMPOSITE-2 on Maintenance Menu page. 2 Press [360]. 3 Select NAV1 and NAV2 bearing pointers by pressing [BRG] until both are displayed.
EFFECTIVITY: Serials 0002 thru 0434, 0435 thru 0820 w/o PFD
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
CAUTION:
If steady local VOR frequency is not available, use VOR signal generator.
Note:
Use same frequency on both GPS's, preferably generated with a VOR signal generator.
4
(y)
On dual GNS 430 or GNS 430/GNC 420, select a stable NAV signal for GPS 1 and GPS 2. 5 Verify that both BGR PTR's are indicating the same bearing. 6 On SN3308 EHSI, note bearing of NAV1 BGR PTR at bottom left. 7 Press [SHFT], then [MAINT] to return to Maintenance Menu page. 8 With COMPOSITE-2 selected, adjust value until bearing in lower left corner matches NAV1 BRG PTR noted previously. 9 Press [360] to confirm adjustment. 10 If necessary, re-adjust NAV2 BRG PTR until pointers are at the same bearing. Set parameters for the 16: Relay Sense page. NAV-2
OFF
GPS-1
OFF
GPS-2
OFF
CDI SRC SEL
OFF
RCVR 1 / 2
OFF
(z) The 17: System LCD Setups page is not used. (aa) Set parameters for the 18: System page.
(4)
COLOR SELECT
PILOT
400 Hz INVERTER (w/ Stormscope)
ENABLED
400 Hz INVERTER (w/o Stormscope)
DISABLE
BOOTSTRAP OUT (w/ Stormscope)
NORMAL
BOOTSTRAP OUT (w/o Stormscope)
OFF
WX DETECTION (w/ Stormscope)
WX-500
WX DETECTION (w/o Stormscope)
OFF
(ab) The remaining pages 19 through 27 are for diagnostics and do not require setup. (ac) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (ad) Reset STARTER RELAY and FUEL PUMP RELAY circuit breakers. Operational Test - SN3308 EHSI System CAUTION:
Prior to verifying SN3308 EHSI system, verify that doors are closed, flaps are in retracted position, engine is running, and airplane is in level flight attitude. Engine starting, taxiing, and shut-down may only be performed by authorized personnel.
EFFECTIVITY: Serials 0002 thru 0434, 0435 thru 0820 w/o PFD
34-50
Page 47 15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
Note: (a)
If compass rose is not available, a calibrated boresight compass may be used. Acquire necessary tools, equipment, and supplies. Description Boresight Compass (if compass rose is unavailable)
(b) (c) (d) (e) (f) (g)
MODEL SR22
P/N or Spec.
Supplier
Purpose
±1° accuracy Any Source Verify SN3308 EHSI system.
Set BAT 1, BAT 2, ALT 1, ALT 2, PITOT HEAT, and all radio switches to ON positions. Set all other cockpit controlled electrical switches to OFF positions. Place airplane in as realistic flight environment as possible. Taxi airplane to compass rose, if available. If using compass rose for verification: 1 Align centerline of airplane on magnetic North heading (±1°). If using boresight compass for verification: WARNING:
Use of a boresight compass requires two technicians. Do not stand or let anyone else stand close to the arc of the airplane’s propeller while conducting test.
1
(h) (i) (j) (k)
34-50
Page 48 15 Apr 2007
With outside technician standing 20-30 ft (6-9 m) in front of airplane and through the use of hand signals, have outside technician direct technician at controls to move airplane so propeller spinner and vertical stabilizer align with magnetic North. Align airplane with West and verify SN3308 EHSI system indicates 90° turn. Align airplane with North and verify SN3308 EHSI system indicates 90° turn. Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. Reset STARTER RELAY and FUEL PUMP RELAY circuit breakers.
EFFECTIVITY: Serials 0002 thru 0434, 0435 thru 0820 w/o PFD
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
O. Slave Amplifier - Serials 0002 thru 0434, 0435 thru 0820 w/o PFD (See Figure 34-507) (1)
(2)
Removal - Slave Amplifier (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull HSI#1 and HSI#2 circuit breakers. (c) Remove passenger side carpeting. (d) Remove access panel CF2R from cabin floor. (e) Disconnect slave amplifier connector assembly. (f) Remove screws securing slave amplifier to access panel and remove from airplane. Installation - Slave Amplifier (a) Position slaving amplifier to access panel CF2R and secure with screws. (b) Connect connector assembly. (c) Install access panel CF2R. (d) Reset HSI#1 and HSI#2 circuit breakers.
EFFECTIVITY: Serials 0002 thru 0434, 0435 thru 0820 w/o PFD
34-50
Page 49 15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
P. Flux Detector - Serials 0002 thru 0434, 0435 thru 0820 w/o PFD (See Figure 34-507) (1)
(2)
Removal - Flux Detector (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull HSI#1 and HSI#2 circuit breakers. (c) Remove wing access panel RW6. (d) Remove cable tie securing connector to wing. Remove flux detector from airplane. (e) Remove screws and washers securing flux detector to standoffs. Installation - Flux Detector CAUTION:
Verify flux detector is installed with arrow and word FORE embossed on top of flux detector pointing forward. Failure to do will cause HSI system malfunction.
(a) (b) (c) (d)
(3)
Position flux detector to standoffs and secure with washers and screws. Connect connector assembly. Secure connector assembly to tie down with cable tie. Serials 0002 thru 0820 w/ NSD-360A HSI: Perform Functional Test - Flux Detector Calibration with NSD-360A HSI Installed. (Refer to 34-50) (e) Serials 0002 thru 0820 w/ NSD-1000 HSI: Perform Functional Test - Flux Detector Calibration with NSD-1000 HSI Installed. (Refer to 34-50) (f) Serials 0002 thru 0820 w/ SN3308 EHSI: Perform Functional Test - Flux Detector Calibration with SN3308 EHSI Installed. (Refer to 34-50) (g) Reset HSI#1 and HSI#2 circuit breakers. Functional Test - Flux Detector Calibration with NSD-360A HSI Installed CAUTION:
Prior to calibrating flux detector, verify that doors are closed, flaps are in retracted position, engine is running, and airplane is in level flight attitude. Engine starting, taxiing, and shut-down may only be performed by authorized personnel.
Note: (a)
If compass rose is not available, a calibrated boresight compass may be used. Acquire necessary tools, equipment, and supplies. CAUTION:
Using the boresight compass for calibration requires two technicians. Description Boresight Compass (if compass rose is unavailable)
(b) (c) (d) (e) (f) (g)
34-50
Page 50 15 Apr 2007
P/N or Spec.
Supplier
Purpose
±1° accuracy Any Source Calibrate flux detector.
Set BAT 1, BAT 2, ALT 1, ALT 2, PITOT HEAT, and all radio switches to ON positions. Set all other cockpit controlled electrical switches to OFF positions. Place airplane in as realistic flight environment as possible. Taxi airplane to compass rose, if available. If using compass rose for calibration: 1 Align centerline of airplane on magnetic North heading (±1°). If using boresight compass for verification:
EFFECTIVITY: Serials 0002 thru 0434, 0435 thru 0820 w/o PFD
CIRRUS
AIRPLANE MAINTENANCE MANUAL
WARNING:
MODEL SR22
Use of a boresight compass requires two technicians. Do not stand or let anyone else stand close to the arc of the airplane’s propeller while conducting test.
1
(4)
With outside technician standing 20-30 ft (6-9 m) in front of airplane and through the use of hand signals, have outside technician direct technician at controls to move airplane so propeller spinner and vertical stabilizer align with magnetic North. (h) Align airplane with North. Rotate HSI compass card to center slaving meter at 45°. Record heading deviation. (i) Align airplane with East. Rotate HSI compass card to center slaving meter at 45°. Read heading deviation. (j) Align airplane with South. Rotate HSI compass card to center slaving meter at 45°. Read heading deviation. (k) Align airplane with West. Rotate HSI compass card to center slaving meter at 45°. Read heading deviation. (l) Find average deviation and direction of average deviation. (m) Rotate flux detector in opposite direction of the deviation by degrees of average deviation. (n) Repeat heading checks. (o) Readjust if necessary. (p) Compare North and South heading deviations. Deviations that occur on same side of the North-South reference line are reduced by adjusting N-S adjusting screw on compensator. (q) Compare East and West heading deviations. Deviations that occur on same side of the East-West reference line are reduced by adjusting E-W adjusting screw on compensator. (r) Repeat heading checks. (s) Re-adjust if necessary. Functional Test - Flux Detector Calibration with NSD-1000 HSI Installed CAUTION:
Prior to calibrating flux detector, verify that doors are closed, flaps are in retracted position, engine is running, and airplane is in level flight attitude. Engine starting, taxiing, and shut-down may only be performed by authorized personnel.
Note: (a)
If compass rose is not available, a calibrated boresight compass may be used. Acquire necessary tools, equipment, and supplies. CAUTION:
Using the boresight compass for calibration requires two technicians. Description Boresight Compass (if compass rose is unavailable)
(b) (c) (d) (e) (f)
P/N or Spec.
Supplier
Purpose
±1° accuracy Any Source Calibrate flux detector.
Set BAT 1, BAT 2, ALT 1, ALT 2, PITOT HEAT, and all radio switches to ON positions. Set all other cockpit controlled electrical switches to OFF positions. Place airplane in as realistic flight environment as possible. Taxi airplane to compass rose, if available. If using compass rose for calibration: 1 Align centerline of airplane on magnetic North heading (±1°).
EFFECTIVITY: Serials 0002 thru 0434, 0435 thru 0820 w/o PFD
34-50
Page 51 15 Apr 2007
CIRRUS (g)
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
If using boresight compass for verification: WARNING:
Use of a boresight compass requires two technicians. Do not stand or let anyone else stand close to the arc of the airplane’s propeller while conducting test.
1
(5)
With outside technician standing 20-30 ft (6-9 m) in front of airplane and through the use of hand signals, have outside technician direct technician at controls to move airplane so propeller spinner and vertical stabilizer align with magnetic North. (h) Align airplane with North. Rotate HSI compass card to center slaving meter at 45°. Record heading deviation. (i) Align airplane with East. Rotate HSI compass card to center slaving meter at 45°. Read heading deviation. (j) Align airplane with South. Rotate HSI compass card to center slaving meter at 45°. Read heading deviation. (k) Align airplane with West. Rotate HSI compass card to center slaving meter at 45°. Read heading deviation. (l) Find average deviation and direction of average deviation. (m) Rotate flux detector in opposite direction of the deviation by degrees of average deviation. (n) Repeat heading checks. (o) Readjust if necessary. (p) Compare North and South heading deviations. Deviations that occur on same side of the North-South reference line are reduced by adjusting N-S adjusting screw on compensator. (q) Compare East and West heading deviations. Deviations that occur on same side of the East-West reference line are reduced by adjusting E-W adjusting screw on compensator. (r) Repeat heading checks. (s) Re-adjust if necessary. Functional Test - Flux Detector Calibration with SN3308 EHSI Installed CAUTION:
Prior to calibrating flux detector, verify that doors are closed, flaps are in retracted position, engine is running, and airplane is in level flight attitude. Engine starting, taxiing, and shut-down may only be performed by authorized personnel.
Note: (a)
If compass rose is not available, a calibrated boresight compass may be used. Acquire necessary tools, equipment, and supplies. CAUTION:
Using the boresight compass for calibration requires two technicians. Description Boresight Compass (if compass rose is unavailable)
(b) (c) (d) (e)
34-50
Page 52 15 Apr 2007
P/N or Spec.
Supplier
Purpose
±1° accuracy Any Source Calibrate flux detector.
Set BAT 1, BAT 2, ALT 1, ALT 2, PITOT HEAT, and all radio switches to ON positions. Set all other cockpit controlled electrical switches to OFF positions. Place airplane in as realistic flight environment as possible. Taxi airplane to compass rose, if available. EFFECTIVITY: Serials 0002 thru 0434, 0435 thru 0820 w/o PFD
CIRRUS (f) (g)
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
If using compass rose for calibration: 1 Align centerline of airplane on magnetic North heading (±1°). If using boresight compass for verification: WARNING:
Use of a boresight compass requires two technicians. Do not stand or let anyone else stand close to the arc of the airplane’s propeller while conducting test.
1
(h) (i) (j) (k) (l) (m)
With outside technician standing 20-30 ft (6-9 m) in front of airplane and through the use of hand signals, have outside technician direct technician at controls to move airplane so propeller spinner and vertical stabilizer align with magnetic North. Align airplane with North. Highlight North calibration value and adjust using right knob to calibrate heading. Align airplane with East. Highlight East calibration value and adjust using right knob to calibrate heading. Align airplane with South. Highlight South calibration value and adjust using right knob to calibrate heading. Align airplane with West. Highlight West calibration value and adjust using right knob to calibrate heading. Repeat heading checks. Toggle BAT 1 switch to OFF, then ON position to put EHSI in normal operating mode.
EFFECTIVITY: Serials 0002 thru 0434, 0435 thru 0820 w/o PFD
34-50
Page 53 15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
Q. Remote Gyro - Serials 0002 thru 0434, 0435 thru 0820 w/o PFD (See Figure 34-507) CAUTION:
(1)
(2)
34-50
Page 54 15 Apr 2007
Remote gyro is a precision instrument and is easily damaged by rough handling. Always place remote gyro on a padded surface. Avoid all shock impacts to gyro.
Removal - Remote Gyro (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull HSI#1 and HSI#2 circuit breakers. (c) Remove RH passenger seat. (Refer to 25-10) (d) Disconnect remote gyro connector assembly. (e) Remove screws securing remote gyro to fuselage mounting tray and remove from airplane. Installation - Remote Gyro (a) Position remote gyro to mounting tray and secure with screws. (b) Connect remote gyro electrical connector assembly. (c) Install RH passenger seat. (Refer to 25-10) (d) Reset HSI#1 and HSI#2 circuit breakers. (e) Serials 0002 thru 0820 w/ NSD-1000 HSI: Perform Operational Test - NSD-1000 HSI System. (Refer to 34-50) (f) Serials 0002 thru 0820 w/ SN3308 EHSI: Perform Operational Test - SN3308 EHSI System. (Refer to 34-50)
EFFECTIVITY: Serials 0002 thru 0434, 0435 thru 0820 w/o PFD
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
5
6
4
3 2
NOTE
7
Chamfer must be in upper right-hand location.
8
2
2
1
Serials 0002 thru 0434, 0435 thru 0820 w/o PFD.
LEGEND 1. EHSI SN3308 2. Screw 3. Washer 4. HSI NSD-1000 5. Electrical Connector 6. Electrical/Data Connector 7. Mounting Tray 8. Mounting Plate
SR22_MM34_2004A
Figure 34-507 HSI Components - Serials 0002 thru 0434, 0435 thru 0820 w/o PFD (Sheet 1 of 2) EFFECTIVITY: Serials 0002 thru 0434, 0435 thru 0820 w/o PFD
34-50
Page 55 15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
2
ACCESS COVER CF2R (REF)
10 6 11
5
12
UPPER WING SKIN (REF)
3 2
9 2 3 6
AFT FLOOR (REF)
LEGEND 9. Remote Gyro 10. Slaving Amplifier 11. Flux Detector 12. Standoffs
SHELF (REF)
Serials 0002 thru 0434, 0435 thru 0820 w/o PFD.
SR22_MM34_2005A
Figure 34-507 HSI Components - Serials 0002 thru 0434, 0435 thru 0820 w/o PFD (Sheet 2 of 2)
34-50
Page 56 15 Apr 2007
EFFECTIVITY: Serials 0002 thru 0434, 0435 thru 0820 w/o PFD
