HISTORY OF FLIGHTOn September 11, 2019, at 0239 eastern daylight time, a Convair 440 airplane, N24DR, was destroyed when it was involved in an accident near Monclova, Ohio. Both pilots were fatally injured. The airplane was operated under Title 14 Code of Federal Regulations Part 125 as a nonscheduled cargo flight. The flight crew initially departed Laredo International Airport (LRD), Laredo, Texas, about 1838 central time the evening before the accident and arrived at Millington/Memphis Airport (NQA), Millington, Tennessee, about 2210 central time. The airplane was refueled before it departed NQA at 2314 for the accident flight. Air traffic control position data depicted the airplane proceed direct to Toledo Express Airport (TOL), Toledo, Ohio, after departure from NQA at a cruise altitude of 7,000 ft mean sea level. About 39 miles southwest of TOL, the airplane entered a cruise descent in preparation for approach and landing. At 0225, the flight was handed off to TOL tower and instructed to descend to 3,000 ft. At 0233, the TOL tower controller instructed the flight crew to descend and maintain 2,100 ft. At 0235, the flight crew informed the controller that they were flying a wide base, and the controller cleared the pilots for a visual approach to runway 25. The airplane was about 5 miles southeast of TOL at that time. At 0236, the controller cleared the pilots to land. The landing clearance was acknowledged, and no further communications from the airplane were received. No problems or anomalies were reported by the flight crew during the flight. The airplane became briefly established on final approach before radar contact was lost. The airplane impacted trees and terrain and came to rest in a trucking company parking lot short of the runway 25 arrival threshold. A review air traffic control radar data performed by a National Transportation Safety Board (NTSB) aircraft performance specialist revealed that the airplane airspeed decayed to about 70 to 75 kts on final approach. The data depicted a flight path consistent with small bank angles through the end of the data. The airplane flight manual noted the zero thrust (power off) aerodynamic stall speed for the airplane in the landing configuration (landing gear and wing flaps extended) was about 75 kts. PERSONNEL INFORMATIONThe pilots’ logbooks were not available to the National Transportation Safety Board during the investigation. Flight times were obtained from their most recent Federal Aviation Administration medical certificate applications. Daily flight logs corresponding to the airplane, dated March 2018 to July 2019, indicated that the pilots were paired together for every flight during that time. The logs reflected 175.1 hours during the preceding 1 year, 3.9 hours within the preceding 90 days, and 0.2 hours within the 30 days preceding the accident. The pilots accumulated an additional 6 hours of flight time during the flights from LRD to NQA to TOL. WRECKAGE AND IMPACT INFORMATIONThe airplane struck trees about 0.65 mile northeast of the runway arrival threshold. The initial strikes were about 55 ft above ground level and consistent with a right bank angle of about 20°. Multiple tree breaks were observed along the flightpath through the wooded area east of the accident site. The airplane flightpath was oriented on a westerly heading and continued through the wooded area. The airplane came to rest in a trucking company parking lot about 0.50 mile from the threshold and near the extended centerline of the runway. A postimpact fire ensued. The wreckage was intermingled with the trucks and trailers parked in the lot. The top and side of a parked tractor trailer exhibited propeller strikes. In addition, portions of airplane structure were located in the woods immediately east of the accident site and along the flightpath leading to the final wreckage location. The main fuselage and cargo area (including the cargo), portions of the right and left wings, main landing gear, nose landing gear structure, flight deck, engine nacelles, and left engine exhibited extensive postimpact fire damage. Damage to the landing gear indicated that it was extended at the time of impact. The position of the wing flaps could not be determined due to the impact and postimpact fire damage. An examination of the airframe revealed no evidence of a preimpact structural failure. The left (No. 1) engine and propeller assembly came to rest on the ground against the aft side of a semi-tractor trailer. Both the engine and propeller were damaged by impact forces and the postimpact fire. The fire consumed the portions of the engine accessories and multiple cylinders, which prevented a full engine teardown. However, there was no evidence of a preimpact failure in the crankcase or cylinders that remained intact. The left propeller blades exhibited bending opposite the direction of rotation. The left propeller assembly was disassembled and no anomalies consistent with a preimpact failure or malfunction were observed. The left propeller blade shim spider impacts indicate that the propeller blades were at angles between 41-44°. The presence of multiple propeller strike marks at the accident site after the airplane had encountered the wooded area, including propeller strikes on a semi-tractor trailer, was consistent with the engine producing power at the time of impact. The right (No. 2) engine was separated from the wing and came to rest in the trucking company parking area. The right propeller was separated from the engine consistent with impact forces and located in the main debris field. The fracture surfaces on the front case were jagged and dimpled consistent with overload failure. The right propeller blades exhibited bending opposite the direction of rotation, and teardown examination of the propeller assembly did not reveal any anomalies consistent with a preimpact failure or malfunction. The right propeller blade spider shim impact marks indicated that the blades were at angles between 26-27° when the airplane impacted the trees/ground. The overload fracture of the engine accessory case and the low propeller blade angles at the time of impact are consistent with the engine producing power.