INSTALLATION MANUAL AND OPERATING INSTRUCTIONS
Contents
1. MID CONTINENT INSTRUMENTS 4 LU INSTALLATION MANUAL AND OPERATING INSTRUCTIONS MD200 302 303 306 307 Series COURSE DEVIATION INDICATOR WW 2 MID CONTINENT INST CO INC MANUAL NUMBER 8017972 9400 E 34 Street N Wichita KS 67226 USA REV 3 Dec 15 2003 Phone 316 630 0101 e Fax 316 630 0723 Revisions Rev Date Description of Change ECO 1 8 11 00 Corrected typographical errors added section 4 2 Annunciator Dimming Adjustment 2 4 11 02 Added MD200 302 5V 303 5V 306 5V 307 5V indicators These units have 5 volt bezel lighting 3 12 15 03 Corrected 5 volt lighting connections to J1 REV 3 Dec 15 2003 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 SECTION4 4 1 4 2 FIGURE NO 3 1 3 2 3 3 3 4 3 5 REV 3 Dec 15 2003 TABLE OF CONTENTS GENERAL DESCRIPTION INTRODUCTION SPECIFICATIONS TECHNICAL PHYSICAL CHARACTERISTICS ENVIRONMENTAL CHARACTERISTICS SPECIFICATIONS ELECTRICAL FRONT PANEL CONTROLS CONTROLS ANNUNCIATIONS INTERFACE EQUIPMENT LIMITATIONS MAJOR COMPONENTS INSTALLATION CONSIDERATIONS COOLING EQUIPMENT LOCATION ROUTING OF CABLES INSTALLATION PROCEDURE GENERAL INFORMATION UNPACKING AND INSPECTING MOUNTING THE MD200 INSTALLATION LIMITATIONS POST INSTALLATION CHECKOUT PRE2. INSTALLATION TEST OPERATING INSTRUCTIONS LIST OF ILLUSTRATIONS MATING CONNECTORS CUTOUT DEMENSIONS FOR PANEL MOUNTING MD200 302 303 306 307 SERIES OUTLINE DRAWING MD200 306 307 SERIES WIRING DIAGRAM MD200 302 303 SERIES WIRING DIAGRAM APPENDIX ENVIRONMENTAL QUALIFICATION FORM SECTION 1 GENERAL DESCRIPTION 1 1 INTRODUCTION The Mid Continent Instruments MD200 302 303 306 307 Nav Indicator is designed to operate with VHF and GPS navigational equipment to provide OMNI VOR GPS LOCALIZER LOC and Glideslope GS information The MD200 302 303 is designed to accept DC Left Right To From and Nav warn flag signals from a remote mounted VOR converter Additionallv the MD200 306 307 will accept DC signals from a glideslope receiver which will drive the UP DOWN needle along with a GS warn meter Both units incorporate NAV GPS and BC annunciation with photocell dimming When GPS is selected for displav the MD200 receives inputs from compatible GPS navigation receivers or Flight Management Svstems to provide a visual presentation to the pilot All information presented on the navigation indicator is generated from this external receiver Course datum information is offered on the MD200 303 and 307 versions The course resolver is ORZ zero ed to industry standard 300 deg Five volt bezel lighting is offered with the MD200 302 5V 303 5V 306 5V 307 5V indicators 1 2 SPECIFICATIONS TECHNICAL 1 2 1 PHYSICAL CHA
3. ATION LIMITATIONS Wire the aircraft harness according to the appropriate figure Use at least 24 AWG wire for all connections You MUST use shielded wire where shown by the receiver manufacture Avoid sharp bends and routing cable near high energv sources Care must be taken to tie the harness away from aircraft controls and cables REV 3 Dec 15 2003 9 200000000000 00000000000e FIGURE 3 1 REAR VIEW OF MATING CONNECTORS Dag P P i L gt L i a FIGURE 3 2 CUTOUT DIMENSIONS FOR PANEL MOUNTING REV 3 Dec 15 2003 10 5 0 7 Annun Dim Adj JI 25 PIN D DSUB MALE pins ED AND CRIMP CONTACTS 01250 zy I 20 How FIGURE 3 3 OUTLINE DRAWING REV 3 Dec 15 2003 11 FROM F t LEFT RIGHT J2 9 PIN D SUB 8 I 2 ER GROUND LIGHTING GROUND VOLT DIMMER QA N gt NINININI NIN ir 3 VOLT FOR MD200 302 303 UT 2 3 A 5 RESOLVER 6 RESO 7 CDI FLAG 8 9 0 4 FIGURE 3 5 WIRING DIAGRAM MD200 306 307 REV 3 Dec 15 2003 SECTION A POST INSTALLATION CHECK 4 1 PRE INSTALLATION TESTS With the MD200 disconnected turn o
4. HE and transponder transmitter coax Alwavs use shielded wire when shown on the installation print Avoid sharp bends in cabling and routing near aircraft control cables REV 3 Dec 15 2003 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 MD200 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 MD200 Series course Deviation Indicator Connector Kit 9 pin MCI P N 8017287 303 307 only Connector Kit 25 pin MCI P N 7014517 Installation Manual MCI P N 8017972 PRE 3 3 MOUNTING THE MD200 JINDICATOR Plan a location in the aircraft for the MD200 course deviation indicator to be mounted as close to the pilot s field of view as possible 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 three 6 32 x 1 0 flat head phillips screws 34 INSTALL
5. RACTERISTICS MD200 302 303 306 307 Size 3 1 8 inch Round Mounting Panel Width 3 25 Inches Height 3 25 Inches Depth 4 75 Inches max Weight MD200 302 1 4 Ibs MD200 303 1 5 Ibs MD200 306 1 4 lbs MD200 307 1 5 Ibs REV 3 Dec 15 2003 4 1 2 2 ENVIRONMENTAL CHARACTERISTICS TSO Compliance TSO C34e C36e C40c Applicable Documents RTCA DO 160B DO 192 DO 195 DO 196 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 1 2 3 1 GENERAL DESIGN All Solid State OPERATING CURRENT MD200 302 0 30 Amps MD200 303 0 30 Amps MD200 306 0 30 Amps MD200 307 0 30 Amps 1 2 3 2 VOR LOC GPS OBS RESOLVER Electrical zero 300 degrees ORZ DEVIATION Input impedance 1K ohms 10 Deflection sensitivity 150mV 10 for full scale deflection VALID FLAG Input impedance 1K ohms 10 Flag sensitivity 125mV 10 for flag to leave stop 260mV 10 maximum flag fully concealed TO FROM FLAG 200 ohms 10 40mV 15 at 25 C flag fully in view COURSE DATUM MD200 303 307 Standard Arinc X Y Z 11 8 VRMS 030 Amp 400 Hz REV 3 Dec 15 2003 5 1 2 3 3 GLIDESLOPE MD200 306 307 only DEVIATION Input Impedance 1K ohms 10 Deflection sensitivity 150mV 10 for full scale deflection VALID FLAG Input Impedanc
6. e 1K ohms 10 Flag sensitivity 125mV 10 for flag to leave stop 260mV 10 maximum flag fully concealed 1 2 4 FRONT PANEL CONTROLS 1 2 4 1 CONTROLS OBS Used to select appropriate inbound or outbound bearing to a VOR station or waypoint 1 2 5 INTERFACE NAV LOC GPS Receives vertical lateral deviation warn flags TO FROM and OBS resolver information from the GPS NAV receiver GLIDESLOPE Receives GS up down and warn flag input from glideslope receiver REV 3 Dec 15 2003 6 1 2 6 EQUIPMENT LIMITATIONS N R REQUIRMENTS FOR TSO D VOR ILS SYSTEM The navigation receiver shall be certified to the standards of TSO C40a b c or TSO C36c d e VOR phase error shall not exceed 1 5 degrees Variation in VOR composite output not to exceed 43dB from 500VRMS as the RF input level of a standard VOR test signal to the receiver is varied from 10uV to 10 000uV Variation in the LOC composite output not to exceed 2dB from 333VRMS as the RF input level of a standard localizer test signal to the receiver is varied from 50uV to 10 000uV A control line ILS Energize must be provided as a low impedance to ground when an ILS frequency is selected REQUIRMENTS FOR TSO D GLIDESLOPE SYSTEM The glideslope receiver converter shall be certified to the standards of TSO C34c d e The centering error as presented to the pilot shall not exceed 13 of standard deflection with a 95 probability under all combinations of the servic
7. e conditions listed in RTCA paper DO 192 Deviation current with a 700uV standard glideslope deviation signal applied to the receiver input shall be 78uA 10 into a 1000 ohm load Deviation current shall not change more than 15 as the RF level of a standard glideslope deviation signal is varied from 100 to 10 000uA Deviation current shall be proportional within 5 to the difference in depth of modulation of the 90Hz and 150Hz tones Warning signal output shall be a DC current less than 125uA into a 1000 ohm load for a warning flag to be fully visible Warning signal for a fully concealed warning flag shall be a DC current of 260uA minimum into a 1000 ohm load 1 2 7 MAJOR COMPONENTS The system is comprised of one major component the MD200 Course Deviation Indicator REV 3 Dec 15 2003 7 SECTION 2 INSTALLATION CONSIDERATIONS 2 1 COOLING No direct cooling is required As with any electronic equipment overall reliabilitv may be increased if the MD200 is not located near anv high heat source or crowded next to other equipment 2 2 EQUIPMENT LOCATION The MD200 course deviation indicator must be mounted as close to the pilot s field of view as possible The unit depth with connector attached must also be taken into consideration 29 ROUTING OF CABLES Care must be taken not to bundle the MD200 logic and low level signal lines with anv high energy sources Examples of these sources include 400 HZ AC Comm DME
8. n the avionics master switch and verify that aircraft power on JI pin 19 is 14Vdc or pin 20 is 28Vdc Using an ohmmeter verify pin 21 is aircraft ground 4 2 ANNUNCIATOR DIMMING ADJUSTMENT Following installation of the MD200 CDI check the brightness of the GPS NAV and BC annunciations as necessary with the ambient and aircraft panel lighting levels set to simulate minimum light operations If required the dimming adjustment is located on the side of the MD200 unit and is labeled ANNUN DIM ADJ 4 3 OPERATING INSTRUCTIONS All controls required to operate the MD200 course deviation indicator are located on the unit s front panel and on the front panel of the related navigation receiver 4 3 1 VOR OPERATION Channel the NAV receiver to the desired VOR frequency and positively identify the station by listening to received audio Determine the NAV warning flag is out of view Flying inbound to a VOR station is accomplished by first rotating the OBS knob to center the deviation indicator and determining the TO FROM meter is in the TO condition The aircraft is then turned to a magnetic heading which is the same as the selected course with proper allowance for wind correction When the aircraft is on course the vertical pointer will be centered If the aircraft moves off course the deviation indicator will move away from the center position and flying in the direction of pointer deflection left or right is required to re i
9. ntercept the course The procedure for flying outbound from a VOR station is the same as flying inbound except the OBS knob is first rotated to cause a FROM indication to appear with the pointer centered To intercept a selected VOR radial from the station and fly outbound turn the OBS control to set the desired radial under the top indicator index Maneuver the aircraft to fly the selected radial magnetic heading plus 45 intercept angle which will provide a sufficient intercept angle The intercept angle should be reduced as the deviation needle approaches an on course condition center to prevent excessive course bracketing 4 3 2 LOCALIZER OPERATION REV 3 Dec 15 2003 13 Select the desired localizer frequency and observe that the localizer warning flag is concealed The TO FROM flag is not functional for localizer operation When flying on the front course or outbound on the back course make corrections toward the localizer vertical needle deflection The localizer path narrows as the approach end of the runwav becomes closer When flving inbound on the back course or outbound on the front course the corrections are made away from the direction of needle deflection A helpful hint when flying the localizer is to set the localizer heading on the OBS dial under the lubber line for quick reference 4 2 3 GLIDESLOPE OPERATION The glideslope horizontal needle provides the pilot with vertical steering information during ILS appr
10. oaches The glideslope circuitry is energized when the associated localizer frequency is selected on the navigation receiver Observe that the glideslope warning flag is concealed The glideslope needle deflects towards the direction the pilot must fly to remain on the glide path If the glideslope needle deflects upward the aircraft is below the glide path and the pilot must climb to again intercept the glide path and center the needle If the needle deflects downward the aircraft is above the glide path and the pilot must descend to again intercept the glide path and center the needle When the needle is centered the aircraft is on the glide path E A REV 3 Dec 15 2003 14 ENVIRONMENTAL QUALIFICATION FORM RTCA DO160B NOMENCLATURE MD200 COURSE DEVIATION INDICATOR MODEL NO MD200 TSO NO C34e C36e C40c MANUFACTURER TEST SPECIFICATION MPS 8014565 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 F2 except as noted Low Temperature 4 5 1 High Temperature 4 5 2 amp 4 5 3 Altitude 4 6 1 Decompression 4 6 2 Not Tested Overpressure 4 6 3 Not Tested Shock 7 0 Equipment tested per DO 160B Operational Crash Safety Vibration Equipment tested without shockmounts to Categories M and N Table 8 1 pm EE Equipment identified as Category X no test required Equipment identified as Category X no test
11. required Fluids Susceptibility Equipment identified as Category X no test required REV 3 Dec 15 2003 15 Environmental Qualification cont Sand and Dust Equipment identified as Categorv X no test required Equipment identified as Category X no test required Salt Spray Equipment identified as Category X no test required 1 1 1 1 Susceptibilit 19 2 Magnetic Effect RCE Equipment tested to Class A 2 3 A 5 6 7 8 0 Induced Signal Susceptibility BS Equipment tested to Categorv B Radio Frequencv Equipment tested to Categorv B Susceptibilitv Radio Frequencv Emissions Equipment tested to Categorv B Lightning Induced Transient 22 Equipment identified as Categorv X no test required Susceptibilit Lightning Direct Effects Equipment identified as Categorv X no test required Equipment identified as Categorv X no test required 0 0 0 0 0 0 0 0 0 0 REV 3 Dec 15 2003 16
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