N2196FSchweizer 269C · 1994

On June 2, 2012, about 1135 mountain daylight time, a Schweizer 269C helicopter, N2196F, entered ground resonance when it set down on the ramp at the Rocky Mountain Metropolitan Airport (BJC), near Denver, Colorado. The commercial pilot and the passenger were uninjured. The helicopter sustained substantial damage to its tail boom during the ground resonance. The helicopter was registered to Top Flight Rotors LLC and operated by TYJ Global under the provisions of 14 Code of Federal Regulations Part 91 as an instructional flight. Day visual flight rules (VFR) conditions prevailed for the flight, which operated on a company VFR flight plan. The local flight was originating from BJC at the time of the accident.

The pilot reported that the flight was an introductory discovery flight for his student passenger. The pilot indicated that he picked the helicopter up into a two-foot skid height hover. An airplane started to taxi in front of the helicopter. The pilot, in part, stated:

To avoid my downwash disturbing the airplane, or his prop wash from

disturbing me, I set the helicopter back onto the ground as a courtesy. I

set down the left skid first and then the right, utilizing a two point touch

down. When the right skid made contact, the helicopter tried to drift to

the right. I put slight left cyclic input in to keep the helicopter from

drifting to the right as I lowered collective. As I lowered the collective fully

and the skids started to settle apart, I noticed a slight low frequency

vibration. Immediately, the vibration got worse, and I determined the

helicopter was in the beginning phase of ground resonance. My engine

RPM was too low, as was my collective, to pick the helicopter up off the

ground to restore the rotor blades to their correct phase in time. With

the collective full down, I rolled the throttle to idle to try and get rid of

ground resonance. Within seconds, the helicopter had shaken itself apart.

The pilot held a Federal Aviation Administration (FAA) commercial pilot certificate with rotorcraft helicopter and instrument helicopter ratings. He also held a Flight Instructor certificate with rotorcraft helicopter and instrument helicopter ratings. The pilot was issued a second-class FAA airman medical certificate, which listed no limitations, on January 3, 2012. The operator reported that the pilot had accumulated 259 hours of total flight time and 212 hours of flight time in the same make and model as the accident helicopter.

N2196F, was a 1994 Schweizer 269C helicopter with serial number S1647. The helicopter was equipped with fixed skids for landing gear and was configured for two occupants. The helicopter was powered by a direct drive, horizontally opposed, fuel injected, air-cooled, four-cylinder engine. The engine was a Lycoming HIO-360-D1A, serial number L-26088-51A, and was driving a three-blade main rotor assembly.

The maintenance records noted that the front landing gear struts were replaced at a Hobbs time of 1185.6 on August 8, 2011, and the rear landing gear struts were replaced at a Hobbs time of 1439.7 on November 14, 2011.

The helicopter manufacturer's maintenance procedures require that the forward and aft landing gear dampers are checked for operation, condition, and extension at each 100 hour inspection. In the event that the dampers do not meet the extension requirements, the dampers must be repaired or recharged.

The helicopter's most recent inspection was a 100-hour inspection, which was completed on May 17, 2012. According to the operator, the helicopter had accumulated 1,720 hours of total flight time at the time of the accident.

The mechanic who performed the 100-hour inspection stated that the periodic inspection procedure specified in maintenance manual was used to complete the inspection of the dampers and all measurements were found to be within limits.

At 1050, the recorded weather at BJC was: wind variable at 4 knots; visibility 50 statute miles; sky condition scattered 7,000 feet, scattered 20,000 feet; temperature 23 degrees C; dew point 4degrees C; altimeter 30.00 inches of mercury.

N2196F, was a 1994 Schweizer 269C helicopter with serial number S1647. The helicopter was equipped with fixed skids for landing gear and was configured for two occupants. The helicopter was powered by a direct drive, horizontally opposed, fuel injected, air-cooled, four-cylinder engine. The engine was a Lycoming HIO-360-D1A, serial number L-26088-51A, and was driving a three-blade main rotor assembly.

The maintenance records noted that the front landing gear struts were replaced at a Hobbs time of 1185.6 on August 8, 2011, and the rear landing gear struts were replaced at a Hobbs time of 1439.7 on November 14, 2011.

The helicopter manufacturer's maintenance procedures require that the forward and aft landing gear dampers are checked for operation, condition, and extension at each 100 hour inspection. In the event that the dampers do not meet the extension requirements, the dampers must be repaired or recharged.

The helicopter's most recent inspection was a 100-hour inspection, which was completed on May 17, 2012. According to the operator, the helicopter had accumulated 1,720 hours of total flight time at the time of the accident.

The mechanic who performed the 100-hour inspection stated that the periodic inspection procedure specified in maintenance manual was used to complete the inspection of the dampers and all measurements were found to be within limits.

The helicopter came to rest upright, located on a parking pad adjacent to a taxiway at BJC. The helicopter sustained damage to the main rotor blades and tail rotor blades. The tail boom sustained damage at its aft end consistent with a main rotor strike with it. The main rotor mast separated from its upper aft fuselage structure and the mast came to rest behind and to the left of the fuselage as viewed from the tail rotor looking forward. A postaccident examination conducted by FAA inspectors did not reveal any preimpact mechanical failures or malfunctions.

The FAA Rotorcraft Flying Handbook noted that ground resonance develops when the rotor blades move out of phase with each other and cause the rotor disc to become unbalanced. This can occur when a helicopter touches down firmly on one corner of the landing gear (skid). This condition can lead to a violent, uncontrollable oscillation. In the event that the rotor speed is low, the corrective action to stop ground resonance is to close the throttle immediately and fully lower the collective to place the blades in low pitch. On the other hand, if the rotor speed is in the normal operating range, the helicopter should be brought off the ground into a hover to allow the blades to automatically realign.

The helicopter manufacturer issued a safety advisory, dated February 22, 2012, regarding ground resonance events. The advisory noted that landing gear dampers act to slow airframe rocking motion, which may be initiated by a pronounced ground contact on one landing skid. The advisory warned that ground resonance can occur when landing dampers do not meet design specifications and that helicopters are to be maintained in accordance with current maintenance manuals.

The maintenance manual overhaul procedure for the landing gear dampers, current at the time of the accident, provided for the inspection, cleaning, reassembly, and recharging of the components. The overhaul procedure did not provide for functional/operational testing of the dampers following overhaul. The procedure noted that incorrect fluid levels, improper pressure, or inoperable valve function will reduce the effectiveness of the dampers and may lead to ground resonance.

A representative of the repair station that overhauled the accident dampers stated that the steps and procedures called out in the helicopter's maintenance manuals are what are followed when overhauling or repairing these dampers. Every step during the repair/overhaul process is monitored by a trained and experienced mechanic and an experienced inspector. He further indicated that nowhere within any of the manuals is there a provision, requirement, or any instructions, as to performing a "Test" on any overhauled damper.

The pilot's postaccident toxicology testing was negative for the tests performed.

On July 3, 2012, testing was conducted on the landing skid dampers at the manufacturer's facilities under supervision of a FAA Rochester Flight Standards District Office representative. During testing, a specified load profile is applied to the subject damper and the resulting displacement (stoke) is measured. The load vs. displacement profile is compared to a specification in order to determine the status of the damper.

The damper identified as left forward, part number 269A3150-19, serial number HT13324-1, was intact with minor bending to the upper bearing lug. The load stroke test showed that it was out of limits on the compression stroke at the lower pressure test point. It was within the ultimate load range.

The damper identified as right forward, part number 269A3150-19, serial number HT13324-2, was intact with no obvious damage or leakage. The load stroke test showed that it was out of limits on the compression stroke at the lower pressure test point. It was within the ultimate load range.

The damper identified as left rear, part number 269A3150-21, serial number HT13443-1, was intact. The load stroke test indicated a high out of limits condition at the ultimate load point.

The damper identified as right rear, part number 269A3150-21, serial number HT13443-2, was intact and exhibited a dent in the lower barrel. The load stroke test indicated a bulge in the plot on the chart consistent with barrel diameter change due to the dent. This damper failed the test due to a high ultimate load point.