700-00006-0XX PFD & 700-00011-0XX Mag/OAT

Instructions for Continued Airworthiness

Part 23, Class I & II Installations

A VIDYNE
CORPORATION
55 Old Bedford Road
Lincoln, MA 01773

Document Number AVPFD-174 Control Category N/A

Revision Description ECO Date
00 Initial Release 03-244 09/24/03
Draft 01-A Revision to incorporate PA-46 information Keirnan 2/28/05

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700-00006-0XX PFD & 700-00011-0XX Mag/OAT Instructions for Continued Airworthiness
Part 23, Class I & II Installations

Table of Contents
1. Introduction ........................................................................... 4
1.1 Aircraft Description ......................................................................................................... 4
1.2 Scope ............................................................................................................................. 4
1.3 Applicability .................................................................................................................... 4
1.4 Definitions and Abbreviations......................................................................................... 4
1.5 Precautions .................................................................................................................... 4
1.6 Units of Measure ............................................................................................................ 4
1.7 Referenced Publications ................................................................................................ 4
1.8 Distribution ..................................................................................................................... 4

2. Description............................................................................. 5
3. Control and operation information ...................................... 7
4. Servicing information ........................................................... 7
5. Maintenance Instructions ..................................................... 7
5.1 Recommended periodic scheduled servicing tasks ....................................................... 7
5.2 Cleaning Cover Screen .................................................................................................. 7

6. Troubleshooting Information ............................................... 8

7. Removal and Replacement Information ............................ 12
7.1 Primary Flight Display Removal ................................................................................... 12
7.2 Primary Flight Display Installation ................................................................................ 13
7.3 Magnetometer/OAT Sensor Assembly Removal ......................................................... 14
7.4 Magnetometer/OAT Sensor Assembly Installation ...................................................... 14
7.5 System Setup and Checkout........................................................................................ 16
7.6 Functional Checks........................................................................................................ 27

8. Special Inspection Requirements ...................................... 30

9. Application of Protective Treatments................................ 30
10. Data .................................................................................. 30
11. List of Special Tools ....................................................... 30
12. For Commuter Category Aircraft ................................... 30
13. Recommended Overhaul Periods.................................. 30
14. Airworthiness Limitation Section .................................. 30
15. Revision ........................................................................... 30
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700-00006-0XX PFD & 700-00011-0XX Mag/OAT Instructions for Continued Airworthiness
Part 23, Class I & II Installations

Table of Figures
Figure 1 Avidyne 700-00006-0XX PFD...................................................................................................... 5
Figure 2 Avidyne 700-00011-000 Magnetometer/OAT Sensor Assembly........................................... 6
Figure 3 Avidyne PFD System Block Diagram........................................................................................ 6
Figure 4 PFD Pitot-Static Quick Disconnects......................................................................................... 12
Figure 5 PFD Rear View ........................................................................................................................... 12
Figure 6 PFD Handling When Installing................................................................................................ 13
Figure 7 PFD Pin & Horizontal Support Bracket Retention Configurations..................................... 14
Figure 1 PFD Controls............................................................................................................................... 16
Figure 2 System Setup Page (Example) .................................................................................................. 17
Figure 3 IRU Installation Page. ................................................................................................................ 25
Figure 4 Initial Magnetometer Calibration Page ................................................................................... 26
Figure 5 Final Magnetometer Calibration Page..................................................................................... 27

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700-00006-0XX PFD & 700-00011-0XX Mag/OAT Instructions for Continued Airworthiness
Part 23, Class I & II Installations

1. Introduction
1.1 Aircraft Description
Make: Various
Model: Various

Make and models as listed in Avidyne Document, AVPFD-170, 700-00006-0XX PFD Approved
Model List Single Engine Piston.

1.2 Scope
This document identifies the Instructions For Continued Airworthiness for above referenced
aircraft modified to include installation of an Avidyne 700-00006-0XX Primary Flight Display
(PFD) and 700-00011-000 Magnetometer/OAT Sensor Assembly.
This ICA satisfies the requirements of 14 CFR 23.1529.

1.3 Applicability
Applies to aircraft altered by the installation of an Avidyne 700-00006-0XX Primary Flight
Display and 700-00011-000 Magnetometer/OAT Sensor Assembly.

1.4 Definitions and Abbreviations

ICA – Instructions for Continued Airworthiness
STC – Supplemental Type Certificate
PFD – Primary Flight Display
AEG – Aircraft Evaluation Group
LSK – Line Select Key

1.5 Precautions
This section not applicable.

1.6 Units of Measure

This section not applicable.

1.7 Referenced Publications

Document Number Title

600-00104-000 FlightMax Entegra Primary Flight Display Pilot’s Guide
600-00080-000 FlightMax Entegra Primary Flight Display Installation Manual

1.8 Distribution
This Instructions For Continued Airworthiness is to be furnished to the owner of an aircraft
modified in accordance with this STC, and is to become part of the permanent aircraft record.
A current revision of this ICA shall be available on the Avidyne website at
www.avidyne.com (Technical Publications in the Products section).

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Part 23, Class I & II Installations

2. Description
The Avidyne 700-00006-0XX-() Entegra display is a panel mounted 10.4-inch diagonal
Primary Flight Display that provides the following display capabilities:

Attitude Airspeed
Altitude Horizontal Situation Indication
Slip Indication Vertical Speed
Navigation Source Slection Glideslope Indication
VOR/LOC Indication FMS-supplied Flight Plan
Wind Direction/Velocity True Airspeed

As appropriate for engine type and based upon set-up configuration, the PFD will also
display the following engine and aircraft systems parameters:

Engine Manifold Pressure Engine RPM

Oil Pressure Fuel Flow
Outside Air Temperature

The PFD is capable of receiving data from and transmitting data to compatible GPS
Nav/Comm systems and autopilots.

Figure 1 Avidyne 700-00006-0XX PFD

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The 700-00011-000 Magnetometer/OAT Sensor Assembly provide magnetic heading and outside
air temperature information to the PFD for display and computations. Figure 2 depicts the
sensor assembly.

Magnetometer

OAT Probe

Figure 2 Avidyne 700-00011-000 Magnetometer/OAT Sensor Assembly

A block diagram of the PFD interfaced in a fully equipped aircraft is presented in Figure 3.

PFD A429

Analog
PFD A429
GPS/VHF GPS A429
Analog Autopilot
Navigator #1 Digital
VHF A429
Discrete

serial cross-fill

PFD A429 Engine

FlightMax Entegra
GPS/VHF GPS A429 RS232 Sensor
PFD
Navigator #2 VHF A429 Interface Unit
(SIU)

Pitot

Static
28V DC
ADAHRS
OAT Sensor/ Power
RS-422
Magnetometer

Figure 3 Avidyne PFD System Block Diagram

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3. Control and operation information

The PFD operation is controlled through 8 bezel keys, 2 rotary knobs, and a rocker switch.
Both the right and left knob’s function are specific to the particular page that is currently
selected, and are appropriately labeled on the LCD above each knob.
The rocker switch located in the top right corner of the bezel controls the display brightness,
which is adjusted manually by pushing the top portion of the switch to increase intensity and
pushing the bottom portion of the switch to decrease intensity.
The functionality of the 8-bezel keys is specific to the currently displayed page, and each key
is labeled accordingly on the LCD adjacent to the key.
Refer to the FlightMax Entegra Primary Flight Display Pilot’s Guide, P/N 600-00104-000 for
more detail on PFD operation.

4. Servicing information
This section not applicable.

5. Maintenance Instructions
Other than the periodic servicing task discussed below, maintenance of the Avidyne 700-
00006-XXX-() PFD and 700-00011-XXX-() Magnetometer/OAT Sensor Assembly is based on
condition only; no other periodic maintenance is required.

5.1 Recommended periodic scheduled servicing tasks

An altimeter accuracy check is required every 24 months.
A compass swing is required to be performed every 24 months. This check will result in a re-
calibration of the magnetometer system.

5.2 Cleaning Cover Screen

If the PFD cover screen should become dirty due to finger prints, dust etc the following
materials and methods can be used to safely clean the screen.
• A soft lint free cloth
• Cleaning solution such as Optimax brand cleaner or water if Optimax is not
available
• ALWAYS apply cleaning solution directly to the cloth and NEVER directly to the
screen
• NEVER use products that contain ammonia, alcohol, acetone, ethyl alcohol, ethyl
acid, methyl chloride etc.

CAUTION: Using products with ammonia or other harmful ingredients or materials could void
the warranty.

NOTE: The cover screen is not glass, the surface is made of a soft film that is vulnerable to
scratches, damage by a sharp articles or improper cleaners. Use care when cleaning.

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Part 23, Class I & II Installations

6. Troubleshooting Information

Note: For troubleshooting instructions recommending wiring checks, refer to the Avidyne
document, 600-00080-000, FlightMax Entegra Primary Flight Display Installation Manual for
wiring diagram information.

Component Trouble Probable Cause Remedy

Pitch ladder and horizon PFD AHRS failure Replace PFD
Attitude
Display

removed and replaced with red X

Instruments removed and PFD Air Data Computer failure Replace PFD
Airspeed,
Altitude,

Velocity
Vertical

Display

replaced with red X

Heading indication removed and Break in wire between PFD and Test and repair wiring.
replaced with red X Magnetometer
Magnetometer failed Replace Magnetometer/OAT
Heading

Assembly
PFD RS-422 or Magnetometer Replace PFD
output power failure
Excessive heading error Magnetometer not properly Calibrate Magnetometer
calibrated
PFD fails to align after power up Aircraft was moved during power Cycle PFD power and remain
up alignment stationary during power up
alignment
Alignment

PFD ADAHRS failure Replace PFD

Display indicates red dashes OAT probe failed Replace Magnetometer/OAT

(Option)

Assembly
OAT

Excessive temperature error OAT probe failed Replace Magnetometer/OAT

Assembly
Display indicates red dashes OAT probe failed Replace Magnetometer/OAT
Assembly
True Airspeed

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Component Trouble Probable Cause Remedy

Display indicates dashes Winds aloft have been calculated Behavior by design, no action
as light and variable or less than 5 required
knots
Wind Vector
PFD not receiving ground speed. Test and repair wiring
Break in wire between PFD and
VHF/GPS NAV 1 & VHF/GPS
NAV 2
Aircraft has zero ground speed Behavior by design, no action
required
PFD Primary Nav, Bearing, or VHF/GPS NAV 1 not configured Configure unit
Auxiliary indication displays properly
dashes when GPS 1 or VLOC 1
selected Break in wire between PFD and Test and repair wiring
VHF/GPS NAV 1
VHF /GPS NAV 1

VHF/GPS NAV 1 ARINC 429 Replace VHF/GPS NAV 1

Output failed
PFD ARINC 429 input failed Replace PFD
GPS1 does not slave to PFD Break in ARINC 429 wire between Test and repair wire
course pointer in OBS mode PFD and GPS NAV 1
ARINC 429 Receive Input failed Replace VHF/GPS NAV 1
ARINC 429 Transmit output failed Replace PFD
PFD Primary Nav, Bearing, or VHF/GPS NAV 2 not configured Configure unit
Auxiliary indication displays properly
dashes when GPS 2 or VLOC 2
selected Break in wire between PFD and Test and repair wiring
VHF/GPS NAV 2
VHF /GPS NAV 2

VHF/GPS NAV 2 ARINC 429 Replace VHF/GPS NAV 2

Output failed
PFD ARINC 429 input failed Replace PFD
GPS2 does not slave to PFD Break in ARINC 429 wire between Test and repair wire
course pointer in OBS mode PFD and GPS NAV 2
ARINC 429 Receive Input failed Replace VHF/GPS NAV 2
ARINC 429 Transmit output failed Replace PFD

All engine/system parameter Break in wire between PFD & SIU Test and repair wiring
counters display dashes.
Sensor Interface Unit

SIU Interface Failure Replace SIU

PFD Interface Failure Replace PFD
Single engine/system parameter SIU Interface Failure Replace SIU
counters display dashes.
Break in wire between SIU & Test and repair wiring
Sensor
Sensor Failure Replace Sensor

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Component Trouble Probable Cause Remedy

Airspeed, Heading, or Altitude Break in Annunciator wires Test and repair wiring
bugs do not “fill” but autopilot between PFD and AP Computer
modes still engage.
Autopilot Computer interface Replace unit
failure
PFD interface failure Replace unit
Autopilot annunciators on the Break in Annunciator wires Test and repair wiring
PFD (if equipped) do not between PFD and AP Computer
illuminate or illuminate erratically.
Autopilot Computer interface Replace unit
failure
PFD interface failure Replace unit
Autopilot VS mode does not Break in VS Command wires Test and repair wiring
track PFD Vertical Speed setting, between PFD and Autopilot
but autopilot mode engages. Computer
Autopilot HDG mode does not Break in Heading Datum wire Test and repair wiring
track PFD Heading setting, but between PFD and Autopilot
autopilot mode engages. Computer
Autopilot HDG mode does not Autopilot Computer interface Replace unit
Autopilot Integration

track PFD Heading setting, but failure

autopilot mode engages (con.)
PFD interface failure Replace unit
PFD heading bug out of alignment Perform PFD heading bug
calibration
Autopilot NAV mode does not Break in Course Datum and Cross Test and repair wiring
track PFD Nav Course Pointer track wires between PFD and
setting or CDI. Autopilot Computer
Autopilot Computer interface Replace unit
failure
PFD interface failure Replace unit
Autopilot out of alignment Perform autopilot alignment in
NAV mode
Autopilot NAV annunciator Break in CDI Flag wire between Test and repair wiring
flashes and FAIL indication PFD and Autopilot Computer
appears.
Autopilot Computer interface Replace unit
failure
VHF/GPS NAV 1 or 2 Nav data Refer to VHF/GPS NAV 1 & 2
invalid Troubleshooting procedure
PFD interface failure Replace unit

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Component Trouble Probable Cause Remedy

Airspeed, Heading, or Altitude Break in CDI and VDI wires Test and repair wiring
bugs do not “fill” but autopilot between PFD and Autopilot
modes still engage. Computer
Autopilot Computer interface Replace unit
failure
PFD interface failure Replace unit
Autopilot APR mode fails to Break in Glideslope flag or LOC Test and repair wiring
engage. Switch wires between PFD and
Autopilot Computer
Autopilot Computer interface Replace unit
failure
PFD interface failure Replace unit
Autopilot Computer display Break in ALT Select wire between Test and repair wiring
indicates vertical speed value PFD and Autopilot
Autopilot Computer interface Replace unit
Autopilot Integration failure
PFD interface failure Replace unit
Autopilot Integration

Autopilot GPSS mode fails to Break in PFD ARINC 429 Test and repair wiring
(continued)

engage in flight Transmit or Autopilot Relay

Control wire
(GPSS mode will not engage Autopilot Relay failure Replace relay
during a ground test)
Autopilot Computer interface Replace unit
failure
PFD interface failure Replace unit

Autopilot GPSS only follows Break in Autopilot Relay Control Test and repair wire
GPS 1 source wire
Autopilot Relay failure Replace relay
PFD interface failure Replace unit
Flight Director command bars (if PFD out of alignment Perform PFD heading bug
equipped) do not align to attitude calibration
reference symbol or behave
erratically. Break in pitch / roll command Test and repair wiring
signal wires between PFD and
Autopilot computer
(Test alignment on in level flight
in smooth air with HDG and ALT Autopilot computer interface Replace unit
modes engaged) failure
PFD interface failure Replace unit

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700-00006-0XX PFD & 700-00011-0XX Mag/OAT Instructions for Continued Airworthiness
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7. Removal and Replacement Information

7.1 Primary Flight Display Removal
Remove the Avidyne PFD from the instrument panel by turning four corner-mounted 5/64”
allen head screw fasteners counter-clockwise and pulling the unit away from instrument
panel. Remove the pitot-static hoses via the quick disconnects by pressing on the quick
release button (see Figure 4). Remove Connectors (P730, P731, P732, P733) located on the
back of PFD by turning the two jackscrews counter-clockwise (see Figure 5).

Figure 4 PFD Pitot-Static Quick Disconnects

Figure 5 PFD Rear View

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7.2 Primary Flight Display Installation

Secure the connectors onto the PFD and tighten the jackscrews. Connect the pitot-static
connectors. Rest the PFD on the edge of the instrument panel cutout and assure that the
service loop of the PFD cables is routed away from any moving parts behind the instrument
panel. Hold the PFD as shown in Figure 5 and lift up on the edge of the rear of the PFD,
while simultaneously pushing the upper edge of the PFD under the glare shield. Ensure the
PFD mating pins or horizontal bracket engage the respective aircraft rear support bracket
located approximately 8 inches behind the instrument panel (see Figure 7) and locate the PFD
bezel against the instrument panel. Secure the PFD to the instrument panel by turning four
corner-mounted 5/64” allen head screw fasteners clockwise.
Upon reinstallation, a functional check should be performed in accordance with the System
Setup and Checkout procedures detailed in Section 7.5.

Figure 6 PFD Handling When Installing

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700-00006-0XX PFD & 700-00011-0XX Mag/OAT Instructions for Continued Airworthiness
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Figure 7 PFD Pin & Horizontal Support Bracket Retention Configurations

7.3 Magnetometer/OAT Sensor Assembly Removal

Refer to aircraft maintenance manual for access details on magnetometer or flux valve
installation location and access instructions.

1. Ensure PFD power (as applicable), and AVIONICS master switches are in off position.
2. Pull PFD circuit breakers
3. Remove OAT probe nut from the airframe-mounting hole.
4. Gain access to the magnetometer in accordance with the magnetometer/flux valve access
instructions contained within the aircraft model specific maintenance manual.
5. Remove screws and washers securing the Magnetometer to aircraft mounted standoffs.
6. Cut cable tie securing Magnetometer connector assembly to tie down and remove
Magnetometer/OAT Sensor Assembly from airplane.

7.4 Magnetometer/OAT Sensor Assembly Installation

CAUTION: Ensure Magnetometer is installed with arrow and letters FWD pointing forward.
1. Unfasten the appropriate wingtip aircraft access panel to permit servicing the
magnetometer.
2. Position Magnetometer to standoffs and attach with washers and screws.
3. Connect connector assembly.
4. Secure connector assembly to tie down with cable tie.
5. Insert OAT probe through airframe mounting panel and secure with washers and nut.
6. Wire tie connector assembly to aircraft structure to minimize vibration induced motion.
7. Re-assemble aircraft magnetometer access provisions in accordance with the
magnetometer/flux valve access instructions contained within the aircraft model specific
maintenance manual.

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700-00006-0XX PFD & 700-00011-0XX Mag/OAT Instructions for Continued Airworthiness
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8. Perform Magnetometer Calibration procedure defined in section Error! Reference source
not found..

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7.5 System Setup and Checkout

CAUTION: The procedures in this section are to be performed by authorized Avidyne
Entegra Service Centers
Any time the Avidyne PFD or Magnetometer/OAT Sensor Assembly is replaced with
another unit, these system setup procedures should be performed to assure that the unit is
properly configured for the installation.
Turn on the PFD by applying power to the aircraft. Allow the PFD to initialize. This will take
approximately 3 minutes.
7.5.1 System Setup Page Access
Apply power to all the sensors that interface with the PFD, including: the GPS and the
autopilot. System Setup Page will allow you to configure the PFD. The System Setup Page
can only be accessed by pressing the line select keys in a specific manner.
The System Setup Page is accessible as follows:
1. Turn on the PFD by applying power to the aircraft via the battery switch.
2. The system will begin its normal start up sequence.
3. Simultaneously press and hold the top left (L1), and third down from top left
(L3) Line Select Keys until the countdown timer in the lower left corner of the
display indicates zero seconds (See Figure 1. for depiction of Line Select Keys)
4. At the end of a displayed countdown clock adjacent to the L4 line select key, the
System Setup Page will appear (See Figure 9).

Figure 8 PFD Controls

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Figure 9 System Setup Page (Example)

7.5.2 GNS-430 Nav/Com Setup

7.5.2.1 PFD Unit
Software Part Numbers other than 530-00123-000 Rev 02 and subsequent revisions, 530-
00159-000 Rev 00 and subsequent revisions, and 530-00171-000 Rev 00 and subsequent
revisions:
The ARINC 429 ports on the PFD come hard-wired and pre-assigned. GNS-430 Unit #1 must
be connected to ARINC port 1 (GPS output line) and port 2 (VLOC output line). GNS-430
Unit #2 (if installed) must be connected to ARINC port 3 (GPS output line) and port 4 (VLOC
output line). Use the line select keys R1, R2 to configure the PFD in the following manner:
Line Select Key (LSK) R1: GPS1 Port: ARINC 1;
LSK R1: GPS1 Port: NONE, if GNS-430 No.1 not installed;
LSK R2: GPS2 Port: ARINC 3, if GNS-430 No.2 installed;
LSK R2: GPS2 Port: NONE, if GNS-430 No. 2 not installed.

NOTE: GNS-430 and GNS-530 are electrically identical and are treated as one in the same
when integrating with the Entegra PFD.
Once complete, verify the displayed configuration in the sensor suite section of the System
Setup page accurately reflects actual configuration.

Software Part Numbers 530-00123-000 Rev 02 and subsequent revisions or 530-00159-000 Rev
00 and subsequent revisions:
The ARINC 429 ports on the PFD come hard-wired and pre-assigned. GNS-430 Unit #1 must
be connected to ARINC port 1 (GPS output line) and port 2 (VLOC output line). GNS-430
Unit #2 (if installed) must be connected to ARINC port 3 (GPS output line) and port 4 (VLOC
output line). When GNC-420 units are to be installed, they must be connected to ARINC port

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1 (or 3 if serving as the 2nd navigator), leaving port 2 (or 4 if serving as the 2nd navigator)
vacant. Use the line select keys R1, R2 to configure the PFD in the following manner:
Line Select Key (LSK) R1: Nav 1: 430/530, 420, or None as appropriate;
LSK R2: Nav 2: 430/530, 420, or None as appropriate.

Software Part Numbers 530-00171-000 Rev 00 and subsequent revisions:

Based on the aircraft model, the PFD will either be pre-configured to assume dual GNS-430s
are connected or will require configuration via the system setup page to tell it what
navigators are connected.
If pre-configured to work with dual GNS-430s, the system setup page will display the
configuration but will not provide a means to change the configuration.
If not pre-configured for dual GNS-430s, the system setup page will provide a means to tell
the PFD which navigators are connected. The ARINC 429 ports on the PFD come hard-wired
and pre-assigned. GNS-430 Unit #1 must be connected to ARINC port 1 (GPS output line)
and port 2 (VLOC output line). GNS-430 Unit #2 (if installed) must be connected to ARINC
port 3 (GPS output line) and port 4 (VLOC output line). When GNC-420 units are to be
installed, they must be connected to ARINC port 1 (or 3 if serving as the 2nd navigator),
leaving port 2 (or 4 if serving as the 2nd navigator) vacant. Use the line select keys R1, R2 to
configure the PFD in the following manner:
Line Select Key (LSK) R1: Nav 1: 430/530, 420, or None as appropriate;
LSK R2: Nav 2: 430/530, 420, or None as appropriate.

NOTE: GNS-430 and GNS-530 are electrically identical and are treated as one in the same
when integrating with the Entegra PFD.
Once complete, verify the displayed configuration in the sensor suite section of the System
Setup page accurately reflects actual configuration.
7.5.2.2 GNS-430 Unit(s)
NOTE: Refer to the GNS 430 users guide for GNS 430 detailed operations.
The GNS-430s must be configured as indicated below to integrate with the PFD.
1) Place the GNS 430 unit(s) into Maintenance Mode via the following steps:
a) Ensure GNS 430 unit(s) off
b) Depress the “ENT” button as the power to the GNS 430 unit(s) is applied
c) Continue to depress the ENT button until the GNS 430 self -test is completed
2) Depress the ENT button twice to display the “MAIN ARINC 429 CONFIG” page
3) Configure the GNS 430 unit(s) to have the following mandatory settings (See Table 1):

Field GNS-430/530 in slot #1 GNS-430/530 in slot #2 (if installed)

IN 1 Low, Sandel EHSI Low, Sandel EHSI
IN 2 Low, OFF Low, OFF
Out Low, GAMA 429 Graphics Low, GAMA 429 Graphics
SDI LNAV1 LNAV2
Table 1 Main ARINC 429 Configuration Page

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4) Turn the right inner knob until the “MAIN RS232 CONFIG” page is displayed.
5) Configure the GNS 430 unit(s) to have the following mandatory settings (See Table 2):

GNS-430 in slot #1 GNS-430 in slot #2 (if installed)

Field
Input Output Input Output
CHNL 1 Off (1) Aviation Off (1) Aviation
CHNL 2 Off (1) Off (1) Off (1) Off (1)
CHNL 3 Crossfill(2) Crossfill(2) Off (1) Off (1)
CHNL 4 Off (1) Off (1) Off (1) Off (1)
Table 2 Main RS232 Configuration Page

Note 1: Unless other equipment installed (i.e., Stormscope)

Note 2: Applies when two GNS-430’s are installed, otherwise ignore.
6) Turn the right inner knob until the “MAIN INPUTS 2” page is displayed. Verify CDI =
“GPS”
7) Turn the right inner knob until the “MAIN DISCRETE OUTPUTS” page is displayed.
Verify Discrete Toggle = “APR”
8) Turn the right inner knob until the “VOR/LOC/GS ARINC 429 CONFIG” page is
displayed
9) Configure the GNS 430 unit(s) to have the following mandatory settings (See Table 3):
Field GNS-430 in slot # 1 GNS-430 in slot #2 (if installed)
Speed Low - Low Low – Low
IN 2 VOR/ILS1 VOR/ILS2
DME Mode Directed Freq. 1 Directed Freq. 2

Table 3 VOR/LOC/GS ARINC 429 Configuration Page

10) Power up the GNS-430 unit(s) normally (not in Maintenance Mode).

11) Using the right knobs, access the Aux/Setup 1 page.
12) Ensure that Mag Var is set to Auto.

Note: Ensure GNS430 Lighting is set-up appropriately and that night lighting is
balanced with the PFD, other avionics and aircraft systems.
7.5.2.3 GNC-420 Unit(s)
NOTE: GNC-420 interface support is only available for PFD software part numbers 530-
000123-000 Revision 02 and subsequent revisions or 530-00159-000 Rev 00 and subsequent
revisions
NOTE: Refer to the GNC 420 users guide for GNC 420 detailed operations.

1) Place the GNC 420 unit(s) into Maintenance Mode via the following steps:
a) Ensure GNC 420 unit(s) off

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b) Depress the “ENT” button as the power to the GNC 420 unit(s) is applied
c) Continue to depress the ENT button until the GNC 420 self -test is completed
2) Depress the ENT button twice to display the “MAIN ARINC 429 CONFIG” page
3) Configure the GNC 420 unit(s) to have the following mandatory settings (See Table 4):

Field GNC-420 in slot #1 GNC-420 in slot #2 (if installed)

IN 1 Low, Sandel EHSI Low, Sandel EHSI
IN 2 Low, OFF Low, OFF
Out Low, GAMA 429 Graphics Low, GAMA 429 Graphics
SDI LNAV1 LNAV2
Table 4 Main ARINC 429 Configuration Page

4) Turn the right inner knob until the “MAIN RS232 CONFIG” page is displayed.
5) Configure the GNC 420 unit(s) to have the following mandatory settings (See Table 5):

GNC-420 in slot #1 GNC-420 in slot #2 (if installed)

Field
Input Output Input Output
CHNL 1 Off (1) Aviation Off (1) Aviation
CHNL 2 Off (1) Off (1) Off (1) Off (1)
CHNL 3 Crossfill(2) Crossfill(2) Off (1) Off (1)
CHNL 4 Off (1) Off (1) Off (1) Off (1)
Table 5 Main RS232 Configuration Page

Note 1: Unless other equipment installed (i.e., Stormscope)

Note 2: Applies when two GNC-420’s are installed, otherwise ignore.
6) Power up the GNS-430 unit(s) normally (not in Maintenance Mode).
7) Using the right knobs, access the Aux/Setup 1 page.
8) Ensure that Mag Var is set to Auto.
Note: Ensure GNC420 Lighting is set-up appropriately and that night lighting is
balanced with the PFD, other avionics and aircraft systems
7.5.3 Aircraft Model Setup
The following steps shall be performed to configure the PFD for the correct aircraft model.
1. Enter the System Setup Page (see section 3.1).
Press LSK R4, labeled “A/C Model”, as required until the appropriate aircraft model is displayed
on the button label. Note that the model field in the middle of the page reflects the model
selected. For those aircraft models that have a “+” suffix displayed in the LSK R4 button label,
OAT will be suppressed from the display.

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7.5.4 Autopilot Setup

7.5.4.1 PFD Unit
The following steps shall be performed to configure the autopilot interface.
1. Enter the System Setup Page (see section 3.1) and press the line select key R3,
labeled “Perform A/P Cal” and depress line select key R1 “ A/P Type” to select
the appropriate autopilot.
For Software Part Numbers other than 530-00123-000 Rev 02:
2. Select line select key L4 labeled “Back to PFD” and reenter the System Setup
Page. Verify the displayed autopilot configuration in the sensor suite section of
the System Setup page accurately reflects actual configuration.

For Software Part Number 530-00123-000 Rev 02 and subsequent revisions or 530-00159-
000 Rev 00 and subsequent revisions:
3. Select line select key L3 labeled “Back to Setup” to return to the System Setup
Page. Verify the displayed autopilot configuration in the sensor suite section of
the System Setup page accurately reflects actual configuration.
7.5.4.2 Autopilot Unit – Bendix-King KAP-140 autopilots
If the autopilot installed in the aircraft is a Bendix-King KAP-140, perform the standard
autopilot installation calibration steps as outlined in the KAP-140 installation and
maintenance manuals. A computer with serial input and terminal application and a serial
adapter cable are required. (see KAP-140 documentation) Be sure to make note of the
following factors during the autopilot calibration:
a) When calibrating the autopilot, ensure that the PFD has completely initialized and
heading is valid before performing the calibration steps.
b) For calibrating the deviation signals for VOR, localizer, and glideslope, ensure that the
PFD NAV source (top left line select) is set to VLOC (1 or 2, corresponding to the nav radio in
use).
c) For calibrating GPS NAV mode, ensure that the PFD NAV source (top left line select) is set
to GPS (1 or 2, corresponding to unit in use).
d) If the autopilot exhibits some roll bias from the turn gyro input, consult the KAP-140
documentation for instructions on how to adjust the unit for this bias.

7.5.4.3 Autopilot Unit – STEC autopilots

If the autopilot installed in the aircraft is an S-Tec System 1500, 55X, or 55SR, ensure it is
configured as a KCS-55 compatible unit. Refer to the S-Tec System 1500, 55X, 55SR
Installation Manual for details.
In dual PFD installations, the procedure below needs to be performed on both PFDs. The
procedure, however, can be conducted simultaneously on both PFDs.

Note: The following steps are to be performed in-flight in smooth air for aircraft
equipped with an S-Tec 55X or 55SR autopilot.

1. While NAV (without GPSS) mode is engaged on the System 55X or System 55SR,
using a GNS-4XX GPS source, insert an appropriately sized screwdriver into the
slotted hole to perform the alignment procedures in accordance with the System
55X or 55SR Installation Manual.
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2. Perform a NAV course alignment by slowly adjusting the screw until the aircraft
closely tracks the GPS course. Allow the aircraft to stabilize between
adjustments. This may take several minutes and require several adjustments.
For aircraft equipped with flight director enabled PFDs and S-Tec 55X equipped or S-
Tec 1500 equipped:
3. Select AP/FD or AP ON position on the aircraft Autopilot Master switch
4. Engage the 55X or 1500 in HDG and ALT mode and allow aircraft to “settle on
heading bug” The heading bug and flight director may be offset from the lubber
line by several degrees.
5. Turn off all GPS/NAV systems
6. Enter System Setup mode on the PFD by following steps 1 through 4 in the
System Setup Page Access section.
7. Turn on all GPS/NAV systems.
8. Select “Perform A/P Cal”.
9. Select "Sync HDG". Autopilot should immediately command the aircraft to turn
toward the heading bug.
10. Select "Back to PFD".
11. Verify HDG mode accurately tracks heading bug.

Note: In dual PFD installations, the Copilot PFD may show a slight error between
heading bug and heading when in HDG mode. This is normal and is due to normal
tolerances between the heading systems in the two PFDs.

12. Verify the Flight Director Command Bars are above the aircraft reference symbol
with no gap between the two.
13. Engage NAV (without GPSS) mode on the autopilot.
14. Verify NAV mode accurately tracks flight plan (Flight plan or waypoint will
need to be entered).
15. A/P calibration is complete.
16. If autopilot does not track the heading bug or NAV mode correctly, repeat steps
in this procedure.
For aircraft equipped with non flight director enabled PFDs and S-Tec 55X equipped:
3. Engage the 55X or 55SR in HDG mode and allow aircraft to “settle on heading
bug” (If heading bug agrees with aircraft heading stop procedure here, other
wise continue calibration steps below).
4. Turn off all GPS/NAV sources.
5. Enter System Setup mode on the PFD by following steps 1 through 4 in the
System Setup Page Access section.
6. Turn on all GPS/NAV sources.
7. Select “Perform A/P Cal”.
8. Select "Sync HDG". Autopilot should immediately command the aircraft to turn
toward the heading bug.
9. Select "Back to PFD".
10. Verify HDG mode accurately tracks heading bug.

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11. Engage NAV (without GPSS) mode on the autopilot.
12. Verify NAV mode accurately tracks flight plan (Flight plan or waypoint will
need to be entered).
13. A/P calibration is complete.
14. If autopilot does not track the heading bug or NAV mode correctly, repeat steps
in this procedure.

7.5.5 Units Setting

7.5.5.1 Barometric Units Setting
The following steps shall be performed to configure the PFD for desired barometric units.
Note: This section does not apply to PFDs with software part number 530-00123-000, Version
00.
1. Enter the System Setup Page (see section 3.1).
2. Press LSK R3, labeled "Perform A/P Cal", button to enter the Autopilot
Calibration page.
3. Press LSK R4, labeled "Baro Unit", button to cycle through barometric pressure
units (inHg, hPa, Mb).
Once the desired units have been selected and appear in the button label, press the "Back to
PFD" button (LSK L4).
7.5.5.2 Fuel Quantity Units Setting
The following steps shall be performed to configure the PFD for desired fuel quantity and
flow units, if applicable.
Note: This section applies to certain aircraft models with software part number
1. Enter the System Setup Page (see section 3.1).
2. Press LSK R2, labeled "Fuel Units", button to change between English and Metric
units for fuel quantity and fuel flow.
Once the desired units have been selected and appear in the button label, press the "Back to
PFD" button (LSK L4).
7.5.6 Dual PFD Setup
In some dual PFD capable aircraft, the second, copilot side, PFD is an option. For these
aircraft, the pilot-side PFD needs to configured appropriately depending on whether a
copilot PFD is installed or not. For these aircraft, perform the following procedure:
1. Enter the System Setup Page (see section 3.1).
2. Press LSK R1, labeled "Copilot PFD", button to change between Installed or None
depending on whether or not a copilot PFD is installed.
Once the applicable configuration has been selected and appears in the button label, press the
"Back to PFD" button (LSK L4).
7.5.7 PFD System Calibrations
The PFD and Magnetometer require calibrations upon initial installation, when replaced, or
bi-annual periodic inspection. The following two aircraft level calibration procedures are
listed below:

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Periodic
Calibration When Performed Notes
Calibration
IRU Initial installation and replacement Must be performed first upon initial None
installation with Magnetometer
Magnetometer Initial installation, replacement, Must be performed after IRU calibration Every 24
replacement of PFD, or bi-annual upon initial installation or replacement of months
inspection PFD

Note: The IRU calibration must be completed prior to the Magnetometer calibration

Note: In dual PFD installations IRU and Magnetometer calibrations must be completed
on both PFDs.

7.5.7.1 IRU Calibration Procedure

Approximate duration: Approximately 20 Minutes
Required Equipment: Digital Level, Resolution: 0.25°, Accuracy: +/- 0.25°
Recommended Personnel: One avionics technician
Procedure:
1. Avionics power applied.
2. Allow the PFD to align (approximately 3 minutes) until the ADAHRS
countdown timer expires and the Gyro Warm-up box is removed.
3. Wait in the aligned state for an additional 10 minutes.
4. Enter System Setup mode on the PFD by following steps 1 through 4 in the
System Setup Page Access section.
5. Press the IRU Install line select key (L2).

Note: The IRU Installation page is displayed (see Figure 10).

6. Place a digital level in accordance with aircraft ICA (An aircraft ICA is required by
Federal Aviation Regulations (FAR) Part 23, Appendix G. Chapter 4) instructions for
lateral leveling of the aircraft.
7. Following the directions on the IRU installation page, adjust the “IRU Installed
Roll Attitude” counter to be equal to the digital level reading. (if the right wing is
low, as viewed by the pilot, enter a positive number.)
8. Place a digital level in accordance with aircraft ICA instructions for longitudinal
leveling of the aircraft.
9. Following the directions on the IRU installation page, adjust the “IRU Installed
Pitch Attitude” counter to be equal to the digital level reading ± 0.25degrees.

Note: The only two axis that are changed via installation calibration input is
the pitch axis and roll axis
Note: The pitch attitude as determined by the digital level should have a
resolution of at least ¼°. This applies to the roll axis also.

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10. Press the Install IRU line select key (R4) when proper pitch and roll is
displayed.
11. After the display indicates the IRU calibration is done wait 10 seconds and then
cycle power on the PFD in order for the IRU calibration to take effect.

Figure 10 IRU Installation Page.

7.5.7.2 Magnetometer Calibration Procedure

Approximate duration: 20 minutes (assuming airplane is free to rotate 360°
without magnetic disturbances)
Required equipment: Installed PFD
Installed magnetometer
Reference Compass: Resolution: 1°, Accuracy: +/- 1°
Recommended personnel: 2 avionics technicians (one in the aircraft to push required bezel
buttons, one on the wing to push the aircraft to new headings
and read the marine compass)

Note: Ensure the IRU install calibration procedure has been completed.

Procedure:
1. Aircraft doors closed.
2. Flaps in retracted position.
3. Engine off.
4. Airplane in level flight attitude.
5. Install the marine compass onto the top surface of the left tail surface.
6. Position lubber line to be parallel with longitudinal axis of the airplane.
7. Position marine compass to be approximately ½ chord length back from
leading edge of tail and 43 inches outboard from fuselage.

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8. Turn battery switch to on. (Consider attaching an external power cart until ready
for step 11.) PFD may already be on and aligned from IRU install. If so, skip to
step 11. All other aircraft equipment shall be operating.
9. Allow the PFD to align (approximately 3 minutes) until the ADAHRS
countdown timer expires and is removed from the display.
10. Wait in the aligned state for an additional 10 minutes.
11. Enter System Setup mode on the PFD by following steps 1 through 4 in the
System Setup Page Access section.
12. Press the Perform Mag Cal line select key (L1).

Note: The Magnetometer Calibration page is displayed (See Figure 11)

13. Align centerline of airplane on magnetic north heading as indicated by tail

mounted compass by pushing the aircraft as required. Ensure this is
being done clear of magnetic disturbances in the pavement or immediate
vicinity.
14. Follow the directions on the Magnetometer Calibration page (press the
Calibrate Heading button and wait until “Done” is displayed, see note).

Note: On the last heading calibration point (330°), it may take up to a

minute for “Done” to be displayed.

15. Align centerline of airplane on consecutive 30° headings as indicated by

the tail-mounted compass by pushing the aircraft as required and continue
following the directions of the Magnetometer Calibration page until complete.
(see Figures 4 and 5).

Figure 11 Initial Magnetometer Calibration Page

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Figure 12 Final Magnetometer Calibration Page

Note: Pressing (R3) “Redo Previous” provides an “undo” capability.

Note: Aborting the calibration process (i.e., by exiting the Magnetometer

Calibration Page or shutting off power to the PFD) prior to completion
will result in the loss of stored calibration parameters. Restarting the
calibration process over from the beginning will be required.

16. After the last heading point of 330° is calibrated the PFD will present a text
message “Magnetometer Calibration Complete”. After this message appears,
wait approximately 10 seconds and cycle power to the PFD.
17. Align the centerline of the airplane with consecutive 90° headings as
indicated on the tail-mounted magnetic compass and verify the
accuracy of the PFD heading display is within +/- 4° of the tail mounted
magnetic compass.
18. Calibration complete.

7.6 Functional Checks

7.6.1 Lighting Check
Rotate the “INST” instrument lighting control rheostat through its full range of motion.
Ensure the PFD LED lights around all bezel keys and knobs come on and match the MFD
LED lighting.

Note: An approximate 1 second lag to full brightness is normal.

7.6.2 GPS NAV-COMM Check

7.6.2.1 Dual GPS-NAV-COM (2 x GNS-430/530) Combination:

1. PFD Nav Button- Ensure GPS1 displayed. Observe that the GNS-430 No. 1 CDI
button label displays GPS.

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2. GNS-430 No. 1 CDI button- Press once and observe CDI button displays VLOC
label. Observe the PFD Nav button changes to VLOC1.
3. GNS-430 No.1 CDI button- Press once and observe the CDI button label displays
GPS. Note that the PFD Nav button changes to GPS1.
4. PFD Nav button- Press once and observe VLOC1 is displayed. Observe the GNS-
430 No. 1 CDI button changes to VLOC.
5. PFD Nav button- Press once and note GPS2 is displayed. Observe the GNS-430
no. 2 CDI button displays GPS.
6. GNS-430 No. 2 CDI button- Press once and observe the CDI button label displays
VLOC. Observe the PFD Nav button changes to VLOC2.
7. GNS-430 No. 2 CDI button- Press once and observe the CDI button label displays
GPS. Observe the PFD Nav button changes to GPS2.
8. PFD Nav button- Press once and observe VLOC2 is displayed. Observe the GNS-
430 No. 2 CDI button changes to VLOC.

7.6.2.2 Single GPS-NAV-COM and Single GPS-COM Combination (1 x GNS-430/530, 1 x GNC-

420):

1. PFD Nav Button- Ensure GPS1 displayed. Observe that the GNS-430 No. 1 CDI
button label displays GPS.
2. GNS-430 No. 1 CDI button- Press once and observe CDI button displays VLOC
label. Observe the PFD Nav button changes to VLOC1.
3. GNS-430 No.1 CDI button- Press once and observe the CDI button label displays
GPS. Note that the PFD Nav button changes to GPS1.
4. PFD Nav button- Press once and observe VLOC1 is displayed. Observe the GNS-
430 No. 1 CDI button changes to VLOC.
5. PFD Nav button- Press once and note GPS2 is displayed. Observe the GNC-420
no. 2 CDI button displays GPS.

7.6.2.3 Single GPS-COM Configuration (1 x GNC-420):

1. GNS 420 No. 1 OBS button – Press once and observe the OBS label is present on
the GNC-420 and that the left knob on the PFD is now labeled “CRS
SET/CENTER”.
2. GNS 420 No. 1 OBS button – Press once and observe the OBS label is not
displayed on the GNC-420 and that the left knob on the PFD has no label.

Note: Two-way communication between the PFD and both GNS-430 units has just
been demonstrated.
7.6.3 Pitot-Static Leak Check
The pitot-static leak check shall be performed anytime time the pitot-static ports are
disconnected from the PFD. The pitot-static leak check shall be performed in accordance
with the specific Aircraft Maintenance Manual.

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7.6.4 EMI Check

Verify that no interference is noted through the use of the PFD on other systems in the
aircraft. The operation of the PFD should not result in Nav flags, constant location lightning
strikes on the WX-500 sensor, noise on COMM channels, or other phenomena.
1. Comm Radios - Scan through radio channels to ensure there is no interference
caused by the PFD. Check random frequencies from 118MHZ through
136.975MHZ as well as your local ground and tower frequencies to ensure there
is no break in squelch due to the installation.
2. GPS - Ensure that correct position is displayed and that there is no change in
satellite signal strength with the PFD powered off.
3. Autopilot - Ensure that autopilot self-test passes OK with the PFD powered on.
4. Other Instruments - Verify there is no adverse effect on other instruments with
the PFD powered on.
7.6.5 Magnetic Compass Swing
After installation and EMI checks are complete, perform a magnetic compass “swing” in
accordance with the aircraft installation manual for updating the heading correction card in
accordance with 14 CFR 23.1327 and 23.1547.
7.6.6 Dual PFD Checks
The following additional checks should be performed on dual PFD installations:
1. Verify that there are no yellow alert messages displayed.
2. On either PFD cycle through all of the available Nav sources and verify that the
Nav source on the other PFD matches that on the one where the changes were
made.
If equipped with a Copilot PFD Controls Inhibit switch, perform the following additional
check:
3. Set the Copilot PFD Controls Inhibit switch in the “Inhibit” position. Verify that
the Nav, Hdg, Alt, VSI (if applicable), and Baro Set button labels are removed.
4. Set the Copilot PFD Controls Inhibit switch in the “Normal” position. Verify that
the button labels are restored.

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Diagrams
This section is not applicable.

8. Special Inspection Requirements

This section not applicable.

9. Application of Protective Treatments

This section not applicable.

10. Data
This section not applicable.

11. List of Special Tools

1. Master or Sight compass, Resolution: 1 °, Accuracy: +/- 1 °
2. Digital level, Resolution: 0.25 °, Accuracy: +/- 0.25 °

12. For Commuter Category Aircraft

This section not applicable.

13. Recommended Overhaul Periods

This section not applicable.

14. Airworthiness Limitation Section

The Airworthiness Limitations section is FAA approved and specifies maintenance required
under §43.16 and §91.403 of the Federal Aviation Regulations unless an alternative program
has been FAA approved.
There are no additional airworthiness limitations as a result of this modification.

15. Revision
Revisions to this document shall be coordinated through the Boston Aircraft Certification
Office, the Kansas City AEG, and the STC holder. Inquiries relating to the ICA should be
made to Avidyne Corporation. If you would like to be notified of future revisions to this
manual please furnish the information listed below:

Name
Address
City, State, and Zip Code
Part Number of Manual
Current Revision Status of Manual

Please submit this information to:

Avidyne Corporation
55 Old Bedford Road
Lincoln, MA 01773

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