N177GC
Registered owner: DIAMOND BAR LLC, WA (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| Grand Canyon Airlines, Inc. (GCNA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
3 reports on file, 1998-02-10 – 2013-06-02.
Part: CLEVIS BOLT — FAILED (RUDDER TAB) · airframe 57,072 hrs · 114,664 cycles
DURING CRUISE FLIGHT, PILOTS FELT AN AGGRESSIVE FLUTTER COMING FROM RUDDER. DECLARED AN EMERGENCY AND LANDED WITHOUT FURTHER INCIDENT. MX INSPECTED THE ACFT AND DETERMINED THE RUDDER GEAR TAB HAD FAILED DUE TO A BROKEN CLEVIS BOLT. NOTICED THAT TO RIG THE RUDDER GEAR TAB, HAD TO POSITION ROD END DIFFERENT TO WHAT IT HAD BEEN TO PLACE THE BOLT IN THE VERTICAL POSITION AS DESCRIBED IN THE MM 27-26-00. 1A (2). REPLACED FAILED PART AND RIGGED GEAR TAB IAW AMM 27-26-00. ACFT TEST FLOWN SATIFACTORY AND RETURNED TO SERVICE.
Part: CLEVIS BOLT — SHEARED (RUDDER) · airframe 56,532 hrs · 113,852 cycles
IN FLIGHT PILOT REPORTED ACFT BEGAN TO SHAKE VIOLENTLY. RUDDER PEDALS SHOOK. NO ENGINE ANOMALIES NOTED NO OPEN DOOR INDICATIONS. FLIGHT WAS DISCONTINUED AND ACFT RETURN TO DEPARTURE AIRPORT. UPON INSPECTION THE CLEVIS FORK THAT ATTACHES THE RUDDER GEAR TAB ROD TO THE GEAR TAB MECHANISM WAS FOUND TO BE SHEARED. THE MECHANISM WAS FOUND TO OPERATE SMOOTHLY AND THE TAB WAS FOUND TO MOVE FREELY ON THE HINGE.
Part: ENGINE — FAILED (LEFT)
LEFT ENGINE TORQUE PRESSURE DROPPED TO ZERO AFTER SLIGHT POWER REDUCTION, CAME BACK UP TO ABOUT 4 PSI, POWER INCREASED TO 15 PSI. AFTER ANOTHER SLIGHT POWER REDUCTION, TORQUE DROPPED TO ZERO AND OIL PRESSURE DROPPED BELOW 40 PSI. FEATHERED AND SECURED ENGINE. ONCE ON GROUND, MAINTENANCE PERSONNEL RESTARTED ENGINE AND PERFORMED A THOROUGH GROUND RUN, AND COULD NOT DUPLICATE PROBLEM OR FIND ANY DISCREPANCIES. REPLACED THE FUEL CONTROL UNIT AS A PRECAUTIONARY MEASURE BECAUSE NO DISCREPANCIES IN THE ENGINE, ENGINE ACCESSORIES, OR ENGINE SYSTEMS COULD BE FOUND.