MD41-444 Installation Manual - Mid
Contents
1. CONN_6PIN Note 1 All relays shown in NAV position FIGURE 3 2 SCHEMATIC PINOUT 50 PIN DSUB 11 REV C Mar 5 2013 MD156 Front Mounting Plate Opti onal must be ordered from Mid Continent Inst Z ACTUAL SIZE Note 1 Use four 4 40 X 3 8 to 1 0 Flat Head Phillips Screws for Mounting MCI PN 7016165 supplied MD155 punch is available for hole cutout FIGURE 3 3 CUTOUT DIMENSIONS FOR PANEL MOUNTING REV C 5 2013 12 1 ENS HOLD MSG AUTO LAMP NAV ARM GPS ACTV NAV GPS GPS APR GPS TEST SEQ GARMIN REV C Mar 5 2013 FIGURE 3 4 OUTLINE DRAWING 13 MD41 DIM NC N NO7 NCE NO8 T ILS FI TO ROT E 244i NA NAV NA NC NO NC NO2 NC3 NO 4 NC4 NO4 5 54 H 4VDC FLAG FLAG D BAI b E DIM TO LIGHTING BUS for pushbutton lighting LO TO LIGHTING2. 7 2 NC7 RELA Y 3 SPARE 4 SPARE 5 C8 RELAY NC8 RELAY 7 NO8 RELAY 8 GPS APR ACTV ANNUNCIATION Q GPS SEQ HOLD LOW gnd to GPS 10 MSG ANNUNCIATION WPT ANNUNCIATION 12 14 VDC UNIT PWR 444 454 ONLY 13 28 VDC UNIT PWR 448 458 448 5V 458 5V ONLY 14 ILS FROM VOR REC for ILS override optional 15 C7 RELAY 16 APR ARM ANNUNCIATION 17 SPARE 18 C5 RELAY 19 NC5 RELAY 20 DIM LOW to lighting bus 2 DIM HIGH to lighting bus 22 NOS RELAY 23 TO NAV CIRCUIT BREAKER for fault monitoring 24 GPS ARM momentary logic low to GPS 25 POWER GROUND FIGURE 3 1 SCHEMATIC PINOUT 25 PIN DSUB REV C Mar 5 2013 10 gc
3. REV C Mar 5 2013 17 Environmental Qualification 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 C 5 2013 Description of Conducted Tests M acerca snn _ La m ee ae D R gu Equipment tested to Category Z Equipment identified as Category X no tests required Equipment identified Category X 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 18
4. 4 SECTION 4 4 1 4 2 FIGURE N0 3 1 2 2 3 3 3 4 3 5 3 6 REV C 5 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 ADDITIONAL ANNUNCIATIONS ADDITIONAL RELAYS 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 SCHEMATIC PINOUT 50 PIN DSUB CUTOUT DIMENSION FOR PANEL MOUNTING OUTLINE DRAWING WIRING DIAGRAM MD41 444 454 14V WIRING DIAGRAM MD41 448 458 448 5V 458 5V 28V APPENDIX ENVIRONMENTAL QUALIFICATION FORM SECTION 1 GENERAL DESCRIPTION 1 1 INTRODUCTION The MD41 is a self contained GPS Annunciation and Control unit It combines all the necessary functions required for switching HSI CDI data inputs between a conventional VOR receiver and the Garmin GPS 155XL GNC 300 and GNC 300XL approach certified GPS receivers 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 spe
5. B AIRCRAFT PWR TO MD4 ARCUIT BREAKER ER GND u NAV CIRCUIT BREAKER for fault monitorir GNC GNC XL FROM NAV RECEIVEI L ARM ANN 28 APPR ACTV ANN EQ HOLD 10 ANN ANN 2 APPR ARM LO FLAG FLAG t FROM TO D BAR LEFT D BAR RIGHT 41 4 7 4 H STATOR F 7 S TATOI 7 STATOR TATOR E S HSI CDI zt M LEFT RIGHT lt R dR H OR F OR G R D OR E ek d ANVERTEI FLAG FLAG FROM TO D BAR LEFT D BAR RIGHT ROTOR H STATOR F TATOR G STATOR I STATOR E NOTE CONNECT ONLY IF SYSTEM IS TO BE FORCED TO NAV MODE HEN ILS ELECTED RELAYS IN NORMALLY CLOSED POSITION WITH NAV SELECTEL REFER TO THE GARMIN INSTALLATION MANUAL FOR ACTUAL INSTALLATION 4 ALL RELAYS CONTROLLED BY THE NAV GPS SELECT ITCH ALL WIRING SHALL BE 24 A NLESS OTHERWISE NOTED E INTERLOCK ONLY IF EXTERNAL RELAYS ARE TO BE ADDEI MPER MUST BE OPENED INSIDE UNIT ON RELAY BOARI ANNUNCIATE INTERLOCK ANNUNCIATE INTERLOCK FIGURE 3 6 WIRING DIAGRAM MD41 444 454 GARMIN GPS 155XL GNC 300 GNC 300XL 14V REV C Mar 5 2013 14 DIM TO ROT ROT STAT STAT STAT NA NA NA NA NA NA NA NA NA NA NC N NCZ NO2 N N NC4 NO4 FIGURE 3 6 REV C Mar 5 2013 FROh LIGHTING 1 DIM Of DIM T
6. a logic low from the GPS receiver J1 Pin 16 to annunciate ARM GPS SEQ Select Provides a logic low to the GPS receiver JI Pin 9 when HOLD is selected GPS APR ACTV ANN Receives a logic low from the GPS receiver Jl Pin 8 ILS Override to annunciate ACTV Receives a logic low from the VOR receiver JI Pin 14 when tuned to an ILS frequency This will force the MD41 into NAV mode regardless of the NAV GPS selection This connection is optional MSG and WPT A logic low will cause the appropriate annunciation annunciation to illuminate GPS receiver must REV C Mar 5 2013 be able to accept 100ma 1 2 0 EQUIPMENT LIMITATIONS The MD41 series 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 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 444 448 454 458 448 5V 458 5V is TSO D and certified for use with the Garmin GPS 155XL GNC 300 and GNC 300XL systems Any attempts to i
7. this should occur you may use one spare relay pole to switch additional relays In cases where it may be more desirable to have all the relay switching done at a remote location i e remote mounted equipment one relay pole the MD41 may be used for switching this bank of relays Please note that the maximum relay contact rating for the MD41 is 2 amps DC 2 5 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 C Mar 5 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 444 14v or MD41 448 28v Horiz Mount MD41 454 14v or MD41 458 28v Vert Mount MD4A1 448 5V 28volt 5 volt button lighting Horiz Mount MD41 458 5V 28volt 5
8. 5 G Crash Safety 1 22 3 SPECIFICATIONS ELECTRICAL Design Solid State MD41 444 454 14VDC 0 65 Amps MD41 448 458 28VDC 0 40 Amps MD41 448 5V 458 5V 28VDC 0 40 Amps Relay contact current rating 2 Amps DC Available relay poles spdt 19 1 2 4 FRONT PANEL CONTROLS AND ANNUNCIATIONS 1 2 4 1 CONTROLS NAV GPS Alternate action switch when pressed will select VOR or GPS presentation on HSI CDI GPS APR Momentary switch when pressed will control GPS Approach Mode GPS SEQ Alternate action switch when pressed will select between AUTO and HOLD modes LAMP TEST Momentary switch for testing annunciation lamps Note Screwdriver adjustable control located on right side of case sets annunciation low dimming level REV C Mar 5 2013 1 2 4 2 ANNUNCIATIONS NAV GPS ARM ACTV HOLD AUTO MSG WPT 1 2 5 INTERFACE 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 also 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 GPS receiver GPS waypoint alert from GPS receiver APPR ARM Select Provides a momentary logic low to the J1 Pin 24 GPS receiver when approach arm is selected APPR ARM ANN Receives
9. J Midcontinent INSTRUMENTS AVIONICS INSTALLATION MANUAL AND OPERATING INSTRUCTIONS MD41 Series GPS ANNUNCIATION CONTROL UNIT FOR GARMIN GPS 155XL GNC 300 GNC 300XL MFG P N MD41 448 MFG P N MD41 444 MFG P N MD41 458 MFG P N MD41 454 28VDC 14VDC 28VDC 14VDC GARMIN P N 013 00029 10 GARMIN P N 013 00029 11 GARMIN P N 013 00029 15 GARMIN P N 013 00029 16 Mid Continent Instruments and Avionics 9400 E 34 Street N Wichita KS 67226 USA Phone 316 630 0101 e Fax 316 630 0173 Horizontal Mount Horizontal Mount Vert Mount shown on page 13 Vert Mount shown on page 13 Manual Number 7016181 REV C Mar 5 2013 MANUAL REVISION AND HISTORY MANUAL MD41 444 454 448 458 448 5v 458 5v REVISION Mar 13 1997 1 MANUAL NUMBER 7016181 This revision level of this manual consist of the following changes Revised DO160C section 4 0 environmental test data Test D1 is now F2 REVISION Feb 24 1998 Rev 2 This revision level of this manual consist of the following changes Added GPS 155XL and GNC 300XL GPS receivers REVISION MAR 5 2013 REV C Updated relay board schematic diagram on page 11 Relay board updated due to End of Life of 4 pol relays 4 pol relays changed for dual 2 pol relays REV C Mar 5 2013 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 22 2 3 2 4 2 5 SECTION 3 3 1 3 2 3 3 3
10. O for pushbutton lighti LO TO LIGHTING B DC AIRCRAFT PWR TO MD41 CIRCUIT BREAKEI ER GND CIRCUIT BREAKEI fault monitoring NC300XL FROM NAV RECEIVER NOTE GI XL S ARM ANN PPR ACTV ANN SEQ HOLD L ANN ANN APPR ARM LO S FLAG FLAG I FROM 4 5 TO gt D BAR LEFT D BAR RIGHT 5 j ROTOR H STATOR F 7 STATO STATOR E Ji S HSI CDI LEFT RIGHT 3 R H GRE I OR E Y ae 5 NVERTER FLAG FLAG FROM D BAR LEFT D BAF RIGHT ROTOI l ROTOR H STATOR F l STATOI STATOR D l STATOR E NOTES 1 CONNECT ONLY IF SYSTEM IS TO BE FORCED TO NAV MODE ILS 15 SELECTEI RELAYS IN NORMALLY CLOSED POSITION WITH SELECTEI REFER TO THE GARMIN INSTALLATION MANUAL FOR ACTUAL INSTALLATION 4 ALL RELAYS ARE CONTROLLED BY THE NAV GPS SELECT SWITCH ALL WIRING SHALL BE 24 AWG UNLESS OTHERWISE NOTEI MD41 448 458 WILL HAVE 28V PUSHBUTTON LIGHTING MD41 44 4 ILL HAVE 5V PUSHBUTTON LIGHTING 7 USE INTERLOCK ONLY IF EXTERNAL RELAYS ARE TO ADDEI INTER 7 MPER MUST BE OPENED INSIDE UNIT ON RELAY BOARD ANNUNCIATE INTERLOC WIRING DIAGRAM MD41 448 458 GARMIN GPS 155XL GNC 300 GNC 300XL 28V 15 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 12 for 14VDC systems and pin 13 for 28VDC sy
11. cial ILS override feature has been incorporated to cause the MD41 to automatically switch to the NAV mode when the VOR receiver is tuned to an ILS frequency Other features include dual 16 000 hour lamps used for all annunciations internally lighted selection switches automatic photocell dimming and built in annunciation self test A external annunciation dimming adjustment is provided for balancing low level light conditions A 19 pole relay assembly is included within the MD41 to simplify installation of the switching between VOR GPS and the associated HSI CDI relays have gold plated contacts and are nitrogen filled for high reliability Two versions are available that will allow the lighted selection buttons to operate from a 5 volt instrument dimming bus These part numbers are as follows MD41 448 5V and MD41 458 5V A MD156 adapter plate is available for front mount installations Also MD155 punch is available for instrument hole cutout 1 2 SPECIFICATIONS TECHNICAL 1 2 1 PHYSICAL CHARACTERISTICS Mounting Panel Width 3 50 Inches Height 1 350 Inches Depth 4 625 Inches Weight 0 75 lbs REV C Mar 5 2013 4 1 2 2 ENVIRONMENTAL CHARACTERISTICS TSO Compliance TSO C129 Applicable Documents RTCA DO 160C DO 208 Operating Temperature Range 55 C to 70 Humidity 95 Non Condensing Altitude Range 0 to 55 000 ft Vibration Cat M and N Operational Shock Rigid Mounting 6 G Operational 1
12. nstall the MD4A1 444 448 454 458 448 5 V A458 5V in a installation other than the listed GPS receivers is prohibited This will void the TSO NOTE Anytime the MD41 is disconnected or removed from the aircraft the HSI CDI will be inoperative in both VOR and GPS 1 2 7 MAJOR COMPONENTS The system is comprised of one major component the MD41 GPS Annunciation Control Unit REV C Mar 5 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 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 A MD 156 adapter plate is available for front mounting 253 ADDITIONAL ANNUNCIATIONS Depending upon the installation and approving agency you may be required to provide additional NA V Source Select external annunciators near the HSI CDI Spare relay contacts on the MD41 11 or J2 connector may be used for this purpose 24 ADDITIONAL RELAYS The MD41 contains 19 relay poles Some installations may require more than 19 poles due to data lines super flags etc If
13. 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 GPS APR test will not work without a valid GPS signal Please refer to Section 4 of the Garmin GPS 155XL GNC 300 and GNC 300XL installation manual for the remaining system tests No periodic maintenance or calibration is necessary for continued airworthiness of the MD41 REV C Mar 5 2013 16 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 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 7 2 1 Crash Safety Vibration Equipment tested without shockmounts to Categories M and N Table 8 1 7 3 pU 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
14. stems 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 NAV or GPS 2 HOLD or AUTO 3 MSG and or WPT may be flashing depending on the status of the GPS receiver Press the lamp test button all annunciations should light Continue pressing the lamp test button and cover the photocell window located on the left side of the front panel AII annunciations should dim Annunciation brightness at the minimum dimming level may be adjusted by rotation of the dimmer control located on the right side of the 41 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 71 pin 14 was not connected at the time of installation Next verify that HOLD and AUTO annunciations will cycle alternately when
15. volt button lighting Vert Mount J1 Connector Kit 25 pin MCI PN 7014517 J2 Connector Kit 50 pin MCI PN 7014509 Installation Manual MCI PN 7016181 4 40 x 1 0 Mounting Screws 4ea MCI PN 7016165 Ge 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 3 Secure the indicator in place with four 4 40 x 3 8 to 1 0 flat head phillips screws A MD156 adapter plate is available for front mount installations Also a MD155 punch is available for hole cutout 34 INSTALLATION LIMITATIONS Wire the aircraft harness according to figure 3 5 or 3 6 Use at least 24 AWG wire for all connections You MUST use shielded wire where shown 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 REV C Mar 5 2013 9 REAR VIEW 11 bottom CONNECTOR PIN 1
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