Altitude Data System Installation Manual
SANDIA aerospace, Inc.3700 Osuna Rd. NE, Suite 711Albuquerque, NM 87109305186-00Rev. 3SAE5-35Altitude Data SystemInstallation ManualThis 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 anymeans without the prior written consent of SANDIA aerospace, Inc. Due to SANDIA aerospace’scontinued product and quality improvement programs, information contained in this document issubject to change without prior notice.Copyright 2000 SANDIA aerospace, Inc., All rights reserved. Printed in USARevision Date Description Approval-1 000908 Initial Release J. Fiala-2 030722 ECN 3379 J. Fiala-3 20040716 ECN 3429 J. FialaRecord of Revisions1Table Of ContentsRecord of Revisions .............................................................................................................. 1Table of Contents ................................................................................................................ 2List of Illustrations .............................................................................................................. 2Section 1 - General Description .......................................................................................... 31.1 Introduction ............................................................................................................ 31.1.1 Product Description ....................................................................................... 31.2 Technical Characteristics ........................................................................................ 31.2.1 Physical Characteristics ................................................................................ 31.2.2 Operational Characteristics .......................................................................... 31.2.3 Gillham Grey Code Output........................................................................... 41.2.4 AIM Outputs ................................................................................................ 41.2.5 Discrete Inputs ............................................................................................. 41.2.6 RS-232 Outputs............................................................................................ 41.2.6.1 Standard Mode ..................................................................................... 41.2.6.2 Extended Mode..................................................................................... 51.2.7 Certification ................................................................................................... 5Environmental Qualification Form ...................................................................................... 6Section 2 - Installation Considerations ............................................................................... 72.1 Introduction ............................................................................................................ 72.2 Mounting Considerations ....................................................................................... 72.3 Cooling ................................................................................................................... 7Section 3 - Installation Procedures ..................................................................................... 83.1 General ................................................................................................................... 83.2 Equipment Required ............................................................................................... 83.2.1 Equipment Supplied ....................................................................................... 83.2.2 Equipment Not Supplied .................................................................................. 83.2.3 AIM Annuciator ............................................................................................... 83.3 Mounting Tray Installation ......................................................................................... 83.4 Static Port Connection ........................................................................................... 93.5 Electrical Installation .............................................................................................. 93.6 Calibration ............................................................................................................ 143.6.1 Equipment Required .................................................................................... 143.6.2 Calibration Procedures ................................................................................. 153.6.3 Placarding .................................................................................................... 163.7 Continued Airworthiness ...................................................................................... 16List Of IllustrationsFigure 3-1 SAE5-35 Outline Dimensions (with tray) ...................................................... 9Figure 3-2 J4/J5 Connector Wiring ............................................................................... 11Figure 3-3 J4/J5 Connector Hood Assembly ................................................................. 11Figure 3-4 J4 Pinout ...................................................................................................... 12Figure 3-5 J5 Pinout ...................................................................................................... 12Figure 3-6 Interconnect To Popular Transponders ........................................................ 13Figure 3-7 Interconnect to Garmin & UPSAT GPS and MX20 .................................... 14Figure 3-8 SAE5-35 Adjustment ................................................................................... 16Figure 3-9 Gillham Grey Code Chart ....................................................................... 17-192Section 1 General Description1.1 INTRODUCTIONThis manual describes the installation of the SANDIA aerospace SAE5-35 Altitude Data System. Itis intended for use by FAA certified repair stations to install the SAE5-35 Altitude Data System andincludes both the mechanical and electrical installation information for the SAE5-35. Calibration andcheckout procedures are included. The installer should insure that all functions are operating accordingto their intended purpose in their particular installation.1.1.1 Product DescriptionThe SAE5-35 is a solid state -1000 to 35,000 foot altitude data system that converts pressure altitudeinto a digital output as set forth in the International Standard for SSR Pressure Altitude Transmission.The data output of the SAE5-35 is referenced to 29.92 inch HG (1013 Millibars). The SAE5-35 has been designed to provide altitude data to GPS and Terrain Awareness Systems in addition toMode C Transponders. The SAE5-35 outputs Gillham Grey Code to the transponder and two independentRS232 digital outputs that can be used by GPS or other systems requiring this format.Additionally, the SAE5-35 includes SANDIA aerospace’s exclusive Altitude In-flight Monitoring(AIM) feature. With the addition of an optional panel mounted switch and annunciator the AIMmode will monitor and advise the pilot if the aircraft deviates from a selected altitude.1.2 TECHNICAL CHARACTERISTICS1.2.1 Physical CharacteristicsWidth: 4.87” (5.11” with mounting tray)Height: 1.06” (1.57” with mounting tray)Depth: 4.74” (4.80” with mounting tray)Weight: 0.7 lbs. (.86 lbs. with mounting tray)1.2.2 Operational CharacteristicsOperating Temp. -20o C to + 55o CAltitude: 35,000 feetVoltage: 11 - 32 VdcCurrent 1.0 amps maximum with heater on<100 mA quiescentAccuracy: +/- 50 feet TypicalResolution: Grey Code 100’RS232 10’Burst Pressure 90 in HgMaximum Rate of Altitude Change: 12,000 Feet/Minute31.2.3 Gillham Grey Code Outputsa. 10 Bits available: D4, A4, A2, A1, B4, B2, B1, C4, C2, C1b. Bit On Impedance: Less than 5 ohmsc. Bit Off Leakage: Less than 10uAd. Maximum Current per bit: 20 mAe. Minimum working current: 10 uAf. Maximum voltage per bit: 50Vg. Minimum working voltage: 5Vh. Bit update rate: Less than 250 mSi. Minimum strobe switching bandwidth: Greater than 10kHz1.2.4 AIM OutputsMaximum Lamp Current: 80 mAMaximum off Voltage: 50V1.2.5 Discrete InputsAIM SET, Strobe and RS232 Mode Select InputsAsserted: < 0.4 VdcNot Asserted: > 1.7 VdcPull-up current: 150 uA1.2.6 RS-232 OutputsThere are two modes of operation for the RS232 outputs. The Data Mode pin, J5 pin 4 selects thedata formats.1.2.6.1 Standard ModeWhen the Mode pin (J5 pin 4) is open:a. Baud: 9600b. Data bits: 8c. Stop bit: 1d. Parity: Nonee. Output rate: 1 +/- .2 secondsf. Message length: 11 bytesg. Altitude resolution: 10 footh. Works with Garmin and Trimble GPS4 305186-0051.2.6.2 Extended ModeWhen the Mode pin (J5 pin 4) is grounded:a. Baud: 1200b. Data bits: 8c. Stop bit: 1d. Parity: Nonee. Output rate: 1 +/- .2 secondsf. Message length: 17 bytesg. Altitude resolution: 10 footh. Temperature resolution: 1 degree Ci. For use with UPSAT MX20 and GPS receivers1.2.7 CertificationTSO: C88aSoftware: DO-178B Level CEnvironmental: DO-160D(C1)CAA[(SM)(UF)]XXXXXXZBBBBTBXXXXEnvironmental Qualification Form for the SAE5-35 Altitude Data SystemNOMENCLATURE: SAE5-35, Altitude Data SystemTYPE/MODEL/PART NO: SAE5 – 35 / 305154-00TSO NUMBER: C88aMANUFACTURER’S SPECIFICATION AN/OR OTHER APPLICABLE SPECIFICATION:SAE5-35 INSTALLATION MANUAL P/N 305186-00QUALIFICATION TEST PLAN, SAE5-35 ALTITUDE ENCODER. P/N AENC0051MANUFACTURER: SANDIA AEROSPACEADDRESS: 5445 EDITH BLVD. NE, SUITE I ALBUQUERQUE, NM 87107REVISION & CHANGE NUMBER OF DO-160: REV D, DATED JULY 27 1997CONDITIONS SECTION DESCRIPTION OF TESTS CONDUCTEDTemperature and AltitudeLow TemperatureHigh TemperatureIn-Flight Loss of CoolingAltitudeDecompressionOverpressure4.04.5.14.5.2 & 4.5.34.5.44.6.14.6.24.6.3Equipment Tested to Category C1Tested to-20°C Operating Low TempTested to +55°C Operating High TempTest not Applicable35,000 feetTest not ApplicableTest not ApplicableTemperature Variation 5.0 Tested to CategoryCHumidity 6.0 Tested to CategoryAOperational Shock and Crash Safety 7.0 Tested to CategoryAVibration 8.0 Tested to Category S, Aircraft Zone 2 using vibration curve M. Testedto Category U, Helicopter Zone 2 using vibration curves F and F1.Explosion 9.0 Equipment identified as Category X, no test performedWaterproofness 10.0 Equipment identified as Category X, no test performedFluids Susceptibility 11.0 Equipment identified as Category X, no test performedSand and Dust 12.0 Equipment identified as Category X, no test performedFungus 13.0 Equipment identified as Category X, no test performedSalt Spray 14.0 Equipment identified as Category X, no test performedMagnetic Effect 15.0 Equipment is categoryZPower Input 16.0 Tested to CategoryBVoltage Spike 17.0 Tested to CategoryBAudio Frequency Susceptibility 18.0 Tested to CategoryBInduced Signal Susceptibility 19.0 Tested to CategoryBRadio Frequency Susceptibility 20.0 Tested to CategoryTRadio Frequency Emission 21.0 Tested to CategoryBLighning Induced Transient Susceptibility22.0 Equipment identified as Category X, no test performedLightning Direct Effects 23.0 Equipment identified as Category X, no test performedIcing 24.0 Equipment identified as Category X, no test performedElectrostatic Discharge 25.0 Equipment identified as Category X, no test performed6 305186-00DATE OF TEST: July 2000Section 2 Installation Considerations2.1 INTRODUCTIONThe SAE5-35 Altitude Data System simplifies installations that include GPS, Terrain AwarenessSystems and other avionics that require RS232 altitude input information. The SAE5-35provides standard Gillham Grey Code output on its 15 pin connector. Grey code is requiredfor interface to Mode C ATCRBS and Mode S transponders. Two independent RS232outputs are provided on the nine pin connector. The SAE5-35 also incorporates SANDIAaerospace’s exclusive Altitude In-flight Monitoring (AIM) feature that advises pilots if theydeviate from their selected altitude by more than one hundred feet. The AIM feature can beinstalled by purchasing SANDIA aerospace’s optional annunciator/switch assembly, P/N305217-00. Or the installer can supply his own switch and annunciator assembly(s). Themain 15 pin connector follows the standard encoder interconnect used by many manufacturers.By following this convention, upgrading to the SAE5-35 is made easier. If anothermanufacturers encoder is being replaced, it is important to check the wiring informationbefore plugging the existing connector into the SAE5-35. Both the Grey Code output andeach of the RS232 outputs have separate drivers. This ensures that a load on one line doesnot load the other. Additionally, the RS232 output is available even if the enable line on theGrey Code has not been enabled by the transponder.The SAE5-35 does not require warm up unless the outside temperature is below 20 degreesC. When warm up time is required, the internal heater is capable of warming the SAE5-35from -20 degrees C to operating temperature in less than two minutes.2.2 MOUNTING CONSIDERATIONSThe SAE5-35 can be mounted in any axis and either inside or outside the pressure vessel.Mounting should allow for as short a pressure line as possible from the encoder to the altimeter.Be sure to allow an ample service loop on the cable to allow for calibration of theSAE5-35CAUTION: DO NOT mount the SAE5-35 inthe direct airstream or near either the hot orcold air ducts.2.3 COOLINGThe SAE5-35 does not require external cooling.73.1 GENERALThe SAE5-35 is supplied with a mounting tray and solder type mating connectors. It is importantthat proper solder techniques be observed in attaching wires to the mating connectors. Failure to doso could result in a failure in the connection and cause intermittent or non operation of the SAE5-35.Section 3 Installation Procedures3.2 EQUIPMENT REQUIRED3.2.1SuppliedSAE5-35 System 705154-00Includes: SAE5-35 Encoder 305154-00SAE5-35 Installation Manual 305186-00SAE5-35 Installation Kit 305216-0015 Pin Mating Connector 30521515 Pin Connector Hood 3052089 Pin Mating Connector 3052149 Pin Connector Hood 305207Mounting Tray 305145Knurled Holdown Nut 3051893.2.2
Required but not suppliedNumber 6-32 mounting screwsStatic port fitting3.2.3
Optional EquipmentAIM Annunciator, Installer supplied or Sandia Part Number 307217-003.3 MOUNTING TRAY INSTALLATIONThe mounting tray is mounted to the airframe using either three or four number 6-32 screws. Themounting hole pattern for the SAE5-35 mounting tray contains five holes. For new installations, it isrecommended that the four corner holes be used to mount the SAE5-35 tray. The fifth hole has beenadded to facilitate upgrades from other manufactures encoders. Refer to the SAE5-35 tray dimensionsin Figure 3-1 to determine if the hole pattern of the removed system match the hole pattern ofthe SAE5-35 mounting tray.8 305186-003.4 STATIC PORT CONNECTIONA standard 1/8 - 27 NPT brass fitting is provided on the front plate of the encoder for attaching to theaircraft static air system. An adapter may be used to convert this to match the aircraft static plumbing.When attaching the mating fitting, make sure that it is secure and free from leaks that can induceerrors in the static system. In installations where an existing encoder is being replaced, the existingtubing and fittings should be examined for any damage or deterioration and replaced if necessary. Toreduce the likelihood of the brass fitting rotating while installing the static lines, a “D” shaped hole isused to mount the brass fitting into the front panel. Upon completion of installation of the SAE5-35, aCase Leak test is to be performed per FAR Part 43 Appendix ENOTE: Since significant force can be applied to the encoderduring static fitting installation, dual wrench techniques are alwaysrecommended to avoid damage to the encoder.3.5 ELECTRICAL INSTALLATIONThe SAE5-35 is designed to operate from 11-32Vdc without any special wiring considerations.Power can be supplied from the transponder’s switched A+ output, the transponder circuit breaker orfrom the aircraft buss. If supplied from the aircraft buss, the line must be protected with a 2 amp fuseFigure 3-1SAE5-35 Outline Dimensions (with tray)9J4 J5or circuit breaker. SAE document AS8003 Minimum Performance Standard for Automatic PressureAltitude Reporting Code Generating Equipment states that “a means shall be incorporated in theequipment to indicate the loss of electrical power or the effect thereof, unless the electrical power tooperate the code generating equipment is supplied by an ATC Transponder which also supplies anindication of this power loss.” This is typically accomplished by using the switched A+ output fromthe transponder or by connecting the SAE5-35 power input to the transponder circuit breaker. Alternatively,the two power pins, 8 and 14, are internally connected in the SAE5-35. Only one of theseconnections is necessary to supply power to the unit. The unused connection can be used to drive apanel-mounted indicator if desired.All transponder functions including the Grey code output are on the 15 pin connector J4. The RS232digital outputs for GPS and other avionics requiring this format as well as the AIM function are onthe 9 pin connector J5. The Grey code output on the transponder is disabled whenever Mode C onthe transponder is not selected.Note: The RS232 serial data output is always present wheneverthere is power to the SAE5-35 and the warm up time is completed,even when the Strobe/Enable line is not grounded.Note: If power is supplied from the transponder, the RS232 andAIM functions will be inoperative when the transponder is turnedoff or removed from the aircraft.Grounding the Strobe/Enable line on J4 pin 6 will enable the transponder Grey code data. There arethree methods used to do this.1. Permanently grounding this line.2. The transponder provides a switched ground enable signal.3. The transponder provides a strobe-ground enable signal.The SAE5-35 is compatible with all three systems, refer to the appropriate transponder installationmanual for detail. Interconnect information for the most popular transponders can be found in Figure3-6. For other makes of transponders, refer to the manufacturers installation manual.Note: If the transponder being interfaced has a strobe output,the AIM function will not operate properly and should not beconnected.While several manufacturers use RS232 digital altitude data, their formats and baud rates may vary.The SAE5-35 can accommodate most data formats by either grounding or leaving pin 4 on J5 open.If pin 4 is left open, the output baud rate is 9600. If pin 4 is grounded, the output baud rate is 1200.The RS232 interconnect information can be found in Figure 3-7.Interconnect information for the most popular transponders can be found in Figures 3-6. The RS232interconnect information can be found in Figure 3-7.10 305186-00Figure 3-2J4/J5 Connector WiringFigure 3-3J4/J5 Connector Hood Assembly11The SAE5-35 uses Sub-D solder cup connectors with screw lock assemblies. Proper wire attachmentand assembly of the screw locks and connector hood are shown in Figure 3-2 and 3-3. It is recommendedthat each wire and solder cup be covered with a piece of shrink tubing or other insulator.J4 J5J4 Notes:1. J4 is 15 Pin receptacle2. Pin 6 may be strobed or permanently grounded.Pin 6 must be grounded for AIM function tobe operational.3. Power and ground wires (pins 8, 14 & 15) are20 AWG. All other wires are 22AWG unlessotherwise noted.4. Pin 8 and 14 are internally connected in theSAE5-35. Only one line is necessary to supplypower to the unit. The unused power pin maybe used as a power loss indicator if desired.5. The Garmin 430/530 must be set to IcarusRS232 format.J5 Notes:1. J5 is 9 Pin receptacle2. Maximum lamp current 80mA3. All wires are 22AWG unless otherwisenoted.4. AIM switch is a momentary contact5. Ground pin 4 for 1200 baudLeave pin 4 open for 9600 baud (seeParagraph 1.2.6.1 & 1.2.6.2 for details).6. If the AIM function uses annunciatorlamps provided by the installer, theyshould be appropriately labeled. Thelamp connected to pin 9 should belabeled ‘ALT’ and the lamp connectedto pin 8 should be labeled ‘SET’.Figure 3-4J4 PinoutFigure 3-5J5 Pinout12 305186-00SAE5-35J4 Function BendixTPR2060BendixTR641A/BCessna RT359T,RT459A, RT859AGarminGTX300SeriesHoneywellKT70/71(ConnectorJKT701)HoneywellKT76A/78AHoneywellKXPNarcoAT50/A,AT150NarcoAT5,AT6/AUPSATSL70Wilcox1014A1 D4 NoConnection N 10 18 8 NoConnection V NoConnectionNoConnection 35 C2 A1 4 A 14 3 M M G 7 2 13 k3 A2 6 B 13 5 K K H 6 4 31 c4 A4 8 C 15 6 J J J 8 8 12 W5 B1 9 D 19 9 E E K 12 9 33 T6 Strobe/Enable AircraftGroundAircraftGround 11 AircraftGroundAircraftGroundAircraftGroundAircraftGround 5 12 AircraftGroundAircraftGround7 Ground AircraftGroundAircraftGroundAircraftGroundAircraftGroundAircraftGroundAircraftGroundAircraftGroundAircraftGroundAircraftGroundAircraftGroundAircraftGround8 Aircraft Power Note1 Note1 9 or perNote 1 Note 1 Note1 Note1 Note1 18 or perNote 113 or perNote 1 Note 1 Note19 B2 10 E 17 11 C C L 10 10 14 L10 B4 11 F 16 12 B B M 9 11 32 D11 C1 3 H 21 10 D D P 14 1 16 P12 C4 7 K 20 7 H H S 13 5 15 Z13 C2 5 J 18 4 L L R 11 3 34 f14 Aircraft Power Note1 Note1 Note1 Note1 Note1 Note1 Note1 Note1 Note1 Note1 Note115 Aircraft Ground AircraftGroundAircraftGroundAircraftGroundAircraftGroundAircraftGroundAircraftGroundAircraftGroundAircraftGroundAircraftGroundAircraftGroundAircraftGroundFigure 3-6Interconnect for popular transponders13Notes:1. The two power pins, 8 and 14, are internally connected inthe SAE5-35. Only one of these connections is necessaryto supply power to the unit. The unused connection can beused to drive a panel-mounted indicator if desired.SAE5-35J5 FunctionGarmin430P4001Garmin530P5001UPSATGX60/6537 Pin ConnectorUPSATMX20P21 RS232 TX1 57 57 4or 21 212 RS232 TX2 Note1 Note1 Note1 Note13 N/C No Connection No Connection No Connection No Connection4 RS232 ModeSelect No Connection No Connection Aircraft GroundAircraft Ground5 RS232 Return 77 or 78 77 or 78 25 36 RS232 Shield OpenNote 3OpenNote 3OpenNote 3OpenNote 37 AIM 'SET' Switch Note4 Note4 Note4 Note48 AIM 'SET' Lamp Note4 Note4 Note4 Note49 AIM'ALT' Lamp Note 4 Note4 Note4 Note4Figure 3-7J5 interconnect With Garmin and UPSAT Systems14Notes:1. The SAE5-35 has two independent RS232 outputs. RS232 TX2 can be connected to asecond sysytem in the same manner as RS232 TX12. The RS232 wires are 22 AWG twisted pair.3. Shield grounds are ground at the SAE5-35 and open at the unit being interfaced.4. See Figure 3-5 for AIM function interconnect wiring.305186-003.6 CALIBRATIONThe SAE5-35 is calibrated at the factory to a pressure datum traceable to the National Bureau ofStandards. However, when the encoder is installed in the aircraft it must be recalibrated to correspondenceto the primary flight altimeter, refer to FAR 91.217 and FAR 91.413 for details. Thiscalibration ensures that the altitude code generated from the SAE5-35 is within 125 feet of the altitudedisplayed to the pilot.3.6.1 Equipment Required1. A calibrated pitot-static test set capable of pumping the system from –1000 feet up themaximum test altitude.2. A calibrated transponder ramp tester capable of displaying the encoder altitude information.153.6.2 Calibration ProceduresNote: The Primary Flight Altimeter must be calibrated perpart 43 section E. Verify compliance with AC-43.13 as applicable.1. Connect the pitot-static test set to the aircraft static system. The SAE5-35 must beconnected to the aircraft static line near the flight altimeter and the two altitude adjustmentsbuttons must be accessible. Apply power to the altitude encoder and the ATCtransponder and allow the encoder to stabilize. Set primary flight altimeter to 29.92inches of mercury.2. Apply vacuum from the pitot-static test set to obtain an altimeter reading of 34,800 feet(or 100 feet below the maximum test altitude specified in Part 43, appendix F.)3. Slowly increase altitude and note the flight altimeter at the encoder transition point. If thetransition point is not 34,850 +/- 30 feet (or between –80 feet and –20 feet below themaximum test altitude), press the increase button (behind slot A) or decrease button(behind slot B) until the encoder transition point is within tolerance.4. Increase altitude to obtain an altimeter reading of 35,000 feet (or 100 feet above themaximum altitude specified in Part 43, appendix F.)5. Slowly decrease altitude and read the flight altimeter at the encoder transition point. Verifythe transition point is 34,950 +/- 30 feet (or between 20 feet and 80 feet above the maximumtest altitude.) If necessary, press the increase button (behind slot A) or decreasebutton (behind slot B) until the encoder transition point is within tolerance.6. Apply pressure from the pitot-static test set to obtain an altimeter reading of -800feet7. Slowly decrease altitude and read the flight altimeter at the encoder –800 foot to –900-transition point. If the transition point is higher than -880 feet, hold the increase altitudebutton (behind slot A) while pressing and releasing the decrease altitude button (behindslot B) until the transition point is –850 +/- 30feet. If the transition point is lower than -820 feet, hold the decrease altitude button (behind slot B) while pressing and releasing theincrease altitude button (behind slot A) until the transition point is –850 +/- 30feet.8. Apply pressure from the pitot-static test set to obtain an altimeter reading of -1000feet9. Slowly increase altitude and read the flight altimeter at the encoder –1000 foot to –900-transition point. If the transition point is higher than -920 feet, hold the increase altitudebutton (behind slot A) while pressing and releasing the decrease altitude button (behindslot B) until the transition point is –950 +/- 30 feet. If the transition point is lower than -16980 feet, hold the decrease altitude button (behind slot B) while pressing and releasing theincrease altitude button (behind slot A) until the transition point is –950 +/- 30 feet.10. Repeat steps 2 through 10 until the transition points and the flight altimeter are withintolerance for both low and high altitudes. Verify several test points throughout the rangeto assure correspondence between the SAE5-35 and the flight altimeter.305186-003.6.3 PlacardingWe recommend that the altimeter used for flight reference and the SAE5-35 be placarded with thefollowing information:Replacement or re-calibration of the altimeter used for flightreference requires re-calibration of SAE5-35 Altitude Encoder.Altitude encoded to feet.Figure 3-8SAE5-35 Adjustment3.7 CONTINUED AIRWORTHINESSThe SAE5-35 requires calibration every 24 months per FAR 91.411. All other maintenance of theSAE5-35 is on condition only.OOPS !The SAE5-35 can be reset to factory settings by appling power tothe unit while simultaneously pressing both adjustments A & B17Altitude D4 A1 A2 A4 B1 B2 B4 C1 C2 C4-1000 0 0 0 0 0 0 0 0 1 0-900 0 0 0 0 0 0 0 1 1 0-800 0 0 0 0 0 0 0 1 0 0-700 0 0 0 0 0 0 1 1 0 0-600 0 0 0 0 0 0 1 1 1 0-500 0 0 0 0 0 0 1 0 1 0-400 0 0 0 0 0 0 1 0 1 1-300 0 0 0 0 0 0 1 0 0 1-200 0 0 0 0 0 1 1 0 0 1-100 0 0 0 0 0 1 1 0 1 10 0 0 0 0 0 1 1 0 1 0100 0 0 0 0 0 1 1 1 1 0200 0 0 0 0 0 1 1 1 0 0300 0 0 0 0 0 1 0 1 0 0400 0 0 0 0 0 1 0 1 1 0500 0 0 0 0 0 1 0 0 1 0600 0 0 0 0 0 1 0 0 1 1700 0 0 0 0 0 1 0 0 0 1800 0 0 0 0 1 1 0 0 0 1900 0 0 0 0 1 1 0 0 1 11000 0 0 0 0 1 1 0 0 1 01100 0 0 0 0 1 1 0 1 1 01200 0 0 0 0 1 1 0 1 0 01300 0 0 0 0 1 1 1 1 0 01400 0 0 0 0 1 1 1 1 1 01500 0 0 0 0 1 1 1 0 1 01600 0 0 0 0 1 1 1 0 1 11700 0 0 0 0 1 1 1 0 0 11800 0 0 0 0 1 0 1 0 0 11900 0 0 0 0 1 0 1 0 1 12000 0 0 0 0 1 0 1 0 1 02100 0 0 0 0 1 0 1 1 1 02200 0 0 0 0 1 0 1 1 0 02300 0 0 0 0 1 0 0 1 0 02400 0 0 0 0 1 0 0 1 1 02500 0 0 0 0 1 0 0 0 1 02600 0 0 0 0 1 0 0 0 1 12700 0 0 0 0 1 0 0 0 0 12800 0 0 0 1 1 0 0 0 0 12900 0 0 0 1 1 0 0 0 1 13000 0 0 0 1 1 0 0 0 1 03100 0 0 0 1 1 0 0 1 1 03200 0 0 0 1 1 0 0 1 0 03300 0 0 0 1 1 0 1 1 0 03400 0 0 0 1 1 0 1 1 1 03500 0 0 0 1 1 0 1 0 1 03600 0 0 0 1 1 0 1 0 1 13700 0 0 0 1 1 0 1 0 0 13800 0 0 0 1 1 1 1 0 0 13900 0 0 0 1 1 1 1 0 1 14000 0 0 0 1 1 1 1 0 1 04100 0 0 0 1 1 1 1 1 1 04200 0 0 0 1 1 1 1 1 0 04300 0 0 0 1 1 1 0 1 0 04400 0 0 0 1 1 1 0 1 1 04500 0 0 0 1 1 1 0 0 1 04600 0 0 0 1 1 1 0 0 1 14700 0 0 0 1 1 1 0 0 0 14800 0 0 0 1 0 1 0 0 0 14900 0 0 0 1 0 1 0 0 1 15000 0 0 0 1 0 1 0 0 1 05100 0 0 0 1 0 1 0 1 1 05200 0 0 0 1 0 1 0 1 0 05300 0 0 0 1 0 1 1 1 0 05400 0 0 0 1 0 1 1 1 1 05500 0 0 0 1 0 1 1 0 1 05600 0 0 0 1 0 1 1 0 1 15700 0 0 0 1 0 1 1 0 0 15800 0 0 0 1 0 0 1 0 0 15900 0 0 0 1 0 0 1 0 1 16000 0 0 0 1 0 0 1 0 1 06100 0 0 0 1 0 0 1 1 1 06200 0 0 0 1 0 0 1 1 0 06300 0 0 0 1 0 0 0 1 0 06400 0 0 0 1 0 0 0 1 1 06500 0 0 0 1 0 0 0 0 1 06600 0 0 0 1 0 0 0 0 1 16700 0 0 0 1 0 0 0 0 0 16800 0 0 1 1 0 0 0 0 0 16900 0 0 1 1 0 0 0 0 1 17000 0 0 1 1 0 0 0 0 1 07100 0 0 1 1 0 0 0 1 1 07200 0 0 1 1 0 0 0 1 0 07300 0 0 1 1 0 0 1 1 0 07400 0 0 1 1 0 0 1 1 1 07500 0 0 1 1 0 0 1 0 1 07600 0 0 1 1 0 0 1 0 1 17700 0 0 1 1 0 0 1 0 0 17800 0 0 1 1 0 1 1 0 0 17900 0 0 1 1 0 1 1 0 1 18000 0 0 1 1 0 1 1 0 1 08100 0 0 1 1 0 1 1 1 1 08200 0 0 1 1 0 1 1 1 0 08300 0 0 1 1 0 1 0 1 0 08400 0 0 1 1 0 1 0 1 1 08500 0 0 1 1 0 1 0 0 1 08600 0 0 1 1 0 1 0 0 1 18700 0 0 1 1 0 1 0 0 0 18800 0 0 1 1 1 1 0 0 0 18900 0 0 1 1 1 1 0 0 1 19000 0 0 1 1 1 1 0 0 1 09100 0 0 1 1 1 1 0 1 1 09200 0 0 1 1 1 1 0 1 0 09300 0 0 1 1 1 1 1 1 0 09400 0 0 1 1 1 1 1 1 1 09500 0 0 1 1 1 1 1 0 1 09600 0 0 1 1 1 1 1 0 1 19700 0 0 1 1 1 1 1 0 0 19800 0 0 1 1 1 0 1 0 0 19900 0 0 1 1 1 0 1 0 1 110000 0 0 1 1 1 0 1 0 1 010100 0 0 1 1 1 0 1 1 1 010200 0 0 1 1 1 0 1 1 0 010300 0 0 1 1 1 0 0 1 0 010400 0 0 1 1 1 0 0 1 1 010500 0 0 1 1 1 0 0 0 1 0Altitude D4 A1 A2 A4 B1 B2 B4 C1 C2 C4Figure 3-9Gillham Grey Code Chart18 305186-0010600 0 0 1 1 1 0 0 0 1 110700 0 0 1 1 1 0 0 0 0 110800 0 0 1 0 1 0 0 0 0 110900 0 0 1 0 1 0 0 0 1 111000 0 0 1 0 1 0 0 0 1 011100 0 0 1 0 1 0 0 1 1 011200 0 0 1 0 1 0 0 1 0 011300 0 0 1 0 1 0 1 1 0 011400 0 0 1 0 1 0 1 1 1 011500 0 0 1 0 1 0 1 0 1 011600 0 0 1 0 1 0 1 0 1 111700 0 0 1 0 1 0 1 0 0 111800 0 0 1 0 1 1 1 0 0 111900 0 0 1 0 1 1 1 0 1 112000 0 0 1 0 1 1 1 0 1 012100 0 0 1 0 1 1 1 1 1 012200 0 0 1 0 1 1 1 1 0 012300 0 0 1 0 1 1 0 1 0 012400 0 0 1 0 1 1 0 1 1 012500 0 0 1 0 1 1 0 0 1 012600 0 0 1 0 1 1 0 0 1 112700 0 0 1 0 1 1 0 0 0 112800 0 0 1 0 0 1 0 0 0 112900 0 0 1 0 0 1 0 0 1 113000 0 0 1 0 0 1 0 0 1 013100 0 0 1 0 0 1 0 1 1 013200 0 0 1 0 0 1 0 1 0 013300 0 0 1 0 0 1 1 1 0 013400 0 0 1 0 0 1 1 1 1 013500 0 0 1 0 0 1 1 0 1 013600 0 0 1 0 0 1 1 0 1 113700 0 0 1 0 0 1 1 0 0 113800 0 0 1 0 0 0 1 0 0 113900 0 0 1 0 0 0 1 0 1 114000 0 0 1 0 0 0 1 0 1 014100 0 0 1 0 0 0 1 1 1 014200 0 0 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1 1 0 0 1 1 0 022300 0 1 1 1 0 0 0 1 0 022400 0 1 1 1 0 0 0 1 1 022500 0 1 1 1 0 0 0 0 1 022600 0 1 1 1 0 0 0 0 1 122700 0 1 1 1 0 0 0 0 0 1Altitude D4 A1 A2 A4 B1 B2 B4 C1 C2 C4 Altitude D4 A1 A2 A4 B1 B2 B4 C1 C2 C41922800 0 1 0 1 0 0 0 0 0 122900 0 1 0 1 0 0 0 0 1 123000 0 1 0 1 0 0 0 0 1 023100 0 1 0 1 0 0 0 1 1 023200 0 1 0 1 0 0 0 1 0 023300 0 1 0 1 0 0 1 1 0 023400 0 1 0 1 0 0 1 1 1 023500 0 1 0 1 0 0 1 0 1 023600 0 1 0 1 0 0 1 0 1 123700 0 1 0 1 0 0 1 0 0 123800 0 1 0 1 0 1 1 0 0 123900 0 1 0 1 0 1 1 0 1 124000 0 1 0 1 0 1 1 0 1 024100 0 1 0 1 0 1 1 1 1 024200 0 1 0 1 0 1 1 1 0 024300 0 1 0 1 0 1 0 1 0 024400 0 1 0 1 0 1 0 1 1 024500 0 1 0 1 0 1 0 0 1 024600 0 1 0 1 0 1 0 0 1 124700 0 1 0 1 0 1 0 0 0 124800 0 1 0 1 1 1 0 0 0 124900 0 1 0 1 1 1 0 0 1 125000 0 1 0 1 1 1 0 0 1 025100 0 1 0 1 1 1 0 1 1 025200 0 1 0 1 1 1 0 1 0 025300 0 1 0 1 1 1 1 1 0 025400 0 1 0 1 1 1 1 1 1 025500 0 1 0 1 1 1 1 0 1 025600 0 1 0 1 1 1 1 0 1 125700 0 1 0 1 1 1 1 0 0 125800 0 1 0 1 1 0 1 0 0 125900 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033600 1 1 0 0 1 1 1 0 1 133700 1 1 0 0 1 1 1 0 0 133800 1 1 0 0 1 0 1 0 0 133900 1 1 0 0 1 0 1 0 1 134000 1 1 0 0 1 0 1 0 1 034100 1 1 0 0 1 0 1 1 1 034200 1 1 0 0 1 0 1 1 0 034300 1 1 0 0 1 0 0 1 0 034400 1 1 0 0 1 0 0 1 1 034500 1 1 0 0 1 0 0 0 1 034600 1 1 0 0 1 0 0 0 1 134700 1 1 0 0 1 0 0 0 0 134800 1 1 0 1 1 0 0 0 0 134900 1 1 0 1 1 0 0 0 1 135000 1 1 0 1 1 0 0 0 1 0 Altitude Data System Installation Manual
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回复 1# 帅哥 的帖子
CFM56-7 Starter Reliability
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