The closest I can find on anything remotely similar.
NTSB Looks At Cranes In Potomac Crash | Aero-News Network
Press Release [January 12, 2005] - NTSB - National Transportation Safety Board
NYC05MA039
Full report
According to the flight nurse, after the helicopter flew over the southern half of the Woodrow Wilson Bridge, the next thing he recalled was being submerged in water with his seatbelt on and his helmet off. He stated that the helicopter's master caution lights and panel segment lights did not illuminate and that he did not hear any audio alarms sound before the crash. He stated that the pilot did not execute any evasive maneuvers or communicate any difficulties, either verbally or nonverbally.
According to witnesses in vehicles on the Woodrow Wilson Bridge, the helicopter crossed over the bridge before it descended and then impacted the water. None of the witnesses reported seeing the helicopter impact any objects before its descent. The wreckage was located in the Potomac River about 0.5 nm south of the Woodrow Wilson Bridge.
According to the DCA automated surface observing system, located about 3.5 nm north of the accident site, the reported conditions at 2251 were winds calm, visibility 10 statute miles, broken clouds at 13,000 feet and 20,000 feet, temperature 45 degrees Fahrenheit (F), dew point 36 degrees F, and altimeter setting 30.25 inches of mercury.
Wreckage was scattered along a north-south oriented debris path. The wreckage was recovered, and examination indicated no evidence of a collision with a bird or other object, fatigue fractures, or other anomalies.
The main rotor mast was in place and intact in the main transmission. The root ends of the four main rotor blades remained attached to the main rotor hub on the mast.
The main transmission remained attached to the center section of the upper airframe structure, and all four mounting points were intact. The main transmission turned freely, no chips were found on the detectors, and the transmission appeared intact and functional.
The tail boom was separated at the aft fuselage frame. The tail section included the complete fenestron assembly [11] with the tail rotor gearbox and tail rotor. The tail rotor driveshaft was displaced forward about 1.5 inches. The aft portion of the driveshaft, which was carbon composite, was found fractured, torsionally cracked, and deformed. All tail rotor blades remained complete and attached to the hub. The fenestron shroud around the tail rotor showed a rotational scrape at the 5 o'clock position. The width of the scrape corresponded with the tail rotor-blade width.
Both engines showed little damage, and the gas generator (N1 compressor and turbine) and power turbine (N2 turbine) for each engine rotated freely. Nonvolatile memory data extracted from the electronic engine control units for each engine revealed no evidence of preimpact faults.