N27702

Part: TRANSMITTER — FAILED (FUEL SYSTEM)

FUEL GAUGE READS ZERO.

Part: REGULATOR — FAILED (AC SYSTEM)

GENERATOR DROPPING OFF LINE.

Part: TRANSCEIVER — FAILED (COCKPIT)

TRANSCEIVER UNREADABLE WHEN TRANSMITTING. FOUND NO MODULATION AND UNIT DRAWING 4-5 AMPS OF CURRENT WHEN VOLUME WAS TURNED UP. REPLACED TRANSMIT BRACKET AND T702 TRANSFORMER. REPAIRED BOTH PROBLEMS. ADJUSTED C/N SQUELCH, SIDETONE AND MODULATION. FOUND GUIDE PIN ON REAR CONNECTOR BROKEN.

Part: ENCODER — FAILED (COCKPIT)

ENCODER HAS NO VALID OUTPUT.

Part: REGULATOR — FAILED (DC SYS)

VOLTAGE WILL NOT STAY SET.

Part: VOLT REGULATOR — FAILED (DC SYS)

UNABLE TO ADJUST VOLTAGE WON'T STAY SET.

Part: PUMP — WORN (ENG FUEL)

FUEL PUMP EXCESSIVELY WORN DRIVE SHAFT DRIVE SPLINES AND INNER GEARS.

Part: INDICATOR — READS LOW (COCKPIT TOT)

TOT READING 10 TO 20 DEGREES LOW.

Part: VOLT REGULATOR — FAILED (DC SYS)

FLUCTUATING LOAD METER.

Part: LINK ASSY — SEPARATION (M/R XMSN)

LINK ASSY SEPARATION IN ELASTOMER.

Part: INDICATOR — INOPERATIVE (FUEL QTY)

NO FUEL INDICATION.

Part: TRANSMITTER — FAILED (FUEL QTY)

FUE QTY GAUGE NO FUEL INDICATION.

Part: TRANSMITTER — FLUCTUATES (FUEL QTY)

FUEL TRANSMITTER FLUCTUATES 300 TO 1000 LBS. IN FLIGHT.

Part: TRANSMITTER — FAILED (FUEL QTY)

WHILE CHECKING CALIBRATION BY FUELING AIRCRAFT TRANSMITTER QUIT AT 400 LBS OF FUEL. COMPLETELY DEAD. COULD NOT GET GAUGE TO MOVE EVEN WITH A JUMPER IN CALIBRATION PORTS. NOTE: CALIBRATION PROCEDURE WITH EMPTY TANK HAD WORKED GREAT. ALSOCALIBRATION CORRECT UP TO THE TIME IT QUIT AT 400 LBS.

Part: ALT ENCODER — ERRATIC (COCKPIT)

ENCODER ERRATIC OUTPUT AND WILL NOT CALIBRATE.

Part: TRANSMITTER — FAILED (FUEL SYS)

TRANSMITTER WILL NOT INDICATE ABOVE ZERO. SENT TIME SINCE REPAIR 0:00.

Part: TRANSPONDER — MALFUNCTION (COCKPIT ATC)

REPORTED AS WEAK AND INTERMITTENT. FOUND POWER OUT LOW, PHOTOCELL BAD AND R477 RESISTOR DETERIORATED. REPLACED V101 CAVITY OSC., V301 PHOTOCELL, R477 RESISTOR. REPAIRED. ALSO REPLACED MISSING PHOTOCELL LENS. REPAIRED. BENCH CHECK GOOD.

Part: GEARSHAFT — STEP WEAR (SPUR ADAPTER)

ENGINE REMOVED DUE TO METAL IN OIL. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: STEP WEAR BEYOND SERVICEABLE LIMITS ON SHAFT AFT SPLINES. INSTALLED A USED SERVICEABLE PART.

Part: TRANSMITTER — FAILED (FUEL PRESS)

FUEL PRESS TRANSMITTER WILL NOT INDICATE ABOVE ZERO. TIME SINCE REPAIR 0:00.

Part: INDICATOR — DEFECTIVE (GP RPM)

INDICATOR SLOW AND STICKING BETWEEN 0 TO 20%.

Part: WHEEL — DAMAGED (3RD STAGE)

ENGINE REMOVED DUE TO LOUD ROAR AND WHINE FOLLOWED BY ENGINE CHIP LIGHT. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: RIM BREAKOUT OF 1 3/4" AND 1/4" OF THREE EACH BLADES ON 3RD STAGE WHEEL. SUSPECT CAUSE OF FAILURE TO BE A STRESS CRACK ORIGINATING ON THE LEADING EDGE SIDE OF BREAKOUT IN REFERENCE TO DIRECTION OF ROTATION, ON THE TRAILING EDGE OF RIM SHROUD AND PROGRESSED APPROXIMATELY 1/2 OF CHORDAL LENGTH UNTIL OVERLOAD. SECONDARY DAMAGE - P.T. SECTION EXHIBITSEXCESSIVE F.O.D., KNIFE AND SEAL CONTACT AND BEARING AREA DAMAGE.

Part: WHEEL — RIM BREAK OUT (TURB 3RD STAGE)

LOUD ROAR AND WHINE FOLLOWED BY ENGINE CHIP LIGHT. TEAR DOWN INSPECTION REVEALED 3RD STAGE WHEEL EXHIBITED RIM BREAK OUT OF 1.75 INCH AND .25 INCH OF 3 EACH BLADES. SUSPECT CAUSE OF FAILURE TO BE A STRESS CRACK ORIGINATING ON THE LEADING EDGE SIDE OF BREAK OUT IN REFERENCE TO DIRECTION OF ROTATION, ON THE TRAILING EDGE OF RIM SHROUD AND PROGRESSED APPROXIMATELY ONE-HALF OF CHORDAL LENGTH UNTIL OVERLOAD. POWER TURBINE SECTION EXHIBITS EXCESSIVE KNIFE AND SEAL CONTACT, FOD, AND BEARING AREA DAMAGE. TOTAL CYCLES, 1,140.

Part: SEAL — LEAKING (OIL NOZZLE "T")

PILOT REPORTED A FIRE IN ENGINE COMPARTMENT. THE FIRE FLASHED, THEN EXTINGUISHED. INVESTIGATION REVEALED OIL LEAK AT 6 & 7 OIL NOZZLE "T" FITTING. REPLACED SEAL ASSEMBLY AND RETURNED ENGINE TO SERVICE.