OASIS Standby Instrument System Installation Manual Aerosonic Corporation September 18, 2012 1212 N. Hercules Ave. Clearwater, FL 33765 USA
INSTALLATION MANUAL OASIS Original Aerosonic Standby Instrument System Document No: Revision: X Title and Name Signature and Date Aerosonic Corporation September 18, 2012 1212 N. Hercules Ave. Clearwater, FL 33765 USA
This page intentionally left blank
1 Table of Contents 1... Table of Contents... 4 1... GENERAL DESCRIPTION... 6 1.1 Introduction... 6 1.2 Scope... 6 2... INSTALLATION... 6 2.1 UNPACKING AND INSPECTING... 6 2.2 INSTALLATION PROCEDURES... 6 2.2.1 Location... 6 2.2.2 Electrical Connections... 6 2.2.3 Installation... Error! Bookmark not defined. 2.2.4 Installation Guidelines for the SLZ7367...19
This page intentionally left blank
1 GENERAL DESCRIPTION 1.1 Introduction This manual covers the OASIS standby instrument system, which includes the Display Unit (DU), Aerosonic Sensor Unit (ASU) and the optional Magnetometer (MSU). NOTE Installation must be made by qualified personnel, in conformance with applicable government regulations. Standard installation practices described in FAA Advisory Circular No. 43.1.-2B Acceptable Methods, Techniques, and Practices Aircraft Alterations must be followed. The information furnished is for convenience only. 1.2 Scope This manual applies to the installation of the OASIS standby display, remote sensor unit and the optional external magnetometer. 2 INSTALLATION 2.1 UNPACKING AND INSPECTING Carefully unpack the unit and note any damage to shipping containers or equipment. Visually inspect each component for evidence of damage. Compare the equipment received with that noted on the packing list. Immediately report any missing items or evidence of damage to the carrier making delivery. Every effort should be made to retain the original shipping containers for storage. If the original containers are not available, a separate cardboard container should be prepared that is large enough to accommodate sufficient packing material to prevent movement. 2.2 GENERAL INSTALLATION PROCEDURES NOTES 1. Standard installation practices prescribed in FAA Advisory Circular Number AC 43.13-2B must be followed. 2.3 Electrical Connections 1. The installer must take the following into consideration before installation. All wiring must be in accordance with industry-accepted methods, techniques, and practices. Refer to FAA Advisory Circular AC43.13-2B, Section 4 and Section 8 for aircraft wiring requirements. The installer is responsible for supplying wires, cables and connectors. All wires should be 22 AWG unless otherwise noted. Use IL-DTL16878 or equivalent wire and M27500 or equivalent for twisted shielded wired for installation. The length and routing of the external cables must be carefully studied and planned before attempting installation of equipment.
Wire-marking identification is at the discretion of the installer. The OASIS system should be placed on it s own spare circuit breaker. Use of any cable not meeting specifications voids all warranties. 2. Refer to the appropriate Interconnect Wiring Diagram in Figures #-# and : 3. Wires and cables associated with the OASIS installation shall be fabricated from, Shielded cable shall be in accordance with MIL-C-27500 and non-shielded wire shall be in accordance with MIL-W-22759/16. Wires shall be cut to length as required at the time of installation. Wires shall be cut with sufficient length to adhere to the main aircraft wire runs while maintaining specific aircraft installation practices in accordance with the specific aircraft maintenance manual. Reference the specific aircraft maintenance manual as the primary source for wiring identification and installation practices. Wires are installed and terminated in accordance with the system wiring diagrams in figures XX and XX Figure #-# shows specific recommendation for shield termination for the MIL-27500 shielded cables for the OASIS system mating connectors. It is recommended that no more than four shield wires be connected to a lug. Solder sleeves shown in illustration are S03-03-R-100 from Allied Electronics/Tyco FIGURE 1 SHIELD TERMINATIONS
2.4 DISPLAY UNIT INSTALLATION When locating the OASIS DU in the instrument panel, take the following information into consideration. 1. The OASIS DU should be located in an area where the softkey buttons are within easy reach of the pilot. 2. The OASIS should be accessible for inspection, maintenance, or removal and free from instrument panel structural flexure and excessive vibration or heat. 3. The OASIS wiring cable should not run adjacent to heaters, engine exhaust, heat sources or any high energy electrical sources that may cause electromagnetic interference. 4. Compare the space requirements of the OASIS with the installation area being considered. Refer to Figure 3 for dimensional requirements. FIGURE 2 OASIS DU
FIGURE 3 DU DIMENSIONS
Perform the following installation procedures to install the OASIS standby display. 5. See figures 4 and 5 for typical instrument panel mounting location for the Oasis DU. FIGURE 4 TYPICAL FIXED WING INSTRUMENT PANEL FIGURE 5 TYPICAL ROTARY WING INSTRUMENT PANEL
6. The panel must be cutout if a suitable ATI-3 hole is not available, see Fig 6 for the Instrument cutout dimensions. FIGURE 6 DU PANEL CUTOUT
7. The Oasis DU is secured in the Instrument panel using a 69020-6 ARINC 408A mooring plate, see figure 7. FIGURE 7 DU PANEL INSTALL
8. The Display Unit connector views are shown in Figure 8. The mating connector for the DU is D38999/26FD35S with a M85049/38s15 Strain Relief Clamp. FIGURE 8 DISPLAY UNIT CONNECTOR FACE VIEWS
2.5 AEROSONIC SENSOR UNIT INSTALLATION The Aerosonic Sensor Unit (ASU) is a separate remote mounted LRU that provides power and sensor data to the OASIS DU. The ASU is connected to the aircraft DC buss and powers up to two DU s and a MCU. Sensors within the ASU provide for computation of Indicated Airspeed, Barometric Corrected Altitude, Pressure Altitude and slip/skid. With the remote Magnetometer Heading information is provided to the DU. The ASU can have a internal battery that allows operation for a minimum of 1 hour without aircraft power. The ASU has a STATIC fitting and a PITOT fitting that connect into the aircraft Pitot/Static system For the dimensions of the ASU see Figure FIGURE 9 AEROSONIC SENSOR UNIT
FIGURE 10 ASU DIMENSIONS
For mounting dimensions for the ASU see Figure 11. FIGURE 11 ASU MOUNTING DIMENSIONS
Table 1 provides the installation limits for the ASU installation, Use the following guidelines when measuring angles: Roll angle is (+) right bank and (-) is left bank Pitch angle is (+) nose up and (-) nose down Yaw direction is (+) right yaw and (-) left yaw The ASU must be mounted either parallel to the aircraft centerline or at 90 degrees to the aircraft centerline. The unit may be mounted upright on the mounting surface or may be hung from the mounting surface. TABLE 1 ASU INSTALLATION LIMITS PITCH ROLL YAW The ASU allowed orientations are as shown in Table 2 following TABLE 2 ALLOWED ASU ORIENTATIONS Orientation Bits (3-0) Connector End Axis ASU Mounting Surface 0000 -X +Z 0001 +Y +Z 0010 +Y +Z 0011 -Y +Z 0100 +X -Z 0101 -Y -Z 0110 -X -Z 0111 +Y -Z 1000 -Z +X 1001 +Y +X 1010 +Z +X 1011 -Y +X 1100 -Z -X 1101 +Y -X 1110 +Z -X 1111 -Y -X
See Figure 12 for the connector face views PITOT/STATIC CONNECTIONS PITOT PORT CONNECTION FIGURE 12 ASU CONNECTOR FACE VIEWS The Pitot fitting on the ASU is an AN4 Male fitting with MS33656-4 (7/16-20 thread for ¼ tubing). STATIC PORT CONNECTION The Static fitting on the ASU is an AN6 Male fitting with MS33656-6 (9/16-18 thread for 3/8 tubing).
2.6 INSTALLATION GUIDELINES FOR THE MSU The SLZ7367 Magnetic Sensing Unit (MSU) can be seen in Figure x. Note that the direction of flight (forward in the aircraft) is away from the cable assembly. Strain reliefs are provided at both the housing and connector. FIGURE 13 MAGNETIC SENSOR UNIT See Figure 14 for the dimensions of the MSU FIGURE 14 MSU DIMENSIONS
Note: All mounting hardware must be non-ferrous materials. The MSU is a 3 axis magnetic sensor that is extremely sensitive to magnetic fields; therefore, the use of non-magnetic materials to secure the MSU to the airframe is required. The MSU requires 3 #10-32 socket head screws (i.e. MS16996-11 or Series 300 Non-Magnetic Stainless Steel) torqued to 31.7 inch lbs. Aluminum or brass screws may also be used provided that they are torqued appropriately. NAS620-C10L Washers (or equivalent non-magnetic washers) may also be used with the screws. The pattern for the mounting holes of the MSU is shown in Figure. The mounting holes are slotted to allow the installer flexibility in aligning the direction of flight axis of the MSU with the aircraft s longitudinal axis. The MSU must be installed in the aircraft such that the forward direction of the MSU box is within ±0.5 of parallel alignment with the aircraft s longitudinal axis. The direction of flight (aircraft forward) is away from the cable assembly. Note that the MSU mounting flange is 0.25 above the bottom of the MSU. An aluminum bracket is recommended with a 3 round hole for the MSU. The MSU should be mounted such that it is within 2 degrees of aircraft level. Refer to Maintenance manual for the aircraft to determine aircraft level. The MSU must be installed in the aircraft in a location where there is minimal magnetic interference from other devices in the aircraft and in such a location where physical excursions resulting from natural oscillations are minimal. To insure this, the MSU must be placed as far away as possible from ferromagnetic metals such as iron, cobalt and permalloy. It should also be placed as far away as possible from wires carrying any significant current. Failure to install the MSU in a magnetically friendly environment will result in heading errors which cannot be removed by field calibration. The following guidelines are recommended for MSU installation: The MSU shall be mounted no closer than 10 ft to electric motor and relays. The MSU shall be mounted no closer than 8 ft to ferromagnetic structures greater than 1 kg. The MSU shall be mounted no closer than 4 ft to ferromagnetic structures less than 1 kg. The MSU shall be mounted no closer than 4 ft to any electrical component/conductor drawing in excess of 100mA. The MSU shall be mounted no closer than 2 ft to any electrical component/conductors drawing less than 100 ma. Typical installation areas are the tail section or wing tips (See Appendix X). In rotor craft, installation is usually below the main cabin or in the tail boom away from any rotating ferromagnetic shafts. Installation of the MSU within 2 feet of the cabin is not recommended due to potential interference that would affect the performance of the device. When mounting the MSU in the wing, it is recommended that the wing tip lights have a dedicated power ground supplied through a twisted pair of wire back into the fuselage as opposed to a ground reference back to airframe ground. This will prevent current flow in the wing skin that may degrade the performance of the MSU.
See Figure 15 for the mounting dimensions for the MSU. FIGURE 15 MSU MOUNTING DIMENSIONS The AHR150A-2-A has a cable and six pin connector with a total length of 17.3 ± 0.3. The interconnecting cable should consist of 3 #22 gauge twisted, shielded pairs. The AHR150A-2-A cable connection is given in Error! Reference source not found. The minimum allowable bend radius for the cable is 2.3 (minor axis). NOTE: There is no reverse or short circuit power protection on the AHR150A-2-A. Failure to connect the device as defined in Error! Reference source not found. will result in damage to the AHR150A-2-A, the host AHRU supplying power to the AHR150A-2-A, or both. The shielded cable can be extended to a maximum distance of 100 ft. The mating connector for the AHR150A-2-A cable is D38999/24JB98SN or equivalent, with a M85049/38S11 Strain Relief Clamp. See Figure 16 for the connector face views
FIGURE 16 MSU CONNECTOR FACE VIEWS Pin Name Signal (RS422 Mode) TABLE 3: MSU CABLE DEFINITION Signal (RS485 Mode) Connection A RS422 Tx A, Positive RS485 Tx/Rx A, Positive To the RS422 receiver A terminal or RS485 Tx/Rx A. B Power, Negative Power, Negative Power Supply Ground. (Case Isolated) C RS422 Rx B, Negative No Connect Factory Calibration & Field Calibration Only. D RS422 Rx A, Positive No Connect Factory Calibration & Field Calibration Only. E RS422 Tx B, Negative RS485 Tx/Rx B, Negative To the RS422 receiver B terminal or RS485 Tx/Rx B. F Power, Positive Power, Positive Power Supply 9 VDC (Nominal).
APPENDIX A: SUGGESTED LRU LOCATIONS FIGURE 17 FIXED WING LRU LOCATIONS
FIGURE 18 ROTART WING LRU LOCATIONS
APPENDIX B: System Wiring Diagrams FIGURE 19 SINGLE DU WIRING DIAGRAM
FIGURE 20 DUAL DU WIRING DIAGRAM
APPENDIX C: WEIGHT AND BALANCE Weight and Balance The change to the aircraft empty weight must be determined as follows: 1. List all of the equipment removed from the aircraft in Table C-1 in order to facilitate the addition of the OASIS system. 2. If the aircraft equipment list does not provide moments, multiply the item Weight by the item Arm to calculate the Moment. 3. Add all the removed weights to determine a Total Removed Weight. 4. Add all the removed moments to determine a Total Removed Moment. ITEM MAKE DESCRIPTION PART No. Weight (Pounds) ARM (Inches) MOMENT (Lb-in) ---- Removed Wire, Connectors, etc. TOTAL REMOVED EQUIPMENT 5. The OASIS equipment is listed in Table. Insert the arms of the installed items in the appropriate cell of the ARM column. 6. Insert a weight for the install wire, cable, connectors and brackets 7. Multiply the Weight by the Arm to calculate the Moment of each installed item. 8. Add all the installed weights to determine a Total Installed Weight, Do not include the MSU weight in the total if not installed. 9. Add all the installed moments to determine a Total Installed Moment. Do not include MSU moment if not installed.
ITEM MAKE DESCRIPTION PART No. Weight (Pounds) 1 Aerosonic Display Unit SLZ7363.710 2 Aerosonic Sensor Unit SLZ7366 2.2 3 Aerosonic Magnetometer SLZ7367.3317 TOTAL INSTALLED EQUIPMENT: ARM (Inches Moment (Lb-in) TOTAL CHANGE 10. Calculate the total weight change by subtracting the Total Removed Equipment Weight from the Total Installed Equipment Weight. 11. Calculate the total Moment change by subtracting the Total Removed Equipment Moment from the Total Installed Equipment Moment. 12. Enter these totals in the Total Change cells for Weight and Moment. 13. Update the aircraft empty weight and balance report to include the changes listed above.
APPRENDIX D: ELECTRICAL LOAD EFFECTS Electrical Load Effects The aircraft electrical load analysis must be checked to ensure the aircraft electrical system is able to operate safely with the newly installed OASIS sytem. The electrical load analysis must be checked for two conditions- the total aircraft load is less than the current generating capability of the aircraft electrical source equipment (battery, generator, alternator, etc.) and, the load on the bus used to power the OASIS is less than the maximum load approved for that bus. These maximum load capabilities are provided in the aircraft maintenance manuals. Please note that the ASU provides the power for the DU and the MSU. Update the aircraft electrical load analysis using the electrical load effects shown in Table ITEM MANUFACTURE DESCRIPTION PART NO. POWER REQUIRMENTS 1 Aerosonic DU SLZ7365 28.0 Vdc 3.7 W Max 2 Aerosonic ASU SLZ7366 28.0 Vdc 17 W (1 DU, 1 MSU) X W (2 DU, 1 MSU)