N26156
Registered owner: HYANNIS AIR SERVICE INC, 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
DURING MAINTENANCE CHAFING DAMAGE WAS VISUALLY IDENTIFIED ON THE FORWARD FACE OF THE LH CROSSOVER BEAM (OEM: 5654104-11). THIS CHAFE MEASURES APPROXIMATELY .700 LONG, .500 WIDE, WITH A DEPTH OF APPROXIMATELY .011. THIS BEAM HAS BEEN REPLACED.
DURING NDT INSPECTION AS NOTED IN SID 57-10-16, A CRACK WAS DISCOVERED ON THE LEFT HAND INBOARD NACELLE FITTING. (P/N: 5292029-21) THIS CRACK MEASURES APPROXIMATELY .100 INCHES LONG ON THE INBOARD LOWER LEG OF THE FITTING, AND IS CONSISTENT WITH OTHER CRACKS FOUND USING THE LIGHTED BORESCOPE INSPECTION TECHNIQUE (TEXTRON MEL54-02R2) TO SATISFY REQUIREMENT OF AD2017-10-09. THIS FITTING WILL BE REPLACED USING NEW PARTS.
DURING MAINTENANCE A SPOT OF CORROSION WAS VISUALLY IDENTIFIED ON THE FORWARD FACE OF THE FWD LH UPPER FUSELAGE ATTACH FITTING PN: 0811350-9. THIS CORROSION MEASURES APPROXIMATELY .700 WIDE, AND .400 TALL, WITH AN APPROXIMATE DEPTH OF .025 AND IS CONSISTENT WITH OTHER CORROSION VISUALLY IDENTIFIED IN THE PAST. THIS FITTING HAS BEEN CHANGED USING NEW PARTS.
DURING SCHEDULED NDT INSPECTION A CRACK WAS FOUND ON THE RIGHT MAIN LANDING GEAR AXLE. THE LOWER LEG AND AXLE WERE REPLACED WITH NO FURTHER DEFECTS NOTED.
DURING MAINTENANCE, SEVERAL WORKING FASTENERS WERE NOTED ON THE RIGHT HAND CLOSE OUT RIB OF N26156 AT R.W.S. 106.79. THESE FASTENERS ARE COMMON TO THE AFT TRUNNION SUPPORT PLATE. THESE WORKING FASTENERS RESULTED IN ELONGATION OF THE HOLES THROUGH THE RIB BEYOND LIMITS. THIS RIB WILL BE REPLACED USING NEW PARTS.
DURING MAINTENANCE, CORROSION DAMAGE WAS NOTED UNDERNEATH THE STRIKER PLATE FOR THE UPPER CLAMSHELL DOOR PIN ENGAGEMENT HOLE LOCATED ON THE MAIN CABIN DOOR POST. (F.S. 213.6) THE DEPTH OF THIS CORROSION IN GREATER THAN 25% OF THE THICKNESS OF THE DOOR POST AND WAS NO EASILY VISIBLE WITHOUT REMOVAL OF THE STRIKER PLATE. THIS POST WILL BE REPLACED USING NEW PARTS.
WHILE PERFORMING A RECURRENT NDT INSPECTION (HFEC) TO SATISFY THE REQUIREMENTS OF TEXTRON 57-10-16, A CRACK WAS FOUND ON THE INBOARD SIDE OF THE RIGHT HAND OUTBOARD NACELLE FITTING. THIS CRACK WAS MEASURED AT .055 IN LENGTH. THIS CRACK IS CONSISTENT WITH OTHER'S THAT HAVE BEEN IDENTIFIED USING THE PROCEDURE. THIS FITTING WILL BE REPLACED WITH A FACTORY NEW PART.
THE PILOT REPORTED A BURNING SMELL IN THE CABIN INFLIGHT WITH THE HEATER TURNED ON AND DISSIPATED WHEN THE HEATER WAS TURNED OFF. MAINTENANCE INSPECTED AND FOUND THE FUEL PUMP DRIVE BROKEN AND REPLACED THE HEATER FUEL PUMP WITH NO FURTHER DEFECTS NOTED.
DURING MAINTENANCE TWO CRACKS WERE IDENTIFIED ON THE INBOARD LEG OF THE LEFT HAND OUTBOARD NACELLE FITTING, (P/N: 5292029-23) THESE CRACKS WERE DISCOVERED USING THE LIGHTED BORESCOPE INSPECTION PROCEDURE AS OUTLINED IN MEL-54-02R2 TO SATISFY AD2017-10-09. PLEASE SEE PHOTOS ATTACHED TO THIS SDR FOR ADDITIONAL SUPPORTING DETAILS. THIS FITTING WILL BE REPLACED USING NEW PARTS.
PILOT REPORTED LEFT ENGINE VIBRATION DURING FLIGHT. MAINTENANCE INSPECTED AND FOUND THE LEFT ENGINE NR 3 CYLINDER WITH A COLLAPSED EXHAUST LIFTER, BROKEN VALVE GUIDE AND THE PISTON PIN BUSHING DAMAGED AND CRACKED. THE CYLINDER AND CONNECTING ROD HAS BEEN CHANGED AND OPERATIONALLY CHECKED WITH NO FURTHER DEFECTS NOTED.
PILOT REPORTED AN ELECTRICAL BURNING ODOR IN THE CABIN. MAINTENANCE INSPECTED AND FOUND WEATHER RADAR INDICATOR HAS BURNED INTERNAL CONNECTOR. PULLED AND COLLARED THE CIRCUIT BREAKER.
PILOT REPORTED FUEL SMELL IN CABIN. TIGHTENED UNION JAM NUT & B NUT FOR LINE LEADING INTO RT FUEL TANK, IN RT BOOST PUMP PANEL IAW MM CH 28. LEAK CHECKED GOOD.
DURING CRUISE FLIGHT, CREW NOTICED A BURNING ODOR IN COCKPIT AND A SMALL AMOUNT OF HAZE OR SMOKE. DIVERTED AND MADE AN UNSCHEDULED LANDING. ON MX INSPECTION, AVIONICS MASTER SWITCH WAS FOUND DEFECTIVE. SWITCH R & R IAW MM.
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.
CREW REPORTED AVIONICS MASTER SWITCH INOP. MAINTENANCE REMOVED AND REPLACED MASTER SWITCH.
PILOT PRE-FLIGHT, HYDRAULIC RESERVOIR LOW. MAINTENANCE PRESSURE CHECKED SYSTEM, FOUND NR 6 PRESSURE LINE CRACKED AT BEND RADIUS.
AVIONICS MASTER SWITCH, INOPERATIVE. MAINTENANCE REPLACED SWITCH AND RETURNED THE AIRCRAFT TO SERVICE.