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
© Copyright 2018
Garmin Ltd. or its subsidiaries
All Rights Reserved
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
429
429
429
429
429
#1 GEA 7100
#2 GEA 7100
485
485
485
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
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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