INSTALLATION MANUAL AND OPERATING
Contents
1. INSTALLATION MANUAL AND OPERATING INSTRUCTIONS 4200 Series Electric Attitude Indicator ue gt L r LL S A MID CONTINENT INST CO INC MANUAL NUMBER 9016182 Section 1 Figure No 1 1 NN Fe NF N Rev D September 1 2009 Mid Continent Instruments Wichita KS Table of Contents General Description Purpose of Equipment Physical Description Functional Description Gyro Warning Flag Options and Configurations Specifications Installation General Pre Installation Inspection Parts Included Parts Installer Supplied Parts Equipment Location Installation Continued Airworthiness Operation General Starting Procedures In Flight Procedures Dynamic Errors List of I Illustrations Display Configurations Typical Indicator Display Detail Outline Drawing Panel Cutout Dimensions List of Tables Options Table Physical Characteristics Performance Manual Number 9016182 Page O U UI UI UI UI anu Page 3 of 15 Mid Continent Instruments Wichita KS Revision Detail ECO Rev Date Detail A 08 22 05 Initial Release 4535 B 02 03 06 Table 1 3 Update power rating 4956 C 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 2 as indicated on the unit nameplate2. 5270 D 09 01 09 Remove Equipment Limitations Section 3 5 Rev D September 1 2009 Manual Number 9016182 Page 4 of 15 Mid Continent Instruments Wichita KS Section 1 General Description 1 1 Purpose of Equipment The Model 4200 Electric Attitude Indicator 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 a special configuration available to match electronic flight displays The lighting voltage is user selectable and the input voltage can range from 10 to 32 VDC Panel tilt is an option specified at the time of the order 1 2 Physical Description The 4200 Electric Attitude Indicator 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 4200 s erection system or by pulling the PULL TO CAGE knob A warning flag pops into view to indicate that the gyro motor is not receiving sufficient power to operate 1 3 Functional Description Model 4200 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
3. 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 slide with locking screw 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 symbolic airplane to remove parallax errors Adjustment Typical Electric Attitude I ndicator Display 4200 10 configuration shown Figure 1 2 Rev D September 1 2009 Manual Number 9016182 Page 8 of 15 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 The conditions and tests required for the TSO approval of this article are minimum performance standards It is the responsibility of those installing 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 TSO articles must have a separate approval installation in an aircraft The article may be installed only if performed under 14 CFR Part 43 or the applicable airworthin
4. allation 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 2 5 Installation NOTE Before installing unit verify the option label on the unit matches the aircraft requirements for panel tilt Install the Electric Attitude Indicator within the aircraft in accordance with the aircraft manufacturer s instructions and the following steps A Refer to Figure 2 1 for installation dimensions and electrical information The recommended circuit breaker size is 2A The minimum wire size is 22 AWG B Locate the lighting voltage switch on the rear of the unit If required switch the lighting voltage to the aircraft lighting bus voltage Using a small pointed object push the switches to select the lighting voltage per Fig 2 1 C Ensure the available instrument panel cutout meets the requirements of the indicator See Fig 2 2 for details D Attach aircraft electrical system cable to indicator connector and insert the indicator into the instrument panel cutout Rev D September 1 2009 Manual Number 9016182 Page 10 of 15 Mid Continent Instruments Wichita KS E 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 facil
5. als should be retained for use should the attitude indicator require future shipment B Inspect for Damage Inspect the shipping container and attitude 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 Rev D September 1 2009 Manual Number 9016182 Page 9 of 15 Mid Continent Instruments Wichita KS 2 3 Parts 2 3 1 Included Parts A Model 4200 Electric Attitude Indicator B Mating Connector MS3116F8 4S or equivalent P N 9015514 C Installation Manual P N 9016182 2 3 2 Installer Supplied Parts A 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 CAUTION Do not exceed 1 2 screw depth into bezel 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 inst
6. ess requirements 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 start to spin If gimbal lock occurs while the rotor is turning the gimbal may spin fast enough to damage the gimbal bearings requiring 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 materi
7. f 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 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 corrected by the actuation of the caging system Rev D September 1 2009 Manual Number 9016182 Page 14 of 15 Mid Continent Instruments Wichita KS B Acceleration amp Deceleration Errors Pitch 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 Rev D September 1 2009 Manual Number 9016182 Page 15 of 15
8. 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 Indicator requires 10 to 32 VDC input voltage The lighting system features internal LEDs that operate on a user selectable 5V 14V or 28V input from the aircraft lighting bus 1 4 Gyro Warning Flag A power warning circuit monitors the electrical current used to power the gyro motor When a loss of input voltage occurs the gyro warning flag comes into view 1 5 Options and Configurations Options Table Panel Tilt Calibration 0 to 20 set to customer requirements Symbolic Airplane Part Number Specific Traditional or Delta Mating Connector 9015514 MS3116F8 4S Table 1 1 Rev D September 1 2009 Manual Number 9016182 Page 5 of 15 Mid Continent Instruments Wichita KS 1 6 Specifications Physical Characteristics Qualification FAA TSO C4c Environmental Qualification RTCA DO 160D Environmental Category C1BABXXXXXXXZZAZZ WFIM A3H33 XXA Weight 1 6 Ibs Dimensions Length behind panel not including mating connector 5 94 inches long maximum 2 39 inches high maximum 2 39 inches wide maximum Mating Connector MS3116F8 4S or equivalent MCI P N 9015514 Cover Glass HEA anti reflective coated Instrument Panel Mounting Rear mount Table 1 2 Performance 2500 Hour Mea
9. ity is responsible for supplying appropriate installation hardware F Apply the correct input power to the indicator G The Power Indicator Flag red will be out of view H Check to determine that the indicator internal lighting is working correctly This indicator requires the main power to be on for the lighting to work The indicator lighting will not work when just the lighting bus is turned on 2 6 Continued Airworthiness No periodic scheduled maintenance or calibration is necessary for continued airworthiness of the 4200 series Electric Attitude Indicator If the unit fails to perform to specifications it must be removed and serviced by a qualified service facility Rev D September 1 2009 Manual Number 9016182 Page 11 of 15 Rev D September 1 2009 Mid Continent Instruments Wichita KS Figure 2 1 Outline Drawing Manual Number 9016182 Page 12 of 15 Mid Continent Instruments Wichita KS Figure 2 2 Panel Cutout Dimensions Rev D September 1 2009 Manual Number 9016182 Page 13 of 15 Mid Continent Instruments Wichita KS Section 3 Operation 3 1 General This section describes the Model 4200 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 4200 display and a table describing indicator functions 3 2 Starting Procedures The following operational proced
10. n Time Between Failure MTBF 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 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 Symbolic Airplane The adjustment range will be 4 minimum from the zero pitch position Power Rating Starting Will not exceed 1 4A at 14 VDC Will not exceed 0 6A at 28 VDC Running 0 37 0 51 at 14 VDC 0 18 0 25 at 28 VDC Table 1 3 Rev D September 1 2009 Manual Number 9016182 Page 6 of 15 Mid Continent Instruments Wichita KS Figure 1 1 Display Configurations Rev D September 1 2009 Manual Number 9016182 Page 7 of 15 Mid Continent Instruments Wichita KS Roll Pointer Indicates aircraft roll displacement relative to a rotating roll dial Power Indicator Flag f loss of input voltage should occur power indicator 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
11. ures are recommended when preparing the indicator for use CAUTION THE INDICATOR MAY BE DAMAGED IF THE PULL TO CAGE KNOB IS RELEASED WITH A SNAP RELEASE PULL TO CAGE KNOB AVOI DING 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 Warning flag red will pull out of view Also allow three minutes for presentation stabilization B For trim adjustment use a 5 64 hex drive wrench to loosen the lock screw Slide the screw up or down in the slot to the desired pitch attitude presentation aligning the symbolic airplane with the horizon and retighten the screw 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 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 symbolic airplane to obtain desired pitch attitude presentation after take of
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