Accident Details
On August 7, 2024, at 1544 eastern daylight time, a Beech 23, registration N2376L, was substantially damaged in an accident near Jacksonville, Florida. The private pilot and a pilot-rated passenger were not injured. The flight was conducted as a personal flight under Title 14 Code of Federal Regulations Part 91.
The pilot reported that the purpose of the flight was to check for oil leaks, as trace amounts of oil had been observed in the cowling. After a preflight inspection and engine run-up, the pilot took off and climbed to 1,500 ft mean sea level (msl). He completed one full traffic pattern at that altitude. During the downwind leg of a second traffic pattern, he descended to 1,000 ft msl to set up for a full-stop landing. As the airplane approached the runway numbers, the pilot noted the airspeed seemed low, and when he added throttle, the engine rpm dropped to nearly idle. About 20 ft above the runway, the airplane descended rapidly. The airplane landed hard on the runway centerline, causing the left main landing gear to separate from impact. The airplane skidded to a stop in the grass to the left of the runway. Substantial damage occurred to the left wing and fuselage.
Aircraft Examination
Postaccident examination confirmed control continuity for all primary flight controls from the cockpit to the surfaces. The stabilator trim control was observed near the neutral position. The flaps were found in the UP position, and the flap control was also UP. The throttle, mixture, and carburetor heat controls were all in the full forward position and moved smoothly through their ranges.
Fuel System Examination
Both fuel tank caps were secure. The fuel filler opening placards indicated a capacity of 29 US gallons per tank with 26 US gallons usable. The right wing fuel tank contained minimal fuel appearing as 100LL aviation fuel; upon sumping, about 1.5 tablespoons of water were found. The left wing fuel tank contained fuel also appearing as 100LL; no water was found upon sumping. The fuel strainer was sumped with no water detected. The fuel selector in the cockpit was positioned to the right tank and moved freely between detents. During recovery, about 3 gallons of fuel were drained from the right wing tank and about 9 gallons from the left.
The pilot reported using a homemade fuel stick during preflight, indicating 18 gallons in the left tank and 17 gallons in the right. He stated he had no reason to doubt its accuracy and had not calibrated it. Postaccident, the right wing fuel tank was filled with water to check for leaks; none were found.
Engine Test Run
At an aircraft recovery facility, an engine test run was performed. A fuel tank was plumbed to the right wing root, and the engine started with the fuel selector on the right. The engine ran smoothly at idle (700 rpm), was increased to 1,800 rpm for magneto checks (each dropped about 150 rpm and ran smoothly), and achieved 2,450 static rpm at full power. No anomalies precluding normal operation were noted. After the test, the carburetor fuel inlet screen was removed and a small amount of dark granular material was found.
Documentation Review
The Beechcraft 23 pilot operating handbook (POH) for the accident airplane specified a total fuel capacity of 59.8 US gallons with 52.2 gallons usable. The fuel schematic indicated no cross-feed between tanks. Maintenance records showed that Beechcraft service instruction No. 0624-281 had never been complied with. This instruction called for new placards indicating minimum fuel for takeoff and unusable fuel amounts at the filler openings, fuel selector guard, instrument panel, and fuel gauge faces. While the filler opening placards were installed as per the instruction, no corresponding cockpit placards were present to indicate compliance.