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  • Mark replied to the topic ATA 33-40, Logo Lights in ATA 33 Lights
    Both lights will be inop if you pull the inner assembly and see "this".

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  • Mark created a new forum post in ATA 33 Lights
    There are two logo lights installed on each side of the horizontal stabilizer. The inner light has a step-down transformer incorporated in the assembly. This transformer takes the 115VAC input down to 13VAC which is used by the lights themselves.



    The outer light is wired across to the inner assembly's transformer for its 13VAC power.



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  • The system incorporates a couple of in-line filters used on both the sensor signal output and ground wires.



    The filters are a capacitor wired to ground on one leg and an inductor wired in series. They are located in the stabilizer jackscrew area at rear of aircraft.




    We had an aircraft with quite a history of the left elevator position indication being intermittent. A sensor change did not correct the issue. It turned out to be the output signal filter that was causing the problem.

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  • Mark created a new forum post in ATA 27 Flight Controls
    Intermittent EICAS failure warning of the Auto-Speedbrake system.



    Found an associated relay K218 (P33 Panel) that had a bad coil. It would act like a car blinker. The coil got hot and went open. It would cool down again and activate the relay.



    767-300 WDM 27-62-11
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  • We found a bad "X1" pin on relay K513 (actually a bad crimp on the wire). K513 never energized. This kept the original ground path for relay K505 out of the circuit and K505 never energized. The DC pump remained running at all times.

    Pressing on the relay made it energize

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  • Mark created a new forum post in ATA 28 Fuel Systems
    The APU auto-fuel feed system is designed to have the left forward fuel boost pump supply fuel to the APU. This is noted as the "PRESS" light being not illuminated on the switch without the switch being pushed in.

    Fuel pump panel on ground service power.




    The system uses K505 as the controlling relay. If K505 is relaxed (not energized), 28VDC is supplied to the coil of relay K191 (APU DC Pump control) and the APU DC Pump supplies the APU.



    With the aircraft on the ground and "C" phase of the left forward pump three phase breaker being sensed, a time delay relay K512 will be powered. The relay takes 10 seconds to energize after power is applied. With K512 still in a relaxed state, a ground is provided to the coil of relay K505 and it energizes. This provides power to the left forward pump three phase contactor and the pump comes on. A new ground path for the coil of K505 is provided via the pump's low pressure switch. K512 will energize and remove the original ground from K505. As long as the pressure switch's ground is present, K505 will stay energized. Power is removed from the DC pump controlling relay and it turns off. If for any reason (left forward pump failure or bad pressure switch) the ground keeping K505 energized will go open. K505 will then relax and the DC pump will come back on.

    K512



    Two additional relays play a part in K505's coil ground path. K529 Air/Ground and K513 Left Forward Pump Breaker "C" phase power.


    K513



    These drawings are somewhat confusing, but hopefully the power flow of the system can be understood. There is a ton more aspects to this circuit, but the basic premise of how things work is depicted.

    K505 relaxed and DC Pump on.



    K505 energized. Left Forward Pump on, DC Pump off.



    767-300 ASM 28-25-01
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  • Basic shot of sensor. It can be accessed via a inboard panel under the horizontal stabilizer.



    Test plug. Left tunnel, on forward EICAS rack.


    Two bolts hold sensor into mount. One of which slides through grove shown in this image.



    The sensor comes with a basic "null" line scribed or marked on the face. There is one mechanical stop pin. Adjustment of the actual null needs to be accomplished on the aircraft with the flight control faired.

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