L3 comminications Trilogy ESI-2000 Manual

Pilot’s Guide
for the
Electronic Standby Indicator
Avionics Systems
Model ESI-2000
Software Release 1.x

Pilot’s Guide i
Methods and apparatus disclosed and described herein have
been developed solely on company funds of L-3 Communications
Avionics Systems, Inc. No government or other contractual support
or relationship whatsoever has existed which in any way affects or
mitigates proprietary rights of L-3 Communications Avionics Systems,
Inc. in these developments. Methods and apparatus disclosed
herein may be subject to U.S. Patents existing or applied for. L-3
Communications Avionics Systems, Inc reserves the right to add,
improve, modify, or withdraw functions, design modications, or
products at any time without notice.
L-3 Communications Avionics Systems, Inc.
5353 52nd Street, S.E.
Grand Rapids, MI 49512 USA
Customer Support [phone]
International [phone]
FAX [phone]
www.l-3avionics.com
Pilot’s Guide
Product Part No. 9200-32500-( )
Document Part No. 0040-32500-01
© Copyright 2010 and 2011
L-3 Communications Avionics Systems, Inc.
Trilogy™ is a trademark of L-3 Avionics Systems, inc.
Avionics Systems
Distributed by:

Pilot’s Guideii
Document Precedence
This Pilot’s Guide provides general information about the operation
of the ESI-2000. Refer to your FAA-approved Airplane Flight Manual
(AFM) and its ight manual supplements for information specic to
your aircraft. If there is conicting information between the AFM and
this guide, the AFM takes precedence over this guide.
Export Notice
This technical data has been released into the public domain in
compliance with EAR Part 734.7-11.
Disclaimer
This Pilot’s Guide is subject to change without notice. The illustrations
in this guide are typical to the ESI-2000, but may not exactly match
your conguration options or the latest release of the unit.
A Digital Revolution in Standby Instrumentation
The Trilogy™ Electronic Standby Instrument (ESI) is a panel-
mounted solid-state instrument that provides dependable backup for
attitude, altitude and airspeed information for Part 23/25 Fixed Wing
Aircraft and Part 27/29 Rotorcraft. The Trilogy ESI-2000 replaces
traditional electro-mechanical standby instruments and combines
the information into a compact and easy to read 4” x 3” display. Its
space-saving footprint, easy installation and complete digital design
make it the ideal standby for both new aircraft as well as those
outtted with aging or traditional analog gauges. An internal battery
provides backup power for at least 1 hour. Heading is also available,
when coupled with the optional magnetometer or congured to
receive ARINC 429 Heading , which enables the system to display
heading in a dedicated window.
Revision E Highlights
Incorporate Release 1.2.
Minor corrections.
•
•

Pilot’s Guide iii
Table of Contents
Chapter 1 Description.................................................................................1-1
Introduction..................................................................................................1-1
Software Release ........................................................................................1-2
Specications ..............................................................................................1-3
Optional Equipment.....................................................................................1-6
Limitations ...................................................................................................1-7
Display Elements.........................................................................................1-7
Attitude ........................................................................................................1-7
Slip/skid Indicator ........................................................................................1-9
Indicated Airspeed.......................................................................................1-9
Altitude.......................................................................................................1-13
Heading (Optional) ....................................................................................1-15
Battery .......................................................................................................1-16
Chapter 2 Basic Operation .........................................................................2-1
Introduction..................................................................................................2-1
Menu Operation...........................................................................................2-1
Brightness Adjustment ................................................................................2-2
User Initiated Alignment ..............................................................................2-2
Baro Units Adjustment .................................................................................2-4
Baro Adjustment .........................................................................................2-4
Status Screen..............................................................................................2-5
Battery Capacity Meter Calibration Procedure ............................................2-6
Chapter 3 Operating Instructions................................................................3-1
Introduction..................................................................................................3-1
Power On ....................................................................................................3-1
Self Test.......................................................................................................3-1
Cycle Power Instructions.............................................................................3-1
Power Off ........................................................................................................3-2
System Identication ..................................................................................3-3
Alignment.....................................................................................................3-3
Normal Operation ........................................................................................3-4
Pre-Flight Instructions..................................................................................3-5
Menu Settings..............................................................................................3-5
Instrument Check ........................................................................................3-5
In-Flight Instructions ....................................................................................3-5
In-Flight Screen Examples ..........................................................................3-6
Errors and Invalidities ...............................................................................3-10
Chapter 4.....................................................................................................4-1
Troubleshooting...........................................................................................4-1
Corrective Actions .......................................................................................4-1
Appendix A.................................................................................................. A-1
Record Of Important Information................................................................ A-1
Installation Notes ....................................................................................... A-2

Pilot’s Guideiv
List of Illustrations
Figure 1-1: ESI-2000...............................................................................1-1
Figure 1-2a: MAG-3100..............................................................................1-6
Figure 1-2b: MAG-3000..............................................................................1-6
Figure 1-3: Attitude Elements ...................................................................1-8
Figure 1-4: IAS Elements .......................................................................1-11
Figure 1-5a: IAS Awareness Bar Cues for Part 23 Using Vne .................1-11
Figure 1-5b: IAS Awareness Bar Cues for Part 23/25 Using Vmo ...........1-12
Figure 1-5c: IAS Awareness Bar Cues for Part 27/29 .............................1-12
Figure 1-6: Attitude Elements.................................................................1-14
Figure 1-7: Heading Elements................................................................1-15
Figure 2-1: Bezel Buttons.........................................................................2-1
Figure 2-2: Brightness Adjustment Menu ................................................2-2
Figure 2-3: Alignment Menu.....................................................................2-2
Figure 2-4: Alignment Screens (Not In Flight) ........................................2-3
Figure 2-5: Baro Unit Adjustment Menu ...................................................2-4
Figure 2-6: Baro Adjustment Menu...........................................................2-4
Figure 2-7: Status Menu...........................................................................2-5
Figure 2-8: Example of Status Screen .....................................................2-5
Figure 2-9: Battery Calibration Menu .......................................................2-7
Figure 3-1: Shutdown Menu.....................................................................3-2
Figure 3-2: Example of System ID Screen...............................................3-3
Figure 3-3: Alignment Screen (Not In Flight)............................................3-3
Figure 3-4a: Display Elements for Part 27/29 Aircraft ................................3-4
Figure 3-4b: Display Elements for Part 23/25 Aircraft ................................3-4
Figure 3-5: De-cluttered Display in Extreme Roll ....................................3-6
Figure 3-6: De-cluttered Display in Extreme Pitch ...................................3-6
Figure 3-7: Display Showing Menu Window ............................................3-7
Figure 3-8: Display Ascending Right Bank ...............................................3-7
Figure 3-9: Display Descending Left Bank...............................................3-8
Figure 3-10: Display at 90 degree Descent. ..............................................3-8
Figure 3-11: Display Showing Vmc & Vyse ................................................3-9
Figure 3-12: Display Showing Airspeed with Part 27/29.............................3-9
Figure 3-13 Attitude Loss ........................................................................3-10
Figure 3-14: Airspeed Loss.......................................................................3-12
Figure 3-15: Airspeed Awareness Invalidity..............................................3-12
Figure 3-16: Altitude Loss.........................................................................3-13
Figure 3-17: Align Hold.............................................................................3-14
Figure 3-18: Heading Invalidity (No Mag Input).......................................3-15
Figure 3-19: Heading Invalidity (Mag Failed)...........................................3-15
Figure 3-20 Align Hold (No Mag Input)....................................................3-16
Figure 3-21: Align Hold (Mag Failed)........................................................3-16
Figure 3-22: Heading Invalidity (No 429 Input).........................................3-17
Figure 3-23: Heading Invalidity (Inv 429 Input) ........................................3-17
Figure 3-24: Heading Invalidity (Failed 429) ............................................3-18

ESI-2000
Pilot’s Guide 1-1
Description
Introduction
CHAPTER 1
DESCRIPTION
Refer to Figure 1-1. The ESI-2000 Electronic Standby Indicator is a
panel mounted solid state instrument that provides a visual display of
attitude (pitch & roll), slip/skid indicator, barometric corrected altitude,
indicated airspeed, heading (optional), and battery indications.
The indicator uses an Active Matrix Liquid Crystal Display (AMLCD)
with a nominal diagonal size of 3.7 inches and a resolution of ¼ VGA
(320 X 240 RGB). Flicker free operation is obtained with a 60 Hz
refresh rate combined with a minimum 30 Hz update rate.
A bezel mounted light sensor provides automatic dimming with manual
offset controlled via the menu access mode. Four soft key buttons on
the front of the bezel provide the user with quick access for setting baro
level and units, display and button brightness, and access to menu
options. A replaceable battery assembly provides backup power.
Figure 1-1: ESI-2000

ESI-2000
Pilot’s Guide1-2
Description
Software Release
The following software releases are available for the ESI-2000:
Release 1.0. Original Release.
Release 1.1. Provides a conguration option to choose airspeed
units in either knots or miles per hour and incorporates an
Airspeed Unit Descriptor that is shown on the display to show
which unit type is being used.
Release 1.2. New conguration option to receive heading
information digitally from an external source. New VG mode for
Part 27/29 rotorcraft. New display message to give pilot choice to
perform alignment when a overrate condition is detected. Provide
“wrapping” functionality to non-numeric Menu lists. “Attitude Fail”
is displayed when a problem is detected during alignment instead
of waiting for alignment to complete. Provide customer option for
Static Source Error Correction (SSEC) and Maximum Indicated
Airspeed (Max IAS) functionality set by the factory. Additional
software improvements.
•
•
•

ESI-2000
Pilot’s Guide 1-3
Description
Specications
PHYSICAL
Size: Bezel: 4.03” x 3.35” (10.24 x 8.51 cm)
Chassis: 3-ATI Opening 7.66” (19.45 cm)
Weight: 2.75 Lbs (1.25 kg) MAX
Power: +28.0 VDC nominal,
10.0 W MAX (battery not charging)
22.0 W MAX (battery charging)
+14.0 VDC (with external converter)
Environmental: DO-160F
Software: DO-178B, Level A
Hardware: DO-254, Level A
Certication:
(FAA and EASA)
TSO-C2d (Type B, [Part 23/25] 40 to 400
kts & [Part 27/29] 20 to 350 kts), and for
Release 1.1 [Part 23/25] 46 to 460 mph,
[Part 27/29] 23 to 403 mph), C3e (Type
II, Slip Only), C4c, C6e, C10b (-1,500 to
55,000 ft), C46a, C113, C179.
ETSO-C2d (Type B, [Part 23/25] 40 to 400
kts & [Part 27/29] 20 to 350 kts),
and for
Release 1.1 [Part 23/25] 46 to 460 mph,
[Part 27/29] 23 to 403 mph),
C3d (Type
II, Slip Only), C4c, C6d,C10b (-1,500 to
55,000 ft), C46a, C113, (Non-ETSO Func-
tion: Rechargeable Lithium Battery Cells
and Lithium Batteries in compliance with
UL 1642 + TSO-C179 appendix 1)

ESI-2000
Pilot’s Guide1-4
Description
Specications (Continued)
PERFORMANCE
Attitude: Accuracy: Error less than or equal to
+/-3.0 degrees in pitch and roll with valid
air data.
Airspeed, Tape:
Airspeed, Readout:
Viewable Range:
Release 1.0:
(Part 23/25 Aircraft 0 to 450 kts)
(Part 27/29 Rotorcraft 20 to 350 kts)
Release 1.1 & 1.2:
(Part 23/25 Aircraft 40 to 550 units)
(Part 27/29 Rotorcraft 20 to 550 units)
Viewable Range:
Release 1.0:
Part 23/25 Aircraft 40 to 400 kts.
Part 27/29 Rotorcraft 20 to 350 kts
Release 1.1 & 1.2:
Part 23/25 Aircraft 40 to 400 kts or
46 to 460 mph
Part 27/29 Rotorcraft 20 to 350 kts or
23 to 403 mph
Altitude: Viewable Range:
-2,000 to 56,000 ft. /-610 to 17,000 m.
Heading, Magnetic:
Heading, ARINC 429
Release 1.2
Accuracy: 2 degrees static on ground with
magnetometer.
Accuracy: Within +/- 0.1 degree of head-
ing source.

ESI-2000
Pilot’s Guide 1-5
Description
OPERATION LIMITS
Pitch, Roll, Yaw: All angles.
Pitch, Roll, Yaw Rate +/- 100 degrees/second
+/- 135 degrees/second (release 1.2)
Altitude: Calibrated Range:
-1,500 to 55,000 ft. / -457 to 16,764 m.
BARO: 27.00 to 32.00 inches Hg.
914 to 1083 hPa or mb
Altitude Rate: Up to ± 6,000 ft/min
Airspeed: Calibrated Range:
Release 1.0:
(Part 23/25 Aircraft) 40 to 400 kts
(Part 27/29 Rotorcraft) 20 to 350 kts
Release 1.1 & 1.2:
Part 23/25 Aircraft 40 to 400 kts or
46 to 460 mph
Part 27/29 Rotorcraft 20 to 350 kts or
23 to 403 mph
Longitudinal Axis
Acceleration: +/- 7.5 g
Lateral Axis
Acceleration: +/- 7.5 g
Vertical Axis
Acceleration: +/- 12.0 g
BATTERY PERFORMANCE
Capacity: Typical: >2 hours
Minimum: 1 hour when temperature is
-15°C to +60°C (5°F to +140°F)
Discharge Temp.
Range: -40°C to 60°C (-40°F to +140°F)
Charging Temp.
Range: 0°C to 45°C (+32°F to +113°F)
Specications (Continued)

ESI-2000
Pilot’s Guide1-6
Description
The MAG-3100 and MAG-3000 manufactured by L-3 Avionics Systems are
self contained three-axis magnetometers that provides a three component
measurement of the earth’s magnetic eld. Refer to Figure 1-2 a & b.
If the magnetometer option is used, heading is shown on a tape and digital
readout at the bottom of the display.
Optional Equipment
Figure 1-2a: MAG-3100
Figure 1-2b: MAG-3000
SCHEDULED
MAINTENANCE:
Battery capacity meter requires automated
calibration periodically.
Subject to requirements of FAA document
CFR FAR Part 91.411.
SERVICE LIFE: The indicator has unlimited service life.
The battery has approximately 5 years of
service life; provided that the procedures
for maintenance are followed as detailed
in the Battery Capacity Meter Calibration
Procedure (see page 2-6)
Specications (Continued)

ESI-2000
Pilot’s Guide 1-7
Description
ATTITUDE
Attitude Background (refer to Figure 1-3)
The attitude background is divided into an upper blue sky and lower
brown ground with the horizon line located where the sky and ground
backgrounds meet. The attitude background moves up/down and
clockwise/counter-clockwise around the boresight of the aircraft
reference symbol in relation to the pitch and roll of the aircraft.
Pitch Ladder (refer to Figure 1-3)
The pitch ladder scale is located in the center of the display with short
horizontal lines positioned every +/- 5°, and longer, labeled, lines every
+/- 10°. The pitch ladder rotates around the aircraft reference symbol
in relation to aircraft’s roll and scrolls up and down in response to the
aircraft’s pitch. The scale has a maximum pitch of +/- 80°. A bullseye
is shown at the ±90° position of the pitch ladder.
Red “V” shaped chevrons appear on the pitch ladder when the unit
is placed in extreme pitch (See Figure 3-12 and 3-13). The chevrons
point towards the horizon with the point of the chevron positioned at
35°, 50° and 65° (sky-background) and -25°, -45°, & -65° (ground-
background).
Limitations
When congured to operate with a magnetometer for heading reference
input; the use of heading is not authorized to operate in the following
polar regions due to magnetic eld unsuitability:
North of 70° N latitude
South of 70° S latitude
North of 65° N latitude between 75° and 120° W longitude
(northern Canada)
South of 55° S latitude between 120° and 165° E longitude (south
of Australia and New Zealand)
Attitude and air data information is still usable. It is recommended
that the magnetometer power be removed in these geographic
areas.
•
•
•
•
Display Elements

ESI-2000
Pilot’s Guide1-8
Description
Display Elements (continued)
Figure 1-3: Attitude Elements
ATTITUDE (continued)
Roll Indicator (refer to Figure 1-3)
The roll indicator consists of a roll scale and a roll pointer. The white
scale lines are set at +/- 10, 20, 30, 45, and 60 degree tick marks with a
downward white triangle representing the 0° mark. The roll pointer is an
upward pointing triangle located on the inner arc radius of the roll scale.
Conguration Options: If the roll pointer is congured for xed the roll
scale rotates around the aircraft reference symbol boresight and has a roll
angle range of ±180°. If the roll pointer is congured for rotating the roll
pointer rotates around the aircraft reference symbol boresight and has a
roll angle range of ±180°.
Aircraft Reference Symbol (refer to Figure 1-3)
Located in the center of the attitude display, the aircraft reference
symbol is a xed square boresight with L-shaped “wings” to each side
of the boresight. The symbol provides a xed reference as compared to
the attitude background, pitch ladder, and roll indicator to determine the
aircraft’s pitch and roll attitude. The aircraft is at zero-degree pitch when
the intersection of the blue (sky) and brown (ground) articial horizon
intersects the boresight .

ESI-2000
Pilot’s Guide 1-9
Description
Airspeed Tape (refer to Figure 1-4)
The IAS tape is located on the left side of the display. The tape scrolls up
as aircraft speed decreases and scrolls down as aircraft speed increases.
The tape has a viewing span of 60 units.
Conguration Option: The tape background may be either clear or gray.
Release 1.0. The major tick marks are located every 10 kts from 0 to
450; minor tick marks at the midpoint between the major tick marks, and
numbered digits every 20 kts from 0 to 440.
Release 1.1 & 1.2. For Part 23/25 xed wing aircraft the major tick marks
at airspeed values of 10 (kts or mph) from 40 to 550 (kts or mph); minor
tick marks at the midpoint between the major tick marks, and numbered
digits every 20 (kts or mph) from 40 to 540 (kts or mph).
Release 1.1 & 1.2. For Part 27/29 rotorcraft the major tick marks at airspeed
values of 10 (kts or mph) from 20 to 550 ( kts or mph ); minor tick marks at
the midpoint between the major tick marks, and numbered digits every 20
(kts or mph) from 20 to 540 (kts or mph). The calibrated range of the tape is
from 20 to 350 kts (23 to 403 mph).
Slip/Skid Indicator (refer to Figure 1-3)
The indicator has a black background with a white border. A Slip/Skid
indicator ball is positioned in the center of the indicator scale between two
vertical lines. The Slip/Skid indicator has a range of ±7°.
The Slip/Skid indicator has two possible locations described below:
If the ESI-2000 is congured for a magnetometer, then the
indicator is located above the heading tape to the left of the
heading digital readout.
If the ESI-2000 is not congured for a magnetometer, then the
indicator is located at the bottom-center of the ESI-2000 display.
•
•
SLIP/SKID INDICATOR
INDICATED AIRSPEED
Airspeed Units Descriptor (refer to Figure 1-4)
Release 1.1 & 1.2. The Airspeed Units descriptor is located in the
lower left corner of the display. The descriptor indicates the units being
displayed on the airspeed tape and readout.
Conguration Option: The descriptor may be either “KTS” (knots) or
“MPH” (miles per hour).

ESI-2000
Pilot’s Guide1-10
Description
A irspeed Awareness Color Bar (refer to Figure 1-4 and 1-5 a, b, & c)
The airspeed awareness color bar is located along the left side of the
indicated airspeed tape. The color bar indicates critical reference airspeeds
and operating ranges specic to the aircraft.
Part 23/25 Aircraft
Conguration Option: Airspeed Awareness Color Bar may be congured
for V
NE
(cues - V
NE
, V
NO
, Vfe , Vs1 , Vs0 )or V
MO
(cues - V
MO
, Vfe , Vs1 , Vs0 )
aircraft. In addition Vmc and Vyse may be set up for twin-engine applications.
NOTE
For part 25 Aircraft the Airspeed Awareness Color Bar must
be congured for V
MO
Cues Vfe , Vs1 , Vs0 , Vmc and Vyse may be congured off.
Part 27/29 Rotorcraft
Airspeed Awareness Color Bar may be congured for VNE Power On,
VNE Power Off and VCAUTION (the start of the caution range for airspeed warning).
Cues VNE Power On and VCAUTION may be congured off.
INDICATED AIRSPEED ( continued )
Airspeed Digital Readout (refer to Figure 1-4)
The odometer styled IAS digital readout is located in the center of the
airspeed tape and displays the current aircraft speed in knots.
Release 1.0. The readout has a viewing range of 40 to 400 kts for Part
23/25 aircraft and 20 to 350 kts for Part 27/29 rotorcraft.
Release 1.1 & 1.2. The readout has a viewing range of 40 to 400 kts (46 to
460 mph). For Part 27/29 Rotorcraft the readout has a viewing range of 20
to 350 kts (23 to 403 mph).

ESI-2000
Pilot’s Guide 1-11
Description
Figure 1-5a: IAS Awareness Bar Cues for Part 23 Aircraft using Vne
Figure 1-4: IAS Elements
INDICATED AIRSPEED (Continued)

ESI-2000
Pilot’s Guide1-12
Description
Figure 1-5b: IAS Awareness Bar Cues for Part 23/25 Aircraft using Vmo
Figure 1-5c: IAS Awareness Bar Cues for Part 27/29 Rotorcraft
INDICATED AIRSPEED (Continued)

ESI-2000
Pilot’s Guide 1-13
Description
ALTITUDE
Altimeter Tape (refer to Figure 1-6)
The baro-corrected altitude tape is located on the right side of the display.
The tape scrolls up as aircraft altitude decreases and scrolls down as aircraft
altitude increases. Tick marks are shown every 100 feet and numbered digits
every 500 feet. The tape has a maximum viewable altitude of 1000 feet and
can go as low as -2000 feet and as high as 56,000 feet.
Conguration Option: The tape background may be either clear or gray.
Barometric Pressure Window (refer to Figure 1-6)
Located at the top right of the display screen. The value shown is used by
the indicator to determine the current altitude.
Conguration Option: The baro digits may be white, cyan, or green on a
black background.
The units shown in the window can be changed using the menu screen and
has three settings: “in. Hg”, “hPa” and “mb”. The barometric (baro) pressure
ranges and standard values are shown in the table below:
Unit Standard Value Lowest Value Highest Value
In. Hg 29.92 27.00 32.00
hPa 1013 914 1083
mb 1013 914 1083

ESI-2000
Pilot’s Guide1-14
Description
ALTITUDE (Continued)
Altitude Digital Readout (refer to Figure 1-6)
The odometer styled digital readout is located in the center of the altitude
tape and display’s the current baro-corrected altitude in feet above mean sea
level (MSL). The readout can show a minimum of - 2000 feet and maximum
of 56,000 feet. A left justied minus sign “-” is shown when altitude is less
then zero.
Figure 1-6: Attitude Elements
Metric Digital Readout (refer to Figure 1-6)
Conguration Option: The Metric Altitude Digital Readout may be congured
ON or OFF.
The Metric Digital Readout is located on the right side of the display
beneath the odometer styled Altitude Digital Readout. The readout has a
black background surrounded by a white box with medium white digits. The
readout provides baro-corrected altitude in meters and has a range of -610
to 17,070 meters. A left justied minus sign “-” is shown when altitude is less
than zero.