N108JL

ATA 3200

WHILE PERFORMING NOSE LANDING GEAR LINK ASSEMBLY PN:40336-00 INSPECTION 500 HOUR REPETITIVE INSPECTION PER PIPER SERVICE LETTER NO. 1088 A CRACK INDICATION WAS FOUND DURING 10X MAGNIFYING VISUAL INSPECTION. CRACK CONFIRMED DURING LIQUID PENETRANT INSPECTION.

ATA 2910

DURING APPROACH PHASE WHEN ATTEMPTING TO EXTEND THE LANDING GEAR, THE GEAR FAILED TO FULLY EXTEND WITH THE ENGINE DRIVEN PUMPS. PILOT SUCCESSFULLY EXTENDED GEAR USING THE EMERGENCY EXTENSION HANDLE. AFTER LANDING POST FLIGHT REVEALED SIGNIFICANT AMOUNT OF HYDRAULIC FLUID PRESENT ON LEFT LOWER NACELLE AFT. SOURCE OF HYDRAULIC FLUID WAS FOUND TO BE FROM THE LEFT ENGINE HYDRAULIC FILTER HOUSING. VISUAL INSPECTION OF THE FILTER HOUSING REVEALED A RADIAL CRACK AROUND THE THREADS HOLDING THE HOUSING TO THE FILTER BASE.

ATA 2910

DURING APPROACH PHASE WHEN ATTEMPTING TO EXTEND THE LANDING GEAR, THE GEAR FAILED TO FULLY EXTEND WITH THE ENGINE DRIVEN PUMPS. PILOT SUCCESSFULLY EXTENDED GEAR USING THE EMERGENCY EXTENSION HANDLE. AFTER LANDING POST FLIGHT REVEALED SIGNIFICANT AMOUNT OF HYDRAULIC FLUID PRESENT ON LEFT LOWER NACELLE AFT. SOURCE OF HYDRAULIC FLUID WAS FOUND TO BE FROM THE LEFT ENGINE HYDRAULIC FILTER HOUSING. VISUAL INSPECTION OF THE FILTER HOUSING REVEALED A RADIAL CRACK AROUND THE THREADS HOLDING THE HOUSING TO THE FILTER BASE.

ATA 8530

DURING DESCENT, LT ENGINE CYLINDER HEAD TEMP FROM 390 DEGREES F TO APPROXIMATELY ONE NEEDLE WIDTH BELOW RED LINE OBSERVED. TO KEEP TEMP BELOW RED LINE, MIXTURE WAS GRADUALLY INCREASED UNTIL FULL RICH JUST BEFORE CHECKS. DURING CHECKS, LEFT ENGINE OIL PRESSURE WAS OBSERVED TO BE DECREASING, BUT STILL WITHIN NORMAL "GREEN" RANGE AT BOTTOM END. OIL TEMPERATURE NEVER EXCEEDED 200 DEGREES F. ON OIL PRESSURE DECREASED TO ZERO & ENGINE WAS SHUT DOWN DURING ROLL OUT. POST FLIGHT VISUAL INSPECTION REVEALED SUBSTANTIAL AMOUNT OF OIL ON LOWER AFT PORTION OF LEFT ENGINE & ON LEFT MAIN GEAR. OIL QUANTITY INDICATOR SHOWED APPROXIMATELY 6 OF 12 QUARTS REMAINED IN THE SYSTEM. ROCKER BOX INSPECTION PERFORMED ON ALL CYLINDERS & DISCOLORATION CONSISTENT WITH HEAT WAS NOTED AROUND THE EXHAUST VALVE STEM OF NR 6 CYLINDER. VISUAL INSPECTION OF EXHAUST SYSTEM REVEALED CONCENTRATION OF OIL COMING FROM NR 6 CYLINDER EXHAUST PORT. NR 6 CYLINDER WAS REMOVED & PISTON RINGS WERE FOUND TO HAVE BROKEN CAUSING INTERNAL DAMAGE TO CYLINDER, PISTON, & PISTON PIN. FURTHER VISUAL INSPECTION REVEALED DAMAGE TO 2(TWO) COMPRESSOR BLADES ON LEFT ENGINE TURBO CHARGER. NR 5 CYLINDER WAS REMOVED FOR VISUAL INSPECTION & CYLINDERS 1,2,3, & 4 WERE INSPECTED WITH BORESCOPE. CONDITION OF REMAINING CYLINDERS APPEARED NORMAL & CROSS-HATCHING ON CYLINDER WALLS OBSERVED. R&R # 6 CYLINDER ASSEMBLY AND TURBO CHARGER. GROUND AND FLIGHT CHECKS NORMAL.

ATA 3230

DURING APPROACH TO LANDING, PILOT SELECTED LANDING GEAR LEVER TO DOWN POSITION. GEAR POSITION INDICATORS SHOWED NLG AND LT MLG DOWN AND LOCKED. NO DOWN AND LOCKED INDICATION FOR RT GEAR. GEAR UNSAFE "RED" LIGHT REMAINED ILLUMINATED AND LANDING GEAR SELECTOR HANDLE DID NOT RESET TO NEUTRAL POSITION. PILOT EXECUTED EMERGENCY CHECKLIST AND ATTEMPTED TO PUMP GEAR DOWN, BUT NO CHANGE IN INDICATION WAS OBSERVED. AFTER VERIFYING WITH GROUND PERSONNEL THROUGH FSS THAT GEAR APPEARED TO BE DOWN, PILOT LANDED WITHOUT INCIDENT. UPON EXIT OF THE ACFT THE PILOT NOTED THAT THE INBD GEAR DOORS REMAINED OPEN. INSPECTION OF THE RT MAIN LANDING GEAR REVEALED THAT THE GEAR WAS DOWN AND LOCKED, HOWEVER THE BEARING ON THE ROD END, PN: 74087-002, ATTACHED TO THE RT MAIN GEAR DOWN-LOCK CABLE ASSEMBLY, PN 72682-010 HAD SEIZED PREVENTING THE DOWN LOCK HOOK, PN: 41983-001, FROM CONTACTING INDICATOR MICROSWITCH, PN 487-862. DOWN-LOCK HOOK HAD TRAVELED OVER CENTER, BUT SEIZED BEARING PREVENTED REMAINING APPROXIMATELY .1250" OF TRAVEL NEEDED TO ACTIVATE MICROSWITCH WHICH WAS REQUIRED FOR POSITIVE LOCKED INDICATION IN COCKPIT AND FOR INBD GEAR DOORS TO CLOSE. ROD END WAS REPLACED AND FUNCTIONAL CHECK PERFORMED SATISFACTORILY.