N142SA
Registered owner: MONARCH ENTERPRISES INC, 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 |
| MONARCH ENTERPRISES INC | Operator | on 2025-05-06 | Operator named in NTSB report |
Accident & incident history
Operated by MONARCH ENTERPRISES INC (per NTSB report)
Not yet finalized — may be revised.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, 1996-04-01 – 1998-10-24.
Part: ROD ASSEMBLY — GROOVED (WING ROOT)
DURING AIRCRAFT SCHEDULED INSPECTION, MAINTENANCE PERSONNEL FOUND LEFT AND RIGHT WING ROOT TO INBOARD BELLCRANK FLAP ROD ASSEMBLIES HEAVILY GROOVED AND SCORED BY ROD GUIDE ROLLERS. THIS IS AN ONGOING CHRONIC PROBLEM ON THIS AIRCRAFT TYPE. GUIDE ROLLERS ARE MADE FROM A HARD MATERIAL THAT DAMAGED THE SOFTER RODS. THESE RODS ARE THE SUBJECT OF AD 80-03-08. MOD 6/1707 HAD PREVIOUSLY BEEN ACCOMPLISHED. (M)
Part: ROD ASSY — WORN (WING ROOT)
DURING AIRCRAFT SCHEDULED INSPECTION, MAINTENANCE PERSONNEL FOUND LEFT AND RIGHT WING ROOT TO INBOARD BELLCRANK FLAP ROD ASSEMBLIES HEAVILY GROOVED AND SCORED BY ROD GUIDE ROLLERS. THIS IS AN ONGOING CHRONIC PROBLEM ON THIS AIRCRAFT TYPE. GUIDE ROLLERS ARE MADE FROM A HARD MATERIAL THAT DAMAGES THE SOFTER RODS. THESE RODS ARE THE SUBJECT OF AD 80-03-08. MOD 6/1707 HAD PREVIOUSLY BEEN ACCOMPLISHED. (M)
Part: COUPLING — BROKEN (RT ENGINE)
DURING PHASE INSPECTION, MAINTENANCE PERSONNEL FOUND ABNORMAL AMOUNT OF METAL IN RIGHT ENGINE MAIN OIL FILTER. UPON FURTHER INVESTIGATION FOUND LARGE STEEL FRAGMENT ON REDUCTION GEARBOX MAGNETIC PLUG. AFTER REMOVAL OF GEARBOX FROM ENGINE, FOUND POWER TURBINE NOT COUPLED TO PROPELLER SHAFT. UPON DISASSEMBLY OF REDUCTION GEARBOX, FOUND POWER TURBINE SHAFT COUPLING BROKEN AT FORWARD RETAINING RING GROOVE AROUND APPROXMATELY 320 DEGREES OF CIRCUMFERENCE.