SANDIA aerospace SAC 7-35 User manual

SASA
SASA
SAC 7-35C 7-35
C 7-35C 7-35
C 7-35 Air DaAir Da
Air DaAir Da
Air Data Computerta Computer
ta Computerta Computer
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Putting Power In Your Navigation System
Get The Most From Your Garmin GNS430/530
Real Time Winds Aloft
Density Altitude
Outside Air Temperature
Improved Roll Steering And Autopilot Capture
ADS-B Interface to Mode S Transponders SANDIA aerospaceSANDIA aerospace
SANDIA aerospaceSANDIA aerospace
SANDIA aerospace
Photo Courtesy NASA Hubble

PERFORMANCE YOU CAN COUNT ON
The SAC 7-35 has set the Air Data Computer standard for General Aviation aircraft, combining the accuracy
and performance demanded by today’s integrated avionics systems. The addition of the SAC 7-35 will unlock
the powerful features your new system is capable of providing to you. All with the quality and reliability you
have come to expect from SANDIA aerospace.
In addition to the airdata capabilities the -01 version of SAC 7-35 provides interface compatibility between
Garmin 400W/500W navigators and certain Mode S transponders for ADS-B operations.
GET MORE FROM YOUR NAVIGATION SYSTEM
The new generation of integrated avionics have been designed to provide the pilot with a host of information to
make his flying safer and more economical. Such information as real time Winds Aloft which aid the pilot in
selecting the altitude that provides the best cruise performance. And with today’s rising fuel costs, this is
rapidly becoming a more and more important consideration. Density Altitude to help determine takeoff off
distances and make those important go, no-go decisions, particularly at high altitude airports and those with
short runways. Digital OutsideAir Temperature simplifies temperature monitoring to determine when icing
conditions may exist. Fuel Flow data allows you to continually monitor your fuel used and watch any changes
in fuel consumption that may indicate engine problems.
FOUR SYSTEMS INONE
Afull featured Air Data Computer enhancing the utility of your navigation system. The SAC 7-35 provides all
the performance of Airdata Computers costing thousands of dollars more. Altitude In-Flight Monitoring
(AIM) alerts the pilot whenever the aircraft deviates more than 100’ feet from a selected altitude. Certified
Altitude Encoder that provides both Gilliam Grey Code for legacy transponders and RS 232 outputs for modern
designs. With the addition of a fuel flow transducer(s) the SAC 7-35 supplies digital Fuel Flow information to
navigation systems that have Fuel Flow displays.
TECHNICAL SPECIFICATIONS
Electrical:10-32 VDC
1 Amp Max
Mechanical:
4.87W x 5.62L x 1.89H
1.2 Lbs
Inputs: ARINC 407 Synchro Heading
OAT
Pitot (Airspeed)
Static (Altitude)
Track, Mag Var & Ground Speed From On Board GPS
5 Volt Pot Baro
Fuel Flow, Pulse
GPS Position (-01 Version only)
Air Speed:
KTS: 40-450
MACH: 0.1-.99
Wind Speed: 0-200 Kts
Vertical Speed: +/- 9999 Ft/min
+/- 20000 On ARINC Bus
Altitude: 35,000’ Max
Resolution: Grey Code 100’
RS 232 10’
ARINC 429 10’
Accuracy:
-1000’ to 5000’ +25’
5001’ to 11000’ +30’
11001’ to 20000’ +35’
20001’ to 30000’ +50’
30001’ to 35000’ +75’
Fuel Flow:
Flow Rate 1-14400 GPH Per Side
K-Factor Range 500-130,000
Certification:
TSO C88a, ETSO C88a
TSO C106, ETSO C106
DO160E
DO178 Level C
DO254
3700 Osuna Rd NE
Suite 711
Albuquerque, NM 87109
www.sandia.aero R4-022010-1000
SANDIA aerospaceSANDIA aerospace
SANDIA aerospaceSANDIA aerospace
SANDIA aerospace
SASA
SASA
SAC 7-35C 7-35
C 7-35C 7-35
C 7-35 Air DaAir Da
Air DaAir Da
Air Data Computerta Computer
ta Computerta Computer
ta Computer
Air Temp:Range: -60C to +60C
Accuracy: +1.5oC
ADS-B ARINC 743 Labels (-01 Version Only)

SANDIA aerospace, Inc.SANDIA aerospace, Inc.
SANDIA aerospace, Inc.SANDIA aerospace, Inc.
SANDIA aerospace, Inc.
3700 Osuna Rd. NE, Suite 711
Albuquerque, NM 87109
www.sandia.aero 305586-00
SAC 7-35
Airdata Computer
Installation Manual

This document and the information contained herein is the proprietary data of SANDIA aerospace, Inc.
No part of this document may be transmitted, reproduced, or copied in any form or by any means
without the prior written consent of SANDIA aerospace, Inc. Due to SANDIA aerospace’s continued
product and quality improvement programs, information contained in this document is subject to change
without prior notice.
Copyright 2009 SANDIA aerospace, Inc., All rights reserved. Printed in USA
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1

Table Of Contents
Record of Revisions ..................................................................................................................... 1
Table of Contents ...................................................................................................................... 2
List of Illustrations ...................................................................................................................... 2
Section 1 - General Description
1.1 Introduction .................................................................................................................... 4
1.1.1 Product Description ............................................................................................ 4
1.2 Technical Characteristics................................................................................................ 5
1.2.1 PhysicalCharacteristics......................................................................................... 5
1.2.1.1 SAC 7-35 ..................................................................................................... 5
1.2.1.2 STP 78 OAT Probe ....................................................................................... 5
1.2.2 OperationalCharacteristics ................................................................................... 5
1.2.3 Operating Limitations......................................................................................... 5
1.2.4 Outputs ............................................................................................................... 7
1.2.4.1 RS 232 .......................................................................................................... 7
1.2.4.1.1 RS 232 (A and B) Airdata Output........................................................ 7
1.2.4.1.2 RS 232 (C and D) Corresponding Altitude Output ............................. 8
1.2.4.2 ARINC 429 High Speed Labels ................................................................... 8
1.2.4.3 Gillham Grey Code Output .......................................................................... 8
1.2.4.4 AIM Output .................................................................................................. 8
1.2.5 Inputs .................................................................................................................. 9
1.2.6 Certification ........................................................................................................ 9
Section 2 Installation Considerations
2.1 Introduction .................................................................................................................... 12
2.2 Mounting Considerations ............................................................................................... 13
2.3 Cooling ......................................................................................................................13
Section 3 Installation Procedures
3.1 General ......................................................................................................................14
3.2 Equipment Required ....................................................................................................... 14
3.2.1 Equipment Supplied ........................................................................................... 14
3.2.2 Equipment Required But Not Supplied .............................................................. 14
3.3 Mounting Tray Installation ............................................................................................. 14
3.4 Static and Pitot Port Connection..................................................................................... 16
3.5 OAT Probe Mounting and Connection ........................................................................... 16
3.6 Electrical Installation......................................................................................................17
3.7 Fuel Flow Interconnect................................................................................................... 18
3.8 Synchro Inputs................................................................................................................ 18
3.9 BARO Interface.............................................................................................................. 18
3.10 Transponder Interconnect ............................................................................................... 19
3.11 AIM Interconnect ........................................................................................................... 19
Section 4 Configuration and Calibration
4.1 Setup for Configuration .................................................................................................. 24
4.2 Changing Configuration Parameters .............................................................................. 24
4.3 Status Line Descriptions................................................................................................. 26
4.3.1 Serial Port Settings ............................................................................................. 27
4.3.2 Airspeed Trim ..................................................................................................... 27
305586-00

List Of Illustrations
Figure 1-1 System Configuration Diagram .............................................................................. 4
Figure 1-2 SAC 7-35 Environmental Qualification Form...................................................... 10
Figure 1-3 OAT Probe Environmental Qualification Form.................................................... 11
Figure 3-1 Mounting Tray Dimensions .................................................................................. 15
Figure 3-2 SAC 7-35 Outline Dimensions ............................................................................. 15
Figure 3-3 OAT Probe Dimensions ........................................................................................ 16
Figure 3-4 OAT Probe Mounting ........................................................................................... 17
Figure 3-5 Fuel Flow Interconnect......................................................................................... 18
Figure 3-6 AIM Interconnect ................................................................................................. 19
Figure 3-7 Gilham Gray Code Interconnect w/ Most Popular Transponders ........................ 20
Figure 3-8 SAC 7-35 Interconnect Wiring Diagram .............................................................. 21
Figure 3-9 Front Panel Connector Location........................................................................... 23
Figure 4-1 6 Pin Din to Serial Interconnect ........................................................................... 24
Figure4-2 RS-232StatusLinesSetting ................................................................................... 26
Figure4-3 SAC7-35Configuration Mode -UnitTrimStatus................................................... 26
Figure4-4 SAC7-35 ConfigurationMode -Fuel UnitStatus ................................................... 26
3
Table Of Contents Con’t
4.3.3 SynchroInputSettings .......................................................................................... 27
4.3.4 AltitudeTrim......................................................................................................... 28
4.3.5 BAROSettingTrim .............................................................................................. 28
4.3.6 Airspeed Cutoff .................................................................................................. 29
4.3.7 Fuel flow Configuration and K-factor ................................................................ 29
4.3.8 List Inputs ........................................................................................................... 29
4.3.9 ARINC Mode ..................................................................................................... 29
4.3.10 OAT Probe Trim ................................................................................................. 30
4.4 Continued Airworthiness ................................................................................................ 30

Section 1 General Description
1.1 INTRODUCTION
This manual describes the installation of the SANDIA aerospace SAC 7-35 Airdata Computer. It is
intended for use by FAA certified repair stations to install the SAC 7-35 Airdata Computer and in-
cludes both the mechanical and electrical installation information for the SAC 7-35. Calibration, sys-
tem configuration and checkout procedures are included. The installer should ensure that all functions
areoperatingaccording to theirintendedpurposeintheirparticularinstallation.
1.1.1 Product Description
TheSAC7-35 is a solidstate -1000 to 35,000footairdata computer andaltitudeencoder. Withtheaddition
ofafuelflowtransducer(s),theSAC7-35willalsoprovidefuelflowdatatosystemscapableofdisplayingthat
information. TheSAC7-35providesfivedataoutputsthatallow ittointerfacewithawide rangeoftranspon-
ders,TAWS,MFD’s,Navigation Systems anda variety ofother avionics products. TheSAC 7-35 canalso
beinstalledforuseinavarietyofconverterfunctions. Contact factory for more information.
• OneARINC 429 High Speed output, airdata and/orADS-B.
• Two RS-232 airdata output ports (including fuel flow or ADS-B).
• Two RS-232 serial encoder outputs
Note:All four of the RS-232 outputs can be individually configured to match the system(s)
being interfaced.
• One Gillham Grey code output for legacy transponders.
• One SANDIA Altitude In-flight Monitoring (AIM) feature. With the addition of an optional
panel mounted switch and annunciator the AIM mode will monitor and advise the pilot if the
aircraft deviates from a selected altitude.
All calibration and configuration is accomplished via a lap top computer through the 6 pin Din connec-
tor on the front of the SAC 7-35.
SAC 7-35
Airdata Computer
Pitot
Static
OAT
Syncro Heading
Baro Pot *
Fuel **
GPS Track
Grey Code to Transponder
RS 232 Corresponding Alt. C
RS 232 Airdata A
RS 232 Airdata B
ARINC 429 Airdata
AIM (Altitude In-flight
Montoring)
* Optional
** Single or Twin
Figure 1-1
System Configuration
RS 232 Corresponding Alt. D
305586-004

5
1.2 TECHNICAL CHARACTERISTICS
1.2.1 Physical Characteristics
1.2.1.1 SAC 7-35
Width: 4.87”(5.11”withmountingtray)
Height: 1.89” (2.35” with mounting tray)
Depth: 5.62” (5.62” with mounting tray)
Weight: 1.18lbs. (1.39lbs. with mounting tray)
1.2.1.2 STP 78 OAT Probe
SeeFig3.3forDimensions
Weight: .067lbs
1.2.2 Operational Characteristics
Operating Temp. -20o C to + 55oC
Input Voltage: 11 - 32 Vdc
Current 1.0 amp maximum with heater on
Altitude Range -1000’ to 35,000’
PressureAltitude Tolerance: 0’ +/- 25’
2000’ +/- 25”
3000‘ +/- 30’
4000’ +/- 25’
5000’ +/- 25’
8000 +/- 30’
11000’ +/- 35’
14000’ +/- 40’
17000’ +/- 45’
20000’ +/- 50’
30000’ +/- 100’
40000’ +/- 125’
Resolution: Grey Code 100’
RS232 10’
ARINC 429 1’
Density Altitude Accuracy Pressure Alt Correction Tolerance
1000’- 18000’(PAlt) 250 ft. max.
Maximum Vertical Speed: 9,999 fpm Serial
20,000 fpm ARINC 429
Accuracy ±1000 ft/min at ±20000 ft/min
±0300 ft/min at ±6000 ft/min
±0200 ft/min at ±4000 ft/min
±0100 ft/min at ±2000 ft/min
±0050 ft/min at ±1000 ft/min
±0045 ft/min below ±1000 ft/min

305586-006
Indicated Airspeed: 0-450 KTS
0.088-.999 MACH
Accuracy Kts Accuracy
50 5.0
80 3.5
100 2.0
120 2.0
150 2.0
200 2.0
250 2.4
300 2.8
350 3.2
400 3.6
450 4.0
MACH Number Accuracy MACH Tolerance
0.3 to 0.4 0.012
.0.5 0.010
0.6 0.0075
0.7-0.9 0.0050
.95 0.0075
True Airspeed Accuracy ALTIAS TAS TAS Accuracy
10000 50 53 6.6
10000 100 105 3.0
10000 200 211 3.3
10000 300 314 4.6
10000 400 416 5.9
10000 450 467 6.5
30000 50 80 10.1
30000 100 160 4.6
30000 200 315 5.2
30000 300 460 6.9

1.2.4 Outputs
1.2.4.1 RS-232
1.2.4.1.1 RS-232 (A & B) Airdata
The airdata outputs supported by the SAC 7-35 are Garmin Z-message, Garmin-G and
King D. Each of these output formats work with ‘Aviation’format input.
The SAC 7-35 will also interface to a Garmin ADS-B serial output on port -B at 9600
baud. When connected to ADS-B input no serial data is output on port-B.
Baud Rate Installation Configurable to 1200, 9600, 19200 or 38400
Data Bits 8
Stop Bit 1
Parity None
Output Rate: 1 +/- .2 seconds
Altitude Resolution 10”
Airspeed Resolution 1 Kt
7
1.2.2 Operational Characteristics con’t
Wind Speed: 0-200 KTS
Accuracy 6.5 Kts
Wind Direction Accuracy 10 degrees
Air Temp:
Range: -60oC to +60oC
Accuracy +1.5oC
Fuel Flow:
Flow Rate: 1-14400 GPH
K-Factor Range 500-130,000
Outside Air Temperature -60oC - +60oC
Accuracy 1.5oC
1.2.3 Operating Limitations
1.2.3.1 All functions of the SAC 7-35 meet the appropriate design assurance qualifications for a
secondary system for airplanes in Class I, Class II and Class III in accordance with AC
23.1309-1D, Figure 2. The TSO authorization with the RTCA/DO178B software levels by
functions are listed in Section 1.2.6
1.2.3.2 The SAC 7-35 is for navigation information only and not for primary flight information.
1.2.3.3 Fuel flow limited to 2000 input pulses per second.
The SAC 7-35 fuel flow conversion is limited to 2000 input pulses per second
For example, do not install where the K factor and maximum fuel flow exceed:
500K — 14,400 gph 19700K — 365 gph
84600K — 85 gph 130000K — 55 gph