N506PH
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| K & S Helicopter INC | Operator | 2019-02-21 – 2019-02-21 | Operator named in NTSB report |
Accident & incident history
Maintenance disclosures
TAIL ROTOR BLADEWAS FOUND IN A DELAMINATED STATE DURING A POST FLIGHT INSPECTION. THE ABRASION STRIP HAD DELAMINATED FROM THE LEADING EDGE OF THE BLADE. THIS BLADE HAD BEEN INSTALLED FOR 3 DAYS AND ONLY HAD 7.1 HRS ON IT FROM REPAIR. PROBABLE CAUSE OF THE DELAMINATION IS IMPROPER CURE TIME FOR THE BONDING ADHESIVE, IMPROPER MIXING OF THE BONDING ADHESIVE, AND OR IMPROPER BEND RADIUS TO METAL LEADING EDGE CAUSING IT NOT SEAT PROPERLY AGAINST THE BLADES CONTOURED LEADING EDGE. TO PREVENT A REOCCURRENCE OF THE TAIL ROTOR BLADE ABRASION STRIP DELAMINATION, WOULD RECOMMEND FOLLOWING PROPER PROCEDURES WHEN REPAIRING A BLADE AND RE-APPLYING THE ABRASION STRIP.
DURING POST FLIGHT INSPECTION FOUND TAIL ROTOR BLADE LEADING EDGE ABRASION STRIP DELAMINATED.
UPON THE DAILY INSPECTION, A COIN TAP TEST WAS PERFORMED ON THE TAIL ROTOR BLADES. TAIL ROTOR BLADE, PN 500P3100-105, SN C519 WAS DISCOVERED TO BE DELAMINATED. THE DELAMINATION CONSISTS OF A 1.5 INCH AREA OF THE LE ABRASION STRIP ON THE OTBD SIDE OF THE BLADE .5 INCHES FROM THE TIP. THE BLADE HAD ACCUMULATED 275.4 FLIGHT HOURS SINCE IT WAS INSPECTED, REPAIRED & HAD THE LE ABRASION STRIP REPLACED. THE PROBABLE CAUSE OF THE DELAMINATION IS IN PROPER MIXING OF THE ABRASION STRIP BONDING ADHESIVE, IMPROPER CURING OF THE BONDING ADHESIVE, OR IMPROPER CONTOURING OF THE LE ABRASION STRIP, BENT AT THE WRONG DEGREE. TO PREVENT RECURRENCE OF DELAMINATION TO THE LE ABRASION STRIP, THE BONDING ADHESIVE WAS MIXED & CURED PROPERLY & THAT THE LE ABRASION STRIP WAS BENT TO THE CORRECT ANGLE.
UPON THE DAILY INSPECTION, A COIN TAP TEST WAS PERFORMED ON THE TAIL ROTOR BLADES AND BLADE WAS DISCOVERED TO BE DELAMINATED. THE DELAMINATION CONSISTS OF A 2" AREA OF THE L/E ABRASION STRIP ON THE OTBD SIDE OF THE BLADE AND A 1" AREA OF THE L/E ABRASION STRIP ON THE INBD SIDE OF THE BLADE. THIS BLADE WAS REPAIRED, INSPECTED, AND HAD THE ABRASION STRIP REPLACED. IT HAD ONLY ACCUMULATED 66 FLIGHT HOURS BEFORE THE L/E ABRASION STRIP DELAMINATED.
AFTER THE DAY`S FLIGHTS AND DURING THE DAILY INSPECTION WE FOUND, BY TAP TEST, THE L/E OF 1 OF THE TAIL ROTOR BLADES WAS DELAMINATED IN VARIOUS PLACES, VARYING IN LENGTH FROM .5 TO 2 INCHES.
DURING DAILY INSPECTION, AFTER THE DAYS FLIGHTS, ONE OF THE TAIL ROTOR BLADES WAS FOUND TO HAVE VARIOUS SPOTS, VARYING IN LENGTH FROM .5 INCHES TO 2 INCHES, WHERE THE LE WAS DELAMINATING FROM THE BLADE, PN 500P3100-105, SN C700. WE TAP TEST THE LE DAILY.
MAIN ROTOR TRANSMISSION LOW OIL PRESS LIGHT ILLUMINATED IN FLIGHT PREFORMED PRECAUTIONARY LANDING. TRANSMISSION OIL PRESS SWITCH INOPERATIVE. REPLACED PRESS SWITCH RAN ENG, OPERATIONS CHECKED GOOD & LEAK CHECKED GOOD, RETURNED TO SERVICE.
ENGINE CHIP LIGHT ILLUMINATED DURING FLIGHT. PRECAUTIONARY LANDING PERFORMED AND ENGINE SHUTDOWN. MX DISPATCHED WITH COMPANY ACFT AND PASSENGERS WERE FLOWN FOR CONTINUATION OF THE FLIGHT. CHIP DETECTORS SHOWED METAL PARTICLES ON THE LOWER CHIP PLUG OF MEDIUM QUANTITY. CHIP PLUG WAS CLEARED AND PENALTY RUN COMPLETED WITHOUT FURTHER LIGHTS AND CHIP DETECTORS WERE CLEAN. ACFT WAS RELEASED FOR FERRY FLIGHT. NO FURTHER CHIP LIGHTS OR METAL PARTICLES ON THE LOWER OR UPPER PLUGS. INITIAL NUMBER OF CHIPS VIEWED ON THE CHIP PLUG WERE OF A SIGNIFICANT ENOUGH QUANTITY TO WARRANT REPLACEMENT OF THE ENGINE AS A COMPLETE UNIT. ACFT ENGINE WAS REMOVED AND REPLACED, AND INCIDENT ENGINE WAS SENT TO O/H FACILITY AS A COMPLETE UNIT FOR EVALUATION.