N911RX

ATA 2612

Part: FIRE DETECTOR — FALSE INDICATION (ZONE 400) · airframe 13,438 hrs · 17,510 cycles

DURING CRUISE FLIGHT LEFT ENGINE FIRE WARNING LIGHT ILLUMINATED, DETERMINED NO FIRE EXISTED, LANDED AIRCRAFT OAKLAND IAP. MAINTENANCE DETERMINED FIRE DETECTOR WAS MALFUNCTIONING REPLACED THE LOWER NR 1 ENGINE FIREWALL DETECTOR SYSTEM OPERATIONAL TESTS SATISFACTORY.

ATA 2697

Part: ELEC CONNECTOR — LOOSE (ZONE 200) · airframe 13,173 hrs · 11,742 cycles

DURING FLIGHT LEFT ENGINE FIRE WARNING LIGHT ERRATICALLY FLASHES. ELECTED TO PRECAUTIONARY LAND BACK TO BASE. MAINTENACE DISCOVERED LOOSE FIRE DETECTION AMPLIFIER CONNECTOR BACKSHELL

ATA 3240

Part: BRAKE ASSY — LEAKING (MLG) · airframe 5,117 hrs

DURING LANDING ROLL-OUT AND AFTER UTILIZING BETA OR DISCING TO SLOW THE ACFT DOWN TO TAXI SPEEDS, I SWITCHED TO WHEEL BRAKING AND THERE WAS NO PRESSURE ON THE LT SIDE. GROUND CONTROL WAS ABLE TO CLEAR ME TO THE SIGNATURE RAMP AREA WITHOUT REQUIRING A FULL-STOP AFTER CLEARING THE RUNWAY, SO I KEPT THE ACFT MOVING TOWARDS THE RAMP. PRIOR TO ENTERING THE RAMP AREA, UTILIZED THE ACFT PARKING BRAKE WITH A LITTLE REVERSE TO STOP THE ACFT. THEN PROCEEDED FWD ABOUT 100 FT INTO THE RAMP AREA TO CLEAR THE REMAINING TAXI AREA AND ACCESS ROAD AND STOPPED THE ACFT IN THE MIDDLE OF THE RAMP AND SHUTDOWN. WOULD BE UNABLE TO PARK THE ACFT AS THE MARSHALLER DESIRED DUE TO THE BRAKING ISSUE. AFTER SHUTDOWN, I SPOKE WITH THE MARSHALLER TO EXPLAIN WHY I COULDN'T COMPLY WITH HIS DIRECTIONS AND INFORMED HIM THAT WE WOULD NEED TO TOW THE ACFT INTO A PARKING POSITION AFTER OUR PATIENT WAS ON THE WAY TO THE HOSPITAL.

ATA 6420

Part: BEARING — FAILED (T/R SWASHPLATE)

DURING THE PRE-FLIGHT INSPECTION, THE SEAL OF THE DUPLEX BEARING WAS OBSERVED TO BE DETACHED FROM THE BEARING. DISASSEMBLY SHOWED A TOTAL LOSS OF LUBRICANT AND SEVERAL BALLS MISSING FROM THE OUTER DUPLEX BEARING.

ATA 6310

Part: SHAFT ASSY — DAMAGED (XMSN DRIVE)

DURING THE ENGINE 100-HOUR INSPECTION, DAMAGE TO THE ENGINE TO TRANSMISSION DRIVE SHAFT WAS OBSERVED. THE DAMAGE WAS FULL CIRCUMFERENCE AND WAS CAUSED BY CONTACT WITH THE FIREWALL. THE SHAFT PASSES THROUGH TWO HALF FLANGE ASSEMBLIES. THE CLEARANCE BETWEEN THE HALF FLANGE ASSEMBLIES AND THE SHAFT IS NOT SYMMETRICAL AND RANGES FROM APPROXIMATELY .25 INCH TO .50 INCH.

ATA 3422

Part: GYRO — LOOSE PARTS (COCKPIT REMOTE)

AFTER REMOVING GYRO FROM THE AIRCRAFT, A RATTLING NOISE WAS HEARD INSIDE THE GYRO HOUSING. THE UNIT WAS DISASSEMBLED AND INSPECTED. A SMALL BRASS KNURLED NUT (TOOL?) WAS FOUND INSIDE. THERE WAS IMPACT DAMAGE IN THE SPINNING PORTION OF THE GYRO.

ATA 6420

Part: TRUNNION — DAMAGED (T/R HUB)

POST-FLIGHT INSPECTION FOUND PLAY IN T/R HUB ASSY. END CAPS OF TRUNNION WERE REMOVED TO SHOW BURNED TEFLON DEBRIS, SOLDER, AND PRO-SEAL, AND ONE SLEEVE PULLED OFF TRUNNION OUTBOARD .0625 INCH. SUBMITTER STATES REDESIGN IS UNDER WAY.

ATA 6420

Part: TRUNNION ASSY — WORN (T/R HUB)

ON PRE-FLIGHT, A BLUING (HEATED) AREA WAS FOUND ON THE T/R HUB AT THE BUSHING END, ONE SIDE. A TEAR-DOWN REVEALED THE TRUNNION SLEEVE AND BUSHING HAD SEVERE GALLING AND HEAT DAMAGE. BOTH TRUNNION AND BUSHINGS WERE REPLACED. SUBMITTER SUGGESTED RE-DESIGN WITH DIFFERENT MATERIALS AND TOLERANCES MIGHT HELP EXTEND THE LIFE OF THESE PARTS. OPER CONTROL NR QKZA029W.

ATA 6420

Part: TRUNNION — GALLED (T/R HUB)

ON PRE-FLIGHT, A BLUING (HEATED) AREA WAS FOUND ON THE T/R HUB AT THE BUSHING END, ONE SIDE. A TEAR DOWN REVEALED THE TRUNNION SLEEVE AND BUSHING HAD SEVERE GALLING AND HEAT DAMAGE. BOTH TRUNNION AND BUSHINGS WERE REPLACED. SUBMITTER SUGGESTS RE-DESIGN WITH DIFFERENT MATERIALS AND TOLERANCES MIGHT HELP EXTEND THE LIFE OF THESE PARTS.