INSTALLATION MANUAL AND OPERATING
Contents
1. RIEN c o t lt Rev J September 1 2009 Manual Number 9015762 Page 7 of 22 Mid Continent Instruments Wichita KS Face Layout A Face Layout B Fixed Roll Dial Rotating Roll Dial Fixed Pointer Rotating Pointer Traditional Symbolic Airplane Traditional Symbolic Airplane Standard Horizon Dial Standard Horizon Dial Face Layout C Face Layout D Rotating Roll Dial Fixed Roll Dial Fixed Pointer Rotating Pointer Delta Symbolic Airplane Delta Symbolic Airplane Standard Horizon Dial Standard Horizon Dial Face Layout E Face Layout F Rotating Roll Dial Fixed Roll Dial Fixed Pointer Rotating Pointer High Resolution Horizon Dial High Resolution Horizon Dial Traditional Symbolic Airplane Traditional Symbolic Airplane Figure 1 1 Display Configurations Rev J September 1 2009 Manual Number 9015762 Page 8 of 22 Mid Continent Instruments Wichita KS Face Layout G Face Layout H N see O 7 o l Rotating Roll Dial Fixed Roll Dial Fixed Pointer Rotating Pointer Delta Symbolic Airplane Delta Symbolic Airplane High Resolution Horizon Dial High Resolution Horizon Dial Model Input Roll Dial Horizon Dial Symbolic Face Number Voltage Airplane Layout 4300 411 10 to 32 VDC Rotating Standard Traditional A 4300 4122. E N HU f i ia No Pe g p When mounted i i End View G vertically Sew Bs N Y bee 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 J September 1 2009 Manual Number 9015762 Page 18 of 22 Mid Continent Instruments Wichita KS Section 3 Operation 3 1 General This section describes the Model 4300 XXX 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 k CAUTI ON THE I NDI CATOR MAY BE DAMAGED IF THE PULL TO CAGE KNOB IS RELEASED WITH A SNAP SLOWLY RELEASE PULL TO CAGE KNOB AVOI DI NG A SNAP RELEASE 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 A Apply power to the indicator Note that the Gyro War
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 D Plug the standby battery cable into the rear of the Indicator NOTE The cable is disconnected for shipping to prevent accidental activation and battery discharge in transit E 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 F Attach aircraft electrical system cable to the round 4 pin indicator connector and insert the indicator into the instrument panel cutout G 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 H Apply the correct input power to the indicator The Gyro Warning flag red will be out of view J Check to determine that indicator internal lighting is working correctly K 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
4. 10 to 32 VDC Fixed Standard Traditional B 4300 413 10 to 32 VDC Rotating Standard Delta C 4300 414 10 to 32 VDC Fixed Standard Delta D 4300 431 10 to 32 VDC Rotating High Resolution Traditional E 4300 432 10 to 32 VDC Fixed High Resolution Traditional F 4300 433 10 to 32 VDC Rotating High Resolution Delta G 4300 434 10 to 32 VDC Fixed High Resolution Delta H 4300 2XX OEM Specific Figure 1 1 Cont Display Configurations Rev J September 1 2009 Manual Number 9015762 Page 9 of 22 Mid Continent Instruments Wichita KS Roll Pointer A Fixed roll pointer Indicates aircraft roll displacement relative to a rotating roll dial B Rotating roll pointer Indicates aircraft roll displacement relative to a fixed roll dial Gyro Warning Flag If loss of operating voltage should occur gyro warning flag will come into view Display 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 Symbolic Airplane Indicates roll and pitch attitude relative to the horizon The symbolic airplane can be moved pitch only using the symbolic airplane adjustment knob Horizon Line Indicates earth horizon relative to aircraft pitch and roll attitude Caging knob When pulled manually erects the gyro vertical to the case orientation Manual Erection Symbolic Airplane Used to adjust the sym
5. 2009 Manual Number 9015762 Page 3 of 22 Mid Continent Instruments Wichita KS Revision Detail ECO Rev Date Detail N R 10 1 03 Complete issue A 11 4 03 Revise text for improved short battery test Add text to Sec 2 6 2 B for P N 36029 battery charger B 05 25 04 Update display configurations Fig 1 1 update connector pinout Lighting No polarity revise currents in table 1 3 add bezel dims to panel cutouts add DO 160D environmental test qualification in Table 1 2 C 09 15 04 Revise section 2 6 Update DO 160D statement in section 1 6 from A2 to C1 for 35K altitude 4307 D 03 28 05 Add Special HIRF Considerations paragraph to section 2 5 Update DO 160D statement in section 1 6 from RR to WW 4503 E 01 04 06 Add section 2 6 1D 2 regarding automatic capacity test 4834 F 04 30 07 Delete 40X single voltage versions 4956 G 12 13 07 Update DO 160 qualification in section 1 6 from WW to WF and from A3C3 to A3H33 Remove paragraph pertaining to Special HIRF Considerations in section 2 5 Note This change is incorporated only on units identified as Mod Status 4 as indicated on the unit nameplate 5214 H 05 26 09 Change 4300 4XX to 4300 XXX with Battery Backup to include OEM specific versions 5270 J 09 01 09 Remove first paragraph in section 3 6 stating that Indicator is not to be used as a reference for aerobatic flight Upda
6. 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 J September 1 2009 Manual Number 9015762 Page 14 of 22 Mid Continent Instruments Wichita KS D On at least an annual basis as well as any time there may 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 a Ifthe 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 b Ifthe 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
7. Model 4300 Electric Attitude Indicator including Battery Pack P N 9015607 B Mating Connector MS3116F8 4S or equivalent P N 9015514 C Installation Manual P N 9015762 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 some installations The installer 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 moomr 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 cabl
8. automatically switch to the charge float mode to maintain the standby battery at full charge WARNI NG The battery may be permanently damaged if it is left ina discharged state Recharge a discharged battery as soon as possible and maintain with a float charge for maximum battery life 2 6 2 ATTITUDE INDICATOR No periodic scheduled maintenance or calibration is necessary 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 J September 1 2009 Manual Number 9015762 Page 15 of 22 Mid Continent Instruments Wichita KS 411 Configuration sho WA Note 1 Recommended Circuit Breaker 2 Amp fo for 2 Recommended AWG mini mum A L A lt 2 or 14VDC aircraft and 1 L 6 4L lt max up i 4 E 2 2 112 4 4 5 d E x Sec 1 6 CG Figure 2 1 Outline Drawing Rev J September 1 2009 Manual Number 9015762 Page 16 of 22 Mid Continent Instruments Wichita KS l M i zx A T 1 l f lt Figure 2 3 Front Mount Panel Cutout Dimensions Rev J September 1 2009 Manual Number 9015762 Page 17 of 22 Mid Continent Instruments Wichita KS
9. 4 Cover Glass HEA anti reflective coated Instrument Panel Mounting Rear mount Front mount with adapter plate Table 1 2 Rev J September 1 2009 Manual Number 9015762 Page 6 of 22 Mid Continent Instruments 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 P N 9015640 5V 14V Blue White 1 2 White 4 5 Red 7 8 Table 1 4
10. MID CONTINENT nor EM INSTALLATI ON MANUAL AND OPERATI NG I NSTRUCTI ONS 4300 XXX Series Electric Attitude Indicator With Battery Backup MID CONTINENT INST CO INC MANUAL NUMBER 9015762 Mid Continent Instruments Wichita KS Table of Contents Page 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 11 2 1 General 11 2 2 Pre Installation Inspection 11 2 3 Parts 12 2 3 1 Included Parts 12 2 3 2 Installer Supplied Parts 12 2 3 3 Additional Optional Parts 12 2 4 Equipment Location 12 2 5 Installation 13 2 6 Continued Airworthiness 14 Section 3 Operation 19 3 1 General 19 3 2 Starting Procedures 19 3 3 In Flight Procedures 19 3 4 Dynamic Errors 19 3 5 Standby Battery Operation 20 3 6 Equipment Limitations 22 Figure No List of Illustrations 1 1 Display Configurations 8 1 2 Typical Indicator Display Detail 10 2 1 Outline Drawings 16 2 2 Rear Mount Cutout Dimensions 17 2 3 Front Mount Cutout Dimensions 17 2 4 Remote Mount Standby Battery Option with 9015671 Kit 18 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 Table 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 J September 1
11. bolic airplane Adjustment Knob Typical Electric Attitude I ndicator Display Rotating Roll Dial Fixed Roll Pointer Traditional Wing Symbolic Airplane Shown Figure 1 2 Rev J September 1 2009 Manual Number 9015762 Page 10 of 22 Mid Continent Instruments Wichita KS Section 2 Installation 2 1 General This section contains mounting electrical connections 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 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 B 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 C 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 sta
12. e 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 available 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 J September 1 2009 Manual Number 9015762 Page 12 of 22 Mid Continent Instruments 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 Referto Figure 2 1 for installation dimensions and electrical information B Ensure the available instrument panel cutout meets the requirements of the indicator See Fig 2 2 for details C 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
13. e 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 Rev J September 1 2009 Manual Number 9015762 Page 5 of 22 Mid Continent Instruments Wichita KS 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 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 switch to the Power Loss Warning mode If the STBY PWR button on the face of the instru
14. elerated 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 80 g 100 oo 80 E 40 8 60 20 E 40 0 20 20 10 0 10 20 30 40 50 E 1 Temperature C 5 p o a Fig 2 6 Effect of Low Temperature Fig 2 7 Life Characteristics On Standby Battery Capacity In Standby Use Rev J September 1 2009 Manual Number 9015762 Page 22 of 22
15. ely 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 start flashing indicating unit has latched into Battery Test Mode The test runs for approximately one minute during which time the amber LED flashes continuously and either a red or green light is displayed under the word TEST 3 Visually monitor the test lights until the amber LED stops flashing 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 light 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
16. mally occur only if the unit is turned off or after the internal standby battery is exhausted 1 3 Functional Description Model 4300 XXX 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 XXX 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 absent with the unit in either power loss warning mode or turned off pushing the STBY PWR button will put the unit into the standby power mode The instrument will run from standby power until the internal battery is exhausted If the unit is already 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 input voltag
17. ment is not pushed before the end of the nominal one minute timing period the instrument will turn itself off and the gyro warning flag will appear If the STBY PWR button is pushed the gyro will run from standby power until the internal battery is exhausted before the gyro warning flag appears 1 5 Options and Configurations 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 Specifications Physical Characteristics Qualification FAA TSO C4c Environmental Qualification RTCA DO 160D Environmental Category CIBAB SBM RBB1 P XXXXXXZZAZZ WF M 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 901551
18. ning 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 In the 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 exceed 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 cor
19. 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 20 a p 18 m m A 16 a 7 14 30 60 Discharge Time min Fig 2 5 Nominal Battery Discharge Rate at 20 C Rev J September 1 2009 Manual Number 9015762 Page 21 of 22 Mid Continent Instruments 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 XXX series Electric Attitude Indicator with Battery Backup in order to be approved 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 acc
20. or removed from the installation and maintained on a charger C If the 4300 XXX 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 l Keep the battery plugged into the 4300 Electric Attitude Indicator Run the unit overnight 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 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
21. rected by the actuation of the caging system Rev J September 1 2009 Manual Number 9015762 Page 19 of 22 Mid Continent Instruments Wichita KS 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 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 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 A Normal Flight At loss of external power an amber LED will flash indicating a Power Loss Warning With no further action from the pilot the unit will turn off automatically gyro flag in view after approximately one minute This is to prevent battery discharge at the end of a flight when the master power switch is placed in the off position B Loss of Aircraft Power When the instrument swi
22. rt 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 D 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 helps ensure possible reuse 2 2 Pre installation 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 B 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 C CAUTION The unit is shipped with the battery cable disconnected to prevent inadvertent operation of the indicator during shipping If 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 J September 1 2009 Manual Number 9015762 Page 11 of 22 Mid Continent Instruments Wichita KS 2 3 Parts 2 3 1 Included Parts A
23. tches to Power Loss Warning the amber LED flashes for approximately one minute 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 Pushing the STBY PWR button on the face of the instrument will allow the unit to continue operating on the standby battery for nominally one 1 hour or until the battery is exhausted See Fig 2 5 for more information on battery discharge rate The gyro warning flag remains out of view which indicates the gyroscope is valid and running on standby battery power An independent standby dial lighting system also operates in this mode Any time aircraft power is absent with the unit in either Power Loss Warning or shut off pushing the STBY PWR button will put the unit in the standby power mode The instrument will run from standby power until the standby battery is exhausted If the unit is running on the standby battery pushing the STBY PWR button will turn the unit off Pushing the STBY PWR button again will restore standby power and standby lighting Restoring aircraft power will clear any standby operation and resume automatic battery charging Rev J September 1 2009 Manual Number 9015762 Page 20 of 22 Mid Continent Instruments 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 approximat
24. te DO 160 qualification in section 1 6 from SBM RBB1 to L SBM RBB1 P Rev J September 1 2009 Manual Number 9015762 Page 4 of 22 Mid Continent Instruments Wichita KS Section 1 General Description 1 1 Purpose of Equipment The Model 4300 XXX 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 XXX 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 drops into view This will nor
25. 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 Sect 2 6 1D Rev J September 1 2009 Manual Number 9015762 Page 13 of 22 Mid Continent Instruments Wichita KS 2 6 Continued Airworthiness 2 6 1 BATTERY A 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 x NOTE The standby battery contains lead Do not dispose of in local Po landfills or other environmentally sensitive areas Ye Vs NOTE Recycle the battery in accordance with state and local WERE regulations For recycle locations visit www rbrc com or call 1 aes 800 8 BATTERY 1 800 822 8837 B In normal use the 4300 XXX 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
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