Section 16 GMU 22 (Magnetometer) Installation. Garmin G3X Touch for Experimental Aircraft, GDU 465, GDU 455, G3X, GDU 460, GDU 450

12.5 Outline and Installation Drawings

190-01115-01

Rev. AN

Figure 12-2 GMC 305 Outline Drawing

G3X/G3X Touch Installation Manual - GMC 305 Installation

Page 12-4

190-01115-01

Rev. AN

Figure 12-3 GMC 305 Installation Drawing


Page 12-5

2.69068.33

6X 2.860

3.125

79.38

72.64

00.00

3.12579.38

6X 2.86072.64

2.69068.33

190-01115-01

Rev. AN

Figure 12-4 GMC 305 Cutout Drawing (Not to Scale)


Page 12-6

GMC 305 PANEL CUTOUT

IMPORTANT!

Ensure the Page Scaling setting is set to NONE when printing this page. Verify dimensions of printed template are accurate before cutting panel.

CUT OUT PANEL

TO INSIDE LINE

NOTES:

1.

2.

DIMENSIONS: INCHES[mm]. METRIC VALUES ARE FOR REFERENCE ONLY.

DIMENSIONS ARE NOMINAL AND TOLERANCES ARE NOT IMPLIED UNLESS

SPECIFICALLY STATED.

Figure 12-5 GMC 305 Panel Cutout Template

190-01115-01

Rev. AN


Page 12-7

13 GMC 307 (AFCS MODE CONTROLLER) INSTALLATION

NOTE

References to the GMC Mode Controller throughout this manual apply equally to the

GMC 305, GMC 307, and GMC 507 except where specifically noted.

This section contains general information as well as installation information for the GMC 307. Use this section to mount the GMC 307 unit.

Figure 13-1 GMC 307 Unit View (-00 version shown, -20 version has no YD button)

13.1 Equipment Description

The GMC 307 is a Garmin Automatic Flight Control System (AFCS) Mode Controller that can be used in a G3X installation. The GMC 307 provides a user interface for the autopilot function of the G3X system.

The GMC 307 mounts flush to the aircraft instrument panel using two pawl latches.

13.2 Equipment Available

13.2.1 Required Equipment

Table 13-1 GMC 307 Part Numbers

Model

GMC 307 w/Yaw Damper

GMC 307 no Yaw Damper

Assembly Part

Number

010-01595-00

010-01595-20

Unit Only Part

Number

011-03993-00

011-03993-20

190-01115-01

Rev. AN


Page 13-1

13.2.2 Additional Equipment Required

The following accessories are not provided with the GMC 307 unit. The Installation Kit (Table 13-2) is

required to install the unit.

Table 13-2 Contents of GMC 307 Installation Kit (010-12421-00)

Item

Connector Kit, 15 Pin, Hi Density Male w/Jackscrews

Garmin P/N

011-01824-00

Quantity

1

Table 13-3 Contents of Connector Kit (011-01824-00)

Item

Backshell w/Hdw, Jackscrew, 9/15 Pin

Connector, Male, High Density D-Sub,15 CKT

Contact, Pin, Military Crimp, Size 22D

Garmin P/N

011-01855-00

330-00366-15

336-00021-00

Quantity

1

1

12

13.3 General Specifications

See

Section 2.2

for power/current specifications, and Section 2.4.1

for dimension/weight specifications.

13.4 Mounting and Wiring Requirements

13.4.1 Panel Cutout Template

Figure 13-6

can be used as a template when marking the panel for cutout. Dimensions on the figure are to verify accuracy of printout only, see

Figure 13-5

for complete cutout dimensions. A .dxf version of the drawing is also available for download at https://support.garmin.com/support/manuals .

190-01115-01

Rev. AN


Page 13-2

13.4.2 Unit Installation

Fabrication of a wiring harness is required. Sound mechanical and electrical methods and practices are recommended for installation of the GMC 307. Refer to

Section 2.3

for wiring considerations, and to

Section 26.6

for pinouts.

1. Per Figure 13-2, ensure the pawl latch fasteners are fully retracted and in the vertical position.

2. Hold the unit flush with the instrument panel.

3. Using a 3/32" hex drive tool turn each of the two pawl latches clockwise until tightened to

20 +/-2 in-lbs. When tightened, the pawl latches are in the horizontal position.

CAUTION

To remove the GMC from the instrument panel, turn each of the two pawl latches counterclockwise. After initially breaking the pawl latch loose, continue to loosen while not exceeding 15 in-lbs of torque.

Figure 13-2. Pawl Latch

13.4.3 Wiring

The 15 pin connector, pins, and backshell supplied in the GMC 307 installation kit are used to add wiring for the GMC 307.

It is recommended that a 2 Amp fuse or circuit breaker be used to supply power to the GMC 307

( Figure 27-1.7

). Backup power is optional.

The GMC 307 is connected via RS-232 to any GDU 37X/4XX display ( Figure 27-1.7

). The selected GDU

RS-232 channel must be configured for “Garmin Instrument Data”.

If the installation includes a Garmin integrated autopilot using GSA 28 servos, the GMC 307 installation also includes an RS-232 connection to the GSA 28 roll servo (

Figure 27-1.7

). GMC 307 RS-232 channel 1

must be connected to any one of the available RS-232 channels on one of the GDU 37X/4XX units. The

GMC 307 RS-232 channel 2 must be connected to the GSA 28 roll servo RS-232 channel 1 if this roll servo is installed.

For installations using a non-Garmin autopilot with a GMC 307 controller, refer to Figure 27-2.25

.

190-01115-01

Rev. AN


Page 13-3


190-01115-01

Rev. AN

Figure 13-3 GMC 307 Outline Drawing


Page 13-4

190-01115-01

Rev. AN

Figure 13-4 GMC 307 Installation Drawing


Page 13-5

190-01115-01

Rev. AN

Figure 13-5 GMC 307 Cutout Drawing (Not to Scale)


Page 13-6


IMPORTANT!

ENSURE THE PAGE SCALING SETTING IS SET TO NONE

WHEN PRINTING THIS PAGE. VERIFY DIMENSIONS OF

PRINTED TEMPLATE ARE ACCURATE BEFORE CUTTING

PANEL.

1.98

50.3

6.015 152.78

CUT OUT PANEL

TO INSIDE LINE

BEZEL OUTLINE

(REF.)

NOTES:

1. DIMENSIONS: INCHES [mm]. METRIC VALUES ARE FOR REFERENCE ONLY.

2. TOLERANCES: INCH mm

.XX ±.02 .X ±0.5

.XXX ±.010 .XX ±0.25

Figure 13-6 GMC 307 Panel Cutout Template

190-01115-01

Rev. AN


Page 13-7

14 GMC 507 (AFCS MODE CONTROLLER) INSTALLATION

NOTE

References to the GMC Mode Controller throughout this manual apply equally to the

GMC 305, GMC 307, and GMC 507 except where specifically noted.

This section contains general information as well as installation information for the optional GMC 507.

Use this section to mount the GMC 507 unit.

Figure 14-1 GMC 507 Unit View (-00 version)


The GMC 507 is a Garmin Automatic Flight Control System (AFCS) Mode Controller that can be used in a G3X installation. The GMC 507 provides a user interface for the autopilot function of the G3X system.

The GMC 507 mounts flush to the aircraft instrument panel using two pawl latches or may be mounted in the radio stack using the optional mounting rack listed in Table 14-3 .

14.1.1 Equipment Available

The GMC 507 is available by the part numbers listed in Table 14-1.

GMC 507

LRU

Table 14-1 Available LRU Part Numbers

Assembly Part Number

010-01946-00

Unit Only Part Number

011-04548-00

14.1.2 Additional Equipment Required

The following accessories are not provided with the GMC 507 unit. The Connector Kit (Table 14-2) is required to install the unit.

Table 14-2 Contents of Connector Kit (011-01824-01)

Item

Backshell w/Hdw, Jackscrew, 9/15 Pin

Connector, Male, High Density D-Sub,15 CKT

Contact, Pin, Military Crimp, Size 22D

Garmin P/N

011-01855-00

330-00366-15

336-00021-00

Quantity

1

1

15

190-01115-01

Rev. AN


Page 14-1

14.1.3 Optional Equipment

Table 14-3 GMC 507 Installation Rack Kit (010-12700-10)

GMC 507 Installation Rack

Item Garmin P/N

115-02774-00

Quantity

1


See

Section 2.2



14.3 Mounting and Wiring Requirements

14.3.1 Panel Cutout Template

Figure 14-6 can be used as a template when marking the panel for cutout. Dimensions on the figure are to verify accuracy of printout only, see

Figure 14-5

for complete cutout dimensions. A .dxf version of the drawing is also available for download at https://support.garmin.com/support/manuals .

CAUTION

Exercise caution when installing the rack in the instrument panel. Deformation of the rack will make it difficult to install and remove the GMC 507.

NOTE

If the front edges of the installation rack are behind the front surface of the aircraft panel, the GMC 507 pawl latches may not fully engage.

NOTE

The GMC 507 install rack may be used as a template for drilling the mounting holes.

14.3.2 Unit Installation

Fabrication of a wiring harness is required. Sound mechanical and electrical methods and practices are recommended for installation of the GMC 507. Refer to

Section 2.3

for wiring considerations, and to

Section 26.9

for pinouts.

14.3.2.1 Panel Cutout Installation

1. Per Figure 14-2, ensure the pawl latch fasteners are fully retracted and in the vertical position.

2. Insert the unit into the instrument panel cutout so that the backside of the bezel rests against the instrument panel. Orient the install rack as shown in

Figure 14-8

.


20 +/-2 in-lbs. When tightened, the pawl latches are in the horizontal position (see Figure 14-2 ).

190-01115-01

Rev. AN


Page 14-2

14.3.2.2 Radio Stack Installation

The GMC 507 Install Rack (115-02774-00) is to be used when installing the GMC 507 unit into a radio

stack. Figure 14-9 shows the various radio stack cutout configurations that will accommodate the Install

Rack.

1. Ensure the left and right front edges of the install rack are flush with the front surface of the instrument panel.

2. Secure the install rack to a rigid, primary aircraft structure using (qty. 4) #6 100° flat head machine

screws as noted in Figure 14-7 . The screws are inserted from the inside of the installation rack and

may be secured using self-locking hex nuts on the outside.

3. With the pawl latch fasteners retracted, insert the GMC 507 into the Install Rack until the bezel contacts the front edges of the Install Rack.


20 +/-2 in-lbs. When tightened, the pawl latches are in the horizontal position (see Figure 14-2).

CAUTION

To remove the GMC from the instrument panel, turn each of the two pawl latches counterclockwise. After initially breaking the pawl latch loose, continue to loosen while not exceeding 15 in-lbs of torque.

Figure 14-2. Pawl Latch

14.3.3 Wiring

The 15 pin connector, pins, and backshell supplied in the GMC 507 installation kit are used to add wiring for the GMC 507.

See

Figure 27-1.8

for example interconnect drawing.

190-01115-01

Rev. AN


Page 14-3


190-01115-01

Rev. AN

Figure 14-3 GMC 507 Outline Drawing (no installation rack)


Page 14-4

190-01115-01

Rev. AN

Figure 14-4 GMC 507 Installation Drawing (no installation rack)


Page 14-5

Figure 14-5 GMC 507 Cutout Drawing, No Installation Rack (Not to Scale)

190-01115-01

Rev. AN


Page 14-6


IMPORTANT!

ENSURE THE PAGE SCALING SETTING IS SET TO NONE

WHEN PRINTING THIS PAGE. VERIFY DIMENSIONS OF

PRINTED TEMPLATE ARE ACCURATE BEFORE CUTTING

PANEL.

1.930 49.0

CUT OUT PANEL

TO INSIDE LINE

6.020

152.9

BEZEL OUTLINE

(REF.)

NOTES:

1. DIMENSIONS: INCHES [mm]. METRIC VALUES ARE FOR REFERENCE ONLY.

2. TOLERANCES: INCH mm

.XX ±.02 .X ±0.5

.XXX ±.010 .XX ±0.25

Figure 14-6 GMC 507 Panel Cutout Template (no installation rack)

190-01115-01

Rev. AN


Page 14-7

190-01115-01

Rev. AN

Figure 14-7 GMC 507 Outline Drawing with Installation Rack


Page 14-8

190-01115-01

Rev. AN

Figure 14-8 GMC 507 Installation Drawing with Installation Rack


Page 14-9

Figure 14-9 GMC 507 Panel Cutout Template for Installation with Installation Rack

190-01115-01

Rev. AN


Page 14-10

15 GMU 11 (MAGNETOMETER) INSTALLATION

This section contains general information as well as installation information for the GMU 11. Use this section to mount the GMU 11 unit.

Figure 15-1 GMU 11 Unit View


The GMU 11 magnetometer is a remote mounted device that provides magnetometer data to a Garmin

GSU 25 ADAHRS. The Garmin ADAHRS and magnetometer replace traditional rotating mass instruments.

An Attitude and Heading Reference System combines the functions of a Vertical Gyro and a Directional

Gyro to provide measurement of Roll, Pitch, and Heading angles. The Garmin ADAHRS and magnetometer replace traditional rotating mass instruments.

Using long-life solid-state sensing technology, the GMU 11 Magnetometer uses magnetic field measurements to create an electronically stabilized AHRS.

The GMU 11 magnetometer provides magnetic information to support the function of the ADAHRS

(GSU 25). The supply voltage for the GMU 11 Magnetometer comes from aircraft power (9-32 V

100mA.)

NOTE

The GSU 73 is not compatible with the GMU 11 magnetometer. Installations that include a

GSU 73 must also include a GMU 22 connected to the GSU 73.


See

Section 2.2



190-01115-01

Rev. AN

G3X/G3X Touch Installation Manual - GMU 11 Installation

Page 15-1


Model

GMU 11

Table 15-1 GMU 11 Part Numbers

Assembly Part

Number

010-01788-00

Unit Only Part

Number

011-04349-00

GMU 11, Installation Kit

Item

Table 15-2 GMU 11 Accessories

Garmin P/N

011-04349-90

Installation Rack

No

Quantity

1

Table 15-3 Contents of GMU 11 Installation Kit (011-04349-90)

Item

Connector Kit, 9 Pin, w/CAN Term

Nut, Hex, Nyl Locking, 316SS/P, 6-32

Screw, 6-32x.500, PHP, SS/P

Washer, Flat, SAE, SS, #6

Garmin P/N

011-03002-00

210-10008-08

211-60207-12

212-00024-06

Quantity

1

4

4

4

15.4 Unit Installation

The following guidelines describe proper mechanical installation of the Garmin GMU 11 Magnetometer.

The guidelines include requirements for proper location selection in the aircraft, requirements for supporting structure and mechanical alignment and restriction on nearby equipment.

Fabrication of a wiring harness is required. Sound mechanical and electrical methods and practices are required for installation of the GMU 11. Refer to

Section 2.3

for wiring considerations and to Section 26.8

for pinouts.

The GMU 11 is an extremely sensitive three-axis magnetic sensor. It is more sensitive to nearby magnetic disturbances than a flux gate magnetometer. For this reason, when choosing a mounting location for the

GMU 11, observe the following distances from objects or devices that can disturb the magnetic field.

Table 15-4 specifies recommended distances from magnetic disturbances for GMU 11 location.

NOTE

If the requirements listed in

Table 15-4 cannot be met, a magnetometer interference test

must be performed to ensure proper operation of the G3X system. Refer to the AHRS/

Magnetometer Installation Considerations document (190-01051-00) available from the

Garmin website ( www.garmin.com

) .

190-01115-01

Rev. AN


Page 15-2

Table 15-4 Recommended Distance from Magnetic Disturbances

Disturbance Source*

Minimum Distance from GMU 11

10 feet (3.0 meters) Electric motors and relays, including servo motors

Ferromagnetic structure greater than 1 kg total (iron, steel, or cobalt materials, especially landing gear structure)

Ferromagnetic materials less than 1 kg total, such as control cables

Any electrical device drawing more than 100 mA current

Electrical conductors passing more than 100 mA current [(should be twisted shielded pair if within 10 feet (3.0 meters)]

Electrical devices drawing less than 100 mA current

Magnetic measuring device other than another GMU 11 (e.g. installed flux gates, even if not powered)

Electrical conductors passing less than 100 mA current [(should be twisted shielded pair if within 10 feet (3.0 meters)]

*Disturbance sources listed in table do not apply to a second installed GMU 11

8.2 feet (2.5 meters)

3 feet (1.0 meter)

3 feet (1.0 meter)

3 feet (1.0 meter)

2 feet (0.6 meter)

2 feet (0.6 meter)

1.3 feet (0.4 meter)

Ensure that any electrical conductor that comes within 10 feet (3.0 meters) of the GMU 11 is installed as a twisted shielded pair, not a single-wire conductor. (If possible, the shield should be grounded at both ends.)

Use nonmagnetic materials to mount the GMU 11, and replace any magnetic fasteners within 0.5 meter with nonmagnetic equivalents (e.g. replace zinc-plated steel screws used to mount wing covers or wing tips with nonmagnetic stainless steel screws).

In general, wing mounting of the GMU 11 magnetometer is preferred (unless as noted in

Appendix B ).

Fuselage mounting is less desirable because of numerous potential disturbances that interfere with accurate operation. For installations with dual GMU 11 magnetometers, co-locating the two magnetometers close to each other in the tail or in one wing is recommended as this reduces the likelihood of heading splits or miscompares when operating on the ground in the vicinity of local magnetic anomalies.

Mechanical mounting fixtures for the GMU 11 must be rigidly connected to the aircraft structure. Use of typical aircraft-grade non-magnetic materials and methods for rigid mounting of components is acceptable, so long as adequate measures are taken to ensure a stiffened mounting structure.

Level the GMU 11 to within 3.0° of the in-flight level cruise attitude.

Per Figure 15-4

, align the GMU 11’s forward direction to within 0.5° of the any of the 4 cardinal directions with relation between its connector and the nose of the aircraft. Make sure that the bottom of the unit is facing downwards (towards earth) per

Figure 15-4

.

190-01115-01

Rev. AN


Page 15-3

15.4.1 Consideration for Wing Grounded Lighting Fixtures

The following installation practices are recommended if the GMU 11 is mounted in the wing.

The wing tip lights should not have a power ground referenced to the chassis of the light assembly that would then be referenced back to the airframe ground via the light assembly mounting.

A dedicated power ground should be used and returned as a twisted pair with the power source back into the fuselage for a wing mounted GMU 11.

These installation practices will prevent magnetically interfering currents from flowing in the wing skin that encloses the GMU 11. Electrically isolating the light assembly should not be used as an alternative to the preceding consideration, unless the isolated light assembly has been analyzed for adequate protection against direct attachment of lightning.

Refer to

Section 15.5

for outline and installation drawings.

15.4.2 Mounting Instructions

After evaluation of the mounting location has been completed and ensuring that requirements are met, install the unit assemblies.

Mount the GMU 11 in its mounting location, taking care to tighten the mounting screws firmly. Use of non-magnetic tools (e.g. beryllium copper or titanium) is recommended when installing or servicing the

GMU 11. Do not use a screwdriver that contains a magnet when installing or servicing the GMU 11.

Refer to

Section 15.5


190-01115-01

Rev. AN


Page 15-4


2.74

2.28

1.37

0.93

0.38

190-01115-01

Rev. AN

Figure 15-2 GMU 11 Outline Drawing


Page 15-5

190-01115-01

Rev. AN

Figure 15-3 GMU 11 Installation Drawing


Page 15-6

190-01115-01

Rev. AN

Figure 15-4 GMU 11 Orientation Drawing


Page 15-7

16 GMU 22 (MAGNETOMETER) INSTALLATION

NOTE

All GMU 22 information in this Installation Manual also applies to the GMU 44, which had previously been the G3X magnetometer but has been replaced by the GMU 22.

This section contains general information as well as installation information for the GMU 22. Use this section to mount the GMU 22 unit. Installers may also benefit from studying

Appendix B , which provides

guidance for installing the GMU 22 into specific experimental airframes.

Figure 16-1 GMU 22 Unit View


The GMU 22 magnetometer is a remote mounted device that provides magnetometer data to Garmin

ADAHRS devices (GSU 25/73). The Garmin ADAHRS and magnetometer replace traditional rotating mass instruments.

An Attitude and Heading Reference System combines the functions of a Vertical Gyro and a Directional

Gyro to provide measurement of Roll, Pitch, and Heading angles. The Garmin ADAHRS and magnetometer replace traditional rotating mass instruments.

Using long-life solid-state sensing technology, the GMU 22 Magnetometer uses magnetic field measurements to create an electronically stabilized AHRS.

The GMU 22 magnetometer provides magnetic information to support the function of the ADAHRS

(GSU 25/73). The ADAHRS (GSU 25/73) provides operating voltage to the GMU 22 Magnetometer.

16.1.1 Interface Summary

The following is an interface summary for the GMU 22:

• GMU 22 to ADAHRS (GSU 25/73) Interface: Power, RS-232, RS-485 (19,200 baud)


See

Section 2.2



190-01115-01

Rev. AN


Page 16-1


Model

GMU 22

Table 16-1 GMU 22 Part Numbers

Assembly Part

Number

010-01196-00

Unit Only Part

Number

011-03269-00

Installation Rack

No

Table 16-2 GMU 22 Accessories

GMU 22, Connector Kit

GMU 22 Universal Mount*

Item Garmin P/N

011-00871-10

011-01779-01

Quantity

1

1 (optional)

Installation Rack, GMU 22 115-00481-10 1

*Refer to AHRS Magnetometer Installation Considerations (190-01051-00) from www.garmin.com

Table 16-3 Contents of GMU 22 Connector Kit (011-00871-10)

Item

Modified Install Rack

Screw, 6-32x .250, Pan Head Phillips, Brass, w/Nylon

Circular Connector, Female, 9 Ckt

Circular non-Magnetic Backshell

Socket Contact Mil Crp, Size 20

Garmin P/N

115-00481-10

211-60037-08

330-00360-00

330-90005-01

336-00022-00

Quantity

1

3

1

1

10

16.4 Unit Installation

The following guidelines describe proper mechanical installation of the Garmin GMU 22 Magnetometer.

The guidelines include requirements for proper location selection in the aircraft, requirements for supporting structure and mechanical alignment and restriction on nearby equipment.

Fabrication of a wiring harness is required. Sound mechanical and electrical methods and practices are required for installation of the GMU 22. Refer to

Section 2.3

for wiring considerations and to Section 26.8

for pinouts.

The GMU 22 is an extremely sensitive three-axis magnetic sensor. It is more sensitive to nearby magnetic disturbances than a flux gate magnetometer. For this reason, when choosing a mounting location for the

GMU 22, observe the following distances from objects or devices that can disturb the magnetic field.

Table 16-4 specifies recommended distances from magnetic disturbances for GMU 22 location.

NOTE

If the requirements listed in

Table 16-4 cannot be met, a magnetometer interference test

must be performed to ensure proper operation of the G3X system. Refer to the AHRS/

Magnetometer Installation Considerations document (190-01051-00) available from the

Garmin website ( www.garmin.com

) .

190-01115-01

Rev. AN


Page 16-2

Table 16-4 Recommended Distance from Magnetic Disturbances

Disturbance Source*

Minimum Distance from GMU 22

10 feet (3.0 meters) Electric motors and relays, including servo motors

Ferromagnetic structure greater than 1 kg total (iron, steel, or cobalt materials, especially landing gear structure)

Ferromagnetic materials less than 1 kg total, such as control cables

Any electrical device drawing more than 100 mA current

Electrical conductors passing more than 100 mA current [(should be twisted shielded pair if within 10 feet (3.0 meters)]

Electrical devices drawing less than 100 mA current

Magnetic measuring device other than another GMU 22 (e.g. installed flux gates, even if unpowered)

Electrical conductors passing less than 100 mA current [(should be twisted shielded pair if within 10 feet (3.0 meters)]

*Disturbance sources listed in table do not apply to a second installed GMU 22

8.2 feet (2.5 meters)

3 feet (1.0 meter)

3 feet (1.0 meter)

3 feet (1.0 meter)

2 feet (0.6 meter)

2 feet (0.6 meter)

1.3 feet (0.4 meter)

Ensure that any electrical conductor that comes within 10 feet (3.0 meters) of the GMU 22 is installed as a twisted shielded pair, not a single-wire conductor. (If possible, the shield should be grounded at both ends.)

Use nonmagnetic materials to mount the GMU 22, and replace any magnetic fasteners within 0.5 meter with nonmagnetic equivalents (e.g. replace zinc-plated steel screws used to mount wing covers or wing tips with nonmagnetic stainless steel screws).

In general, wing mounting of the GMU 22 magnetometer is preferred (unless as noted in

Appendix B ).

Fuselage mounting is less desirable because of numerous potential disturbances that interfere with accurate operation. For installations with dual GMU 22 magnetometers, co-locating the two magnetometers close to each other in the tail or in one wing is recommended as this reduces the likelihood of heading splits or miscompares when operating on the ground in the vicinity of local magnetic anomalies.

Mechanical mounting fixtures for the GMU 22 must be rigidly connected to the aircraft structure. Use of typical aircraft-grade materials and methods for rigid mounting of components is acceptable, so long as adequate measures are taken to ensure a stiffened mounting structure.

Level the GMU 22 mounting rack to within 3.0° of the in-flight level cruise attitude.

Align the GMU 22 mounting rack’s forward direction to within 0.5° of the longitudinal axis of the aircraft.

In a system with more than one ADAHRS (GSU 25/73), ADAHRS 1 must be connected to a GMU22, but installing additional GMU 22 units for other GSU 25 ADAHRS units is optional. An ADAHRS without a

GMU 22 connected will use magnetometer data supplied by other ADAHRS as long as they are both communicating via CAN.

190-01115-01

Rev. AN


Page 16-3

16.4.1 Consideration for Wing Grounded Lighting Fixtures

The following installation practices are recommended if the required GMU 22 mounting bracket is located in the wing.

The wing tip lights should not have a power ground referenced to the chassis of the light assembly that would then be referenced back to the airframe ground via the light assembly mounting.

A dedicated power ground should be used and returned as a twisted pair with the power source back into the fuselage for a wing mounted GMU 22.

These installation practices will prevent magnetically interfering currents from flowing in the wing skin that encloses the GMU 22. Electrically isolating the light assembly should not be used as an alternative to item 1 above, unless the isolated light assembly has been analyzed for adequate protection against direct attachment of lightning.

Refer to

Section 16.5


16.4.2 ADAHRS (GSU 25/73) to GMU 22 Interconnect Harness Fabrication Instructions

Table 16-5 lists parts needed for the GMU 22 interconnect harness. Some of the parts for installation are

included in the GMU 22 Connector Installation Kit. Other parts are provided by the installer. Reference

numbers refer to item bubble numbers shown in Figure 16-7 .

Table 16-5 Parts Needed for GMU 22 Installation

Figure D-2.4 Ref

1

2

3, 4, 9

Description

Shield Termination

(method optional)

Shield Extension Wire

GMU 22 Connector Kit*

Qty. Included

5

6

3-Conductor Cable

2-Conductor Cable

*Included in G3X w/GSU 73 Installation Kit (K10-00017-00)

0

0

0

0

1

GPN or MIL Spec

Parts used depend on method chosen

M22759/16-22

011-00871-00

M27500-22TE3T14

M27500-22TE2T14

Table 16-6 lists material in the GMU 22 connector kit and the associated reference number, as shown in

Figure 16-7 . The GMU 22 magnetometer has an attached pigtail with male polarity. The harness connector

for the GMU 22 has female polarity.

Table 16-6 GMU 22 Connector Kit (011-00871-00)** Contents, Reference

Figure 16-7

Item

Screw,6-32x.250,PHP,BR,w/Nyl

Conn,Circular,Female,9 Ckt

Backshell,Circular,Kit,SS

Garmin P/N

211-60037-08

330-00360-00

330-90005-01

Cont,Sckt,Mil Crp,Size 20 336-00022-00

**Included in G3X w/GSU 73 Installation Kit (K10-00017-00)

Quantity

3

1

1

10

Figure 16-7

Ref

9

4

4

3

190-01115-01

Rev. AN


Page 16-4

16.4.3 Mounting Instructions

After evaluation of the mounting location has been completed and ensuring that requirements are met, assemble the GMU 22 mounting plate kits according to the dimensions given in

Figure 16-3 . Install the

unit assemblies.

Mount the GMU 22 to its mounting plate, taking care to tighten the mounting screws firmly. Use of nonmagnetic tools (e.g. beryllium copper or titanium) is recommended when installing or servicing the

GMU 22. Do not use a screwdriver that contains a magnet when installing or servicing the GMU 22.

The metal components in the GMU 22 connector may slightly affect the magnetic field sensed by the

GMU 22. Place the connector at least 2 inches from the body of the GMU 22 to minimize this effect. After attaching the GMU 22's connector to its mate in the aircraft wiring, secure the connector in place using good installation practices. This will ensure that any remaining magnetic effect can be compensated for

using the Magnetometer Calibration ( Section 34.4.4.3

for GDU 37X systems and

Section 34.4.4.3

for

GDU 4XX systems).

See Figure 16-2 for minimum recommended clearance for bend radius of the GMU 22 cable.

NOTE

If the GMU 22 is ever removed, the anti-rotation properties of the mounting screws must be restored. This may be done by replacing the screws with new Garmin part number

211 60037 08. If original screws must be re-used, coat screw threads with Loctite 242

(blue) thread-locking compound, Garmin part number 291 00023 02, or equivalent.

Important: Mounting screws must be brass.

MINIMUM RECOMMENDED CLEARANCE

FOR MINIMUM BEND RADIUS OF THE

GMU 22 CABLE IS 1.57[40] FROM THE

GMU 22 SURFACE

1.57 40

190-01115-01

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Figure 16-2 GMU 22 Minimum Recommended Clearance


Page 16-5


0

1.54

.061

65.33

63.79

2.511

2.572

31.90

1.256

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Figure 16-3 GMU 22 Mounting Rack (115-00481-00)


Page 16-6

190-01115-01

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Figure 16-4 GMU 22 Mounting Rack (115-00481-10)


Page 16-7

190-01115-01

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Figure 16-5 GMU 22 Top Mounted Installation


Page 16-8

190-01115-01

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Figure 16-6 GMU 22 Bottom Mounted Installation


Page 16-9

NOTE:

1. BUBBLE NUMBERS IN THIS DRAWING REFER TO

REFERENCE NUMBERS LISTED IN TABLES 13-5 AND 13-6.

190-01115-01

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Figure 16-7 GMU 22 Wiring Details


Page 16-10

17 GPS 20A (WAAS GPS POSITION SOURCE) INSTALLATION

This section contains general information as well as installation information for the GPS 20A. Use this section to mount the GPS 20A unit.

NOTE

The GPS 20A can only be used with GA 35, GA 36, or GA 37 antennas.

,

GPS STATUS LED

UNIT STATUS LED

J201

Figure 17-1 GPS 20A Unit View


The GPS 20A provides an ADS-B Out position source. The WAAS/SBAS position information is compatible with a wide range of 1090 ES transponders to meet the position requirements of

14 CFR 91.227. The GPS 20A also provides position data to all G3X and G3X Touch displays.

NOTE

If a GPS 20A (and connected GA 35, GA 36, or GA 37 antenna) is used for GPS position, additional GPS antennas (connected to GDU 37X/4XX units) may be used for redundancy, but are not required.

NOTE

The GPS 20A is not an FAA-approved product and thus is not eligible for installation in certified aircraft.

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G3X/G3X Touch Installation Manual - GPS 20A Installation

Page 17-1

17.1.1 Status LED

The GPS 20A has two LEDs on its outer case that indicate its current unit and GPS status (

Figure 17-1 ).

The unit status LED is in the middle of the outer case between the coax and 9 pin connectors. See

Section

36.1.1

for details.

The GPS status LED is on the edge of the outer case, to the left of the coax connector. Table 17-1 lists the

GPS status indications.

Table 17-1 GPS Status LED Indications

Red

LED Indication

No Light

Slow Flashing Green

Fast Flashing Green

Steady Green

Alternating Red/Green

Description

GPS hardware failure

GPS acquiring, low signal to noise ratio or antenna not connected

GPS acquiring, good signal to noise ratio

GPS fix acquired

GPS WAAS fix acquired

CAN bus network error, two similar devices are configured with same unit ID

17.2 Statement of Compliance (per AC 90-114A CHG1)

The Garmin GPS 20A, while not TSO approved, meets the ADS-B Out position source performance requirements for FAR 91.227 compliance when used in combination with a Mode S ADS-B Out transponder meeting the requirements of TSO-C166b and installed in accordance with the instructions in this document. Example transponders which may be used in combination with the GPS 20A for FAR

91.227 compliance are the Garmin GTX 330ES, GTX 23ES, GTX 35R, GTX 45R, GTX 345/345R, and

GTX 335/335R.


17.3.1 Required Equipment

Model

GPS 20A

Table 17-2 GPS 20A Part Numbers

Assembly Part

Number

010-01546-00

Unit Only Part

Number

011-03913-00

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G3X/G3X Touch Installation Manual - GPS 20A Installation

Page 17-2

Section 16 GMU 22 (Magnetometer) Installation. Garmin G3X Touch for Experimental Aircraft, GDU 465, GDU 455, G3X, GDU 460, GDU 450

13 GMC 307 (AFCS MODE CONTROLLER) INSTALLATION

14 GMC 507 (AFCS MODE CONTROLLER) INSTALLATION

15 GMU 11 (MAGNETOMETER) INSTALLATION

16 GMU 22 (MAGNETOMETER) INSTALLATION

17 GPS 20A (WAAS GPS POSITION SOURCE) INSTALLATION

Related manuals

Table of contents

Section 16 GMU 22 (Magnetometer) Installation. Garmin G3X Touch for Experimental Aircraft, GDU 465, GDU 455, G3X, GDU 460, GDU 450

13 GMC 307 (AFCS MODE CONTROLLER) INSTALLATION

14 GMC 507 (AFCS MODE CONTROLLER) INSTALLATION

15 GMU 11 (MAGNETOMETER) INSTALLATION

16 GMU 22 (MAGNETOMETER) INSTALLATION

17 GPS 20A (WAAS GPS POSITION SOURCE) INSTALLATION

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FPRU19F8WF

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Table of contents