g1000 field upgrade instructions model c90a/c90gt king...

190-00682-06 May 2009 Revision 1

G1000 Field Upgrade Instructions Model C90A/C90GT King Air

STC #SA01456WI-D

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G1000 Field Upgrade Instructions – Model C90A/C90GT King Air Page A 190-00682-06 Revision 1

© Copyright 2009 Garmin Ltd. or its subsidiaries

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Fax: +44 (0) 23 8052 4004

RECORD OF REVISIONS

Revision Revision Date Description ECO #1 5/19/2009 Initial release for STC. -------

DOCUMENT PAGINATION

Section Pagination

Table of Contents i – ii Section 1 1-1 – 1-4 Section 2 2-1 – 2-2 Section 3 3-1 – 3-2 Section 4 4-1 – 4-14 Section 5 5-1 – 5-2 Section 6 6-1 – 6-4 Section 7 7-1 – 7-2 Section 8 8-1 – 8-6 Section 9 9-1 – 9-2

Page B G1000 Field Upgrade Instructions – Model C90A/C90GT King Air Revision 1 190-00682-06

INFORMATION SUBJECT TO EXPORT CONTROL LAWS

This document may contain information which is subject to the Export Administration Regulations (“EAR”) issued by the United States Department of Commerce (15 CFR, Chapter VII Subchapter C) and which may not be exported, released or disclosed to foreign nationals inside or outside the United States without first obtaining an export license. The preceding statement is required to be included on any and all reproductions in whole or in part of this manual.

WARNING

This product, its packaging, and its components contain chemicals known to the State of California to cause cancer, birth defects, or reproductive harm. This Notice is being provided in accordance with California's Proposition 65. If you have any questions or would like additional information, please refer to our web site at www.garmin.com/prop65.

CAUTION

The GDU lens is coated with a special anti-reflective coating that 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.

NOTE:

All G1000 screen shots used in this document are current at the time of initial publication. Screen shots are intended to provide visual reference only. All information depicted in screen shots, including software file names, versions and part numbers, is subject to change and may not be up to date.

G1000 Field Upgrade Instructions – Model C90A/C90GT King Air Page i 190-00682-06 Revision 1

TABLE OF CONTENTS PARAGRAPH PAGE

1 INTRODUCTION 1-1 1.1 Scope..................................................................................................................................................1-1 1.2 Required Upgrade Documents ...........................................................................................................1-1 1.3 Identifying the Aircraft’s Existing Configuration..............................................................................1-2 1.4 Record Currently Activiated Configuration and Options ..................................................................1-3 2 Upgrade Preparation 2-1 2.1 Document Structure ...........................................................................................................................2-1 3 LRU Upgrade Summary (Optional) 3-1 3.1 GMA 1347D Audio Panel..................................................................................................................3-1 3.2 GTX 33 Extended Squitter (ES) Transponder ...................................................................................3-2 4 Installation Upgrade Procedures (Optional) 4-1 4.1 Engine Signal Conditioner Modification ...........................................................................................4-1 4.2 Passenger Address System Wiring Modification...............................................................................4-8 5 Software Upgrade Procedure 5-1 5.1 G1000 Software/Configuration Procedure.........................................................................................5-1 6 Reactivation of C90 Airframe Options / Configurations 6-1 6.1 Airframe Configuration......................................................................................................................6-1 6.2 C90 Aircraft Weight and Airspeed Configurations............................................................................6-1 6.3 C90 Options .......................................................................................................................................6-2 6.4 G1000 System Configurations ...........................................................................................................6-3 7 Activation of SVS and GTX 33 ES Configuration Options 7-1 7.1 Synthetic Vision / Pathways Configuration .......................................................................................7-1 7.2 GTX 33 Extended Squitter Transponder Option................................................................................7-1 8 G1000 Equipment Testing 8-1 8.1 G1000 Normal Mode .........................................................................................................................8-1 8.2 System Return to Service Procedure..................................................................................................8-2 8.3 Configuration and Option Functional Checks....................................................................................8-2 8.4 LRU Upgrade Testing ........................................................................................................................8-3 8.5 Installation Upgrade Testing ..............................................................................................................8-3 9 Aircraft Logbook Entry 9-1

Page ii G1000 Field Upgrade Instructions – Model C90A/C90GT King Air Revision 1 190-00682-06

LIST OF ILLUSTRATIONS FIGURE PAGE FIGURE 3-1. GMA 1347D PN 011-01257-20 CONTROLS..................................................................3-1 FIGURE 8-1. NORMAL MODE..............................................................................................................8-1

LIST OF TABLES TABLE PAGE TABLE 1-1. REQUIRED DOCUMENTS ...............................................................................................1-2 TABLE 1-2. ACTIVATED CONFIGURATIONS AND OPTIONS .......................................................1-3 TABLE 4-1. PARTS REQUIRED FOR ENGINE SIGNAL CONDITIONER UPGRADE....................4-1 TABLE 4-2. PARTS REQUIRED FOR PA SYSTEM UPGRADE ........................................................4-8

G1000 Field Upgrade Instructions – Model C90A/C90GT King Air Page 1-1 190-00682-06 Revision 1

1 INTRODUCTION 1.1 Scope

This document presents approved field rework instructions which are to be used to perform upgrades of the C90A G1000 integrated avionics system with new software, optional LRUs and installation upgrades that were incorporated into the STC data at Master Drawing List (MDL) 005-00375-30 Revision 5. These upgrades are applicable to fielded aircraft with STC SA01456WI-D installed at MDL 005-00375-30 Revision 4 and previously approved revisions. A Garmin service bulletin will be issued to support these upgrades.

Upgrade of the existing G1000 system software version 0636.01 to system software version 0636.02 is a recommended change to all fielded aircraft. Compliance with any aspect of this upgrade document requires the system software upgrade be completed.

The following additional changes are also available with this upgrade. Installation of G1000 system software version 0636.02 or later FAA approved version is a prior or concurrent requirement for these modifications.

• Upgrade GMA 1347D audio control panel to the new PN 011-01257-20 variant to obtain additional cabin audio feature.

• Upgrade of existing GTX 33 transponders to the GTX 33ES units to obtain extended squitter ADS-B (transmission only) functionality.

• Replacement of the Sandia ST26 tach-gen adapter, Senior Aerospace PC920 fuel flow signal conditioner and the Garmin tach-gen filter assembly with a Vibro-Meter signal conditioner, PN 85-292-2. This signal conditioner upgrade will provide a robust alternative to the existing signal conditioner components.

• Modification to the passenger address system that introduces a relay-interlock into the GMA-PA interface in order to prevent the "pop" sound within the PA from occurring during system turn-on.

• Activation of Garmin Synthetic Vision and Pathways option.

1.2 Required Upgrade Documents

Table 1-1 defines all necessary documents and drawings needed to perform this upgrade, as well as new operating documents required to be delivered to the aircraft owner and/or operator before return to service.

2 G1000 Field Upgrade Instructions – Model C90A/C90GT King Air Revision 1 190-00682-06

Table 1-1. Required Documents

Part Number Garmin Document

*005-00375-30, Rev. 5 Master Drawing List, G1000 & GFC 700 AFCS in Hawker Beechcraft C90A/C90GT King Air Aircraft

*005-00375-22, Rev. 11 General Arrangement, G1000/GFC700 AFCS, King Air C90A/C90GT

*190-00682-01, Rev. D G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air

*005-00375-28, Rev. 7 Main Instrument Panel Installation, King Air C90A/C90GT

*005-W0022-00, Rev. 10 Wiring Diagram G1000/GFC 700 King Air C90A/C90GT

*005-00375-29, Rev. 5 Circuit Breaker Panel Modification, King Air C90A

*005-00375-70, Rev. 5 Circuit Breaker Panel Modification, King Air C90A

005-00375-94 Tach-Gen Filter Instl., King Air C90A

Other Documents

90-590012-13 King Air Model 90 Series Maintenance Manual

523-0772458-00611A Collins DME-42 Transceiver Repair Manual (If DME is installed)

* Or later FAA-Approved revisions to the data listed above.

1.3 Identifying the Aircraft’s Existing Configuration

Prior to performing any modification contained in this document, the technician should determine the configuration of the aircraft being modified to ensure applicability and scope of the modifications required. The optional hardware changes defined in this document may be incorporated at a later date than the software upgrade. However, the technician must confirm the presence of G1000 system software version 0636.02 prior to initiating the hardware modification. This STC addresses multiple C90A/C90GT configurations. These configuration variants are added by loading the applicable airframe configuration. Refer to Table 5 of the General Arrangement Drawing listed in Table 1-1 for C90GT and Blackhawk and/or Raisbeck configuration information. It is important that the technician know what the current STC airframe configuration is prior to initiating the modification. This information will be required during the software upgrade.

IMPORTANT! If the technician is unsure of the aircraft’s STC airframe configuration and/or G1000 system software version, perform the following steps:

1. Inspect the aircraft maintenance logs for records of which STC configuration is installed. Inspect

aircraft records for signs of other alterations, including field updates and Service Bulletins.

2. Power on the G1000 system by setting the BAT switch to ON, then the EXT PWR switch to ON and finally the AVIONICS MASTER switch to ON.

3. Following MFD power-up, observe upper right section of MFD splash screen for airframe configuration. OR


After acknowledgement of the splash screen, use the FMS knob on the GCU 475 controller to go to the AUX – SYSTEM STATUS page on the MFD. In the AIRFRAME section (upper right corner,) the display shows the current G1000 airframe configuration and system software version number. The airframe configuration is shown in the AIRFRAME field and the system software version number is shown in the following format: ‘System Software Version 0636.02’. It correlates to the G1000 software used to load the software to the system:

EXAMPLE:

System Software Version ‘0636.02’ = G1000 Software P/N 006-B0636-02 The G1000/GFC 700 C90 General Arrangement Drawing listed in Table 1-1 defines the approved G1000 software for this STC.

1.4 Record Currently Activiated Configuration and Options Record all currently activated configurations and options in Table 1-2 below. Table 1-2. Activated Configurations and Options

Configuration Enabled (√)

C90 Airframe Configurations

King Air C90 - Baseline

King Air C90 - Config 1



















C90-Weight & Airspeed Configuration

King Air C90 – Weight LJ 1063-1137,1146 (MTOW 9,650 lbs)

King Air C90 – 90-206CGW (MTOW 10,100 lbs)

King Air C90 – 05-206CGW (MTOW 10,350 lbs)

King Air C90 – Airspeed LJ 1063-1137, 1146

C90-Options

King Air C90 - ADF-60 Option

*King Air C90 – DME-42 Option

King Air C90 – Traffic System Option

King Air C90 – WX 500 Option

G1000 System Configurations

TIS (Default)

TAWS – B

FliteCharts (Default)

ChartView

* NOTE The DME channel one audio level must be adjusted by the procedure contained within Collins DME-42 Transceiver Repair Manual 523-0772458-00611A, Maintenance Section 523-0772460-006118 to adjust DME channel one audio level. Recommended nominal DME audio output level is 4.46 Vpp +0.10 Vpp for aircraft with C90A G1000 System Software Version 0636.02 and subsequent approved versions. Procedure must be accomplished by an approved repair station.


2 Upgrade Preparation 2.1 Document Structure

This C90 G1000 Field Upgrade Instruction document is structured as follows:

• Section 3 provides instructions to install the optional new GMA1347D audio control panels, PN 011-01257-20 and GTX 33ES extended squitter transponders.

• Section 4 provides instructions for the optional installation upgrade for the Vibro-Meter signal conditioners and wiring modifications for the PA system.

• Section 5 provides instructions for upgrading the aircraft to the G1000 system software version 0636.02

• Section 6 provides reactivation of existing options and configuration items

• Section 7 provides activation of SVS/Pathways and GTX 33 ES options

• Section 8 provides G1000 system and return to service tests If the aircraft operator chooses not to upgrade the subject aircraft with the optional LRU and/or installation upgrades, then skip directly to Section 5 of this document to load the system software version 0636.02. Otherwise, if the operator chooses to upgrade the aircraft with either of the optional LRUs in Section 3, and/or installation upgrades in Section 4, then complete the LRU and/or installation upgrades prior to loading G1000 system software version 0636.02 detailed in Section 5. Section 6 provides direction on the reactivation of previously selected options and configuration items. Certain selected options need to be reselected after reloading of G1000 software. This section directs the technician on how to reactivate those features. Section 7 provides the instructions on how to activate Garmin's optional Synthetic Vision and Pathways feature and the GTX 33 ES option. If the operator did not purchase this feature or install the GTX 33ES transponders, skip directly to section 8. Testing for the G1000 system software version 0636.02, new LRUs, and installation upgrades are provided in Section 8 of this document.

IMPORTANT!

The portions of section 8 applicable to the selected upgrades must be successfully completed prior to return to service of the aircraft.


3 LRU Upgrade Summary (Optional)

3.1 GMA 1347D Audio Panel

This section will provide instructions for upgrading the aircraft to the GMA 1347D audio control panel, PN 011-01257-20. The GMA 1347D (-20) has a CABIN key that initiates two way communication between the pilot or copilot and the passengers in the cabin. This option is only available with C90 G1000 System Software version 0636.02. Figure 3-1 provides a format of the panel button layout for the GMA 1347D, PN 011-01257-20.

IMPORTANT!

If this upgrade is selected, both #1 and #2 Audio Panels must be upgraded to P/N 011-01257-20.

Transceiver Audio

Telephone

Speaker

Marker Beacon SignalSensitivity

Transceiver Audio

Passenger Address

Music

Marker Beacon Mute

Transmitters

Digital Recording Playback

Cabin Intercom

Master VOL (Large Knob)

Reversionary Mode

Aircraft NavigationRadio Audio

Manual Squelch

Intercom System (ICS)

ICS VOL SQ (Small Knob)

Figure 3-1. GMA 1347D PN 011-01257-20 Controls


3.1.1 GMA Upgrade Instructions

1. Remove existing No. 1 GMA 1347D (011-01257-00) and install GMA 1347D (011-01257-20) in the

No. 1 location according to G1000/GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Section 6.2. Installer should not complete Step 4 of replacement instructions in Section 6.2 at this time.

2. Remove existing No 2 GMA 1347D (011-01257-00) and install GMA 1347D (011-01257-20) in the No. 2 location according to G1000/GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Section 6.2. Installer should not complete Step 4 of replacement instructions in Section 6.2 at this time.

3. If installing GTX 33 option continue to Section 3.2 of this document, otherwise proceed to Section 4 of this document for installation upgrade procedures.

3.2 GTX 33 Extended Squitter (ES) Transponder

This section will provide instructions for upgrading the aircraft with a GTX 33 Extended Squitter (ES) transponder part number 011-00779-30 to provide the extended squitter ADS-B (transmission only) function.

NOTE The GTX 33 Transponder Part Number 011-00779-10 will require an upgrade to support ES functionality prior to enabling the GTX 33 ES Option and must be routed to the Garmin Service Center for this upgrade. If GTX 33 ES Transponder Part Number 011-00779-30 is installed in the aircraft, then the GTX 33 ES Option can be enabled.

3.2.1 GTX 33 ES Transponder Upgrade Instructions Replace the GTX 33 Garmin part number 011-00779-10 with GTX 33 ES Garmin part number 011-00779-30. 1. Remove existing No. 1 GTX 33 (011-00779-10) transponder and install GTX 33 ES (011-00779-30)

transponders in the No. 1 location according to G1000/GFC 700 System Maintenance Manual, Model C90A/C90GT King Air Section 6.5. Installer should not complete Step 5 of replacement instructions in Section 6.5 at this time.

2. Remove existing No. 2 GTX 33 (011-00779-10) transponder and install GTX 33 ES (011-00779-30) transponders in the No. 2 location according to G1000/GFC 700 System Maintenance Manual, Model C90A/C90GT King Air Section 6.5. Installer should not complete Step 5 of replacement instructions in Section 6.5 at this time.

3. Proceed to Section 4 of this document for installation upgrade procedures.


4 Installation Upgrade Procedures (Optional) This section includes instructions to perform the following optional installation upgrades.

• Engine Signal Conditioner Modification to replace existing tach generator unit, filter assembly with new Vibro-meter signal conditioner (Refer to Section 4.1 of this document)

• Audio system upgrade to remove PA “pop” on power up.(Refer to Section 4.2 of this document)

If installing neither of these modifications, proceed directly to Section 5 of this document to load the new G1000 System Software version 0636.02.

4.1 Engine Signal Conditioner Modification This section will provide instructions for replacing the Sandia ST26 Tach Generator Unit (PN 305662-00), Senior Aerospace PC920 Signal Conditioning Unit (PN PC920-6A0600PH-2A1) and the Garmin 005-00375-93 Tach-Gen Filter Assembly with the Vibro-Meter Signal Conditioner, PN 85-292-2. 4.1.1 Parts Required:

Table 4-1. Parts Required for Engine Signal Conditioner Upgrade

QTY Part Description Part Number (MFG) Vendor

10 Washer, Plain #10, .032 Thick NAS1149F0332P Best Source

18 Washer, Plain #6, .032 Thick NAS1149FN632P Best Source

8 Screw, Pan HD, 6-32 X .500 MS35206-230 Best Source

2 #6 Ring Terminal MS25036-111 Best Source

10 Nut, Locking, 6-32 MS21044N06 Best Source

2 Signal Conditioner 85-292-2 Vibro-Meter

AR Flat Braid, 3/8” Wide (QQB575F36T0375)

AA59569F36T0375 Best Source

2 Plate, Signal Conditioner 115-01184-00 Garmin

2 Rack, Universal 115-00899-00 Garmin

2 Nut Plate, Kit, 3 Position 011-00915-01 Garmin

2 Connector, Sub-D M24308/2-3 Best Source

NOTE The Universal Rack, part number 115-00899-00 and 3-Position Nut Plate, part number 011-

00915-01 can be retained from the installation with the Sandia ST26 tach-gen adapters and Senior Aerospace PC920 fuel flow signal conditioner and reused for the Vibro-Meter signal conditioner installation.


NOTE Vendor contact information is provided in the General Arrangement Drawing, 005-00375-

22 Revision 11 or later FAA approved revision. 4.1.2 Signal Conditioner Rework Instructions

4.1.2.1 Instrument Panel and Equipment Removal

1. Remove power from aircraft. 2. Remove the following equipment from the instrument panel and store for later re-

installation into the instrument panel. Cap all pitot and static lines. Retain all equipment for re-installation in the aircraft. Reference the G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air for removal instructions.

NOTE If the original equipment is re-installed in their original positions, no software or

configuration loading is required. Identify the equipment with the position from which it was removed.

a. No. 1 and 2 GMA 1347D Audio Panels b. No. 1 and 2 GDU 1040A PFD c. GDU 1500 MFD d. GMC 710 Mode Controller e. Standby Attitude, Altimeter, Airspeed Indicators

3. Remove the following equipment from the instrument panel system racks. Cap all pitot and

static lines. Retain all equipment for re-installation in the aircraft except for the No. 1 and 2 ST26 tach-gen adapter units and the PC920 fuel flow signal conditioner. Reference the G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air for removal instructions.

NOTE If the original equipment is re-installed in their original positions, no software or


a. No. 1 and 2 GDC 74B Air Data Computers b. No. 1 and 2 GEA 71 Engine and Airframe Units c. GDL 69A Data Link Unit d. PC920 Fuel Flow Signal Conditioner Unit e. No. 1 and 2 ST26 Tach-Gen Adapter Units

4. Disconnect all electrical connectors for removed equipment in Steps 2 and 3 if applicable

from the system racks. Disconnect the Marker Beacon coaxes from coupler located at the back and top of the left system rack. Secure all connectors for re-installation in the system racks.

5. Disconnect the following electrical connectors for equipment that will remain in the

instrument panel or system racks.

a. Connector 1P1281 for PFD#1 Fan


b. Connector 2P1281 for PFD#2 Fan c. Connector 3P1281 for MFD Fan d. Connector GS150 for Prop Sync Switch e. Connector G97AE for Standby Battery Switch f. Connector P258A for Stall Warning Indicator Light

6. Disconnect all environmental hoses and electrical connectors to glareshield. Retain all

hardware from all components for re-installation of the glareshield. Remove the glareshield from the aircraft.

7. Remove the four fasteners from the front of the instrument panel and remove the

instrument panel from the aircraft. Retain all hardware for reinstallation of the instrument panel. Refer to the Main Instrument Panel Installation Drawing, 005-00375-28, Sheet 4 for location of the four fasteners.

8. Remove the left and right system racks from the instrument panel. Retain all hardware for

re-installation of the system racks on to the instrument panel. 9. Remove both universal racks, Garmin PN 115-00899-00 from the left system rack. Retain

all hardware from one of the removed universal racks for re-installation back into the left system rack. Refer to Main Instrument Panel Installation Drawing, 005-00375-28 for universal rack location and removal details.

10. Remove the universal plate, Garmin PN 115-00900-00 from the removed and retained

universal rack, Garmin PN 115-00899-00. Obtain signal conditioner plate, Garmin PN 115-01184-00 and Vibro-Meter signal conditioner PN 85-292-2. Install the signal conditioner and plate in the left universal rack. Refer to Main Instrument Panel Installation Drawing, 005-00375-28 Sheet 19, Detail S for installation detail.

11. Remove the universal rack, Garmin PN 115-00899-00 from the right system rack. Retain

all hardware from the removed universal rack for re-installation back into the right system rack. Refer to Main Instrument Panel Installation Drawing, 005-00375-28 for universal rack location and removal detail.

12. Remove the universal plate, Garmin PN 115-00900-00 from the removed universal rack,

Garmin PN 115-00899-00. Obtain signal conditioner plate, Garmin PN 115-01184-00 and Vibro-Meter signal conditioner PN 85-292-2. Install the signal conditioner and plate in right universal rack. Refer to Main Instrument Panel Installation Drawing, 005-00375-28 Sheet 19, and Detail S for installation detail.

13. Re-install the left and right system racks on the instrument panel using retained hardware.

4.1.2.2 Wiring Changes for Aircraft LJ-1063 through LJ-1282 without PC920 Fuel Flow Signal Conditioner

1. Locate the left tach-gen filter harness connectors PAD26 and JAD26. Connector PAD26

was previously disconnected from the left ST26 tach-gen adapter connector J1. Disconnect JAD26 from the connector 1P261. Stow both left connectors PAD26 and JAD26.

2. Locate the left ST26 tach-gen adapter connector 1P261 and left PC920 connector P9201.

Remove wires from both connectors. Obtain connector 1PVIB1, PN M24308/2-3 and install wires according to the Wiring Diagram 005-W0022-00, Sheet 47 and 49.


3. Locate the right tach-gen filter harness connectors PAD26 and JAD26. Connector PAD26

was previously disconnected from the right ST26 tach-gen adapter connector J1. Disconnect JAD26 from the connector 2P261.

4. Locate the right ST26 tach-gen adapter connector 2P261 and right PC920 connector P9202.

Remove wires from both connectors. Obtain connector 2PVIB1, PN M24308/2-3 and install wires according to the Wiring Diagram 005-W0022-00, Sheet 47 and 49.

4.1.2.3 Circuit Breaker Wiring Changes 1. For affected aircraft, serial numbers LJ-1063 through LJ-1282 with Gull fuel flow

transducer, there are no circuit breaker wiring changes. Proceed to Step 4 for continuity checks.

2. For affected aircraft, serial numbers LJ-1283 through LJ-1360 and LJ-1362 accomplish the

following wiring changes at the right hand circuit breaker panel. Refer to the Wiring Diagram 005-W0022-00 Sheet 41 for pre-modification configuration and Sheet 49 for post modification configuration of the circuit breaker wiring. Refer to the Circuit Breaker Modification drawing 005-00375-70 for right hand circuit breaker panel details.

a. Locate and remove wire G77119A22 from the load side of the LEFT FUEL FLOW

circuit breaker CB139 and relocate to the load side of the LEFT PROP/N1 TACH circuit breaker CB143.

b. Locate and remove wire G77120A22 from the load side of the RIGHT FUEL FLOW

circuit breaker CB140 and relocate to the load side of the RIGHT PROP/N1 TACH circuit breaker CB158.

c. Re-identify the nomenclature for the PROP/N1 TACH circuit breaker as SIGNAL

COND. d. Proceed to Step 4 for continuity checks.

3. For effective aircraft, serial numbers LJ-1361, LJ-1363 and after, accomplish the following

wiring changes at the left hand circuit breaker panel. Refer to the Wiring Diagram 005-W0022-00 Sheet 41 for pre-modification configuration and Sheet 49 for post modification configuration of the circuit breaker wiring. Refer to the Circuit Breaker Modification Drawing 005-00375-29 Sheets 7 and 8 for pre-modification configuration and Sheets 9 and 10 for post modification configuration of the left hand circuit breaker panel.

a. Locate and remove wire G77119A22 from connector J111 pin 16. Locate wire

G77115A22 at connector J111 pin 18. Splice wire G77119A22 with wire G77115A22 and re-terminate at connector J111 pin 18.

b. Locate and remove wire CCB20-P6-16 from the load side of the LEFT FUEL FLOW

circuit breaker. Cap and stow wire CCB20-P6-16.


c. Locate and remove wire G77120A22 from connector J109 pin 18. Locate wire G77117A22 at connector J109 pin 16. Splice wire G77120A22 with wire G77117A22 and re-terminate at connector J109 pin 16.

d. Locate and remove wire CCB35-P2-18 from the load side of the RIGHT FUEL FLOW

circuit breaker. Cap and stow wire CCB35-P2-18. e. Re-identify the nomenclature for the PROP/N1 TACH circuit breakers as SIGNAL

COND. 4. Accomplish continuity check for the installed left and right engine signal conditioner

wiring per the Wiring Diagram 005-W0022-00 Sheet 47, 48 and 49.


4.1.2.4 Tach-Gen Filter Assembly Removal 1. Gain access to the left tach-gen filter assembly by removing the pilot’s floor panel.

Disconnect the tach-gen harness connector PFILT from the RC filter board assembly. Remove the filter board from the floor panel. Reference the Tach-Gen Filter Installation Drawing, 005-00375-94 for location details.

2. Remove the left tach-gen filter harness assembly from the aircraft. Reference the Tach-Gen

Filter Installation Drawing, 005-00375-94 for routing details. 3. Re-install the pilot’s floor panel. 4. Gain access to the right tach-gen filter assembly by removing the co-pilot’s floor panel.

Disconnect the tach-gen harness connector PFILT from the RC filter board assembly. Remove the filter board from the floor panel. Reference the Tach-Gen Filter Installation Drawing, 005-00375-94 for location details.

5. Remove the right tach-gen filter harness assembly from the aircraft. Reference the Tach-

Gen Filter Installation Drawing, 005-00375-94 for routing details. 6. Re-install the pilot’s floor panel.

4.1.2.5 Re-install the Main Instrument Panel and Equipment NOTE

If also intending to incorporate PA System Wiring modification, installer may skip 4.1.2.5, which re-installs all equipment, and proceed to Section 4.2.

1. Re-install the instrument panel using hardware retained in removal process. Refer to the

Instrument Panel Installation Drawing, 005-00375-28 for installation details. 2. Re-install the glareshield in the aircraft using hardware retained in removal process. Re-

connect all environmental hoses and electrical connectors. 3. Re-connect the following electrical connectors for equipment that remained in the


a. Connector 1P1281 for PFD#1 Fan b. Connector 2P1281 for PFD#2 Fan c. Connector 3P1281 for MFD Fan d. Connector GS150 for Prop Sync Switch e. Connector G97AE for Standby Battery Switch f. Connector P258A for Stall Warning Indicator Light

4. Re-connect all electrical connectors to the system racks for equipment removed in Section

4.1.2.1, Steps 2 and 3. Re-connect the Marker Beacon coaxes to the coupler located at the back and top of the left system rack.

5. Connect 1PVIB1 to the left engine signal conditioner located in the left system rack. 6. Connect 2PVIB1 to the right engine signal conditioner located in the right system rack.


7. Re-install the following equipment in the instrument panel system racks. Remove caps

from pitot and static lines. NOTE If the original equipment is re-installed in their original positions, no software or


a. No. 1 and 2 GDC 74B Air Data Computers b. No. 1 and 2 GEA 71 Engine and Airframe Units c. GDL 69A Data Link Unit

8. Re-install the following equipment in the instrument panel. Remove all caps from pitot and

static lines. Retain all equipment for re-installation I the aircraft. NOTE If the original equipment is re-installed in their original positions, no software or



9. Restore power to aircraft. 10. If accomplishment of this installation upgrade is being completed prior to loading the C90

G1000 system software version 0636.02, then proceed to Section 5 of this document and load the C90 G1000 system software version 0636.02.


4.2 Passenger Address System Wiring Modification

This section will provide passenger address system wiring modification instructions for aircraft installations with STC SA01456WI-D MDL 005-00375-30 Revision 4 and previously approved revisions. Aircraft that are eligible for this modification are those with passenger address system wiring installed per Sheet 37 of Wiring Diagram 005-W0022-00 to the fore mentioned STC. This modification does not affect the PA function. A relay-interlock is introduced into the GMA-PA interface in order to prevent a "pop" sound within the PA from occurring during system turn-on.

4.2.1 Parts Required:

Table 4-2. Parts Required for PA System Upgrade

QTY Part Description Part Number (MFG) Vendor

6 20 ga socket contact (91CB) LMD-4120-96LD (Pyle Nat’l) Hawker Beechcraft

4 22 ga socket contact (91CG) LMD-4122-96LD (Pyle Nat’l) Hawker Beechcraft

5 20 ga MIL pin contact (GBA()) M39029/4-110 Best Source

5 20 ga MIL socket contact (GBB()) M39029/5-115 Best Source

6 crimp splice M81824/1-1 Best Source

4 solder sleeve (twisted pair) MS83519/1-4 Best Source

2 solder sleeve (twisted triple) MS83519/1-5 Best Source

AR flat braid 1/16 in (for shields) AA59569F36T0062 Best Source

3 20 ga D-Sub socket contact (10AN,10AM)

M39029/63-368 Best Source

8 22 ga Hi-Dens D-Sub contact (GMA) M39029/58-360 Best Source

AR 22 gauge stranded wire M22759/16-22-9 Best Source

AR 22 gauge shielded twisted pair M27500-22TE2T14 Best Source

AR 22 gauge shielded twisted triple M27500-22TE3T14 Best Source

5 ring terminal #8 stud MS25036-149 Best Source

AR silicon fusion tape AA59163-1II0020 Best Source

AR Lace tying tape MIL-T-43435B Best Source


4.2.2 Passenger Address System Wiring Modification Instructions

NOTE It may not be necessary to accomplish 4.2.2.1, if installer has already removed equipment as part of Section 4.1 for the Engine Signal Conditioner modification.

4.2.2.1 Instrument Panel and Equipment Removal

1. Remove power from aircraft.

2. Remove the following equipment from the instrument panel and store for later re-installation into the instrument panel. Cap all pitot and static lines. Retain all equipment for re-installation in the aircraft. Reference the G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air for removal instructions.

NOTE If the original equipment is retained and re-installed in their original positions, no software or configuration loading is required. Identify the equipment with the position from which it was removed.


3. Remove the following equipment from the instrument panel system racks. Cap all pitot and

static lines. Retain all equipment for re-installation in the aircraft.

NOTE If the original equipment is retained and re-installed in their original positions, no software or configuration loading is required. Identify the equipment with the position from which it was removed.

a. No. 1 and 2 GDC 74B Air Data Computers b. No. 1 and 2 GEA 71 Engine and Airframe Units c. GDL 69A Data Link Unit d. PC920 Fuel Flow Signal Conditioner Unit (or Vibro-Meter Signal Conditioner if

installed) e. No. 1 and 2 ST26 Tach-Gen Adapter Units (or Vibro-Meter Signal Conditioners if

installed)

4. Disconnect all electrical connectors for removed equipment in Steps 2 and 3 from the system racks, if applicable. Disconnect the Marker Beacon coaxes from coupler located at the back and top of the left system rack. Secure all connectors for re-installation in the system racks.


5. Disconnect the following electrical connectors for equipment that will remain in the



6. Disconnect all environmental hoses and electrical connectors to glareshield. Retain all

hardware from all components for re-installation of the glareshield. Remove the glareshield from the aircraft.

7. Remove the left and right system racks and audio panel racks from the instrument panel. Retain all hardware for re-installation of the racks on to the instrument panel.

8. Remove the four fasteners from the front of the instrument panel and remove the

instrument panel from the aircraft. Retain all hardware for reinstallation of the instrument panel. Refer to the Main Instrument Panel Installation Drawing, 005-00375-28, Sheet 4 for location of the four fasteners.

4.2.2.2 Cabin Side Wiring Changes

1. Fabricate the following wires and identify them as noted: WIRE ID WIRE TYPE LENGTH**

G23143A22 M27500-22TE2T14 70 in G23144A22 M22759/16-22-9 70 in G23146A22 M22759/16-22-9 70 in ** This length is long on purpose to allow ease in installation. Once wire is tied into the harness, it may be cut to length before making final termination.

2. Locate harness connector 1P13471. Disassemble the backshell from this connector and

locate twisted-triple-conductor wire number G23143A22. Extract all conductors of this wire from the 1P13471 (pins 67, 68, and 48).

3. Locate bulkhead connector GBB2. Disassemble the strain-relief to gain access to the wires.

Locate twisted-triple-conductor wire number G23143A22 and extract all conductors of this wire from connector GBB2 (pins Z, A*, and C*).

4. Remove wire G23143A22 from the harness. 5. While in GBB2, locate twisted-triple-conductor wire number G23131A22. Extract all

conductors of this wire from connector GBB2 (pins G*, I*, and K*) and re-route the end of this wire to 1P13471 following the existing harness layout.

6. Referencing sheet 50 of Wiring Diagram 005-W0022-00, take newly fabricated wire

G23143A22 and splice conductors to existing re-routed wire G23131A22 at the 1P13471 connector. Terminate wires and connect as shown on sheet 50. Route the remaining length of G23143A22 to GBB2.



G23144A22 and splice it to wire(s) that are in position 29 of 1P13471. (Existing wires have blue stripe insulation and are spliced together and are part of shielded conductors G23110A22 and G23110B22). Route the remaining length to GBB2 following existing harness layout.

8. Referencing sheet 50 of Wiring Diagram 005-W0022-00, at GBB2 trim newly fabricated

wire G23143A22 to lie neatly in harness and connect conductors as shown on sheet 50.

9. Referencing sheet 50 of Wiring Diagram 005-W0022-00, at GBB2 trim newly fabricated wire G23144A22 to lie neatly in harness and connect as shown on sheet 50.

10. Reassemble connectors GBB2 and 1P13471.

11. Locate harness connector 2P13471. Disassemble the backshell from this connector and

locate twisted-triple-conductor wire number G23144A22. Extract all wires of this conductor from the 2P13471 (pins 67, 68, and 48).

12. Locate bulkhead connector GBB3. Disassemble the strain-relief to gain access to the wires.

Locate twisted-triple-conductor wire number G23144A22 and extract all wires of this conductor from connector GBB3 (pins H, J, and K). Locate wire G23146A22 and extract it from GBB3 (pin G).

13. Locate twisted-triple-conductor wire number G23136A22. Extract all wires of this

conductor from connector GBB3 (pins L, M, and N) and re-route the end of this wire to 2P13471 following existing harness layout.

14. Locate harness connector 2P13472. Disassemble the strain-relief to gain access to the

wires. Locate wire number G23146A22 and extract this wire from connector 2P13472 (pin 64).

15. Remove wires G23144A22 and G23146A22 from the harness.

16. Reassemble 2P13472.

17. Referencing sheet 50 of Wiring Diagram 005-W0022-00, trim existing re-routed wire

G23136A22 to neatly fit harness up to the 2P13471 connector. Terminate wires and connect as shown on sheet 50.


G23146A22 and splice it to wire that is in position 29 of 2P13471. (Existing wires have blue stripe insulation and are spliced together and are part of shielded conductors G23116A22 and G23116B22). Route the remaining length to GBB3 following existing harness layout.

19. Reassemble 2P13471 connector.

20. Referencing sheet 50 of Wiring Diagram 005-W0022-00, at GBB3 trim newly fabricated

wire G23146A22 to lie neatly in harness. Terminate wire and connect as shown on sheet 50.

21. Reassemble GBB3.


4.2.2.3 Re-install the Main Instrument Panel and Equipment

1. Re-install the instrument panel using hardware retained in removal process. Refer to the Main Instrument Panel Installation Drawing, 005-00375-28 for installation details.

2. Re-install the glareshield in the aircraft using hardware retained in removal process. Re-

connect all environmental hoses and electrical connectors. 3. Re-connect the following electrical connectors for equipment that remained in the



4. Re-connect all electrical connectors to the system racks for removed equipment in Section

4.2.2.1, Steps 2 and 3. Re-connect the Marker Beacon coaxes to the coupler located at the back and top of the left system rack.

5. Re-install the following equipment in the instrument panel system racks. Remove caps

from pitot and static lines. NOTE

If the original equipment is retained and re-installed in their original positions, no software or configuration loading is required.

a. No. 1 and 2 GDC 74B Air Data Computers b. No. 1 and 2 GEA 71 Engine and Airframe Units c. GDL 69A Data Link Unit

6. Re-install the following equipment in the instrument panel system racks. Remove all caps

from pitot and static lines. NOTE

If the original equipment is retained and re-installed in their original positions, no software or configuration loading is required.



4.2.2.4 Nose Side Wiring Changes

1. Fabricate the following wires and identify them as noted: WIRE ID WIRE TYPE LENGTH**

G23143B22 M27500-22TE2T14 60 in G23144B22 M22759/16-22-9 65 in G23145B22 M22759/16-22-9 65 in G23146B22 M22759/16-22-9 65 in G23147A22 M22759/16-22-9 30 in G23148A22 M22759/16-22-9 30 in G23149A20 M22759/16-20-9 95 in ** This length is long on purpose to allow ease in installation. Once wire is tied into the harness, it may be cut to length before making final termination.

2. Remove avionics equipment to gain access to the LMD modules, the wiring harness, bulkhead connectors GBA2 and GBA3, and the installed PA amplifier connectors.

3. Locate bulkhead connector GBA2 and disassemble the strain-relief to gain access to the

wires. Locate twisted-triple-conductor wires, numbers G23143B22 (pins Z, A*, and C*) and G23131E22 (pins G*, I*, and K*), and wire number G23145B22 (pin E*) and extract all wires of these conductors from connector GBA2. These wires are to be removed from the harness.

4. Locate bulkhead connector GBA3 and disassemble the strain-relief to gain access to the

wires. Locate twisted-triple-conductor wires, numbers G23144B22 (pins H, J, and K) and G23136E22 (pins L, M, and N), and wire number G23146B22 (pin G) and extract all wires of these conductors from connector GBA3. These wires are to be removed from the harness.

5. Locate LMD module 91CJ. Remove all wires from 91CJ. LMD module 91CJ is removed

from the aircraft.

6. Locate LMD module 91CC. Remove all wires from 91CC. LMD module 91CC is removed from the aircraft.

7. Locate LMD module 91BZ. Remove all wires from 91BZ. LMD module 91BZ is removed

from the aircraft.

8. Locate LMD module 91CB. Remove all wires from 91CB. Module 91CB stays in the aircraft as it will be reused.

9. Locate LMD module 91CG. Remove wires G23151A22, G23145B22, G23146B22, and

G23152A22.

10. Locate LMD module 91CA. Remove all wires from 91CA. Module 91CA is removed from the aircraft.

11. Locate PA connector 10AN. Disassemble connector to gain access to the wires. Locate

conductor G23159A22 (pins 4 & 1) and remove.


12. Locate PA connector 10AM. Disassemble connector to gain access to the wires. Locate

wire G23158A20 and remove at the splice.

13. Referencing sheet 50 of Wiring Diagram 005-W0022-00, take newly fabricated wires G23144B22, G23145B22, and G23143B22, terminate and connect to GBA2 as shown. Route wires following existing harness layout as follows: G23144B22 & G23145B22 are routed to LMD module 91CB. G23143B22 is routed to PA Amp connector 10AN. Reassemble GBA2.


G23146B22 and terminate and connect to GBA3 as shown. Route wire to 91CB following existing harness layout. Reassemble GBA3.

15. For LMD module 91CB: Referencing sheet 50 of Wiring Diagram 005-W0022-00, take

newly fabricated wires G23149A20, G23147A22, and G23148A22, terminate and connect to 91CB as shown. Connect other “91CB wires” from Step 13 to 91CB being careful to allow sufficient wire length for a service loop. Route loose wires as follows: G23147A22 and G23148A22 are routed to LMD module 91CG. G23149A20 is routed to PA connector 10AM following existing harness layout. Reinstall 91CB in its original location if it was removed previously.

16. For LMD module 91CG: Referencing sheet 50 of Wiring Diagram 005-W0022-00, connect

“91CG wires” from Step 15 to 91CG being careful to allow sufficient wire length for a service loop.

17. For 10AN connector: Referencing sheet 50 of Wiring Diagram 005-W0022-00, take wire

G23143B22 and terminate and connect to PA connector 10AN as shown. Reassemble 10AN.

18. For 10AM connector: Referencing sheet 50 of Wiring Diagram 005-W0022-00, take newly

fabricated wire G23149A20 and splice into existing wires as shown. Reassemble 10AM. 19. Reconnect bulkhead connectors GBA2 and GBA3. Reinstall equipment that was removed

in Step 2. 20. Restore power to aircraft. 21. If accomplishment of this installation upgrade is being completed prior to loading the C90

G1000 system software version 0636.02, then proceed to Section 5 of this document and load the C90 G1000 system software version 0636.02. Otherwise if accomplishment of this installation upgrade is being completed after loading the C90 G1000 system software version 0636.02, then no software loading is required if the original equipment is, re-installed in their original positions.


5 Software Upgrade Procedure

5.1 G1000 Software/Configuration Procedure This section will provide instructions for upgrading the C90 G1000 integrated avionics system with G1000 system software version 0636.02. To perform this procedure, the technician must first obtain the correct software image. The software image part number is listed on the Garmin Equipment and Software List found in the General Arrangement Drawing, 005-00375-22 listed in Table 1-1. The General Arrangement Drawing is the certified software definition which is required to be used as a means of verification of software versions and part numbers.

5.1.1 Software Loader Card Creation

1. Create a software loader card per the G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 3.8.2.

5.1.2 G1000 Software and Configuration Procedure

1. Load the G1000 system software version 0636.02 per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 3.9.1 and 3.9.2.

2. Accomplish a final review of the software part numbers and versions numbers with the

PFD No. 1 in configuration mode to confirm the part numbers listed on the system status page match the information in the General Arrangement Drawing listed in Table 1-1. Ensure the status for each LRU is reporting OK. (Reference the G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 3.9.3)

NOTE If problems occur after the software and configuration procedure, consult the G1000/ GFC

700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 5 for troubleshooting procedures.

3. Proceed to Section 6, Reactivation of C90 Airframe Configurations / Options of this

document to load the C90 airframe options.


6 Reactivation of C90 Airframe Options / Configurations This section provides instructions for reactivation of the options and configuration items recorded in Table 1-2 of this document.

6.1 Airframe Configuration This section provides instructions to the load the airframe configuration file that was recorded in Table 1-2. If the King Air C90 – Baseline was recorded in Table 1-2, then no other airframe configuration is required. Proceed to Section 6.2 of this document to load the airframe weight and airspeed configurations.

1. Load the C90 airframe configuration file that was recorded in Table 1-2 per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 3.9.4.1.1.

2. Verify the correct airframe configuration was loaded per G1000/ GFC 700 System

Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 3.9.4.1.2.

6.2 C90 Aircraft Weight and Airspeed Configurations

6.2.1 Aircraft Weight Configuration This section provides instructions to the load the airframe MTOW weight configuration file that was recorded in Table 1-2. If no airframe MTOW weight configuration was recorded in Table 1-2, then no other airframe weight configuration is required. Proceed to Section 6.2.2 of this document to load the airframe airspeed configuration.

NOTE The nomenclature for the airframe weight configuration files have been revised in the C90 G1000 system software version 0636.02. Reference the table below to correlate the nomenclature for the airframe weight configuration files in C90 G1000 system software version 0636.01 with version 0636.02.

Optional Weight Configurations Optional Weight Configurations For Software Version 0636.01 For Software Version 0636.02 and Sub. King Air C90 – Weight LJ 1063-1137, 1146 → King Air C90 – MTOW 9,650 lbs

King Air C90 – 90-206CGW → King Air C90 – MTOW 10,100 lbs

King Air C90 – 05-206CGW → King Air C90 – MTOW 10,350 lbs 1. Load the C90 airframe weight configuration file that was recorded in Table 1-2 per G1000/

GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 3.9.4.2.

6.2.2 Airspeed Configuration This section provides instructions to the load the airspeed configuration file, King Air C90 – Airspeed LJ 1063-1137, 1146. If subject aircraft is a serial number other than LJ-1063 to LJ-1137 and LJ-1146, then proceed to Section 6.3 of this document to load the C90 options.

1. Load the airspeed configuration file, King Air C90 – Airspeed LJ 1063-1137, 1146 per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 3.9.4.2.3.


6.3 C90 Options

6.3.1 Traffic System Option This section provides instructions to enable the traffic system option if previously enabled as recorded in Table 1-2. If the traffic system option is not enabled for subject aircraft, then proceed to Section 6.3.2 of this document to enable the Stormscope (WX-500) option.

1. Enable the traffic system option per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 3.9.4.4.1.

2. Configure the navigation map for the traffic system per G1000/ GFC 700 System

Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 3.9.4.4.2.

6.3.2 Stormscope (WX-500) Option This section provides instructions to enable Stormscope (WX-500) system option if previously enabled as recorded in Table 1-2. If the Stormscope (WX-500) system option is not enabled for subject aircraft, then proceed to Section 6.3.3 of this document to enable the ADF-60 option.

1. Enable the Stormscope (WX-500) system option per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 3.9.4.5.

6.3.3 ADF-60 Option This section provides instructions to enable the ADF-60 option if previously enabled as recorded in Table 1-2. If the ADF-60 system option is not enabled for subject aircraft, then proceed to Section 6.3.4 of this document to enable the DME-42 option.

1. Enable the ADF-60 option per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 3.9.4.6.

6.3.4 DME-42 Option This section provides instructions to enable the DME-42 option if previously enabled as recorded in Table 1-2. If the DME-42 option is not enabled for subject aircraft, then proceed to Section 6.4 of this document to enable the G1000 system configurations.

1. Enable the DME-42 option per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 3.9.4.7.

NOTE If the DME option was configured in the above procedure, the DME channel one audio

level must be adjusted by the procedure contained within Collins DME-42 Transceiver Repair Manual 523-0772458-00611A, Maintenance Section 523-0772460-006118 to adjust DME channel one audio level. Recommended nominal DME audio output level is 4.46 Vpp +0.10 Vpp for aircraft with C90A G1000 System Software Version 0636.02 and subsequent approved versions. Procedure must be accomplished by an approved repair station.


6.4 G1000 System Configurations This section will enable the G1000 system configurations; ChartView, TAWS-B and Aviation Database. Garmin FliteCharts and SafeTaxi are configured by default with the G1000 software. The SafeTaxi database is included on the Terrain/Obstacle database card that is installed in the bottom SD card slot on the PFD 1, PFD 2, and MFD. 6.4.1 ChartView This section provides instructions to enable the ChartView configuration. A ChartView enable card as specified on the General Arrangement Drawing listed in Table 1-1 will be required for this procedure. A ChartView database subscription service must be procured directly from Jeppesen. If not enabling the ChartView configuration, then proceed to Section 6.4.2 of this document to enable the TAWS-B configuration.

1. Load the ChartView configuration per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 3.9.7.

6.4.2 TAWS-B This section provides instructions to enable the TAWS Class B configuration. A TAWS enable card as specified on the General Arrangement Drawing listed in Table 1-1 will be required for this procedure. If not enabling the TAWS-B configuration, then proceed to Section 6.4.3 of this document to enable the aviation database.

1. Load the TAWS-B configuration per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 3.9.8.

6.4.3 Aviation Database This section provides instructions to load the aviation database. An aviation database enable card as specified on the General Arrangement Drawing listed in Table 1-1 will be required for this procedure.

1. Load the aviation database per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 3.9.10.


7 Activation of SVS and GTX 33 ES Configuration Options This section provides instructions for activation of the synthetic vision /pathways (SVS) and GTX 33 extended squitter (ES) transponder optional configuration items new with C90 G1000 system software version 0636.02.

7.1 Synthetic Vision / Pathways Configuration This section provides instructions to enable the synthetic vision/pathways configuration. A synthetic vision/pathways enable card as specified on the General Arrangement Drawing listed in Table 1-1 will be required for this procedure. If not enabling the synthetic vision/pathways configuration, then proceed to Section 7.2 of this document to enable the GTX 33 extended squitter option.

1. Load the synthetic vision/pathways configuration per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 3.9.11.

7.2 GTX 33 Extended Squitter Transponder Option This section provides instructions to enable the GTX 33 ES transponder option if the GTX 33 ES transponder upgrade was accomplished in Section 3.2 of this document. This procedure will enable extended squitter functionality for both transponders.

1. Enable the GTX 33 ES option per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 3.9.4.8.

2. Configure the GTX 33 ES transponders per G1000/ GFC 700 System Maintenance Manual,

Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 3.10.


8 G1000 Equipment Testing 8.1 G1000 Normal Mode

To start the G1000 system in Normal Mode:

1. With a ground power unit connected to the external power receptacle, set the BAT and EXT PWR switches to ‘ON’. The following G1000 equipment is powered:

• PFDs displays & MFD display

• GRS 77 AHRS Units

• GDC 74B Air Data Computers

• GIA 63W Integrated Avionics Units

• GEA 71 Engine/Airframe Units

• GCU 475 FMS Control Unit

• GMC 710 Autopilot Control Unit

2. Set the AVIONICS MASTER switch to ‘ON’. The following G1000 equipment is powered:

• GTX 33 Mode S Transponders

• GMA 1347D Digital Audio Panels

• GDL 69A Datalink Unit

• GSA Servos

• GWX 68 Weather Radar Unit

The G1000 system is now powered in the normal mode. In the normal operating mode, data fields that are invalid have large red X’s through them. A valid field does not display a red X. Allow the displays to initialize for approximately one minute. The GDC 74Bs requires a longer initialization period than do the other LRUs. During normal operation, this causes the airspeed, altitude, vertical speed, and OAT fields to be invalid during the first ~40-60 seconds of PFD power-up.

NOTE

If problems occur after the software and configuration procedure, consult the G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 5 for troubleshooting procedures.

Figure 8-1. Normal Mode


8.2 System Return to Service Procedure This section will provide instructions to accomplish the system return to service procedure after completion of the G1000 system software upgrade to G1000 system software version 0636.02.

1. Accomplish the Backup Path System Testing per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 8.1.

2. Accomplish the GFC 700 Ground Checkout per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 8.2.

8.3 Configuration and Option Functional Checks After the installation of G1000 system software version 0636.02 accomplish the following functional checks for all configurations and options that were enabled in Section 6 of this document.

1. If the traffic system option was enabled in Section 6.3.1 of this document, then accomplish the Traffic System Functional Check per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 7.13.

2. If the Stormscope (WX-500) system option was enabled in Section 6.3.2 of this document,

then accomplish the Stormscope (WX-500) Functional Check per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 7.14.

3. If the TAWS-B option was enabled in Section 6.4.2 of this document, then accomplish the

TAWS Functional Check per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 7.15.

4. If FliteCharts is enabled then accomplish the FliteCharts Functional Check per the G1000/

GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 7.16.

5. If the ChartView option was enabled in Section 6.4.1 of this document, then accomplish the

ChartView Functional Check per the G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 7.17.

6. Accomplish a SafeTaxi Functional Check per the G1000/ GFC 700 System Maintenance

Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 7.18

7. If the DME-42 option was enabled in Section 6.3.4 of this document, then accomplish the

DME Functional Check per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 7.19.

8. If the ADF-60 option was enabled in Section 6.3.3 of this document, then accomplish the

ADF Functional Check per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 7.20.


9. If an optional aircraft weight configuration was enabled in Section 6.2.1 of this document, then accomplish the Aircraft Weight Configuration Functional Check for the aircraft weight configured per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 7.21.

10. If subject aircraft is serial number LJ-1063 to LJ-1137 or LJ-1146 and the optional airspeed

configuration King Air C90 – Airspeed LJ 1063-1137, 1146 was enabled in Section 6.2.2 of this document, then accomplish the Airspeed Test per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 7.6.2.

Aircraft LJ-1063 through LJ-1137, and LJ-1146: Vyse = 107 kts, Vmca = 90 kts, Vs1 = 89 kts.

NOTE If an installation upgrade was accomplished in Section 4 of this document, then correlate the accomplishment the Airspeed Test with the Air Data System Test in Section 8.5.1, Step 6 of this document.

8.4 LRU Upgrade Testing This section will provide testing instructions for the GMA 1347D audio panel and/or GTX 33 extended squitter (ES) transponder upgrade that is outlined in Section 3 of this document. Accomplish the testing requirements for the LRU upgrade option completed for subject aircraft. 8.4.1 GMA 1347D Audio Panel Test Accomplish the following test requirements if the audio panels were upgraded by this document in Section 3.1 to the GMA 1347D audio control panel, PN 011-01257-20. If the GMA 1347D upgrade was not accomplished on subject aircraft this test procedure is not required.

1. Test the No. 1 and No. 2 GMA 1347D audio control panels, PN 011-01257-20 per G1000/

GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 7.2.1.2.

8.4.2 GTX 33 ES Transponder Test Accomplish the following test requirements if the GTX 33 transponders were upgraded by this document in Section 3.2 to the GTX 33 ES transponders, PN 011-00779-30. If the GTX 33 ES transponder upgrade was not accomplished on subject aircraft this test procedure is not required.

1. Test the No. 1 and No. 2 GTX 33 ES transponders, PN 011-00779-30 per G1000/ GFC 700

System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 7.5.2.

8.5 Installation Upgrade Testing

This section outlines testing instructions for the optional installation upgrade to the Vibro-Meter signal conditioner and/or the passenger address system wiring modification accomplished in Section 4 of this document. If the installation upgrades were not accomplished on subject aircraft this test procedure is not required.


8.5.1 Instrument Panel Removal/Replacement System Tests The followings tests are required for all units removed and replaced for any of the installation upgrades accomplished in Section 4 of this document.

1. Test the PFD 1, PFD 2 and MFD per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 7.1.1.

2. Test the No. 1 and No. 2 GMA 1347D per G1000/ GFC 700 System Maintenance Manual,

Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 7.2.1. 3. Test the No. 1 and No. 2 GIA 63W per G1000/ GFC 700 System Maintenance Manual,

Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 7.3.1

4. Test the No. 1 and No. 2 GEA 71 per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 7.4.1

5. Accomplish a Pitot and Static Leak Check per the C90 AMM 34-00-00-201 as referenced

in Table 1-1.

6. Test the Air Data System by accomplishing the following test from the G1000/ GFC 700

System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision:

a. Air Data Test, Section 7.6.1 b. Airspeed Test, Section 7.6.2 (Installer may skip step if accomplished as part of 8.4) c. Static Port Vertical Speed (Rate of Climb) Test, Section 7.6.3

NOTE If subject aircraft is serial number LJ-1063 to LJ-1137 or LJ-1146 and the optional airspeed configuration King Air C90 – Airspeed LJ 1063-1137, 1146 was enabled in Section 6.2.2 of this document, then verify the correct airspeed configuration. See Section 8.3, Step 10 of this document.

7. Test the GDL69A per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 7.8.1.

8. Test the GMC 710 AFCS Controller per G1000/ GFC 700 System Maintenance Manual,

Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 7.11.1. 9. Accomplish the re-installation test for the instrument panel annunciators (Prop Sync and

Standby Battery per G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 6.21.

10. Accomplish a test of the stall warning annunciator by pushing the annunciator and

verifying that the annunciator illuminates.


8.5.2 Engine Signal Condition Test This section will provide instructions for testing the Vibro-Meter signal conditioners that were installed in Section 4.1 of this document. If the Vibro-Meter signal conditioner installation was not accomplished on subject aircraft this test procedure is not required.

1. Test the No. 1 and No. 2 Vibro-Meter signal conditioners per G1000/ GFC 700 System

Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 7.4.1. Verify there are no red Xs displayed on left and right Prop RPM indicators and left and right turbine % RPM indicators.

NOTE If red Xs are displayed on the Prop RPM and turbine % RPM indicators, consult the G1000/ GFC 700 System Maintenance Manual, Model C90A/C90GT King Air, Revision D or later FAA-approved revision, Section 5 for troubleshooting procedures.

8.5.3 Passenger Address System Test This section will provide instructions for testing the passenger address system that was modified in Section 4.2. If the passenger system wiring modification was not accomplished on subject aircraft this test procedure is not required.

1. Verify cabin (PA) speakers do not exhibit a popping sound during initial avionics power up.

2. On pilot’s GMA 1347D, select PA and verify the PA select annunciator is illuminated on the pilot GMA 1347D. Verify COM1 active frequency is displayed white on pilot PFD.

3. On copilot’s GMA 1347D, select PA and verify the PA select annunciator is illuminated on the copilot GMA. Verify COM2 active frequency is displayed white on copilot PFD.

4. Initiate passenger address using pilot’s headset boom microphone by keying the pilots PTT switch on yoke. Verify clear PA audio can be heard over cabin speaker and passenger headsets, PA selected annunciator on pilot GMA 1347D flashes ~ once per second during PA activation. Repeat using pilot hand microphone.

5. Initiate passenger address using copilot’s headset boom microphone by keying the copilots PTT switch on yoke. Verify clear PA audio can be heard over cabin speaker and passenger headsets, PA selected annunciator on copilot GMA 1347D flashes ~ once per second during PA activation. Repeat using copilot hand microphone.


9 Aircraft Logbook Entry The upgrade process for the C90A G1000 is complete. Before returning the aircraft to service, make the appropriate entry in aircraft’s maintenance records, noting that this upgrade has been performed in accordance with STC SA01456WI-D Master Drawing List 005-00375-30 Revision 5.

Record the newly installed G1000/C90A System Software Version in the maintenance records.

Return the aircraft to service in accordance with applicable FAA-requirements.

Verify the required upgrade operating documents are delivered to the aircraft owner or operator (See Section 1.2).

A copy of this procedure should be left with the aircraft records.

Testing Completed By: _________________________________________

(Print Name)

Signature: ________________________________________

Date: _________________________________________