INSTALLATION MANUAL AND OPERATING INSTRUCTIONS
Contents
1. from the GPS receiver APR GPS is actively engaged in approach mode HOLD Automatic waypoint sequencing is disabled 1 2 5 INTERFACE NAV Ann Receives ground from transfer relay JI Pin 16 when relays are in NAV mode GPS Ann Receives ground from transfer relay JI Pin 2 when relays are in GPS mode Lamp Test Receives ground from remote test switch JI Pin7 to light all annunciations optional connection MSG Ann Receives ground to activate annunciation JI Pin3 REV 2 Aug 5 1999 5 1 2 5 INTERFACE cont REV 2 Aug 5 1999 WPT Ann JI Pin 4 APR Ann JI Pin 9 HOLD Ann JI Pin 10 ILS Override JI Pin 11 Receives ground to activate annunciation Receives a ground to activate annunciation Receives a ground to activate annunciation 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 1 2 6 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 co2. 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 162X 163X 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 2 75 Inches Height 80 Inches Depth 3 22 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 Aug 5 1999 1 2 3 SPECIFICATIONS ELECTRICAL Design All Solid State MD41 1624 1634 14VDC 0 40 Amps MD41 1628 1638 28VDC 0 30 Amps MDAL 1628 5V 1638 5V 28DC 0 30 Amps 1 2 4 FRONT PANEL CONTROLS AND ANNUNCIATIONS 1 2 4 1 CONTROLS NAV GPS Alternate action switch when pressed will select NAV VOR GPS presentation on HSI CDI 1 2 4 2 ANNUNCIATIONS NAV NAV VOR information presented on the HSI or CDI GPS GPS information presented on the HSI or CDI MSG GPS message alert from the GPS receiver WPT GPS waypoint alert
3. 6 ee REAR VIEW OF JI bottom CONNECTOR JI PIN NO TO NAV CIRCUIT BREAKER for fault monitoring 2 GPS ANNUNCIATION receives ground from remote transfer relays 3 MSG ANNUNCIATION receives ground from GPS receiver 4 WPT ANNUNCIATION receives ground from GPS receiver DIMMER IN from aircraft dimming bus 6 SPARE T LAMP TEST receives ground from remote test switch optional conn 8 SPARE 9 APR ANNUNCIATION receives ground from GPS receiver 10 HOLD ANNUNCIATION receives ground from GPS receiver 1 ILS ENERGIZE 12 SPARE 13 14 or 28 VDC UNIT POWER 14 SPARE 15 SPARE 16 NAV ANNUNCIATION receives ground from remote transfer relays 17 SPARE 18 SPARE 19 SPARE 20 SPARE 21 SPARE 22 SPARE 23 SPARE 24 EXTERNAL RELAY ENERGIZE ground to energize remote transfer
4. relays when GPS is selected 25 POWER GROUND FIGURE 3 1 SCHEMATIC PINOUT 25 PIN DSUB REV 2 Aug 5 1999 10 PDs H H Wa S p a MSG WPT II R NAV Nav HOLD NS A DA Gps CPS APR ce b W K l Ad A In i b N K ka ti aN M a Note 1 Use two 4 40 X 3 8 Flat Head Phillips Screws for Mounting FIGURE 3 2 OUTLINE DRAWING REV 2 Aug 5 1999 11 SIS b ie Dfa N FIGURE 3 3 WIRING DIAGRAM MD41 1624 1634 1628 1638 1628 5V 1638 5V for 2000APR 2101 2101 I O AN ASN 175 including PLUS versions GPS systems REV 2 Aug 5 1999 12 FIGURE 3 4 WIRING DIAGRAM MD41 1624 1634 1628 1638 1628 5V 1638 5V SERIES ACU WITH AlliedSignal KI 208A 209A COURSE DEVIATION INDICATOR FOR THE 2000APR 2101 2101 I O AN ASN 175 including PLUS versions GPS systems REV 2 Aug 5 1999 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 1 NAV or GPS 2 MSG and or WPT may be flashing depending on the status of th
5. ER TEST SPECIFICATION MPS 7015613 MANUFACTURER MID CONTINENT INSTRUMENT CO INC 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 Equipment tested per DO 160C Operational Par 7 2 1 Crash Safety Vibration Equipment tested without shockmounts to Categories M and N Table 8 1 1 7 4 Equipment identified as Categorv X no test required Equipment identified as Category X no test required Fluids Susceptibility Equipment identified as Category X no test required REV 2 Aug 5 1999 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 Susceptibility 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 Transien
6. MID CONTINENT INSTRUMENTS LI 9 INSTALLATION MANUAL AND OPERATING INSTRUCTIONS MDAI Series GPS ANNUNCIATION CONTROL UNIT FOR TRIMBLE 2000APR 2000APR PLUS 2101 2101 PLUS 2101 T O 2101 I O PLUS and AN ASN 175 MD41 1628 28vdc Horizontal Mount MDA l 1638 28vdc Vertical Mount shown on page 11 MD41 1624 14vde Horizontal Mount MD41 1634 14vde Vertical Mount shown on page 11 Ok INJAM Ap ay MID CONTINENT INST CO INC MANUAL NUMBER 8013567 9400 E 34 Street N Wichita KS 67226 USA REV 2 Aug 05 1999 Phone 316 630 0101 e Fax 316 630 0723 MANUAL REVISION AND HISTORY MANUAL MD41 1624 1634 1628 1638 1628 5v 1638 5v REVISION Oct 26 1997 Rev 1 MANUAL NUMBER 8013567 This revision level of this manual consist of the following changes Added AlliedSignal KI 208A 209A Navigation Indicators to be used with the MD41 162X 163X series ACU in place of the MD41 244 248 series Relay Units REVISION Aug 5 1999 Rev 2 This revision level of this manual consist of the following changes Added AN ASN 175 GPS system REV 2 Aug 5 1999 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 22 2 3 SECTION 3 3 1 3 2 3 3 3 4 SECTION 4 4 1 4 2 FIGURE NO 3 1 32 3 3 3 4 REV 2 Aug 5 1999 TABLE OF CONTENTS GENERAL DESCRIPTION INTRODUCTION SPECIFICATIONS TECHNICAL PHYSICAL CHARACTERISTICS ENVIRO
7. NMENTAL 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 POST INSTALLATION CHECKOUT PRE INSTALLATION TEST OPERATING INSTRUCTIONS LIST OF ILLUSTRATIONS SCHEMATIC PINOUT 25 PIN DSUB OUTLINE DRAWING WIRING DIAGRAM MD41 1624 1634 14volt MD41 1628 1638 1628 5V 1638 5V 28volt MD41 244 248 WIRING DIAGRAM MD41 162X 163X SERIES ACU AlliedSignal KI 208A 209A INDICATOR APPENDIX ENVIRONMENTAL QUALIFICATION FORM SECTION 1 GENERAL DESCRIPTION 1 1 INTRODUCTION The MD41 162X 163X is a compact self contained GPS Annunciation and Control unit It combines all the necessary functions required to interface the Trimble 2000APR 2101 2101 I O AN ASN 175 and later PLUS version 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
8. UIPMENT 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 209A the transfer relays are internal to the indicator 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 2 Aug 5 1999 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 insure that power is applied only to the pins specified in the interconnect diagram 3 2 UNPACKING AND INSPECTING EQUIPMENT When unpacking e
9. e GPS receiver Select test if installed with the remote test switch All annunciations should light Continue selecting test 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 CW rotation lowers the dimming level Select NAV using the NA V GPS button The presentation on the HSI CDI will now be information from the NAV 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 11 was not connected at the time of installation Please refer to Section 3 of the Trimble 2000APR 2101 2101 I O PLUS installation manual for the remaining system tests Refer to section 2 for AN ASN 175 No periodic maintenance or calibration is necessary for continued airworthiness of the MD41 REV 2 Aug 5 1999 14 ENVIRONMENTAL QUALIFICATION FORM RTCA DO160C NOMENCLATURE MD41 GPS ANNUNCIATION CONTROL UNIT MODEL NO MDAI TSO NO C129 CLASS AI MANUFACTUR
10. nditions 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 1624 1634 1628 1638 1628 5V 1638 5V ACU MUST be installed with the Mid Continent Inst 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 1624 1634 1628 1638 1628 5V 1638 5V is TSO D and certified for use with the Trimble 2000APR 2101 2101 I O AN ASN 175 and PLUS versions GPS system Any attempts to install the listed units in an installation other than the listed systems 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 162X 163X series GPS Annunciation Control Unit and the MD41 244 248 Remote Relay or the AlliedSignal KI 208A 209A course deviation indicator REV 2 Aug 5 1999 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 EQ
11. quipment make a visual inspection for evidence of damage incurred during shipment The following parts should be included 1 MD41 1624 14 volt or MD41 1628 28 volt Horiz Mount MD41 1634 14 volt or MD41 1638 28 volt Vert Mount MD41 1628 5V 28volt 5 volt button lighting Horz Mount MD41 1638 SV 28volt 5 volt button lighting Vert Mount 2 J1 Connector Kit 25 pin sockets MCI PN 7014517 3 Installation Manual MCI PN 8013567 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 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 Aug 5 1999 9 secececeeeeeeeeSe eee 6 6 6 6
12. t 2 Susceptibility Lightning Direct Effects 23 0 Icing 24 0 REV 2 Aug 5 1999 16
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