INSTALLATION MANUAL AND OPERATING INSTRUCTIONS MD41
Contents
1. note 2 ANNUNCIATOR DIMMING IN 135 TEST note 3 14V PANEL LIGHTING BUS HI PANEL LIGHTING BUS LO TERRAIN NOT AVAILABLE ANNUNCIATE IN 4 9 TERRAIN WARNING ANNUNCIATE IN 4 10 note 2 INTERNAL DIMMING PROGRAM 2 14V AIRCRAFT POWER TO MD41 ACU CIRCUIT BREAKER SPARE ER SPARE SPARE SPARE SPARE TAWS ANNUNCIATE INHIBIT IN 12 TAWS INHIBIT OUT 1 POWER GROUND AIRCRAFT GROUND 17 AIRCRAFT GROUND 18 AIRCRAFT GROUND h AIRCRAFT GROUND 34 29 AIRCRAFT GROUND 21 NOTES 1 JUMPER 3 TO 1 FOR FULL BRIGHT TERRAIN WARNING JUMPER 3 TO 4 FOR TERRAIN WARNING BRIGHTNESS TO BE CONTROLLED BY INTERNAL PHOTOCELL 2 JUMPER 7 TO 12 FOR ANNUNCIATION BRIGHTNESS TO BE CONTROLLED BY INTERNAL PHOTOCELL OTHERWISE CONNECT PIN 7 TO AIRCRAFT BRIGHT DIM SWITCH 3 MOMENTARY SWITCH FOR ANNUNCIATION LAMP TEST optional connection 4 REFER TO GARMIN INSTALLATION MANUAL FOR ACTUAL INSTALLATION DESIGNATES AN ACTIVE LOW SIGNAL 5 REFER TO ACU SCHEMATIC IN THIS MANUAL FOR DETAILED CIRCUIT FIGURE 3 3 WIRING DIAGRAM MD41 1024 1034 REV C October 28 2013 Manual Number 9015308 13 of 18 Mid Continent Instruments and Avionics Wichita KS MD41 1028 ANNUNCIATION CONTROL GNS 530 J1 28 VOLT P5050 note 1 ANNUNCIATOR FULL BRIGHT 1 ANNUNGIATOR FULL BRIGHT 2 TERRAIN WARNING2. MidContinent INSTRUMENTS AVIONICS INSTALLATION MANUAL AND OPERATING I NSTRUCTIONS MD41 1000 SERI ES TERRAIN AWARENESS ANNUNCI ATION CONTROL UNIT FOR GARMI N TAWS SYSTEMS MD41 1028 28vdc Horizontal Mount MD41 1038 28vdc X Vertical Mount shown on page 12 MD41 1028 5V 28vdc Horizontal Mount MD41 1038 5V 28vdc X Vertical Mount shown on page 12 MD41 1024 1l4vdc Horizontal Mount MD41 1034 14vdc Vertical Mount shown on page 12 GARMIN TE p PUN _ TE TERR Mar INHB INHB N Mid Continent I nstruments and Avionics Manual Number 9015308 9400 E 34 Street N Wichita KS 67226 USA REV C October 28 2013 Phone 316 630 0101 Fax 316 630 0723 Mid Continent Instruments and Avionics Wichita KS FOREWORD This manual provides information intended for use by persons who in accordance with current regulatory requirements are qualified to install or repair this equipment If further information is required please contact Mid Continent Instruments and Avionics Attn Customer Service Dept 9400 34 ST North Wichita KS 67226 USA Phone 316 630 0101 Fax 316 630 0723 We welcome your comments concerning this manual Although every effort has been made to keep it free of errors some may occur When reporting a specific problem please describe it briefly and include the manual part number the paragraph figure table number and the page number Send your comments to Mid Continent Instrument
3. Red close proximity to the terrain The aircraft is in imminent danger and actions should be taken to rectify the situation TERR The TAWS system has been placed in the Inhibit mode INHB White 1 2 5 EQUIPMENT LIMITATIONS The MD41 1000 series control units contain specific dash numbers to be used with various Terrain Awareness Warning Systems The installer must match the correct controller part number with the system that is being installed The MD41 1028 1028 5V 1038 1038 5V 1024 1034 is TSO D and certified for use with the Garmin International GNS 500 500A 530 530A Terrain Awareness Warning System TAWS Any attempt to install the listed units in an installation other than above system is prohibited This will void the TSO NOTE f the MD41 is disconnected or removed from the aircraft there will be no effect in the operation of the TAWS system REV C October 28 2013 Manual Number 9015308 8 of 18 Mid Continent Instruments and Avionics Wichita KS 1 2 7 MAJOR COMPONENTS This system is comprised of one major component the MD41 1000 series TAWS Annunciation Control Unit SECTION 2 INSTALLATION CONSI DERATI ONS 2 1 COOLING No direct cooling is required As with any electronic equipment overall reliability may be increased if the MD41 1024 1034 1028 1038 is not located near any high heat source or crowded next to other equipment Means of providing a gentle airflow will be a plus 2 2 EQUIPMEN
4. CONTI NUED AI RWORTHI NESS 5 1 INTRODUCTION 5 2 CONTROL OPERATION INFORMATION 5 3 MAINTENANCE INSTRUCTIONS 5 4 TROUBLESHOOTING INFORMATION 5 5 REMOVAL AND REPLACEMENT INFORMATION 5 6 DIAGRAMS 5 7 SPECIAL INSPECTION REQUIRMENTS 5 8 SPECIAL TOOLS 5 9 OVERHAUL PERIOD REV C October 28 2013 Manual Number 9015308 4 of 18 Mid Continent Instruments and Avionics Wichita KS FIGURE LIST OF ILLUSTRATIONS 3 1 SCHEMATIC PINOUT 25 PIN DSUB 3 2 OUTLINE DRAWING 3 3 WIRING DIAGRAM MD41 1024 1034 3 4 WIRING DIAGRAM MD41 1024 1034 1028 1038 1028 5v 1038 5V APPENDIX ENVIRONMENTAL QUALIFICATION FORM REV C October 28 2013 Manual Number 9015308 5 of 18 Mid Continent Instruments and Avionics Wichita KS SECTION 1 GENERAL DESCRI PTI ON 1 1 INTRODUCTION The MD41 1024 1034 1028 1038 is a compact self contained Annunciation and Control unit The fully integrated control unit provides annunciation and mode selection for TAWS Terrain Awareness Warning System It combines all the necessary functions required to interface a wide range of TAWS systems for FAA approval Other features include dual 20 000 hour lamps used for all annunciations internally lighted selection switches and choice of manual or automatic photocell dimming An external annunciation dimming adjustment is provided for balancing low level light conditions 1 2 SPECIFICATIONS TECHNICAL Mid Continent Instruments Co Inc certifies that th
5. 40 10 011 00940 11 011 00940 31 GNS 530A 011 00864 00 011 00864 01 011 00864 10 011 00864 11 Model GTN 6XX 7XX Series Part Numbers GTN 6XX 011 02254 00 011 02255 00 011 02256 00 011 02256 50 GTN 7XX 011 02281 00 011 02282 00 011 02282 50 REV C October 28 2013 1 2 1 PHYSICAL CHARACTERISTICS Mounting Width Height Depth Weight 1 2 2 ENVIRONMENTAL CHARACTERISTICS TSO Compliance Applicable Documents Operating Temperature Range Humidity Altitude Range Operational Shock Panel 2 75 Inches 0 80 Inches 3 22 Inches 0 50 Ibs TSO 151 RTCA DO 160D 55 C to 70 C 95 Non Condensing 0 to 55 000 ft Rigid Mounting 6 G Operational 20 G Crash Safety Manual Number 9015308 7 of 18 Mid Continent Instruments and Avionics Wichita KS 1 2 3 SPECIFICATIONS ELECTRICAL Design All Solid State MD41 1024 1034 0 30 Amps MD41 1028 1038 0 40 Amps MD41 1028 5V 1038 5V 0 42 Amps 1 2 4 FRONT PANEL CONTROLS AND ANNUNCIATIONS 1 2 4 1 CONTROLS TERR INHB Momentary switch when pressed will toggle the Inhibit mode When active the Inhibit mode will inhibit certain TAWS alerts 1 2 4 2 ANNUNCIATIONS TERR NA Terrain information is not available Amber TERR The current flight trajectory brings the aircraft in close Amber proximity to the terrain Extreme caution should be exercised PULL UP The current flight trajectory brings the aircraft in extremely
6. 8volt 5 volt button lighting Vert Mount 2 J1 Connector Kit 25 pin MCI P N 7014517 3 Installation Manual MCI P N 9015308 3 3 MOUNTING THE 041 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 drive 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 Also see equipment limitations section 1 2 5 The TSO identifies the minimum performance standards tests and other conditions applicable for issuance of design and production approval of the article The TSO does not specifically identify acceptable conditions for installations of the article The TSO applicant is responsible for documenting all limitations and conditions suitable for installation of the article An applicant requesting approval for installation of the article within a specific type or class of product is responsible for determining environmental and functional compatibility This Annunciation Control Unit is part of an incomplete system The intend
7. BRT DIM INTERNAL DIMMING PROGRAM 1 TERRAIN CAUTION ANNUNCIATE IN TERRAIN TEST IN ANNUNCIATOR DIMMING IN TEST note 3 28V PANEL LIGHTING BUS HI PANEL LIGHTING BUS LO TERRAIN NOT AVAILABLE ANNUNCIATE IN E TERRAIN WARNING ANNUNCIATE IN 34 10 INTERNAL DIMMING PROGRAM 2 28V AIRCRAFT POWER TO MD41 ACU CIRCUIT BREAKER SPARE 2A SPARE SPARE SPARE SPARE TAWS ANNUNCIATE INHIBIT IN 12 TAWS INHIBIT OUT 1 POWER GROUND AIRCRAFT GROUND 4 17 note 1 note 1 note 2 note 4 note 2 AIRCRAFT GROUND 18 AIRCRAFT GROUND 19 AIRCRAFT GROUND 2 AIRCRAFT GROUND 121 NOTES 1 JUMPER 3 TO 1 FOR FULL BRIGHT TERRAIN WARNING JUMPER 3 TO 4 FOR TERRAIN WARNING BRIGHTNESS TO BE CONTROLLED BY INTERNAL PHOTOCELL 2 JUMPER 7 TO 12 FOR ANNUNCIATION BRIGHTNESS TO BE CONTROLLED BY INTERNAL PHOTOCELL OTHERWISE CONNECT PIN 7 TO AIRCRAFT BRIGHT DIM SWITCH 3 MOMENTARY SWITCH FOR ANNUNCIATION LAMP TEST optional connection 4 5 VOLT FOR MD41 1028 5V 1038 5V 5 REFER TO GARMIN INSTALLATION MANUAL FOR ACTUAL INSTALLATION DESIGNATES AN ACTIVE LOW SIGNAL 6 REFER TO ACU SCHEMATIC IN THIS MANUAL FOR DETAILED CIRCUIT FIGURE 3 4 WIRING DIAGRAM MD41 1028 1038 1028 5V 1038 5V REV C October 28 2013 Manual Number 9015308 14 of 18 Mid Continent Instruments and Avionics Wichita KS SECTION 4 POS
8. T 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 21 is aircraft ground 4 2 OPERATING INSTRUCTIONS Refer to the TAWS pilots guide or installation manual for final testing of the MD41 REV C October 28 2013 Manual Number 9015308 15 of 18 Mid Continent Instruments and Avionics Wichita KS SECTION 5 INSTRUCTIONS FOR CONTINUED Al RWORTHI NESS 5 1 INTRODUCTION This document identifies the instructions for Continued Airworthiness for the MD1000 series TAWS Annunciation Control Unit 5 2 CONTROL OPERATION INFORMATION Refer to the Garmin International GNS 530 Pilots Guide and section 1 2 4 of this manual 5 3 MAINTENANCE INSTRUCTIONS Repair of the MD41 1000 ACU is on condition only periodic maintenance is not required Calibration and inspection intervals are not required Service life will be a minimum of 20 000 hours 5 4 TROUBLESHOOTING INFORMATION Refer to the MD41 1000 series Maintenance Manual 5 5 REMOVAL AND REPLACEMENT INFORMATION If the unit is removed and reinstalled a functional check of the equipment should be conducted in accordance with the Garmin International GNS 530 preflight test procedure 5 6 DIAGRAMS Refer to figure 3 2 3 3 and 3 4 of this manual 5 7 SPECIAL INSPECTION REQUIRMENTS N A 5 8 SPECIAL TOOLS None 5 9 OVERHAUL PERIOD No overha
9. T LOCATION The MD41 1028 must be mounted as close to the pilot s field of view as possible Please reference the TAWS installation manual for approved locations The unit depth with connector attached must also be taken into consideration 2 3 ROUTING OF CABLES Care must be taken not to bundle the MD41 1024 1034 1028 1038 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 C October 28 2013 Manual Number 9015308 9 of 18 Mid Continent Instruments and Avionics Wichita KS 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 1024 1034 1028 1038 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 1024 14V or MD41 1028 28V Horiz Mount MD41 1034 14V or MD41 1038 28V Vert Mount MD41 1028 5V 28volt 5 volt button lighting Horiz Mount MD41 1038 5V 2
10. d as Category X no tests required Equipment identified as Category X no test required REV C October 28 2013 Manual Number 9015308 18 of 18
11. e model MD41 series Annunciation Control Unit has been tested to and meets or exceeds the functional and environmental requirements of the following FAA Technical Standard Order TSO e 50 151 TERRAIN AWARENESS AND WARNING SYSTEM We also certify we meet the requirements of Part 21 Subpart 0 of the Code of Federal Regulations The MD41 series Annunciation Control Unit conforms to all pertinent documented design and internal manufacturing standards This includes but is not limited to component drawings specifications testing criteria inspection requirements quality processes manufacturing instructions and handling procedures It shall be manufactured in accordance with Mid Continent Instruments FAA approved Production Approval Holder Quality System Manual Revision M dated April 14 2011 or later The MD41 10XX series complies with the manufacturers specifications and has been verified and approved for use with the following systems Mid Continent I nstruments and Avionics Designed for use with Model Number s TAWS System MD41 1028 Manufacturer Garmin International MD41 1028 5V MD41 1038 Model GXX500 Series MD41 1038 5V Part Numbers MD41 1024 MD41 1034 GPS 500 011 00863 00 011 00863 01 011 00863 10 011 00863 11 REV C October 28 2013 Manual Number 9015308 6 of 18 Mid Continent Instruments and Avionics Wichita KS GNS 530 011 00940 00 011 00940 01 011 009
12. ed function is to provide required or optional annunciation and mode selection for Class B TAWS systems REV C October 28 2013 Manual Number 9015308 10 of 18 Mid Continent Instruments and Avionics Wichita KS Rear View of J1 Mating Connector PIN PIN NAME 4 INTERNALDIMMINGPROGRAM 1 0 O 6 TERRAINTESTF IN S O 8 28 V PANEL LIGHTING BUSHI gt S O 9 PANEL LIGHTING BUSLO 000 O Designates an active low signal FIGURE 3 1 SCHEMATIC PI NOUT 25 PIN DSUB REV C October 28 2013 Manual Number 9015308 11 of 18 Mid Continent Instruments and Avionics Wichita KS acm Locatic 4 40 thread ee C WHITE MD41 1024 1028 1028 5V Horizontal b MD41 1034 1038 1038 5V Vertical Note 1 Use two 4 40 X 3 8 Flat Head Phillips Screws for Mounting FI GURE 3 2 OUTLI NE DRAWI NG REV C October 28 2013 Manual Number 9015308 12 of 18 Mid Continent Instruments and Avionics Wichita KS note 1 ANNUNCIATOR FULL BRIGHT 1 ANNUNCIATOR FULL BRIGHT 2 note 1 TERRAIN WARNING BRT DIM note 1 INTERNAL DIMMING PROGRAM 1 TERRAIN CAUTION ANNUNCIATE IN TERRAIN TEST IN
13. s and Avionics Attn Technical Publications 9400 E 34 ST North Wichita KS 67226 USA Phone 316 630 0101 Fax 316 630 0723 Copyright 2003 Mid Continent Instruments and Avionics REV C October 28 2013 Manual Number 9015308 2 of 18 Revision Detail Mid Continent Instruments and Avionics Wichita KS ECO Rev Date Detail N R 04 22 04 Complete issue A 01 21 05 Added otherwise connect pin 7 to bright dim switch on aircraft dimming bus to note 2 of fig 3 3 and 3 4 B 07 02 12 Removed schematics Figure 3 5 6051 10 28 13 Updated Technical Specifications to include compatible Garmin TAWS Systems REV C October 28 2013 Manual Number 9015308 3 of 18 Mid Continent Instruments and Avionics Wichita KS TABLE OF CONTENTS SECTION 1 GENERAL DESCRI PTI ON 1 1 INTRODUCTION 1 2 SPECIFICATIONS TECHNICAL 1 2 1 PHYSICAL CHARACTERISTICS 1 2 2 ENVIRONMENTAL CHARACTERISTICS 1 2 3 SPECIFICATIONS ELECTRICAL 1 2 4 FRONT PANEL CONTROLS AND ANNUNCIATIONS 1 2 4 1 CONTROLS 1 2 4 2 ANNUNCIATIONS 1 2 5 EQUIPMENT LIMITATIONS SECTION 2 I NSTALLATI ON CONSI DERATI ONS 2 1 COOLING 2 2 EQUIPMENT LOCATION 2 3 ROUTING OF CABLES SECTION 3 INSTALLATION PROCEDURE 3 1 GENERAL INFORMATION 3 2 UNPACKING AND INSPECTING 3 3 MOUNTING THE MD41 3 4 INSTALLATION LIMITATIONS SECTI ON 4 POST INSTALLATI ON CHECKOUT 4 1 PRE INSTALLATI ON TEST 4 2 OPERATING INSTRUCTIONS SECTI ON 5 I NSTRUCTI ONS FOR
14. ul time limitations REV C October 28 2013 Manual Number 9015308 16 of 18 Mid Continent Instruments and Avionics Wichita KS ENVIRONMENTAL QUALI FI CATION FORM RTCA DO160D NOMENCLATURE MD41 TERRAIN AWARENESS ANNUNCIATI ON CONTROL UNIT MODEL NO MD41 TSO C151a MANUFACTURER Mid Continent Instruments and Avionics 9400 E 34 Street Wichita KS 67226 Phone 316 630 0101 Temperature and Altitude 4 0 Equipment tested to Category A1 and F2 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 Temperature Variation Equipment tested to Category B Shock 7 0 Equipment tested to Category B Operational 7 2 Crash Safety 7 3 Vibration Aircraft type 1 helicopter tested to category U Aircraft type 2 through 6 tested to category S pamm TUE Equipment identified as Category X no test required Equipment identified as Category X no test required REV C October 28 2013 Manual Number 9015308 17 of 18 Mid Continent Instruments and Avionics Wichita KS Environmental Qualification cont Fluids ae eee s identified as Category X no test i odi oir o d RM MN C ERA ree MM eee memi EE Radio Emissions tested to B and M Induced Transient BEN ud od to Category A3C3 Susceptibility Lightning Direct Effects EUN Equipment identifie
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