MD41-1444 Installation Manual - Mid
Contents
1. 4 or 28VDC TO LIGHTING BUS for pushbutton lighting PARE 14 OR 28VDC AIRCRAFT PWR TO MD4 ACU RELAY UNIT CIRCUIT BREAKEI POWER GND ILS ENERGIZE note SPS SEQ SELECT SPS APR ACTV ANN NOTE MSG ANN GNC ABBAS SELEGT CONNECT ONLY IF SYSTEM IS TO BE FORCED TO NAV MODE CDS ABR ABM ANN HEN ILS IS SELECTEI SPARE 2 RELAYS IN NORMALLY CLOSED POSITION WITH NAV SELECTED NAV ANRUNGIATION 3 D 18 uL INSTALLATION MANUAL FOR ACTUAL GPS ANNUNCIATION ALBATIC TO NAV CIRCUIT BREAKER for fault monitoring 4 ALL WIRING SHALL BE 24 AWG UNLESS OTHERWISE NOTED S ENGAGE pravides Ground ii eapereac 5 MOMENTARY SWITCH FOR TEST optional connection SPARE 6 5 VOLT FOR MDA 448 5V 1458 5V 14 VOLT FOI LAMP TEST e NES MDA1 1444 1454 AND 28 VOLT FOR MD41 1448 145 SPARE i i 7 USE MD41 244 RELAY FOR 14 VOLT SYSTEMS SPARE JSE MD41 248 RELAY FOR 28 VOLT SYSTEMS SPARE 8 POWER FOR ACU AND RELAY UNIT MUST BE TIED TO SAME SPARE CIRCUIT BREAKEI EXTERNAL RELAY ENERGIZE MD41 244 18 24 POLE RELAY UNIT TOP note 7 BOTTOM Ld 3PS ANNUNCIATION INTERLOCK T GNC 300 GNC XL POWER GROUNI SPS 155XL NOTE THIS IS A 24 POLE RELAY PS FLAG 3 T AIE cC cuo PS FLAG NOT ALL POLES ARE SHOWN ON Quen T L3 PS FROM4 THIS DRAWING PS TO 2 PS D BAR L2. 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 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 Feb 24 1998 10 v 4 1 5 PIN DSUB CONNECTOR ERTICAL MOUNT HORIZONTAL MOUNT Note 1 Use two 4 40 X 3 8 Flat Head Phillips Screws for Mounting FIGURE 3 2 OUTLINE DRAWING REV 2 Feb 24 1998 11
3. annunciation dimming adjustment is provided for balancing low level light conditions The MD41 144X 145X series annunciation control unit must be installed with the companion MD41 244 248 series Relay Unit or the AlliedSignal KI 208A 209A course deviation indicator to be approved as a complete TSO d system 1 2 SPECIFICATIONS TECHNICAL 1 2 1 PHYSICAL CHARACTERISTICS Mounting Panel Width 3 25 Inches Height 0 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 Feb 24 1998 1 2 3 SPECIFICATIONS ELECTRICAL Design All Solid State MD41 1444 1454 14VDC 0 40 Amps MD41 1448 1458 28VDC 0 30 Amps MD41 1448 5V 1458 5V 28DC 0 30 Amps 1 2 4 FRONT PANEL CONTROLS AND ANNUNCIATIONS 1 2 4 1 CONTROLS NAV GPS GPS APR GPS SEQ 1 242 ANNUNCIATIONS NAV GPS ARM ACTV HOLD AUTO MSG WPT 1 2 5 INTERFACE Alternate action switch when pressed will select NAV VOR GPS presentation on HSI CDI Momentary 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 info
4. 15613 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 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 REV 2 Feb 24 1998 15 Environmental Qualification cont Conditions Section Description of Conducted Tests Sand and Dust Equipment identified as Category X no test required Equipment identified as Category X no test required Equipment identified as Category 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 Susc
5. EFT GPS D BAR FIGHT PS ROTOF 14 PS ROTOR H j PS STATOR F 7 PS STATOF 1 PS STATOR 55 PS STATOR E HSI CDI FLAG FLAG FROM TO D BAR LEFT D BAR RIGHT ROTOR STATOR F TATOR G STATOR D TATOR E NA ZONVERTER NAV FLAG NAV FLAG NAV FROM NAV TO NAV D BAR LEFT NAV D BAR RIGHT NAV ROTOF NAV ROTOR H NAV STATOR F NAV STATOF NAV STATOR NAV STATOR E PARE l 14 DC AIRCRAFT PWR TO MD41 A RELAY CIRCUIT BREAKER note 7 note 8 FIGURE 3 3 WIRING DIAGRAM MD41 1444 1454 1448 1458 1448 5V 1458 5V MD41 244 248 for the GPS 155XL GNC 300 and GNC 300XL GPS SYSTEMS REV 2 Feb 24 1998 12 4 or 28VDC TO LIGHTING BUS for pushbutton lightinc TO MD4 A RELAY UNIT IT BREAKER note 7 28VDC AIRCRAFT PWR Z POWER GNI T ILS ENERGIZE note GPS SEQ SELECT S jp 2 ACTV ANN NOTES CONNECT ONLY IF SYSTEM IS TO BE FORCED TO NA VODE APR ARM SELECT Bie Ape ARMA HEN ILS IS SELECTEI SPARE 2 RELAYS IN NORMALLY CLOSED POSITION WITH NAV SELECTED NA RNNUNTATIBR 5 REFER TO GARMIN INSTALLATION MANUAL FOR ACTUAL GPS ANNUNCIATION INSTALLATION TO NAV CIRCUIT BREAKER for fault monitoring 4 ALL WIRING SHALL BE 24 AWG UNLESS OTHERWISE NOTED ix ES ENGAGE SProyioes ground in eperedem MOMENTARY SWITCH FOR TEST optional connection S
6. MidContinent INSTRUMENTS AVIONICS 9 INSTALLATION MANUAL AND OPERATING INSTRUCTIONS MDAI Series GPS ANNUNCIATION CONTROL UNIT FOR GARMIN GPS 155XL GNC 300 GNC 300XL MFG P N MD41 1448 28VDC Horizontal Mount MFG P N MD41 1444 14VDC Horizontal Mount MFG P N MD41 1458 28VDC Vert Mount shown on page 11 MFG P N MD41 1454 14VDC Vert Mount shown on page 11 Mid Continent Instruments and Avionics Manual Number 7019813 9400 E 34 Street N Wichita KS 67226 USA REV 2 Feb 24 1998 Phone 316 630 0101 e Fax 316 630 0723 MANUAL REVISION AND HISTORY MANUAL MD41 1444 1448 1454 1458 1448 5v 1458 5v REVISION 1Oct 18 1997 MANUAL NUMBER 7019813 This revision level of this manual consist of the following changes Added AlliedSignal KI 208A 209A Navigation Indicators to be used with the MD41 144X 145X series ACU in place of the MD41 244 248 series Relay Units REVISION 2 Feb 24 1998 Added GPS 155XL and GNC 300XL GPS receivers REV 2 Feb 24 1998 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 3 2 3 3 3 4 SECTION 4 4 1 4 2 FIGURE N0 3 1 3 2 3 3 3 4 REV 2 Feb 24 1998 TABLE OF CONTENTS GENERAL DESCRIPTION INTRODUCTION SPECIFICATIONS TECHNICAL PHYSICAL CHARACTERISTICS ENVIRONMENTAL CHARACTERISTICS SPECIFICATIONS ELECTRICAL FRONT PANEL CONTROLS AND ANNUNCIATIONS C
7. ONTROLS 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 1444 1454 14Volt MD41 1448 1458 1448 5V 1458 5V 28volt MD41 244 248 WIRING DIAGRAM MD41 144X 145X SERIES ACU AlliedSignal KI 208A 209A INDICATOR 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 155XL GNC 300 and GNC 300XL approach certified GPS receivers 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
8. PARE 3 5 VOLT FOR MD41 1448 5V 1458 5V 14 VOLT FOR TEST P way i RE ETE I LAMP TEST gt jeu MD41 1444 1454 AND 28 VOLT FOR MD4 1 1448 145 SPARE yee Ss 7 POWER FOR ACU AND RELAY UNIT MUST BE TIED TO SAME SPARE d CIRCUIT BREAKEI 3PARE PARE EXTERNAL RELAY ENERGIZE A 209A 2 T KI 2 A 209A 55 REL El 7 LT 3A 209A 14 VOLT be FEL ER r OLT FIGURE 3 4 WIRING DIAGRAM md41 144X 1445X SERIES ACU WITH AlliedSignal KI 208A 209A COURSE DEVIATION INDICATOR FOR THE GPS 155XL GNC 300 and GNC 300XL GPS SYSTEMS REV 2 Feb 24 1998 13 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 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 contr
9. 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 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 1444 1454 1448 1458 1448 5V 1458 5V ACU MUST be installed with the Mid Continent Instruments and Avionics MD41 244 248 remote transfer relay or the AlliedSignal KI 208A 209A course deviation indicator 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 1444 1454 1448 1458 1448 5V 1458 5V is TSO D and certified for use with the Garmin GPS 155XL GNC 300 and GNC 300XL GPS systems Any attempts to install the listed units in an i
10. eptibility Lightning Direct Effects 23 0 Icing 24 0 REV 2 Feb 24 1998 16
11. nstallation 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 default to NAV VOR mode 1 2 7 MAJOR COMPONENTS This system is comprised of two major components the MD41 144X 145X series GPS Annunciation Control Unit and the MD41 244 248 Remote Relay or the AlliedSignal KI 208A 209A course deviation indicator REV 2 Feb 24 1998 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 For systems that utilize the AlliedSignal KI208A 2094 the transfer relays are internal to the indicator 23 ROUTING OF CABLES Care m
12. ol 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 annunciations 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 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 MDAI REV 2 Feb 24 1998 14 ENVIRONMENTAL QUALIFICATION FORM RTCA DO160C NOMENCLATURE MD4AI GPS ANNUNCIATION CONTROL UNIT MODEL NO MD41 TSO NO C129 CLASS Al MANUFACTURER TEST SPECIFICATION MPS 70
13. rmation 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 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 REV 2 Feb 24 1998 1 2 5 INTERFACE cont connection Lamp Test Jl Pin 7 APR ARM Select 11 Pin 6 APR ARM Jl Pin4 GPS SEQ select 11 Pin 10 GPS APR ACTV 11 Pin 8 MSG and WPT annunciation ILS Override JI Pin 15 FCS LOC ENGAGE Jl pin 11 REV 2 Feb 24 1998 Receives ground from remote test switch to light all annunciations optional Provides a momentary logic low to the GPS receiver when approach arm is selected Receives a logic low from the GPS receiver to annunciate ARM 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
14. s 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 away from aircraft controls and cables Normal installation techniques should be applied Also see equipment limitations section 1 2 6 REV 2 Feb 24 1998 9 NNECTOR ee ceo o o 6060009 ee eo 9 9 9 999999 REAR VIEW OF J1 bottom CONNECTOR 11 GPS ANNUNCIATION receives ground from remote transfer relays 2 NAV ANNUNCIATION receives ground from remote transfer relays 3 MSG ANNUNCIATION receives logic low from GPS receiver 4 ARM ANNUNCIATION receives logic low from GPS receiver 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
15. ust 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 Feb 24 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 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 1444 14volt or MD41 1448 28 volt Horiz Mount MD41 1454 14volt or MD41 1458 28volt Vert Mount MD41 1448 5V 28volt 5 volt button lighting Horiz Mount MD41 1458 5V 28volt 5 volt button lighting Vert Mount 2 J1 Connector Kit 25 pin MCI PN 7014517 3 Installation Manual MCI PN 7019813 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 vent
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