INSTALLATION MANUAL AND OPERATING
Contents
1. i NNUNCIATION CO TU _ PART OF INCOMPLETE SYSTEM Ho EL 0007 TSO 3 20 MAX EL MANUFACTURED BY MID ONTINERNT INSTRUMENTS MOD 2121151211818 0 125 EN ABE L 0 156 typ T 3 en Ri GARMIN 7 i S 3 00 a U ga 3 25 NE E MD41 1510 MD41 1511 MD41 1512 MD41 1513 MD41 1514 MD41 1515 Note Use two 4 40 X 3 8 Flat Head Phillips Screws for Mounting FI GURE 3 4 OUTLI NE DRAWI NG 9 Manual Number 9017211 REV A February 21 2011 MD41 151X Series ACU c A E E E A I RESERVED o ds RESERVED ET 5 14 or 2 FROM LIGHTING BUS for pushbutton lighting see note 4 14 OR 28VDC AIRCRAFT PWR 7 USE 2A CIRCUIT BREAKER POWER GND 2A RESERVED OBS SUSP MODE SELECT APR ANNUN TERM ANNUN WPT ANNUN MSG ANNUN VLOC ANNUN GPS ANNUN CDI SOURCE SELECT LOI ANNUN OBS ANNUN RESERVED LAMP TEST r GTN 6XX 7XX TEST note 3 RESERVED F AUTOMATIC INTERNAL DIMMING ONLY eae ee m RESERVED INTERNAL DIMMING2. ANNUN BRIGHT DIM 3 OPTIONS EXTERNAL DIMMING EXCEPT 1514 1515 FROM LIGHTING BUS SPARE FULL BRIGHT FROM MD41 ACU CIRUIT BREAKER 14 OR 28VDC SPARE NOTES 1 REFER TO GARMIN GTN 6XX 7XX INSTALLATION MANUAL FOR ACTUAL INSTALLATION 2 ALL WIRING SHALL BE 24 AWG UNLESS OTHERWISE NOTED 3 MOMENTARY SWITCH FOR TEST optional connection 4 5 VOLT FOR MD41 1514 1515 14 VOLT FOR MD41 1512 1513 AND 28 VOLT FOR MD41 1510 1511 FI GURE 3 5 WIRING DIAGRAM REV February 21 2011 10 Manual Number 9017211 SECTION 4 OPERATION 4 1 FRONT PANEL CONTROLS AND ANNUNCIATIONS 4 1 1 CONTROLS CDI Momentary Switch when pressed will select VLOC or GPS presentation on HSI CDI OBS SUSP Momentary switch when pressed will select OBS or SUSP In OBS MODE this will enable OBS selection input from a remote HSI CDI indicator In SUSP mode this will suspend automatic waypoint sequencing in the active flight plan All button switch controls are white backlit Refer to the operation manual of the GPS SBAS System equipment manufacturer for additional operational and functional interface details 4 1 2 ANNUNCIATI ONS LOI AMBER Loss of Integrity WAAS GPS detects a position error or unable to calculate integrity of position TERM GREEN Terminal Indicates aircraft is navigating within 30 miles of the departure or arrival airport APR GREEN Approach Indicates the approach is active MSG WHITE Message Indicates messa
3. MID CONTINENT INSTRUMENTS INSTALLATI ON MANUAL AND OPERATI NG I NSTRUCTI ONS MD41 151X Series GPS Annunciation Control Unit For Garmin GTN 6XX 7XX Systems MD41 1510 28vdc Horizontal Mount MD41 1512 14vdc Horizontal Mount MD41 1514 28vdc X Horizontal Mount 5vdc lighting MD41 1511 28vdc Vertical Mount MD41 1513 l4vdc Vertical Mount MD41 1515 28vdc Vertical Mount 5vdc lighting REV A February 21 2011 MANUAL NUMBER 9017211 REVISION DETAIL Detail A 02 21 11 Initial release REV A February 21 2011 Manual Number 9017211 TABLE 5 SECTION 1 GENERAL DESCRIPTION 11 INTRODUCTION 1 2 TECHNICAL SPECIFICATIONS 1 2 1 MODELS 12 2 PHYSICAL ATTRIBUTES 12 3 PERFORMANCE SECTION2 INSTALLATION CONSI DERATI ONS 2 1 COOLING 2 2 EQUIPMENT LOCATION 2 3 ROUTING OF CABLES 2 4 LIMITATIONS SECTION3 INSTALLATION PROCEDURE 3 1 GENERAL INFORMATION 3 2 UNPACKING AND INSPECTING 3 3 CABLE HARNESS 3 3 1 LIGHTING CONTROLS 3 32 SIGNALS AND POWER 3 3 3 HARNESS VERIFICATION 3 4 MOUNTING SECTION 4 OPERATION 41 FRONT PANEL CONTROLS AND ANNUNCI ATI ONS 4 1 1 CONTROLS 4 1 2 ANNUCIATIONS SECTION5 CONFORMANCE 5 1 OPERATING INSTRUCTIONS 5 2 CONTINUED AIRWORTHINESS STATEMENT 5 3 ENVIRONMENTAL QUALIFICATION STATEMENT NUMBER LIST OF TABLES AND FIGURES 11 MODELS TABLE 1 2 PHYSICAL ATTRIBUTES TABLE 1 3 PERFORMANCE TABLE 3 3 CONNECTOR PINOUT F
4. 28VDC Lighting Input 28VDC 14VDC 5VDC Table 1 1 1 2 2 PHYSICAL ATTRI BUTES Characteristics Weight 0 26 pounds Dimensions 3 2 inches long not including connector or mate 3 25 inches wide 0 8 inches high Mating Connector Positronic RD25F10J VLO or equivalent MCI P N 7014517 Instrument Panel Mounting Rear mount Table 1 2 1 2 3 PERFORMANCE Specifications Qualification FAA TSO C129 Environmental Qualification RTCA DO 160D Environmental Category F2CAB SM UG XXXXXXZBABA TT M A3C3 XXA Sections 16 20 21 and 22 comply with DO 160C Section 8 UG complies with DO 160F Power Requirement 0 20 A max REV A February 21 2011 5 Manual Number 9017211 Table 1 3 SECTION 2 PRE I NSTALLATI ON CONSI DERATI ONS 2 1 COOLI NG No direct cooling is required As with any electronic equipment overall reliability may be increased if the unit is not located near a high heat source or crowded next to other equipment Means of providing some airflow would be considered beneficial 2 2 EQUI PMENT LOCATI ON The MD41 151X series ACU must be mounted as close to the pilot s field of view as possible Please reference the GPS SBAS installation manual for approved locations The unit depth with connector attached must also be taken into consideration when selecting an appropriate location Allow at least 3 inches of space behind the unit for connector attachment and removal 2 3 ROUTI
5. IGURE 3 3 SCHEMATIC PIONOUT TABLE 3 4 OUTLINE DRAWING 3 5 WIRING DIAGRAM 4 1 FRONT PANEL FIGURE REV A February 21 2011 4 Manual Number 9017211 SECTION 1 GENERAL DESCRI PTI 1 1 INTRODUCTION The MD41 151X series products are compact self contained Annunciation and Control Units ACUs The fully integrated control unit provides annunciation and mode selection for Global Positioning System GPS Satellite Based Augmentation System SBAS navigators This series of the MD41 product family is specifically designed to work with the Garmin GTN 6XX 7XX series WAAS navigator systems and derivatives with equivalent functionality It combines the necessary functions and annunciations required to interface with an approved system and provide regulatory compliance with GPS SBAS minimum performance specifications Highlighted features include long life LEDs used for all lighting internally backlit selection switches dead front inactive annunciations and the installation option for manual or automatic dimming An external annunciation dimming adjustment is provided for balancing low level light conditions 1 2 TECHNI CAL SPECI FI CATI ONS 1 2 4 MODELS Unit Configurations MD41 1510 MD41 1512 MD41 1514 Orientation Horizontal Horizontal Horizontal Power Input 28VDC 14VDC 28VDC Lighting Input 28VDC 14VDC 5VDC MD41 1511 MD41 1513 MD41 1515 Orientation Vertical Vertical Vertical Power Input 28VDC 14VDC
6. NG OF CABLES Care must be taken not to bundle the MD41 series ACU logic and low level signal lines with any high energy sources Examples of these sources include 400 HZ AC Comm DME HF and transponder transmitter coaxial cables Always use shielded wire when shown on the installation print Avoid sharp bends in cabling and routing near aircraft control cables Also avoid proximity and contact with aircraft structures avionics equipment or other obstructions that could chafe wires during flight and cause undesirable effects 2 4 LI MITATI ONS 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 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 Note that this product is part of an incomplete system It is designed to be installed with other applicable equipment to provide functionality for global positioning satellite based augmentation systems REV A February 21 2011 6 Manual Number 9017211 SECTION 3 INSTALLATION PROCEDURES 3 1 GENERAL I NFORMATI ON This section contains interconnect diagrams mounting dimensions and other information pertaining to the installation of the MD41 series ACU After installati
7. ODEL NUMBER MD41 151X series TSO NUMBER C129 MANUFACTURERS SPECI FI CATI ONS Minimum Performance Specifications Test Specification TS 187 Test Data Sheet TDS 444 QUALI FI CATI ON STANDARD RTCA DO 160D denotes qualification to RTCA DO 160C denotes qualification to RTCA DO 160F CONDITIONS DESCRI PTI ON OF TEST Temperature and Altitude Category F2 Low Temperature D Operating Low Temp 55C High Temperature 5 Operating High Temp 70 Decompression 6 Altitude 55K Overpressure_ 15 000 ft Temperature Variation 5 Humidity 16 4 O I d S Crash Safet Vibration Category S Curve M Category U Curve G SM UG explosion 29 Audio Frequency Conducted 18 Category B Susceptibilit Induced Signal Susceptibilit Radio Frequency Susceptibility 20 Category T conducted Category T radiated TT M Lightning Induced Transient Category A3 pin injection Susceptibility Category C3 cable bundle A3C3 REV A February 21 2011 12 Manual Number 9017211
8. craft with 5V lighting bus e Automatically dimming using the internal photocell of the unit o Connect pin 23 Annun Bright Dim Output to pin 6 3 3 2 POWER AND SIGNALS Wire aircraft power and aircraft ground according to the associated ACU pins in the Pinout Diagram Annunciation signals should be wired from the appropriate system inputs and outputs to the associated ACU pins in the Pinout Diagram 3 3 3 HARNESS VERIFICATION With the MD41 ACU disconnected turn on the avionics master switch and use an ohm meter to verify that aircraft power and panel lighting bus power is on the appropriate pin s with appropriate voltage Also verify that aircraft ground is applied to the appropriate pins REV A February 21 2011 7 Manual Number 9017211 3 4 MOUNTI NG Refer to Section 2 Pre Installation Considerations in regards to equipment location The MD41 ACU is designed for rear panel mounting only A cutout should be made in the panel in accordance with Figure 3 4 for the unit bezel and two mounting holes A cutout template is available from Mid Continent Instruments reference p n 8014458 upon request Prior to completing the mounting of the unit in the aircraft make sure to set the Annunciator Dim Adjustment if automatic dimming is configured for the annunciations Ideally this procedure is best performed in a dark cockpit to simulate low light night time conditions Connect the unit to the cable harness and turn on master power to the instrumen
9. ge s is active VLOC GREEN VOR Localizer NAV ILS information presented on the HSI or CDI GPS WHITE GPS information presented on the HSI or CDI WPT WHITE Waypoint Indicates reaching the arrival waypoint AUTO WHITE Automatic sequencing of waypoints is active SUSP Suspended Automatic sequencing of waypoints has been suspended FI GURE 4 1 FRONT PANEL 4 2 LI GHTI NG BEHAVI OR Lighting behavior can be controlled in multiple ways Button lighting is controlled manually using the aircraft s panel lighting bus controller Annunciations can be configured to automatically dim using the internal photocell configured to be on full bright or controlled manually with external dimming excluding 1514 1515 using the aircraft s panel lighting bus controller when activated If using the internal dimming feature for the annunciations the Annunciator Dim Adjust on the outside of the unit can be used to set the brightness at their dimmest level for best night time viewing REV A February 21 2011 11 Manual Number 9017211 SECTION 5 CONFORMANCE 5 1 CONTI NUED AIRWORTHI NESS STATEMENT No periodic scheduled maintenance or calibration is necessary for continued airworthiness of the MD41 series ACU If the unit fails to perform to specifications the unit must be removed and serviced by Mid Continent Instruments or their authorized designee 5 2 ENVI RONMENTAL QUALI FI CATI ON STATEMENT NOMENCLATURE GPS Annunciator Control Unit ACU M
10. on of cabling and before installation of the equipment ensure that power is applied only to the pins specified in the interconnect diagram 3 2 UNPACKI NG AND I NSPECTI NG EQUI PMENT 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 a GPS ACU MCI P N MD41 151X series b 1 Connector Kit 25 pin MCI P N 7014517 c Installation Manual MCI P N 9017211 3 3 CABLE HARNESS The MD41 cable harness should be made using 24 AWG wire or larger for all connections Construct the cable harness with regards to the instructions below and using the Connector Pinout of Figure 3 3 Schematic Pinout of Table 3 3 and Wiring Diagram of Figure 3 5 Refer to Section 2 Pre Installation Considerations in regards to routing precautions 3 3 1 LIGHTI NG CONTROL Button backlighting pin 5 is powered 5vdc 14vdc or 28vdc from the aircraft s panel lighting bus This will allow manual dimming control of the button brightness using the aircraft s panel lighting control dimmer There are three options for annunciation brightness control The annunciations options can be configured in the following ways e Full bright when active o connect aircraft power same as pin 13 input to pin 6 e Manual control using the aircraft s panel lighting control o connect the aircraft lighting bus power output same as pin 5 input to pin 6 o not available for air
11. t panel and lighting bus Use a small flat bladed screwdriver to access the adjustment screw inside the hole on the bottom of the unit Adjust the screw to increase or decrease the annunciator lighting brightness to a level appropriate with the rest of the panel instrument lighting Secure the indicator to the panel with two 44 40 x 3 8 flat head phillips screws FI GURE 3 3 REAR VI EW OF 25 PI N D SUB CONNECTOR J 1 1 T 1 amun GPSiput i4 Reseed 2 nunViOC mut 15 Reseved 3 Annun TERM input 16 Reemed 4 EDI Switch output 17 Reseved 5 BighuDim Button Backightinput 18 Reserved 6 Annun Bight Dim input 19 Reseved 7 AmunlOImpu 8 AnnunWPTiput 21 Reseed 9 Annun APRinput 22 Reseved 3o Annun MSG input 23 Annun Bight Dim output iijomipu 1 24 SUP i2 0 5 Swichoutput 25 Gmud 13 Aircrat Power riav 2ey OOOO TABLE 3 3 SCHEMATI C PI NOUT REV A February 21 2011 8 Manual Number 9017211
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