Garmin G5000 NG - Beechcraft Model 400A (Beechjet) Owner's manual

G5000

®

GIFD (EWIS)

System Maintenance Manual

Beechcraft Model 400A

Contains Instructions for

Continued Airworthiness

for STC ST01821WI

Document Number:

190-01508-E1 Rev. 1

G5000 EWIS Maintenance Manual 190-01508-E1

Beechcraft Model 400A Rev. 1

Page ii

Garmin Ltd. or its subsidiaries

Except as expressly provided herein, no part of this manual may be reproduced, copied,

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without the express prior written consent of Garmin. Garmin hereby grants permission to

download a single copy of this manual and of any revision to this manual onto a hard drive or

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contain the complete text of this copyright notice and provided further that any unauthorized

commercial distribution of this manual or any revision hereto is strictly prohibited.

Garmin International, Inc.

1200 E. 151

st

Street

Olathe, KS 66062 USA

Telephone: 913-397-8200

www.garmin.com

Garmin (Europe) Ltd.

Liberty House

Bulls Copse Road

Hounsdown Business Park

Southampton, SO40 9RB, UK

Phone: +44 (0) 23 8052 4000

Fax: +44 (0) 23 8052 4004

RECORD OF REVISIONS

Revision

Revision Date

Description

ECO #

1

07/11/2018

Initial release of EWIS ICA for Williams Engines

------

G5000 EWIS Maintenance Manual 190-01508-E1

Beechcraft Model 400A Rev. 1

Page iii

DOCUMENT PAGINATION

Section

Pagination

Table of Contents

i ˗˗ iii

Section 1

1-1 ˗˗ 1-5

Section 2

2-1 ˗˗ 2-2

Section 3

3-1 ˗˗ 3-2

Section 4

4-1 ˗˗ 4-3

Section 5

5-1 ˗˗ 5-27

Section 6

6-1 ˗˗ 6-4

G5000 EWIS Maintenance Manual 190-01508-E1

Beechcraft Model 400A Rev. 1

Page iv

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.

G5000 EWIS Maintenance Manual 190-01508-E1

Beechcraft Model 400A Rev. 1

Page v

TABLE OF CONTENTS

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

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

1.1 Content, Scope, Purpose ................................................................................................. 1-1

1.2 Organization ..................................................................................................................... 1-2

1.3 Acronyms & Abbreviations ............................................................................................... 1-3

1.4 Definitions ........................................................................................................................ 1-3

1.5 Publications ...................................................................................................................... 1-3

1.6 Revision and Distribution ................................................................................................. 1-5

2. SYSTEM DESCRIPTION ......................................................................................................... 2-1

3. ELECTRICAL POWER DISTRIBUTION .................................................................................. 3-1

4. INSPECTION DETAILS ........................................................................................................... 4-1

4.1 GVI (General Visual Inspection) ...................................................................................... 4-1

4.2 DET (Detailed Inspection) ................................................................................................ 4-1

4.3 G5000 EWIS Separation Requirements. ......................................................................... 4-1

4.4 G5000 STC EWIS Inspection Boundaries ....................................................................... 4-1

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

5.1 Airworthiness Limitations ................................................................................................. 5-1

5.2 Servicing Information ....................................................................................................... 5-2

5.3 Maintenance Intervals ...................................................................................................... 5-3

5.4 Maintenance Tasks .......................................................................................................... 5-4

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

6.1 GDU 1250W Display Unit................................................................................................. 6-1

6.2 GIA 64E Integrated Avionics Unit .................................................................................... 6-1

6.3 GSD 41 Data Concentrator .............................................................................................. 6-2

6.4 GMA 36B Audio Processor .............................................................................................. 6-3

6.5 GEA 7100 Engine and Airframe Unit ............................................................................... 6-3

6.6 GTX 3000 Transponder ................................................................................................... 6-4

Figures

Figure Page

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

Tables

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

G5000 EWIS Maintenance Manual 190-01508-E1

Beechcraft Model 400A Rev. 1

Page vi

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

Table 5-3, LH Forward PBH Nose Harness .................................................................................. 5-6

Table 5-4, RH Forward PBH Nose Harness ............................................................................... 5-11

Table 5-5, Flight Deck Equipment Removal ............................................................................... 5-16

Table 5-6, LH Flight Deck Harness ............................................................................................. 5-17

Table 5-7, RH Flight Deck Harness ............................................................................................ 5-22

G5000 EWIS Maintenance Manual 190-01508-E1

Beechcraft Model 400A Rev. 1

Page 1-1

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.

Any changes to EWIS by subsequent follow-on STCs must be shown to comply with 25.1711 of Title 14 of

the Code of Federal Regulations.

1.1.1 Applicability

This document applies to all Beechcraft Model 400A series aircraft equipped with the G5000 and GFC700

AFCS systems and Williams FJ44-4A engines. The information herein supplements and supersedes the

Sierra Industries ATSI Report 194-806 only in those areas presented in this document.

This document is not applicable to any Beechcraft Model 400A series aircraft that is equipped with

the Pratt and Whitney JT15D-5 engines.

The EWIS Instructions for Continued Airworthiness are only applicable to the G5000 Integrated Flight Deck

as installed in the Beechjet Model 400A with Williams FJ44-4A engines in accordance with Garmin STC

ST01821WI and Sierra Industries STC ST02538LA, and only in the following areas:

• G5000 wiring for FADEC EIS (N1, N2, and ITT) display inputs, new EWIS:

o Wiring from FADEC in-line connectors J767 and J768 located in the cockpit, through fwd

PBH connectors, to GIA 64E units located in the nose compartment

• G5000 air data outputs to the FADEC (PRI and SEC), new EWIS:

o Wiring from both the GIA 64E and GDC 7400 units located in the nose compartment to

forward PBH connectors

• Sierra Industries wiring, existing EWIS (altered by Garmin):

o FADEC EIS display input wiring secured near FADEC in-line connectors P767 and P768

and instrument panel shelf

o FADEC air data wiring (PRI and SEC) re-terminated at the forward PBH to accommodate

the G5000 installation

• Sierra Industries wiring, existing EWIS (altered by Garmin):

o Engine Oil Temperature wiring routed from aft bulk head to GEAs in lieu of dedicated Oil

Temp/Pressure Indicator.

o Engine Oil Pressure wiring routed from aft bulk head through forward bulkhead to Radio

Junction Box and then back through forward bulkhead to GEAs in lieu of dedicated Oil

Temp/Pressure Indicator.

o Engine fuel flow wiring routed from fuel flow signal conditioner to GEA in lieu of dedicated

fuel flow indicator.

G5000 EWIS Maintenance Manual 190-01508-E1

Beechcraft Model 400A Rev. 1

Page 1-2

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

operator to include the information, provided by this document, in the operator’s Aircraft Maintenance

Manual and the operator’s Aircraft Scheduled Maintenance Program.

1.2 Organization

This manual is structured as described below:

Section 2: G5000 System Description & Operation

A brief overview of the G5000 and GFC 700 system interface is provided.

Section 3: Electrical Power Distribution

High level description of the Beechjet 400A power system.

Section 4: EWIS Inspection Definition

Provides instructions for the EWIS inspection.

Section 5: Instruction for Continued Airworthiness

Presents inspection requirements and intervals for new or altered G5000 EWIS wiring affected by the

G5000 installation.

Section 6: Equipment Removal & Replacement

Provides instructions for the removal and replacement of G5000 and GFC700 equipment.

G5000 EWIS Maintenance Manual 190-01508-E1

Beechcraft Model 400A Rev. 1

Page 1-3

1.3 Acronyms & Abbreviations

AC: Advisory Circular

AFCS: Automatic Flight Control System

AFM: Airplane Flight Manual

AFMS: Airplane Flight Manual Supplement

CFR: Code of Federal Regulations

DET: Detailed Inspection

EAU: Engine/Airframe Unit

EWIS: Electrical Wiring Interconnection System

EZAP: Enhanced Zonal Analysis Procedure

FAA: Federal Aviation Administration

FADEC: Full Authority Digital Electronic Control

GIFD: Garmin Integrated Flight Deck

GVI: General Visual Inspection

ICA: Instructions for Continued Airworthiness

ITT: Interstage Turbine Temperature

LRU: Line Replaceable Unit

MFD: Multi-Function Display

MFW: Multi-Function Window

MM: Maintenance Manual

N1: Low pressure Rotor Group Shaft Speed (Engine Fan Speed)

N2: High pressure Rotor Group Shaft Speed (Compressor Fan Speed)

NG: Next Generation

OAT: Outside Air Temperature

PBH: Pressure Bulkhead

PFD: Primary Flight Display

PRI: Primary

RAT: Ram Air Temperature

SEC: Secondary

STC: Supplemental Type Certificate

1.4 Definitions

Critical Wiring - Critical wiring, for the purposes of this EWIS ICA, is the wiring between the FADECs

and GIAs and GDCs that can impact the flight critical essential functions of displaying N1,

N2 and ITT indications.

Non–Critical Wiring - Non-critical wiring for this STC (oil pressure, oil temperature & fuel flow), is the

wiring that supports essential non-flight critical engine secondary display functions.

1.5 Publications

The following documents are required by this maintenance manual to perform maintenance. It is the

responsibility of the owner / operator to ensure the appropriate version of these documents are used during

operation and while servicing or conducting maintenance on the airplane.

Table 1-1, Required Documents

Document Number

Document Title

005-00756-00

Master Drawing List, G5000/GFC 700, Beechjet 400A

G5000 EWIS Maintenance Manual 190-01508-E1

Beechcraft Model 400A Rev. 1

Page 1-4

Document Number

Document Title

005-00756-N2

General Arrangement, G5000 GIFD &GFC 700, Beechcraft Model 400A

005-00756-05

Wire Harness Routing/Inst, Nose, Beechjet Model 400A

005-00756-06

Wire Harness Routing, Cabin, Beechjet Model 400A

005-00756-08

Nose Avionics Install, Beechjet Model 400A

005-00756-09

Main Instrument Panel Install, Beechjet Model 400A

005-00756-47

Radio Junction Box Modification Beechjet Model 400A

005-00756-10

Circuit Breaker Panels Modification, Beechjet 400A

005-00756-19

Pedestal Equipment Install, Beechjet Model 400A

005-00756-46

Console Panel Beechjet Model 400A

005-00756-60

Wire Harness Routing/Inst, Cabin Beechjet Model 400A, Older S/N

005-00756-95

Wire Harness Routing/Inst, Nose Beechjet Model 400A, Older S/N

005-00756-D2

Circuit Breaker Panels Modification, Early S/N Beechjet Model 400A

005-W0230-01

Wiring Diagram, G5000/GFC 700, Beechjet Model 400A, NG Late S/N

005-W0236-01

Wiring Diagram, G5000/GFC 700, Beechjet Model 400A, NG Early S/N

320-01225-XX

Wire Harness Assembly Beechjet Model 400A, NG

320-01226-XX

Wire Harness Assembly Beechjet Model 400A, NG Early S/N

128-590001-9

Beechjet Model 400/400A Maintenance Manual*

*Non-Garmin Document

ASTM F2799-14

Standard Practice for Maintenance of Aircraft Electrical Wiring Systems

Sierra Industries, Ltd.

ATSI Report No. 194-

806

Sierra Industries, Ltd Instructions for Continued Airworthiness (ICA) for the

Electrical Wiring Interconnection Systems (EWIS) Hawker Beechcraft 400A

with the Williams FJ44-4A FADEC Engines

Sierra Industries, Ltd.

ATSI Report No. 194-

801

400A RE-ENGINE Instructions for Continued Airworthiness

Sierra Industries

SI510-964

Left and Right Engine FADEC Annunciators/Switches Hawker 400

Sierra Industries

SI510-965

Left and Right Engines Engine Instruments Hawker 400

Sierra Industries

SI510-968

Air Data Computers Right and Left Engine Hawker 400

Sierra Industries

SI510-805

Cabin Electrical Installation Hawker 400

G5000 EWIS Maintenance Manual 190-01508-E1

Beechcraft Model 400A Rev. 1

Page 1-5

Generic installation manuals for individual Garmin LRUs are also available through the ‘Dealer Resource

Center’ section of the Garmin web site; refer to Section 1.6 for details.

1.6 Revision and Distribution

This document is required for maintaining the continued airworthiness of the aircraft. When this document

is revised, each page will also be revised to indicate the current revision level.

Garmin Dealers may obtain the latest revision of this document on the Garmin Dealer Resource Center

website.

Owners/operators may obtain the latest revision of this document by one of the following methods:

• Visit https://fly.garmin.com/support

• Contact a Garmin dealer

• Contact Garmin Product Support at 913-397-8200, toll free 866-739-5687, or use around the world

contact information on https://fly.garmin.com/

A Garmin Service Bulletin describing the revision to this document will be sent to aircraft owners and

operators if the revision is determined to be significant.

G5000 EWIS Maintenance Manual 190-01508-E1

Beechcraft Model 400A Rev. 1

Page 2-1

2. SYSTEM DESCRIPTION

This section provides an overview of the G5000 GIFD that is installed in accordance with STC ST01821WI

on those Beechcraft Model 400A that are equipped with Williams FJ44-4A FADEC engines.

The installation incorporates three high-resolution 12-inch flight displays, along with two touch screen

display/controllers that serve as the primary crew interface for the system. The landscape oriented flight

displays have multi-pane capability that allow essential flight data to be displayed with electronic maps &

charts, TAWS, TCAS, flight plan and weather information on multiple flight display windows simultaneously.

A GMC 7250 autopilot controller and GCU 275 Display controller are installed above the MFD and both

PFDs respectively. A 3-in-1 digital standby instrument (Mid Continent Instruments Model MD302) is

installed beneath the MFD, along with the relocated fuel quantity indicators. The forward pedestal transition

panel includes two GTC 575 touch-screen controllers. A new display format and dimming panel and

miscellaneous switch panel is installed in the aft pedestal. There are additional modifications to the

electrical power distribution system, overhead dimming panel and circuit breaker panels. Refer to Figure

2-1 for the instrument panel layout.

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

Engine indications are normally shown on the MFD engine indicating window or on the PFD during display

reversion mode, except as noted in the list below. There are no changes in engine gauge limits or markings

with the implementation of the G5000; engine gauge limits are incorporated based on existing AFM/AFMS

limitation data from the Sierra STC.

Gauges/indicators removed and incorporated into the G5000 are as follows:

• ITT

• N1 fan

• N2 turbine

• Oil pressure

• Oil temperature

• Fuel flow

• Fuel temperature

• Consumed fuel totalizer

G5000 EWIS Maintenance Manual 190-01508-E1

Beechcraft Model 400A Rev. 1

Page 2-2

The ITT, N1 and N2 display data is supplied by ARINC 429 data from the engine FADECs. The oil pressure,

oil temperature, fuel flow and fuel temperature are supplied from dedicated sensors installed in the engines

and in the right wing fuel tank for the fuel probe.

G5000 EWIS Maintenance Manual 190-01508-E1

Beechcraft Model 400A Rev. 1

Page 3-1

3. ELECTRICAL POWER DISTRIBUTION

The Beechcraft Model 400A aircraft incorporates three electrical power systems: the DC electrical system,

the AC electrical system, and the standby power system. The DC electrical system consists of generators,

a power distribution system, a battery system and an external power system. The AC electrical system

consists of two inverters and a power distribution system. The standby power system consists of a battery

and an ON / ARM / OFF switch. The core electrical generation and distribution system is unchanged from

the original aircraft design by this STC.

Left and Right Main Buses: The left and right main buses receive power from their respective left and right

generators. These buses are the distribution bus for their respective generators.

Start Bus: The start bus provides power distribution for the battery or for external power.

Battery Charge Bus: The battery charge bus acts as a connection bus for al DC power.

Left and Right Load Buses: The left and right load buses receive power from the primary distribution system

through sets of three feeder cables which are protected by circuit breaker. In each set, only two feeder

cables are active, while the third is considered a standby feeder. The system incorporates a Load Bus Tie

circuit which under normal conditions connects the two load buses together.

Left and Right Nonessential Buses: The left and right nonessential buses receive power from their

respective left and right load buses. The nonessential buses are connected to the load buses by toggle-

switch type circuit breakers located on the main circuit breaker panel.

Left and Right Radio Buses: The left and right radio buses receive power from their respective left and

right load buses. The radio buses are connected to the load buses by toggle-switch type circuit breakers

located on the main circuit breaker panel just forward of the non-essential circuit breakers.

Left and Right Overhead Buses: The left and right overhead buses receive power from their respective left

and right load buses. The overhead buses are protected by push-pull type circuit breakers which are also

located on the main circuit breaker panel.

Emergency Bus: The emergency bus provides power from the main battery to a set of essential equipment

via circuit breakers. With the battery switch in the EMER position a set of essential equipment is isolated

to the main battery.

Standby Battery Bus: The standby battery bus provides power to the standby instrument from a standby

battery in the event of failure of all other electrical sources.

Hot Battery Bus: The hot bus is connected directly to the battery via a circuit breaker. This bus is used to

power systems for the ground comm function.

G5000 EWIS Maintenance Manual 190-01508-E1

Beechcraft Model 400A Rev. 1

Page 3-2

Figure 3-1, Power Generation Overview

G5000 EWIS Maintenance Manual 190-01508-E1

Beechcraft Model 400A Rev. 1

Page 4-1

4. INSPECTION DETAILS

4.1 GVI (General Visual Inspection)

A stand-alone GVI is an inspection that is performed separately from the regularly scheduled GVI and

focuses on specific electrical wiring or components. A zonal analysis GVI is an inspection that is regularly

scheduled for an entire zone and each of its systems and structures are inspected all at once.

4.2 DET (Detailed Inspection)

A DET is an intensive examination of a specific item, installation, or assembly to detect damage, failure or

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.

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

Cockpit

FADEC EIS Channel A – Wire ID

FADEC EIS Channel B – Wire ID

1E791B22

2E791B22

G1E791C22

G2E791C22

1E792B22

2E792B22

G1E792C22

G2E792C22

Nose

FADEC EIS Channel A – Wire ID

FADEC EIS Channel B – Wire ID

G1E791D22

G2E791D22

G1E791E22

G2E791E22

G1E792D22

G2E792D22

G1E792E22

G2E792E22

4.4 G5000 STC EWIS Inspection Boundaries

This document contains detailed inspection requirements for EWIS in the nose zonal section, the flight

deck section and the cabin section. The wiring was either added as new or modified from the previous

EWIS routing.

The EWIS wiring in the nose zone is newly routed from the forward pressure bulkhead connectors to the

GIAs, GDCs and Radio Junction Box. The wiring between the FADECs and GIAs and GDCs is described

as EWIS critical wiring in this document because it could possibly impact the critical functions of the

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

G5000 EWIS Maintenance Manual 190-01508-E1

Beechcraft Model 400A Rev. 1

Page 4-2

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

unchanged from the previous Sierra STC installation.

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.

All previous Sierra STC EWIS wiring installed in locations other than the nose section and flight deck

section is unaltered and the inspection requirements in Sierra document 194-806 EWIS ICA remain

effective.

Figure 4-1 shows the EWIS wiring added or modified by this STC.

The solid purple wiring shown in Figure 4-1 indicates the EWIS critical wiring added / modified by this STC:

1) 429 bus from Left FADEC channel A to GIA1 and GIA2

2) 429 bus from Left FADEC channel B to GIA1 and GIA2

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) 429 bus from #1 GDC to Left and Right FADEC

6) 429 bus from #2 GDC to Left and Right FADEC

7) 429 bus from GIA1 to Left and Right FADEC

8) 429 bus from GIA2 to Left and Right FADEC

The dashed purple wiring shown in Figure 4-1 indicates the EWIS non-critical wiring added / modified by

this STC.

1) Left Oil Temperature wiring to GEA #1 routes from aft pressure bulkhead.

2) Right Oil Temperature wiring to GEA #2 routes from aft pressure bulkhead.

3) Left Oil Pressure wiring to GEA #1 (routes from aft PBH through fwd PBH and back to GEA #1)

4) Right Oil Pressure wiring to GEA #2 (routes from aft PBH through fwd PBH and back to GEA #2)

5) Fuel Flow wiring to GEA #1 and GEA #2 from Fuel Flow Signal Conditioner

A minimum of 2 inches separation must be maintained between the FADEC A and the FADEC B wiring to

GIA1 and GIA2 unless the items are rigidly held apart so that it is not possible to force the separated items

together without excessive force.

Note:

EWIS identification methods and details are provided within the Garmin wiring diagrams and harness

assembly drawings provided in Section 1.6.

.

G5000 EWIS Maintenance Manual 190-01508-E1

Beechcraft Model 400A Rev. 1

Page 4-3

*WILLIAMS FJ44-4A ENGINES INTERFACE DETAIL

#2 GIA 64E

#1 GIA 64E

L FADEC

CHA CHB

R FADEC

CHA CHB

From

#1 GDC

From

#2 GDC

429

#1 GEA 7100

#2 GEA 7100

485

To

#2 GSD

To

#1 GSD

PC920 SIGNAL

CONDITIONER

L Oil TEMP

L Oil Pressure

L Fuel Flow Sensor

R Oil TEMP

R Oil Pressure

R Fuel Flow Sensor

Garmin Eqmt

Standard

Non-Garmin Eqmt

Standard

Non-Garmin Eqmt

Optnl, as installed

Non-Garmin Eqmt

Standard (added)

429

Dashed purple line indicates other EWIS Wiring

Solid purple line indicates EWIS Critical Wiring

Dashed magneta line indicates RS-485 bus and is not EWIS

Figure 4-1, Williams Engine Wiring Schematic

G5000 EWIS Maintenance Manual 190-01508-E1

Beechcraft Model 400A Rev. 1

Page 5-2

5.2 Servicing Information

5.2.1 Replacement Times

There is no EWIS mandatory replacement time.

IMPORTANT

It is impossible to provide guidance for every conceivable failure

scenario within the scope of this manual. Every effort has been

made to provide comprehensive guidance for possible failures.

The information in this document should always be combined

with sound aviation maintenance practices and a thorough

knowledge of the system. Use sound avionics maintenance

practices when working around or on G5000 equipment.

5.2.2 Required Tools

The following tools are needed to perform maintenance tasks on G5000 equipment:

• #2 Non-Magnetic Phillips Screwdriver

• 3/32”, 7/64” 3/16”, Hex drive tool

• Standard sockets & wrenches

5.2.3 Special Tools

None

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Garmin G5000 NG - Beechcraft Model 400A (Beechjet) Owner's manual

Garmin G5000 NG - Beechcraft Model 400A (Beechjet) Owner's manual

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