MD41-244 Installation Manual - Mid
Contents
1. 5 49 48 47 46 45 11 4 5 42 REAR VIEW OF J2 bottor FIGURE 3 2 MATING CONNECTOR LAYOUT REV B Mar 9 2011 12 BOARD 1 ASSEMBLY 8017642 TH uss rus erue FIGURE 3 3 SCHEMATIC DIAGRAM MD41 244 248 24 POLE RELAY UNIT REV B 9 2011 13 SECTION 4 POST INSTALLATION CHECKOUT 4 1 PRE INSTALLATION TESTS With the MD41 244 248 disconnected turn on the avionics master switch and verify that aircraft power is on 11 pin 33 Using an ohm meter verify 72 pin 50 is aircraft ground 42 OPERATING INSTRUCTIONS Turn off the avionics master switch and connect the mating connector to the MD41 244 248 Turn on the avionics master switch and verify the NAV GPS annunciators transfer correctly with the appropriate switch selection Select NAV using the NAV 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 244 248 and tune the VOR receiver to an ILS frequency The MD41 244 248 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 16 was not c2. MD41 244 248 APPENDIX ENVIRONMENTAL QUALIFICATION FORM SECTION 1 1 1 1 2 1 2 1 12 2 1 2 3 1 2 4 1 25 1 2 6 SECTION 2 24 2 2 23 2 4 SECTION 3 3 1 3 2 3 3 3 4 SECTION 4 4 1 4 2 FIGURE N0 B 3 2 3 3 REV B Mar 9 2011 SECTION 1 GENERAL DESCRIPTION 1 1 INTRODUCTION The MD41 244 248 is a bulkhead mounted remote transfer relay unit specifically designed for switching a CDI or HSI Indicator between two aircraft radio navigation systems The remote switching unit is designed to be used with the companion MD41 1XXX series Annunciation Control Unit ACU This pertains to GPS systems where the user desires to share a common CDI or HSI between an existing NAV system and a GPS system The 24 pole unit features eight relay pairs consisting of 3 poles per relay pair Each relay pair can be activated individually by either voltage or ground keying or as a group by ground keying Other design features include interlocking of transfer relays utilizing one pole per relay pair for failure monitoring This feature provides indication that all relays have power applied to their activating coils It does not monitor all relay contacts or coils A special ILS override that will automatically force the MD41 244 248 to switch to NAV mode when the NAV VOR receiver is tuned to an ILS frequency optional connection Also an adjustable dimming regulator is included to provide dimmed voltage to an external annunc
3. a MidContinent INSTRUMENTS AVIONICS INSTALLATION MANUAL AND OPERATING INSTRUCTIONS MD41 244 248 RELAY UNIT MD41 244 14vdc 24 Pole 14 volt operation MD41 248 28vdc 24 pole 28 volt operation Mid Continent Instruments and Avionics Manual Number 7019029 9400 E 34 Street N Wichita KS 67226 USA REV B Mar 9 2011 Phone 316 630 0101 Fax 316 630 0723 REVISION DETAIL Detail Revised DO160C section 5 0 environmental test data Test Category is now category Revise Sec 1 1 amp 1 2 4 to indicate relay and interlock failure monitoring by means of power being applied to activating coils Add section 2 4 Limitations to describe MOD 0 amp MOD 1 Revise Fig 3 3 to reflect MOD 1 schematic Date 08 22 97 03 09 11 ECO Rev 5566 B REV B Mar 9 2011 TABLE OF CONTENTS GENERAL DESCRIPTION INTRODUCTION SPECIFICATIONS TECHNICAL PHYSICAL CHARACTERISTICS ENVIRONMENTAL CHARACTERISTICS SPECIFICATIONS ELECTRICAL INTERFACE EOUIPMENT LIMITATIONS MAJOR COMPONENTS INSTALLATION CONSIDERATIONS COOLING EOUIPMENT LOCATION ROUTING OF CABLES LIMITATIONS INSTALLATION PROCEDURE GENERAL INFORMATION UNPACKING AND INSPECTING MOUNTING THE MD41 244 248 INSTALLATION LIMITATIONS POST INSTALLATION CHECKOUT PRE INSTALLATION TEST OPERATING INSTRUCTIONS LIST OF ILLUSTRATIONS OUTLINE DRAWING MOUNTING MATING CONNECTOR LAYOUT SCHEMATIC
4. arantee of individual relay contact for the interlock functionality This is only an indicator that relays have power applied to their activating coils Refer to Fig 3 3 for MOD 1 schematic diagram REV B Mar 9 2011 7 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 244 248 After installation of cabling and before installation of the eguipment insure that power is applied only to the pins specified in the interconnect diagram 32 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 244 14volt 24 pole MD41 248 28volt 24 pole J1 Connector Kit 50 pin sockets MCI PN 7014509 J2 Connector Kit 50 pin pins MCI PN 8012247 Vertical and horizontal mounting brackets MCI PN 7018658 2 required 5 Installation Manual MCI PN 7019129 Optional parts Mounting brackets for mount MCI PN 8012379 2 required 3 3 MOUNTING THE MD41 244 248 The MD41 244 248 is provided with mounting rails that will allow mounting on the side rear or with flat side down Locate a area large enough to facilitate mounting of unit with connector and back shell in place Insure area is clear of mechanical obstructions and is not impeding movement of any other aircra
5. ft systems Avoid mounting close to heater vents or other high heat sources Allow a clearance of at least 3 inches from front of unit for plug removal 34 INSTALLATION LIMITATIONS Wire the aircraft harness according to figure 3 3 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 Also see equipment limitations Section 1 2 5 REV B Mar 9 2011 8 at ERTICAL MOUNT FIGURE 3 1A OUTLINE DRAWING VERTICAL MOUNT REV B Mar 9 2011 II IC IC E FIGURE 3 15 OUTLINE DRAWING HORIZONTAL MOUNT REV B Mar 9 2011 10 NNNM mee i si EAR MOUNT FIGURE 3 16 OUTLINE DRAWING REAR MOUNT Mar 9 2011 ONNECTOR sockets 5 REAR VIEW OF 6 MATING CONNECTOR NNECTOR pin
6. iation 750ma max All transfer relays have gold plated contacts and are nitrogen filled for high reliability Two versions of the MD41 244 248 series relay units are available MD41 244 24 pole relay for 14 volt operation MD41 248 24 pole relay for 28 volt operation 1 2 SPECIFICATIONS TECHNICAL 1 2 1 PHYSICAL CHARACTERISTICS Mounting Bulkhead Width 2 86 Inches Height 1 52 Inches Depth 2 60 Inches Weight 0 75 lbs REV B Mar 9 2011 4 22 ENVIRONMENTAL CHARACTERISTICS TSO Compliance TSO C129 Applicable Documents 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 All Solid State 2 00 Amps Max 2 00 Amps Max 2 Amps DC Not to exceed 30 Volts Receives a logic low from the NA V VOR receiver when tuned to an ILS frequency This will force the MD41 244 248 into NAV mode regardless of the NAV GPS selection This connection is optional Provides an adjustable dim voltage to be used with a remote mounted annunciation unit 750 ma max Pins 16 and 17 will short together when all transfer relays are energized This can be be used to complete the GPS annunciation circuit to monitor that power has been applied to each relay coil 1 2 3 SPECIFICATIONS ELECTRICAL Design MD41 244 14VDC MD41 248 28VDC Relay contact cur
7. nt 22 EQUIPMENT LOCATION The MD41 244 248 18 provided with mounting rails that will allow mounting on side rear or flat side down Rails for end mount are an optional item Order p n 8011991 2 required Locate an area large enough to facilitate mounting of unit with connector and back shell in place Insure area is clear of mechanical obstructions and is not impeding movement of any other aircraft systems 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 which now provides more options for panel mounting 23 ROUTING OF CABLES Care must be taken not to bundle the MD41 244 248 logic and low level signal lines with any high energy sources Examples of these sources include 400 HZ AC Comm DME 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 24 LIMITATIONS The MOD 0 relay unit interlock functionality has the capability of monitoring 1 contact per relay to indicate power has been applied to the activating coil The MOD 1 relay unit interlock functionality has the capability of monitoring 1 contact per relay pair to indicate power has been applied to the pair of activating coils In either MOD 0 or MOD 1 there is no gu
8. nvironmental Qualification cont Section Description of Conducted Tests 0 0 0 0 0 Susceptibility Susceptibility Lightning Induced Transient 2 Equipment identified as Category X no tests required Susceptibility Lightning Direct Effects 23 0 Equipment identified as Category X no tests required 0 Equipment identified as Category test required 21 2 Mar 9 2011 16
9. onnected at the time of installation Select GPS using the NAV GPS button Operate the GPS receiver through a self test cycle to verify all meters are operating correctly on the HSI CDI Annunciation brightness if used at the minimum dimming level may be adjusted by rotation of the dimmer control located on the MD41 244 248 case CW rotation lowers the dimming level No periodic maintenance or calibration is necessary for continued Airworthiness of the MD41 244 248 REV B Mar 9 2011 14 ENVIRONMENTAL OUALIFICATION FORM RTCA DO160C NOMENCLATURE MD41 244 248 RELAY UNIT TSO C129 CLASS MODEL NO MD41 244 248 MANUFACTURER TEST SPECIFICATION MPS 7015613 MANUFACTURER Mid Continent Instruments and Avionics 9400 E 34 Street N Wichita K 67226 Phone 316 630 0101 Temperature and Altitude 4 0 Equipment tested to Categories A1 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 7 2 1 Crash Safety Vibration Equipment tested without shockmounts to Categories and N Table 8 1 El Equipment identified as Category X no test required Equipment identified as Category X no test required Fluids Susceptibility Eguipment identified as Category X no test reguired Mar 9 2011 15 E
10. rent rating 1 2 4 INTERFACE ILS Override JI Pin 16 Dimming Output J2 Pin 33 GPS annunciation interlock J2 Pins16 and 17 REV B Mar 9 2011 1 2 5 EQUIPMENT LIMITATIONS 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 244 248 relay unit MUST be installed with a TSO approved MDA1 1XXX series Annunciation Control Unit ACU in order to be approved as a complete TSO system These items will not be TSO d if one is installed without the other NOTE Anytime the MD41 244 248 relay transfer unit is disconnected or removed from the aircraft the HSI CDI will be inoperative in both NAV VOR and GPS 1 2 06 MAJOR COMPONENTS The system is comprised of two major components the MD41 244 248 relay unit and the MD4A1 1XXX series annunciation control unit REV B Mar 9 2011 6 SECTION 2 INSTALLATION CONSIDERATIONS 2 1 COOLING No direct cooling 18 required As with any electronic equipment overall reliability may be increased 11 the MD41 244 248 18 not located near any high heat source or crowded next to other equipme
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