N769EA
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 |
| HYANNIS AIR SERVICE INC. (HYIA) | Operator | 2012-08-31 – 2012-08-31 | Operator named in NTSB report |
| HYANNIS AIR SERVICE INC. (HYIA) | Operator | 2009-04-27 – 2009-04-27 | Operator named in NTSB report |
| Hyannis Air Services Inc | Operator | 2009-04-27 – 2009-04-27 | Operator named in NTSB report |
Accident & incident history
Maintenance disclosures
THE PILOT REPORTED THE RUDDER PEDALS JAMMED IN FLIGHT. MAINTENANCE HAS INSPECTED ALL PULLEYS, BELLCRANKS, TORQUE TUBES AND INTERCONNECT SPRINGS WITH NO DEFECTS NOTED. TROUBLESHOOTING IS ONGOING AND THE SUBMISSION WILL BE UPDATED.
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION; EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
PILOT REPORTED ELECTRIC ODOR & SMOKE IN COCKPIT. FOUND IGNITION UNIT & COIL PACK BURNED, SMOKED DURING TEST. REPLACED UNIT, OPERATIONS OK.
THIS ACFT WAS MODIFIED TO INCORPORATE STC SA04160AT ON 12 16 2015. THIS STC REMOVES OEM GRIMES STYLE RETRACTABLE LANDING LIGHT ASSEMBLIES INSTALLED AT LT & RT WINGTIPS & PROVIDES FOR INSTALLATION OF FLUSH MOUNTED HID LIGHTS WITHIN THE LE OF LT & RT WINGTIPS. AT LINE INSPECTION ON 03 17 2016, 3 OF 4 REFLECTOR ASSEMBLIES, RAA-HID-RFL4, WERE FOUND TO BE DEBONDED FROM PARENT ASSEMBLY & RESTING DIRECTLY ON HID BULB ASSEMBLY. THE REFLECTORS WERE FOUND TO BE MELTED BY THE HEAT OF HID BULB ASSEMBLY. FURTHER INSPECTION NOTED THE MOUNTING BRACKET FOR REFLECTOR ASSEMBLIES, RAA-63-301, DID NOT PROVIDE ADEQUATE CLEARANCE BETWEEN REFLECTOR ASSEMBLY & UPPER INTERNAL SURFACE OF WINGTIP. THE STC HOLDER HAS BEEN NOTIFIED OF THIS DEFECT & IS WORKING A DESIGN CHANGE TO BRACKET PN RAA-63-301.
DURING A SCHEDULED MX EVENT, DAMAGE WAS NOTED TO THE AFT CARRY THROUGH SPAR. MULTIPLE DAMAGE POINTS WERE DISCOVERED ON THE SPAR FLOOR SUPPORT FLANGE. OPEN
ON LANDING ROLLOUT, ACFT SUSTAINED DAMAGE FROM A NOSE GEAR DRAG BRACE STRUCTURAL FAILURE. NOSE GEAR DRAG BRACE REPLACED, DRAG BRACE HAD BEEN INSPECTED 130 HOURS PRIOR TO FAILURE, UTILIZING A DIE PENETRANT INSPECTION. DIE PENETRANT INSPECTION FAILED TO DETECT SUBSURFACE DEFECTS THAT WERE MOST LIKELY PRESENT AT THE TIME OF INSPECTION. THE PART IS BEING FURTHER ANALYZED TO DETECT THE ROOT CAUSE OF THE FAILURE. THIS PART HAD BEEN INSPECTED 5 TIMES SINCE 2009, AND HAD BEEN IN SERVICE SINCE WELL BEFORE 2009.
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, ON FINAL APPROACH, LANDING GEAR DOWNLOCK LIGHTS FAILED TO ILLUMINATE. WITH GEAR SELECTED DOWN, BOTH HYD FLOW WARNING LIGHTS CAME ON STEADY. CREW ELECTED TO RETURN TO ORIGINAL DEPARTURE FIELD. EMERGENCY DECLARED, PERFORMED EMERGENCY GEAR EXTENSION, ONLY NOSE AND RT MAIN GEAR DOWNLOCK LIGHTS ILLUMINATED. PERFORMED LANDING WITH DEFECTIVE MAIN GEAR CHECKLIST. LT MAIN GEAR FAILED TO EXTEND, LANDED ON NOSE AND RT GEAR ONLY. PASSENGERS AND CREW EVACUTED SAFELY. MX JACKED ACFT AND INSP EXTENSION AND RETRACTION SYS, FOUND LT MAIN GEAR UPLOCK ACTUATOR EXTEND LINE FLARE HAD FAILED AT ACTUATOR ATTACH POINT. ACFT IS CURRENTLY IN REPAIR, TO CORRECT DAMAGES CAUSED BY PARTIAL GEAR UP LANDING.
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 INOPERATIVE, WILL NOT SHUTOFF. MX REMOVED AND REPLACED AVIONICS MASTER SWITCH.
ON APPROACH, CREW REPORTED NO LEFT MAIN GEAR DOWN LOCK INDICATION. PERFORMED GEAR WILL NOT EXTEND HYDRAULICALLY PROCEDURE, STILL NO DOWN LOCK INDICATION. TOWER FLYBY INDICATED GEAR SEEMED TO BE DOWN. ON LANDING LEFT MAIN GEAR COLLAPSED. GEAR SWING INDICATED NO MALFUNCTION OF LEFT MAIN GEAR ACTUATOR. FURTHER INSPECTION FOUND LEFT MAIN LANDING GEAR UPLOCK ACTUATOR RESTRICTING HYDRAULIC FLUID FLOW TO LEFT MAIN GEAR ACTUATOR. TEARDOWN REVEALED ONE INCORRECT SIZE SEQUENCE BALL INSTALLED, CAUSING INTERNAL RESTRICTION OF HYDRAULIC FLUID.
REGULAR SCHEDULED INSPECTION FOUND NOSE GEAR DRAG BRACE CRACKED AT ACTUATOR ATTACH LUG. MECHANIC REMOVED AND REPLACED DRAG BRACE.(K)
FOUND PRESSURE LINE 5100111-71 CRACKED IN A BEND. CRACK ALLOWED ALL HYDRAULIC FLUID TO PUMP OVERBOARD. THE FAILURE POINT OF THE LINE IS AFT OF THE ENGINE FIREWALL WITH NO DIRECT ACCESS FOR INSPECTION. THE FAULT WAS FOUND WHEN THE LINE WAS REMOVED FOR TROUBLESHOOTING USING A 15X MAGNIFYING GLASS.