MD41-1928 Installation Manual - Mid
Contents
1. LAMP TEST receives ground from remote test switch optional conn 8 ACTV ANNUNCIATION receives logic low from GPS receiver Q WPT ANNUNCIATION receives logic low from GPS receiver 10 OBS HOLD logic low sent to the GPS receiver 1 SPARE 12 TO NAV CIRCUIT BREAKER for fault monitoring 13 14 or 28 VDC UNIT POWER depends on dash number 14 EXTERNAL RELAY ENERGIZE ground to energize remote transfer relays when GPS is selected 15 ILS ENERGIZE from NAV VOR receiver optional connection for ILS override 16 GPS DISPLAY ground to GPS receiver in NAV mode 17 SPARE 18 SPARE 19 SPARE 20 SPARE 2 SPARE 22 SPARE 23 OBS ANNUNCIATION receives logic low from GPS receiver 24 LEG ANNUNCIATION receives logic low from GPS receiver 25 POWER GROUND FIGURE 3 1 SCHEMATIC PINOUT 25 PIN DSUB REV 1 Oct 18 1997 10 i Fy F T n I IN j CONNECTO ny ERTI2. MidContinent INSTRUMENTS AVIONICS INSTALLATION MANUAL AND OPERATING INSTRUCTIONS MD41 Series GPS ANNUNCIATION CONTROL UNIT FOR ALLIED SIGNAL KLN 900 MD41 1924 14vdc Horizontal Mount MD41 1934 14vdc Vertical Mount shown on page 11 MD41 1928 28vdc Horizontal Mount MD41 1938 28vdc Vertical Mount shown on page 11 Mid Continent Instruments and Avionics Manual Number 8012528 9400 E 34 Street N Wichita KS 67226 USA REV 1 Oct 18 1997 Phone 316 630 0101 Fax 316 630 0723 MANUAL REVISION AND HISTORY MANUAL MD41 1924 1928 1934 1938 1928 5v 1938 5v REVISION Oct 18 1997 Rev 1 MANUAL NUMBER 8012528 This revision level of this manual consist of the following changes Added AlliedSignal KI 208A 209A Navigation Indicators to be used with the MD41 1900 series ACU in place of the MD41 244 248 series Relay Units Note The KLN 900 has a 360 deg resolver adjustment range REV 1 Oct 18 1997 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 NO 3 1 3 2 3 3 3 4 REV 1 Oct 18 1997 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
3. 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 1924 1934 14Volt MD41 1928 1938 1928 5V 1938 5V 28volt MD41 244 248 WIRING DIAGRAM MD41 1900 SERIES ACU AlliedSignal KI 208A 209A INDICATOR APPENDIX ENVIRONMENTAL QUALIFICATION FORM SECTION 1 GENERAL DESCRIPTION 1 1 INTRODUCTION The MD41 19XX is a compact self contained GPS Annunciation and Control unit It combines all the necessary functions required to interface the Allied Signal KLN 900 approach certified GPS receiver with the MD41 244 248 remote mounted relay transfer system In addition the MD41 19XX 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 annunciation dimming adjustment is provided for balancing low level light conditions The MD
4. BAR RIGHT RO T GPS ST CPS aT EET CDI FLAG FLAG FROM TO D BAR LEFT D BAR RIGHT ROTOF ROTOR H STATOR F TATOR G STATOR I STATOR E NAV CONVERTER NAV FLAC NAV FLAG NAV FROM NAV NAV D BAR LEFT NAV D BAR RIGHT4 NAV NAV ROTOR H NAV STATOR F NAV STATOR NAV STATOR D NAV STATOR E Pal x A 28VDC AIRCRAFT PWR TO MD41 ACU RELAY UNIT CIRCUIT BREAKEI p REV 1 Oct FIGURE 3 3 WIRING DIAGRAM MD41 1924 1934 1928 1938 1928 5V 1938 5V MD41 244 248 for KLN 900 18 1997 12 MD41 190 4 OR 28VI SPARE OBS AMN LEG ANN OURSE MODE PS APR ACT MSG ANN PT ANN APR ARM SELECT APR ARM ANN PS DISPLAYED SELECT ANN TO LIGHTING T MD41 AC for pushbuttor CI RELAY KLI NAV ANNUNCIATION gt ANNUNCIATION 2 e TO NAV SPARE PARE SPARE TE TEST gt SPARE JWER GNI ENERGIZE RE EXTERNAL RELAY ENERGIZE IT BREAKER for fault T 3 4 ALL POWER lighting not 5 IT BREAKER note NOTES IF SYSTEM IS TO NAV MODE ELECTED CLOSED POSITION WITH NA INSTALLATION MANUAL FOR SONNECT ONLY BE FORCED HEN ILS IS RELAYS IN NORMALL REFER TO BENDIX KING INSTALLATION IRING SHALL BE 24 A SELECTED ACTUAL OTHER NLESS ISE NOTED MOMENTARY SWITCH FOR TEST OLT FOR MD41 1928 5V 1938 5V 14 VOLT FOI MD41 1924 9 54 AND 3 VOLT FOR
5. MD41 1 9 3t FOR AC AND RELAY UNIT MUST BE TIED TO SUIT BREAKER optional conr SAME A 208A 209A 28 VOLT KI2 SL RELAY ACU POWER note 7 OLT A A 14 LT KIZ A A FIGURE 3 4 WIRING DIAGRAM MD41 1900 SERIES ACU WITH AlliedSignal KI 208A 209A COURSE DEVIATION INDICATOR REV 1 Oct 18 1997 13 FOR THE KLN 900 GPS SYSTEM 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 for 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 s OBS or LEG 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 control located on the bottom of the MD41 case CW rotation lowers the dimming level Select NAV using the NAV GPS button The
6. 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 15 was not connected at the time of installation Next verify that OBS and LEG annunciations will cycle alternately when pressing the OBS LEG 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 KLN 900 installation manual for the remaining system tests No periodic maintenance or calibration is necessary for continued airworthiness of the MDAI REV 1 Oct 18 1997 14 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 Equip
7. 41 1900 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 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 1 Oct 18 1997 1 2 3 SPECIFICATIONS ELECTRICAL Design All Solid State MD41 1924 1934 14VDC 0 40 Amps MD41 1928 1938 28VDC 0 30 Amps MD41 1928 5V 1938 5V 28DC 0 30 Amps 1 2 4 FRONT PANEL CONTROLS AND ANNUNCIATIONS 1 2 4 1 CONTROLS NAV GPS GPS APR OBS LEG 1 242 ANNUNCIATIONS NAV GPS ARM ACTV OBS LEG 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 Momentary switch when pressed will select between OBS and LEG modes NAV 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 active
8. CAL MOUNT HORIZONTAL MOUNT Note 1 Use two 4 40 X 3 8 Flat Head Phillips Screws for Mounting FIGURE 3 2 OUTLINE DRAWING REV 1 Oct 18 1997 1 5 14 or 28VDC TO LIGHTING BUS for pushbutton lighting note 6 4 OR 28VDC AIRCRAFT PWR TO MD4 ACU RELAY UNIT CIRCUIT BREAKER not SPARE o 5 ANN LEG ANN E MODE SELECT 9 GF APR ACTV ANN KLN MSG ANN PT ANN CONNECT ONLY IF SYSTEM IS TO BE FORCED TO NAV MODE ABR CABINA HEN ILS 15 SELECTEI PE DEBEN EI RELAYS IN NORMALLY CLOSED POSITION WITH NAV SELECTED NAV A REFER TO BENDIX KING INSTALLATION MANUAL FOR ACTUAL ANNUNCIATION AON 7 NAV CIRCUIT BREAKEI Paul momo 4 ALL WIRING SHALL BE 24 A NLESS OTHERWISE NOTED 2 ns MOMENTARY SWITCH FOR TEST optional connectior SPARE VOLT FOR MD41 1928 5V 1938 5V 14 VOLT FOF 3 LAMP TEST MD41 1924 1934 ANI LT FOR MD41 1928 1938 SPARE 7 USE MD41 244 RELAY FOR 14 VOLT SYSTEMS POWER GND ale E MD41 248 FOR 28 VOLT SYSTEMS ENERGIZE r POWER FOR ACU AND RELAY UNIT MUST BE TIED TO SAME 7 AR CIRCUIT BREAKER 4 EXTERNAL RELAY ENERG MD41 244 248 RELAY UNIT TOI note 7 BOTTOM T ANNUNCIATION INTERLOCK GROUNI KLN p GPS FLAG SPS FLAG PS FROM PS GPS D BAR LEFT GPS D
9. V is selected on the MD41 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 Receives a logic low to the GPS receiver to annunciate OBS mode Receives a logic low to the GPS receiver to annunciate LEG mode 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 1924 1934 1928 1938 1928 5V 1938 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 1924 1934 1928 1938 1928 5V 1938 5V is TSO D and certified for use with the A
10. er 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 1 Oct 18 1997 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 1924 14volt or MD41 1928 28 volt Horiz Mount MD41 1934 14volt or MD41 1938 28volt Vert Mount MD41 1928 5V 28volt 5 volt button lighting Horiz Mount MD41 1938 5V 28volt 5 volt button lighting Vert Mount 2 J1 Connector Kit 25 pin MCI PN 7014517 3 Installation Manual MCI PN 8012528 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 w
11. ill 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 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 1 Oct 18 1997 9 NNECTOR ececccc60660 0060 00 99 9 999 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 for push button lighting 6 GPS APR ARM SELECT logic low sent to GPS T
12. lliedSignal KLN 900 system Any attempts to install the listed units in an installation other than the AlliedSignal KLN 900 is prohibited This will void the TSO NOTE Anytime the MD41 ACU 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 1900 series GPS Annunciation Control Unit and the MD41 244 248 Remote Relay or the AlliedSignal KI 208A 209A course deviation indicator REV 1 Oct 18 1997 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 transf
13. ly engaged in the approach mode This will activate the course selector and also disable the automatic GPS waypoint sequencing to the next leg This will disable the course selector input to the GPS and will enable automatic GPS waypoint sequencing to the next leg of the pre planned route 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 Jl Pinl REV 1 Oct 18 1997 when relays are in GPS mode 1 2 5 INTERFACE cont Lamp Test Jl Pin 7 APR ARM Select 11 Pin 6 APR ARM 11 Pin 4 OBS LEG Select J1 Pin 10 GPS APR ACTV 11 Pin 8 MSG and WPT annunciation GPS DISPLAYED Jl pin 16 ILS Override JI Pin 15 OBS Annunciate J1 Pin 23 LEG Annunciate J1 Pin 24 REV 1 Oct 18 1997 Receives ground from remote test switch to light all annunciations optional connection 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 OBS 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 Provides a ground to the GPS receiver when NA
14. ment 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 e o 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 1 Oct 18 1997 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 Susceptibility Lightning Direct Effects 23 0 Icing 24 0 REV 1 Oct 18 1997 16
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