Garmin STC Instruction Manual
Rev.
Date
Description of Change
E
12/23/09
Update referenced publications and revision procedures
Updated referenced publications. Clarified periodic maintenance
instructions. Added new special inspection requirements.
Update referenced IM. Specify overbraid, bonding strap, foil, corrosion
Include GDC 74( ). TVS replace required after lightning.
Remove “FAA Approved” language. Update IM rev. Add additional
instructions for Mid-Continent standby attitude indicator installations.
Added GAD 43e. Removed reference to Pilot’s Guide. Revised lightning
strike inspection.
K
09/30/13
Added RVSM support for TBM700(850).
G600 PFD/MFD System
Instructions for Continued Airworthiness
as installed in
_____________________________
(Make and Model Airplane)
Reg. No.____________ S/N_______________
Dwg. Number:
190-00601-00 Rev. K
Garmin International, Inc.
1200 E. 151st Street
Olathe, Kansas 66062 USA
Record of Revision
F 12/16/10
G 03/21/11
H 08/31/11
J 10/12/12
inspections; periodic bonding test. Clarify TVS test. Foil check annual.
1. INTRODUCTION ................................................................................................................... 3
1.1 Purpose ................................................................................................................. 3
1.2 Scope .................................................................................................................... 3
1.3 Document Control ................................................................................................. 3
1.4 Airworthiness Limitations Section ......................................................................... 3
1.5 Permission to Use Certain Documents ................................................................. 3
1.6 Definitions ............................................................................................................. 3
2. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS .................................................... 4
2.1 Introduction ........................................................................................................... 4
2.2 Description of Alteration ........................................................................................ 4
2.3 Control, Operating Information ............................................................................. 4
2.4 Servicing Information ............................................................................................ 5
2.5 Periodic Maintenance Instructions ........................................................................ 6
2.6 Troubleshooting Information ................................................................................. 9
2.7 Removal and Replacement Information ............................................................... 9
2.8 Diagrams............................................................................................................... 9
2.9 Special Inspection Requirements ......................................................................... 9
2.10 Application of Protective Treatments .................................................................... 10
2.11 Data Relative to Structural Fastener s ................................................................... 10
2.12 Special Tools ........................................................................................................ 10
2.13 Additional Instructions ........................................................................................... 10
2.14 Overhaul Period .................................................................................................... 10
2.15 ICA Revision and Distribution ............................................................................... 10
2.16 Assistance............................................................................................................. 11
2.17 Implementation and Record Keeping ................................................................... 11
3. APPENDIX A ......................................................................................................................... 12
3.1 LRU Locations ...................................................................................................... 12
3.2 Wire Routing – Single-Engine .............................................................................. 13
3.3 Wire Routing – Twin-Engine ................................................................................. 14
G600 PFD/MFD System 190-00601-00 Rev. K
Instructions for Continued Airworthiness Page 2 of 14
1. INTRODUCTION
1.1 Purpose
This document is designed for use by the installing agency of the Garmin G600 PFD/MFD System as
Instructions for Continued Airworthiness in response to Federal Aviation regulation (FAR) Part 23.1529,
and Part 23 Appendix G. This ICA includes information required by the operator to adequately maintain
the Garmin G600 system installed under Approved Model List (AML) STC.
1.2 Scope
This document identifies the Instruction for Continued Airworthiness for the modification of the aircraft for
installation of the Garmin G600 PFD/MFD System installed under Approved Model List (AML) STC.
1.3 Document Control
This document shall be released, archived, and controlled in accordance with the Garmin document
control system. When this document is revised, refer to Section 2.15 for information on how to gain FAA
acceptance or approval and how to notify customers of changes.
1.4 Airworthiness Limitations Section
There are no addition al Air wor thi nes s Lim itati ons as defined in 14 CFR § 23, Appendix G. G23.4 that
result from this modification. 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.
1.5 Permission to Use Certain Documents
Permission is granted to any corporation or person applying for approval of a Garmin G600 system to
use and reference appropriate STC documents to accomplish the Instructions for Continued
Airworthiness and show compliance with STC engineering data. This permission does not construe
suitability of the documents. It is the responsibility of the applicant to determine the suitability of the
documents for the ICA.
1.6 Definitions
The following terminology is used within this document:
1) AC: Advisory Circular
2) ACO: Aircraft Certification Office
3) ADC: Air Data Computer
4) AEG: Aircraft Evaluation Group
5) AHRS: Attitude Heading Reference System
6) CFR: Code of Federal Regulations
7) FAA: Federal Aviation Administration
8) ICA: Instructions for Continued Airworthiness
9) MFD: Multi-Function Display
10) PFD: Primary Flight Display
11) PMI: Primary Manufacturing Inspector
12) RVSM: Reduced Ver t ical S eparation Minima
13) STC: Supplemental Type Certificate
14) TSO: Technic al Sta ndard O rder
15) TVS: Transient Voltage Suppressor
G600 PFD/MFD System 190-00601-00 Rev. K
Instructions for Continued Airworthiness Page 3 of 14
2. INSTRUCTIONS FOR CONTI NUED AIRWORT HINES S
2.1 Introduction
Content, Scope, Purpose and Arrangement: This document identifies the Instructions for
Continued Airworthiness for the modification of the
aircraft by installation of the Garmin G600
PFD/MFD System.
Applicability: Applies to aircraft altered by installation of the
Garmin G600 PFD/MFD System.
Definition of Abbreviations: See Section 1.6
Precautions: None
Units of measurement: None
Referenced publications:
Retention: This document, or the information contained within,
Garmin 190-00601-06 Rev. L “G600 AML STC
Installation Manual” or later revisions
will be included in the aircraft’s permanent records.
2.2 Description of Alteration
The Garmin G600 PFD/MFD System is a combination of Garmin LRUs designed to provide both a PFD
and MFD in the primary field of view. The system consists of a GDU 620 display, GRS 77 AHRS, GDC
74( ) ADC, GMU 44 magnetometer, and GTP 59 outside air temperature probe. This modification may
also include a Garmin GAD 43/43e Adapter and/or Mid Continent Instruments attitude indicator (models
4300-4( ), or 4200-( ) with MD42 0). Installation of the Garmin G600 system, specific for the aircraft
installation, is documented in the G600 AML STC Installation Manual.
2.3 Control, Operating Information
The GDU 620, GRS 77, GMU 44, and GDC 74( ) are powered by an electrical bus which is normally
energized with battery, generator, or external power applied to the aircraft. The GAD 43/43e is typically
powered by an avionics bus which is normally controlled by the avionics bus power switch. The LRUs
do not have individual power switches and are powered when the bus is energized and the circuit
breakers are closed. The following circuit breakers provide power to the individual LRUs:
• PFD: GDU 620
• AHRS: GRS 77 #1 and GMU 44 #1
• ADC: GDC 74( )
• GAD: GAD 43/43e
In a dual G600 installation, the PFD, AHRS, and ADC circuit breakers are suffixed with the numbers 1
and 2 (i.e. PFD 1 and PFD 2). If an LRU is optionally powered from multiple circuit breakers, then the
circuit breakers will be suffixed with the letters A and B (i.e PFD 1A and PFD 1B).
The GDU 620 has a PFD and MFD display and front panel controls for performing all G600 normal and
configuration operations. Knobs at the lower left and right corners are used for selecting and entering
data on each screen. The function of the soft keys along the bottom of the display is depicted by the text
above the key. There are dedicated ENT, CLR, and MENU keys on the MFD side of the unit.
G600 PFD/MFD System 190-00601-00 Rev. K
Instructions for Continued Airworthiness Page 4 of 14
Turning the PFD knob adjusts the values for the mode selected by the PFD bezel keys, such as,
Heading (HDG), Course (CRS), Altitude (ALT), Vertical Speed (V/S), and Barometric Setting (BARO).
The values are shown in a window to the left of the HSI. Pressing the PFD knob reverts to the default
value of the selected mode.
The Small (Inner) MFD Knob selects a specific page within a page group. Pressing the small MFD knob
turns the selection cursor ON and OFF. When the cursor is ON, data may be entered in the applicable
window by turning the small and large MFD knobs. In this case, the large MFD knob moves the cursor
on the page and the small MFD knob selects individual characters or values for the highlighted cursor
location. The Large (Outer) MFD Knob selects the MFD page group. When the cursor is ON, the large
MFD knob moves the cursor to highlight available fields.
The G600 system starts in normal mode when power is applied to the LRUs. After completing the selftest, the database confirmation page is displayed. Invalid or expired databases are displayed in yellow.
Press ENT to proceed to normal mode. Normal mode consists of a Primary Flight Display (PFD) on one
screen and a Multifunction Display (MFD) on the other screen. The AHRS alignment should complete
within one minute and attitude should be displayed on the PFD. System alerts are accessible via an
“ALERTS” softkey at the lower right of the MFD. During normal system operation with all aircraft
systems and avionics powered there should not be any red Xs or system alerts on the GDU 620.
To enter into Configuration Mode for the G600 system, verify that the GDU 620 is off and an Installer
Unlock Card is inserted in the SD card slot of the GDU 620. Apply power to the GDU 620 while holding
the ENT key. Release the ENT key when “INITIALIZING SYSTEM” appears in the upper left corner of
the display.
Refer to the G600 AML STC Installation Manual for further configuration instructions.
2.4 Servicing Information
None. In the event of system failure, troubleshoot the G600 system in accordance with Section 2.6
Troubleshooting Information.
If the Mid-Continent Instruments 4300-4XX Electric Attitude Indicator or MD420 battery pack is installed,
the battery or batteries may be charged by one of the following methods:
1. Keep the battery or batteries plugged into the Attitude Indicator or Battery Module. Apply power
to the aircraft and run the unit overnight (approx. 15 hours) at the rated voltage.
2. Float Charging: Disconnect the battery or batteries from the indicator or module. Connect the
battery or batteries to a constant voltage source (battery plug (pin 1) red wire = positive) of 20.4
to 20.6 VDC continuously. Float charging may take 24 hours or longer to charge a battery pack.
3. Routine Charging: Disconnect the battery or batteries from the indicator or module. Connect the
battery or batteries to a constant voltage source (battery plug pin 1 red wire = positive) of 21.6 to
22.1 VDC with a current limit of 0.1 ampere maximum. When the charging current drops to
approximately 5mA, the battery is fully charged and should be disconnected. Leaving 21.6 to
22.1 VDC charge voltage on the battery for an extended time will degrade its life. If continuous
maintenance of the charge is desired, refer to step 2, Float Charging.
****WARNING****
Battery out gassing and a rotten egg odor may occur due to
prolonged high rate overcharging and may result in battery
damage. The battery assembly must be replaced if
out gassing has occurred.
G600 PFD/MFD System 190-00601-00 Rev. K
Instructions for Continued Airworthiness Page 5 of 14
Loading...