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uAvionix AV-30-C Installation Manual Download Page 42

 
 

 

 

UAV-1003947-001, AV-30-C, Installation Manual  

42 

Rev E 

 

 

 

 

 

5. 

“Calibration in progress” will be displayed with a percentage complete. 

 

Figure 20 - Gyro Calibration Procedure

 

 

6.  AV-30-C 

will indicate “Calibration successfully completed / Press DONE”.  

 
Press 

the left button under “DONE” and the calibration will be complete. If 

an error is shown, repeat the calibration process. 

 

 

 

 

 

 

 

 

 

 

 

Figure 19 - Gyro Calibration Selection 

Summary of Contents for AV-30-C

Page 1: ...UAV 1003947 001 Rev E AV 30 C Installation Manual ...

Page 2: ...permissions to download a single copy of this guide onto an electronic storage medium to be viewed for personal use provided that the complete text of this copyright notice is retained Unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited uAvionix and Ping are registered trademarks of uAvionix Corporation and may not be used without express permission of...

Page 3: ...n the ICA Added startup time and AoA reference per MOPS requirement Added reference to CFR 23 1321 C 8 10 2020 Added reference to AoA operation in inverted flight and operation in excess of G limits Added reference to utilize wire type in accordance with AC 43 13 1B D 6 3 2021 Updated Top Level Assembly references E 9 2 2021 Software update to 2 1 2 Added Definition of Acronyms Terms section Added...

Page 4: ...sification Number ECCN 7A994 These items are controlled by the U S Government and authorized for export only to the country of ultimate destination for use by the ultimate consignee or end user s herein identified They may not be resold transferred or otherwise disposed of to any other country or to any person other than the authorized ultimate consignee or end user s either in their original form...

Page 5: ...odified or altered Disclaimer of Warranty IN NO EVENT SHALL UAVIONIX BE LIABLE FOR ANY INCIDENTAL SPECIAL INDIRECT OR CONSEQUENTIAL DAMAGES WHETHER RESULTING FROM THE USE MISUSE OR INABILITY TO USE THE PRODUCT OR FROM DEFECTS IN THE PRODUCT SOME STATES DO NOT ALLOW THE EXCLUSION OF INCIDENTAL OR CONSEQUENTIAL DAMAGES SO THE ABOVE LIMITATIONS MAY NOT APPLY TO YOU Warranty Service Warranty repair se...

Page 6: ...ble Performance Standards 15 8 Installation Limitations 16 8 1 Installation Approval Limitations 16 9 Installation Locations Operating Modes 17 9 1 Installation Locations 17 9 2 Operating Mode Configuration 18 10 Functionality and Required Interfaces 19 10 1 Aircraft Systems Connections 19 10 2 Feature Matrix 20 10 2 1 Power Input Required 21 10 2 2 Pitot and Static Interfaces Required 21 10 2 3 O...

Page 7: ... 34 13 1 Mandatory Settings 37 13 1 1 Unit Function 37 13 1 2 Function Lock 37 13 1 3 Trim 37 13 1 4 V Speeds 37 13 1 5 Display Units 37 13 1 6 Serial Inputs 38 13 1 7 AID Mode 39 13 1 8 Demo Mode 40 13 2 System Checkout 40 13 2 1 Alignment 40 13 2 2 Gyro Calibration 41 13 2 3 OAT Interface 43 13 2 4 GPS Navigator Interface 43 13 2 5 Vibration Check 44 13 2 6 EMC Checkout 46 14 Troubleshooting 48 ...

Page 8: ...mum controllable airspeed VYSE Best rate of climb speed with one engine inoperative V2 Take off safety speed The lowest speed at which the aircraft complies with the handling criteria associated with the climb VT Threshold crossing speed target speed after V2 has been reached VSO Minimum stall speed with gear and full flaps The bottom end of the ASI white arc VS1 Minimum steady flight velocity whi...

Page 9: ...asic Display When configured as an AI primary attitude and slip are always displayed The unused portions of the display area can be customized by the pilot to show a variety of textual and graphical data overlay fields Three pages may be customized by the pilot while a fourth page presents a fully decluttered view of only attitude and slip When configured as a Directional Gyro DG direction of flig...

Page 10: ...he look and feel of older aircraft applications A wide variety of supplemental functions including audio alerting derived angle of attack presentation g load display and more are provided An internal rechargeable battery allows for operation for a nominal 2 hours in the event of aircraft power loss in flight and 30 minutes minimum under all temperature conditions See AV 30 C Pilots Guide UAV 10039...

Page 11: ...dicated Airspeed Altitude V Speeds Angle of Attack Vertical Trend Vertical Speed Set Altitude Heading Bus Voltage G Load Outside Air Temp True Airspeed Density Altitude GPS Navigator Waypoint Data GPS Navigator Nav Data GPS Navigator Route Line Heading Bug Audio and Visual Alerting Functions AoA Alerting G Limit Alerting Excessive Roll Alerting Misc Functions Internal Battery Operation Auto Manual...

Page 12: ...3 1 8 Round Instrument Hole Dimensions w o Connector 3 38 x 3 38 x 1 6 Weight 0 56 Lbs Electrical Connector 15 Pin Male D Sub Pneumatic Connectors 1 4 OD Quick Connect Mounting 4X 6 32 Machine Screws Case Material Billet Aluminum Environmental Ground Survival Low 55 C Operating Low 20 C Ground Survival High 85 C Operating High 55 C Altitude 25 000 Feet maximum Optical Characteristics Diagonal Size...

Page 13: ...c and non metallic aircraft The AV 30 C is approved for primary Attitude Slip and Direction of Flight All other functionality is supplemental in nature and may not satisfy regulatory requirements for required instrumentation The installer must ensure that all installation limitations as defined in this document are observed The internal battery capacity has been tested and verified to provide 30 m...

Page 14: ...on slaved directional gyro indicator Note that when installed as a DG a reversionary AI is available for display This functionality is supplemental only and does not satisfy requirements for a backup or standby attitude turn and slip or turn coordinator 7 2 Non Required Instrument Addition Approval is granted to install the AV 30 C as a non required instrument augmenting existing required instrume...

Page 15: ...e Performance Standards MOPS Title Category SAE AS8019 Airspeed Instruments Type B SAE AS392C Altimeter Pressure Actuated Sensitive Type Type I SAE AS8005A Standard Temperature Instruments Class IIIc SAE AS8034 Airborne Multipurpose Electronic Displays N A RTCA DO 334 Attitude and Heading Reference Systems AHRS A5 H9 T7 ASTM F3011 13 Angle Of Attack System N A RTCA DO 347 Cert and Test for Small a...

Page 16: ...e than 6000 lbs 6 seats or less including pilot copilot Installation is restricted to aircraft with a 25 000 foot maximum or less ceiling limitation Installation is restricted to aircraft with equal to or less than 300 knot Vne airspeed Installation may not be performed as part of an integrated autopilot system including heading bug interface attitude source or flight director display Installation...

Page 17: ...s of installation locations as a non required instrument The existing mechanically based altimeter and airspeed indicator must remain in their factory locations for this installation configuration Installation as a pilot configurable AI DG may not replace a primary instrument The replaced instruments may NOT be part of an autopilot or primary navigational display such as an integrated autopilot sy...

Page 18: ...s mandatory and non pilot accessible If the functionality is not locked pressing and holding the rotary knob will toggle between AI and DG mode This mode is only applicable for installation as a non required instrument An AV 30 C that replaces the Attitude Indicator must have the operating mode locked as an AI An AV 30 C that replaces that Directional Gyro must have the operating mode locked as a ...

Page 19: ...nnections are provided on the single 15 Pin D sub connector and two quick connect pneumatic fittings Various interfaces are optional and interface to some systems may require additional installation approval Do not plug the pitot and static lines Figure 3 AV 30 C Aircraft Systems Interfaces AI Mode Figure 4 AV 30 C Aircraft Systems Interfaces DG Mode ...

Page 20: ...or Graphical Indicated Airspeed Textual Pitot Static V Speeds Graphical Pitot Static Baro Altitude Textual Pitot Static Angle Of Attack Graphical Pitot Static Vertical Trend Graphical Pitot Static Vertical Speed Textual Pitot Static Set Altitude Textual None Heading Textual Pitot Static Bus Voltage Textual None G Load Textual None Outside Air Temp Textual OAT Probe True Airspeed Textual Pitot Stat...

Page 21: ... Interfaces Required Pitot and static connections are required for DG and AI modes Airspeed altitude derived angle of attack AoA True Airspeed TAS Density Altitude DALT DG heading and traffic altitude all require pitot and static connections as they are based on either altitude or airspeed measured from those connections When installed as a DG the pitot and static connections must be connected for...

Page 22: ...o connect directly to an audio panel typically a non switched or unswitched audio input High power outputs capable of directly driving a cockpit speaker are not provided Other unswitched unmuted inputs can be used but they may need to be mixed with an existing audio source Audio shields must be grounded only at audio panel to avoid ground loops Contact audio manufacture for further instructions Wh...

Page 23: ... are contained in 17 Serial Interface Specification 10 2 6 Internal Magnetometer Optional The internal magnetometer when available is detected in software version 2 1 2 or later It is currently disabled by configuration Application of magnetometer data requires calibration before use If magnetometer is desired and is not detected please contact uAvionix technical support to discuss upgrade options...

Page 24: ...tion 11 1 Overview Installation consists of the following steps Remove relocate any legacy instrumentation Add or locate an appropriate power source breaker Wire power and system interfaces as needed Mount the unit to the instrument panel with supplied screws Apply power and perform setup Connect pitot and static to both AI and DG Perform leak check after installation 11 2 Supplied Components Tabl...

Page 25: ...ired for each instrument OAT Probe Davtron P N C307PS Power and Interconnect Wire See AC 43 13 1B Chapter 11 7 for acceptable wire types 11 4 Installation Records The date of installation should be recorded in the aircraft s log book Entry should include instrument s being replaced AI or DG or both or if the installation is being performed as a non required instrument Entry should also include a d...

Page 26: ...UAV 1003947 001 AV 30 C Installation Manual 26 Rev E 11 5 Mechanical Drawing Figure 5 Mechanical Drawing ...

Page 27: ...nternal components Installing a mounting screw that is longer than optimal will not damage the unit but will result in the unit not being fully fastened to the panel Mounting Screw Optional Spacing Washer Instrument Panel Internal Components Figure 6 Mounting Screw Dept Limits The installation kit contains multiple length screws to assist in compensating for different instrument panel thicknesses ...

Page 28: ...G and therefore wiring varies based on installation Figure 7 and Figure 8 show connections for each configuration The primary difference is that the DG does not support audio alerting See AC 43 13 1B Chapter 11 7 for acceptable wire types for both power and interconnect purposes Figure 7 Wiring Diagram Attitude Indicator Position Installation ...

Page 29: ...G Position Installation 11 8 Bonding Requirements The following figure shows the grounding requirements for the electrical connections The two D Sub screws are to be utilized for shield and ground strap connections The supplied ring terminal connectors are sized for these screws ...

Page 30: ...p 8 or Less in Length The exposed non shielded portions of the interface cables AND the shield grounds are to remain less than 2 5 inches 2 5 Inches Maximum Non Shielded Shielded Figure 9 Shielded Cable The bond between the unit measured at the D sub screws to the aircraft frame must be 2 5 milli Ohms or less GROUND STRAP 8 AIRCRAFT GROUND CABLE SHIELD DRAIN 2 5 D SUB BACK SHELL Figure 10 Cable Sh...

Page 31: ...Connect 6 Spare Serial Input Reserved Do Not Connect 7 OAT Supply Output White Probe Wire 8 MFG Serial Input Reserved Do Not Connect 9 Ground Power Aircraft Ground 10 Aux Power Ret Power Reserved Do Not Connect 11 Audio H Output Audio Alerts Hi 12 Audio L Output Audio Panel Lo 13 Aux Power Out Power Reserved Do Not Connect 14 OAT Return Input White Blue Probe Wire 15 MFG Serial Output Reserved Do ...

Page 32: ...mpany logo unit model number and the currently installed software version Figure 10 Splash Screen Operation in both AI and DG modes share common user interface controls as follows Rotary Knob with Momentary Push Left Push Button Right Push Button Hold For Brightness Adjust Photo Cell Auto Screen Brightness TFT Color Display Figure 11 Common User Interface Components ...

Page 33: ...ails of this are covered in AV 30 C Pilots Guide UAV 1003946 001 and not addressed here The Setup Menu allows the pilot to set various configurations and alerting limits as desired for the type of operations being performed These are also covered in the Pilot s Guide referenced above The installer may wish to pre configure some or all these settings for the pilot but the default settings are accep...

Page 34: ...in control knob in while power is applied Figure 12 Installation Menu Access Keep the knob pressed until the startup logo has appeared The installation menu will now be enabled for access but will not automatically appear on the screen Ensure the unit is in AI or DG mode select the mode by pressing and holding the center button until the mode display changes When in AI or DG mode press and release...

Page 35: ...ing the knob when the desired field is shown will allow the associated setting to be adjusted After adjustment pressing the knob again will exit the editing mode but the installation menu will remain active Figure 14 Exiting Edit Mode Pressing DONE or a lack of user input for 30 seconds will exit the installation menu and return to the primary screen Figure 15 Setup Done Exit Option ...

Page 36: ... VNE AI Never exceed speed Set to match limits 40 to 300 knots 175 IAS VMC AI Minimum control airspeed with the critical engine inoperative Set to match limits 40 to 300 knots or disabled IAS VYSE AI Speed for best rate of climb OEI single engine Set to match limits 40 to 300 knots or disabled BARO UNITS AI Altimeter barometric units Inches of Mercury INHG Millibars MB TEMP UNITS AI OAT units Cels...

Page 37: ...ing mode Installation on a non required instrument may be locked or not locked based on owner preferences Pressing and holding the center knob when functionality is not locked will toggle between AI DG and MFD modes 13 1 3 Trim Set Pitch Roll and Slip Trim to accommodate any mounting variations o Accurate pitch roll and slip trim is important to ensure optimal performance Set IAS and Altitude Trim...

Page 38: ...ator input type Value GPS Source NONE No source available AV1 9600 Aviation format 9600 bps NMEA1 4800 NMEA format 4800 bps NMEA1 9600 NMEA format 9600 bps BEACON X tailBeaconX BEACON X must be selected for SERIAL 2 SERIAL 2 Set SERIAL 2 to NONE Value Serial 2 Source NONE No source available BEACON X tailBeaconX Do Not Enable unless authorized by follow on approval APA MINI Autopilot adapter Do No...

Page 39: ... used MAG1 Internal magnetometer provides correction data to DG Do Not Enable unless authorized by follow on approval MAG2 Internal magnetometer provides correction data to DG and aiding to core AHRS algorithm Do Not Enable unless authorized by follow on approval Rotate the center knob until AID MODE is displayed If the internal magnetometer is available P N UAV 1003429 002 then you will have a ch...

Page 40: ...rtup the ALIGN annunciator should be presented and flash This indicates internal sensor stabilization is occurring During the alignment do not move the aircraft This should extinguish within 3 minutes at which point valid attitude or direction indication is displayed If power is removed from the unit while it is still aligning the unit will go to battery mode until it has completed the alignment p...

Page 41: ...on 2 1 2 or later 2 With the AV 30 C in the AI mode enter the Install Menu page by pressing and releasing the left button repeatedly until the 3rd menu is displayed The aircraft must be on the ground with no movement Figure 18 Install Mode Selection 3 It is critical to ensure the aircraft is completely motionless and on the ground during the next several steps The aircraft should be in a hangar an...

Page 42: ...ed with a percentage complete Figure 20 Gyro Calibration Procedure 6 AV 30 C will indicate Calibration successfully completed Press DONE Press the left button under DONE and the calibration will be complete If an error is shown repeat the calibration process Figure 19 Gyro Calibration Selection ...

Page 43: ...Figure 22 OAT Indicator Note that OAT calibration is performed in the Setup procedures This step only ensures that the OAT probe is detected properly 13 2 4 GPS Navigator Interface If a GPS Navigator is connected utilize the display customization guidance provided in the Pilot s Guide to configure the display to show GPS navigational data in at least one textual display field The image below shows...

Page 44: ...cs of the aircraft and installation are suitable for use The check procedure is performed during an engine run up 1 Before applying power to the AV 30 C press and hold the center rotary knob and apply power As the splash screen appears check that a minimum version of 2 1 2 is displayed 2 Enter the Install Menu page by pressing and releasing the left button repeatedly until the 3rd menu is displaye...

Page 45: ... propeller balancing Replace worn engine mounts and address causes of high engine vibration Ensure the AV 30 C is not mounted in a location subject to high vibration This can often be detected by placing your hand on various locations in the panel and can be caused by poorly supported panel regions adjacent equipment or proximity to engine structure On isolated panels replace the grommets concurre...

Page 46: ...r on the AV 30 C and perform the following tests as they apply to the existing aircraft equipment 5 Observe load shedding procedures as appropriate for the aircraft during testing to ensure adequate power to complete the testing while maintaining enough reserve to support pre flight and engine start VHF COM RADIOS Verify AV 30 C operates without interference from the VHF COM operation 1 Power on t...

Page 47: ...at would prevent identification ADDITIONAL AVIONICS Additional Avionics should be tested according to the manufacturer EMC EMI test procedures This testing assumes the existing equipment is functional and operating correctly at time of testing The following summarizes a typical EMC test 1 Operate the AV 30 C 2 Operate the existing installed avionics according to manufacturer instructions If capabl...

Page 48: ...Slip show small but constant error Ensure unit is level in panel using a bubble level or similar Set trim adjustment in Installation menu See Installation Manual for instructions Airspeed or Altitude shows small but constant error Set trim adjustment in Installation menu See Installation Manual for instructions Interface GPS information is expected but does not show up in data overlays Check GPS i...

Page 49: ...CA for replacement inspection requirements and procedures The ICA addresses the following aspects of continued airworthiness Visual Inspection Procedure Altimeter Test and Calibration Battery Test and Replacement Procedure 16 Aircraft Flight Manual Supplements See AV 30 C Flight Manual Supplement UAV 1004044 001 for normal emergency and limitations as required by CFR 23 1581 ...

Page 50: ...kets received are as follows Table 9 GPS Serial Specification Parameter Name Aviation Packet NMEA Packet GPS Track C Packet GPRMC Field 8 GPS Ground Speed D Packet GPRMC Field 7 Distance to Waypoint E Packet GPRMB Field 10 Cross Track Error G Packet GPRMB Field 2 Desired Track I Packet Computed Waypoint ID K Packet GPRMB Field 5 Bearing to Waypoint L Packet GPRMB Field 11 Magnetic Variation Q Pack...

Page 51: ...8 Field Update Capability The unit software can be field updated Updating requires an in line harness and Windows based PC Contact uAvionix support for additional information or reference available Service Bulletins Figure 26 Field Update Interface Diagram ...

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