N525RH
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 A 402-22 VISUAL WING ATTACHMENT FITTING INSPECTION, CORROSION WAS NOTED ON THE AFT VERTICAL PORTION OF THE LEFT HAND LOWER INBOARD WING ATTACH FITTING, JUST BEFORE THE AREA WHERE THE FITTING MOUNTS IN THE SPAR CAP. UPON REMOVAL OF THE FITTING, A LARGER AREA OF CORROSION AND THREE CRACKS WERE NOTED ON THE AFT VERTICAL FACE OF THE FITTING. THE LONGEST OF THE CRACKS (APPROX 2.5 INCHES) APPEARS TO FOLLOW THE PROFILE OF THE FITTING. THIS FITTING WILL BE REPLACED WITH FACTORY NEW. THE CORRODED/CRACKED FITTING WILL BE SENT TO AN OUTSIDE ENGINEERING COMPANY WHO WILL CONDUCT AN ANALYSIS. AFTER THE ANALYSIS, THE FITTING WILL BE SENT TO A METALLURGIST FOR FURTHER TESTING.
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION; EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE AND PISTON RINGS SHOW DEFECTS.
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.
PILOT REPORTED LOWER PANEL DIMMER SWITCH MOVEMENT CAUSED LIGHTS TO FLICKER THEN SHORT OUT. FOLLOWED A FEW SECONDS LATER BY AN ELEC BURNING SMELL. REPLACED THE DIMMING CONTROL ASSEMBLY WITH SERVICEABLE ASSEMBLY IAW MM 33-10-05 WITH NO FURTHER DEFECT NOTED.
SMOKE COMING OUT OF CABIN HEAT SWITCH. REPLACED DEFECTIVE SWITCH WITH SERVICEABLE SPARE W31-X2MIG-15 SWITCH. FUNCTIONAL CHECK NORMAL.
DURING A ROUTINE SCHEDULED INSPECTION A .61 INCH CRACK WAS FOUND IN THE RT SIDE OF THE FORWARD SPAR WEB AT FS 154.50. THE DAMAGED AREA WAS REPAIRED IAW AAS-SSR-13-70, REV NC, DATED JUNE 10,2013.
DURING A SCHEDULED MX EVENT, THE AFT CARRY THROUGH SPAR CAP WAS FOUND TO HAVE A CRACKED ANGLE AT LT FWD CENTER FLOOR STRINGER. THE C/A WAS TO FABRICATE AND INSTALL A DOUBLER AND SHIMS IAW DWG CAS-CAP13, REV 10-9-2012 FS186 REAR SPAR FLOOR SUPPORT FLANGE REPAIR.
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 APPROACH, CREW REPORTED THAT THE AUTO-PILOT WOULD NOT DISENGAGE THROUGH NORMAL MEANS. AUTO PILOT AND ELECTRIC TRIM (ELEVATOR) CIRCUIT BREAKERS WERE PULLED TO DISCONNECT AUTO-PILOT. MAINTENANCE INSPECTED AIRCRAFT AND AUTO-PILOT FUNCTIONED NORMALLY, BUT FOUND THE ELECTRIC TRIM SERVO TO BE BAD. MAINTENANCE REMOVED AND REPLACED ELECTRIC TRIM (ELEVATOR) SERVO.
PILOT REPORTED HEATER QUIT WORKING. TROUBLESHOOT HEATER ASSEMBLY FOUND COMBUSTION AIR BLOWER MOTOR TURNING VERY SLOWLY.
UNABLE TO CONTROL MANIFOLD PRESSURE
ENGINE DRIVEN FUEL PUMP - FUEL PUMP ERRATIC ON UNMETERED FUEL PRESSURES.
UNABLE TO CONTROL MAIN PRESSURE.