What happened
On October 4, 2014, a Catalina NG R5lar582 (identified as 988-IB) was conducting a scenic flight over the Nouville Lagoon near Nouméa, New Caledonia. The pilot and one passenger departed from the Vacherie ramp for a planned 30-minute tour of the lagoon.
During the takeoff run, the pilot navigated away from the usual launch ramp to find a favorable wind direction for planing. After reaching a speed of 60 km/h on the water, the pilot initiated the takeoff. While climbing to an altitude of approximately 15 feet, the pilot applied full power to accelerate in a straight line. At a speed of approximately 80 km/h, the aircraft suddenly pitched down at a 45-degree angle, striking the water surface. The impact destroyed the forward section of the aircraft. The emergency parachute system's pyrotechnic cartridge was activated during the impact, though the parachute had barely deployed before the aircraft came to rest in the water.
The investigation
The investigation examined several critical factors, including meteorological conditions, aircraft weight, and operational procedures. Investigators noted that at the time of the accident, METAR reports from Nouméa-Magenta indicated winds from 140 degrees at 17-18 knots. Maritime assistance services reported sea conditions corresponding to a Beaufort scale of 4 to 5.
Technical analysis of the 988-IB revealed that the aircraft's takeoff mass was 510 kg, which exceeded the maximum authorized takeoff mass of 495 kg. Furthermore, the investigation reviewed the manufacturer's limitations, which prohibit operations in winds exceeding 28 km/h. The investigation also examined the pilot's actions regarding rotation speed, noting that the manual recommends a rotation speed of 70 km/h, whereas the pilot initiated rotation at 60 km/h.
Findings
Several contributing factors led to the loss of control:
- The aircraft was operating above its maximum allowable takeoff weight.
- The sustained wind speed exceeded the operational limits specified in the pilot's manual.
- The pilot performed the rotation at 60 km/h, which was below the recommended 70 km/h threshold.
- The combination of these factors likely caused the aircraft to enter a second-regime flight state (aerodynamic stall/instability) immediately following takeoff, resulting in the sudden pitch-down and subsequent impact.