Technical Specification SAGEM ICDS-10 - Styles & Scribbles

Technical Specification
SAGEM ICDS-10
GENERAL OVERVIEW
The SAGEM ICDS-10 interfaces with aircraft systems to provide a
centralized display for integration, computation, and control. The
ICDS-10 displays information in alphanumeric text and graphic
formats to provide enhanced situational awareness, increased
fl ight safety and effi ciency, and a reduced pilot workload.
Depending on the confi guration, the ICDS-10 can function as a
Multi-Function Display (MFD), Primary Flight Display (PFD), Engine
Monitoring System (EMS), Navigation Display (ND), or a combination
of those displays.
PHYSICAL
Height: 8.00 in. (20.96 cm)
Width: 10.75 in. (29.21 cm)
Depth: 2.75 in. (8.92 cm)
Weight: 6.1 lb (2.76 kg)
Mounting of the ICDS-10 is compatible with DZUS systems. The
above dimensions are for the panel-mount inset; see reverse for
panel cutout and face dimensions.
CONTROL DISPLAY UNIT
Unit: Factory-confi gured, fully self-contained control
display unit (CDU)
Display Type: Color active matrix liquid crystal display (AMLCD)
Features: Optical compensation, anti-glare, full sunlight
readability
Display Area: Diagonal: 10.4 in. (26.4 cm)
Resolution: 100 dots per inch
Mount: Panel mount, vertical or horizontal
Connections: 100-pin MIL-SPEC connector (included)
Controls: 11 line-select keys
Indicators: Power-on light, on-screen indicators
Other: Front-accessible data card
POWER
Voltage: 10 to 35 Vdc
Consumption: 18W normal operating mode; 70W maximum (in cold
conditions with all heaters turned on)
CERTIFICATIONS & ENVIRONMENT
FAA TSOs: C113 – Airborne Multipurpose Electronic Display;
C8d Type C – Vertical Velocity Instruments (Rate-of-Climb); C2d Type
C – Airspeed Instruments; C10b Type II – Altimeter, Pressure Actuated,
Sensitive Type, or later revisions; C43c Class IIIa – Temperature
Instruments; C44b – Fuel Flowmeters; C47 – Pressure Instruments -
Fuel, Oil, and Hydraulic
RTCA/DO-178B – Software Considerations in Airborne Systems and
Equipment Software
RTCA/DO-160D – Environmental Conditions and Test Procedures for
Airborne Equipment: [B2]BAB[RG]XXXXXXZZAZZWM[XXE3]XXA
Summary of Environmental Conditions and Test Procedures:
Condition Category Description
Temperature, In-Flight
Loss of Cooling,
Altitude, Decompression,
Overtemperature
B2 Operating Temperature: -55 to +70°C
Storage Temperature: -55 to +85°C
No external cooling required
Altitude: to 25,000’ above sea level
Decompression: 8000 to 25,000’ in 15s
Overpressure: -15,000’
Temperature Variation B Performed in conjunction with 4.0 (for noncontrolled
or partially controlled temperature,
internal section of the aircraft)
Humidity A Standard environment
Operational Shock &
Crash Safety
B Equipment installed in fi xed-wing aircraft or
helicopters
Vibration RG Helicopters (reciprocating and turbojet engines)
to be installed in instrument panel, console, or
equipment rack
Magnetic Effect Z Less than 0.3m
Power Input Z DC equipment may be used on all other types of
aircraft electrical systems; implies compliance with
Category A() and B
Voltage Spike A Fifty 600V spikes/min, both polarities
Audio Frequency
Conducted Susceptibility
Z DC equipment may be used on all other types of
aircraft electrical systems; implies compliance with
Category A() and B
Induced Signal
Susceptibility
Z Interference-free operation required
Radio Frequency (RF)
Susceptibility
W Tested conducted and radiated susceptibility
Emission of RF Energy M May be suitable for equipment and associated
interconnecting wiring located in the passenger
cabin or the cockpit
Lightning-Induced
Transient Susceptibility
XXE3 Cable bundling single-stroke 3 installed in a
moderately exposed environment
Electrostatic Discharge A Equipment is installed, repaired, or operated in an
aerospace environment
X – No testing was required for Explosion Proofness, Waterproofness, Fluids Susceptibility,
Sand and Dust, Fungus Resistance, Salt Spray, Lightning Direct Effects, Icing
TS-0500-100 Rev A

TECHNICAL SPECIFICATION | SAGEM ICDS-10
INTERFACES AND COMPATIBILITY
Video input (composite) NTSC/PAL (optional)
NVG (night vision goggles) compatible (optional)
GPS RS-232 (ARNAV Star 5000, Garmin 430/530, GNS 480,
others)
NAV Source (Garmin 430/530, GNS 480, KX 165, KNS 80/81,
Collins, others)
ADF (KR 87, Collins, others)
ARINC 429 (Garmin VOR/ILS, GPS; Honeywell EPIC, others)
Discrete inputs options include pilot in command, PFD show
engines, PFD/MFD mode, maintenance mode, others
Discrete outputs include gauge in caution range, latched exceedance,
primary engine page not selected, others
Other interfaces and applications, not listed, may be compatible.
Contact Sagem Avionics, Inc. for details.
INSTALLATION REQUIREMENTS
Cooling: No external cooling necessary; requires clearance
for internal cooling fan and vents
Breaker: Klixon 5A trip-free circuit breaker* or equivalent
Wiring: Power input wires* (18 or 20 AWG), signal wires*
(22 or 24 AWG), 100-pin adapter
*Not supplied: circuit breaker, wiring
NOTES
For safety reasons, operation of the ICDS-10 must be learned on
the ground.
For maximum versatility, the ICDS-10 modes of operation and
confi guration are factory-set for the specifi c aircraft.
www.sagemavionics.com
TEXAS DIVISION
2701 Forum Drive
Grand Prairie, TX 75052 USA
Tel.: +1.972.314.3600
Fax: +1.972.314.3640
WASHINGTON DIVISION
16923 Meridian East
Puyallup, WA 98375 USA
Tel.: +1.253.848.6060
Fax: +1.253.848.3555
SAGEM DÉFENSE SÉCURITÉ
27, rue Leblanc
75512 PARIS CIDEX 15 France
Tel.: +33 (0) 1 58 11 78 00
Fax: +33 (0) 1 58 11 78 50
©2006 Sagem Avionics, Inc. All rights reserved. Printed in USA. Specifi cations are subject to change without notice.
The SAGEM logo is a registered trademark of SAGEM S.A. DZUS is a registered trademark of McKechnie Specialized Products Limited.
TS-0500-100 Rev A