INSTALLATION MANUAL AND OPERATING INSTRUCTIONS 4300
Contents
1. 4 5 6 Red 9015640 7 8 9 NVIS Green A 9015640 10 n a 12 28V White LED light tray is part number 9016909 no dash number suffix Note NVIS light tray provides standard dial lighting for NVIS applications However TEST and STBY PWR annunciators are not filtered for NVIS operation Consider your application accordingly Table 1 4 Rev A January 5 2011 Page 7 of 21 Manual Number 9017205 Mid Continent Instruments and Avionics Wichita KS CU Kt Rotating Roll Dial Rotating Roll Dial Fixed Pointer Fixed Pointer Traditional Symbolic Airplane Delta Symbolic Airplane Standard Horizon Dia Standard Horizon Dial Model Input Roll Dial Horizon Dial Symbolic Number Voltage Airplane 4300 611 10 to 32 VDC Rotating Standard Traditional 4300 613 10 to 32 VDC Rotating Standard Delta Rev A January 5 2011 Figure 1 1 Display Configurations Page 8 of 21 Manual Number 9017205 Roll Pointer Gyro Warning Flag Display Symbolic Airplane Horizon Line Caging knob Manual Erection Symbolic Airplane Adjustment Knob Roll dial background Rotating Blue Brown Fixed Black Steady on yperation ir Chalf bright indicates standby s switch pushbutton ower On or Off Mid Continent Instruments and Avionics Wichita2. Mid Continent Instruments and Avionics Wichita KS CONTINUED Al RWORTHINESS A Battery The battery is designed to be a user replaceable item if desired Recommended replacement interval for the standby battery P N 9015607 is 3 years because of diminished capacity See Figures 2 6 and 2 7 for more information yd NOTE The standby battery contains lead Do not dispose of in local landfills or Po other environmentally sensitive areas NOTE Recycle the battery in accordance with state and local regulations For 5 recycle locations visit www rbrc com or call 1 800 8 BATTERY 1 800 canis 822 8837 In normal use the 4300 6XX with Battery Backup supplies the proper float charge voltage to maintain its battery at peak capacity however the battery will slowly self discharge if the attitude indicator is left unused for long periods over 3 months In addition self discharge rates are directly related to the storage temperature The higher the storage temperature the faster the self discharge rate Therefore the battery should be periodically charged or removed from the installation and maintained on a charger If the 4300 6XX Electric Attitude Indicator with Battery Backup has not been operated for an extended period more than 3 months to keep the battery charged the standby battery should be charged by one of the following methods 1 Keep the battery plugged into the 4300 Electric Attitude Indicator Run the unit overnight
3. approx 15 hours at the rated voltage 2 Float Charging Disconnect the battery from the indicator Connect the battery to a constant voltage source battery plug pin 1 red wire positive of 20 4 to 20 6 VDC continuously Float charging may take 24 hours or longer to charge a battery pack 3 Routine Charging Disconnect the battery from the indicator Connect the battery to a constant voltage source battery plug pin 1 red wire positive of 21 6 to 22 1 VDC with a current limit of 0 1 ampere maximum When the charging current drops to approximately 5mA the battery is fully charged and should be disconnected Leaving 21 6 to 22 1 VDC charge voltage on the battery for an extended time will degrade its life If continuous maintenance of the charge is desired refer to step 2 Float Charging x WARNI NG Battery out gassing and a rotten egg odor may occur due to prolonged high rate overcharging and may result in battery damage MCI recommends that the battery assembly be replaced if out gassing has occurred 4 MCI Battery Charger Tester P N 36029 may be used This Battery Charger Tester will apply an initial charge per step 3 above and then automatically switch to maintain a float charge per step 2 above indefinitely after initial charging is complete Rev A January 5 2011 Page 13 of 21 Manual Number 9017205 Mid Continent Instruments and Avionics Wichita KS D On at least an annual basis as well as any time there may
4. Instruments and Avionics Wichita KS UP When mounted End View fp vertically Side View I Figure 2 4 Remote Mount Standby Battery Option using 9015671 Kit Contents of Standby Battery Remote Mount Kit Part Number Description Qty 7016975 Crimp Pin 2 7016983 Connector Housing Cap 1 7017676 Screw 4 40x3 16 Pan Head Phillips 4 7018328 Contact Socket 2 7018336 Connector Housing Plug 1 9015725 Battery Mount Plate 1 Rev A January 5 2011 Page 17 of 21 Manual Number 9017205 Mid Continent Instruments and Avionics Wichita KS SECTION3 OPERATION 3 1 GENERAL This section describes the Model 4300 6XX Electric Attitude Indicator operating procedures The indicator is required to be installed in an aircraft with the specified inputs applied Figure 1 2 provides an illustration of a typical Model 4300 display and a table describing indicator functions 3 2 STARTING PROCEDURES The following operational procedures are recommended when preparing the indicator for use NOTE Indicator may be momentarily caged by pulling PULL TO CAGE knob to the fully extended position holding knob until the display stabilizes and then allowing the knob to return to the normal position CAUTI ON THE INDICATOR MAY BE DAMAGED IF THE PULL T
5. run from standby power until the standby battery is exhausted before the gyro warning flag appears If the STBY PWR button is pushed before the battery is exhausted the instrument will be removed from standby power and the gyro warning flag will appear 1 5 OPTI ONS AND CONFI GURATI ONS Options Table Panel Tilt Calibration 0 to 20 Lighting Voltage 5V 14V or 28V See Table 1 4 Lighting Color Blue White White or Red See Table 1 4 Miscellaneous Parts Non Trimmable Symbolic Airplane Knob Cover P N 36022 Slip Indicator Kit P N 36023 Front Mount Kit 3 32 thk P N 36028 1 or 1 2 thk P N 36027 1 Panel Wedges 3 P N PW3R 3 or 4 P N PW3R 4 Mating Connector Kit P N 9015514 Remote Battery Mounting Kit P N 9015671 Replacement Standby Battery P N 9015607 Battery Charger P N 36029 Table 1 1 1 6 SPECI FI CATI ONS Physical Characteristics Qualification FAA TSO C4c Environmental Qualification RTCA DO 160D Environmental Category C1BAB SBM RBB1 P XXXXXXZZAZZ WF IM A3H33 XXA Weight 3 7 pounds 2 7 pounds without battery Dimensions Length behind panel not including mating connector 6 6 inches long max battery not installed 8 6 inches long max battery installed 3 28 inches high maximum 3 28 inches wide maximum Mating Connector MS3116F8 4S or equivalent MCI P N 9015514 Cover Glass HEA anti reflec
6. KS Fixed roll pointer Indicates aircraft roll displacement relative to a rotating roll dial If loss of operating voltage should occur gyro warning flag will come into view Lower area of display when referenced to the symbolic airplane indicates aircraft nose is below horizon or in a dive attitude Upper area of display indicates aircraft nose is above horizon or in a climb attitude Indicates roll and pitch attitude relative to the horizon The symbolic airplane can be moved pitch only using the symbolic airplane adjustment knob Indicates earth horizon relative to aircraft pitch and roll attitude When pulled manually erects the gyro vertical to the case orientation Used to adjust the symbolic airplane ew _ Ma Roll Pointe i rar N OFF Flag Ko Red Ie S Blue SS A Background Ma So twin n symbolic Airplane 7 range mg ma BY N Brown J N NR Background 1 m s iging knol LED amber Red LED Lights if batt battery mode Green LED Lights if batt l Symbolic Airplar Adjustment Knok Typical Electric Attitude I ndicator Display Rotating Roll Dial Fixed Roll Pointer Traditional Wing Symbolic Airplane Shown Rev A January 5 2011 Figure 1 2 Page 9 of 21 Manual Number 9017205 Mid Continent Instruments and Avionics Wichita KS SECTION 2 INSTALLATION 2 1 GENERAL This section contains mounting electrical connections
7. O CAGE KNOB IS RELEASED WITH A SNAP SLOWLY RELEASE PULL TO CAGE KNOB AVOIDING A SNAP RELEASE A Apply power to the indicator Note that the Gyro Warning flag red will pull out of view Allow three minutes for presentation stabilization B On models with trim adjustment rotate the symbolic airplane adjustment knob for the desired pitch attitude presentation i e aligning the symbolic airplane with the horizon C If caging is required caging should be accomplished when the aircraft is in a wings level normal cruise attitude as indicated by other instruments or the earth s horizon If the gyro is caged when the aircraft is not in this attitude the resulting attitude presentation immediately after caging will be in error by the difference between true vertical and actual aircraft attitude Small errors in caging erection will be corrected by the indicator to true vertical in pitch and roll at 2 5 per minute minimum 5 min nominal 3 3 IN FLIGHT PROCEDURES A Adjust the symbolic airplane to obtain desired pitch attitude presentation after take off B Inthe event of errors in excess of 10 caused by extended bank or fore aft acceleration the indicator should be momentarily caged after the aircraft is returned to level flight 3 4 DYNAMIC ERRORS A Turn Induced Errors Pitch indication errors resulting from a standard coordinated turn 180 degrees in one minute at a true airspeed of 156 knots will not ex
8. Wy MidContinent INSTRUMENTS AVIONICS INSTALLATION MANUAL AND OPERATING INSTRUCTIONS 4300 6XX Series Electric Attitude I ndicator With Battery Backup ue eis STBY os TEST 9 Sol U 2 lt Ne Mid Continent I nstruments and Avionics 9400 E 34 Street N Wichita KS 67226 USA phone 800 821 1212 e fax 316 630 0723 e web www mcico com Rev A January 5 2011 1 of 21 Manual Number 9017205 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 this equipment If further information is required please contact Mid Continent Instruments and Avionics Attn Customer Service Dept 9400 E 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 Instruments and Avionics s Attn Technical Publications 9400 E 34 ST North Wichita KS 67226 USA Phone 316 630 0101 Fax 316 630 0723 info mcico com www mcico com Copyright 2011 Mid Continent Instruments and Avionics Rev A J
9. ailable for the attitude indicator as well as the expected battery lifetime Fig 2 7 and 2 8 For optimum battery performance it is recommended to mount the battery in a temperature controlled section of the aircraft Rev A January 5 2011 Page 11 of 21 Manual Number 9017205 Mid Continent Instruments and Avionics Wichita KS 2 5 INSTALLATION NOTE Before installing unit verify the option label on the unit matches the aircraft requirements for instrument voltage lighting voltage color and panel tilt Install the Electric Attitude Indicator within the aircraft in accordance with the aircraft manufacturer s instructions and the following steps A B Refer to Figure 2 1 for installation dimensions and electrical information Ensure the available instrument panel cutout meets the requirements of the indicator See Fig 2 2 for details If a remote mounted standby battery is preferred 1 Remove 4 screws mounting the standby battery to the rear of the indicator and remove the standby battery 2 Re install the 4 screws into the rear of the indicator 3 Mount the standby battery in a protected location inside the aircraft using 9015671 kit oriented at any angle from horizontal to vertical If mounted vertically cable side must be down as shown in Fig 2 4 4 Make an extension cable 22 AWG minimum using the connectors provided in 9015671 kit Plug the standby battery cable into the rear of the Indicator NOTE The
10. and other information required for installation After installation of cabling and before installation of the equipment ensure that power is applied only to the pins specified in the interconnection diagram CAUTION GYROS ARE DELICATE INSTRUMENTS THE FOLLOWING PRECAUTIONS MUST BE OBSERVED A high gyroscope failure rate can be directly related to rough or improper handling Gyros are delicate and cannot withstand the shock of being dropped jarred or struck by pieces of equipment Do not place gyros on any hard surface Pad with generous foam Handle like eggs To prevent damage to a gyro the instrument should be transported to and from the aircraft in it s original shipping container If this is impractical the gyro should be hand carried carefully in an upright position A gyro should never be removed while it is spinning or running down The instrument normally operates at high RPM and may take 10 minutes or longer to run down If it is removed while running and tilted more than 20 degrees the gyro can develop a gimbal lock The gimbal will tumble and start to spin If gimbal lock occurs while the rotor is turning the gimbal may spin fast enough to damage the gimbal bearings requiring an overhaul A malfunctioning gyro should be handled with the same care given a new instrument Most malfunctioning instruments can be repaired and returned to service Using proper handling procedures during removal prevents additional damage and h
11. anuary 5 2011 Page 2 of 21 Manual Number 9017205 Mid Continent Instruments and Avionics Wichita KS REVISION HI STORY ECO Rev Date Detail 01 5 11 Initial release Rev A January 5 2011 Page 3 of 21 Manual Number 9017205 Mid Continent Instruments and Avionics Wichita KS TABLE OF CONTENTS Section Page Cover Page 1 Forward 2 Revision History 3 Table of Contents 4 Section 1 General Description 5 1 1 Purpose of Equipment 5 1 2 Physical Description 5 1 3 Functional Description 5 1 4 Gyro Warning Flag 6 1 5 Options and Configurations 6 1 6 Specifications 6 Section 2 Installation 10 2 1 General 10 2 2 Pre Installation Inspection 10 2 3 Parts 11 2 3 1 Included Parts 11 2 3 2 Installer Supplied Parts 11 2 3 3 Additional Optional Parts 11 2 4 Equipment Location 11 2 5 Installation 12 2 6 Continued Airworthiness 13 Section 3 Operation 18 3 1 General 18 3 2 Starting Procedures 18 3 3 In Flight Procedures 18 3 4 Dynamic Errors 18 3 5 Standby Battery Operation 19 3 6 Equipment Limitations 21 Figure No List of I Illustrations 1 1 Display Configurations 8 1 2 Typical Indicator Display Detail 9 2 1 Outline Drawings 15 2 2 Rear Mount Cutout Dimensions 16 2 3 Front Mount Cutout Dimensions 16 2 4 Remote Mount Standby Battery Option 17 2 5 Nominal Battery Discharge Rate at 20 C 20 2 6 Effect of Low Temperature on Battery Capacity 21 2 7 Life Characteristics in Standby Use 21 Tabl
12. be a question about battery performance life a Full Capacity Test should be performed To perform a Full Battery Capacity Test use one of the following methods 1 Manual a Disconnect battery pack from the 4300 Attitude Indicator b Ensure the battery is completely charged and at or near normal room temperatures 20 25 C Ref Sect 2 6 1C c Connect the battery to a load of 90 ohms rated for 10 watts for 60 minutes while monitoring the battery voltage level i If the battery voltage is above 15 0 volts at the end of the 60 minute battery capacity test the battery should be capable of continued use after recharging is complete ii If the battery voltage drops below 15 0 volts before the end of the 60 minute test period while under load the battery pack is nearing the end of its service life and should be replaced d Recharge the battery pack immediately 2 Automatic a Use MCI Battery Charger Tester P N 36029 When in the capacity test mode this Charger Tester will charge the battery and measure the time required for discharge 60 minutes minimum The unit will then automatically switch to the charge float mode to maintain the standby battery at full charge The battery may be permanently damaged if it is left in a discharged state Recharge a discharged battery as soon as possible and maintain with a float charge for maximum battery life 2 6 2 Attitude I ndicator No periodic scheduled maintenance or calibration is nece
13. cable is disconnected for shipping to prevent accidental activation and battery discharge in transit The unit may start when the battery is connected Momentarily push the STBY PWR button twice if necessary until the Red Gyro Warning flag shows Continue the installation after the Gyro has spun down Attach aircraft electrical system cable to the round 4 pin indicator connector and insert the indicator into the instrument panel cutout Secure the indicator to the instrument panel using the screw sizes called out in the mounting instructions Length of screws will be determined by aircraft instrument panel thickness The aircraft manufacturer or the installation facility is responsible for supplying appropriate installation hardware Apply the correct input power to the indicator The Gyro Warning flag red will be out of view Check to determine that indicator internal lighting is working correctly After the unit has been powered for at least a 3 minute spin up period press and hold the STBY PWR button A green light will illuminate under the word TEST indicating the standby battery is functioning properly If a red light illuminates the standby battery will need to be charged for 1 hour before retesting If the standby battery fails to pass the short battery capacity test after 1 hour charging a full battery capacity test must be performed See Section 2 6 1D Rev A January 5 2011 Page 12 of 21 Manual Number 9017205 2 6 2 6 1
14. ceed 3 Dynamic errors developed under non standard conditions may be greater Errors that develop will be self corrected by the internal erection system or manually corrected by the actuation of the caging system B Acceleration amp Deceleration Errors Pitch roll indicating errors may occur due to accelerations experienced during takeoff climb out descent and landing Errors that develop will be self corrected by the internal erection system or manually corrected in straight and level flight by the actuation of the caging system Rev A January 5 2011 Page 18 of 21 Manual Number 9017205 Mid Continent Instruments and Avionics Wichita KS C Taxiing Errors A pitch and roll indicator display error of approximately 1 will occur during a sudden 90 ground turn A pitch indicator display error of approximately 2 will occur during a sudden 180 ground turn Errors that develop will be self corrected by the internal erection system or manually corrected by the actuation of the caging system 3 5 STANDBY BATTERY OPERATION A Normal Flight Supply aircraft power to the instrument The internal standby battery charges automatically while the gyro is running Lighting is on a separate circuit connected to the aircraft lighting bus B Loss of Aircraft Power At loss of aircraft power to the unit the attitude indicator will automatically and immediately transition to standby battery power A half bright steady amber annunciat
15. e No List of Tables 1 1 Options Table 6 1 2 Physical Characteristics 6 1 3 Performance 7 1 4 Light Tray Assembly Options 7 Rev A January 5 2011 Page 4 of 21 Manual Number 9017205 Mid Continent Instruments and Avionics Wichita KS SECTION 1 GENERAL DESCRIPTION 1 1 PURPOSE The Model 4300 6XX Electric Attitude Indicator with Battery Backup incorporates a moving display that simulates the earth s horizon and provides the pilot with a real time visual indication of the aircraft pitch and roll attitude relative to the indicator symbolic airplane The instrument can function as a primary or standby indicator with special configurations available to match existing systems or electronic flight displays In the event aircraft electrical power is lost the indicator will switch to an internal backup power source rechargeable sealed lead acid battery to permit continued operation of the indicator Panel tilt lighting color voltage non trimmable knob cover front mount adapter plates and a slip indicator are available as options 1 2 PHYSICAL DESCRIPTION The 4300 6XX Electric Attitude Indicator with Battery Backup incorporates pitch and roll displays that are mechanically linked to a spinning mass gyroscope The horizon bar moves behind the symbolic airplane Precession error is corrected by the 4300 s erection system or by pulling the PULL TO CAGE knob If the gyro motor is not receiving sufficient power to operate a warning flag drop
16. elps ensure possible reuse 2 2 PRE I NSTALLATI ON INSPECTION A Unpacking Carefully remove the attitude indicator from shipping container The shipping container and packing materials should be retained for use should the attitude indicator require future shipment Inspect for Damage Inspect the shipping container and indicator for any signs of damage sustained in transit If necessary return attitude indicator to the factory using the original shipping container and packing materials File any claim for damages with the carrier CAUTION The unit is shipped with the battery cable disconnected to prevent inadvertent operation of the indicator during shipping f the cable was found connected when received check the battery condition per section 2 6 3 and then reconnect the battery during instrument installation if it checks out ok Remaining discharged for extended periods may permanently damage the battery pack Rev A January 5 2011 Page 10 of 21 Manual Number 9017205 Mid Continent Instruments and Avionics Wichita KS 2 3 PARTS 2 3 1 Included Parts Model 4300 Electric Attitude Indicator including Battery Pack P N 9015607 Mating Connector MS3116F8 45S or equivalent P N 9015514 Installation Manual P N 9017205 owe 2 3 2 Installer Supplied Parts Mounting Screw 6 32UNC 2A Three 3 required 1 long screws are suggested for panel thickness between 0 05 and 0 19 but may not be optimum in all cases Install
17. er will need to determine what is correct for a particular installation Do not exceed 1 06 screw depth into bezel 2 3 3 Additional Parts that may be required Symbolic Airplane Adjustment Knob Cover Kit P N 36022 Slip Indicator Kit P N 36023 Front Mount Kit 3 32 thk P N 36028 1 or 1 2 thk P N 36027 1 Panel Wedges 3 P N PW3R 3 or 4 P N PW3R 4 Remote Battery Mounting Kit P N 9015671 moOoOw gt 2 4 EQUIPMENT LOCATION The attitude indicator should be located within the aircraft in accordance with the following considerations A The indicator is ideally located in the instrument panel directly in line with the pilot s normal line of sight The PULL TO CAGE knob should be within easy reach Installations that result in viewing angles in excess of 30 degrees may reduce display readability B Compare the space requirements of the indicator with the installation area being considered C The power cable should not run adjacent to heaters engine exhausts or other heat sources Also take care to route and tie the cable away from aircraft controls and cables D If remote mounting the standby battery the cable length from the battery to the unit should be kept as short as practical using wire of 22 AWG minimum 18 AWG wire is recommended for cable runs over 50 feet Remote mounting the battery in a location subject to extreme temperature variations may dramatically shorten the emergency operation time av
18. ht throughout this short test does not guarantee that a full hour of operation time is available Actual operation time on the battery may vary considerably depending on temperature charge status and battery condition See Sect 3 6 for more details Complete charging may be required to bring the battery up to full charge if it has been stored for more than four months or if it has been partially discharged If a steady red light is observed at any time during the test charge the standby battery completely using one of the methods described in section 2 6 and retest the battery If after charging the test still fails service may be required It is not recommended to test the battery when aircraft power is not available but it is possible to put the indicator into test mode while operating on the backup battery The test will run but the indicator will turn off at the end of the test period To turn the indicator back on simply push the STBY PWR button again g F 7 30 60 Discharge Time min Fig 2 5 Nominal Battery Discharge Rate at 20 C Rev A January 5 2011 Page 20 of 21 Manual Number 9017205 Mid Continent Instruments and Avionics Wichita KS 3 6 EQUIPMENT LIMITATIONS The Mid Continent 9015607 battery pack is part of a complete system When remote mounted the 9015607 battery pack MUST be installed with the Mid Continent 4300 6XX series Electric Attitude Indicator with Battery Backup in order to be appro
19. input voltage of 10 to 32 volts An integral lighting system featuring a user replaceable light tray assembly operates from the aircraft lighting bus and is available in 5V 14V or 28V versions dependent on configuration In standby power operation low intensity LED dial lighting is automatically turned on to provide nighttime visibility The internal battery is designed for emergency use only Frequent use extended discharging extended lack of charging misuse and age will require battery replacement Replacement can be done in the field with or without removal of the attitude indicator Do not operate this model without the specified battery intact Battery substitution modification misuse and lack of specified maintenance will void all warranties and hold the manufacturer harmless from any and all claims or legal actions Refer to an FAA authorized maintenance facility for testing and maintenance of this instrument excluding battery or light tray replacement Rev A January 5 2011 Page 5 of 21 Manual Number 9017205 Mid Continent Instruments and Avionics Wichita KS 1 4 GYRO WARNING FLAG A warning circuit monitors the electrical voltage used to power the gyro motor When the Indicator is turned off or after the internal battery is discharged the gyro warning flag comes into view Anytime aircraft power is lost including normal end of flight power down the unit will automatically be put in the standby power mode The instrument will
20. or light next to the STBY PWR text on the unit will turn on This is intended to attract the pilot s attention and indicate that there has been a loss of primary power to the 4300 Attitude Indicator The unit will continue operating on the standby battery for approximately one 1 hour or until the battery is exhausted See Fig 2 5 for more information on battery discharge rate The Gyro Warning flag will remain out of view which indicates the gyroscope is valid and operating normally Internal instrument lighting is provided in standby battery mode with preset brightness not controllable through the panel lighting bus OK KK OK OK K K WARNING The unit does not distinguish between loss of power in flight during an emergency and loss of power during post flight shutdown Therefore it is REQUIRED to turn off the standby battery backup power after each flight Failure to do so will deplete the battery and cause permanent damage requiring replacement of the standby battery KKK KK KK When the unit is running on standby battery power pushing the STBY PWR button will turn the unit off The amber STBY PWR annunciator will extinguish and the Gyro Warning flag will come into view indicating that the unit is completely off with no power supplied by either the aircraft or the standby battery Any time the unit is completely off pushing the STBY PWR button will put the unit in the standby power mode The instrument will run from standby powe
21. r until the standby battery is exhausted Pushing the STBY PWR button again will remove standby battery power and turn the unit off Restoring aircraft power will clear any standby battery operation and resume automatic charging of the standby battery Rev A January 5 2011 Page 19 of 21 Manual Number 9017205 Mid Continent Instruments and Avionics Wichita KS C Standby Battery Test The control panel on the front of the instrument incorporates a manual test feature This test feature places the standby battery pack under load for approximately one minute the gyro is used as a load while displaying either a red or green light under the word TEST on the front panel To initiate this test 1 Turn on the indicator with aircraft power and allow the unit to spin up for 3 minutes or more 2 Press and hold the STBY PWR button After several seconds the amber LED will light indicating unit has latched into Battery Test Mode The test runs for approximately one minute during which time the amber LED stays on and either a red or green light is displayed under the word TEST 3 Visually monitor the test lights until the amber LED goes out signaling the end of the test 4 A green light throughout the test indicates the standby battery pack is healthy and should be able to function normally A red light at any time during the test means that the standby battery is at least in need of charging and possibly of replacement Note A green lig
22. s into view This will normally occur only if the unit is turned off or after the internal standby battery is exhausted 1 3 FUNCTIONAL DESCRIPTION Model 4300 6XxX Electric Attitude Indicators employ an efficient electrically driven internal vertical gyroscope assembly incorporating a special air erection mechanism This mechanism simultaneously erects the pitch and roll axes of the gyroscope Movement of the aircraft generates a reaction of the display that simulates the visual reference seen by the pilot when looking outside at the earth s true horizon line The 4300 6XX Electric Attitude Indicator with Battery Backup offers the unique feature of a self contained standby power source Advances in the design of this gyro system allow it to operate for about one hour after main input power is lost depending on the battery condition at the time of power failure Anytime aircraft power is lost either during flight or during post flight shutdown the instrument will automatically and immediately be placed in standby power mode The instrument will run from standby power until the internal battery is exhausted If the unit is running on standby power internal battery pushing the STBY PWR button will turn the unit off completely Pushing the STBY PWR button again will restore unit operation to standby power Restoring aircraft power will clear any standby power mode and automatically resume standby battery charging The indicator will operate on an
23. ssary for continued airworthiness of the 4300 series Electric Attitude Indicator If the unit fails to perform to specifications it must be removed and serviced by a qualified service facility Rev A January 5 2011 Page 14 of 21 Manual Number 9017205 Mid Continent Instruments and Avionics Wichita KS e to nnector Pinout uy A Ground I ae eee eee f m STEY A TEST 9 I Liohtir polarit J ate t Input D Lightir polarit nfiguration sl Recommended Circuit Breaker 2 Amp for 14VDC aircraft and 1 Amp for 28VD jircraft mmended wir jau 22 A minimut max 4 4 N K ie H t mir Standby Battery Not Installed ICONNEGTOR NI ATES WITH tar iby ittery lr led R EQUI Figure 2 1 Outline Drawing Rev A January 5 2011 Page 15 of 21 Manual Number 9017205 Mid Continent Instruments and Avionics Wichita KS t ey 170 or pl i Ga LS 4 it Yp om zel 45 typ yp anne x l ries ar Mount Panel Cutout aximum par thickness 4 Figure 2 2 Rear Mount Panel Cutout Dimensions Figure 2 3 Front Mount Panel Cutout Dimensions Rev A January 5 2011 Page 16 of 21 Manual Number 9017205 Mid Continent
24. tive coated Instrument Panel Mounting Rear mount Front mount with adapter plate Table 1 2 Rev A January 5 2011 Page 6 of 21 Manual Number 9017205 Mid Continent Instruments and Avionics Wichita KS Performance 7500 Hour Mean Time Between Failure MTBF Initial Erection The PULL TO CAGE knob will erect the gyroscope to within 2 0 of case vertical in roll and pitch from any position at any time Final Erection The vertical gyroscope should be allowed to spin up for 3 minutes after rated power is applied and after initial erection After 5 minutes the final erection accuracy of pitch and roll will be within 1 of vertical Erection Rate Gyroscope erects to local vertical in pitch and roll at 2 5 per minute minimum Warning Flag A gyro warning circuit provides for continuous monitoring of gyro voltage If loss of gyro motor voltage occurs the red warning flag will appear See section 3 5 for battery operation Symbolic Airplane The adjustment range is 4 minimum from the zero pitch position Power Consumption Starting 1 8A maximum at 14 VDC input 0 9A maximum at 28 VDC input Running Nominal 0 55A 15 at 14 VDC input Nominal 0 27A 15 at 28 VDC input Lighting 2 5 watts maximum for all models using 5V 14V or 28V lighting Table 1 3 Light Tray Assembly Options 5V 14V 28V LED White 9016909 5 14 Blue White 9015640 1 2 3 White 9015640
25. ved as a complete TSO d system This battery is not FAA approved if installed or used in any other way Actual operation time on the battery may vary considerably depending on temperature charge status and battery condition Low temperatures will temporarily degrade battery capacity as shown in Fig 2 6 Internal chemistry will slowly degrade battery capacity over several years of operation as shown in Fig 2 7 even when correctly maintained A poorly maintained battery will suffer accelerated degradation in excess of the guidelines given in this document Extended storage in a discharged state or at high ambient temperatures and over charging will all permanently damage a battery Complete charging is required to bring the battery up to full capacity if it has been stored for more than four months or if it has been partially discharged Fig 2 6 Effect of Low Temperature On Standby Battery Capacity Retention Capacity 2 3 Time Years Fig 2 7 Life Characteristics In Standby Use Rev A January 5 2011 Page 21 of 21 Manual Number 9017205
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