GDU 620 Installation Manual Rev. B
GDU 620 Installation Manual Rev. B
GDU 620 Installation Manual Rev. B
Installation Manual
DOCUMENT PAGINATION
Section Page Range
Table of Contents i through vi
Section 1 1-1 through 1-10
Section 2 2-1 through 2-4
Section 3 3-1 through 3-10
Section 4 4-1 through 4-14
Section 5 5-1 through 5-26
Section 6 6-1 through 6-2
Section 7 7-1 through 7-2
Section 8 8-1 through 8-2
Appendix A A-1 through A-2
Appendix B B-1 through B-10
Appendix C C-1 through C-18
CAUTION
The GDU 620 lens is coated with a special anti-reflective coating which is very sensitive
to skin oils, waxes and abrasive cleaners. CLEANERS CONTAINING AMMONIA
WILL HARM THE ANTI-REFLECTIVE COATING. It is very important to clean the
lens using a clean, lint-free cloth and an eyeglass lens cleaner that is specified as safe for
anti-reflective coatings.
5.4 GDU 620 System Status Page (Left Side) .................................................................................... 5-2
81H 20H
5.5 GDU 620 System Setup and Checkout Pages (Right Side) .......................................................... 5-3
82H 21H
5.5.4 GDL Page Group (Available only when GDL 69 Datalink present) ................................. 5-18
86H 25H
Figure C-1. Power and Configuration Module Lighting Interconnect – Single GDU .............................. C-3
104H 254H
Figure C-2. Attitude – Air Data Interconnect – Single GDU ................................................................... C-4
105H 25H
Figure C-13. Attitude – Air Data Interconnect – Dual GDUs ................................................................ C-15
16H 26H
LIST OF TABLES
Table 2-1. Catalog Part Numbers............................................................................................................... 2-1 269H
Table 3-5. Configuration Module Wire Color Reference Chart ................................................................ 3-8 27H
Heading Select
Range Select
Course Select
Altitude Select Menu
Vertical Speed Select Enter
Barometric Correction Clear
Smart Keys Bottom SD Card Slot Smart Keys Outer MFD Knob
(Database Loader Card) (Select Page Group)
Top SD Card Slot
(Software Loader Card)
Notes:
[1] The TSOs identified in the table above are for an incomplete system and requires the GDU 620 to
be installed and checked out according to this installation manual.
[2] The GDU 620 displays data for all classes of compatible interfaced TSO-C147 authorized
equipment. The GDU 620 equipment class is identical to that of the interfaced equipment.
GDU 620 Installation Manual Page 1-7
190-00601-04 Rev. B
Software Design Assurance
Function DO-178B Level
Operating System B
PFD display of Flight Director Bars B
PFD display of VOR/ILS LOC/Glide Slope CDI & VDI information B
PFD display of ADF bearing pointer information B
PFD display of GPS altitude, CDI & VDI, and level of service information B
PFD display of baro altitude, attitude, slip-skid, rate-of-turn, heading, track, air B
speed, vertical speed, ground speed, track information, and outside air
temperature
Display of charts and TAS/TIS traffic information C
Display of other information – moving map, terrain, flight plan overlay, D
XM weather data, XM audio entertainment, supplement waypoint and airport
information, and time.
GDU 6xx ChartView Activation Card – Heavy Aircraft [1] 010-00769-50 010-00770-00
GDU 6xx ChartView Activation Card – Light Aircraft [1] 010-00769-53 010-00770-10
GDU 6xx Altitude Preselect Activation Card [1] [2] 010-00769-52 010-00770-30
[1] An SD activation card is required to enable the indicated feature. Each activation card can only be
used once and, once used, the card will be only work with that particular system.
[2] The Altitude Preselect option is only available for certain autopilots. Contact Garmin for availability
for a specific autopilot.
2.2.4 Materials Required But Not Supplied
The GDU 620 is intended for use with the standard aviation accessories. The following items are required
for installation, but not supplied:
• Wire (MIL-W-22759/16 or equivalent)
• Shielded Wire (MIL-C-27500 or equivalent)
• Nut Plates, Reduced Rivet Spacing, No. 6 (six minimum – MS21071-06 or equivalent)
• Circuit Breaker (5A for 28V installations, 7.5A for 14V installations)
• Tie Wraps or Lacing Cord
• Ring Terminals (for grounding)
1. Position the GDU 620 Cutout Template on the instrument panel at the desired location for the
GDU 620 and temporarily affix the Cutout Template in this location. When positioning the
template ensure that the existing instrument panel material is visible by the maximum number of
mounting holes. This will permit the maximum number of nutplates to be mounted in the
instrument panel.
2. Using the template as a guide, drill six 0.1285” holes for the GDU 620 mounting points using a
#30 drill bit.
3. Transfer the GDU 620 LRU outline to the instrument panel, using the outside edges of the cutout
pattern.
4. Remove the template from the instrument panel. Fill in the gaps in the cutout markings on the
instrument panel using a straight edge.
5. Enlarge the six mounting holes to 0.144 using a #27 drill bit.
6. Cut out the GDU 620 outline on the instrument panel.
GDU 620 Installation Manual Page 3-1
190-00601-04 Rev. B
7. Install six No. 6 fixed nutplates (P/N MS21071-06) as shown in Figure B-7.
283H
8. If required, install the trim plate prior to installing the GDU 620.
3.4 Unit Replacement
Whenever the GDU 620 is removed and reinstalled, verify that the slide-lock is engaged on both sides of
each connector. Also verify that the GDU 620 unit power-up self-test sequence is successfully completed,
all databases are present and no failure messages are annunciated. If the unit was serviced or if a different
unit is being installed, verify that the configuration is correct using the previously completed checkout log
prior to verifying that the GDU 620 unit power-up self-test sequence is successfully completed and no
failure messages are annunciated.
NOTE
The installation configuration settings are stored in the configuration module and will be
retained when the GDU 620 is replaced with a new unit. However, user settings are in
internal LRU flash memory and will be lost when the GDU 620 is replaced with a new
unit.
3.5 Cabling and Wiring
The GDU 620 connector kit includes connectors and crimp contacts. Make the crimp connections with a
crimp tool as specified in Table 3-2.
284H
Refer to the interconnection diagrams in Appendix C for the appropriate interconnections. Use 22 or 24
285H
AWG wire for all connections except for power. Use 20 AWG for power/ground. Install the configuration
module as described in Section 3.6.1.2. Once the cable assemblies have been made, position the cable so
286H
that there is sufficient length to allow the GDU to be removed from the instrument panel with the cables
attached. Route the wiring bundle as appropriate. Avoid sharp bends.
engaged into the connector by gently tugging on the wire. Route and secure the cable run from the
GDU 620 to the other units away from sources of electrical noise.
Section 4 provides I/O definition of all input and output signals. Required connectors and associated
28H
hardware are supplied with the connector kit. See Appendix C for interconnect wiring diagrams.
289H
CAUTION
Check wiring connections for errors before connecting the cables to the GDU 620. Incorrect
wiring could cause component damage.
for the GDU 620 D-sub connectors and the backshell assemblies.
Table 3-3. Backshell Assembly
The GDU 620 connector kit (P/N 011-01656-00) includes three Garmin backshell assemblies and three
Garmin ground adapter assemblies. Backshell connectors give the installer the ability to terminate shield
grounds at the backshell housing using the Shield Block ground kit. Table 3-3 lists Garmin part numbers
for the GDU 620 D-sub connectors and the backshell assemblies.
2. Connect a 20 or 22 AWG wire (13) to the exposed shield of the prepared cable assembly. (See Figure 297H
3. Slide a shield terminator (12) onto the prepared cable assembly (11) and connect the wire (13) to the
shield using a heat gun approved for use with solder sleeves. The chosen size of solder sleeve must
accommodate both the number of conductors present in the cable and the wire (13) to be attached.
5. Crimp pins/sockets (14) onto the wires and terminate in the connector (10) in accordance with the
aircraft wiring drawings.
6. For P6202, install the configuration module wires into the connector. Refer to Section 3.6.1.2, steps 1
30H 301H
CAUTION
When mounting the slide lock, use only the specified screws (6). Do not attempt to use
the self-tapping screws supplied in the slide lock kit, as these will damage the backshell
housing.
2. Place the slide lock (5) over the connector (10). While holding the slide lock in place, attach the
connector / slide lock to the backshell (1) by inserting two screws (6) through the holes on the
connector and threading into the tapped holes on the backshell (1). (See Figure 3-1)
304H
3. Wrap the cable bundle with Silicone Fusion Tape (19 or a similar version) at the point where the
backshell strain relief and cast housing will contact the cable bundle.
CAUTION
Placing the grooved side of the strain relief across the cable bundle may damage wires.
4. Place the smooth side of the backshell strain relief (7) across the cable bundle and secure using the
three screws (6).
5. For P6202, install the configuration module into the connector backshell. Refer to Section 3.6.1.2
305H
steps 3 through 6 for instructions on installing the configuration module into the backshell.
306H 307H
7. Install ring terminals (15) onto the wires (13), grouping wires as appropriate for the connector.
8. Terminate the ring terminals to the shield block (2) by placing items on the pan head screw (16) in the
following order: split washer (17), flat washer (18), first ring terminal, second ring terminal if needed,
before finally inserting the screw into the tapped holes on the shield block.
3.6.1.2 Configuration Module Installation (P6202 Only)
Table 3-4 lists part numbers for the Configuration Module Kit, which is used with P6202 only.
308H
1. Crimp socket contacts (4) onto each wire of the four-conductor wire harness (3). Strip 1/8” of
insulation from each wire prior to crimping.
2. Insert newly crimped socket contacts and wires (3, 4) into the appropriate connector housing
location as shown in Figure 3-4, Figure C-1, and Figure C-12.
310H 31H 312H
3. Apply the spacer (2) by wrapping it around the PCB board (1) making sure to insert the plastic
connector mounted on the board into the hole provided in the spacer.
4. Plug the four-conductor wire harness (3) into the connector on the PCB board (1).
5. With pad (2) in position, insert PCB board (1) into the backshell recess.
6. Orient the connector housing so that the inserted four conductor wire harness (3) is on the same
side of the backshell as the inserted PCB board (1), as shown in Figure 3-4.
31H
20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37
18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33
34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50
42 41 40 39 38 37 36 35 34 33 32 31 30 29 28 27 26 25 24 23 22
62 61 60 59 58 57 56 55 54 53 52 51 50 49 48 47 46 45 44 43
4.2.1 Power
Pin Name Connector Pin I/O
AIRCRAFT POWER P6202 1 In
AIRCRAFT POWER P6202 18 In
AIRCRAFT POWER P6201 34 In
AIRCRAFT GND P6202 2 --
AIRCRAFT GND P6202 19 --
AIRCRAFT GND P6201 35 --
The GDU 620 will accept input power from 9 to 33 VDC. At least two of the power inputs should be
connected.
4.2.3.3 Ethernet
Pin Name Function Connector Pin I/O
ETHERNET IN 1A GDL 69/69A P6201 11 In
ETHERNET IN 1B GDL 69/69A P6201 12 In
ETHERNET OUT 1A GDL 69/69A P6201 13 Out
ETHERNET OUT 1B GDL 69/69A P6201 14 Out
ETHERNET IN 2A GWX 68 P6201 30 In
ETHERNET IN 2B GWX 68 P6201 31 In
ETHERNET OUT 2A GWX 68 P6201 32 Out
ETHERNET OUT 2B GWX 68 P6201 33 Out
This Ethernet based HSDB (High Speed Data Bus) meets the hardware aspects of IEEE standard 802.3
for 10 base T Ethernet communications.
4.2.3.4 RS-422/RS-485
Pin Name Function Connector Pin I/O
RS-422/RS-485 1A S-TEC 55X P6203 9 I/O
RS-422/RS-485 2A P6203 10 I/O
RS-422/RS-485 3A P6203 11 I/O
RS-422/RS-485 4A P6203 12 I/O
RS-422/RS-485 1B S-TEC 55X P6203 31 I/O
RS-422/RS-485 2B P6203 32 I/O
RS-422/RS-485 3B P6203 33 I/O
RS-422/RS-485 4B P6203 34 I/O
The RS-422/485 ports conform to EIA Standard RS-485 (RS-422 when configured as RS-422) with a
differential output voltage swing of at least ± 1.5V when driving a standard RS-422/485 load.
The serial ports can receive/transmit serial data from/to various sources.
Refer to section 5.5.1.9 for configuration information.
316H
Each superflag output provides (Vin – 2) volts relative to ground when valid information is present, where
Vin represents the aircraft power supplied to the GDU 620. Each output is capable of supplying up to
250 mA.
The flight director interface has a discrete input associated with it. When configured for an external flight
director, this input is used by the GDU 620 to determine whether or not to display the FD bars. Refer to
Section 4.2.7.4 for additional details.
321H
8. New software is loaded to the GDU. When complete, the following screen is displayed:
9. Press any soft key to acknowledge the prompt, and the GDU starts in configuration mode.
5.3 Initial Configuration of the GDU 620
As part of the initial configuration, the GDU 620 functions must be enabled/disabled as desired, external
data sources must be configured, and miscellaneous options must be set up. To do this an Installer Unlock
Card (P/N 010-00769-60) must be inserted, and the unit must be started in configuration mode by
pressing and holding the ENT button while applying power.
When in configuration mode the left display has only one page that is used to display status and product
information. The right display has multiple pages that are used to configure and checkout the installation
of the GDU 620.
NOTE
To access all of the configuration screens shown herein, an Installer Unlock Card
P/N 010-00769-60 must be inserted in the bottom card slot prior to applying power to the
GDU 620.
1. GDL 69 Page
Activate the cursor, select the system using the large MFD knob, and then press the ENT button. This will
activate or deactivate the highlighted system. For activated systems, use the small knob to select the
appropriate LRU from the dropdown TYPE menu, and then press enter to select the LRU.
Continue to activate or deactivate each LRU, as required.
A green light means that the LRU is configured as ‘present’. No light (black) means that the LRU is
configured as ‘not present’ (the TYPE field will be blank in this case).
INTERFACING SYSTEMS Window:
1. Cross-side GDU Type, Selections: GDU 620 is the only selection.
2. AHRS Type, Selections: GRS 77 is the only selection.
3. ADC Type, Selections: GDC 74 is the only selection.
4. GPS1 Type, Selections: GPS 400W, GNC 420W, GNS 430W, GNS 480, GPS 500W, GNS 530W.
5. GPS2 Type, Selections: GPS 400W, GNC 420W, GNS 430W, GNS 480, GPS 500W, GNS 530W.
NOTE
The SL30 can only be configured as NAV1 or NAV2, and not for both NAV receivers
simultaneously.
6. NAV1 Type, Selections: GNS 430W, GNS 480, GNS 530W, SL30.
The DISPLAY and KEY lighting characteristics are adjusted separately, each with the following fields:
BRIGHTNESS Window:
1. INPUT SOURCE, this selection determines if the display brightness control is controlled by the
photo cell or the dimming bus input. Selections: Photo, 14V DC, 28V DC, 5V DC, 5V AC.
Source Input Level and Backlight Output Level cannot change the display information about the current
GDU620 screen settings.
2. MINIMUM LEVEL, sets the minimum brightness of the display. The higher the number, the
brighter the minimum brightness. Display Minimum Level has a range of 5 and higher. Key
Minimum Level has a range of 14 and higher. It is prudent to verify that display and key lighting
characteristics match those of other equipment in the panel under night lighting conditions.
3. RESPONSE TIME, sets the speed with which the brightness responds to the input level (bus
voltage or ambient light) changes. The higher the number the slower the display responds. This
field has a range of 2-7.
4. SLOPE, sets the sensitivity of the display brightness in proportion to changes in the input level.
The higher the number, the brighter the display is for a given increase in the input level. This field
has a range of 0 to 99.
5. OFFSET, adjusts the lighting level up or down for any given input level. This field has a range of
0 to 99. This may also be used to match lighting curves with other equipment in the panel.
2. KEY BACKLIGHT CUTOFF % - When the photocell input is used to control the lighting of
the bezel keys this parameter sets the point on the photocell input above which the key lighting is
switched off. This field has a range of 20 to 99.
NOTE
If the display lighting is set to track the lighting bus, (the display input source is set to
any selection other than PHOTO) and the lighting bus control is turned to its minimum
(daytime) setting, the display brightness tracks the GDU 620 unit’s photocell using
additional parameters described below.
3. PHOTO TRANS % - When a lighting bus is used to control the lighting of the display, this
parameter sets the points on the lighting bus below which the display brightness tracks the GDU
620 photocell. This field has a range of 0 to 99.
4. PHOTO SLOPE & PHOTO OFFSET – These fields are equivalent to the SLOPE/OFFSET
fields described above, with the exception that they only control the display lighting
characteristics when the lighting bus control is below the level specified in the PHOTO TRANS
% field. Both fields have a range of 0 to 99.
5.5.1.4 Manifest Configuration Page
This page allows the installer to enter or verify the software versions used in a particular installation.
NOTE
Upon first use, the manifest is empty and this page has no entries.
NOTE
When using the MANIFEST soft key, ensure that all configured LRUs show up as online
in the DEVICES ONLINE window before pressing the MANIFEST soft key. The
GDU 620 will only write the information for LRUs that have reported information. If an
LRU has not reported information when the MANIFEST soft key is pressed, that LRU
will automatically be removed from the manifest.
MANIFEST Soft Key: Pressing this soft key causes all LRU-reported software part numbers and
versions to be written to the manifest. To edit individual items proceed as described below:
MANIFEST Window:
Activate the cursor and select the part number or version number that you wish to edit. Turn the small
knob one click to begin editing the first digit in the part number or version number. Use the large knob to
select the digit to be changed, and the small knob to change the value of the selected digit. When done,
press ENT to accept the changes. The cursor automatically moves to the next editable field. When
finished, press the small knob to deactivate the cursor.
FEATURES Window:
Activate the cursor to select from the following fields:
1. CHARTS: determines the type of charts to be displayed. Selections: None, FliteCharts,
ChartView (ChartView requires an unlock card to enable. Refer to section 2.2.3 for information
328H
RS-232 Window:
1. Green Light: The device is configured as ‘Present’ and data is being received on this input.
2. No Light (Black): The device is configured as ‘Not Present’ (OFF is set for INPUT), or the
device is configured as ‘Present’ and no data is being received on this input.
AHRS Window:
T HDG, True heading value input from GRS 77, expressed in degrees.
ROLL, Roll value input from GRS 77, expressed in degrees.
PTCH, Pitch value input from GRS 77, expressed in degrees.
YAW RATE, Yaw rate value input from GRS 77, expressed in degrees/sec.
ROLL RATE, Roll rate value input from GRS 77, expressed in degrees/sec.
PITCH RATE, Pitch rate value input from GRS 77, expressed in degrees/sec.
X ACC, X Axis acceleration value, expressed in m/s².
Y ACC, Y Axis acceleration value, expressed in m/s².
Z ACC, Z Axis acceleration value, expressed in m/s².
VERT ACC, Vertical acceleration value, expressed in m/s².
Air Data Window:
SAT, Static Air Temperature measurement input from GDC, expressed in degrees Centigrade.
TAT, Total Air Temperature measurement input from GDC, expressed in degrees Centigrade.
IAS, Indicated Air Speed measurement input from GDC, expressed in knots.
TAS, True Air Speed measurement input from GDC, expressed in knots.
B ALT, Barometric corrected altitude input from GDC, expressed in feet.
D ALT, Density altitude input from GDC, expressed in feet.
P ALT, Pressure altitude input from GDC, expressed in feet.
CONFIGURATION Window:
1. OAT, specifies the type of OAT probe connected to the GDC 74A. Selections: None, GTP 59,
Goodrich 102AU1AG, Harco 100723-2, ARINC TAT Input.
CONFIGURATION Window:
NOTE
Refer to the GDL 69 Installation Manual (190-00322-02) for antenna gains and
calculation of cable loss.
1. ANTENNA GAIN (LOWER dB), this is used to specify the antenna gain from 22.00 to 40.00
dB in 0.25 dB increments.
2. CABLE LOSS (NOMINAL dB), this is used to specify the antenna cable loss from 3.00 to
11.00 dB in 0.1 dB increments .
NOTE
The GDU 620 automatically calculates the total attenuation value that is required by the
GDL 69/69A. The GDU 620 prevents the installer from entering antenna gain and cable
loss values that result in a total attenuation that is outside the acceptable range of the
GDL 69/69A.
3. TOTAL ATTENUATION (dB), this field is automatically calculated based upon the antenna
gain and cable loss values.
4. ETHERNET PORT 2/3/4, this is used to enable or disable Ethernet ports 2, 3, or 4 on the
GDL 69/69A.
DATA Window:
1. ID, displays the identification number for the data (GDL 69/69A) and audio (GDL 69A) radios.
SYSTEM Window:
1. AUTOPILOT, specifies type of autopilot present. Selections: Bendix IN-831, Century 2000,
Century 21/31/41, Century II or III, Century IV, Century NSD 360 AC, Century NSD 360 DC,
Cessna 400B AC, Cessna 400B DC, Collins APS-65, Collins PN 101, King KFC 250, King KFC
325, King KI 525, Sperry SPZ-500
CONFIGURATION Window:
1. AC/DC, type of error signal. Selections: AC or DC.
2. HDG +, positive sense of the heading error signal. Selections: Left or Right.
3. CRS +, positive sense of the course error signal. Selections: Left or Right.
4. HDG V/DEG, scaling of the heading error signal. Selections: 0.000 to 1.000.
5. CRS V/DEG, scaling of the course error signal. Selections: 0.000 to 1.000.
6. V Min, minimum voltage output for error signals. Selections:+18.000 to -18.000.
7. V Max, maximum voltage output for error signals. Selections: +18.000 to -18.000.
8. V Ref, voltage output for 0° heading/course error signal. Selections: +18.000 to -18.000.
Once the Autopilot type has been selected the default values will be populated and displayed. If any
changes are made to the default values, the message “MODIFIED NONDFLT” will be displayed on
the screen.
SYSTEM Window:
1. FLIGHT DIRECTOR, specifies type of flight director present. Selections: S-TEC® 55X
CONFIGURATION Window:
1. PITCH FILTER, specifies the type of pitch command filtering algorithm to be used. Selections:
Absolute or Relative.
2. PITCH FILTER TIME, +, time constant (sec) for filtering applied to pitch axis of FD. A higher
value corresponds to a slower response to the analog inputs. Selections: 0.0 to 9.9.
3. PITCH +, positive sense of flight director pitch input. Selections: Up or Down
4. PITCH V/DEG, scaling of flight director pitch input. Selections: 0.000 to 9.999
5. PITCH ANGLE MAX, maximum allowed pitch command. Selections: 0 to 90 degrees.
6. PITCH ANGLE MIN, minimum allowed pitch command. Selections: -90 to 0 degrees.
7. PITCH V ref, specifies voltage for 0° pitch command. Selections: -15.000 to +15.000 volts.
8. ROLL FILTER, specifies the type of roll command filtering algorithm to be used. Selections:
Absolute or Relative.
9. ROLL FILTER TIME, time constant (sec) for filtering applied to roll axis of FD. A higher
value corresponds to a slower response to the analog inputs. Selections: 0.0 to 9.9.
10. ROLL +, positive sense of flight director roll input, Selections: Left or Right.
11. ROLL V/DEG, scaling of flight director roll input. Selections: 0.000 to 9.999
12. ROLL V ref, specifies voltage for 0° pitch command. Selections: -15.750 to +15.750 volts.
NOTE
Ports are selected by activating the cursor and moving it to the desired port.
PORTS Window:
1. ARINC 429, select a port and information received on that port will be displayed on the right.
2. RS-232, select a port and information received on that port will be displayed on the right.
3. RS-485, select a port and information received on that port will be displayed on the right.
The PAUSE soft key is used to pause the data information for viewing. Pressing PAUSE a second
time will resume data streaming.
The CLR LOG soft key is used to clear the information from the log window.
7.2 Installation
The conditions and tests required for TSO authorization of this article are minimum performance
standards. It is the responsibility of those installing this article either on or within a specific type or class
of aircraft to determine that the aircraft installation conditions are within the TSO standards. TSO articles
must have separate approval for installation in an aircraft. The article may be installed only if performed
under 14 CFR Part 43 or the applicable airworthiness requirements.
J6202
J6203
30° MAXIMUM
INSTRUMENT
PANEL
GDU 620
INSTRUMENT
GDU 620 PANEL GDU 620
45° 45°
MAXIMUM MAXIMUM
FORWARD
LINE OF SIGHT
OUTER PERIMETER OF
TEMPLATE IS SAME SIZE
AS GDU 620 BEZEL
RIGHT
10.00
9.600
3.050
6.459 6.70
3.250
CUTOUT PERIMETER
9.459
CUTOUT REPRESENTS
PFD DISPLAY AREA
NOTES:
1. CUTOUT TEMPLATE IS MADE FROM STAINLESS STEEL AND CAN BE USED FOR MULTIPLE
INSTALLATIONS.
2. CUTOUT TEMPLATE SHOULD BE TEMPORARILY AFFIXED TO INSTRUMENT PANEL IN DESIRED
LOCATION PRIOR TO MARKING CUTOUT. THE OUTSIDE EDGES OF THE CUTOUT PATTERN SHOULD
BE USED WHEN MARKING THE CUTOUT ONTO THE INSTRUMENT PANEL.
3. INSTRUMENT PANEL HOLES FOR GDU MOUNTING NUTPLATES SHOULD BE DRILLED USING A #30
(0.1285") DRILL BIT PRIOR TO REMOVAL OF THE TEMPLATE FROM THE INSTRUMENT PANEL. THE
HOLES ARE RESIZED LATER TO THEIR FINAL DIAMETER.
0.80
R0.07
6.30 6.306.46
2X 4.24
3.25
2X 1.74
(0.08)
0.02
9.46 (0.07)
9.60
0.20
0.08
0.07
0.20
DETAIL A
NO SCALE DETAIL D
NO SCALE
(0.08)
0.32 0.23
0.05
107°
R0.12 TYP
DETAIL B (4X)
NO SCALE 0.07
0.20
DETAIL E
0.04 NO SCALE
(Ø0.144) 0.20
0.07
107° (Ø0.144)
R0.69
0.28
0.12
(0.56)
DETAIL C (2X) (0.08)
NO SCALE
0.27
DETAIL F
NO SCALE
EXISTING INSTRUMENT
PANEL CUTOUTS
FOR A THIN TRIM PLATE INSTALLATION:
-LOCATE AND INSTALL ALL NUTPLATES ON THE INSTRUMENT PANEL SO
1) RIVET HEADS ARE FLUSH AND HIDDEN BY TRIM PLATE
2) NUTPLATE BODY DOES NOT INTERFERE WITH ADJACENT INSTRUMENT BODIES
3) NUTPLATE BODY DOES NOT LIE IN CUTOUT OPENING
4) ADEQUATE INSTRUMENT PANEL MATERIAL EXISTS.
-APPLY A FINISH COAT OF PAINT TO PLATE PRIOR TO FINAL INSTALL.
-TRIM PLATE OUTSIDE EDGE AS REQUIRED TO CLEAR ADJACENT INSTRUMENTS OR SWITCHES.
-FINISH CORNERS AT R.25" TYP.
GPS NO. 2 6
GARMIN NAVIGATOR
NOTES:
1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED.
2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND
3. AT GDU 620, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD LEADS MUST BE LESS
THAN 3.0 ". CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS
PRACTICAL.
4. IF ONLY ONE NAVIGATOR IS INSTALLED, WIRE AS SHOWN FOR GPS 1.
5. FOR GDU 620 SETUP ITEMS REFER TO SECTION 5.5
6. IF A TAWS-EQUIPPED 500W SERIES UNIT IS INSTALLED, IT MUST BE CONNECTED AS GPS1 – ONLY TAWS
ANNUNCIATIONS FROM GPS1 ARE DISPLAYED ON THE PFD. IF TWO TAWS-EQUIPPED UNITS ARE INSTALLED, THE
TAWS-EQUIPPED UNIT THAT IS CONNECTED TO THE AUDIO PANEL MUST BE CONNECTED AS GPS1.
7. THE TIME MARK B/- CONNECTION IS NOT REQUIRED FOR THE 400W/500W SERIES UNITS AND SHOULD BE LEFT
UNCONNECTED IN THE INSTALLATION.
8. REFER TO MANUFACTURER’S DOCUMENTATION FOR COMPLETE PIN-OUT AND INTERCONNECT INFORMATION. PIN-
OUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY.
NOTES:
1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED.
2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND
3. ETHERNET PORT 1 MAY BE USED INSTEAD OF PORT 2, OR IF THERE ARE NO FREE ETHERNET PORTS THE
GWX 68 MAY BE CONNECTED TO AN ETHERNET PORT THE GDL 69.
4. USE AIRCRAFT GRADE CATEGORY 5 ETHERNET CABLE. THESE INCLUDE THE FOLLOWING:
MANUFACTURER P/N
PIC WIRE AND CABLE E10422 (22 AWG)
PIC WIRE AND CABLE E10424 (24 AWG)
ELECTRONIC CABLE SPECIALIST 392404 (24 AWG)
NOTE
This feature is currently not implemented. However, provisional wiring for the interface
defined above may be installed.
P6201
TIS/TAS STANDBY* 26 STANDBY / OPERATE
(OPTIONAL) 5
TAS TEST* 27 FUNCTIONAL TEST
TIS SOURCE
TIS SOURCE
GARMIN
(TRANSPONDER)
GTX 33
GTX 330
GDU 620 PFD/MFD
P6203 P3301
7 7
A 4 30 A
ARINC 429 IN 1 ARINC 429 OUT 2
B 26 28 B
s
P6201
TIS/TAS STANDBY* 26 46 TIS CONNECT SELECT
NOTES:
1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED.
2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND
3. AT GDU 620, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD LEADS MUST BE
LESS THAN 3.0 ". CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR
AS PRACTICAL.
4. ONLY ONE TRAFFIC SOURCE MAY BE CONNECTED TO THE GDU 620.
5. THESE OPTIONAL DISCRETE CONNECTIONS ARE NOT REQUIRED IF THE GDU 620 IN IS CONFIGURED FOR
‘SKYWATCH+DISP’. IN THIS CASE, THE GDU 620 WILL NOT CONTROL THE TRAFFIC ADVISORY SYSTEM
OPERATION.
6. GDU 620 MUST BE CONFIGURED FOR TRAFFIC SYSTEM: RYAN TCAD, SKYWATCH OR SKYWATCH+DISP (SEE
NOTE 4).
7. GDU 620 MUST BE CONFIGURED FOR TRAFFIC SYSTEM: GTX 330, AND THE TRAFFIC FUNCTION MUST BE
ENABLED. THE ARINC 429 OUTPUT MUST BE SET TO ‘GARMIN W/TIS’. THE ‘TIS CONNECT SELECT’ DISCRETE
INPUT MAY BE DRIVEN BY MULTIPLE DISPLAY SOURCES.
NOTES:
1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED.
2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND
3. AT GDU 620, GRS 77 AND GDC 74A, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL
-- THE SHIELD LEADS MUST BE LESS THAN 3.0 ".
ARINC 429 IN 6A 9
NAV 2
ARINC 429 IN 6B 26
s
RS-232
PILOT’S GDU 620 6 P6202
NAV 1 RS-232 OUT 5 31
RS-232 IN 5 14
NAV 2 RS-232 GND 5 48 NAV 1 OR NAV 2
s
GARMIN
4 5 7
SL30
COPILOT’S GDU 620 6 37-Pin
P6202
NAV 1 RS-232 OUT 5 31 N/C 4 RXD1
RS-232 IN 5 14 5 TXD1
NAV 2 RS-232 GND 5 48 3 SERIAL GROUND
s
NOTES:
1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED.
2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND
3. AT GDU 620, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD LEADS MUST
BE LESS THAN 3.0 ". CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A
CONDUCTOR AS PRACTICAL, IN ACCORDANCE WITH LRU INSTALLATION INSTRUCTIONS.
4. IF ONLY ONE NAV RECEIVER IS INSTALLED, WIRE AS SHOWN FOR NAV 1.
5. ONLY ONE SL30 MAY BE CONNECTED TO THE GDU 620. IT CAN BE CONFIGURED AS NAV 1, OR AS NAV 2 IF
NAV 1 IS CONFIGURED FOR AN ARINC 429 NAV SOURCE.
6. FOR GDU 620 SETUP ITEMS REFER TO SECTION 5.5.
7. THE SL30 MUST BE CONNECTED AS THE SAME NAVIGATION SOURCE TO BOTH GDU’S (I.E. AS NAV 1 ON
BOTH GDU’S, OR AS NAV 2 ON BOTH GDU’S)