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Kc 192 Replacement

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KFC 150
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  Date:Mar/97IB #385Rev. 4:Apr/04P/N:600-09385-0004Page 1 of 4  Installation Bulletin BULLETIN NO:  385 APPLICABLE TO: KAP 150 and KFC 150 Flight Control Systems SUBJECT:  Approval of replacement part numbers for KC 191 and KC 192Flight Computers in existing installationsThe new generation of the KC 191 and KC 192 Flight Computers has updated circuitcomponents with newer technology. The new KC 191 P/N 065-0054-15 is a direct replacement for any of the following partnumbers: 065-0054-00065-0054-05065-0054-01065-0054-06065-0054-02065-0054-07065-0054-03065-0054-09065-0054-04065-0054-12The new KC 192 P/N 065-0042-15 is a direct replacement for any of the following partnumbers:065-0042-00065-0042-05065-0042-01065-0042-06065-0042-02065-0042-07065-0042-03065-0042-09065-0042-04065-0042-12The Annunciator Dimming Adjust has been moved from the side of the unit to the faceof the unit, below the hold down screw. The adjustment is labeled BL (Brightness of Lamps).The Adapter Modules used in the following certifications remain unchanged, and willfunction exactly the same with the new flight computers. As always, refer to theapplicable STC Installation Manual for the proper Adapter Module part numbers thatapply to your specific aircraft and flight control configuration.  Date:Mar/97IB #385Rev. 4:Apr/04P/N:600-09385-0004Page 2 of 4  A gyro alignment procedure is included with this install bulletin and should be followedwhen aligning the KFC/KAP 150 Flight Control System. NOTE Before aligning a KFC/KAP 150 Flight Control System with an updated KC191 or KC 192, check the mod status of the KI 256 to see if Mod 11 has beenincorporated into the unit. Without Mod 11 installed, you might not be able toalign the KI 256 with the updated KC 191 or KC 192 due to incompatibilityissues between the units. This installation bulletin is approved for incorporation in the following aircraft inconjunction with the following STCs: AIRCRAFTSTC Beechcraft A36, A36TC, B36TCSA1574CE-DBeechcraft F33ASA1789CE-DCessna 172N, 172P, 172QSA1570CE-DCessna 172RGSA1568CE-DCessna 182P, 182Q, 182R, T182SA1770CE-DCessna F182P, F182QSA1794CE-DCessna R182, TR182SA1571CE-DCessna FR182 SA1783CE-DCessna U206G, TU206GSA1569CE-DCessna 208, 208A, 208BSA2053CE-DCessna 210R, T210RSA2050CE-DConsolidated Aeronautics Lake 250SA2069CE-DGulfstream Aerospace AG-5BSA00058WI-DMooney M20J, M20KSA1561CE-DMooney M20LSA2074CE-DMooney M20M, M20RSA2319CE-DPartenavia AP68TP 300, AP68TP 600SA1784CE-DPartenavia P 68C, P 68C-TCSA1791CE-DPiper PA-28-161, PA-28-181, PA-28-236SA1565CE-DPiper PA-28R-201, PA-28R-201TSA1563CE-DPiper PA-28RT-201, PA-28RT-201TSA1563CE-DPiper PA-32-301, PA-32-301TSA1567CE-DPiper PA-32R-301, PA-32R-301TSA1572CE-DPiper PA-34-200T, PA-34-220TSA1575CE-DPiper PA-44-180SA2321CE-DPiper PA-46-310P, PA46-350PSA1778CE-DPiper PA-60-700PSA1777CE-DSOCATA TB 10, TB 20SA1785CE-D  Date:Mar/97IB #385Rev. 4:Apr/04P/N:600-09385-0004Page 3 of 4 11.1.3GYRO ALIGNMENT PROCEDURES   The following system alignment is required in the KFC/KAP 150 System: A. Remove the KC 191/192 Computer from the airplane panel. Connectthe computer to the autopilot tester with the cables provided.B. Mount the gyro in the gyro tilt stand. Place the tilt stand in aconvenient location with reference to the autopilot computer. Level thetilt stand using the twist adjust knobs and bubble level. Connect thegyro air input to a regulated 4.5 in. Hg. source. Connect the KI 256/KG258 Flight Command Indicator to the airplane harness using gyroextender cable. NOTE  A properly regulated and filtered air source is essential for correct gyro operation. NOTE When making gyro alignment adjustments, always havegyro set to zero in axis not under test.C. Before applying power, make sure that the proper adapter boards areinstalled in the KC 191/192 by checking the part numbers in thewindows on the top and bottom of the unit. Refer to the system partslist for the correct numbers. Apply power to the system. All associatedcircuit breakers must be installed and activated.D. After the gyro is fully erected (ten minutes minimum run-up time),proceed with the following.E. Set the gyro stand to zero in both pitch and roll axis. Adjust levelingscrews for pitch and roll zero visual indication. NOTE It is normal for the gyro to drift during testing. To minimizeerror due to drift, it is advisable to tilt the gyro and makethe scale factor adjustment quickly. After each adjustment,return the tilt stand scales to zero and, if necessary, resetelectrical zero by adjusting the leveling screws on the gyrotilt stand.F. Adjust R401, Roll Null Adjust for 0.0 VDC. This is a potentiometer thatis accessible through the hole labeled RN in the front of the computer.Measure the voltage from J19X1 (22) to the signal ground J19X2 (10)with a digital voltmeter when making this adjustment.  Date:Mar/97IB #385Rev. 4:Apr/04P/N:600-09385-0004Page 4 of 4 NOTE Pitch null has been deleted.G. Tilt the gyro to a twenty-degree right bank using the gyro tilt stand. Adjust R1211, accessible through the hole labeled RDG on the rightside of the computer, for -4 ±  0.2 VDC. Measure the voltage at J19X1(22) with respect to signal ground.H. Tilt the gyro to a twenty-degree left bank using the gyro tilt stand.Measure the voltage at the same point as Step H. It should read 4 ± 0.2 VDC.   If the reading in Step H exceeds +4.2 VDC, repeat Step G and reducethe gain by one-half the amount exceeded in Step H. If Step Hmeasured less than 3.8 VDC, repeat Step G and increase the gainsetting by one-half the amount short in Step H. Repeat until there is abalance between left and right bank. The proper total voltageexcursion should be 8 ±  .4 VDC.I. With the gyro test stand in the zero pitch position, adjust the levelingscrews on the test stand to obtain a pitch zero visual indication on thevertical gyro. (Horizon Line aligned with 90 °  index marks.)J. Measure the voltage from J19X1 (2) to signal ground with a digitalvoltmeter for reference.K. Tilt the gyro ten degrees nose-up on the tilt stand, and adjust R1212potentiometer, located on the right side of the computer through thehole labeled PDG, for -2 ±  0.1 VDC from the Pitch Reference Voltageas measured in step J. Measure the voltage at J19X1 (2) to signalground.L. Tilt the gyro ten degrees nose-down on the tilt stand. The meter should read +2 ±  0.25 VDC from the Pitch Reference Voltage (J) at thesame point as Step K. If the meter exceeds +2.25 VDC, repeat Step Kand reduce the gain by one-half the amount exceeded in Step L. If themeter reads less than +1.75 VDC, repeat Step K and increase the gainby one-half the amount short in Step L. FAA APPROVAL: The data contained herein have been reviewed by a representativeof the Federal Aviation Administration (FAA) and found to complywith all applicable Federal Aviation Regulations. This installationbulletin is FAA-approved, and its contents may be incorporated intothe subject aircraft.
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