CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL...

C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0

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EFFECTIVITY:

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 Navigator transceiv-ers, GPS / WAAS GPS antennas, transponder, course deviation indicator (CDI), VOR/LOC antenna, HSI components, XM Weather system, Iridium Weather system, Automatic Direction Finder (ADF), and Dis-tance Measuring Equipment (DME) receiver and antenna.

A. GPS Navigator Transceivers

One or two VHF communications (COM) transceivers are installed to provide VHF communication. The transceivers and integrated controls are mounted in a single GNC 420(W) unit, single GNS 430(W) unit, GNS 430(W)/GNC 250XL units, GNS 430(W)/GNC 420(W) units, or dual GNS 430(W) units.

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 250XL is an VFR certified VHF communications transceiver and GPS sensor. The GNC 250XL includes a removable data card.

The Garmin GNC 420 is an IFR certified VHF communications transceiver and GPS sensor. The trans-ceiver incorporates a GPS sensor and includes two removable data cards, one with a Jeppesen data base, and the second being a custom data card.

The Garmin GNC 420W is an IFR certified, WAAS capable 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. WAAS guidance functionality is avail-able to provide additional instrument approach options.

The Garmin GNS 430 is an IFR certified VHF communications transceiver and Navigation Manage-ment 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.

The Garmin GNS 430W is an IFR certified, WAAS capable VHF communications transceiver and Nav-igation Management System (NMS). The NMS includes GPS sensor, VOR/Localizer and Glideslope receivers. The GNS 430W includes two removable data cards, one with a Jeppesen data base, and the second being a custom data card. WAAS guidance functionality is available to provide additional instrument approach options.

Serials 1005 thru 1422 before SB 2X-34-06: GPS signals are received by an antenna mounted inside the fuselage under the forward headliner and by an antenna mounted inside the fuselage under the instrument console.

Serials 1423 thru 1801, 1803 thru 1815, Serials 1005 thru 1422 after SB 2X-34-06: GPS signals are received by antennas mounted inside the fuselage under the instrument console.

Serials 1802, 1816 & subs, Serials 1005 thru 1422 after SB 2X-34-23, Serials 1337 thru 1801, 1803 thru 1815 after SB 2X-34-24: WAAS GPS signals are received by antennas mounted externally to top of fuselage.

Note: Serials w/ Garmin GNC 250XL GPS2: WAAS capability for GPS2 is not supported.

Serials w/ single GNC 420(W) unit: For single GNC 420(W) designated as COM1, 28 VDC is supplied through the 5-amp GPS1 and 7.5-amp COM1 circuit breakers on the Avionics Non-Essential Bus.

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Serials w/ single GNS 430(W) unit: For single GNS 430(W) designated as COM1, 28 VDC is supplied through the 5-amp GPS1 and 7.5-amp COM1 circuit breakers on the Avionics Essential Bus.

Serials w/ GNS 430(W)/GNC 250 XL units: For upper GNS 430(W) designated as COM1, 28 VDC is supplied through the 5-amp GPS1 and 7.5-amp COM1 circuit breakers on the Avionics Essential Bus. For lower GNC 250XL designated as COM2, 28 VDC is supplied through the 5-amp GPS2 and 7.5-amp COM2 circuit breakers on the Avionics Non-Essential Bus.

Serials w/ GNS 430(W)/GNC 420(W) units: For upper GNS 430(W) designated as COM1, 28 VDC is supplied through the 5-amp GPS1 and 7.5-amp COM1 circuit breakers on the Avionics Essential Bus. For lower GNC 420 designated as COM2, 28 VDC is supplied through the 5-amp GPS2 and 7.5-amp COM2 circuit breakers on the Avionics Non-Essential Bus.

Serials w/ dual GNS 430(W) units: For upper GNS 430(W) designated as COM1, 28 VDC is supplied through the 5-amp GPS1 and 7.5-amp COM1 circuit breakers on the Avionics Essential Bus. For lower GNS 430(W) designated as COM2, 28 VDC is supplied through the 5-amp GPS2 and 7.5-amp COM2 circuit breakers on the Avionics Essential Bus.

For additional information on the GPS navigator transceivers, see the Garmin 400 Series Installation Manual. (Refer to 05-10)

B. Transponder

Serials 1005 thru 2015, 2016 & subs w/o Perspective Avionics: The Garmin GTX 320 (Serials 1005 thru 1099), Garmin GTX 327 (Serials 1100 & subs w/o Mode S), or Garmin GTX 330 (Serials 1425 & subs w/ Mode S, Serials 1337 & subs after SB 2X-34-09) transponder is mounted in the center con-sole.

The transponder receives interrogations from a ground-based secondary radar transmitter and trans-mits 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 transponder-equipped 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.

For additional information on the Garmin transponders, see the GTX 327 Transponder Installation and Operation Manual and the GTX 330 Pilot’s Guide. (Refer to 05-10)

Serials 2016 & subs w/ Perspective Avionics: The Garmin GTX 32 or GTX 33 transponder is located behind the aft cabin bulkhead in the empennage avionics compartment.

The GTX 32 transponder provides Modes A and C interrogation/reply capabilities. The GTX 33 Mode S solid-state transponder provides Modes A, C, and S interrogation/reply capabilities. The transponder communicates with the primary Integrated Avionics Unit and is controlled via the PFD or Flight Man-agement System Keyboard. 28 VDC for transponder operation is supplied through the 2-amp XPO-NDER circuit breaker on the Avionics Bus.

Refer to the Perspective Integrated Avionics System Pilot’s Guide for a complete description of the sys-tem, its operating modes, and additional detailed operating procedures. (Refer to 05-10)

The GTX 32 and GTX 33 transponders are integral to the Perspective Integrated Avionics system. For an overview of the Perspective Avionics system, refer to Chapter 42, Integrated Modular Avionics. (Refer to 42-00)

C. Course Deviation Indicator (CDI)

Serials 1005 thru 1336, 1337 thru 1422 w/o PFD: The Garmin GI-102(A) and GI-106(A) are panel-mounted 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 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.


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D. Horizontal Situation Indicator (HSI/EHSI)

Serials 1005 thru 1267: The NSD-360A HSI, located directly below the attitude indicator, has an vac-uum 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 indi-cation of the airplane heading to the pilot. 28 VDC is supplied through the 5-amp HSI#1 circuit breaker on the Essential Bus and 5-amp HSI#2 circuit breaker on Main Bus 2.

Serials 1005 thru 1336, 1337 thru 1422 w/o PFD: The NSD-1000 HSI, located directly below the atti-tude 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 redun-dant power circuits is supplied through the 5-amp HSI#1 circuit breaker on the Essential Bus and 5-amp HSI#2 circuit breaker on Main Bus 2.

Serials 1148 thru 1336, 1337 thru 1422 w/o PFD: The SN3308 EHSI is located directly below the atti-tude 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 5-amp HSI#1 circuit breaker on the Essential Bus and 5-amp HSI#2 circuit breaker on Main Bus 2.

E. XM Weather System - Serials w/o Perspective Avionics

Serials 1005 thru 1797: The Avidyne XM Weather system consists of the XM Weather Receiver mounted behind the RH bolster panel, XM Weather antenna (standalone, XM/COM1, or XM/WAAS) mounted externally to top of fuselage, and system wire harness.

Serials 1798 & subs: The Avidyne XM Weather system consists of the XM Weather Receiver mounted in the RH aft fuselage, XM Weather antenna (standalone, XM/COM1, or XM/WAAS) mounted exter-nally to top of fuselage, and system wire harness.

The XMD076A Data Link Satellite Receiver receives and transmits real-time weather information to the MFD and PFD. The receiver also provides digital XM audio entertainment to the cabin audio system controlled by the XMC050 Remote Control.

The XM Weather system utilizes continuous satellite broadcasts to display real time, location-specific graphical weather information on the MFD. To enhance the situational awareness to the pilot, the MFD will display NEXRAD Radar, METARs, SIGMETs, AIRMETs, TFRs, and Lightning Strikes from the National Lightning Detection Network. XM Radio is optionally integrated into the XM Weather system. (Refer to 23-30)

The XM Weather system is powered by 28 VDC through the 3-amp WEATHER/STORMSCOPE circuit breaker on the Avionics Non-Essential Bus. Refer to the manufacturer’s approved Instructions For Continued Airworthiness.

F. XM Weather System - Serials w/ Perspective Avionics

The XM Weather system consists of the XM Weather Receiver mounted in the empennage avionics compartment, XM Weather/WAAS Combo Antenna mounted externally to top of fuselage, and system wire harness.

The GDL 69/69A Data Link Satellite Receiver receives and transmits real-time weather information to the MFD and PFD.

• Serials w/o Flight Stream 210: If GDL 69A option is installed, this unit also provides digital XM audio entertainment to the cabin audio system via the audio panel. It is controlled by the MFD or the GRT 10 XM Remote Transceiver with GRC 10 Remote Control.

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• Serials w/ Flight Stream 210: If GDL 69A option is installed, this unit also provides digital XM audio entertainment to the cabin audio system via the audio panel. It is controlled by MFD or the Flight Stream 210 Bluetooth™ Transceiver with compatible mobile devices. For maintenance practices related to the Flight Stream 210, see the Passenger Address and Entertainment section of Com-munications. (Refer to 23-30)

The XM Weather system utilizes continuous satellite broadcasts to display real time, location-specific graphical weather information on the MFD. To enhance the situational awareness to the pilot, the MFD will display NEXRAD Radar, METARs, SIGMETs, AIRMETs, TFRs, and Lightning Strikes from the National Lightning Detection Network. XM Radio is optionally integrated into the XM Weather system. (Refer to 23-30)

Serials 2016 thru 2126: The XM Weather system is powered by 28 VDC through the 3-amp WEATHER circuit breaker on the Avionics Non-Essential Bus.

Serials 2127 & subs: The XM Weather system is powered by 28 VDC through the 5-amp WEATHER/DATALINK circuit breaker on the Avionics Non-Essential Bus.

The GDL 69/69A Data Link Satellite Receiver 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 42-00)

Note: Serials 2127 & subs: The XM Weather System is available as an optional installation with or without the Iridium Weather System.

G. Iridium Weather System - 2016 & subs w/ Perspective Avionics

The Iridium Weather system consists of the GSR 56 Iridium Transceiver installed immediately behind the aft cabin bulkhead, the GPS/Iridium Combo Antenna mounted externally to top of fuselage, and system wire harness.

The GSR 56 Transceiver receives and transmits real-time weather information to the MFD and PFD. If the Iridium subscription-based voice and data service is active, satellite telephone/voice communica-tions and text messaging (SMS) are provided. The dialing interface is provided through the MFD and incoming call messages are prioritized with other aural messages.

The Iridium Weather system utilizes continuous satellite broadcasts to display real time, worldwide graphical weather information on the MFD. To enhance the situational awareness to the pilot, the MFD will display NEXRAD Radar, METARs, Winds Aloft, Temps Aloft, NOTAMs, SIGMETs, AIRMETs, TFRs, PIREP, and Lightning Strikes from the National Lightning Detection Network. In addition, radar and satellite imagery are available for the United States, Southern Canada and Western Europe.

The Iridium Weather system is powered by 28 VDC through the 5-amp WEATHER/DATALINK circuit breaker on the Avionics Non-Essential Bus.

The GSR 56 Transceiver 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 42-00)

Note: The Iridium Weather System is available as an optional installation with or without the XM Weather System.


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2. TROUBLESHOOTING

Serials 2016 & subs w/ Perspective Avionics:

Serials 2127 & subs w/ Iridium Weather System:

Trouble Probable Cause Remedy

Transponder not receiving valid data.

Software or configuration error. Check PFD Alert Window for GIA1, GIA2, and GTX 32/33 con-figuration, software, or failed data path error messages. Correct any errors before proceeding.

Perform a SET>ACTV configura-tion reset on GTX Transponder Configuration page for each installed GTX.

For GTX 33 transponders, verify aircraft registration is entered in GTX Transponder Configuration page.

Faulty connector. Check GIA and GTX racks for con-nector pin faults (push-back or bent) on the RS-232 interconnect lines.

Faulty transponder. Replace transponder.


No communication with GSR 56. Disconnected or faulty wiring. Check power wiring and pin out.

Incorrect settings. Verify correct communication port setting on display/control device.

No or low-quality signal. Antenna interference. Ensure the Iridium antenna has an unobstructed view of satelliteconstellation.

Disconnected or faulty wiring. Check the antenna cable and con-nectors.

Compromised ground plane. Verify antenna ground plane is adequate.

No audio output. Disconnected or faulty wiring. Check wiring from GSR 56 to audio panel.

No subscription with Garmin Irid-ium Services.

Verify subscription with Garmin Iridium Services.

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Unable to make a phone call. No subscription with Garmin Irid-ium Services.

Verify subscription with Garmin Iridium Services.

No call signal. Verify signal quality is adequate.

Disconnected or faulty wiring. Verify communication between GSR 56 and the display/controldevice..



34-50Serials 1005 thru 2015, 2016 & subs w/o Perspective

Avionics

EFFECTIVITY:

3. MAINTENANCE PRACTICES

A. Garmin 400 Series GPS Navigator - Serials 1005 thru 2015, 2016 & subs w/o Perspective Avion-ics (See Figure 34-501)

(1) Removal - Garmin 400 Series GPS Navigator(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 trans-

ceiver unit out 0.25 inch (0.64 cm) and disengage from the electrical connectors.

CAUTION: For dual GNS or GNS/GNC configurations, note positions for GPS1 and GPS2 when originally installed transceivers will be replaced.

(e) Pull transceiver from mounting tray.(2) Installation - Garmin 400 Series GPS Navigator

CAUTION: When mounting the transceivers, do not press on display window as dam-age may result.

For dual GNS or GNS/GNC configurations, verify when replacing originally installed transceivers that GPS1 and GPS2 positions are retained.

(a) 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 400 Series GPS Navigator Setup. (Refer to 34-50)2 Perform Functional Test - Garmin 400 Series GPS Navigator Clock Setup. (Refer to

34-50)3 Serials w/ Dual GNS: Perform Functional Test - Dual Garmin 400 Series GPS Navi-

gator Crossfill Setup. (Refer to 34-50)4 Perform Operational Test - Garmin 400 Series GPS Navigator VHF COM Check.

(Refer to 34-50)(f) If transceiver is the same unit as the originally installed transceiver:

1 Serials w/ Dual GNS: Perform Functional Test - Dual Garmin 400 Series GPS Navi-gator Crossfill Setup. (Refer to 34-50)

2 Perform Operational Test - Garmin 400 Series GPS Navigator VHF COM Check. (Refer to 34-50)

(3) Operational Test - Garmin 400 Series GPS Navigator VHF COM CheckA flight test is recommended after the installation to verify satisfactory performance. To check the communications transceiver:

(a) 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.

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Serials 1005 thru 2015, 2016 & subs w/o Perspective Avionics

EFFECTIVITY:


01 Jan 2012

(4) Functional Test - Garmin 400 Series GPS Navigator 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 transceiver(s), rotate [C] knobs for COM power counter-clockwise to OFF positions.

Note: Right data card slot contains blank card.

(e) On transceiver(s), verify data cards are installed for GPS1 and, if applicable, GPS2 in left data card slot.

(f) While holding [ENT], rotate [C] knobs for COM power clockwise to ON positions. Release [ENT] after display is on.

(g) After power-up, the Self Test pages will display, followed by the Database page. (h) On dual GNS or GNS/GNC units, verify GPS1 and GPS2 have the same MAIN SOFT-

WARE VERSION, GPS SOFTWARE VERSION, and CYCLE numbers displayed.(i) On the Database page, press [ENT]. (j) On the Instrument Panel Self-Test page, press [ENT]. (k) Navigate subsequent pages by use of transceiver 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 GPS1.

SPEED DATA

IN 1 - Serials 1005 thru 1422 w/ Century HSI Low Off

IN 1 - Serials 1005 thru 1422 w/ Sandel EHSI, Serials 1337 thru 1422 w/ PFD, 1423 & subs

Low Sandel EHSI

IN 2 - Serials 1005 & subs w/o SkyWatch and w/ GNC 420W/GNS 430W

Low Off

IN 2 - Serials 1005 & subs w/ SkyWatch and w/o GNC 420W/GNS 430W

Low Traffic Advisory

IN 2 - Serials 1005 & subs w/ SkyWatch and w/ GNC 420W/GNS 430W

High Traffic Advisory

OUT Low GAMA 429 grph w/int

SDI LNAV 1

VNAV - Serials w/ PFD S/W Rel. 6.2.2 or lower

Disable Labels



Avionics

EFFECTIVITY:

2 Set parameters for the Main ARINC 429 Config page for GPS2.

3 Set parameters for the Main RS232 Config page for GPS1 and GPS2.

4 The Main Inputs 1 page is not used.5 The Main Inputs 2 page is not used.

VNAV - Serials w/ PFD S/W Rel. 7.0 or higher Enable Labels

SPEED DATA

IN 1 - Serials 1005 thru 1336, 1337 thru 1422 w/o PFD

Low Off

IN 1 - Serials 1337 thru 1422 w/ PFD, 1423 thru 2015, 2016 & subs w/o Perspective Avi-onics

Low Sandel EHSI

IN 2 - Serials 1005 & subs w/o SkyWatch and w/ GNC 420W/GNS 430W

Low Off

IN 2 - Serials 1005 & subs w/ SkyWatch and w/o GNC 420W/GNS 430W

Low Traffic Advisory

IN 2 - Serials 1005 & subs w/ SkyWatch and w/ GNC 420W/GNS 430W

High Traffic Advisory

OUT Low GAMA 429 grph w/int

SDI LNAV 2

VNAV - Serials w/ PFD S/W Rel. 6.2.2 or lower

Disable Labels

VNAV - Serials w/ PFD S/W Rel. 7.0 or higher Enable Labels

INPUT OUTPUT

CHAN 1 Icarus-alt Aviation

CHAN 2 - Serials 1005 & subs w/o TAWS Off Off

CHAN 2 - Serials 1005 & subs w/ TAWS Off HW EGPWS

CHAN 3 Crossfill Crossfill

CHAN 4 - Serials 1005 & subs w/o Stormscope and GNC/GNS Main S/W Rel. 2.0 or lower

Off Off

CHAN 4 - Serials 1005 & subs w/ Stormscope and GNC/GNS Main S/W Rel. 3.0 or higher

WX 500 Off

FUEL TYPE AV gas

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EFFECTIVITY:


01 Jan 2012

6 Set parameters for the Instrument Panel Self-Test page.

7 For the Main Lighting page, cover photocell and observe that display slowly dims and lighting values decrease.

Note: Main Lighting page values may differ from those below due to your unique lighting environment.

8 Set parameters for the Main Lighting page.

9 Set parameters for the Date/Time Setup page.10 Set parameters for the Main Discrete Inputs page.

11 The Main Discrete Outputs page is not used.12 Serials 1005 thru 1422 w/ Century HSI: Set parameters for the Main CDI/ OBS Con-

fig page.

LCDI Half Left

LFLG Out of View

TO/FRM To

RMI 135°

DTK 150°

DISPLAY KEY

LIGHTING 0-9999 0-9999

SOURCE PHOTO 28VDC

RESP TIME/MIN 4 080 4 40

SLOPE/OFFSET 50 50 50 50

GRAY CODE 00000000000

DECODED ALTITUDE _ _ _ _ _ _ ft

RMT CDI unchecked

RMT OBS unchecked

CDI NAV FLAG TO-FROM

LAT Center Hidden Hidden

VERT Center Hidden

SELECTED COURSE 148° Calibrate to 150°?

CDI GPS

OBI SOURCE Track CDI

VERT Flag Center



Avionics

EFFECTIVITY:

13 Serials 1005 thru 1422 w/ Century HSI: Toggle settings to verify outputs display cor-rectly for the corresponding indicators.

14 Serials 1005 thru 1422 w/ Century HSI: Set OBS dial on HSI to “150°”.15 Serials 1005 thru 1422 w/ Century HSI: Select “Calibrate To 150°?”, then press

[ENT].16 Serials 1005 thru 1422 w/ Century HSI: Set OBS to other headings around dial to

verify correct readings.17 Serials 1005 thru 1422 w/ Sandel EHSI, 1337 thru 1422 w/ PFD, 1423 & subs: The

Main CDI / OBS Config page is not used.18 Set parameters for the COM Setup page for COM1 and COM2.

19 The VOR Discrete Inputs page is not used.

Note: Set DME CGNL MODE only. Do not adjust any other settings.

20 Set parameters for the VOR/LOC/GS CDI page.

CDI NAV FLAG TO-FROM

LAT Max LeftFull LeftCenterFull RightMax Right

HiddenIn View

FromHiddenTo

VERT Max UpFull UpCenterFull DownMaxDown

HiddenIn View

FREQ 136.975

SPACING 25.0 KHz

S 250 10

S 833 08

SIDE 07

MIC 44

CDI FLAG S-FLG TO-FR

LAT Center Hide Hide From

VERT Center Hide Hide

SELECTED COURSE No input

DME CGNL MODE Parallel 2x5

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EFFECTIVITY:


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21 Set parameters for the VOR / LOC / GS ARINC 429 Config page for GPS1.

22 Set parameters for the VOR / LOC / GS ARINC 429 Config page for GPS2.

23 Serials w/ GNC 420W or GNS 430W: Set parameters for the GPS Vertical Offset page.

24 Serials w/ GNC 420 or GNS 430 and GNC/GNS Main S/W Rel. 5.01 or higher: On the Main System Config page, set parameters for GPS1 and GPS2.

25 Serials w/ GNC 420 or GNS 430 and GNC/GNS Main S/W Rel. 5.01 or higher: High-light the TEST CARD field, then press [ENT]. Verify the TEST CARD field indicates “Pass”.

(l) When setup is completed, on transceiver(s), rotate [C] knobs for COM power counter-clockwise to OFF positions.

(m) Allow display to blank completely.(n) On transceiver(s), rotate [C] knobs for COM power clockwise to ON positions.

The Self-Test pages will be displayed followed by the Database page.

(o) On the Database page, press [ENT]. (p) Set parameters on the Instrument Panel Self-Test page.

RX TX

SPEED Low Low

SDI VOR / ILS 1

DME MODE Directed freq 1

RX TX

SPEED Low Low

SDI VOR / ILS 2

DME MODE Directed freq 2

GPS ANTENNA HEIGHT ABV GND 6.0ft

CONFIGURE Terrain

TERRAIN TYPE Terrain

TEST CARD Untested

HW CONFIG Terrain

LCDI Half Left

LFLG Out of View

VCDI Half Up

VFLG Out of View



Avionics

EFFECTIVITY:

(q) Verify parameters for self-test data output by GNS 430(W) on the displays indicated.

(r) On transceiver(s), press [ENT]. Upon approval of the Database page, the Satellite Status page will be displayed.

(s) Serials w/ GNC 420W or GNS 430W: Verify continuous GPS reception during COM trans-missions for GPS1 and GPS2.1 Using large outer RH knob, select NAV group.2 Rotate small RH knob to select Satellite Status page.3 On audio panel, select “COM1”.4 Set COM1 to each of the following frequencies and verify that the reception of GPS1

and GPS2 is not lost during a COM transmission.

5 On audio panel, select “COM2”.

CAP 56gl

FOB 0gl

FF 0.0gl

TO/FRM To

RMI 135°

OBS 150°

ANNUN On

DTK 150°

Display Parameter Self-Test

VOR and HSI/PFD Course Deviation ½ scale left deviation, TO flag, NAV flag pulled

VOR and HSI - Serials 1005 thru 1336, 1337 thru 1422 w/o PFD

Glidescope/ Vertical Deviation

½ scale up deviation, GS flag pulled

MFD and EHSI/PFD Active Waypoint (WPT) "GARMN"

MFD and EHSI/PFD Distance To Go (DIS) 10.0 nautical miles

MFD and EHSI/PFD Desired Track (DTK) 150°

MFD and EHSI/PFD Bearing to Wpt (BRG) 135°

MFD and EHSI/PFD Groundspeed (GS) 150 knots

MFD and EHSI - Serials 1005 thru 1336, 1337 thru 1422 w/o PFD

Track (TRK) 135°

MFD and EHSI/PFD Time to Go (ETE) 4 minutes

121.150 MHz 121.225 MHz 131.225 MHz 131.300 MHz

121.175 MHz 121.250 MHz 131.250 MHz 131.325 MHz

121.200 MHz 131.200 MHz 131.275 MHz 131.350 MHz

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EFFECTIVITY:


01 Jan 2012

6 Set COM2 to each of the following frequencies and verify that the reception of GPS1 and GPS2 is not lost during a COM transmission.

(t) Serials 1337 thru 1422 w/ PFD, 1423 & 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(W).3 On PFD, press [Nav1] to select "VLOC1".4 Verify CDI setting on GNS 430(W) changes to "VLOC".5 On GNS 430(W), press [CDI] to select "GPS".6 On PFD, verify Nav1 selection changes back to "GPS1".7 If applicable, repeat coupling procedure for the lower GNS 430(W) or GNC 420(W).

(u) Reset STARTER RELAY and FUEL PUMP RELAY circuit breakers.(v) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.(w) Disconnect 28 ±1 VDC external power from external power receptacle.

(5) Functional Test - Garmin 400 Series GPS Navigator 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.

(6) Functional Test - Dual Garmin 400 Series GPS Navigator 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.

121.150 MHz 121.225 MHz 131.225 MHz 131.300 MHz

121.175 MHz 121.250 MHz 131.250 MHz 131.325 MHz

121.200 MHz 131.200 MHz 131.275 MHz 131.350 MHz


34-50All

EFFECTIVITY:

B. Garmin GNC 250XL GPS Navigator (See Figure 34-501)

(1) Removal - Garmin GNC 250XL GPS Navigator(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 trans-

ceiver unit out 0.25 inch (0.64 cm) and disengage from the electrical connectors.

CAUTION: For dual GNS or GNS/GNC configurations, note positions for GPS1 and GPS2 when originally installed transceivers will be replaced.

(e) Pull transceiver from mounting tray.(2) Installation - Garmin GNC 250XL GPS Navigator

CAUTION: When mounting the transceivers, do not press on display window as dam-age may result.

For dual GNS or GNS/GNC configurations, verify when replacing originally installed transceivers that GPS1 and GPS2 positions are retained.

(a) 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 250XL GPS Navigator Setup. (Refer to 34-50)

2 Perform Functional Test - Garmin GNC 250XL GPS Navigator Clock Setup. (Refer to 34-50)

3 Perform Operational Test - Garmin GNC 250XL GPS Navigator Check. (Refer to 34-50)

(f) If transceiver is the same unit as the originally installed transceiver:1 Perform Operational Test - Garmin GNC 250XL GPS Navigator Check. (Refer to 34-

50)(3) Operational Test - Garmin GNC 250XL GPS Navigator Check

A flight test is recommended after the installation to verify satisfactory performance. To check the communications transceiver:

(a) 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.(4) Functional Test - Garmin GNC 250XL GPS Navigator 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 GNC 250XL, rotate LH power/volume knob counter-clockwise to OFF position.

01 Jan 2012

34-50

AllEFFECTIVITY:


01 Jan 2012

(e) Remove data card from LH data card slot. (f) Rotate LH power/volume knob for COM power clockwise to ON position. (g) When SELECT OPERATING MODE NORMAL OK? is displayed, press [ENT].(h) When NO JEPPESEN DATABASE RTE/PRX LIMITED TO USER WPTS OK? is displayed,

press [ENT].(i) After the Satellite Status page is displayed for 5 seconds, rotate power/volume knob for

COM power counter-clockwise to OFF position.(j) Install data card to LH data card slot. (k) While holding [ENT], rotate LH power/volume knob for COM power clockwise to ON posi-

tion. (l) When the Display Test page is displayed, release [ENT].(m) Navigate subsequent pages by use of GNC 250XL controls.

Note: Only the GPS indicated by the NAV selection on the PFD will be displayed. Not all parameters are editable.

To turn on and off cursor, press [CRSR].

To move between pages, rotate outer dial of RH knob.

To move between selections, rotate inner dial of RH knob.

1 Verify cursor is off.2 Verify for the Display Test page that uniform color is appears on screen as display

tests are cycled.3 Verify for the Key Test page that depressing a key causes the corresponding key on

the display to light up.4 Set parameters for the Lighting page.

5 The I/O Channel 1 page is not used.6 The ARINC 429 page is not used.7 The CDI Calibration page is not used.8 Set parameters for the Config Fuel page.

9 The Remote Battery page is not used.10 Set parameters for the Volume page.

11 Set parameters for the Signal page.

SLOPE 20

MIN 50

RESPONSE TIME 6

CONFIG FUEL av gas

VOLUME 39 dB

SVID 16

SNR 0.0


34-50All

EFFECTIVITY:

12 The OBI Test page is not used.13 Set parameters for the Altitude Input Test page.

Note: The gray code alt should be approximately 1400 ft ±300 feet.

14 The Communications Loopback Test page is not used.15 Verify for the External Switch Test page that pressing pilot and co-pilot PTT switches

on LH and RH yokes changes fields in display from “off” to “on”.16 Set parameters for the Annunciator Test page.

17 The CDI and Flag Test page is not used.18 Set parameters for the Power Test page.

19 Rotate power/volume knob for COM power counter-clockwise to OFF position, then clockwise to ON position.

20 The Self-Test pages will be displayed followed by the Database page.21 On the Database page, press [ENT]. 22 Verify the Satellite Status page is displayed.23 Rotate LH power/volume knob for COM power counter-clockwise to OFF position.

(n) Reset STARTER RELAY and FUEL PUMP RELAY circuit breakers.(o) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.(p) Disconnect 28 ±1 VDC external power from external power receptacle.

(5) Functional Test - Garmin GNC 250XL GPS Navigator Clock Setup(a) Set BAT 1 and AVIONICS switches to ON positions.(b) On GNC unit, rotate LH power/volume knob for COM power clockwise to ON position. (c) When SELECT OPERATING MODE NORMAL OK? is displayed, press [ENT].(d) When NO JEPPESEN DATABASE RTE/PRX LIMITED TO USER WPTS OK? is displayed,

press [ENT].(e) After the Satellite Status page is displayed, press [NAV].(f) Rotate outer dial of RH knob to select the NAV Menu 2 page.(g) Press [CRSR] twice.

SGNL ~1500

DRFT 19.978

FQ 16367673

GRAY CODE ALT ~1400 ft

PANEL off

MSG off

ARRVL off

EXTERNAL POWER 14.0

RMT BAT none

MEM BAT ok

01 Jan 2012

34-50

AllEFFECTIVITY:


01 Jan 2012

(h) Rotate outer dial of RH knob to select “Clock?”, then press [ENT].(i) Rotate inner dial of RH knob to select “utc” or “local” for displayed time fields.(j) Rotate outer dial of RH knob to select local date.(k) Rotate inner dial of RH knob to set local date, then press [ENT].(l) Rotate outer dial of RH knob to select local time.(m) Rotate inner dial of RH knob to set local time, then press [ENT].(n) Press [CRSR].(o) Rotate LH power/volume knob for COM power counter-clockwise to OFF position. (p) Set BAT 1 and AVIONICS switches to OFF positions.



Avionics

EFFECTIVITY:

Figure 34-501Transceiver Installation - Serials 1005 thru 2015, 2016 & subs w/o Perspective Avionics

Airplanes with GNC 420 GPS in the COM 1 position do not have a GPS configured for the COM 2 position.

NOTE

Airplanes may be equipped with GNS 430 GPS in the COM 1 position with no GPS configured for the COM 2 position. SR20_MM34_1091B

LEGEND 1. GNC 250XL Transceiver 2. GNC 420 Transceiver 3. GNS 430 Transceiver

2 or 3

INSTRUMENT PANEL (REF)

1, 2 or 3

01 Jan 2012

34-50

Serials 1005 thru 1801, 1803 thru 1815EFFECTIVITY:


01 Jan 2012

C. GPS1 / GPS2 Antenna - Serials 1005 thru 1801, 1803 thru 1815 (See Figure 34-502)

(1) Removal - GPS1 / GPS2 Antenna(a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.(b) Pull ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers.(c) Serials 1005 thru 1422: For GPS1, remove cabin headliner. (Refer to 25-10)(d) Serials 1423 thru 1801, 1803 thru 1815: For GPS1, remove glareshield. (Refer to 25-10)(e) For GPS2, remove glareshield. (Refer to 25-10)(f) Disconnect antenna cable from antenna.(g) Pry antenna from hook and loop fastener securing antenna to installation area.(h) Remove antenna from airplane.

(2) Installation - GPS1 / GPS2 Antenna(a) To secure antenna to installation area, firmly press fastener strip on antenna against fas-

tener strip.(b) Connect antenna cable.(c) Reset ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers.(d) Serials 1005 thru 1422: For GPS1, install cabin headliner. (Refer to 25-10)(e) Serials 1423 thru 1801, 1803 thru 1815: For GPS1, install glareshield. (Refer to 25-10)(f) For GPS2, install glareshield. (Refer to 25-10)


34-50Serials 1802, 1816 & subs

EFFECTIVITY:

D. WAAS GPS1 / GPS2 Antenna - Serials 1802, 1816 & subs (See Figure 34-502)

(1) Removal - WAAS GPS1 / GPS2 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 GPS cable from antenna.(e) Serials w/ XM Weather: Disconnect XM Weather cable from antenna.(f) Serials w/ Iridium Weather: Disconnect Iridium Weather cable from antenna.(g) Remove nuts, washers, and screws securing antenna to fuselage.(h) Remove antenna and gasket from fuselage.(i) Remove remaining sealant from fuselage.

(2) Installation - WAAS GPS1 / GPS2 Antenna

(a) Acquire necessary tools, equipment, and supplies.

(b) Position gasket and antenna to fuselage and insert screws through mounting holes.

CAUTION: To prevent damage to rubber gasket at screwhead, turn nuts onto screws during installation.

Note: Tighten forward screws prior to tightening aft screws.

(c) Install washers and nuts securing antenna to fuselage. Torque nuts to maximum of 20 - 25 in-lb (2.26 - 2.82 Nm).

(d) Fillet seal antenna perimeter. (Refer to 20-10)(e) Connect GPS cable to antenna.(f) Serials w/ XM Weather: Connect XM Weather cable to antenna.(g) Serials w/ Iridium Weather: Connect Iridium Weather cable to antenna.(h) Install cabin headliner. (Refer to 25-10)(i) Reset ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers.

Description P/N or Spec. Supplier Purpose

Caulk Sealant (Refer to 51-30) (Refer to 51-30) Weather sealant.

01 Jan 2012

34-50

Serials 1005 thru 1801, 1803 thru 1815EFFECTIVITY:


01 Jan 2012

Figure 34-502GPS Antenna Installation - Serials 1005 thru 1801, 1803 thru 1815 (Sheet 1 of 2)

Serials 1423 thru 1801, 1803 thru 1815.

Serials 1005 thru 1422 after SB 2X-34-06.

Serials 1005 thru 1422 before SB 2X-34-06.

NOTE

GPS 1 installed on cabin ceiling.

GPS 2 installed on glareshield.

GPS 1 installed on RH glareshield.

GPS 2 installed on LH glareshield.

GPS 1 installed on RH outboard glareshield.

GPS 2 installed on RH inboard glareshield.SR20_MM34_1090H

CABIN CEILING (REF)OR

GLARESHIELD (REF)


34-50Serials 1802, 1816 & subs

EFFECTIVITY:

Figure 34-502WAAS GPS Antenna Installation - Serials 1802, 1816 & subs (Sheet 2 of 2)

56

7

3

4

2

FUSELAGE(REF)

Serials 2127 & subsw/ WAAS GPS2.

3

NOTE

Optional Iridium Weather system installation.

Serials 1802, 1816 & subs w/ WAAS GPS1 w/o XM Weather,Serials 1005 thru 1422 after SB 2X-34-23 w/o XM WeatherSerials 1337 thru 1801, 1803 thru 1815 after SB 2X-34-24w/o XM Weather.

FUSELAGE(REF)

FUSELAGE(REF)

Serials 1802, 1816 & subs w/ WAAS GPS2,Serials 1005 thru 1422 after SB 2X-34-23,Serials 1337 thru 1801, 1803 thru 1815after SB 2X-34-24.

3

4

56

7

56

7

3 LEGEND 1. WAAS GPS 1 Antenna 2. WAAS GPS 2 Antenna 3. Antenna Connector 4. Screw 5. Washer 6. Nut 7. Gasket

4

1

2

SR20_MM34_2564B

01 Jan 2012

34-50

Serials 1613 & subs, Serials 1005 thru 1612 before SB 2X-34-06 w/ combo antenna in kit, 1005 thru 1612 after SB 2X-34-06 w/o combo antenna in kit

EFFECTIVITY:


01 Jan 2012

E. COM1 Antenna - Serials 1613 & subs, Serials 1005 thru 1612 before SB 2X-34-06 w/ combo antenna in kit, 1005 thru 1612 after SB 2X-34-06 w/o combo antenna in kit (See Figure 34-503)

(1) Removal - COM1 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.

(2) Installation - COM1 Antenna


(b) Position gasket and antenna on fuselage roof, then insert screws through mounting holes.(c) Install washers and nuts securing antenna to fuselage.(d) Fillet seal antenna perimeter. (Refer to 20-10)(e) Connect antenna cable.(f) Install cabin headliner. (Refer to 25-10)(g) Reset ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers.




34-50Serials 1473 thru 1581 w/ factory installed XM

Weather, Serials 1005 thru 1612 after SB 2X-34-06 w/ COM1 / XM antenna in kit

EFFECTIVITY:

01 Jan 2012

F. COM1 / XM Weather Antenna - Serials 1473 thru 1581 w/ factory installed XM Weather, Serials 1005 thru 1612 after SB 2X-34-06 w/ COM1 / XM antenna in kit (See Figure 34-503)

(1) Removal - COM1 / 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 COM1 cable from antenna.(f) Remove nuts, washers, and screws securing antenna to fuselage.(g) Remove antenna and gasket from top of fuselage.(h) Remove remaining sealant from fuselage.

(2) Installation - COM1 / XM Weather Antenna


(b) Position gasket and antenna to fuselage and insert screws through mounting holes.(c) Install washers and nuts securing antenna to fuselage.(d) Fillet seal antenna perimeter. (Refer to 20-10)(e) Connect XM Weather cable to antenna.(f) Connect COM1 cable to antenna.(g) Install cabin headliner. (Refer to 25-10)(h) Reset ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers.



34-50

AllEFFECTIVITY:


G. COM2 Antenna (See Figure 34-503)

(1) Removal - COM2 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.

(2) Installation - COM2 Antenna


(b) Position gasket and antenna on fuselage belly, then insert screws through mounting holes.(c) Install washers and nuts securing antenna to fuselage.(d) Fillet seal antenna perimeter. (Refer to 20-10)(e) Connect antenna cable.(f) Install baggage compartment floor access panel. (Refer to 06-00)(g) Reset ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers.



01 Jan 2012


34-50All

EFFECTIVITY:

01 Jan 2012

Figure 34-503COM Antenna Installation

Serials 1613 & subs, Serials 1005 thru 1612before SB 2X-34-06 w/ COM 1 / XM antenna in kit,

Serials 1005 thru 1612 after SB 2X-34-06w/o COM 1 / XM antenna in kit.

76

4

52

4

1

6

7

5

FUSELAGE(REF)

FUSELAGE(REF)

8

8

3

5

7

6

4

BAGGAGECOMPARTMENT

FLOOR (REF)

8

Serials 1456 thru 1581 w/ factory XM Weather,Serials 1005 thru 1612 after SB 2X-34-06

w/ COM 1 / XM antenna in kit.

SR20_MM34_2472A

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

34-50


EFFECTIVITY:


H. Garmin GTX Transponder - Serials 1005 thru 2015, 2016 & subs w/o Perspective Avionics (See Figure 34-504)

(1) 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.

(2) 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 1005 thru 1099 w/ GTX 320 Transponder: Perform Functional Test - Garmin GTX 320 Transponder Setup. (Refer to 34-50)

2 Serials 1100 & subs w/ GTX 327 Transponder: Perform Functional Test - Garmin GTX 327 Transponder Setup. (Refer to 34-50)

3 Serials 1337 & 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)

(3) Operational Test - Garmin Transponder(a) Verify transponder operation in accordance with 14 CFR 91.413.

(4) Functional Test - Garmin GTX 320 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 320, rotate RH function selector switch to SBY position.(d) Set code selector switches to “1200”(e) Rotate RH function selector switch to TST position.(f) Verify reply indicator light is on.(g) Rotate RH function selector switch to ON position.(h) Verify reply indicator light flashes on and off.(i) Rotate SBY selector switch to OFF position.(j) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.(k) Reset STARTER RELAY and FUEL PUMP RELAY circuit breakers.

(5) 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 selec-tions with 8 or 9 keys.

01 Jan 2012



Avionics

EFFECTIVITY:

01 Jan 2012

To accept changes, press [CRSR] key. Pressing [FUNC] key moves on to the next configu-ration page without saving the changes.

1 Set parameters for the Display Mode page.

2 Set parameters for the Display Backlight page.

3 Set parameters for the Key Lighting page.

4 Set parameters for the Contrast Configuration page.

5 Set parameters for the RS-232 Input/Output page.

6 Set parameters for the Operation Configuration page.

DISPLAY MODE AUTO

LEVEL 75

BKLT AUTO

RSP TIME 4

MIN 08

BKLT SRCE PHOTO

SLOPE 50

OFFSET 50

KEY AUTO

RSP TIME 4

MIN 08

KEY SRCE 28V

SLOPE 50

OFFSET 50

CONTRAST MODE AUTO

INPUT OUTPUT

CHNL 1 OFF ICARUS ALT

CHNL 2 GPS

VS RATE 0500

FLT TMR CLEAR

VFR ID 1200

34-50


EFFECTIVITY:


7 Set parameters for the Squat Switch page.

8 Set parameters for the Aircraft Type page.

9 Set parameters for the RS-232 INPUT VIEW page.

Note: With GPS in self-test mode, GSPD should read 150 kts.

10 Set parameters for the Gray Code Input page.

Note: No external switches are used.

11 Set parameters for the External Switch page.

12 Set parameters for the Analog Input page.

FORMAT FEET

SQUAT SWITCH? NO

SENSE LOW

AUTO STANDBY? ON

DELAY TIME 10

AC TYPE <15.5K lb

CH1 OFF + _ _ _ _ _ _ . _ _ n/a

CH2 GSPD + _ _ _ 1 5 0 . 0 0 kts

GRAY CODE ##########

DECODED ALTITUDE #### (Field Eleva-tion ±300 ft)

IDENT unchecked

STANDBY unchecked

SQUAT unchecked

14/5V LTG 000

PHOTO 000

LCD TEMP 000

28V LTG 000

REPLY 000

UNIT TMP 000

01 Jan 2012



Avionics

EFFECTIVITY:

01 Jan 2012

13 Press [OFF] to exit setup.(e) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.(f) Reset STARTER RELAY and FUEL PUMP RELAY circuit breakers.

(6) 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 selec-tions with 8 or 9 keys.

To accept changes, press [CRSR]. Pressing [FUNC] moves on to the next configuration page without saving changes.

Note: The MODE S Address (A/C Reg) page will only be displayed on initial power-up if no address is entered.

1 Set parameters for the MODE S Address (A/C Reg) page.

2 Set parameters for the Configuration Menu page.

3 Set parameters for the Audio Mode pages. Verify audio messages by selecting 2, 3, 4, or 5 for MESSAGE.

4 Set parameters for the Traffic Information page.

5 Set parameters for the Display Mode page.

ADDRESS US TAIL# NXXX

JUMP TO DIAGNOSTICS

VOICE FEMALE

MESSAGE 0

AUDIO PAGE CHANGE

ALTITUDE MONITOR MSG ENABLE

COUNT DOWN TIMER MSG

TRAFFIC MESSAGES TONE

DISPLAY MODE AUTO

LEVEL 75

34-50


EFFECTIVITY:


6 Set parameters for the Display Backlight page.

7 Set parameters for the Key Lighting page.

8 Set parameters for the Contrast Configuration page.

9 Set parameters for the ARINC 429 Input pages.

10 Set parameters for the ARINC 429 Output page.

11 Set parameters for the RS-232 Input/Output page.

BKLT AUTO

RSP TIME 4

MIN 08

BKLT SRCE PHOTO

SLOPE 50

OFFSET 50

KEY AUTO

RSP TIME 4

MIN 08

KEY SRCE 28V

SLOPE 50

OFFSET 50

CONTRAST MODE AUTO

SPEED DATA

CHANNEL 1 LOW GPS

CHANNEL 2 LOW OFF

SPEED DATA

CHANNEL 3 LOW OFF

CHANNEL 4 OFF

CHANNEL 1 OFF

CHANNEL 2 OFF

INPUT OUTPUT

01 Jan 2012



Avionics

EFFECTIVITY:

01 Jan 2012

12 Set parameters for the Operation Configuration page.

13 Set parameters for the Squat Switch page.

14 Set parameters for the Temperature page.

15 Set parameters for the Mode S Address (A/C Reg) page.

16 Set parameters for the Mode S Address (Flight ID) page.

17 Set parameters for the Mode S Aircraft Type page.

18 Set parameters for the Gray Code Input page.

Note: No external switches are used.

CHNL 1 OFF ICARUS ALT

CHNL 2 OFF OFF

VS RATE 0500

FORMAT FEET

VFR ID 1200

ALT ALRT DEV 200

SQUAT SWITCH? NO

SENSE LOW

DELAY TIME 10

AUTO FLT TMR? CLEAR

SENSOR INSTALLED NO

ADDRESS US TAIL# NXXX

FLT ID SAME AS TAIL

AC TYPE <15.5K lb

MAX A/S <=300 kt

GRAY CODE ##########

DECODED ALTITUDE #### (Field Eleva-tion ±300 ft)

34-50


EFFECTIVITY:


19 Set parameters for the External Switch page.

20 Set parameters for the Analog Input page.

21 Set parameters for the RS-232 Input page.

22 Set parameters for the ARINC 429 Channel pages.

Note: With GPS in self-test mode, GSPD should read 150 kts.

23 Press [OFF] to exit setup.(e) Set BAT 1, BAT 2, and AVIONICS switches in OFF positions.(f) Reset STARTER RELAY and FUEL PUMP RELAY circuit breakers.

IDENT unchecked

STANDBY unchecked

SQUAT unchecked

14/5V LTG 000

PHOTO ###

LCD TEMP ###

28V LTG 000

REPLY 000

UNIT TMP ###

CH1 OFF + _ _ _ _ _ _ . _ _ n/a

CH2 OFF + _ _ _ _ _ _ . _ _ n/a

CH1 ### + _ _ _ 1 5 0 . 0 0 kts

CH2 000 + _ _ _ _ _ _ . _ _ n/a

CH3 000 + _ _ _ _ _ _ . _ _ n/a

CH4 000 + _ _ _ _ _ _ . _ _ n/a

01 Jan 2012



Avionics

EFFECTIVITY:

01 Jan 2012

I. Transponder Antenna - Serials 1005 thru 2015, 2016 & subs w/o Perspective Avionics (See Fig-ure 34-504)

(1) Removal - Transponder Antenna(a) Remove access panel CF8. (Refer to 06-00)(b) Disconnect antenna cable from antenna.(c) Verify transponder antenna is supported and remove nut and washers securing antenna to

fuselage belly.(d) Remove antenna from airplane.

(2) Installation - Transponder Antenna(a) Solvent clean installation area. (Refer to 20-30)(b) Verify transponder antenna is inserted and supported in antenna mounting hole in fuse-

lage belly by another aircraft technician.(c) Install washers and nut securing antenna to fuselage belly.(d) Connect antenna cable to antenna.(e) Install access cover CF8. (Refer to 06-00)

34-50


EFFECTIVITY:


Figure 34-504Transponder and Antenna Installation - Serials 1005 thru 2015, 2016 & subs w/o Perspective Avionics

SR20_MM34_1546C

DRAIN

5

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

7

9

4

3

6

6

8

4

5

6

7

8

9

12

FUSELAGE BELLY (REF)

FUSELAGE BELLY (REF)

Serials 1005 thru 1361before SB 2X-34-05.

Serials 1362 & subs,Serials 1005 thru 1361after SB 2X-34-05.

6

Typical installation shown.Avionics stackup may change based on optional equipment installation.

NOTE

01 Jan 2012


34-50Serials 2016 & subs w/ Perspective Avionics

EFFECTIVITY:

19 Sep 2017

J. Garmin GTX Transponder - Serials 2016 & subs w/ Perspective Avionics (See Figure 34-505)

(1) Removal - Garmin GTX Transponder(a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.(b) Pull XPONDER circuit breaker.(c) Remove empennage access panel RE3. (Refer to 06-00)(d) Remove ELT. (Refer to 25-60)(e) Loosen screw securing handle-lock mechanism to transponder.(f) Lift handle-lock mechanism to disengage transponder from connectors.(g) Remove transponder from rack.

(2) Installation - Garmin GTX Transponder(a) Position transponder to rack, ensuring handle-lock mechanism engages slot on side of

rack.(b) Using handle-lock mechanism, gently push transponder into rack to engage connectors.(c) Tighten screw securing handle-lock mechanism to transponder.(d) Reset XPONDER circuit breaker.(e) If transponder is a different unit from the originally installed transponder, perform Adjust-

ment/Test - Component Software and Configuration Loading. (Refer to 42-00)(f) Perform Adjustment/Test - Garmin GTX Transponder Setup. (Refer to 34-50)(g) Perform Operational Test - Garmin GTX Transponder. (Refer to 34-50)(h) Install ELT. (Refer to 25-60)(i) Install empennage access panel RE3. (Refer to 06-00)

(3) Operational Test - Garmin GTX Transponder(a) Verify transponder operation in accordance with 14 CFR 91.413.

(4) Adjustment/Test - Garmin GTX Transponder Setup(a) Power on PFD and MFD in Configuration mode.

1 While holding far right softkey on PFD and MFD, set BAT 1 and AVIONICS switches to ON positions.

2 When “INITIALIZING SYSTEM” appears in upper left corner of displays, release softkeys.

(b) On PFD, use [FMS] knob to select GTX page group.(c) Select Transponder Configuration page.(d) Verify 'ADDRESS TYPE' is 'US TAIL' under the 'SET' and 'ACTIVE' columns.(e) Activate cursor and highlight 'ADDRESS' field. On PFD, use inner and outer [FMS] knobs

to enter aircraft registration number.(f) On PFD, press [ENT] key.(g) When transponder has successfully configured, press [ENT] key on PFD to accept the

message.(h) Deactivate cursor.(i) Pull PFD#1, PFD#2, MFD#1, MFD#2 circuit breakers.(j) Reset PFD and MFD circuit breakers to restart displays in normal operating mode.

34-50

Serials 2016 & subs w/ Perspective AvionicsEFFECTIVITY:


K. Transponder Antenna - Serials 2016 & subs w/ Perspective Avionics (See Figure 34-505)

(1) Removal - Transponder Antenna(a) Remove empennage access panel RE3. (Refer to 06-00)(b) Disconnect antenna cable from antenna.(c) With antenna supported, remove nut and washers securing antenna to empennage.

Remove antenna from airplane.(2) Installation - Transponder Antenna


(b) Solvent clean installation area. (Refer to 20-30)(c) To ensure electrical contact, sand or burnish EMM where washer contacts empennage

skin. (Refer to 51-20)(d) Position antenna to empennage and secure with washers and nut.(e) Torque nut as necessary to ensure antenna collar makes electrical contact with washer.(f) Apply sealant to perimeters of washers and base of antenna. (g) Connect antenna cable to antenna.(h) Perform Operational Test - Garmin GTX Transponder. (Refer to 34-50)(i) Install empennage access cover RE3. (Refer to 06-00)



19 Sep 2017



EFFECTIVITY:

19 Sep 2017

Figure 34-505Transponder and Antenna Installation - Serials 2016 & subs w/ Perspective Avionics

1

2

3

4

MOUNTING SHELF(REF)

NOTE

EMPENNAGE SKIN (REF)

8

4

4

7

5

6

4

LEGEND 1. GTX Transponder 2. Rack 3. Screw 4. Washer 5. Transponder Antenna 6. Gasket 7. Nut 8. Antenna CableTo ensure electrical contact, sand or burnish EMM

where washer contacts empennage skin. SR20_MM34_2724

34-50

Serials 1005 thru 1336, 1337 thru 1422 w/o PFDEFFECTIVITY:


L. Course Deviation Indicator - Serials 1005 thru 1336, 1337 thru 1422 w/o PFD (See Figure 34-506)

(1) 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.(2) Installation - Course Deviation Indicator

(a) Position course deviation indicator in instrument panel and attach with screws and wash-ers.

(b) Connect electrical connector.(c) Install glareshield. (Refer to 25-10)(d) Reset INSTRUMENT LIGHTS circuit breaker.

19 Sep 2017


34-50Serials 1005 thru 1336, 1337 thru 1422 w/o PFD

EFFECTIVITY:

19 Sep 2017

Figure 34-506Course Deviation Indicator - Serials 1005 thru 1336, 1337 thru 1422 w/o PFD

Serials 1005 thru 1336, 1337 thru 1422 w/o PFD.

SR20_MM34_1605

INSTRUMENT PANEL (REF)

21

3

LEGEND1. Screw2. Washer3. Course Deviation Indicator

34-50

AllEFFECTIVITY:


M. VOR/LOC Antenna (See Figure 34-507)

(1) 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.

(2) Installation - VOR/LOC Antenna


(b) Remove old sealant and solvent clean antenna mounting surfaces. (Refer to 20-30)(c) Install screws securing antenna to antenna mounting plate.(d) Connect antenna cable to antenna.(e) Install antenna mounting plate assembly into vertical stabilizer recess.(f) Install screws securing antenna mounting plate to vertical stabilizer.(g) Solvent clean mounting plate surface. (Refer to 20-30)

CAUTION: Do not allow tape perimeter to exceed edges of mounting plate.

(h) Apply tape covering screw heads and 0.5 inch (1.27 cm) radius minimum around each screw head.

(i) Apply sealant around perimeter of antenna mounting plate.



19 Sep 2017



Avionics

EFFECTIVITY:

19 Sep 2017

N. VOR/LOC Diplexer - Serials 1005 thru 2015, 2016 & subs w/o Perspective Avionics (See Figure 34-507)

(1) 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) Remove screws and nuts securing diplexer to center console. Remove diplexer from air-

plane.(2) Installation - VOR/LOC Diplexer

(a) Position diplexer to center console and secure with screws and nuts.(b) Connect G/S 1, G/S 2, VOR 1, VOR 2, and ANT cables to diplexer.(c) Install radio module assembly. (Refer to 25-10)

34-50



O. VOR/LOC Diplexer - Serials 2016 & subs w/ Perspective Avionics (See Figure 34-507)

(1) Removal - VOR/LOC Diplexer(a) Remove sidewall air duct trim. (Refer to 25-10)(b) Disconnect G/S 1, G/S 2, VOR 1, VOR 2, and ANT cables from diplexer.(c) Remove cable ties securing diplexer to fuselage. Remove diplexer from airplane.

(2) Installation - VOR/LOC Diplexer(a) Position diplexer to fuselage and secure with cable ties.(b) Connect G/S 1, G/S 2, VOR 1, VOR 2, and ANT cables to diplexer.(c) Install sidewall air duct trim. (Refer to 25-10)

19 Sep 2017


34-50All

EFFECTIVITY:

19 Sep 2017

Figure 34-507VOR/LOC Antenna Installation

Serials 2156 & subsw/ Perspective Avionics.

FUSELAGE(REF)

12 10

11

13

LEGEND 1. VOR/LOC Antenna 2. Washer 3. Screw 4. Tape 5 Mounting Plate 6. Grommet 7. Connector, Straight 8. Nut 9. Antenna Cable10. Diplexer Antenna11. Connector, Right Angle12. Cable Tie13. Tie Down

SR20_MM34_1547D

NOTE

Apply tape covering screw heads and 0.50 inch (1.27 cm) minimumradius around each screw head. Do not allow tape to exceed edgesof mounting plate, except toward rudder hinge where upper boltsmust be contacted.

8

4

7

2

2

69

61

3

5

3

9

Serials 1005 thru 2015,2016 & subs w/o Perspective Avionics.

Serials 2016 thru 2155w/ Perspective Avionics.

FUSELAGE(REF)

12

11

3

10

8

CENTER CONSOLE(REF)

10

11

13

34-50

Serials 1005 thru 1267EFFECTIVITY:


P. NSD-360A HSI - Serials 1005 thru 1267 (See Figure 34-508)

(1) Removal - NSD-360A 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 vacuum and vent hoses and cap.(e) Disconnect electrical connector.(f) While supporting HSI, remove screws securing unit to instrument panel.(g) Cap off fittings on back of HSI to prevent possible contamination and remove HSI from air-

plane.(2) Installation - NSD-360A HSI

(a) Position HSI in instrument panel and secure with screws.(b) Connect electrical connector.(c) Attach vacuum and vent hoses.(d) Install MFD. (Refer to 31-60)(e) Reset HSI#1 and HSI#2 circuit breakers.(f) If NSD-360A HSI is a different unit from the originally installed NSD-360A HSI:

1 Perform Functional Test - Flux Detector Calibration with NSD-360A HSI Installed. (Refer to 34-50)

2 Perform Operational Test - NSD-360A HSI Setup. (Refer to 34-50)(g) If NSD-360A HSI is the same unit as the originally installed NSD-360A HSI:

1 Perform Operational Test - NSD-360A HSI Setup. (Refer to 34-50)(3) Operational Test - NSD-360A 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-360A 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) Set HSI switch to SLAVE position.(d) 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) Wait 5 minutes and verify the compass card remains on correct heading.(f) To test HSI navigation, perform Functional Test - Garmin 400 Series GPS Navigator

Setup. (Refer to 34-50)

CAUTION: Prior to verifying NSD-360A HSI system, verify that doors are closed, flaps are in retracted position, engine is running, and airplane is in level flight atti-tude.

Engine starting, taxiing, and shut-down may only be performed by autho-rized personnel.

Note: If compass rose is not available, a calibrated boresight compass may be used.

19 Sep 2017


34-50Serials 1005 thru 1267

EFFECTIVITY:

19 Sep 2017

(g) Acquire necessary tools, equipment, and supplies.

(h) Set BAT 1, BAT 2, ALT 1, ALT 2, PITOT HEAT, and all radio switches to ON positions.(i) Set all other cockpit controlled electrical switches to OFF positions.(j) Place airplane in as realistic flight environment as possible. (k) Taxi airplane to compass rose, if available.(l) If using compass rose for verification:

1 Align centerline of airplane on magnetic North heading (±1°).(m) 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 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.

(n) Align airplane with West and verify NSD-360A HSI system indicates 90° turn.(o) Align airplane with North and verify NSD-360A HSI system indicates 90° turn.(p) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.(q) Reset STARTER RELAY and FUEL PUMP RELAY circuit breakers.


Boresight Compass(if compass rose is unavailable)

±1° accuracy Any Source Verify NSD-360A HSI system.

34-50



Q. NSD-1000 HSI - Serials 1005 thru 1336, 1337 thru 1422 w/o PFD (See Figure 34-508)

(1) 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 air-

plane.(2) 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)(3) 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) Set HSI switch to SLAVE position.(d) 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) Wait 5 minutes and verify the compass card remains on correct heading.(f) To test HSI navigation, perform Functional Test - Garmin 400 Series GPS Navigator

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 atti-tude.

Engine starting, taxiing, and shut-down may only be performed by autho-rized personnel.


19 Sep 2017



EFFECTIVITY:

19 Sep 2017

(g) Acquire necessary tools, equipment, and supplies.

(h) Set BAT 1, BAT 2, ALT 1, ALT 2, PITOT HEAT, and all radio switches to ON positions.(i) Set all other cockpit controlled electrical switches to OFF positions.(j) Place airplane in as realistic flight environment as possible. (k) Taxi airplane to compass rose, if available.(l) If using compass rose for verification:

1 Align centerline of airplane on magnetic North heading (±1°).(m) If using boresight compass for verification:



(n) Align airplane with West and verify NSD-1000 HSI system indicates 90° turn.(o) Align airplane with North and verify NSD-1000 HSI system indicates 90° turn.(p) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.(q) Reset STARTER RELAY and FUEL PUMP RELAY circuit breakers.



±1° accuracy Any Source Verify NSD-1000 HSI system.

34-50



R. SN3308 EHSI - Serials 1005 thru 1336, 1337 thru 1422 w/o PFD (See Figure 34-508)

(1) Removal - SN3308 EHSI


(b) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.(c) Pull HSI#1 and HSI#2 circuit breakers.(d) Loosen top two screws above EHSI to remove tension from mounting tray.(e) Remove lower-left screw securing EHSI to mounting tray.(f) Insert hex wrench into lower-left hole approximately 0.75 inch (1.9 cm) and engage jack-

screw.

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) To remove EHSI from instrument panel, rotate jackscrew clockwise in 1/2 turn increments while simultaneously pulling on EHSI bezel.

(2) Installation - SN3308 EHSI


CAUTION: When mounting the EHSI, do not press on display window as damage may result.

(b) Tighten lower right mounting screw(c) Insert hex wrench into lower-left hole approximately 0.75 inch (1.9 cm) and engage jack-

screw.(d) Turn jackscrew clockwise until finger tight.(e) Slide EHSI into mounting tray.(f) Rotate jackscrew counter-clockwise until EHSI is fully engaged in tray connectors.(g) Install lower-left screw.(h) Tighten upper two screws.

CAUTION: 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.

(i) Reset HSI#1 and HSI#2 circuit breakers.(j) 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)


7/64-inch Hex Wrench - Any Source EHSI installation and removal.


7/64-inch Hex Wrench - Any Source EHSI installation and removal.

19 Sep 2017



EFFECTIVITY:

19 Sep 2017

3 Perform Operational Check - SN3308 EHSI. (Refer to 34-50)(k) If SN3308 EHSI is the same unit as the originally installed SN3308 EHSI:

1 Perform Operational Check - SN3308 EHSI. (Refer to 34-50)(3) 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 per-sonnel.



(b) Set BAT 1, BAT 2, ALT 1, ALT 2, PITOT HEAT, and all radio switches to ON positions.(c) Set all other cockpit controlled electrical switches to OFF positions.(d) Place airplane in as realistic flight environment as possible. (e) Taxi airplane to compass rose, if available.(f) If using compass rose for verification:

1 Align centerline of airplane on magnetic North heading (±1°).(g) If using boresight compass for verification:



(h) Align airplane with West and verify SN3308 EHSI system indicates 90° turn.(i) Align airplane with North and verify SN3308 EHSI system indicates 90° turn.(j) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.(k) Reset STARTER RELAY and FUEL PUMP RELAY circuit breakers.

(4) Functional Test - SN3308 EHSI Setup


(b) Pull STARTER RELAY and FUEL PUMP RELAY circuit breakers.(c) Set BAT 1, BAT 2, and AVIONICS switches to ON positions.(d) Pull circuit breakers.



±1° accuracy Any Source Verify SN3308 EHSI system.


VOR Signal Generator(if steady VOR frequency is not available)

NAV-402 Any Source Simulate VOR bearing.

34-50



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.

(e) On SN3308 EHSI, press and hold [SHFT] and [A-B].(f) Reset HSI#1 and HSI#2 circuit breakers. (g) Continue to hold [SHFT] and [A-B] until the first Maintenance Menu page appears.

Note: 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.

(h) Press [LAST] key repeatedly to access 2: Compass System page. (i) Set parameters for the 2: Compass System page.

(j) The 3: Compass Calibration page is not used.(k) Set parameters for the 4: BRG PTR Setup page.

(l) Set parameters for the 5: DME-1 Select page.

(m) Set parameters for the 6: DME-2 Select page.

(n) Set parameters for the 7: DME 1 / 2 Change page.

GYRO TYPE MID-CONT DG

GYRO VALID P1-9 LOW

SLAVING YES

FLUX GATE STEC 6446

QUADRANT 270°

PEAKING 6

BRG NAV-1 429

NAV-2 COMPOSITE

BRG ADF-1 DISABLED

ADF-2 DISABLED

CURRENT SELECTION NOT INSTALLED

CURRENT SELECTION NOT INSTALLED

DME1: NOT INSTALLED

DME2: NOT INSTALLED

19 Sep 2017



EFFECTIVITY:

19 Sep 2017

(o) Set parameters for the 8: FCS Emulation page.

(p) Set parameters for the 9: FCS Change page.

(q) Adjust HDG Bug.1 On SN3308 EHSI, select CURRENT-REF VOLTS on the Maintenance Menu page.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 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.(r) Set parameters for the 10: LNAV-1 Select page.

(s) Set parameters for the 11: LNAV-2 Select page.

(t) Set parameters for the 12: LNAV 1 / 2 Change page.

CURRENT SELECTION CENTURY 21/31/41 DC

HDG DATUM - CURRENT +RIGHT

CRS DATUM - CURRENT +RIGHT

REF VOLTS - CURRENT 04.950

CURRENT SELECTION GARMIN GNS 430(ARINC)

CURRENT SELECTION NONE

LNAV 1 GARMIN GNS 430(ARINC)

ANNUN SERIAL

COURSE OBS/LEG

DEVIATION SER DATA

LNAV 2 NONE

34-50



(u) Set parameters for the 13: MKR Select page.

(v) Set parameters for the 14: MKR Change page.

(w) Set parameters for the 15: NAV Change page.

Note: VHF Omni-directional Range (VOR) value for 175° is not labeled in display.

(x) 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.

CAUTION: If steady local VOR frequency is not available, use VOR signal gener-ator.

Note: Use same frequency on both GPS's, preferably generated with a VOR signal generator.

4 On dual GNS or GNS/GNC, select a stable NAV signal for GPS1 and GPS2. 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.

CURRENT SELECTION KING KMA-24

MKR KING KMA-24

MKR VALID VALID HIGH

THRESH 2.0 Volts

DEVIATION SER DATA

LNAV 2 NONE

NAV-1 ENABLE YES

PORT 429 PORT-2

NAV-2 ENABLE NO

RELAY MODE MASTER

ILS LOCKOUT NO

COMPOSITE-2 000.0

175°

19 Sep 2017



EFFECTIVITY:

19 Sep 2017

(y) Set parameters for the 16: Relay Sense page.

(z) The 17: System LCD Setups page is not used.(aa) Set parameters for the 18: System page.

(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.

NAV-2 OFF

GPS-1 OFF

GPS-2 OFF

CDI SRC SEL OFF

RCVR 1 / 2 OFF

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

34-50



S. Slave Amplifier - Serials 1005 thru 1336, 1337 thru 1422 w/o PFD (See Figure 34-508)

(1) 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.

(2) 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.

19 Sep 2017



EFFECTIVITY:

19 Sep 2017

T. Flux Detector - Serials 1005 thru 1336, 1337 thru 1422 w/o PFD (See Figure 34-508)

(1) 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.

(2) 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) Position flux detector to standoffs and secure with washers and screws.(b) Connect connector assembly.(c) Secure connector assembly to tie down with cable tie.(d) Serials 1005 thru 1422 w/ NSD-360A HSI: Perform Functional Test - Flux Detector Cali-

bration with NSD-360A HSI Installed. (Refer to 34-50)(e) Serials 1005 thru 1422 w/ NSD-1000 HSI: Perform Functional Test - Flux Detector Calibra-

tion with NSD-1000 HSI Installed. (Refer to 34-50)(f) Serials 1005 thru 1422 w/ SN3308 EHSI: Perform Functional Test - Flux Detector Calibra-

tion with SN3308 EHSI Installed. (Refer to 34-50)(g) Reset HSI#1 and HSI#2 circuit breakers.

(3) 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.




CAUTION: Using the boresight compass for calibration requires two technicians.

(b) Set BAT 1, BAT 2, ALT 1, ALT 2, PITOT HEAT, and all radio switches to ON positions.(c) Set all other cockpit controlled electrical switches to OFF positions.(d) Place airplane in as realistic flight environment as possible. (e) Taxi airplane to compass rose, if available.(f) If using compass rose for calibration:

1 Align centerline of airplane on magnetic North heading (±1°).(g) If using boresight compass for verification:



±1° accuracy Any Source Calibrate flux detector.

34-50





(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.

(4) Functional Test - Flux Detector Calibration with NSD-1000 HSI Installed






(b) Set BAT 1, BAT 2, ALT 1, ALT 2, PITOT HEAT, and all radio switches to ON positions.(c) Set all other cockpit controlled electrical switches to OFF positions.(d) Place airplane in as realistic flight environment as possible. (e) Taxi airplane to compass rose, if available.(f) If using compass rose for calibration:

1 Align centerline of airplane on magnetic North heading (±1°).




19 Sep 2017



EFFECTIVITY:

19 Sep 2017

(g) If using boresight compass for verification:



(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.

(5) Functional Test - Flux Detector Calibration with SN3308 EHSI Installed






(b) Set BAT 1, BAT 2, ALT 1, ALT 2, PITOT HEAT, and all radio switches to ON positions.(c) Set all other cockpit controlled electrical switches to OFF positions.(d) Place airplane in as realistic flight environment as possible. (e) Taxi airplane to compass rose, if available.




34-50



19 Sep 2017

(f) If using compass rose for calibration:1 Align centerline of airplane on magnetic North heading (±1°).

(g) If using boresight compass for verification:



(h) Align airplane with North. Highlight North calibration value and adjust using right knob to calibrate heading.

(i) Align airplane with East. Highlight East calibration value and adjust using right knob to cal-ibrate heading.

(j) Align airplane with South. Highlight South calibration value and adjust using right knob to calibrate heading.

(k) Align airplane with West. Highlight West calibration value and adjust using right knob to calibrate heading.

(l) Repeat heading checks.(m) Toggle BAT 1 switch to OFF, then ON position to put EHSI in normal operating mode.



EFFECTIVITY:

U. Remote Gyro - Serials 1005 thru 1336, 1337 thru 1422 w/o PFD (See Figure 34-508)

CAUTION: 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.

(1) 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 air-

plane.(2) 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) Perform Operational Check - SN3308 EHSI. (Refer to 34-50)

19 Sep 2017

34-50



19 Sep 2017

Figure 34-508HSI Components - Serials 1005 thru 1336, 1337 thru 1422 w/o PFD (Sheet 1 of 2)

Serials 1005 thru 1336, 1337 thru 1422 w/o PFD.

23

46

8

7

2

2

1

5

NOTE

Chamfer must be in upperright-hand location.

SR20_MM34_1088B

LEGEND1. EHSI SN3308 2. Screw3. Washer4. HSI NSD-10005. Electrical Connector6. Electrical/Data Connector7. Mounting Tray8. Mounting Plate



EFFECTIVITY:

Figure 34-508HSI Components - Serials 1005 thru 1336, 1337 thru 1422 w/o PFD (Sheet 2 of 2)

3

2

1211

6

5

SHELF(REF)

2

10

ACCESS COVER CF2R(REF)

23

9

AFT FLOOR(REF)

UPPER WINGSKIN (REF)

6

LEGEND 9. Remote Gyro10. Slaving Amplifier11. Flux Detector12. Standoffs

Serials 1005 thru 1336, 1337 thru 1422 w/o PFD. SR20_MM34_1425B

19 Sep 2017

34-50


EFFECTIVITY:


19 Sep 2017

V. XM Weather Receiver - Serials 1005 thru 2015, 2016 & subs w/o Perspective Avionics (See Fig-ure 34-509)

Note: Serials 1473 thru 1581 w/ factory installed XM Weather, Serials 1005 thru 1612 after SB 2X-34-06 w/ COM1 / XM antenna in kit: The XM Receiver and COM1 share the same antenna. For maintenance practices pertinent to the XM Weather antenna on these air-planes, refer to COM1 / XM Weather Antenna. (Refer to 34-50)

Serials 1613 & subs w/ factory installed XM Weather, Serials 1005 & subs after SB 2X-34-06 w/ standalone XM antenna in kit: The XM Receiver uses a standalone antenna. For maintenance practices pertinent to the XM Weather antenna on these airplanes, refer XM Weather Antenna. (Refer to 34-50)

Serials w/ WAAS GPS/XM antenna: The XM Receiver and GPS1 share the same antenna. For maintenance practices pertinent to the XM Weather antenna on these air-planes, refer XM Weather Antenna. (Refer to 34-50)

(1) Removal - XM Weather Receiver(a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.(b) Pull ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers.(c) Serials 1005 thru 1797: Remove MFD. (Refer to 31-60)(d) Serials 1005 thru 1797: Remove glareshield. (Refer to 25-10)(e) Serials 1798 & subs: Remove RH rear cabin side trim. (Refer to 25-10)(f) Disconnect antenna cable from receiver.(g) Serials 1747 & subs w/o WAAS GPS, Serials 1005 thru 1746 after SB 2X-34-06: Remove

attenuator from "Ant In" input.(h) To remove receiver:

1 Disconnect electrical connector from receiver.2 Serials 1005 thru 1797: At RH forward console, remove screws and washers secur-

ing receiver to attach brackets. Remove receiver from airplane.

Note: Serials 1798 & subs: At upper aft receiver installation hole, two thin washers are installed between the receiver and fuselage. Retain washers when removing screw at this location.

3 Serials 1798 & subs: At RH aft fuselage, remove screws and washers securing receiver to fuselage. Remove receiver from airplane.

(2) Installation - XM Weather Receiver(a) To install receiver:

1 Serials 1005 thru 1797: At RH forward console, position receiver to attach brackets and secure with screws and washers.

Note: Serials 1798 & subs: At upper aft receiver installation hole, two thin washers are installed between the receiver and fuselage.

2 Serials 1798 & subs: At RH aft fuselage, position receiver to fuselage and secure with screws and washers.

3 Connect electrical connector to receiver.(b) Serials 1747 & subs w/o WAAS GPS, Serials 1005 thru 1746 after SB 2X-34-06: Connect

attenuator to "Ant In" input on receiver. Torque attenuator nut to 7 - 10 in-lbs (0.79 - 1.1 Nm).

(c) Connect antenna cable to "Ant In" input on receiver. Torque cable nut to 7 - 10 in-lbs (0.79 - 1.1 Nm).



Avionics

EFFECTIVITY:

(d) Serials 1005 thru 1797: Install glareshield. (Refer to 25-10)(e) Serials 1005 thru 1797: Install MFD. (Refer to 31-60)(f) Serials 1798 & subs: Install RH rear cabin side trim. (Refer to 25-10)(g) Reset ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers.(h) Perform Operational Test - XM Weather Receiver. (Refer to 34-50)(i) Serials 1005 & subs w/ XM Radio: Perform Operational Test - XM Radio. (Refer to 23-30)

(3) Operational Test - XM Weather Receiver(a) Set BAT 1, BAT 2, and AVIONICS switches to ON positions.(b) Set GNS power in GPS1 position to ON position.(c) Bring airplane to an area that has as few obstacles to line-of-sight viewing to the southern

horizon as possible.(d) On MFD, when PRESS ANY BEZEL KEY TO CONTINUE is displayed, press any key.(e) If Engine Monitoring is selected, press [Fuel Done]. (f) Rotate left knob to select Trip page.(g) Press [Display] until “Broadcast Status” is selected.(h) Verify SIGNAL QUALITY is reported as “Good”, “Marginal”, “Weak”, or “None”.(i) If the receiver is working, antenna and cabling are correct, and airplane is in view of at

least one XM Weather satellite, SIGNAL QUALITY will be “Good” and the RECEIVER ID will be reported.

(j) If SIGNAL QUALITY is not reported as “Good”, the antenna field of view may be obstructed. Try moving or rotating the airplane until SIGNAL QUALITY improves.

(k) Set GNS power in GPS1 position to OFF position.(l) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.

19 Sep 2017

34-50



19 Sep 2017

W. XM Weather Receiver Brackets - Serials 1005 thru 1797 (See Figure 34-509)

(1) Removal - XM Weather Receiver Brackets(a) Remove XM Receiver. (Refer to 34-50)(b) Remove screws, washers, and nuts securing aft attach bracket to console ribs. Remove

aft attach bracket.(c) Remove screws, washers, and nuts securing forward attach bracket to lower strut.

Remove forward attach bracket.(2) Installation - XM Weather Receiver Brackets

(a) Position forward attach bracket at forward installation holes on lower strut between RH out-board and inboard console ribs.

(b) Install screws, washers, and nuts securing forward attach bracket to lower strut.(c) Position aft attach bracket at aft installation holes on RH outboard and inboard console

ribs. (d) Install screws, washers, and nuts securing aft attach bracket to console ribs.(e) Install XM Receiver. (Refer to 34-50).


34-50Serials 1005 thru 1638

EFFECTIVITY:

Figure 34-509XM Weather Receiver - Serials 1005 thru 1638 (Sheet 1 of 3)

9

7

SR20_MM34_2039D

5

43

2

1

LEGEND 1. XM Weather Receiver 2. Aft Attach Bracket 3. Forward Attach Bracket 4. Screw 5. Washer 6. Nut 7. Antenna Cable 8. Electrical Cable 9. Attenuator

Serials 1005 thru 1455.

Serials 1005 thru 1632, 1634 thru 1638.

CONSOLE BOLSTER(REF)

INBOARDCONSOLE RIB

(REF)

OUTBOARDCONSOLE RIB

(REF)

OUTBOARDCONSOLE RIB

(REF)

8

45

6

6 5

5

4

34

56

NOTE

Serials 1747 & subs, Serials 1005 thru 1746 after SB 2X-34-06 w/ attenuator in kit.

Torque nut to 7 - 10 in-lb (0.79 - 1.1 Nm).

Serials w/ WAAS: Do not install attenuator.

19 Sep 2017

34-50



19 Sep 2017

Figure 34-509XM Weather Receiver - Serials 1639 thru 1797 (Sheet 2 of 3)

NOTE

Serials 1747 & subs, Serials 1005 thru 1746 after SB 2X-34-06 w/ attenuator in kit.


Serials w/ WAAS: Do not install attenuator.

9

SR20_MM34_2328B

5

3

2

1

LEGEND 1. XM Weather Receiver 2. Aft Attach Bracket 3. Forward Attach Bracket 4. Screw 5. Washer 6. Nut 7. Antenna Cable 8. Electrical Cable 9. Attenuator

Serials 1633, 1639 thru 1797.

CONSOLE BOLSTER(REF)

INBOARDCONSOLE RIB

(REF)

OUTBOARDCONSOLE RIB

(REF)

8

7

45

6

6 5

5

4

4

45



Avionics

EFFECTIVITY:

Figure 34-509XM Weather Receiver - Serials 1798 thru 2015, 2016 & subs w/o Perspective Avionics (Sheet 3 of 3)


Serials w/WAAS: Do not install attenuator.

Serials 1747 & subs, Serials 1005 thru 1746after SB 2X-34-06 w/attenuator in kit.

NOTE

8

7

CABIN FLOOR(REF)

1

FUSELAGE SKIN(REF)

54

5

9

54

LEGEND 1. XM Weather Receiver 4. Screw 5. Washer 7. Antenna Cable 8. Electrical Cable 9. Attenuator

Serials 1798 & subs.SR20_MM34_2674

At upper aft receiver installation hole, two thinwashers are installed between the receiverand fuselage.

19 Sep 2017

34-50



19 Sep 2017

X. XM Weather Receiver - Serials 2016 & subs w/ Perspective Avionics (See Figure 34-5010)

(1) Removal - GDL 69A XM Weather Receiver(a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.(b) Serials 1005 thru 2126: Pull WEATHER circuit breaker.(c) Serials 2127 & subs: Pull WEATHER/DATALINK circuit breaker.(d) Remove empennage access panel RE3. (Refer to 06-00)(e) Remove ELT. (Refer to 25-60)(f) Loosen screw securing handle-lock mechanism to receiver.(g) Lift handle-lock mechanism to disengage receiver from connectors.(h) Remove receiver from rack.

(2) Installation - GDL 69A XM Weather Receiver(a) Position receiver to rack, ensuring handle-lock mechanism engages slot on side of rack.(b) Using handle-lock mechanism, gently push receiver into rack to engage connectors.(c) Tighten screw securing handle-lock mechanism to receiver.(d) Serials 1005 thru 2126: Reset WEATHER circuit breaker.(e) Serials 2127 & subs: Reset WEATHER/DATALINK circuit breaker.(f) Install ELT. (Refer to 25-60)(g) Install empennage access panel RE3. (Refer to 06-00)(h) If XM Weather Receiver has been replaced with a new or different unit, or original unit has

been repaired, perform Adjustment/Test - Component Software and Configuration Load-ing. (Refer to 42-00)



EFFECTIVITY:

Figure 34-5010XM Weather Receiver - Serials 2016 & subs w/ Perspective Avionics

1

2

3

4

MOUNTING SHELF(REF)

SR20_MM34_2787

LEGEND 1. XM Weather Receiver 2. Rack 3. Screw 4. Washer

19 Sep 2017

34-50

Serials 1582 & subs w/ factory XM Weather, Serials 1005 & subs after SB 2X-34-06 w/ standalone XM antenna in kit, Serials w/ WAAS GPS/XM antenna

EFFECTIVITY:


19 Sep 2017

Y. XM Weather Antenna - Serials 1582 & subs w/ factory XM Weather, Serials 1005 & subs after SB 2X-34-06 w/ standalone XM antenna in kit, Serials w/ WAAS GPS/XM antenna (See Figure 34-5011)

(1) Removal - 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) Serials w/ WAAS GPS: Disconnect GPS1 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.

(2) Installation - XM Weather Antenna


(b) Position gasket and antenna to fuselage and insert screws through mounting holes.

CAUTION: To prevent damage to rubber gasket at screwhead, turn nuts onto screws during installation.

Note: Tighten forward screws prior to tightening aft screws.

(c) Install washers and nuts securing antenna to fuselage. Torque nuts to maximum of 20 - 25 in-lb (2.26 - 2.82 Nm).

(d) Fillet seal antenna perimeter. (Refer to 20-10)(e) Connect XM Weather cable to antenna.(f) Serials w/ WAAS GPS: Connect GPS1 cable to antenna.(g) Install cabin headliner. (Refer to 25-10)(h) Reset ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers.




34-50Serials 1582 & subs w/ factory XM Weather

EFFECTIVITY:

Figure 34-5011XM Weather Antenna - Serials 1582 & subs w/ factory XM Weather

LEGEND 1. Screw 2. Washer 3. Nut 4. XM Weather Antenna 5. WAAS GPS/XM Weather Antenna 6. Gasket 7. Antenna Connector

FUSELAGE(REF)

5

1

3

7

2

6

GPS1ANTENNA

CONNECTOR(REF)

Serials 1802, 1816 & subs w/ WAAS GPS/XM,Serials 1005 thru 1422 after SB 2X-34-23,Serials 1337 thru 1801, 1803 thru 1815after SB 2X-34-24.

Serials 1582 thru 1801, 1803 thru 1815w/ factory XM Weather,Serials 1005 thru 1801, 1803 thru 1815 afterSB 2X-34-06 w/ standalone XM antenna in kit.

4

FUSELAGE(REF)

1

32

6

SR20_MM34_2612C

NOTE

At upper aft receiver installation hole, two thinwashers are installed between the receiverand fuselage.

7

19 Sep 2017

34-50



19 Sep 2017

Z. Iridium GSR 56 Transceiver - Serials 2016 & subs w/ Perspective Avionics (See Figure 34-5012)

(1) Removal - Iridium GSR 56 Transceiver(a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.(b) Pull WEATHER/DATALINK circuit breaker.(c) Remove empennage access panel RE3. (Refer to 06-00)(d) To prevent debris and components from falling into bottom of empennage, place catch

cloth below transceiver installation.(e) Loosen screw securing handle-lock mechanism to transceiver.(f) Lift handle-lock mechanism to disengage transceiver from connectors.(g) Remove transceiver from rack.

(2) Installation - Iridium GSR 56 Transceiver(a) Position transceiver to rack, ensuring handle-lock mechanism engages slot on side of

rack.(b) Using handle-lock mechanism, gently push transceiver into rack to engage connectors.(c) Tighten screw securing handle-lock mechanism to transceiver.(d) Remove catch cloth from below transceiver installation.(e) Using a vacuum cleaner, remove all debris from fuselage floor.(f) Install empennage access panel RE3. (Refer to 06-00)(g) Reset WEATHER/DATALINK circuit breaker.(h) If avionics system has not been previously configured for GSR 56 or system configuration

has been corrupted, perform Adjustment/Test - Component Software and Configuration Loading. (Refer to 42-00)

(i) Perform Operational Test - Iridium GSR 56 Transceiver. (Refer to 34-50)(j) If GSR 56 has been replaced with a new or different unit, or original unit has been

repaired, perform Functional Test - Iridium GSR 56 Transceiver. (Refer to 34-50)(3) Operational Test - Iridium GSR 56 Transceiver

(a) Set BAT 1, BAT 2, and AVIONICS switches to ON positions.(b) On MFD, press [ENT] softkey to acknowledge prompts as directed.(c) On Initial Usable Fuel page, press [ENT] softkey to accept usable fuel quantity. (d) On FMS keyboard, Rotate outer dial of [CRSR] knob to select the Aux page group.(e) Rotate inner dial of [CRSR] knob to select the Aux (System Status) page.(f) Press inner dial of [CRSR] knob to activate cursor.(g) Scroll through LRU INFO window and verify that the green check-mark is in the STATUS

column for the GSR1.(h) Press inner dial of [CRSR] knob to de-activate cursor.(i) Position the aircraft away from buildings. The Iridium antenna must have an unobstructed

view of the sky.(j) Rotate outer dial of [CRSR] knob to select the Aux page group.(k) Rotate inner dial of [CRSR] knob to select the Aux (Satellite Phone) page.(l) Verify that Iridium signal strength - green bars above the satellite icon - shows 4 to 5 bars.(m) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.

(4) Functional Test - Iridium GSR 56 Transceiver

Note: Prior to performing Functional Test - Iridium GSR 56 Transceiver, contact Garmin Flight Data Service for weather and/or voice system activation.

(a) Set BAT 1, BAT 2, and AVIONICS switches to ON positions.(b) On MFD, press [ENT] softkey to acknowledge prompts as directed.(c) On Initial Usable Fuel page, press [ENT] softkey to accept usable fuel quantity.



EFFECTIVITY:

(d) For weather activation:1 Rotate outer dial of [CRSR] knob to select the Map page group.2 Rotate inner dial of [CRSR] knob to select the Map (Weather Data Link) page.

Note: Press MENU to select DISPLAY GFDS WEATHER from the PAGE MENU, if required.

3 Press MENU button on the keypad to activate PAGE MENU pop-up screen.4 Select 'Register with GFDS' from PAGE MENU pop-up screen and press [ENT] soft-

key.5 Using FMS knobs, enter registration number in NEW REGISTRATION field. 6 Position cursor on 'REGISTER' and press [ENT] softkey to initiate registration pro-

cess.

Note: Enabling a temporary Iridium network registration can take approxi-mately 30 minutes. System registration is complete when 'REGIS-TERED' is displayed on STATUS field.)

(e) For voice activation:1 Serials w/ GMA 347: On audio panel, select [TEL] and [PILOT] to ensure telephone

I/O is enabled.2 Serials w/ GMA 350: On audio panel, select ENTERTAINMENT button (shown as a

phone and music-note symbol) and [PILOT] to ensure telephone I/O is enabled. 3 Ensure pilot's headset is active.4 Rotate outer dial of [CRSR] knob to select the Aux page group.5 Rotate inner dial of [CRSR] knob to select the Aux (Satellite Phone) page.6 Press [DIAL] softkey to display PHONE CALL pop-up screen.

Note: Completing call will incur charges to service billing.

7 Use FMS knobs or MFD bezel keys to enter a working phone number.8 Select OK and press [ENT] softkey to initiate phone call.9 Verify that call completes and that call quality is acceptable.

(f) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.

19 Sep 2017

34-50



19 Sep 2017

AA.Iridium GSR 56 Transceiver Rack - Serials 2016 & subs w/ Perspective Avionics

(1) Removal - Iridium GSR 56 Transceiver Rack(a) Remove Iridium GSR 56 transceiver. (Refer to 34-50)(b) Disconnect antenna and GIA #2 wire harnesses from rack connectors.(c) Remove Iridium GSR 56 mounting shelf. (Refer to 34-50)(d) Remove screws and washers securing rack to mounting shelf.

(2) Installation - Iridium GSR 56 Transceiver Rack(a) Position rack to mounting shelf and secure with screws and washers.(b) Install Iridium GSR 56 mounting shelf. (Refer to 34-50)(c) Connect antenna and GIA #2 wire harnesses to rack connectors.(d) Install Iridium GSR 56 transceiver. (Refer to 34-50).



EFFECTIVITY:

AB.Iridium GSR 56 Mounting Shelf - Serials 2016 & subs w/ Perspective Avionics

(1) Removal - Iridium GSR 56 Mounting Shelf(a) Disconnect antenna and GIA #2 wire harnesses from rack connectors.(b) Remove aft cabin bulkhead (BH 222) trim panel and carpet. (Refer to 25-10)(c) Remove screws and washers securing mounting shelf to aft cabin bulkhead (BH 222).

Remove mounting bracket.(2) Installation - Iridium GSR 56 Mounting Shelf

(a) Position mounting shelf to aft cabin bulkhead (BH 222) and secure with screws and wash-ers.

(b) Install aft cabin bulkhead (BH 222) trim panel and carpet. (Refer to 25-10)(c) Connect antenna and GIA #2 wire harnesses to rack connectors.(d) Perform Operational Test - Iridium GSR 56 Transceiver. (Refer to 34-50)

19 Sep 2017

34-50



19 Sep 2017

Figure 34-5012Iridium Weather System - Serials 2016 & subs w/ Perspective Avionics

4

7

62

5

3

21

BULKHEAD (REF)

SR20_MM34_3486

LEGEND 1. Bolt 2. Washer 3. Mounting Shelf 4. Back Plate 5. Rack 6. Screw 7. Transceiver



EFFECTIVITY:

AC.Automatic Direction Finder (ADF) Receiver - Serials 2016 & subs w/ Perspective Avionics (See Figure 34-5013)

(1) Removal - ADF Receiver(a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.(b) Pull DME / ADF circuit breaker.(c) Loosen screw to disengage ADF receiver from mounting tray connectors.(d) Remove ADF receiver from mounting tray.

(2) Installation - ADF Receiver(a) Position ADF receiver into mounting tray until connectors mate.(b) Tighten screw to fully engage connectors, then tighten an additional quarter turn.(c) Reset DME / ADF circuit breaker.(d) Perform Operational Test - ADF Receiver. (Refer to 34-50)

(3) Operational Test - ADF Receiver(a) Verify ADF window is displayed on PFD. If ADF window is not displayed, press [PFD] soft-

key.(b) Using either [BRG1] or [BRG2] softkeys, toggle softkey until ADF bearing is displayed. (c) Press [BACK] softkey.(d) Verify ADF window is not invalid (no red ‘X’).(e) Verify audio from tuned station can be heard on pilot and copilot headsets.(f) Verify audio from tuned station can be heard over cabin speaker.

19 Sep 2017

34-50



19 Sep 2017

AD.Automatic Direction Finder (ADF) Antenna - Serials 2016 & subs w/ Perspective Avionics (See Figure 34-5013)

(1) Removal - ADF Antenna(a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.(b) Pull DME / ADF circuit breaker.(c) Remove access panel CF3C. (Refer to 06-00)(d) Remove nut and washers securing terminal ring to antenna backing plate.(e) Remove screws securing antenna to backing plate. Remove antenna from airplane.

(2) Installation - ADF Antenna


(b) Position antenna to fuselage.(c) Install screws securing antenna to backing plate.(d) Position terminal ring to antenna backing plate and secure with washer and nut.(e) Install access panel CF3C. (Refer to 06-00)(f) Fillet seal antenna perimeter. (Refer to 20-10)(g) Reset DME / ADF circuit breaker.(h) Perform Operational Test - ADF Receiver. (Refer to 34-50)





EFFECTIVITY:

Figure 34-5013ADF Receiver and Antenna Installation - Serials 2016 & subs w/ Perspective Avionics

6

65

57

4

3

3

2

1

FUSELAGE(REF)

SR20_MM34_2726

LEGEND 1. ADF Receiver 2. Antenna 3. Screw 4. Backing Plate 5. Washer 6. Nut 7. Terminal Ring

19 Sep 2017

34-50



19 Sep 2017

AE.KN 63 Distance Measuring Equipment (DME) Receiver - Serials 2016 & subs w/ Perspective Avi-onics (See Figure 34-5014)

(1) Removal - KN 63 DME Receiver(a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.(b) Pull DME / ADF circuit breaker.(c) Remove access panel CF1L and CF2L. (Refer to 06-00)(d) Disconnect connector from DME receiver.(e) Remove screws securing DME receiver mounting shelf to fuselage floor.(f) Remove screws and washers securing DME receiver to mounting shelf. Remove DME

receiver from airplane.(2) Installation - KN 63 DME Receiver

(a) Position DME receiver to mounting shelf and secure with screws and washers.(b) Position DME receiver mounting shelf to fuselage floor and secure with screws.(c) Connect connector to DME receiver.(d) Install access panel CF1L and CF2L. (Refer to 06-00)(e) Reset DME / ADF circuit breaker.(f) Perform Operational Test - DME Receiver. (Refer to 34-50)

(3) Operational Test - DME Receiver(a) On PFD, press [PFD] softkey, then press [DME] softkey to display DME window.(b) On PFD, press [ADF/DME] softkey. Verify ADF/DME TUNING screen is displayed.(c) With ADF/DME TUNING screen activated, use outer [FMS] knob to highlight DME field.(d) Verify NAV1, NAV2 and HOLD modes can be selected by turning inner [FMS] knob.(e) Verify NAV1 frequency is set to 108.00.(f) Verify NAV2 frequency is set to 117.00.(g) Press [ENT] softkey to select DME NAV1 mode. Verify DME window display is set to NAV1

frequency of 108.00.(h) Press [ENT] softkey to select DME NAV2 mode. Verify DME window display is set to NAV2

frequency of 117.00.(i) Press [ENT] softkey to select DME HOLD mode. Verify last selected NAV frequency of

117.00 remains the same when NAV2 frequency is changed.(j) On audio panel, press [DME] button to select DME audio.(k) On audio panel, press [SPKR] button to turn on cabin speaker.(l) Verify DME audio can be heard over cabin speaker.(m) On PFD, set DME mode to NAV2 and verify DME distance is dashed out.



EFFECTIVITY:

AF. KN 63 Distance Measuring Equipment (DME) Antenna - Serials 2016 & subs w/ Perspective Avi-onics (See Figure 34-5014)

(1) Removal - KN 63 DME Antenna(a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.(b) Pull DME / ADF circuit breaker.(c) Remove access panel CF8. (Refer to 06-00)(d) Disconnect antenna cable from antenna.(e) Remove nut, and washers securing antenna to cabin floor. Remove antenna from air-

plane.(2) Installation - KN 63 DME Antenna


(b) Position antenna to cabin floor and secure with washers and nuts.(c) Connect antenna cable to antenna.(d) Install access panel CF8. (Refer to 06-00)

CAUTION: Ensure drain hole is unobstructed and free of sealant.

(e) Fillet seal antenna perimeter. (Refer to 20-10)(f) Reset DME / ADF circuit breaker.(g) Perform Operational Test - DME Receiver. (Refer to 34-50)



19 Sep 2017

34-50



19 Sep 2017

Figure 34-5014DME Receiver and Antenna Installation - Serials 2016 & subs w/ Perspective Avionics

LEGEND 1. DME Receiver 2. Screw 3. Washer 4. Mounting Shelf 5. Antenna 6. Antenna Cable 7. Nut 8. Cable Tie Anchor 9. Cable Tie

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FUSELAGE (REF)

CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL...

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