N202P
Registered owner: SC INFINITIES LLC, DE (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
Maintenance disclosures
REAR SPAR CARRY THROUGH IS CRACKED.THE CRACK RADIATES FROM THE LOWER RIGHT MOST OUTBOARD FASTENER OF THE FUSELAGE REAR WING ATTACH FITTING. THE LENGTH OF THE CRACK IS APPROXIMATELY 5/16" AND CAN BE SEEN WITHOUT MAGNIFICATION. THE CRACK WAS CONFIRMED WITH EDDY CURRENT EQUIPMENT.
FS 280 FLOOR CROSS BEAM REPAIR ANGLE IS CRACKED. REPAIRED PER BOMBARDIER REO 601R-53-11-171 REV D.
DURING CLIMBOUT, PILOT NOTICED SMOKE TRAILING FROM THE LT ENGINE. IMMEDIATELY LANDED AT DEPARTURE AIRPORT AND AT SHUTDOWN, SAW A GREAT DEAL OF OIL DRIPPING FROM LOWER COWLING AND COWL FLAP. DURING AN INSPECTION RUN-UP, OIL WAS SEEN PUMPING FROM AREA OF TACHOMETER DRIVE HOUSING. REVEALED STUD THAT SUPPORTS BRACKET TO INDUCTION SYSTEM WYE PIPE HAD BACKED OUT LEAVING AN OPENING TO THE PRESSURE SIDE OF OIL SYSTEM. APPROXIMATELY 3.5 QUARTS OF OIL WERE PUMPED OVERBOARD. A NEW STUD WAS INSTALLED AND FOUND THERE WAS NO LOCKING FEATURE ON THIS STUD OTHER THAN THE USE OF LOCKING FLUID DURING INSTALLATION.
DURING AN INSPECTION, CRANKCASE OF THE RT ENGINE WAS OBSERVED TO BE CRACKED BETWEEN THE NR 1 AND NR 3 CYLINDERS. THE ENGINE WAS REMOVED AND SENT OUT FOR REPAIR.
NOSE GEAR ACTUATOR ARM FOUND CRACKED IN AREA OF WHERE THE ARM JOINS THE INPUT DRIVE BOSS. 2 OF THE 4 WEBS ATTACHING THE ARM TO THE BOSS WERE CRACKED.
THE CROSS FEED LINE PN 002-92000-51 WAS IMPROPERLY MANUFACTURED WHICH CAUSED THE RT LANDING GEAR DRIVE TUBE TO CONTACT, AND ABRADE THE LINE DURING LANDING GEAR RETRACTION. THE ABRASION HAD PROGRESSED TO THE POINT THAT ONLY 10 PERCENT OF THE WALL THICKNESS REMAINED. THE REPLACEMENT LINE PN HAS BEEN MANUFACTURED TO ALLOW GREATER CLEARANCE WITH THE LANDING GEAR DRIVE TUBE. IT IS RECOMMENDED THAT THE CLEARANCE BETWEEN THE CROSS FEED LINE AND THE DRIVE TUBE BE CHECKED. (K)
PNEUMATIC SYSTEM INSPECTED AND TRACES OF WATER WERE FOUND IN THE EJECTOR VALVE AND AREA BELOW THE VALVE. FURTHER INSPECTION REVEALED WATER IN THE PNEUMATIC MANIFOLD VALVE AND ASSOCIATED PLUMBING. APPROXIMATELY .5 OZ OF WATER WAS REMOVED FROM THE SYSTEM. THE PNEUMATIC SYSTEM INLET FILTER WERE INSPECTED AND SHOWED SIGNS OF WATER INGESTION. THERE WERE NO SIGNS OF WATER OR MOISTURE OR WATERE INT THE INSTRUMENTS AND THE PILOT HAD NO INDICATION OF ANY CONTAMINATION. RELOCATE THE PNEUMATIC SYSTEM FILTER TO AN AREA WHERE IT WILL NOT BE SUBJECT TO WATER INGESTION. (K)