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Installation Manual and Operating Instructions Model MD302 Series

1. Standby Attitude Module FIGURE 2 5 MD302 OUTLINE DRAWING Unit Versions Part Number Battery Yes 6420302 2 6420302 3 6420302 4 Yes 6420302 5 6420302 6 Remote mounted unit version Contact manufacturer for details Non standard version Mid Continent Instruments and Avionics TABLE 2 2 MD302 UNIT VERSIONS 20 Manual Number 9017782 Revision H January 7 2015 a AX 16 0 01 thru N 0 175 X 82 countersink AX R 0 10 max only 1 of 3 required per side 2 i js 9 i l gt i W 750 2 34 0 02 T i 2 090 750 3 25 0 05 O e 295 50 50 5 220 FIGURE 2 6 PANEL CUTOUT STEP 1 FIGURE 2 7 INSTALL ILLUSTRATION Mid Continent Instruments and Avionics 21 Manual Number 9017782 Revision H January 7 2015 SECTION 3 OPERATION IMPORTANT READ THIS ENTIRE SECTION PRIOR TO OPERATING THE UNIT IN FLIGHT This section contains information on how to use and interpret the information presented to the pilot and crew during normal and emergency operation of the MD302 SAM Standby Attitude Module 3 1 USER INTERFACE The MD302 SAM Standby Attitude Module is desig
2. 16 800 FIGURE 4 9 VNE CASE 2 260 4 250 n 240 230 4 2 220 VNE case 1 210 J e VNE case 2 200 T T T T T 0 5000 10000 15000 20000 25000 Baro Altitude Ft FIGURE 4 10 VNE CURVE Mid Continent Instruments and Avionics 42 Manual Number 9017782 Revision H January 7 2015 4 3 CONFIGURE ARINC The CONFIGURE ARINC action presents the option to select either LOW or HIGH speed serial communication data This option configures the unit s ability to output ARINC 429 communication data as listed in Table 1 5 Select the option which corresponds to the receiving equipment s capability in regards to data speed expectation Figure 4 11 CONFIGURE MENU gt CONFIGURE ARINC CONFIGURE AIRCRAFT LOW SPEED CONFIGURE ARINC HIGH SPEED CONFIGURE DIMMING CONFIGURE DISPLAY CONFIGURE HEADING CALIBRATE PRESSURES FIGURE 4 11 CONFIGURE ARINC 4 4 CONFIGURE DIMMING When the CONFIGURE DIMMING menu option is selected the sub menu and its various options are displayed The EXIT selection will return the user back to the CONFIGURE MENU Figure 4 12 Within the CONFIGURE DIMMING sub menu are the following options e DIMMING CONTROL e DIMMING CURVE e EXIT CONFIGURE MENU CONFIGURE AIRCRAFT CONFIGURE ARINC CONFIGURE DIMMING gt CONFIGURE DIMMING DIMMING CONTROL DIMMING CURVE EXIT CONFIGURE DISPLAY CONFIGURE HEADIN
3. 80 or one hundred sixty 160 units from top to bottom depending on unit type The airspeed tape will roll or scroll to assist in quick reference as to the increasing or decreasing nature of the aircrafts airspeed The airspeed limitations also known as V speeds or range markings are indicated with colored bands placed vertically along the left margin next to the airspeed tape The colors and values of each bar can be set during installation in Configuration Mode see Section 4 Colors should be selected based on industry defined colors and V speed limits as defined by the aircraft s specific Pilots Operating Handbook POH Range markings are represented by full width bars half width bars and or radial marks A traditional barber pole may also be displayed if required by the aircraft and provides the appropriate Vye Vmo and or Myo values 3 3 1 4 SLIP OPERATION The slip indicator portion of the display will appear at the bottom of the attitude display see Figure 3 3 If heading is enabled the slip indicator portion of the display will appear above and to the left of the heading window Figure 3 9 The slip indicator is represented by a shaded translucent background with two white lines around center and a white ball When the ball is maintained between the vertical lines during banking maneuvers the turn is considered coordinated without slip Electronic damping of the ball movement is provided to prevent overly sensitive
4. NOMENCLATURE 2 inch Standby Attitude Module SAM MODEL NUMBER MD302 Series PART NUMBER 6420302 TSO NUMBERS C2d Type B C3e C4c C10b C106 C113a C179a MANUFACTURERS SPECIFICATIONS Minimum Performance Specifications T9302 TDS302 Qualification Test Reports QTR1201 10 04 05 MANUFACTURER Mid Continent Instrument Co Inc ADDRESS 9400 E 34 St North Wichita KS 67226 USA RTCA DO 160 Rev G dtd 12 08 10 DATES TESTED 06 12 09 12 03 13 CONDITIONS SECTION DESCRIPTION OF TEST Temperature and Altitude 4 Category F1 Low Temperature 4 5 1 Short and Normal Operating Low Temp 30C High Temperature 4 5 2 Short and Normal Operating High Temp 70C Decompression 4 6 2 Altitude 55K Overpressure 4 6 3 15 000 ft Temperature Variation 5 CategoyS2 Humidity 1 6 CategoyA Operational Shock and 7 Category B Crash Safety Vibration Fixed Wing Category R Curves B B1 Helicopter Category U Curve G RBB1 UG Lg a Explosion Category X Audio Frequency Conducted 18 Category Z susceptibility Induced Signal Susceptibility Category ZC Radio Frequency Susceptibility 20 Category W conducted Category F radiated WF Emission of Radio Freq Energy Category P Lightning Induced Transient 22 Category B3 pin injection Susceptibility Category H3L3 cable bundle B3H3L3 B3K3L3 Category X REMARKS Sections 4 Category F1 complete with addition
5. and total operating time Figure 1 1 manufacturer s logo y M ic roO nti nent INSTRUMENTS AVIONICS eos SAN METER silat S W VERSION 1 0 total operating time RUN TIME HRS 44 m MidContinent NL Mid Continent NSTRUMENTS AVIONICS NSTRUMENTS AVIONICS SAM 0302 SAM mp302 S W VERSION 1 0 1 S W VERSION 1 0 1 RUN TIME HRS 1764 RUN TIME HRS 1764 J FIGURE 1 1 PRE FLIGHT MODE Mid Continent Instruments and Avionics 7 Manual Number 9017782 Revision H January 7 2015 1 2 2 FLIGHT MODE In Flight Mode the unit operates normally by displaying attitude altitude airspeed and slip information Figure 1 2 roll bank scale pitch scale symbolic airplane slip indicator barometer value altitude window airspeed window altitude trend bar altitude units airspeed units altitude scale airspeed scale E BARO 900 20 30 00 800 CTS FEET 480 jouu 500 FIGURE 1 2 FLIGHT MODE Mid Continent Instruments and Avionics 8 Manual Number 9017782 Revision H January 7 2015 1 2 3 EMERGENCY MODE In Emergency Mode aircraft power to the instrument has been lost and the unit continues to operate in Flight Mode utilizing power from the internal battery This is indicated with a battery icon displayed on the attitude display Figure 1 3 1 at J a battery icon A ed TY d IO 10 FIGURE 1 3 EMERGENCY MODE 1 2 4 CONFIGURATI
6. 8 Turn the Control Knob to highlight the UPDATE SOFTWARE option External power must be applied to complete this step Software updates cannot be performed using internal battery power 9 Press the Control Knob to initiate the software load Mid Continent Instruments and Avionics 52 Manual Number 9017782 Revision H SECTION 5 CONFORMANCE January 7 2015 If the software update is unsuccessful a message will display FAILED UPDATE Should this occur remove the USB flash drive power down the unit and return to Step 5 of the Service Action above If the error message persists contact Mid Continent Instruments and Avionics 10 When the software load is complete the unit will display SUCCESSFUL UPDATE 11 Press and hold the Control Knob on the faceplate Continue holding as prompted up to 10 seconds until the Pre Flight Screen appears Once the CONFIGURE MENU is displayed the unit is in Configuration Mode Please note in some installations a dialog box may appear displaying an error message or an inverted error message This is normal Press the Control Knob to acknowledge the message and continue Settings will not be lost but will be updated once steps 11 13 are completed 12 Turn the Control Knob to highlight the ACCEPT CHANGES option 13 Press the Control Knob to accept changes 14 The unit will reboot into Flight Mode 15 To verify proper software load confirm that the new software version number is displayed on th
7. DOS oaa 1500 to 55 000 FT SEE IM FOR LIMITS RICA DO 2 Lad DOVER Lo K DOBOG n Nes NEEEEHEE ETSO C2d Cd nco Y e CEN ETO tn EUROCAE ED M ED O ED 80 RTCA DO SEE IM FOR LIMITS Ed S S FIGURE 2 2 NAMEPLATE AND MOD STATUS Mid Continent Instruments and Avionics 15 Manual Number 9017782 Revision H January 7 2015 2 6 CABLE HARNESS Construct the cable harness in accordance with the instructions below including the Connector Pinout of Table 2 1 and Figure 2 3 and Configuration Module Assembly of Figure 2 4 Installers should follow industry accepted practices regarding aircraft wiring and applicable regulatory requirements and guidance The instructions for constructing the cable harness as listed within this manual were also used to construct the harness during environmental and electrical testing Alterations may invalidate environmental qualification and or performance results Refer to Section 2 3 Equipment Location for routing precautions 2 6 1 WIRE GAUGE SELECTION Wire gauge should be 22 AWG Use of PTFE ETFE TFE Teflon or Tefzel insulated wire is recommended for aircraft use per MIL DTL 16878 or equivalent Additionally for data signals associated with ARINC 429 inputs and outputs shielded twisted pair wiring per M27500 or equivalent is recommended pin pairs 3 amp 8 and 12 amp 13 2 6 2 CONFIGURATION MODULE The supplied custom configuration module is required for proper installation and operation
8. NL MidCtontinent Installation Manual and Operating Instructions Model MD302 Series SAM Standby Attitude Module f BARO Y pur 170 29 92 8000 0 io 180 1 A Tuy T Teao Pla m ix To Mid Continent Instruments and Avionics Mid Continent Instrument Co Inc dba Mid Continent Instruments and Avionics 9400 E 34 Street N Wichita KS 67226 USA PH 800 821 1212 Manual Number 9017782 FX 316 630 0723 Revision H January 7 2015 FOREWORD This manual provides information intended for use by persons who in accordance with current regulatory requirements are qualified to install this equipment If further information is required please contact Mid Continent Instruments and Avionics Attn Customer Service Dept 9400 E 34 St N Wichita KS 67226 USA Phone 316 630 0101 Fax 316 630 0723 ks customerservice mcico com www mcico com We welcome your comments concerning this manual Although every effort has been made to keep it free of errors some may occur When reporting a specific problem please describe it briefly and include the manual part number the paragraph figure table number and the page number Send your comments to Mid Continent Instruments and Avionics Attn Customer Service Dept 9400 E 34 St N Wichita KS 67226 USA Phone 316 630 0101 Fax 316 630 0723 ks customerservice mcico com Copyright 2014 Mid Continent Instrument Co Inc Mid Continent Instru
9. followed by entering Flight Mode Figure 4 29 CONFIGURE MENU CONFIGURE HEADING CALIBRATE PRESSURES UPDATE SOFT WARE BATTERY STORAGE MODE ACCEPT CHANGES CANCEL CHANGES FIGURE 4 29 ACCEPT CHANGES 4 7 5 CANCEL CHANGES When selecting CANCEL CHANGES any settings or changes made while in Configuration Mode are canceled ANY SETTINGS WILL NOT BE SAVED After selecting CANCEL CHANGES the unit will automatically reset and return to the Pre flight Mode followed by entering Flight Mode Figure 4 30 CONFIGURE MENU CONFIGURE HEADING CALIBRATE PRESSURES UPDATE SOFT WARE BATTERY STORAGE MODE ACCEPT CHANGES CANCEL CHANGES FIGURE 4 30 CANCEL CHANGES Mid Continent Instruments and Avionics 51 Manual Number 9017782 Revision H January 7 2015 5 1 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 5 1 1 PRESSURE SYSTEM AND ALTIMETER VERIFICATION Per federal regulation 14 CFR 91 411 it is required that each static pressure system and each altimeter have been tested and inspected within the last twenty four 24 months See Section 4 6 to calibrate pressures should pressures be out of calibration per 14 CFR 91 411 5 1 2 SOFTWARE UPDATES Mid Continent will have on occasion the need to update the software of the MD302 to maintain improve and or enhance functionality or performance With the MD302 s easy field upgrade option the unit does not have to be returned to the factory and in some cases may not have to be re
10. on the front of the panel for the bezel of the unit which will extend significantly outside the main rectangular cutout e he dimension of the smaller side of the rectangle is critical for a good finished appearance If it is too large the cutout will be visible outside the unit bezel The relationship of the holes to the cutout should be maintained closely to ensure proper installation e One countersink hole on either side of the rectangular cutout is required Any of the three hole locations is acceptable More than one countersink hole on each side is optional Screws for these holes will retain the Nutplate and not support the weight of the unit e Verify that a flathead screw will sit flush or below the panel surface in the countersink holes If not deepen the countersinks slightly e Remove burrs around the cutout and holes to allow the unit to mount flush with the panel 2 Install the Nutplate on the backside of the instrument panel using at least one 1 flathead screw on each side of the rectangular cutout e The Nutplate should mount flush to the backside of the instrument panel The threaded nuts in corners of the Nutplate should protrude to the rear 3 Route the prepared cable harness and pitot static fittings from behind the panel and through the panel cutout The length of the cable harness should allow the unit to be connected in front of the panel 4 VERIFY THAT AIRCRAFT POWER IS TURNED OFF 5 Connect the cable harness wit
11. or hoses during flight and cause undesirable effects Mid Continent Instruments and Avionics 12 Manual Number 9017782 Revision H January 7 2015 side view l l l l l l l pt l Panel tilt 90 to 90 horizontal shown also applicable for vertical VERTICAL KNOB LEFT BARO 30 00 1900 A direction of flight top view MUST BE INSTALLED IN THE DIRECTION OF FLIGHT horizontal shown also applicable for vertical VERTICAL KNOB RIGHT BARO 1900 30 00 800 HORIZONTAL ATTITUDE LEFT Mid Continent Instruments and Avionics HORIZONTAL ATTITUDE RIGHT FIGURE 2 1 INSTALLATION ORIENTATION OPTIONS 13 Manual Number 9017782 Revision H January 7 2015 2 4 LIMITATIONS The conditions and tests for TSO approval of this article are minimum performance standards Those installing this article on or in a specific type or class of aircraft must determine that the aircraft installation conditions are within the TSO standards specification of the article and deviations listed below TSO articles must have separate approval for installation in an aircraft The article may be installed only according to 14 CFR Part 43 or the applicable airworthiness requirements There are some portions of the approved TSOs which represent outdated requirements or do not apply to the product These items are highlighted below and have been submitted to and approved by the FAA as deviations t
12. response and comply with regulatory requirements 3 3 2 OPTIONS MENU While in Flight Mode the Options Menu is available to the pilot or cockpit crew members The Options Menu offers multiple selections that are available during flight but do not affect the aircraft specific configuration of the unit these must be set in Configuration Mode by authorized personnel during installation and or maintenance These options are provided for convenience preference or potentially necessary in flight adjustments The Options Menu can be accessed by pushing and holding the control knob for approximately two 2 seconds The brightness adjustment bar will appear briefly before the menu is visible The menu will appear in place of the attitude display and will revert to the active attitude display if no activity occurs for ten 10 seconds The menu title displays an indication gt if there is a sub menu associated with it The Option Menu root menu contains the following options Figure 3 11 e e BAROUNITS e SYMBOL BARO UNITS i ATT MASK ME Bom ALT TREND INFO gt e EXIT MENU EXIT MENU e POWER OFF FIGURE 3 11 OPTIONS MENU Mid Continent Instruments and Avionics 29 Manual Number 9017782 Revision H January 7 2015 3 3 2 1 MENU OPERATION The menu parts are defined below Menu title white text on a blue background at the top of each menu highlighted by a white box and green background Selectable items any selectable item on the m
13. shelf life by temporarily disabling battery operation until the unit is restarted by external power To utilize this function first select the BATTERY STORAGE MODE option from the CONFIGURE MENU Figure 4 26 CONFIGURE MENU CONFIGURE HEADING CALIBRATE PRESSURES UPDATE SOFT WARE ACCEPT CHANGES CANCEL CHANGES FIGURE 4 26 BATTERY STORAGE MODE Once the BATTERY STORAGE MODE function is selected two screens will appear The first screen will read ENTERING STORAGE MODE and a yellow status bar will appear Figure 4 27 After the unit is in storage mode a second screen will read TURN OFF EXTERNAL POWER NOW and at this time external power should be removed Figure 4 28 The unit is now in BATTERY STORAGE MODE NOTE Upon applying external power the unit will ext BATTERY STORAGE MODE and return to normal operation ENTERING STORAGE MODE _z FIGURE 4 27 ENTERING STORAGE MODE Mid Continent Instruments and Avionics 50 Manual Number 9017782 Revision H January 7 2015 TURN OFF EXTERNAL POWER NOW FIGURE 4 28 TURN OFF EXTERNAL POWER 4 7 4 ACCEPT CHANGES When selecting ACCEPT CHANGES all settings and changes made while in Configuration Mode are saved into memory and saved to the Configuration Module memory as well NOTE SETTINGS WILL NOT BE SAVED UNLESS ACCEPT CHANGES IS SELECTED WHEN DONE After selecting ACCEPT CHANGES the unit will automatically reset and return to the Pre flight Mode
14. the aircraft However within the limitations of the environmental qualifications other locations may be acceptable when considered within the context of the specific application and with the appropriate installation certification The MD302 has an extra wide viewing angle and AnyWay selectable orientation that allows for flexible installation locations and options The unit can be mounted vertically knob left or knob right or horizontally attitude left or attitude right During configuration the display orientation can be selected to match the desired installation However when selecting a location to install the MD302 be sure to consider appropriate field of view with regard to pilot and or co pilot visibility and accessibility Note when installing in vertical orientation choose the knob position based on whether or not the pilot s hand will obscure the display during operation Figure 2 1 Additionally consider what equipment is behind the panel which may impede the installation of the MD302 Clearance for the unit as well as its electrical and pneumatic connections and routing must be allowed Be aware of routing cables near other electronics or with other wire bundles that may be susceptible to high energy flow Avoid sharp bends in cabling or hoses and routing near aircraft control cables Also avoid proximity and contact with aircraft structures avionics equipment heat sources or other obstructions that could chafe or damage wires
15. value manual changing Barometer value synced changing Oo Oo lalelei 300 200 FIGURE 3 7 ALTITUDE OPERATION BARO CHANGE Mid Continent Instruments and Avionics 27 Manual Number 9017782 Revision H January 7 2015 3 3 1 2 1 ALTITUDE TREND The altitude trend bar is located along the right margin of the altitude display This feature is optional and can be turned on or off using the Options Menu see Section 3 3 2 The trend bar is magenta in color and originates at the current altitude on the altitude tape always from the middle of the display directly across from the altitude pointer The height of the trend bar above or below the current altitude indicates the altitude of the aircraft on the altitude tape if the current vertical speed or altitude trend is maintained over a period of six 6 seconds For example in Figure 3 5 the current altitude is approximately 9 315 feet The trend bar is at approximately 9 325 feet indicating that the aircraft s altitude will be 9 325 feet in 6 seconds if the current vertical speed or climb is maintained constant The length of the trend bar will increase with increased dive or climb rates and approach zero or disappear entirely as the vertical speed reaches zero in level flight 3 3 1 3 AIRSPEED OPERATION airspeed scale tape BARO 30 02 range markings airspeed window airspeed units FIGURE 3 8 AIRSPEED OPERATION The airspeed indicator porti
16. 3 3 2 6 ALT TREND 3 3 2 7 INFO gt 3 3 2 7 1 REVIEW CFG 3 3 2 7 2 BATTERY INFO 3 3 2 8 EXIT MENU 3 3 2 9 POWER OFF BRIGHTNESS ADJUSTMENT EMERGENCY OPERATION seeissiwesscteeceverteteeniiavinen IN FLIGHT ON THE GROUND Mid Continent Instruments and Avionics 4 Manual Number 9017782 Revision H January 7 2015 SECTION 4 CONFIGURATION SETUP 4 1 CONFIGURATION MODE MENU cccccceeeeeeeeeeeeceeeaneseeeseenanenas 4 1 1 CONFIGURE PREVIEW 4 2 ONFIGURE AIRGRAET Li cucssc asztas cuu E eseg sek EDI nes SH ee ns 4 2 1 PANEL TILT 4 2 2 PANEL ROLL 4 2 3 RANGE MMO 42 4 RANGE MARKINGS 42 5 VNE TABLE 4 3 CONFIGURE ARINC riii aono tex EE vat cde eiae iiri a m te 4 4 CONFIGURE DIMMING rernm nmn mnn nnn nnn nnn nnn 4 4 1 DIMMING CONTROL 4 4 2 DIMMING CURVE 4 5 CONFIGURE DISPLAY 2 2 narius oru EVE Pops Eu es I Eri Pest pes Toesotr te redes ss 4 5 1 ROLL DISPLAY 4 5 2 AIRSPEED UNITS 4 5 3 AIRSPEED MINIMUM 4 5 4 DISPLAY ORIENTATION 4 55 HORIZON DISPLAY 4 6 CALIBRATE PRESSURES nae isosuta tata dpor ed ebi can Cxteu EA 4 7 CONFIGURATION MODE ACTIONS cccscceeeeeeeeeceeeceeneeeneenanenas 4 7 1 CONFIGURE HEADING 4 7 2 UPDATE SOFTWARE 4 7 3 BATTERY STORAGE MODE 4 7 4 ACCEPT CHANGES 4 7 5 CANCEL CHANGES SECTION 5 CONFORMANCE 5 1 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 5 1 1 PRESSURE SYSTEM AND ALTIMETER VERIFICATION 5 1 2 SOFTWARE UPDATES 5 1 3 BATTERY REPLACEMENT 5 1 4 TROUBLESHOOTING 5 2 ENVIRONMENTAL Q
17. BE USED SEEK SERVICE IF WARNING CONTINUES WARNING FAILED TO SET CONFIG SETTINGS TO DEFAULT SEEK SERVICE IF ERROR CONTINUES SETTINGS DISPARITY YES USE EXTERNAL NO USE INTERNAL CONFLICTING MODULE IS OVERWRITTEN YES Mid Continent Instruments and Avionics FIGURE 5 12 External settings configuration module were found to be invalid The internal settings will be copied to the configuration module memory Service unit if this error persists FIGURE 5 13 Internal unit and external configuration module settings were found to be different This is typically the result of replacing a unit in an existing installation The external settings will be copied to replace the settings in internal memory FIGURE 5 14 In configuration mode this may be the result of lost settings both internally and externally Try to configure the unit Seek service if error persists FIGURE 5 15 In configuration mode this may be the result of lost settings and a failure to initialize memory Try to restart and configure the unit Seek service if error persists FIGURE 5 16 Internal unit and external configuration module settings were found to be different This is typically the result of replacing a unit in an existing installation In configuration mode this choice allows selection of which settings to use 56 Manual Number 9017782 Revision H January 7 2015 5 2 ENVIRONMENTAL QUALIFICATION STATEMENT
18. CONTROL FIGURE 3 18 REVIEW CONFIGURATION Mid Continent Instruments and Avionics 33 Manual Number 9017782 Revision H January 7 2015 3 3 2 7 2 BATTERY INFO The BATTERY INFO selection allows the user to view real time status of the internal battery The information available includes the Estimated Run Time in minutes the Temperature in Celsius the current battery State of Charge percentage and the Battery Capacity in milliamp hours Push the control knob to return to the INFO sub menu Figure 3 19 BATTERY INFO EST RUN TIME MINS TEMPERATURE C CHARGE CAPACITY MAH FIGURE 3 19 BATTERY INFO 3 3 2 8 EXIT MENU The EXIT MENU action allows the user to manually exit the Options Menu and return to the active attitude display There are no selectable options After confirming any setting by selecting it that setting will become immediately active and be saved in memory This will occur regardless of whether the EXIT MENU command is selected or should it time out after ten 10 seconds of inactivity and automatically revert to the attitude display Figure 3 20 OPTIONS MENU ALT UNITS BARO UNITS SYMBOL ATT MASK ALT TREND INFO gt FIGURE 3 20 EXIT MENU Mid Continent Instruments and Avionics 34 Manual Number 9017782 Revision H January 7 2015 3 3 2 9 POWER OFF The POWER OFF action allows the user to immediately turn the unit off when it is operating on its internal battery and there is no
19. Continent Instruments and Avionics 30 Manual Number 9017782 Revision H January 7 2015 3 3 2 3 BARO UNITS The BARO UNITS setting allows the user to select the altimeter or altitude barometric adjustment units to either inHg inches of mercury or MBAR HPA millibars hectopascals This feature is provided during flight in the event that the aircraft crosses airspace boundaries that require or report different barometric units Figure 3 13 OPTIONS MENU BARO UNITS MBAR FIGURE 3 13 BARO UNITS 3 3 2 4 SYMBOL The SYMBOL setting allows the user to select the type of symbolic airplane on the attitude display to either DELTA or TRADITIONAL This feature is provided for pilot preference and or to match other instruments in panel Figure 3 14 OPTIONS MENU SYMBOL TRADITIONAL DELTA WING SYMBOL TRADITIONAL SYMBOL FIGURE 3 14 AIRCRAFT SYMBOL OPTIONS Mid Continent Instruments and Avionics 31 Manual Number 9017782 Revision H January 7 2015 3 3 2 5 ATT MASK The ATT MASK setting allows the user to turn the attitude mask ON or OFF The attitude mask provides gradient dimming of the corners of the attitude display to give the aesthetic look of a round instrument Figure 3 15 OPTIONS MENU ATT MASK ON ATTITUDE MASK OFF ATTITUDE MASK ON FIGURE 3 15 ATTITUDE MASK 3 3 2 6 ALT TREND The ALT TREND setting allows the user to turn the altitude trend bar ON or OFF The altitude trend bar provides a graphical r
20. G CALIBRATE PRESSURES FIGURE 4 12 CONFIGURE DIMMING 4 4 4 DIMMING CONTROL The DIMMING CONTROL setting allows the installer to select the source of dimming control It can be an external source typically the aircrafts adjustable lighting bus or it can use the INTERNAL photocell built into the unit which senses the ambient light conditions and adjusts the display brightness dimming automatically If an external source is to be used the EXT 5V EXT 14V and EXT 28V options represent the input voltage range the unit will accept 0 5VDC 0 14 VDC and 0 28VDC respectively This feature is provided for maximum installation flexibility and control for the pilot Figure 4 13 Mid Continent Instruments and Avionics 43 Manual Number 9017782 Revision H January 7 2015 gt DIMMING CONTROL INTERNAL EXT SV EXT l4V EXT 28V FIGURE 4 13 DIMMING CONTROL 4 4 2 DIMMING CURVE The DIMMING CURVE feature allows the installer to customize the response to the DIMMING CONTROL input whether internal or external over its range of operation Therefore for various points throughout the input range the brightness can be adjusted up or down to produce a unique dimming scheme that most closely matches the other instruments in the panel and the pilot s preferences This feature is provided for maximum installation flexibility and control for the pilot NOTE When new the display is daylight visible at approximately 75 brightness It may n
21. HEADING CONFIGURE ARINC CALIBRATE PRESSURES CONFIGURE DIMMING UPDATE SOFT WARE CONFIGURE DISPLAY BATTERY STORAGE MODE CONFIGURE HEADING ACCEPT CHANGES CALIBRATE PRESSURES CANCEL CHANGES FIGURE 4 1 CONFIGURE MENU The CONFIGURE MENU root menu includes the following e CONFIGURE AIRCRAFT e CALIBRATE PRESSURES e CONFIGURE ARINC e UPDATE SOFTWARE e CONFIGURE DIMMING e BATTERY STORAGE MODE e CONFIGURE DISPLAY e ACCEPT CHANGES e CONFIGURE HEADING e CANCEL CHANGES The sub menu title at the top of the screen displays an indication gt if there is a parent menu associated with it see Section 3 3 2 1 for more details regarding menu operation Mid Continent Instruments and Avionics 37 Manual Number 9017782 Revision H January 7 2015 NOTE In Configuration Mode unlike in the Options Menu any changes made to any settings will not be saved until you select ACCEPT CHANGES prior to exiting the Configuration Mode 4 1 1 CONFIGURE PREVIEW Where applicable in Configuration Mode a preview screen is available to assist in visualizing the various selectable settings gt ROLL DISPLAY FIXED POINTER FIXED SCALE FIGURE 4 2 CONFIGURE PREVIEW 4 2 CONFIGURE AIRCRAFT The CONFIGURE AIRCRAFT menu option is selected the sub menu and its various options are displayed Note the sub menu title at the top of the screen and indication gt that there is a parent menu associated with it The CONFIGURE AIRCRAFT will return the us
22. Manual Number 9017782 Revision H January 7 2015 WARNING EXTERNAL SETTINGS MODULE MISSING SEEK SERVICE IF WARNING CONTINUES DETECTED STARTUP FAILURE SERVICE THIS UNIT IMMEDIATELY UNCALIBRATED UNIT CALIBRATION DATA NOTFOUND SEEK SERVICE IMMEDIATELY SETTINGS MISSING ORINVALID SERVICE THIS UNIT IMMEDIATELY INTERNAL SETTINGS INVALID EXTERNAL SETTINGS USED SEEK SERVICE IF ERROR CONTINUES Mid Continent Instruments and Avionics FIGURE 5 7 The configuration module has failed or is not installed properly Internal settings will be used If the configuration module is installed it should be serviced immediately FIGURE 5 8 Internal failure Service unit immediately FIGURE 5 9 Internal failure Service unit immediately FIGURE 5 10 Internal unit and external settings configuration module failure It is unlikely that both settings would be lost Try to reconfigure the unit Service unit if this error persists FIGURE 5 11 Internal unit settings were found to be invalid The configuration module settings will be copied to internal memory Service unit if this error persists 55 Manual Number 9017782 Revision H January 7 2015 EXTERNAL SETTINGS INVALID INTERNAL SETTINGS USED SEEK SERVICE IF ERROR CONTINUES SETTINGS DISPARITY THE EXTERNAL MODULE TAKES PRECEDENCE AND WILL OVERWRITE THE INTERNAL MODULE WARNING SETTINGS COULD NOT BE FOUND DEFAULT VALUES WILL
23. ON MODE In Configuration Mode an authorized installer can change and set the appropriate configuration values that are specific to the aircraft These also include user preferences and certain maintenance functions that are not available during flight Figure 1 4 current menu CONFIGURE VIENU current selection CONFIGURE ARINC CONFIGURE DIMMING CONFIGURE DISPLAY CONFIGURE HEADING unavailable more options available FIGURE 1 4 CONFIGURATION MODE Mid Continent Instruments and Avionics 9 Manual Number 9017782 Revision H January 7 2015 1 3 TECHNICAL SPECIFICATIONS 1 3 1 ELECTRICAL ATTRIBUTES input Voltage input Power nominal maximum Lighting Input 9 14 or 28VDC or automatic photocell control Input Data ARINC 429 see Table 1 5 Output Data ARINC 429 see Table 1 5 discrete valid signal to ground invalid signal is open pin 2 TABLE 1 1 1 3 2 PHYSICAL ATTRIBUTES Weight 1 6 pounds 0 73 kg Dimensions Bezel 2 37 x 5 50 x 0 33 HxWxD without connectors mates amp knob Chassis 2 31 x 3 16 x 4 84 HxWxD Mating Connectors 15 pin D Sub with Configuration Module MCIA p n 9017275 Pneumatic fittings MCIA p n 9017642 Mounting Panel mount from front uses 4 446 32 cap screws and MCIA p n 9017490 2 Nutplate included TABLE 1 2 1 3 3 PERFORMANCE LIMITS Attitude Pitch Angle Pitch Rate Roll Angle Roll Rate Altitude Range Barometer Airspeed
24. Range TABLE 1 3 1 3 4 QUALIFICATIONS Specifications Certifications FAA TSO C2d Type B C3e C4c C10b C106 C113a C179a EASA ETSO C2d C3d C4c C10b C106 C113 C179a Environmental Qualification RTCA DO 160G details listed in Section 5 2 Software Qualification RTCA DO 178B Design Assurance Level A Complex Hardware Qualification RTCA DO 254 Design Assurance Level A TABLE 1 4 Mid Continent Instruments and Avionics 10 Manual Number 9017782 Revision H January 7 2015 1 3 5 ARINC DATA LABELS All labels are defined as Equipment ID 038 in BNR format High and Low speed options for ARINC outputs are configurable See Section 3 4 ARINC 429 Input Description High 014 203 204 magnetic heading altitude rel 29 92 baro altitude magnetic heading ARINC 429 Output Description Low X X Description 203 attitude re1 29 92 x x 204 205 baro altitude i mach number X X 206 computedairspeed x x altitude rate 215 impatpressue x x static pressure 217 324 325 326 327 i X X static pressure pitch attitude roll angle body pitch rate body roll rate body yaw rate body longitudinal acceleration box jo o body lateral acceleration Pose TG body normal acceleration ox jo 4 336 337 340 X lt X inertial pitch rate inertial roll rate inertial yaw rate X custom label for software versi
25. UALIFICATION STATEMENT rH Mid Continent Instruments and Avionics 5 Manual Number 9017782 Revision H January 7 2015 SECTION 1 GENERAL DESCRIPTION 1 1 INTRODUCTION The model MD302 series SAM Standby Attitude Module is a self contained situational awareness instrument that provides aircraft attitude altitude airspeed and slip indication The compact and innovative design of the MD302 is specifically developed for maximum flexibility for installation in retrofit or modern instrument panels Its size extra wide viewing angle and AnyWay selectable orientation allows it to be installed almost anywhere in the instrument panel and in less space than traditional 2 inch mechanical standby or primary flight instruments Regardless of the aircraft you are flying the MD302 is a great fit With a 10 to 32 volt DC input range the unit will work with 14 or 28V aircraft electrical buses and the selectable lighting input allows operation with 5 14 or 28V lighting systems The operation and certification of the MD302 make it well suited for Part 23 and 25 fixed wing applications as well as Part 27 and 29 rotorcraft The MD302 provides critical flight and situational data to the pilot and crew under any circumstances you are likely to encounter The design is built around a solid state electronic sensor array for high reliability and contains an integral and rechargeable Nanophosphate lithium ion battery that can power the unit for up to tw
26. UMENTS AVIONICS S AM MD302 software version SAN VERSION MEINEM total operating time RUN TIME HRS 1764 FIGURE 3 1 PRE FLIGHT MODE Mid Continent Instruments and Avionics 22 Manual Number 9017782 Revision H January 7 2015 oJ Midcontinent a9 Midcontinent NSTRUMENTS AVIONICS NSTRUMENTS AVIONICS SAM p302 SAWN mn302 S W VERSION TE S W VERSION 1 0 1 RUN TIME HRS RUN TIME HRS 1764 FIGURE 3 1 continued PRE FLIGHT MODE 3 3 FLIGHT MODE In Flight Mode the unit operates normally by displaying the four functions of attitude altitude airspeed and slip information The Options Menu and brightness adjustment are also accessible in Flight Mode Figure 3 2 FIGURE 3 2 FLIGHT MODE Mid Continent Instruments and Avionics 23 Manual Number 9017782 Revision H January 7 2015 3 3 1 FUNCTIONS While in Flight Mode the MD302 provides four functions attitude altitude airsoeed and slip indication 3 3 1 1 ATTITUDE OPERATION roll bank scale pitch scale symbolic airplane horizon line slip indicator heading window heading scale FIGURE 3 3 ATTITUDE OPERATION The attitude indicator portion of the display can be configured on the right or left when mounted horizontally and is always on the top display when oriented vertically Figure 3 3 The background of the display consists of the representative white horizon line separating the sky blue and ground brown The
27. URE 4 21 HORIZON DISPLAY 4 6 CALIBRATE PRESSURES The CALIBRATE PRESSURES feature allows field calibration of the MD302 pressure instruments to offset any error such that the displayed values are within required tolerances for a given installation Figure 4 22 CONFIGURE MENU CONFIGURE DISPLAY CONFIGURE HEADING CALIBRATE PRESSURES gt CALIBRATE PRESSURES CALIBRATE ALTITUDE CALIBRATE AIRSPEED EXIT UPDATE SOFT WARE BATTERY STORAGE MODE ACCEPT CHANGES FIGURE 4 22 CALIBRATE PRESSURES Mid Continent Instruments and Avionics 48 Manual Number 9017782 Revision H January 7 2015 An external pitot static tester must be connected to the MD302 with the pressures stabilized to 5 000 ft and 120 knots Figure 4 23 CALIBRATING ALTITUDE APPLY STATIC PRESSURE OF 5000 FEET CALIBRATING AIRSPEED APPLY PITOT PRESSURE OF 120 KNOTS FIGURE 4 23 CALIBRATION REQUIREMENTS IMPORTANT AFTER CALIBRATING PRESSURE THE AIRSPEED AND ALTITUDE FUNCTIONS MUST BE TESTED FOR THE REQUIRED TOLERANCES ACROSS THE OPERATING RANGE OF THE AIRCRAFT 4 7 CONFIGURATION MODE ACTIONS Configuration Mode Actions contain options that do not represent further sub menus but have single settings or initiate actions which exit the Configuration Mode There are multiple selections available below the initial list on the Configuration Menu These can be accessed by scrolling down using the control knob 4 7 1 CONFIGURE HEADING This selects wheth
28. airspeed detected 30 kts This item is typically grayed out and unavailable in flight mode This feature is provided to manually turn the unit off when on the ground or if inadvertently left on internal battery power See Section 3 4 for more information on Emergency Operation when operating on battery power Figure 3 21 OPTIONS MENU ALT UNITS BARO UNITS SYMBOL ATT MASK ALT TREND INFO gt EXIT MENU POWER OFF FIGURE 3 21 POWER OFF 3 3 3 BRIGHTNESS ADJUSTMENT The MD302 SAM can be configured to adjust its brightness manually using the aircraft s lighting bus control or automatically based on the ambient lighting conditions sensed by the photocell on the unit For either option selected in the Configuration Mode see Section 4 the pilot or crew member can override the current brightness and manually increase or decrease the brightness To do so simply press the knob and the brightness bar will appear Figure 3 22 at this time the brightness can be increased or decreased by turning the knob Brightness cannot be reduced below minimum level set in Configuration Mode To manually adjust the brightness briefly press the control knob The brightness bar will appear overlaid on the attitude display and turning the control knob will increase or decrease the current setting The brightness cannot be turned down below the installation configured minimum While the unit remains powered the manual adjustment will remain saved
29. al excursions as listed for Sections 4 5 1 4 5 2 4 6 2 and 4 6 3 Mid Continent Instruments and Avionics 57 Manual Number 9017782 Revision H January 7 2015
30. and any change in the lighting bus or photocell sensor will increase or decrease the brightness from the newly set manual adjustment point When the unit is powered off the manual adjustment will be reset and default to the lighting response curve programmed into memory per the settings in the Configuration Mode setup FIGURE 3 22 BRIGHTNESS ADJUSTMENT Mid Continent Instruments and Avionics 35 Manual Number 9017782 Revision H January 7 2015 3 4 EMERGENCY OPERATION 3 4 1 IN FLIGHT The MD302 SAM is designed to operate reliably and provide the critical situational awareness needed even if the aircraft power systems fail Should this occur the unit provides emergency operation by continuing to perform seamlessly and uninterrupted in Flight Mode The MD302 contains an internal and field replaceable Nanophosphate lithium ion battery which recharges during normal flight contains a heater for low temperature conditions and provides a minimum of one 1 hour of operation up to 2 5 hours when new If aircraft power to the unit is lost in flight the unit will immediately begin operating on internal battery power This is indicated by a green battery icon displayed in the top right of the attitude display Figure 3 23 battery icon FIGURE 3 23 EMERGENCY OPERATION When the battery capacity approaches zero during extended use the battery icon will change to a black battery icon with a red X on it This indicates that the
31. cated airspeed Vne of the aircraft as a function of altitude The maximum allowable airspeed is indicated by a barber pole displayed on the range markings to the left of the airspeed tape If the BAR option is configured in the RANGE MARKINGS settings or the MMO setting is configured the lowest calculated airspeed between the three settings including Vne will be displayed for any particular current altitude Data points are entered as altitude airspeed pairs which define the graph for the calculated VNE The first data point is always at 00000 feet Any altitudes below zero feet will display the airspeed associated with zero feet The second and subsequent points define lines on the curve Values between points are interpolated linearly The last line segment defined is interpolated indefinitely The altitude units are always in feet The airspeed units match the current configuration as defined by the AIRSPEED UNITS setting see Section 4 5 2 and is displayed at the top of the column VNETABLE BARO 7 200 29 92 ALTCFT KTS 250 250 I7 100 2 18000 250 ZU 3 18000 230 anes 5 UNUSED 000 FEET 29 m 6 230 Ts l6 900 7 in 220 z l6 800 FIGURE 4 8 VNE CASE 1 IOE gt VNETABLE gt VNETABLE O o O AES E ALTCFT KTS 250 12000 250 I7 100 F 250 su 2 40 Toco 7230 qs 6 900 17000 230 UNUSED 000 SIO Gn W b 220
32. d 500 units from top to bottom The tape will roll or scroll to for quick reference as to the increasing or decreasing nature of the aircraft s altitude The barometer window shows the currently set barometric pressure located at the top center of the airspeed altitude display and is identified by the abbreviation BARO Setting the current barometric pressure compensates the altitude for the appropriate environmental conditions The barometric setting can be synchronized externally to an ARINC 429 source that supplies data labels 203 and 204 typically the aircraft s primary flight display PFD When the barometric setting on the PFD is changed the MD302 will change to match When the two are synchronized the barometric window will display two arrows located on either side of the word BARO Figure 3 6 Manually changing the MD302 barometric setting will override the external source The barometric setting can be manually adjusted by simply turning the control knob while in Flight Mode When the barometric pressure is adjusted externally or manually the window and digits will turn green Figure 3 7 When finished setting the pressure the window and digits will return to their original color Barometric pressure units can be selected during Flight Mode using the Options Menu see Section 3 3 2 Barometer value synced FIGURE 3 6 ALTITUDE OPERATION BARO SYNCHRONIZATION 4 FEET o o o m T O Barometer
33. d tape To program range markings see Figure 4 7 for examples 1 Use the control knob to select the type of the color bar HALF FULL or RAD radial 2 Use the control knob to select the desired color blue green red white yellow or BAR barber pole 3 Press the control knob to accept the selection and move to the range values 4 Turn the control knob to select each digit and press to move to the next digit a The first three digits are the start or lower limit of the color bar range and the second three digits are the upper limit b If RAD radial is selected the V1 and V2 will default to the same value c Selecting MAX in the V2 column by entering 999 will extend the bar to the top of the scale d Choosing a FULL BAR barber pole type will automatically default V2 to MAX e The values automatically represent the units knots mph kph selected in the CONFIGURE DISPLAY AIRSPEED UNITS menu 5 Continue in sequence until reaching the EXIT prompt and press the control knob to exit the menu a Leaving or selecting 000 for the lower and upper limit creates no color bar Mid Continent Instruments and Avionics 40 Manual Number 9017782 Revision H January 7 2015 FIGURE 4 7 RANGE MARKING EXAMPLES Mid Continent Instruments and Avionics 41 Manual Number 9017782 Revision H January 7 2015 4 2 5 VNE TABLE The VNE TABLE setting provides the ability to automatically adjust the maximum or never exceed indi
34. e Pre Flight Screen during unit startup RETURN TO SERVICE 16 Remove the USB flash drive 17 Close the USB Access Cover and tighten the screw in place 18 Re install the unit into the instrument panel in reverse order as described in Step 3 above 5 1 3 BATTERY REPLACEMENT There should be no regularly scheduled maintenance of the Nanophosphate lithium ion battery The battery will recharge itself from aircraft power while in normal mode A battery capacity check occurs each time the unit is powered on If the battery capacity is determined to be more than 8096 no message is displayed and the battery is good If a unit has a battery pack warning and the warning persists more than once in a short time it can be replaced in the field with minimal effort By removing two small screws on the rear of the unit the battery cover comes off and the battery is accessible Pull the battery out using the handle strain relief built onto the battery Replace with a new battery verify operation and go 5 1 4 TROUBLESHOOTING The following Figures and associated descriptions represent warnings or errors and describe the typical reasons and appropriate response action FIGURE 5 1 The attitude display has failed due to exceedance of internal rate sensors loss of airspeed or other various reasons This will typically self correct However if it does not immediately have the unit serviced Mid Continent Instruments and Avionics 53 Manua
35. eld termination FIGURE 2 4 CONFIGURATION MODULE ASSEMBLY Mid Continent Instruments and Avionics 18 Manual Number 9017782 Revision H January 7 2015 2 7 PITOT STATIC CONNECTIONS The connector kit supplied with the unit contains two 2 pneumatic quick disconnect fittings These fittings are specific to the connections on the rear of the unit and required for proper operation Aircraft tubing that connects to the unit must be 74 OD with an approximate 0 17 ID When determining tubing length be sure that it can extend through the cutout in the panel by approximately 8 to allow the unit to be installed and removed from the front of the panel NOTE It is helpful to identify label each tube pitot or static so that it can be connected to the correct port on the back of the unit during installation WARNING Lock quick disconnect before connecting to the unit to avoid damaging the O ring 2 8 MOUNTING The MD302 is designed primarily to be front mounted in an aircraft instrument panel Refer to Section 2 3 for Equipment Location information To install the unit in the instrument panel follow the instructions below and refer to Figures 2 4 2 5 and 2 6 1 Once a location is selected cut the panel per the dimensions in Figure 2 6 Other notes to consider for panel cutout the Nutplate can be used as a basic template for the panel cutout e For vertical installation rotate the panel cutout profile 90 e Be sure to leave space clear
36. ements This accommodates any noticeable difference between the symbolic airplane and the horizon line when flying straight and level Use the control knob to change the value of each panel roll digit and press the control knob to acknowledge each selection and advance to the next one Figure 4 5 gt PANEL ROLL lo O DEGREES FIGURE 4 5 PANEL ROLL 4 2 3 RANGE MMO The RANGE MMO setting allows the installer to input the maximum operating Mach number specific to the aircraft This is represented by a moving barber pole red and white striped color bar to the left of the airspeed tape that adjusts with varying airspeed and altitude NOTE THIS ONLY APPLIES TO AIRCRAFT WHICH PUBLISH A MAXIMUM OPERATING MACH NUMBER The value should be Zero for those aircraft which do not publish a maximum operating Mach number Myo Use the control knob to change the value of each digit and press the control knob to acknowledge each selection and advance to the next one Figure 4 6 Mid Continent Instruments and Avionics 39 Manual Number 9017782 Revision H January 7 2015 FIGURE 4 6 MMO ENTRY PAGE AND SAMPLE SCREEN 4 2 4 RANGE MARKINGS The RANGE MARKINGS setting allows the installer to input airspeed limits or V speeds specific to the aircraft Aircraft airspeed limits can typically be found in the Pilot s Operating Handbook POH The range markings for airspeed limits appear as a series of colored bars to the left of the airspee
37. enu is indicated with white text Unavailable items information only unavailable options are indicated with gray text indicates an item has another menu page associated with it indicates more options available above or below the current list Menu operation throughout the MD302 is simple and intuitive Turning the control knob will scroll the green cursor highlight over the available options within the current menu By default the currently set value of each menu option is displayed in gray directly to the right of each setting Pressing the control knob for any highlighted item will activate the selection and make its options available to the right Scroll to the desired option and press the control knob to select it The green highlight will return to the menu options on the left and the new value will be displayed in gray to the right After confirming any setting by selecting it that setting will become immediately active and be saved in memory regardless of whether the EXIT MENU command is selected or it times out and automatically reverts to the attitude display 3 3 2 2 ALT UNITS The ALT UNITS setting allows the user to select the altitude units to either FEET or METERS This feature is provided during flight in the event that the aircraft crosses territorial airspace boundaries that require or report different altitude units Figure 3 12 OPTIONS MENU ALT UNITS FEET METERS FIGURE 3 12 ALTITUDE UNITS Mid
38. epresentation of vertical speed near the altitude tape see Section 3 3 1 2 This feature is provided for pilot preference and convenience Figure 3 16 OPTIONS MENU ALT TREND ON FIGURE 3 16 ALTITUDE TREND BAR Mid Continent Instruments and Avionics 32 Manual Number 9017782 Revision H January 7 2015 3 3 2 7 INFO gt While in Flight Mode the INFO sub menu is available to the pilot or cockpit crewmembers It offers read only information available during flight and does not affect the aircraft specific configuration of the unit Figure 3 17 For more information regarding menu operation see Section 3 3 2 1 The INFO gt sub menu contains the following options Figure 3 17 e REVIEW CFG e BATTERY INFO e EXIT INFO OPTIONS MENU ALT UNITS BARO UNITS SYMBOL gt INFO MENU REVIEW CFG BATTERY INFO EXIT INFO ATT MASK ALT TREND EXIT MENU FIGURE 3 17 INFO SUB MENU 3 3 2 7 1 REVIEW CFG The REVIEW CFG selection allows the user to view all the values saved in unit memory which have been set in Configuration Mode during installation or maintenance There are no selectable options and this feature provides a read only verification of information When selected the REVIEW CFG screen will appear and allows the user to scroll through all the configuration values Push the control knob to return to the INFO sub menu Figure 3 18 REVIEW CFG AIRSPEED MINIMUM AIRSPEED UNITS CONFIGURE ARINC DIMMING
39. er back to the CONFIGURE MENU Figure 4 3 Within the CONFIGURE AIRCRAFT sub menu are the following options e PANEL TILT e PANEL ROLL e RANGE MMO e RANGE MARKINGS e VNE TABLE e EXIT CONFIGURE ARINC PANEL ROLL CONFIGURE DIMMING RANGE MMO CONFIGURE DISPLAY RANGE MARKINGS CONFIGURE HEADING VNE TABLE CALIBRATE PRESSURES EXIT FIGURE 4 3 CONFIGURE AIRCRAFT Mid Continent Instruments and Avionics 38 Manual Number 9017782 Revision H January 7 2015 4 2 1 PANEL TILT The PANEL TILT setting allows the installer to input the angle of the instrument panel from 90 to 90 see Figure 2 1 so that the attitude indicator will show zero pitch when in level flight Use the control knob to change the value of each panel tilt digit and press the control knob to acknowledge each selection and advance to the next one Figure 4 4 NOTE To measure and input the panel tilt angle accurately for proper operation the panel tilt should be measured using a digital level or equivalent within 0 5 when in level flight or as simulated on the ground See the unit specifications for the total range of acceptable panel tilt angles gt PANEL TILT lo o O DEGREES FIGURE 4 4 PANEL TILT 4 2 2 PANEL ROLL The PANEL ROLL setting allows the installer to correct for any minor deviations in the actual physical installation if it was not installed precisely straight and level This feature provides adjustments from 5 to 5 in half degree incr
40. er the heading is displayed or not If configured to display heading the MD302 needs to have ARINC input data provided with labels 014 or 320 see Table 1 5 Figure 4 24 CONFIGURE MENU gt CONFIGURE HEADING DISPLAY ON DISPLAY OFF CONFIGURE DIMMING CONFIGURE DISPLAY CONFIGURE HEADING CALIBRATE PRESSURES UPDATE SOFT WARE BATTERY STORAGE MODE FIGURE 4 24 HEADING DISPLAY 4 7 2 UPDATE SOFTWARE The UPDATE SOFTWARE action initiates the unit to look for a software update that is present in a USB flash drive that has been plugged into the rear of the unit This action is unavailable in Emergency Mode on battery power If a USB device is not detected or a valid software update file is not found a failure message will appear and return back to the Configuration Menu If the unit finds a valid software update file a software update progress screen will appear The status screen will indicate when the software update completes successfully Acknowledging this completion will automatically reset the unit and return to the Pre flight Mode followed by entering Flight Mode See Section 5 1 2 for more information Mid Continent Instruments and Avionics 49 Manual Number 9017782 Revision H January 7 2015 CONFIGURE MENU CONFIGURE HEADING CALIBRATE PRESSURES UPDATE SOFTWARE BATTERY STORAGE MODE ACCEPT CHANGES CANCEL CHANGES FIGURE 4 25 UPDATE SOFTWARE 4 7 3 BATTERY STORAGE MODE This feature extends the battery
41. espectively When satisfied press the control knob The next point will be highlighted Repeat Steps 1 4 for each point on the sloped line of the graph The next highlighted point will be on the vertical zero line As the lighting bus is turned down or off there may be a point where it should default to a set level typically for daylight visibility Adjust this dot horizontally with the control knob to set the low input level of the lighting bus where the default brightness takes effect You can verify where this occurs by adjusting the lighting bus input Press the control knob to accept the position chosen If this point is not set the display will follow the dimming curve previously programmed and will be respond to the position of the first point when the lighting bus is turned off 7 The next highlighted point will set the default low input brightness With the lighting bus input to the left of the previous set point adjust the brightness up or down to the desired level Press the control knob to accept the position chosen ol Kuss MIN AMBIENT MAX VOLTS 28 FIGURE 4 14 FIGURE 4 15 INTERNAL DIMMING CURVE EXTERNAL INPUT DIMMING CURVE 4 5 CONFIGURE DISPLAY When the CONFIGURE DISPLAY menu option is selected the sub menu and its various options are displayed Note the sub menu title at the top of the screen and indication gt that there is a parent menu associated with it Selecting the EXIT CONFIG DISPLAY will return t
42. evision H January 7 2015 FIGURE 3 4 ATTITUDE OPERATION EXTREME PITCH 3 3 1 1 1 HEADING OPERATION The configurable heading indicator is comprised of a window showing the current heading and a moving tape along the bottom of the display Figure 3 9 Heading operation can be enabled in configuration mode See Section 4 Configuration Setup The Heading Scale is depicted as a series of graduations representing ten degrees 10 with every thirty degrees 30 numbered A letter representing direction N S E W is provided every ninety degrees 90 The Heading Window displays the Heading Data taken directly from ARINC input The ARINC data is displayed without reprocessing if ARINC input data is lost the display will read Figure 3 10 roll bank scale pitch scale symbolic airplane horizon line ant il heading window heading scale 30 33 345 N FIGURE 3 9 HEADING OPERATION slip indicator LI Mid Continent Instruments and Avionics 25 Manual Number 9017782 Revision H January 7 2015 FIGURE 3 10 ARINC DATA LOSS 3 3 1 2 ALTITUDE OPERATION r7 altitude tape scale barometer value altitude window altitude trend bar altitude units FIGURE 3 5 ALTITUDE OPERATION The altimeter portion of the display will always appear on the right side of airspeed altitude display Figure 3 5 The altimeter consists of four parts the altitude window the altitude tape the barometer window and t
43. fe and certified operation of the unit and the aircraft Several safeguards are in place to prevent a user from ever accessing the Configuration Mode while in flight Only authorized installers and trained personnel should access the Configuration Mode during initial installation or during maintenance adjustments and updates This section discusses the Configuration Mode and Menu completely and is organized into the following categories e Configuration Mode and Menu general usage and purpose Configure Aircraft Configure ARINC Configure Dimming Configure Display Calibrate Pressures 4 1 CONFIGURATION MODE MENU In Configuration Mode all of the parameters specific to the aircraft and particular installation are set and saved into memory These configuration settings are also saved to the external Configuration Module that is part of the aircraft s cable harness This allows for the unit to be removed and or replaced for service or other aircraft maintenance and still retain the configuration settings associated with the aircraft To enter the Configuration Mode press and hold the control knob prior to applying power to the unit After approximately six 6 seconds the following message will appear CONTINUE HOLDING TO ENTER CONFIG MODE After a few more seconds the introduction screen will appear and the knob can be released You will now see the CONFIGURE MENU Figure 4 1 CONFIGURE MENU CONFIGURE MENU CONFIGURE AIRCRAFT CONFIGURE
44. h Configuration Module and pitot static fittings to the rear of the unit 6 Insert the unit through the panel cutout and secure with four 4 hex head cap screws provided e Electrical bonding between the aircraft and the unit chassis is NOT required 2 9 INSTALLATION COMPLETION Prior to operating the unit in the aircraft verify the basic operation of the unit and conduct a standard leak check of the pitot static system per the aircraft maintenance manual or industry practice When initially powering the unit an error may occur if a pre configured unit is being mated to a Configuration Module for the first time or if the unit has yet to be configured Acknowledge this error and either proceed to configuring the installation settings or cycle the power The error should not occur for subsequent startups Mid Continent Instruments and Avionics 19 Manual Number 9017782 Revision H January 7 2015 J Midcontinent INSTRUMENTS AVIONICS A ES 5 50 x 5 22 i A pis i p s 4 L4 2 37 2 09 2 4 diagonal active area ly E i i T AX Q0 150 thru static port 15 pin D sub pitot port USB access 6420302 1 33
45. he optional altitude trend bar The altitude window displays the current barometric corrected altitude The indicated digits of the display are every twenty 20 units and the window is expanded over this portion of the number to display a minimum of forty 40 units The units will roll or scroll to assist in quick reference as to the increasing or decreasing nature of the aircraft s altitude The hundreds thousands and ten thousands digits appear to the left of the tens digits with the thousands and ten thousand digits slightly larger than the others The altitude pointer triangle to the right of the window points to the associated position on the altitude tape of the current altitude Altitude units appear below the altitude window and can be changed during Flight Mode using the Options Menu see Section 3 3 2 The altitude tape is a vertical scale along the right margin of the display The current altitude is always in the middle of the tape and indicated by the triangular pointer on the Mid Continent Instruments and Avionics 26 Manual Number 9017782 Revision H January 7 2015 right side of the altitude window The tape has numeric indications every one hundred 100 units with minor graduations every fifty 50 units and sub graduations every twenty five 25 units In horizontal installations the tape spans approximately four hundred 400 units from top to bottom and in vertical installations the tape spans approximately five hundre
46. he user back to the CONFIGURE MENU Figure 4 16 Within the CONFIGURE DISPLAY sub menu are the following options e ROLL DISPLAY AIRSPEED UNITS AIRSPEED MINIMUM DISPLAY ORIENTATION HORIZON DISPLAY EXIT Mid Continent Instruments and Avionics 45 Manual Number 9017782 Revision H January 7 2015 CONFIGURE MENU gt CONFIGURE DISPLAY CONFIGURE ARINC ROLL DISPLAY CONFIGURE DIMMING AIRSPEED UNITS CONFIGURE DISPLAY AIRSPEED MINIMUM CONFIGURE HEADING DISPLAY ORIENTATION CALIBRATE PRESSURES HORIZON DISPLAY UPDATE SOFT WARE EXIT FIGURE 4 16 CONFIGURE DISPLAY 4 5 1 ROLL DISPLAY The ROLL DISPLAY setting allows the installer to select either the FIXED POINTER or FIXED SCALE option The FIXED POINTER option makes the lower triangle pointer always point to the top of the display to represent the aircraft s position in relation to the scale The roll scale containing the radial grads and triangles on the attitude display will rotate with the horizon The FIXED SCALE option also known as sky pointer sets the role scale stationary and allows the lower triangle pointer to rotate with the horizon This feature should be selected to match other attitude instrument representations in the panel for consistency and reduced fatigue work load on the pilot when switching field of view between instruments Figure 4 17 ROLL DISPLAY FIXED POINTER FIXED SCALE FIXED POINTER FIXED SCALE FIGURE 4 17 ROLL DISPLAY Mid Con
47. l Number 9017782 Revision H January 7 2015 200 WARNING INTERNAL BATTERY MAY PROVIDE LESS THAN 60 MINUTES OF OPERATION ACKNOWLEDGE POWERING DOWN THIS UNIT WILL SHUT OFF IN 42 SECONDS OR MANUALLY SELECT Mid Continent Instruments and Avionics FIGURE 5 2 The altimeter instrument has failed possibly due to exceedance of the pressure sensor range This may self correct but if the error persists immediately have the unit serviced FIGURE 5 3 The airspeed instrument has failed possibly due to exceedance of the pressure sensor range This may self correct but if the error persists immediately have the unit serviced FIGURE 5 4 The airspeed and altimeter display have both failed due to exceedance of their respective sensor ranges This may self correct but if the error persists service unit immediately FIGURE 5 5 Battery failed initial capacity check This may be due to recent battery usage without allowing time to recharge This may also occur during extreme temperature conditions User may acknowledge this error and continue operation but available backup power capacity may be less than required minimum levels If this warning persists the battery will need serviced FIGURE 5 6 This message is displayed when power is removed at low airspeed typical ground condition The pilot has 60 seconds to confirm to remain on otherwise the unit will automatically power off to conserve battery 54
48. ments and Avionics 2 Manual Number 9017782 Revision H January 7 2015 REVISION HISTORY ECO Rev Date Approved Detail 1 1 a 09 10 2012 Engineering release A 10 02 2012 A Initial release 5864 B 10 31 2012 BAW Updates implemented Remove Pending from certification table 1 4 Update Section 2 4 Added panel orientation graphic to Figure 2 1 Updated lightning callout to H3B3L3 Various minor corrections Add Figure 3 6 Consolidate Figures 3 10 3 11 5882 11 21 2012 and Figures 3 12 3 13 Updated logos to include registered trademarks Updated screen captures to reflect software version 1 0 1 Update DO 160 qualification to include helicopter vibration 5962 05 06 2013 Various minor corrections Incorporated changes associated with software version 1 0 3 Added label 204 to ARINC outputs Added Baro Sync m a mul tue information to Section 3 3 1 2 ouai pem gw Added Mod 1 Configuration Incorporated changes associated with software version 1 0 4 Added labels 014 and 320 to ARINC inputs Added Heading Operation to Section 3 3 1 1 1 Added Configure Preview to Section 4 1 1 Added VNE Configuration to Section 4 4 5 Added Heading Display to Section 4 5 Added Calibrate Pressures to Section 4 6 Updated screen captures 6313 12 22 2014 where applicable Updated Section 5 1 to include revised software update 6318 H 01 07 2015 BMC procedure Mid Continent Instruments and A
49. moved from the panel Software updates are typically communicated to the public via Service Bulletins issued by Mid Continent Instruments and Avionics and can be found on the product website www flySAM com Below are instructions for updating the unit software Please read through all instructions before beginning PREPARATION 1 Prepare software update file A Download the approved software file to the root directory of a standard FAT formatted USB flash drive from www flySAM com software updates The downloaded file must retain the exact file name 2 Ensure that the unit is powered off 3 Remove the unit from the instrument panel A Remove the four mounting screws attaching the bezel of the unit to the panel B Pull the unit forward until the end plate is accessible NOTE This can be done without removing the electrical connector or pneumatic connections if the proper service lengths were applied during installation 4 Loosen the screw of the USB access cover on the rear of the unit until the USB port is accessible LOAD SOFTWARE 5 Insert the USB flash drive with the approved software file into the USB port 6 Press and hold the Control Knob on the faceplate while applying external power to the unit Software updates cannot be performed using internal battery power 7 Continue holding as prompted up to 10 seconds until the Pre Flight Screen appears Once CONFIGURE MENU is displayed the unit is in Configuration Mode
50. mp should be placed over the chafe protection installed in Step 2 if used Loosely connect the two halves of the Cable Strain Relief Clamp with 2 screws Item 8 Place the Cable Strain Relief Clamp in the Backshell as shown Bend the wires of the Configuration Module PC Board Assembly 180 degrees so that the PC Board has its electrical components facing down as shown Be careful not to place excess strain on the solder connections between the wires and the PC Board Capture the Configuration Module PC Board Assembly into the Backshell by placing the Backshell Cover Item 2 on top of the Backshell Secure the Backshell Cover onto the Backshell using 2 Screws Item 9 Bundle the exposed shield braids and secure them to either threaded hole on the rear of the Backshell using a 2 56 screw Item 10 A wire that is common to aircraft chassis ground shall also be connected to one of these two holes on the Backshell Use of a ring terminal not included may be useful The completed assembly should look as shown Verify that the Slide Lock operates freely and that no wires are pinched nicked or otherwise damaged Verify that power and ground signals are installed appropriately before connecting to the unit Mid Continent Instruments and Avionics 17 Manual Number 9017782 Revision H January 7 2015 Description Backshell Size 9 Kit DSub 15pin HD er rane peses E pma peermxW Pan UBER Ls I pomo pew rssWTaRBK Ra shi
51. ned for simple intuitive operation for ease of use and quick interpretation of the information displayed The central control knob can be located at the bottom center middle left or middle right of the unit bezel depending on the installation orientation This is the only user interface on the unit The knob has two functions push and turn e The knob provides 16 detents per revolution and typically increments whatever element it is controlling on the display one unit per detent e The push function is typically used to select the highlighted option in a menu and or to enter and exit menus and control functions The push function can also perform certain operations with a push and hold action as described herein 3 2 PRE FLIGHT MODE In Pre flight Mode power is applied to the unit and the introduction screen appears during startup Figure 3 1 During Pre flight Mode the introduction screen will be displayed while the unit conducts an initial power up built in test PBIT of the system to validate operational readiness This includes among others a battery capacity measurement an internal test to verify software and memory and a check that the internal settings and identification of the unit match the Configuration Module installed in the aircraft cable harness The introduction screen will be displayed for approximately five seconds and will transition to Flight Mode when complete manufacturer s logo J M ic 0 nti nent g INSTR
52. o hours if main aircraft power is lost The dual high resolution LCD display uses smooth graphics daylight readable brightness and a configurable lighting response curve to ensure optimal visibility in all conditions The user interface of the product allows for simple intuitive operation using a single push and turn control knob that easily navigates through the user options and menu screens The interactivity of the unit means that it can receive and transmit ARINC 429 data communications Functional outputs of attitude altitude and airspeed can be used for monitoring or backup information while baro input data can be received and will synchronize the baro setting with the primary system to eliminate redundant task loading for the pilot The MD302 is an excellent complement to your avionics suite as a reliable and state of the art instrument that is an essential part of any instrument panel Mid Continent Instruments and Avionics 6 Manual Number 9017782 Revision H January 7 2015 1 2 SYSTEM OVERVIEW The MD302 has four specific modes of operation They are Pre flighnt Mode Flight Mode Emergency Mode Configuration Mode The following sections will briefly introduce each mode with further details provided within sections 3 and 4 of this manual 1 2 1 PRE FLIGHT MODE In Pre flight Mode power is applied to the unit and the introduction screen appears during startup with the manufacturer s logo model name and number software version
53. o the TSO certifications of the product In the case of FAA TSO and EASA ETSO C3e the MD302 has been approved as an incomplete TSO The MD302 meets all TSO requirements for applicable functions slip but does not meet requirements associated with functionality that is not present in the unit rate of turn A note below describes further details regarding the temperature requirements of FAA TSO C113a but does not represent a deviation FAA TSO C2d Airspeed Instruments e instrument is not labeled with Airspeed or IAS FAA TSO C3e Turn and Slip Instrument e instrument does not provide rate of turn functionality FAA TSO C4c Bank and Pitch Instruments e dielectric strength insulation resistance does not apply due to electronic components between chassis and connector pins FAA TSO C10b Altimeter Pressure Actuated Sensitive Type e instrument is not labeled with Altitude or ALT e graduation increments are every 25 feet instead of 20 feet FAA TSO C113a Airborne Multipurpose Electronic Displays e display is operable but marginally usable at 30 C Display is fully functional at temperatures higher than 30 C Heading Display Function e Does not provide independent heading data the ARINC data is displayed without reprocessing if ARINC data is lost the display will read Mid Continent Instruments and Avionics 14 Manual Number 9017782 Revision H January 7 2015 2 5 MODIFICATIONS Each model MD302 part numbe
54. of the unit The functions associated with the 15 pin D subminiature connector are identified as follows Unit Unit Connector Pin Identification Pin Identification ARINC Out B 3 IRE EI 7 LighingBusInput ARINCOutA ss Out A Reserved Reserved TABLE 2 1 UNIT CONNECTOR PIN IDENTIFICATION FIGURE 2 3 VIEW FROM REAR OF MATING CONNECTOR Mid Continent Instruments and Avionics 16 Manual Number 9017782 Revision H January 7 2015 To assemble the aircraft cable harness and Configuration Module refer to the following instructions and Figure 2 4 1 2 3 Install a pin socket as supplied in the Connector Kit using an appropriate crimping tool for each wire in the aircraft cable harness Be sure to make the harness long enough to remove the unit from the front of the panel without stressing the harness approx 8 longer than required to reach the unit connector Braids from shielded wires should be separated from the wire conductors and pulled back from the pin socket termination approximately 2 and gathered together a NOTE Additional chafe protection such as heat shrink or nylon wire braid is recommended over the bundle not including the shields to prevent wear when installed in the cable clamp Insert the pins of the cable harness into the rear of the 15 pin D Sub connector Item 4 per Table 2 1 and Figure 2 3 using an appropriate pin insertion tool CAUTION The Config
55. on oe T vertical acceleration vertical acceleration 377 speoficequipmentid x x X TABLE 1 5 Mid Continent Instruments and Avionics 11 Manual Number 9017782 Revision H January 7 2015 SECTION 2 INSTALLATION 2 1 GENERAL INFORMATION IMPORTANT READ THIS ENTIRE SECTION PRIOR TO STARTING INSTALLATION This section contains interconnect diagrams mounting dimensions and other information pertaining to the installation of the MD302 SAM Standby Attitude Module After installation of cabling and before installation of the equipment ensure that power is applied only to the pins specified in the interconnect diagram 2 2 PARTS LIST When unpacking this equipment make a visual inspection for evidence of any damage that may have incurred during shipment The following parts should be included ltem Description MCIA Part Number a MD302 SAM Standby Attitude Module 6420302 b Installation Manual 9017782 c Connector Kit 9017646 i Nutplate 9017490 2 ii Pneumatic Connector x2 9017642 iii Screw Hex 6 32x5 8 x4 90 620 5201 1 IV Screw Flat 2 56x1 4 x2 90 208 10011 V Screw 2 56x3 16 x2 90 206 0001 1 vi Configuration Module 9017275 1 15 pin D Sub 2 Backshell 3 Backshell Cover 4 Printed Circuit Board Assembly 5 Screw Flat 2 56x1 4 x2 6 Screw 4 40x3 16 x4 2 3 EQUIPMENT LOCATION The MD302 SAM Standby Attitude Module is designed primarily to be installed in the instrument panel of
56. on of the display will always appear on the left side of the airspeed altitude display Figure 3 8 The airspeed indicator display consists of three parts the airspeed window the airspeed tape and the airspeed limitations or range markings The airspeed window displays the current indicated airspeed IAS The digits of the display are enlarged for visibility and increment by one 1 unit The units will roll or scroll to assist in quick reference as to the increasing or decreasing nature of the aircraft s airspeed The airspeed pointer triangle to the left of the window points to the associated position on the airspeed tape of the current airspeed Airspeed units appear below the airspeed window and can be selected during installation in Configuration Mode see Section 4 The airspeed tape is a vertical scale along the left margin of the display The current airspeed is always in the middle of the tape and indicated by the triangular pointer on the left side of the airspeed window The airspeed tape has numeric indications every ten 10 or twenty 20 units depending on the unit type selected Minor graduations appear every five 5 or ten 10 units respectively In horizontal installations the tape spans Mid Continent Instruments and Avionics 28 Manual Number 9017782 Revision H January 7 2015 approximately fifty 50 or one hundred 100 units from top to bottom and in vertical installations the tape spans approximately eighty
57. ot be necessary to set the dimming curve to 100 Setting the high brightness side of the dimming curve to less than 100 will extend the life of the LED backlight and provide margin for the pilot to increase brightness as desired When setting the dimming curve with the dimming control set to INTERNAL the X axis of the dimming graph will read AMBIENT and will range from MIN to MAX This represents the brightness of the light the unit s photocell can see and shows the current ambient light level with the vertical blue line The Y axis represents brightness of the display It will track the dimming curve with the horizontal blue line as the input light increases or decreases The best method for setting the dimming curve is to simulate the range of lighting conditions This is best done after installation in the actual aircraft instrument panel but can be simulated in various environments Figure 4 14 1 Change the light of the cockpit or general area around the unit until the vertical blue line matches or nearly matches the yellow highlighted point on the graph 2 Adjust the control knob to increase or decrease the brightness of the display to the desired level at that lighting condition the point will move up or down respectively 3 When satisfied press the control knob 4 The next point will be highlighted 5 Repeat Steps 1 4 for each point on the graph When setting the dimming curve with the dimming control set to external inp
58. r 6420302 has a nameplate that identifies the manufacturer part number description certifications and technical specifications of the unit It also includes the MOD or modification number representing notable changes in the hardware design of the unit Software revisions are reflected in the software version displayed on the introduction screen during startup The following are descriptions of the current modification releases of the MD302 Standby Attitude Module MOD 0 Modification MOD 0 is identified on the nameplate by the lack of marking on the MOD numbers 1 through 9 i e 1 9 are visible Mod 0 is the initial release of the MD302 Standby Attitude Module MOD 1 Modification MOD 1 is identified on the nameplate by the marking blacking out of MOD number 1 i e 1 is not visible and 2 9 are visible see Figure 2 2 below for example Mod 1 of the MD302 Standby Attitude Module contains the following changes from MOD 0 Added EMI gasket materials to back plate and battery cover Improved ESD protection Increased design margin of the ARINC RX TX function Q9 Miac continent TS0 C2d Cio IHSTRUNENTSEAVIONIGS MOD 0 Ld ee pac e Pero STANDBY ATTITUDE ERU dn Ay Neo boat C6 CIR Ci70a MODEL expe 02 SEE IM FOR LIMITS wD REP 6 Z ES i MFG P N 6420302 X Wem BEBE MEE SERIAL NO XXX XXXXX Rating 10 32 VDC 35 vane MAX MOD i BASSO RC on CP CIR ca cr Weight 16 LBS Range 20 to 500 KTS BOE De EN A
59. re is less than 20 of battery capacity left and possibly as little as ten 10 minutes of backup power available Figure 3 23 3 4 2 ON THE GROUND If primary aircraft power to the unit is lost the unit will immediately begin operating on internal battery power When this occurs as a result of normal landing and shut down procedures the unit will recognize a lack of airspeed and determine that the aircraft is on the ground The unit will then display a warning message that starts a sixty 60 second countdown The unit will turn off automatically at the end of the countdown or the user can choose to manually turn the unit OFF or remain ON immediately by selecting the options on the screen using the control knob Figure 3 24 To turn the unit off after selecting the ON option enter the Options Menu and select the POWER OFF action See Section 3 3 2 9 POWERING DOWN THIS UNIT WILL SHUT OFF IN 58 SECONDS OR SELECT OPTION THEN PUSH KNOB ON OFF FIGURE 3 24 POWERING DOWN SCREEN Mid Continent Instruments and Avionics 36 Manual Number 9017782 Revision H January 7 2015 SECTION 4 CONFIGURATION SETUP IMPORTANT THE UNIT IS NOT APPROVED FOR FLIGHT UNTIL IT HAS BEEN CONFIGURED FULLY USING THE INSTRUCTIONS IN THIS SECTION This section contains information on how to configure the aircraft specific requirements available with the MD302 SAM Standby Attitude Module This includes critical flight parameters that contribute to the sa
60. roll scale is depicted as an arc of graduations representing bank angles of 0 triangle 10 20 30 45 small triangle and 60 The roll scale can be configured during installation to be fixed to the sky horizon or fixed to the top of the display See Section 3 for how to configure this option The unit is operable and usable in a continuous and unlimited roll range of 360 The roll pointer is the triangle just below the roll scale and represents the aircraft in relation to its bank angle It is configured by definition to operate conversely to the roll scale behavior That is a rotating roll scale produces a fixed roll pointer and a fixed roll scale produces a rotating roll pointer The pitch scale is depicted as a series of graduations representing pitch angles of every 5 with every 10 graduation extended and numbered The unit is operable and usable in a continuous and unlimited pitch range of 360 A series of chevrons will appear overlaid on the pitch scale when in extreme pitch attitude This is to indicate to the pilot the direction of the horizon for quick reference Figure 3 4 The symbolic airplane will always remain in the center of the display with the background elements moving behind it to represent the aircraft s relative position The symbol that represents the airplane can be selected during Flight Mode using the Options Menu see Section 3 3 2 Mid Continent Instruments and Avionics 24 Manual Number 9017782 R
61. t be installed with the control knob at the bottom of the unit The HORIZONTAL SWAP positions the attitude display on the right display In the VERTICAL RIGHT orientation the control knob is located on the right side of the unit In the VERTICAL LEFT orientation the control knob is located on the left side of the unit See Section 2 3 Equipment Location when determining where and how to orient the unit in the aircraft instrument panel This feature is provided for maximum installation flexibility but should be chosen carefully to fully comply with regulatory requirements to minimize visual scan and allow for easy access NOTE in the vertical orientation the location of the knob should be selected so that the pilot does not obstruct the display when operating the control knob Figure 4 20 and Figure 2 1 Mid Continent Instruments and Avionics 47 Manual Number 9017782 Revision H January 7 2015 gt DISPLAY ORIENTATION HORIZONTAL VERTICAL RIGHT VERTICAL LEFT HORIZONTAL SWAP FIGURE 4 20 DISPLAY ORIENTATION 4 5 5 HORIZON DISPLAY The HORIZON DISPLAY setting allows the installer to select the visual effect of the horizon background The FLAT option provides a solid blue over brown color scheme The SHADED option provides a gradated blue over brown that lightens closer to the horizon line and darkens towards the edges of the display Figure 4 21 gt HORIZON DISPLAY FLAT HORIZON BACKGROUND SHADED HORIZON BACKGROUND FIG
62. tinent Instruments and Avionics 46 Manual Number 9017782 Revision H January 7 2015 4 5 2 AIRSPEED UNITS The AIRSPEED UNITS setting allows the installer to select the airspeed units to KNOTS MPH miles per hour or KPH kilometers per hour The default setting is KNOTS This feature should be selected to match the other airspeed instrument displays in the panel for consistency and reduced fatigue work load on the pilot when switching field of view between instruments Figure 4 18 gt AIRSPEED UNITS FIGURE 4 18 AIRSPEED UNITS 4 5 3 AIRSPEED MINIMUM The AIRSPEED MINIMUM setting allows the installer to select the lowest airspeed which will be displayed above zero 0 This feature allows the unit to be configured similarly to other airspeed displays in the panel and or for mission specific applications At speeds below this minimum the unit will display zero 0 The options are 20 KTS 30 KTS or 40 KTS The default setting is 30 KTS If MPH or KPH airspeed units are selected the airspeed minimum will be calculated that equates to the KTS value selected on this screen Figure 4 19 FIGURE 4 19 AIRSPEED MINIMUM 4 5 4 DISPLAY ORIENTATION The DISPLAY ORIENTATION setting allows the installer to select how the unit will be oriented in the panel It can be installed HORIZONTAL VERTICAL RIGHT VERTICAL LEFT or HORIZONTAL SWAP In the HORIZONTAL orientation the attitude display defaults to the left display and the unit mus
63. uration Module PC Board Assembly contains sensitive electronics that can be damaged by electrostatic discharge ESD Appropriate precautions should be applied prior to handling this component 4 8 9 10 11 12 13 14 15 16 Insert the pins of the Configuration Module PC Board Assembly Item 3 into their corresponding locations as noted below using an appropriate pin insertion tool a The wires coming from the Configuration Module PC Board Assembly are marked as follows on the circuit board TP1 TP2 TP3 TP4 b With the D Sub oriented up pin locations 1 5 on top orient the Configuration Module PC Board Assembly with the electronic parts facing UP prior to pin insertion c Install each pin into the rear of the D Sub connector as follows e Board IP1 config return D Sub pin 15 e Board TP2 config data D Sub pin 14 e Board TP3 config clock D Sub pin 10 e Board TP4 config power D Subpind5 Install the D Sub Backshell Spring Item 5 as shown Place the D Sub Slide Lock Item 6 over the D Sub connector Install the D Sub connector with Slide Lock and cable harness attached into the Backshell Item 1 and secure with 2 screws Item 8 Verify that the Backshell Spring is between the Slide Lock and Backshell Move the Slide Lock back and forth to verify free movement Route the aircraft wire harness bundle excluding shield braids between the two halves of the Cable Strain Relief Clamp Item 7 The Cla
64. ut EXT oV EXT 14V EXT 28V the X axis of the dimming graph will read VOLTAGE and will range from O to 5 14 or 28 This represents the voltage input of the lighting bus and shows the current input with the vertical blue line The Y axis represents brightness of the display It will track the dimming curve with the horizontal blue line as the input voltage increases or decreases When an external lighting input is selected a low level auto adjust feature is added which is represented by a vertical white line on the dimming curve graph When the input lighting voltage is below this level the unit will automatically adjust the brightness based on the ambient light condition sensed by the photocell This provides more accurate lighting output when the lighting voltage is turned down or off The best method for setting the dimming curve is to simulate the range of lighting inputs or conditions to match other instruments This is best done after installation in the actual aircraft instrument panel but can be simulated in various environments Figure 4 15 Mid Continent Instruments and Avionics 44 Manual Number 9017782 Revision H January 7 2015 1 Change the lighting bus input until the vertical blue line matches or nearly matches the yellow highlighted point on the graph 2 Adjust the control knob to increase or decrease the brightness of the display to the desired level at that lighting bus position the point will move up or down r
65. vionics 3 Manual Number 9017782 Revision H January 7 2015 SECTION 1 1 1 1 2 1 2 1 1 2 2 1 2 3 1 2 4 1 3 1 3 1 1 3 2 1 3 3 1 3 4 1 3 5 SECTION 2 2 6 1 2 6 2 2 2 8 2 9 SECTION 3 3 1 3 2 3 3 3 3 1 3 3 2 3 3 3 3 4 3 4 1 3 4 2 TABLE OF CONTENTS GENERAL DESCRIPTION INTRODUC THON ciciccsoruc veio vei so seio Pedes iun SYOTEM OVERVIEW iik oE n denter gute E rue PRE FLIGHT MODE FLIGHT MODE EMERGENCY MODE CONFIGURATION MODE TECHNICAL SPECIFICATIONS emm ELECTRICAL ATTRIBUTES PHYSICAL ATTRIBUTES PERFORMANCE LIMITS QUALIFICATIONS ARINC DATA LABELS INSTALLATION GENERAL INFORMATION enm n PARTS EIS T sioe iiit toc tomba Seid ede E tebe EQUIPMENT LOCATION enmmnyHHmeIHe LIMITATION cet MODIFICATION Ss dud bacs euet Dinero ede aute she tes CABLE HARNESS stcetuieinakaaie des uM cort Ia iiit ion WIRE GAUGE SELECTION CONFIGURATION MODULE PITOT STATIC CONNECTIONS ene MOUINTIIN LC er INSTALLATION COMPLETION emm OPERATION USER INTERFAGE irit itiess hos E tu eh Rn Rar eet PRE FEIGHT MODE c tee u eei a opo he eR ato E nate eue eaae ene rei 8 i MODE E MAJOR FUNCTIONS 3 3 1 1 ATTITUDE OPERATION 3 3 1 1 1 HEADING OPERATION 3 3 1 2 ALTITUDE OPERATION 3 3 1 3 AIRSPEED OPERATION 3 3 1 4 SLIP OPERATION OPTIONS MENU 3 3 2 1 MENU OPERATION 3 3 2 2 ALT UNITS 3 3 2 3 BARO UNITS 3 3 2 4 SYMBOL 3 3 2 5 ATT MASK

Installation Manual and Operating Instructions Model MD302 Series

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