MD41-1428 Installation Manual - Mid
Contents
1. ILS FROM NAV VOR REC for ILS override optional 16 SPARE 17 SPARE 18 SPARE 19 SPARE 20 SPARE 2 SPARE 22 SPARE 23 SPARE 24 SPARE 25 POWER GROUND FIGURE 3 1 SCHEMATIC PINOUT 25 PIN DSUB REV 2 Jan 2 1998 10 7 PIN DSUB CONNECTOR HORIZONTAL MOUNT ERTICAL MOUNT Note 1 Use two 4 40 X 3 8 Flat Head Phillips Screws for Mounting REV 2 Jan 2 1998 FIGURE 3 2 OUTLINE DRAWING 11 REV 2 TO LIGHTING BUS for pushbutton lighting 4 OR 28VDC AIRCRAFT PWR TO MD41 ACU RELAY UNIT CIRCUIT BREAKEI POWER GNI ILS ENERGIZE not 3PS SEQ SELECT lt SPS APR ACTV ANN NOTES MSG ANN PT ANN si a ER APR ARM SELECT NNECT ONLY IF SYSTEM IS TO BE FORCED TO NAV MODE SPARE HEN ILS IS SELECTEI SPARE 2 RELAYS IN NORMALLY CLOSED POSITION WITH NAV SELECTEI NAV ANNUNCIATION REFER TO GARMIN INSTALLATION MANUAL FOR ACTUAL GPS ANNUNCIATION2. 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 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 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 have been removed and are now remotely mounted in a separate package designated as the MD41 244 248 Relay Unit This has allowed a for a smaller size ACU which now provides more options for panel mounting 23 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 2 Jan 2 1998 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 i
3. 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 POST INSTALLATION CHECKOUT PRE INSTALLATION TEST OPERATING INSTRUCTIONS LIST OF ILLUSTRATIONS SCHEMATIC PINOUT 25 PIN DSUB OUTLINE DRAWING WIRING DIAGRAM MD41 1424 1434 14Volt MD41 1428 1438 1428 5V 1438 5V 28volt MD41 244 248 APPENDIX ENVIRONMENTAL QUALIFICATION FORM SECTION 1 GENERAL DESCRIPTION 1 1 INTRODUCTION The MD41 is a compact self contained GPS Annunciation and Control unit It combines all the necessary functions required to interface the Garmin GPS 155 165 approach certified GPS receiver with the MD41 244 248 remote mounted relay transfer system In addition the MD41 contains several GPS status annunciations used to indicate modes selected by the front panel switches and various inputs from the GPS receiver A special ILS override feature has been incorporated to cause the MD41 to automatically switch to the NAV mode when the NAV VOR receiver is tuned to an ILS frequency Other features include dual 20 000 hour lamps used for all annunciations internally lighted selection switches and automatic photocell dimming A external annunciation dimming adjustment is provided for balancing low level light conditions The MD41 142X 143X seri
4. Ne DEPT M TO NAV CIRCUIT BREAKER for fault monitoring 4 ALL WIRING SHALL BE 24 AWG UNLESS OTHERWISE ENGAGE provides gr ine In dpproger MOMENTARY SWITCH FOR TEST optional connectior SPARE OLT FOR MD41 1428 5V 1438 5V 14 VOLT FOR Lae TEST TET i MD41 1424 1434 AND 28 VOLT FOR MD41 1428 1438 SPARE EMI t 7 USE MD41 244 RELAY FOR 14 VOLT SYSTEMS dr APARE E MD41 248 FOR 28 VOLT SYSTEM 211 SPARE 8 POWER FOR ACU AND RELAY UNIT MUST BE TIED TO 3 SPAR zm AME CIRCUIT BREAKER 1AL EXTERNAL RELAY ENERGIZE MD41 244 248 24 POLE RELAY UNIT TOI note 7 2 BOTTOM 54 3 ANNUNCIATION INTERLOCK BI POWER GROUNI NOT ALL POLES ARE SHOWN ON TOI gt uis THIS DRAWING 3PS FLAG 3PS GPS TO4 GPS D BAR LEFT SPS D BAR RIGHT SPS 1 GI Gl E E FLAG FROM D BAR D BAR RIGHT ROTOR ROTOR H STATOR F STATOR G STATOR I STATOR E NAV FLAG NAV FLA NAV NAV TO NAV D BAR LEFT NAV D BAR RIGHT NAV NAV ROTOR NAV STATOR NAV STATOR NAV STATOR I NAV STATOR E LEFT ONVERTER TO MD41 A RELAY UNIT CIRCUIT BREAKEI not FIGURE 3 3 WIRING DIAGRAM MD41 1424 1434 1428 1438 1428 5V 1438 5V MD41 244 248 for GPS 155 165 Jan 2 1998 12 SECTION 4 POST INSTALLATION CHECKOUT 4 1 PRE INSTALLATION TESTS With the MD41 disconnected turn on the avionics master switch and verify tha
5. Midcontinent INSTRUMENTS AVIONICS 9 INSTALLATION MANUAL AND OPERATING INSTRUCTIONS MD4AI Series GPS ANNUNCIATION CONTROL UNIT FOR GARMIN GPS 155 165 MFG P N MD41 1428 28VDC Horizontal Mount MFG P N MD41 1424 14VDC Horizontal Mount MFG P N MD41 1438 28VDC Vert Mount shown on page 11 MFG P N MD41 1434 14VDC Vert Mount shown on page 11 Mid Continent Instruments and Avionics MANUAL NUMBER 7019805 9400 E 34 Street N Wichita KS 67226 USA REV 2 Jan 2 1998 Phone 316 630 0101 Fax 316 630 0723 MANUAL REVISION AND HISTORY MANUAL MD41 1424 1428 1434 1438 1428 5v 1438 5v REVISION 1 Oct 18 1997 MANUAL NUMBER 7019805 This revision level of this manual consist of the following changes Added AlliedSignal KI 208A 209A Navigation Indicators to be used with the MD41 142X 143X series ACU in place of the MD41 244 248 series Relay Units REVISION 2 Jan 2 1998 Removed KI 208A 209A from install manual due to incapability of OBS resolver REV 2 Jan 2 1998 SECTION 1 1 1 1 2 1 2 1 L2 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 3 2 3 3 3 4 SECTION 4 4 1 4 2 FIGURE NO 3 1 3 2 3 3 REV 2 Jan 2 1998 TABLE OF CONTENTS GENERAL DESCRIPTION INTRODUCTION SPECIFICATIONS TECHNICAL PHYSICAL CHARACTERISTICS ENVIRONMENTAL CHARACTERISTICS SPECIFICATIONS ELECTRICAL FRONT PANEL CONTROLS AND ANNUNCIATIONS CONTROLS
6. eries control units contain specific dash numbers to be used with various GPS receivers The installer must match the correct controller part number with the GPS receiver being installed The conditions and tests required for TSO approval of this article are mintmum 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 1424 1434 1428 1438 1428 5V 1438 5V ACU MUST be installed with the Mid Continent Instruments and Avionics MD41 244 248 remote transfer relay in order to be approved as a complete TSO system These items will not be TSO d if one is installed without the other The MD41 1424 1434 1428 1438 1428 5V 1438 5V is TSO D and certified for use with the Garmin GPS 155 165 system Any attempts to install the listed units in an installation other than the Garmin GPS 155 165 is prohibited This will void the TSO NOTE Anytime the MD41 is disconnected or removed from the aircraft the HSI CDI will default to NAV VOR mode 1 2 7 MAJOR COMPONENTS This system is comprised of two major components the MD41 142X 143X series GPS Annunciation Control Unit and the MD41 244 248 Remote Relay REV 2 Jan 2 1998
7. es annunciation control unit must be installed with the companion MD41 244 248 series Relay Unit 1 2 SPECIFICATIONS TECHNICAL 1 2 1 PHYSICAL CHARACTERISTICS Mounting Panel Width 3 25 Inches Height 80 Inches Depth 3 20 Inches Weight 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 REV 2 Jan 2 1998 1 2 3 SPECIFICATIONS ELECTRICAL Design All Solid State MD41 1424 1434 14VDC 0 40 Amps MD41 1428 1438 28VDC 0 30 Amps MD41 1428 5V 1438 5V 28DC 0 30 Amps 1 2 4 FRONT PANEL CONTROLS AND ANNUNCIATIONS 1 2 4 1 CONTROLS 1 242 ANNUNCIATIONS NAV GPS GPS APR GPS SEQ NAV GPS ARM ACTV HOLD AUTO MSG WPT 1 2 5 INTERFACE REV 2 Jan 2 1998 Alternate action switch when pressed will select NAV VOR GPS presentation on HSI CDI Alternate action switch when pressed will arm GPS Approach Mode Alternate action switch when pressed will select between AUTO and HOLD modes NAV VOR information presented on the HSI or CDI GPS information presented on the HSI or CDI GPS is armed for automatic transition to approach mode GPS is actively engaged in the approach mode This will activate the course selector and als
8. n cont Conditions Sand and Dust Fungus Salt Spray Magnetic Effect Power Input Voltage Spike Audio Frequency Susceptibilit Induced Signal Susceptibility Radio Frequency Susceptibility Radio Frequency Emissions Lightning Induced Transient Susceptibility Lightning Direct Effects REV 2 Jan 2 1998 Description of Conducted Tests aii oaee M cne BER ae Ril ronan sa E LN PW NN a gu Equipment tested to Category Z Equipment identified as Category X no tests required oer Equipment identified as Category X no tests required Equipment identified as Category X no test required 12 0 13 0 14 0 15 0 16 0 17 0 18 0 19 0 20 0 21 0 23 0 4 0 15
9. ns will cycle alternately when pressing the GPS SEQ button two times Press the GPS APR button and the ARM annunciation will illuminate ARM can be canceled by pressing the GPS APR button a second time or by ACTV input from the GPS receiver Please refer to Section 4 of the Garmin installation manual for the remaining system tests No periodic maintenance or calibration is necessary for continued airworthiness of the MD41 REV 2 Jan 2 1998 13 ENVIRONMENTAL QUALIFICATION FORM RTCA DO160C NOMENCLATURE MD4AI 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 7 3 ee ee 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 2 Jan 2 1998 14 Environmental Qualificatio
10. nstallation of cabling and before installation of the equipment insure 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 1424 14volt or MD41 1428 28 volt Horiz Mount MD41 1434 14volt or MD41 1438 28volt Vert Mount MD41 1428 5V 28volt 5 volt button lighting Horiz Mount MD41 1438 5V 28volt 5 volt button lighting Vert Mount 2 J1 Connector Kit 25 pin MCI PN 7014517 3 Installation Manual MCI PN 7019805 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 34 INSTALLATION LIMITATIONS Wire the aircraft harness according to figure 3 3 or 3 4 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 a
11. o disable the automatic GPS waypoint sequencing This will disable the course selector input to the GPS and will enable automatic GPS waypoint sequencing GPS message alert from the GPS receiver GPS waypoint alert from the GPS receiver NAV annunciation Receives ground from transfer relay Jl Pin2 when relays are in NAV mode GPS annunciation Receives ground from transfer relay 11 Pin 1 when relays are in GPS mode 1 2 5 INTERFACE cont REV 2 Jan 2 1998 Lamp Test Jl Pin 7 APR ARM Select 11 Pin 6 GPS SEQ select J1 Pin 10 GPS APR ACTV J1 Pin 8 MSG and WPT annunciation ILS Override JI Pin 15 FCS LOC ENGAGE 11 pin 11 Receives ground from remote test switch to light all annunciations optional connection Providesa logic low to the GPS receiver when approach arm is selected Provides a logic low to the GPS receiver when HOLD is selected Receives a logic low from the GPS receiver when a transition is made from arm to active A logic low will cause the appropriate annunciation to illuminate GPS receiver must be able to accept 100ma Receives a logic low from the NAV VOR receiver when tuned to an ILS frequency This will force the MD41 into NAV mode regardless of the NAV GPS selection This connection is optional Logic low when GPS is in ACTIVE mode Used to provide a ILS ground to the flight control system when the GPS is approach active 1 2 6 EQUIPMENT LIMITATIONS The MD41 s
12. t aircraft power is on pin 13 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 l NAV or GPS HOLD or AUTO 3 MSG and or WPT 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 Select NAV using the NAV GPS button The presentation on the HSI CDI will now be information from the VOR receiver Using a VOR test generator or equivalent VOR signal verify that the presentation and operation of the HSI CDI is correct This will include course resolver left right meter to from meter and nav warn flag Now select GPS on the MD41 and tune the VOR receiver to an ILS frequency The MD41 will be forced to NAV mode and ILS information will be displayed on the HSI CDI NOTE this feature will not work if ILS Energize J1 pin 14 was not connected at the time of installation Next verify that HOLD and AUTO annunciatio
13. way from aircraft controls and cables Normal installation techniques should be applied Also see equipment limitations section 1 2 6 REV 2 Jan 2 1998 9 Oe eeeeeeeveeeeecce 99 999 99999990 REAR VIEW OF J1 bottom CONNECTOR 11 GPS ANNUNCIATION receives ground from remote transfer relays 2 NAV ANNUNCIATION teceives ground from remote transfer relays 3 MSG ANNUNCIATION receives logic low from GPS receiver 4 SPARE 5 DIMMER IN from aircraft dimming bus 6 GPS APR ARM SELECT logic low sent to GPS T LAMP TEST receives ground from remote test switch optional conn 8 ACTV ANNUNCIATION receives logic low from GPS receiver Q WPT ANNUNCIATION receives logic low from GPS receiver 10 GPS SEQ HOLD LOW logic low to the GPS 1 FCS LOC ENGAGE provides ground when GPS is in active mode for autopilot 12 TO NAV CIRCUIT BREAKER for fault monitoring 13 14 or 28 VDC UNIT POWER depends on dash number 14 EXTERNAL RELAY ENERGIZE provides ground to energize remote transfer relays when GPS is selected 15
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