MD41-1474A Installation Manual - Mid
Contents
1. POWER GROUND FIGURE 3 1 SCHEMATIC PINOUT 25 PIN DSUB REV B January 26 2015 10 35 HORIZONAL MOUNT APR Green ej PT Amber 7 OBS Gre 8 AUTO White INTG Amber Note 1 Use two 4 40 X 3 8 Flat Head Phillips Screws for Mounting FIGURE 3 2 OUTLINE DRAWING REV B January 26 2015 11 MD41 146XA 147XA SERIES ACU for pushbutton lighting see note 4 5 14 or 28VDC TO LIGHTING BUS 14 OR 28VDC AIRCRAFT PWR f TO MD41 ACU CIRCUIT BREAKER POWER GND 2A OBS ANN SPARE OBS MODE SELECT APR ANN TERM ANN WPT ANN MSG ANN VLOC ANNUNCIATION GPS ANNUNCIATION CDI SOURCE SELECT INTG ANNUNCIATION SPARE SPARE SPARE SPARE LAMP TEST c SPARE RAT SPARE i SPARE SPARE SPARE SPARE P4001 GNS 430 P5001 GNS 530 efas E TEST 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 5 VOLT FOR MD41 1468A 5V 1478A 5V 14 VOLT FOR MD41 1464A 1474A AND 28 VOLT FOR MD41 1468A 1478A FIGURE 3 3 WIRING DIAGRAM MD41 1468A 1478A 1468A 5V 1478A 5V 1464A 1474A REV B January 26 2015 12 GARMIN GNS 430 530 SECTION 4 POST INSTALLATION CHECKOUT 4 1 PRE INSTALLATION TESTS With the MD41 disconnected turn2. MidContinent INSTRUMENTS AVIONICS J INSTALLATION MANUAL AND OPERATING INSTRUCTIONS MD41 Series GPS Annunciation Control Unit for Garmin GNS 430 530 MD41 1468A 28vdc Horizontal Mount MD41 1478A 28vdc Vertical Mount shown on page 10 MD41 1464A 14vdc Horizontal Mount MD41 1474A 1Avdc Vertical Mount shown on page 10 BA 2 LAA Mid Continent Instruments and Avionics Manual Number 9010778 9400 E 34 Street N Wichita KS 67226 USA REV B January 26 2015 Phone 316 630 0101 e Fax 316 630 0723 Revision Detail ECO Rev Date Detail N R 05 30 00 Complete issue 1 11 28 06 Added A W and TAWS receivers 6051 A 10 28 13 Updated Technical Specifications to include compatible Garmin GTN Svstems 6335 B 01 26 2015 Corrected title and Technical Specifications to reference compatible Garmin GNS Systems REV B January 26 2015 SECTION 1 1 1 1 2 1 2 1 F22 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 22 2 3 SECTION 3 3 1 3 2 3 3 3 4 SECTION 4 4 1 4 2 FIGURE NO 3 1 3 2 3 3 REV B January 26 2015 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 EQUI
3. PMENT LOCATION ROUTING OF CABLES INSTALLATION PROCEDURE GENERAL INFORMATION UNPACKING AND INSPECTING MOUNTING THE MD41 INSTALLATION LIMITATIONS POST INSTALLATION CHECKOUT PRE INSTALLATION TEST OPERATING INSTRUCTIONS LIST OF ILLUSTRATIONS SCHEMATIC PINOUT 25 PIN DSUB OUTLINE DRAWING WIRING DIAGRAM MD41 1464A 1474A 14Volt MD41 1468A 1478A 1468A 5V 1478A S5V 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 Communication 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 pert
4. T PANEL CONTROLS AND ANNUNCIATIONS 1 2 4 1 CONTROLS GPS OBS REV B January 26 2015 Momentary action switch when pressed will select LOC or GPS presentation on HSI CDI Momentary action switch when pressed will select between automatic waypoint sequencing AUTO mode and OBS mode In OBS mode this will enable OBS selection input from a remote HSI CDI indicator 1 2 4 2 ANNUNCIATIONS VLOC NAV or ILS information presented on the HSI or CDI GPS GPS information presented on the HSI or CDI MSG On indicates message s active WPT On indicates reaching the arrival wavpoint AUTO Automatic sequencing of waypoints is active OBS On indicates GPS OBS mode of operation INTG On indicates GPS receiver detecting a position error TERM On indicates aircraft is within 30 miles of departure or arrival airport APR On indicates the approach is active 1 2 5 INTERFACE CDI select Provides a momentary low to the JI Pin 4 GNS 430 530 VLOC annunciation Receives ground from GNS 430 530 JI Pin 2 when in VOR ILS mode GPS annunciation Receives ground from GNS 430 530 JI Pin 1 when in GPS mode OBS select 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 TERM annunciation Requires a logic low to annunciate JI Pin 3 APR annunciation Requires a logic low to annunciate JI Pin 9 WPT annunciation Requires a l
5. en 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 B January 26 2015 9 REAR VIEW OF JI CONNECTOR JI PINNO l GPS ANNUNCIATION 2 VLOC ANNNCIATION 3 TERM ANNUNCIATION 4 CDI SOURCE SELECT momentary logic low sent to receiver 5 DIMMER IN from aircraft dimming bus for push button lighting 6 SPARE T LAMP TEST receives ground from remote test switch optional conn 8 WPT ANNUNCIATION Q APR ANNUNCIATION 10 MSG ANNUNCIATION SPARE 12 OBS MODE SELECT momentary logic low sent to the receiver 13 14 or 28 VDC UNIT POWER depends on dash number 14 SPARE 15 SPARE 16 SPARE 17 SPARE 18 SPARE 19 SPARE 20 INTG ANNUNCIATION 2 SPARE 22 SPARE 23 SPARE 24 OBS ANNUNCIATION 25
6. inent documented design and internal manufacturing standards This includes but is not limited to component drawings specifications testing criteria inspection requirements quality processes manufacturing instructions 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 151X 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 GPS System MD41 1468A Manufacturer Garmin International MD41 1478A Model s 430 530 MD41 1464A CDI HSI Annunciators MD41 1474A REV B January 26 2015 4 1 2 1 PHYSICAL CHARACTERISTICS Mounting Width Height Depth Weight Panel 3 25 Inches 80 Inches 3 20 Inches 0 50 Ibs 1 2 2 ENVIRONMENTAL CHARACTERISTICS TSO Compliance TSO C129 Applicable Documents RTCA DO 160C DO 208 Operating Temperature Range 55 C to 70 C Humidity 95 Non Condensing Altitude Range 0 to 55 000 ft Vibration Cat M and N Operational Shock Rigid Mounting 6 G Operational 15 G Crash Safety 1 2 3 SPECIFICATIONS ELECTRICAL Design All Solid State MD41 1464A 1474A 14VDC 0 40 Amps MD41 1468A 1478A 28VDC 0 30 Amps MD41 1468A 5V 1478A SV 28DC 0 30 Amps 1 2 4 FRON
7. 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 1464A 14volt or MD41 1468A 28 volt Horiz Mount MD41 1474A 14volt or MD41 1478A 28volt Vert Mount MD41 1468A 5V 28volt 5 volt button lighting Horiz Mount MD41 1478A 5V 28volt 5 volt button lighting Vert Mount 2 JI Connector Kit 25 pin MCI PN 7014517 3 Installation Manual MCI PN 9010778 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 displaving 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 tak
8. ogic low to annunciate REV B January 26 2015 6 1 2 5 INTERFACE cont JI Pin8 MSG annunciation Requires a logic low to annunciate JI Pin 10 INTG annunciation Requires a logic low to annunciate J1 Pin 20 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 specific 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 1464A 1474A 1468A 1478A 1468A 5V 1478A S5V is TSO D and certified for use with the Garmin GNS 430 530 system This includes the A W and TAWS versions NOTE If the MD41 is disconnected or removed from the aircraft there will be no effect in the operation of the GNS 430 530 1 2 7 MAJOR COMPONENTS This system is comprised of one major component the MD41 146XA 147XA series GPS Annunciation Con
9. 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 level 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 B January 26 2015 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 te
10. sted 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 7 3 E A Equipment identified as Category X no test required Equipment identified as Category X no test required ibili Equipment identified as Category X no test required Fluids Susceptibility REV B January 26 2015 14 Environmental Qualification cont Conditions Section Description of Conducted Tests Sand and Dust Equipment identified as Categorv X no test required Equipment identified as Categorv X no test required Equipment identified as Categorv X no tests required Equipment identified as Category X no tests required Equipment identified as Category X no test required Fungus Salt Spray Magnetic Effect Power Input Voltage Spike Audio Frequency Susceptibilit Induced Signal Susceptibility Radio Frequency Susceptibility Radio Frequency Emissions 12 0 13 0 14 0 15 0 16 0 17 0 18 0 19 0 20 0 21 0 2 0 Lightning Induced Transient 2 Susceptibility Lightning Direct Effects 23 0 Icing 24 0 REV B January 26 2015 15
11. trol Unit REV B January 26 2015 7 SECTION 2 INSTALLATION CONSIDERATIONS 2 1 COOLING No direct cooling is required As with anv electronic equipment overall reliabilitv mav 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 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 B January 26 2015 8 SECTION 3 INSTALLATION PROCEDURES 3 1 GENERAL INFORMATION This section contains interconnect diagrams mounting dimensions and other information pertaining to the installation
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