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Summary of Contents for Nav-O-Matic 400A

Page 1: ...ility problems it is recommended that SK421 46 be installed at the next convenient inspection period PARTS INFORMATION SK421 46 can be obtained through the Cessna Dealer Organization at a suggested list price of 3 10 A REMARKS While the above change is a beneficial improvement proper service and maintenance continues to be the most important means of insuring maximum performance and reli ability o...

Page 2: ...tude gyro Measure actuator clutch torque 28953 SK402 22 Adapter Torque Connector Kit 5 3 PERFORMANCE TEST AND ADJUSTMENT PROCEDURES Generally the 400A Nav O Matic units are ready for installation if all the adjustments outlined in Preinstallation Adjustments paragraph 2 1 can be accomplished In the event that operation in the air craft is unsatisfactory the best method for trouble shooting is by s...

Page 3: ...er supply and troubleshoot or re place autopilot control unit AUTOPILOT ENGAGE SWITCH WILL NOT ENGAGE ROLL AXIS ENGAGES PITCH AXIS WILL NOT ATTEMPT TO SYNCHRONI ZE AUTOPILOT WILL NOT DISEN GAGE WHEN DISENGAGE SWITCH ON PILOT S CONTROL WHEEL IS ACTUATED ERRATIC PITCH AND ROLL OPERATION AIRCRAFT ROLLS RIGHT AND PITCHES DOWN ABRUPTLY 10 Volt AC power supply in computer is malfunctioning 6 Volt power ...

Page 4: ...tting Refer to Section 2 alignment procedures and align Defective rol 1 Check A 3 and A 1 ROLL MODES FUNCTIONING BUT AIRCRAFT BANKS MORE OR LESS THAN 25 WHEN TURN COMMAND KNOB IS FULL LEFT OR RIGHT OR TO INTERCEPT A NEW HEADING IN HEADING MODE ROLL COMMAND INOPERATIVE HEADING MODE INOPERATIVE Def Heading engage switch or cir ruitry in control unit inopera tive Refer to Section 2 and perform in fli...

Page 5: ...o Section 2 check trim sensor time delay adjust or replace pitch trim sensor as necessary Refer to Section 2 Table 2 1 and adjust actuator for proper torque Pitch actuator cable tension set too low Refer to applicable aircraft ser vice manual and adjust cable tension PITCH MODES FUNCTION BUT ARE SLUGGISH AND OR ERRAT IC ABRUPT PITCH CHANGES INITIATED BY THE PITCH ACTUATOR PITCH TRIM WHEEL DOES NOT...

Page 6: ...TITUDE SWITCH IS HELD ENGAGED MANUALLY ALTITUDE HOLD MODE WILL NOT ENGAGE MANUALLY HOLDING CAUSES NO CHANGE IN AIRCRAFT PITCH ATTITUDE ALTITUDE HOLD POOR AIR CRAFT PORPOISES OR TAKES EXCESSIVE TIME TO REACH SELECTED ALTITUDE Trim sensor inoperative or elec trical connector not connected Defective trim actuator Defective altitude sensor in computer Pitch synchronization in com puter needs alignment...

Page 7: ...NGLE IS NOT THE REQUIRED 45 2 DEGREES FAILS TO CAPTURE AND TRACK VOR RADIAL Right and left intercept adjust ment pots in computer out of adjustment Incorrect heading source voltage to computer Refer to Section 2 and adjust intercept angle Verify heading source voltage is 158 millivolts per degree Add or delete resistance in RJB1 to obtain proper voltage Repair or replace A 5 roll radio module Defe...

Page 8: ...ct attitude gyro and heading gyro Set the calizer enable switch to OUT and set the glide lope disable to OUT push in the heading knob and djust the roll trim until TP 15 is less than 5 mV Heading Demod Refer to Figure6 1 Sheet 2 for Computer Serialization Adjust A3R48 until TP 21 is less than 10 mV DC Heading Amplifier Adjust A3R10 A3R2 until TP 22 is less than 10 mV DC Roll Amplifier Disconnect p...

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