N261PA
Registered owner: CALLA AIRWAYS LLC, MA (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| PRO AIRWAYS, LLC (ZKFA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
DURING A MAINTENANCE GROUND RUN, THE RT ENGINE DEVELOPED A MAJOR OIL LEAK AND WAS IMMEDIATELY SHUT DOWN. TECHNICIANS DISCOVERED THE OIL FILTER BOWL HAD BLOWN OFF. ONE HOLD DOWN STUD HAD COMPLETELY PULLED ITS THREADS OUT OF THE OIL FILTER HOUSING. A SECOND HOLD DOWN STUD HAD PARTIALLY PULLED THREADS. THE BOWL WAS STILL HELD BY ONE STUD, WHICH HAD BEEN BENT WHEN THE OTHER STUDS FAILED. DUE TO THE DESIGN OF THE STUDS AND HOLD DOWN NUTS, NORMAL R&R OF THE OIL FILTER DOES NOT EFFECT THE THREADS THAT FAILED.
PILOTS NOTICED SMOKE SMELL IN COCKPIT DURING CRUISE FLIGHT, ON TRIP KHYA-KAPF, FOLLOWED BY OBSERVING SMOKE. CONDUCTED EMERGENCY DESCENT AND LANDING AT KSAV. MAINT TECHNICIAN FOUND 2 AC CIRCUIT BREAKERS TRIPPED IN LEFT WINDSCREEN CIRCUIT AND LEFT WINDSCREEN ELECTROSTATIC FILTER UNIT OVERHEAT DAMAGED, DETERMINED THE FILTER WAS THE SOURCE OF THE SMOKE. TECHNICIAN INSPECTED ADJACENT AREA AND EWIS, NO OTHER DAMAGE NOTED. PLACED WINDOW HEAT SYSTEM ON MEL, GROUND RUN OF AIRCRAFT AND SYSTEMS ACCOMPLISHED AND AIRCRAFT RETURNED TO SERVICE.
AIRCRAFT IMPACTED A DEER ON LANDING AT KPYM. RIGHT TRAILING EDGE FLAP WAS DAMAGED BEYOND REPAIR AND WAS REPLACED.
AIRCRAFT WAS ON SHORT FINAL TO KPYM, PLYMOUTH, MA MUNICIPAL AIRPORT, FULLY CONFIGURED FOR LANDING, WHEN PILOTS SAW SMOKE AND HEARD A POPPING SOUND FROM THE COPILOTS INSTRUMENT PANEL NEXT TO THE GEAR HANDLE. A FLAME WAS BRIEFLY OBSERVED BY THE COPILOT IN THE SAME AREA. THE CAUSE OF THIS ISSUE IS CURRENTLY BEING INVESTIGATED BY CRS ZKFR180L AT KPYM. THIS SDR WILL BE REVISED AS TO CAUSE. NOTE-PROPELLER LISTED ABOVE IS #2 ENGINE
RH AILERON SIGNIFICANT CORROSION FOUND AT CENTER TRIM TAB HINGE, AROUND BONDING STRAP ATTACHMENT HOLE, IN AFT SPAR STRUCTURE. TEXTRON ENGINEERING NOTIFIED AND NO REPAIR ALLOWED. NO NEW REPLACEMENT AILERONS AVAILABLE. ACQUIRED AS REMOVED RH AILERON S/N DHB1002 AND SAME IRREPARABLE CORROSION FOUND. ACQUIRED SECOND AS REMOVED RH AILERON S/N DHB1032 AND SAME IRREPARABLE CORROSION FOUND. WE NOW HAVE THREE RH AILERONS FROM THREE DIFFERENT AIRCRAFT WITH UNAIRWORTHY RH AILERONS DUE TO SIGNIFICANT CORROSION OF THE AFT SPAR STRUCTURAL CASTINGS.
DURING SCHEDULED INSPECTION, FOUND CORROSION ON LT SIDE OF VERTICAL TO HORIZONTAL STABILIZER ATTACH FITTING. CORROSION IS INTERGRANULAR, AND IS LOCATED AROUND 12 FASTENER HEADS.
DURING PREFLIGHT, FLIGHT CREW NOTICED LT OTBD TIRE LOOKED LOW. MX DISCOVERED TIRE ALMOST COMPLETELY DEFLATED BUT NOT BLOWN. WHEEL ASSYS ONLY HAD 9 CYCLES SINCE IT WAS O/H. REMOVED AND REPLACED WHEEL/TIRE ASSY. INSPECTED REMOVED WHEEL ASSY AND FOUND AIR LEAKING FROM RIM NEAR VALVE STEM LOCATION (BUT NOT FROM VALVE STEM). MX BELIEVES THAT LEAK IS COMING FROM THE WHEEL HALF SEALING O-RING.
DURING PREFLIGHT, FLIGHT CREW NOTICED LT INBD TIRE LOOKED LOW. MX DISCOVERED TIRE ALMOST COMPLETELY DEFLATED BUT NOT BLOWN. WHEEL ASSYS ONLY HAD 9 CYCLES SINCE IT WAS O/H. R & R WHEEL/TIRE ASSY. INSPECTED REMOVED WHEEL ASSY AND FOUND AIR LEAKING FROM RIM NEAR VALVE STEM LOCATION (BUT NOT FROM VALVE STEM). MX BELIEVES THAT LEAK IS COMING FROM THE WHEEL HALF SEALING O-RING. THEY ALSO NOTICED THE WHEEL HALF SEALING O-RING WAS A DIFFERNT COLOR (BLUE) THAN NORMAL (BLACK).
OXYGEN SYS NON-RETURN VALVE LEAKING ALLOWING OXYGEN TO FLOW BACKWARDS AND LEAK OUT OF FILLER PORT. THIS WAS A BRAND NEW CHECK VALVE FROM MFG. REMOVED AND REPLACED UNIT.
OXYGEN SYSTEM LEAKING: FOUND OXYGEN SYSTEM NON-RETURN VALVE INOP AND ALLOWING OXYGEN TO FLOW BACKWARDS AND LEAKING OUT OF FILLER PORT. REMOVED AND REPLACED NON-RETUEN VALVE AND LEAK CHECKED GOOD. THIS NON RETURN VALVE WAS JUST INSTALLED 9 MONTHS AGO FOR THE SAME ISSUE.
DURING ENGINE CHANGE, CORE COWL SEGMENT FOUND DELAMINATED. MFG HAS A REPAIR FOR THIS PROBLEM BUT UNFORTUNATELY THE EXTENT OF DAMAGE TO THIS CORE COWL IS BEYOND ALL LIMITS OF REPAIR. THE REPAIR IS USUALLY FOR A SMALL AMOUNT OF LIFTING AT THE CORNERS OF THE BONDMENT. MFG INFORMED THAT IT DOES NOT HOLD PMA FOR THIS PROGRAM SO THE NEW PART WILL NEED TO BE PURCHASED THROUGH HBP&D. RDO INFORMED THAT THEY ARE NOT ABLE TO PRODUCE A REPAIR FOR THIS ISSUE. THIS IS DUE TO THE ACOUSTIC PROPERTIES OF THE COWL. THE COWL MUST BE REPLACED WITH NEW OR SERVICEABLE PART. R & R CORE COWL SEGMENT.
CABIN TEMPERTURE UNCONTROLLABLE IN AUTO MODE. FOUND CABIN TEMPERTURE CONTROLLER NOT PROVIDING ANY OUTPUT VOLTAGE. CONTROLLLER GIVES MOMENTARY PULSES ONLY VISIBLE USING A TEST LAMP WHICH CAUSES TEMP CONTROL VALVE TO "CLICK" BUT NOT ENOUGH TO MOVE VALVE. R & R CABIN TEMP CONTROLLER. OPS CHECKED GOOD.
ACFT EXPERIENCED MODERATE VIBRATION IN CRUISE, FLIGHT CREW FELT VIBRATION WAS FROM NR 2 ENGINE, FOLLOWED SHORTLY AFTER WITH GEN 2 FAIL INDICATION, CREW SHUTDOWN NR 2 ENGINE, FLIGHT DIVERTED FOR NON-EVENTFUL SINGLE ENGINE LANDING. MX REMOVED NR 2 ENGINE STARTER GEN UNIT, FOUND UNIT FAILED, WITH INTERNAL COOLING FAN ASSY CONTACTING GENERATOR SHROUD. STARTER GEN UNIT HAD 305.1 HOURS SINCE O/H, THIS UNIT TBO IS 1000 HOURS.
DURING CRUISE FLIGHT, EXPERIENCED VIBRATION, BELIEVED TO BE FROM ENGINE AREA. VIBRATION INCREASED, BUT DID NOT SHOW ON EVM INDICATOR, FOLLOWED BY GEN 1 FAIL INDICATION, WITH BUS TIE CLOSED IN FLIGHT. ACFT MADE UNSCHEDULED LANDING. MX FOUND NR1 STARTER GEN FAILED, COOLING FAN ON GEN SHATTERED, SHAFT SHEARED, MANY BROKEN PIECES OF UNIT IN ENGINE COWLING.
DURING TAKEOFF, ENROUTE, THE LANDING GEAR HORN SOUNDED WHEN GEAR LEVER WAS PLACED IN UP POSITION, BOTH WITH FLAPS IN 15 DEGREE AND 0 DEGREE POSITION. CREW PLACED GEAR LEVER IN DOWN POSITION AND HORN SILENCED. CREW CIRCLED AND BURNED OFF FUEL AND RETURNED TO DEPARTURE AIRPORT AND LANDED SAFELY. DID NOT DECLARE EMERGENCY. AC WAS FERRIED TO HOME BASE FOR MAINTENANCE. UPON INVESTIGATION IT WAS FOUND THAT THE FLAP POSITION SWITCH WAS AT FAULT. REMOVED AND REPLACED RT THROTTLE QUADRANT FLAP SWITCH WITH NEW. PERFORMED OPS CHECK OF GEAR HORN SYSTEM. OPS CHECK, NORMAL AND AC RETURNED TO SERVICE.