Occurrence Summary
On November 15, 2024, at approximately 1:40 PM local time (1840 UTC), a Piper PA-23-250 aircraft with United States registration N91119 was on approach to Grand Bahama International Airport (MYGF), Freeport, Bahamas. The aircraft carried one pilot and five passengers.
The pilot reported that about twenty minutes after departing from Cat Cay Airport (MYCC), Cat Cay, en route to MYGF, the left engine surged. The pilot activated the left engine fuel boost pump, after which the engine fuel flow indication returned to normal and the surging ceased.
Approximately five nautical miles from MYGF, air traffic control cleared the aircraft to enter a right base for runway 06. During short final, about three nautical miles from the airport, the pilot advised ATC that the left engine had cut out (loss of power). The pilot stated that the fuel boost pumps were on, the cross-feed was turned on to investigate a potential fuel issue, and all controls were set to full forward. When the airspeed reached approximately 88 knots, the pilot feathered the left propeller.
The pilot indicated that the landing gear indicator and flaps were extended, and the manual hydraulic hand pump was used for gear and flap extension. Subsequently, a loss of power occurred on the right engine. The pilot advised ATC that the aircraft was going down and continued preparations for an emergency landing. ATC initiated emergency response protocols, alerting the Royal Bahamas Police Force and Airport Rescue and Fire Fighting Services.
The aircraft crashed and came to rest in bushes at coordinates 26°32'25.36"N 78°43'17.64"W, approximately 0.90 nautical miles southwest of the approach end of runway 06 at MYGF.
Injuries and Damage
Emergency services responded and documented that occupants received varying degrees of injuries: two persons sustained minor injuries and four persons sustained serious injuries.
The aircraft sustained substantial damage, including to the leading and trailing edges of both wings, both propellers, the underside of the fuselage, the landing gear, and the nose cone.
Post-Accident Examination
Investigators from the Aircraft Accident Investigation Authority (AAIA) arrived on November 16, 2024, to document the site and gather evidence. The post-accident examination revealed:
- No liquid consistent with AVGAS fuel was observed in the left wing outboard or inboard tank, nor under or around the left wing. Fuel supply lines on the left engine were loosened and no AVGAS was present.
- The left engine propeller had one blade bent slightly halfway along its length and at the tip slightly toward the face of the blade. The left propeller was observed in low pitch angle. The left gear was out of its wheel well in the aft position with the wheel directly under the flap.
- A ruler placed inside the right wing inboard tank measured AVGAS fuel up to the 1-inch mark. The right outboard tank had no AVGAS. Fuel supply lines on the right engine were loosened and AVGAS was present. AVGAS was observed leaking from the right wing just outboard of the right main gear door.
- The right gear was outside its wheel well in the aft position with the wheel under the flaps.
- Cabin documentation showed both fuel selectors in the OFF position and the cross-feed valve ON. Both magnetos were OFF for both engines, the aircraft master was OFF, and both electric fuel pumps were OFF. Both engine throttle, mixture, and propeller levers were found full forward.
Documentation was received for the purchase of 36 gallons of AVGAS fuel on the day of the accident, but it was not confirmed how much fuel was present before the flight or which tank(s) received the fuel.
Aircraft Information
The aircraft is a six-place, low-wing, twin-engine airplane with retractable tricycle landing gear, certified in the normal category for day and night VFR/IFR operations when equipped per FAR 91 or 135. It is powered by two Lycoming IO-540-C4B5 engines rated at 250 horsepower each. No documentation was received to indicate whether maintenance complied with manufacturer and regulatory requirements.
Fuel System Description
The Aztec fuel system uses four 36-gallon flexible fuel cells located outboard of the engines. Fuel can be pumped from any tank to both engines via engine-driven and electric fuel pumps. For normal operation, fuel is pumped directly from tanks to their respective engines with the crossfeed off. Electric auxiliary pumps provide backup pressure and are normally used during takeoff and landing. Fuel valve and crossfeed controls are located between the front seats.