N83PB
Registered owner: HYANNIS AIR SERVICE INC DBA, MA (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| HYANNIS AIR SERVICE INC. (HYIA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
WHILE PERFORMING OTHER MAINTENANCE, A CRACK WAS DISCOVERED IN THE LEFT CLOSE OUT RIB. THIS CRACK EXTENDS VERTICALLY THROUGH TWO FASTENERS HOLES IN THE FIRST ROW OF ATTACH HI-LOKS BETWEEN THE AFT TRUNNION SUPPORT AND THE CLOSE OUT RIB. THE CRACK EXTENDS BETWEEN THE SECOND AND THIRD HOLE VERTICALLY OF THIS ROW, AND MEASURES .500 IN LENGTH. THIS CLOSE OUT RIB WAS CHANGED WITH A FACTORY NEW PART.
WHILE PERFORMING OTHER MAINTENANCE, CORROSION WAS IDENTIFIED ON THE LEFT HAND AFT LOWER OUTBOARD SPAR CAP (P/N 5122041-23) AT WING STATION 222.0 TO 229.71. THE DEEPEST AREA OF CORROSION WAS MEASURED AT .033. THIS SPAR CAP WAS REPLACED WITH A FACTORY NEW PART.
PILOT REPORTED "AILERON TRIM TAB EXPLODED IN FLIGHT" INITIAL INSPECTION FOUND THE AILERON TRIM TAB TOP SKIN TO BE DE-LAMINATED FROM THE FORWARD EDGE. MAINTENANCE INSPECTED AND FOUND THE DAMAGE LIMITED TO THE AILERON TRIM TAB, THE TAB WAS REPLACED WITH NO FURTHER DISCREPANCIES NOTED.
THE RT NACELLE IB FITTING WAS FOUND TO BE CRACKED AT THE LWR PORTION OF THE OB LEG WHILE PERFORMING BORESCOPE INSPECTION (TEXTRON MEL54-02R2) TO SATIDFY THE REQUIREMENT OF AD2017-10-09. THE FITTING DOES NOT APPEAR CORRODED OR OTHERWISE DAMAGED AND THERE DO NOT APPEAR TO BE INSTALLATION OR WORKMANSHIP FLAWS. THE CRACK LOCATION AND SIZE APPEAR TO BE CONSISTENT WITH OTHERS IDENTIFIED BY SAME PROCESS. THE FITTING WAS INSTALLED ON 04/20/2009 AS A PORTION OF CESSNA SERVICE KIT SK402-47B (LOWER WING SPAR CAP MODIFICATION) AND HAS BEEN IN SERVICE FOR 8576.5 HOURS. THE FITTING WILL BE REPLACED WITH NEW OEM PART
DURING MAINTNENANCE, CORROSION WAS FOUND ON THE LEFT WING SPAR STRAP, LT WS 136.54. THE DIMENSIONS FOR THIS CORROSION ARE: 1.320 INCHES LONG, .884 INCHES WIDE, AND .050 INCHES DEEP. REPLACED THE SPAR STRAP.
DURING MAINTENANCE CORROSION WAS FOUND ON THE RIGHT REAR LOWER SPAR CAP, AT RT WS. 215.71. THE DIMENSIONS FOR THIS CORROSION ARE .391 INCHES LONG, .375 INCHES WIDE, AND .020 INCHES DEEP. THIS IS GREATER THAN REMOVEABLE LIMITS ALLOWED UNDER MEB95-11R1 SEC. 3. THE SPAR CAP WAS REPLACED.
DURING A ROUTINE INSPECTION, TWO CRACKS WERE FOUND EMANATING FROM A FWD TRUNNION SUPPORT FASTENER HOLE ON THE RT CLOSE OUT RIB (P/N 5122155-56.) THE CRACKS MEASURED .250 IN LENGTH. UPON REMOVAL OF THE CLOSE-OUT RIB, IT WAS DETERMINED THE AFT ROW OF FASTENER HOLES IN THE FWD TRUNNION SUPPORT WERE NO LONGER IN TOLERANCE FOR THEIR ATTACHING HARDWARE.
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION; EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION; EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION; EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION; EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE CRACKED AND DISPLAYS EVIDENCE OF HEAT DAMAGE.
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE CRACKED AND DISPLAYS EVIDENCE OF HEAT DAMAGE.
PILOT REPORTED ELEC BURNING SMELL IN FLIGHT. R & R FAULTY HEATER SWITCH. OPERATIONALLY CHECKED GOOD.
DURING ROUTINE INSPECTION IT WAS DISCOVERED THAT THE NR 1 MAIN THRU BOLT NUT HAD BACKED OFF THE STUD IN FRONT OF THE OIL COOLER ON N83PB RT ENG. AS PRECAUTIONARY MEASURE THE RT ENG IS BEING CHANGED & SENT OUT FOR OVERHAUL.
AT SCHEDULED INSPECTION, NLG DRAG BRACE, PN 5142002-5, WAS FOUND TO BE CRACKED IN THE AREA OF NLG ACTUATOR ATTACH POINT. METHOD OF INSPECTION WAS DYE PENETRANT. THIS CRACK WAS FOUND TO BE BEYOND LIMIT ALLOWABLE OF MEB91-11R1. THIS UNIT HAS BEEN SCRAPPED & A REPLACEMENT DRAG BRACE HAS BEEN INSTALLED IN ACFT.
AT SCHEDULED INSPECTION, NLG DRAG BRACE OEM PN 5142002-5 WAS FOUND TO BE CRACKED IN THE AREA OF NLG ACTUATOR ATTACH POINT. METHOD OF INSPECTION WAS DYE PENETRANT. THIS CRACK WAS FOUND TO BE WITHIN ALLOWABLE LIMIT. THIS UNIT HAS BEEN REPAIRED IAW PROCEDURE OUTLINED IN MEB941-11R1 & RETURNED TO SERVICE.
ON GEAR RETRACTION, 3 GREEN DOWN AND LOCK LIGHTS EXTINGUISHED, HYD PRESSURE LIGHT EXTINGUISHED, BUT GEAR UNLOCK LIGHT REMAINED ILLUMINATED. AFTER SEVERAL ATTEMPTS TO RETRACT THE GEAR, CONDITION REMAINED THE SAME. GROUND PERSONNEL CONFIRMED THAT THE LT MAIN GEAR DID NOT RETRACT. EMERGENCY DECLARED, GEAR EXTENDED USING EMERGENCY GEAR EXTENSION SYS. LANDING WAS UNEVENTFUL. MX INSPECTED LANDING GEAR EXTENSION AND RETRACTION SYS, PERFORMED SEVERAL LANDING GEAR FUNCTION CHECKS, COULD NOT DUPLICATE LT MAIN GEAR NOT RETRACTING CONDITION. AS A PRECAUTIONARY MEASURE, LUBRICATED ALL UPLOCK ASSEMBLIES, AND RELEASED ACFT FOR FUNCTIONAL CHECK FLIGHT (FCF) OF LANDING GEAR EXTENSION AND RETRACTION SYS. CHECK FLIGHT NORMAL, ACFT RELEASED FOR SERVICE.
CREW REPORTED AVIONICS MASTER SWITCH INOPERATIVE. MX REMOVED AND REPLACED AVIONICS MASTER SWITCH.
DURING TAXI OUT FOR REPOSITIONING FLIGHT, PILOT FELT A PULSE FROM THE LEFT RUDDER PEDAL AND THEN A UNCONTROLLABLE TURN TO THE RIGHT. PILOT USED MAXIMUM BRAKING AND THROTTLES TO IDLE TO STOP AIRCRAFT. MAINTENANCE REBUILT, SERVICED, AND BLED THE LEFT BRAKE MASTER CYLINDER, NO FURTHER DEFECTS REPORTED.
AVIONICS MASTER SWITCH FAILED DURING TAXI. MAINTENANCE REMOVED AND REPLACED SWITCH AND RETURNED AIRCRAFT TO SERVICE.
REGULAR SCHEDULED INSPECTION, MECHANIC FOUND NOSE GEAR DRAG BRACE CRACKED AT ATTACH LUG CALCULATOR. REMOVED AND REPLACED DRAG BRACE.(K)
NOSE GEAR DRAG BRACE, P/N 5142002-5, (NEW, HEAVY DUTY STYLE), FAILED ON GEAR EXTENSION APROXIMATELY ONE INCH AFT OF THE NOSE GEAR ACTUATOR ROD END ATTACH LUG. AIRCRAFT LANDED WITH MINOR DAMAGE TO THE NOSE AREA OF THE AIRCRAFT.