INSTALLATION MANUAL AND OPERATING INSTRUCTIONS
Contents
1. 6 Bright Dim annunciation lamp power T LAMP TEST receives ground from remote test switch optional conn 8 WPT ANNUNCIATION Q APR ANNUNCIATION 10 MSG ANNUNCIATION 11 SPARE 12 OBS MODE SELECT momentary logic low sent to the receiver 13 28VDC UNIT POWER 14 SPARE 15 SPARE 16 SPARE 17 SPARE 18 SPARE 19 SPARE 20 INTG ANNUNCIATION 21 SPARE 22 SPARE 23 Internal photocell dimming output To use jumper pin 23 to pin 6 24 OBS ANNUNCIATION 25 POWER GROUND FIGURE 3 1 SCHEMATIC PINOUT 25 PIN DSUB REV A October 28 2013 10 Ga EE Note 1 Use two 4 40 X 3 8 Flat Head Phillips Screws for Mounting FIGURE 3 2 OUTLINE DRAWING REV A October 28 2013 11 28VDC s TOLLIGHTING BUS 28VDC AIRCRAFT PWR FN TO MD41 ACU CIRCUIT BREAKER POWER GND 2A OBS ANN SPARE OBS MODE SELECT APR ANN TERM A2. The MD41 must be mounted as close to the pilot s field of view as possible The preferable location is near the HSI CDI that will be displaying the GPS VLOC information The unit depth with connector attached must also be taken into consideration Note Unlike previous versions of the MD41 Annunciation Control Units ACU the transfer relays are not required as all switching between GPS VOR and ILS is handled by the GNS 430 530 This has allowed a for a smaller size ACU which now provides more options for panel mounting 2 3 ROUTING OF CABLES Care must be taken not to bundle the MD41 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 coax Always use shielded wire when shown on the installation print Avoid sharp bends in cabling and routing near aircraft control cables REV A October 28 2013 8 SECTION 3 INSTALLATION PROCEDURES 3 1 GENERAL INFORMATION This section contains interconnect diagrams mounting dimensions and other information pertaining to the installation of the MD41 After installation of cabling and before installation of the equipment ensure that power is applied only to the pins specified in the interconnect diagram 3 2 UNPACKING AND INSPECTING EQUIPMENT When unpacking equipment make a visual inspection for evidence of damage incurred during shipment The following parts should be included 1 MD41 1470
3. 28 volt Horiz Mount 2 J1 Connector Kit 25 pin MCI PN 7014517 3 Installation Manual MCI PN 9014952 3 3 MOUNTING THE MD41 Plan a location in the aircraft for the MD41 to be mounted as close to the pilot s field of view as possible The preferable location is near the HSI CDI that will be displaying the GPS information Avoid mounting close to heater vents or other high heat sources Allow a clearance of at least 3 inches from back of unit for plug removal The indicator is secured in place behind the panel since it is designed for rear mount only Make a panel cutout as shown in Figure 3 2 Secure the indicator in place with two 4 40 x 3 8 flat head phillips screws 3 4 INSTALLATION LIMITATIONS Wire the aircraft harness according to figure 3 3 Use at least 24 AWG wire for all connections Avoid sharp bends and routing cable near high energy sources Care must be taken to tie the harness away from aircraft controls and cables Normal installation techniques should be applied Also see equipment limitations section 1 2 6 REV A October 28 2013 9 Ci Ti eeeeeeeveeeececce eeeeoeevedeeee2 0 REAR VIEW OF JI CONNECTOR JI PINNO l GPS ANNUNCIATION 2 VLOC ANNNCIATION 3 TERM ANNUNCIATION 4 SPARE 5 28vDCDIMMER IN from aircraft dimming bus for push button lighting
4. NN WPT ANN MSG ANN VLOC ANNUNCIATION GPS ANNUNCIATION SPARE INTG ANNUNCIATION BRIGHT DIM ANNUNCIATOR POWER INPUT NOTE 4 SPARE SPARE SPARE LAMP TEST ikel note 3 INTERNAL DIMMING OUTPUT note 4 SPARE SPARE SPARE SPARE P4001 GNS 430 P5001 GNS 530 EBRERE SERS NOTES 1 REFER TO GARMIN GNS 430 530 INSTALLATION MANUAL FOR ACTUAL INSTALLATION 2 ALL WIRING SHALL BE 24 AWG UNLESS OTHERWISE NOTED 3 MOMENTARY SWITCH FOR TEST optional connection 4 INSTALL JUMPER BETWEEN PIN 6 AND 23 TO USE INTERNAL DIMMING FIGURE 3 3 WIRING DIAGRAM MD41 1470 GARMIN GNS 430 530 REV A October 28 2013 12 SECTION 4 POST INSTALLATION CHECKOUT 4 1 PRE INSTALLATION TESTS With the MD41 disconnected turn on the avionics master switch and verify that aircraft power is on pin 13 for Using an ohm meter verify pin 25 is aircraft ground 4 2 OPERATING INSTRUCTIONS Turn off the avionics master switch and connect the mating connector to the MD41 Turn on the avionics master switch and the MD41 should come on with the following annunciations 1 VLOC or GPS 2 AUTO 3 MSG may be flashing depending on the status of the GPS receiver Press the lamp test button if installed all annunciations should light Continue pressing the lamp test button and cover the photocell window located in the center of the front panel All annunciations should dim Annunciation brightness at the minimum dimming l
5. T INSTALLATION CHECKOUT PRE INSTALLATION TEST OPERATING INSTRUCTIONS LIST OF ILLUSTRATIONS SCHEMATIC PINOUT 25 PIN DSUB OUTLINE DRAWING WIRING DIAGRAM MD41 1470 28Volt APPENDIX ENVIRONMENTAL QUALIFICATION FORM SECTION 1 GENERAL DESCRIPTION 1 1 INTRODUCTION The MD41 is a compact self contained GPS Annunciation and Control unit It meets all requirements for external remote mode selection and status annunciation for the Garmin GNS 430 530 VHF Communications and Navigation Management System Features include dual 20 000 hour lamps used for all annunciations internally lighted selection switches and automatic photocell dimming An external annunciation dimming adjustment is provided for balancing low level light conditions 1 2 SPECIFICATIONS TECHNICAL Mid Continent Instruments Co Inc certifies that the model MD41 series Annunciation Control Unit has been tested to and meets or exceeds the functional and environmental requirements of the following FAA Technical Standard Order TSO e FAA TSO Cl5la TERRAIN AWARENESS AND WARNING SYSTEM We also certify we meet the requirements of Part 21 Subpart 0 of the Code of Federal Regulations The MD41 series Annunciation Control Unit conforms to all pertinent documented design and internal manufacturing standards This includes but is not limited to component drawings specifications testing criteria inspection requirements quality processes manufacturing ins
6. evel may be adjusted by rotation of the dimmer control located on the bottom of the MD41 case CW rotation lowers the dimming level Refer to section 5 2 7 of the Garmin GNS 430 or GNS 530 installation manual for testing of external mode select switches and annunciations No periodic maintenance or calibration is necessary for continued airworthiness of the MD41 REV A October 28 2013 13 ENVIRONMENTAL QUALIFICATION FORM RTCA DO160C NOMENCLATURE MDAI GPS ANNUNCIATION CONTROL UNIT MODEL NO MD41 TSO NO C129 CLASS Al MANUFACTURER TEST SPECIFICATION MPS 7015613 MANUFACTURER Mid Continent Instruments and Avionics 9400 E 34 Street N Wichita KS 67226 Phone 316 630 0101 Temperature and Altitude 4 0 Equipment tested to Categories Al amp F2 except as noted Low Temperature 4 5 1 High Temperature 4 5 2 amp 4 5 3 In Flight Loss of Cooling 4 5 4 Cooling air not required Altitude 4 6 1 Decompression 4 6 2 Overpressure 4 6 3 Not Tested Shock 7 0 Equipment tested per DO 160C Operational 7 2 Par 7 2 1 Crash Safety Vibration Equipment tested without shockmounts to Categories M and N Table 8 1 71 3 Explosion Led Equipment identified as Category X no test required Waterproofness Equipment identified as Category X no test required REV A October 28 2013 14 Environmental Qualification cont Conditions Section Description of Conducted Tests Sand and Dust 2 0 Equipment identified a
7. ic dash numbers to be used with various GPS receivers or Navigation Management Systems The installer must match the correct controller part number with the system being installed The conditions and tests required for TSO approval of this article are minimum performance standards It is the responsibility of those desiring to install this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards The article may be installed only if further evaluation by the applicant documents an acceptable installation and is approved by the Administrator The MD41 1470 is TSO D and certified for use with the Garmin GNS 430 530 system Any attempts to install the listed units in an installation other than the GNS 430 530 system is prohibited This will void the TSO NOTE If the MD41 is disconnected or removed from the aircraft there will be no effect in the operation of the GNS 430 530 system 1 2 7 MAJOR COMPONENTS This system is comprised of one major component the MD41 1470 GPS Annunciation Control Unit REV A October 28 2013 7 SECTION 2 INSTALLATION CONSIDERATIONS 2 1 COOLING No direct cooling is required As with any electronic equipment overall reliability may be increased if the MD41 is not located near any high heat source or crowded next to other equipment Means of providing a gentle air flow will be a plus 2 2 EQUIPMENT LOCATION
8. mi Midcontinent INSTRUMENTS AVIONICS INSTALLATION MANUAL AND OPERATING INSTRUCTIONS MD41 Series GPS Annunciation Control Unit for Garmin GTN 650 750 MD41 1470 28vdc Horizontal Mount Mid Continent Instruments and Avionics Manual Number 9014952 9400 E 34 Street N Wichita KS 67226 USA REV A October 28 2013 Phone 316 630 0101 e Fax 316 630 0723 MANUAL REVISION AND HISTORY MANUAL MD41 1470 ECO Rev Date Approved Detail 1 04 09 2002 CS Added provisions for controlling annunciation externally This includes assignments for pins 6 and 23 6051 A 10 28 2013 BAW Updated Technical Specifications to include compatible Garmin GTN Systems REV A October 28 2013 SECTION 1 1 1 1 2 1 2 1 1 2 2 1 2 3 1 2 4 1 2 4 1 1 2 4 2 1 2 5 1 2 6 1 2 7 SECTION 2 2 1 2 2 2 3 SECTION 3 3 1 IL 3 3 3 4 SECTION 4 4 1 4 2 FIGURE NO 3 1 3 2 3 3 REV A October 28 2013 TABLE OF CONTENTS GENERAL DESCRIPTION INTRODUCTION SPECIFICATIONS TECHNICAL PHYSICAL CHARACTERISTICS ENVIRONMENTAL CHARACTERISTICS SPECIFICATIONS ELECTRICAL FRONT PANEL CONTROLS AND ANNUNCIATIONS CONTROLS ANNUNCIATIONS INTERFACE EQUIPMENT LIMITATIONS MAJOR COMPONENTS INSTALLATION CONSIDERATIONS COOLING EQUIPMENT LOCATION ROUTING OF CABLES INSTALLATION PROCEDURE GENERAL INFORMATION UNPACKING AND INSPECTING MOUNTING THE MD41 INSTALLATION LIMITATIONS POS
9. s Category X no test required G L aa Susceptibilitv Induced Signal Susceptibilitv Equipment tested to Categorv A Radio Frequencv 20 0 Equipment tested to Categorv T Susceptibilitv Radio Frequencv Emissions KI Equipment tested to Categorv Z Lightning Induced Transient Equipment identified as Category X no tests required Susceptibility Lightning Direct Effects Equipment identified as Category X no tests required Equipment identified as Category X no test required REV A October 28 2013 15
10. selection input from a remote HSI CDI indicator NAV or ILS information presented on the HSI or CDI GPS information presented on the HSI or CDI On indicates message s active On indicates reaching the arrival waypoint Automatic sequencing of waypoints is active On indicates GPS OBS mode of operation Illuminates when GPS receiver detects a position error or is unable to calculate the integrity of the position On indicates aircraft is within 30 miles of departure or arrival airport On indicates the approach is active VLOC annunciation Receives ground from GNS 430 530 JI Pin 2 when in VOR ILS mode GPS annunciation Receives ground from GNS 430 JI Pin 1 OBS select when in GPS mode Provides a momentary logic low to the J1 Pin 12 GNS 430 530 when OBS is selected Selects between AUTO and OBS OBS annunciation Requires a logic low to annunciate JI Pin 24 REV A October 28 2013 1 2 5 INTERFACE cont INTG annunciation Requires a logic low to annunciate J1 Pin 20 TERM annunciation Requires a logic low to annunciate J1 Pin 3 APR annunciation Requires a logic low to annunciate JI Pin 9 WPT annunciation Requires a logic low to annunciate J1 Pin 8 MSG annunciation Requires a logic low to annunciate J1 Pin 10 Lamp Test Receives ground from remote test switch JI Pin7 to light all annunciations optional connection 1 2 6 EQUIPMENT LIMITATIONS The MD41 series control units contain specif
11. tructions and handling procedures It shall be manufactured in accordance with Mid Continent Instruments FAA approved Production Approval Holder Quality System Manual Revision M dated April 14 2011 or later The MD41 10XX series complies with the manufacturers specifications and has been verified and approved for use with the following systems Mid Continent Instruments and Avionics Designed for use with Model Number s TAWS System MD41 1470 Manufacturer Garmin International Model GTN 650 750 REV A October 28 2013 4 1 2 1 PHYSICAL CHARACTERISTICS Mounting Width Height Depth Weight 1 2 2 ENVIRONMENTAL CHARACTERISTICS TSO Compliance Applicable Documents Operating Temperature Range Humidity Altitude Range Vibration Operational Shock 1 2 3 SPECIFICATIONS ELECTRICAL Design MD41 1470 28VDC REV A October 28 2013 Panel 3 25 Inches 80 Inches 3 20 Inches 0 50 lbs TSO C129 RTCA DO 160C DO 208 55 C to 70 C 95 Non Condensing 0 to 55 000 ft Cat M and N Rigid Mounting 6 G Operational 15 G Crash Safety All Solid State 0 30 Amps 1 2 4 FRONT PANEL CONTROLS AND ANNUNCIATIONS 1 2 4 1 CONTROLS OBS 1 2 4 2 ANNUNCIATIONS VLOC GPS MSG WPT AUTO OBS INTG TERM APR 1 2 5 INTERFACE Momentary action switch when pressed will select between automatic waypoint sequencing AUTO mode and OBS mode In OBS mode this will enable OBS
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