G5000

®

GIFD (EWIS)

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Garmin International, Inc.

Southampton, SO40 9RB, UK

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SECTION ................................................................................................................................. PAGE

1. INTRODUCTION ..................................................................................................................... 1-1

5. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ....................................................... 5-1

6. G5000 EQUIPMENT REMOVAL & REPLACEMENT ............................................................. 6-1

Figure 2-1, G5000 Instrument Panel Layout in the Model 400A Beechjet ................................... 2-1

Figure 3-1, Power Generation Overview ....................................................................................... 3-2

Figure 4-1 - Williams Engine Wiring Schematic ............................................................................ 4-3

Figure 5-1 – Nose Compartment Harness Routing ...................................................................... 5-5

Table Page

Table 1-1, Required Documents ................................................................................................... 1-3

Table 4-1 FADEC EIS Ch A vs. Ch B Separation ......................................................................... 4-1

Table 5-1, Maintenance Intervals .................................................................................................. 5-3

Table 5-2, Nose Equipment Removal ........................................................................................... 5-4

1. INTRODUCTION

1.1 Content, Scope, Purpose

This document provides Instructions for EWIS Continued Airworthiness (ICA) for the Garmin G5000

Integrated Flight Deck with Next Generation hardware including the GFC700 Automatic Flight Control

System (AFCS) as installed in the Beechcraft Model 400A series under Garmin STC ST01821WI for

Williams FJ44-4A engine installations.

This document satisfies the requirements for continued airworthiness as defined by 14 CFR Part 25.1729.

Information in this document is required to maintain the continued airworthiness of the G5000 and to provide

personnel associated with the maintenance, repair and modification of the new or modified EWIS with

sufficient information to accomplish this.

Modification of an aircraft by Supplemental Type Certificate (STC) ST01821WI obligates the aircraft

1.3 Acronyms & Abbreviations

irregularity. Inspection aids, such as mirrors, magnifying lenses or other means may be necessary.

Surface cleaning and elaborate access procedures may be required. A DET can be more than just a

visual inspection, since it may include tactile assessment in which a component or assembly is checked

for tightness/security. It may be necessary for removal of items such as access panels, drip shields,

equipment, etc.

4.3 G5000 EWIS Separation Requirements.

In the cockpit and the nose the following FADEC EIS Channel A data bus cables must be separated by a

minimum of 2 inches from the following FADEC Channel B data bus cables.

4.4 G5000 STC EWIS Inspection Boundaries

FADEC if damaged or removed. The EWIS wiring being modified or added that is routed to the Radio

Junction Box is considered non-critical EWIS wiring because the loss or removal of those signals will not

cause the loss of any critical or essential functions.

The EWIS critical wiring for this STC in the flight deck zone is a combination of newly routed wiring to the

forward pressure bulkhead connectors and the modification of existing wiring from the aft pressure

bulkhead. The changes for this STC for EWIS critical routing in the cabin is limited to the flight deck section

of the cabin. The EWIS critical wiring between the flight deck and aft pressure bulkhead remains

The other EWIS wiring for this STC (oil pressure, oil temperature & fuel flow) is newly routed wiring from

the aft pressure bulk head up to the GEAs for oil temperature. The wiring for oil pressure is newly routed

from the aft pressure bulkhead up through the forward pressure bulkhead to the radio junction box and

back through the forward pressure bulkhead to the GEAs. The wiring for fuel flow is limited to short runs

from the fuel flow signal conditioner to the GEAs in the flight deck zone.

3) 429 bus from Right FADEC channel A to GIA1 and GIA2

4) 429 bus from Right FADEC channel B to GIA1 and GIA2

5.2 Servicing Information