ASN Wikibase Occurrence # 232183
This information is added by users of ASN. Neither ASN nor the Flight Safety Foundation are responsible for the completeness or correctness of this information.
If you feel this information is incomplete or incorrect, you can submit corrected information.
| Date: | Thursday 9 January 2020 |
| Time: | 11:40 LT |
| Type: |  Piper PA-44-180 Seminole |
| Owner/operator: | Moncton Flight College |
| Registration: | C-FTUU |
| MSN: | 4496224 |
| Year of manufacture: | 2005 |
| Engine model: | Avco Lycoming O-360-A1H6 |
| Fatalities: | Fatalities: 0 / Occupants: 3 |
| Aircraft damage: | Substantial |
| Category: | Accident |
| Location: | Bathurst Airport (CZBF), NB -
 Canada
|
| Phase: | Landing |
| Nature: | Training |
| Departure airport: | Moncton-Metropolitan Area Airport, NB (YQM/CYQM) |
| Bathurst Airport, NB (ZBF/CZBF) | |
| Confidence Rating: |  Information verified through data from accident investigation authorities |
A Piper 44-180 aircraft operated by Canlink Aviation Ltd (Moncton Flight College) was conducting a training flight from Moncton Airport (CYQM), NB to Bathurst Airport (CZBF), NB and returning to CYQM with one instructor and 2 students onboard. Upon completing a second landing (touch and go) at CZBF, the aircraft drifted left on the landing roll. The student pilot brought the aircraft back to the centerline. As the aircraft continued slowing, it started drifting left again and the instructor took control. The propeller began striking the runway at which point the instructor
shutdown the engines and the aircraft came to a stop on the runway. The pilots evacuated. There were no injuries. The aircraft had experienced a left main gear collapse caused by a failure of the piston tube. This damaged the left prop, left engine and left wing. There was a large spill of hydraulic fluid noted at the point of touchdown. The runway was NOTAMed closed until the aircraft could be removed.
Piper has provided instructions on an inspection process using Eddy Current to check for corrosion or cracking through the bolt hole that is used to hold the lower plug of the piston assembly. Piper recommends this testing be started at 6500 hours time in service and every 700 hrs thereafter.
There is believed to have been a pre-existing fatigue crack on this aircraft which had 7900 hours.
Sources:
TSB
Revision history:
| Date/time | Contributor | Updates |
|---|---|---|
| 17-Jan-2020 18:02 | harro | Added |
Corrections or additions? ... Edit this accident description
The Aviation Safety Network is an exclusive service provided by:
Quick Links:
| ASN Home | Send Correction / Feedback |
| FSF Home | Disclaimer | Copyright |
| Contact Us | Privacy Policy |
| Press / Media |
CONNECT WITH US:
©2023 Flight Safety Foundation