FACTUAL REPORT AVIATION

This space for binding National Transportation Safety Board NTSB ID: CHI01LA119 Occurrence Date: 04/18/2001 Occurrence Type: Accident Aircraft Registration Number: N713HT Most Critical Injury: Minor Investigated By: NTSB FACTUAL REPORT AVIATION Location/Time Nearest City/Place State Zip Code Local Time Time Zone DU QUOIN Airport Proximity: Off Airport/Airstrip IL 62832 1430 CDT Distance From Landing Facility: Aircraft Information Summary Aircraft Manufacturer Model/Series Type of Aircraft Hughes 369D Helicopter Revenue Sightseeing Flight: No Narrative Air Medical Transport Flight: No Brief narrative statement of facts, conditions and circumstances pertinent to the accident/incident: On April 18, 2001, at 1430 central daylight time, a Hughes 369D helicopter, N713HT, operated by Aerial Solutions, Incorporated, and piloted by a commercial pilot, was destroyed when it impacted the terrain during an emergency landing after experiencing a loss of engine power. Visual meteorological conditions prevailed at the time of the accident. The tree-trimming operation was being conducted under the provisions of 14 CFR Part 133, Rotorcraft External Load. The operation entailed using an aerial saw suspended beneath the helicopter to trim trees in the vicinity of power lines. There was no flight plan on file. The pilot on board sustained minor injuries. The local flight departed from a landing zone approximately 5 miles northwest of Du Quoin, Illinois, at 1330. In his written statement, the pilot said that he was using an aerial saw to side trim trees along a powerline right-of-way. The pilot said, "At the end of the tree line at approximately 150' (feet) agl (above ground level) I applied power to climb, immediately the low rotor rpm horn sounded. I tried to increase N2/Nr (engine and rotor rpm) with the governor 'beep switch' and checked N2/Nr. There was no response from trying to increase N2/Nr and N2/Nr was in the low 90's. I lowered the collective, released the saw and radioed my ground crew that the engine had stopped. At this point I had low airspeed, low N2/Nr and approximately 100' agl. I aimed the aircraft at an open field and tried to gain airspeed to attempt a running landing." The pilot said the helicopter "impacted the field in a near horizontal attitude." A Federal Aviation Administration (FAA) inspector examined the helicopter at the accident site. The helicopter was resting on its left side in a corn stubble field approximately 300 feet south of east-west running power lines, and approximately 730 feet from a clearway of trees where the helicopter was cutting prior to the accident. Both of the helicopter's skids were broken outward and aft. The bottom of the helicopter was crushed upward. All four main rotor blades were bent upward approximately 12 inches outboard of the rotor head. One blade was broken aft near mid-span. The tail boom was broken downward approximately 30 inches aft of the engine section. The boom remaining with the helicopter fuselage was bent and broken downward in several places and crushed upward immediately aft of the exhaust opening. The aft portion of the boom was crushed inward, bent to the right, and broken downward. Black paint similar to the paint on the broken rotor blade was found on the tail boom where it was crushed inward. Control continuity was established to the control pedals and the collective. Fuel samples were taken from the helicopter and a nurse truck used to refuel the helicopter. The helicopter's engine was retained for further examination. The fuel samples were examined at the FAA Flight Standards District Office, Springfield, Illinois on May 1, 2001. The fuel samples were consistent with type Jet A and showed no water or sediments in suspension. The helicopter's engine was examined at Rolls-Royce Corporation, Indianapolis, Indiana, on May 2, 2001. The engine was mounted on a test stand and run as received. The first engine run resulted FACTUAL REPORT - AVIATION Page 1 This space for binding National Transportation Safety Board NTSB ID: CHI01LA119 Occurrence Date: 04/18/2001 Occurrence Type: Accident FACTUAL REPORT AVIATION Narrative (Continued) in limited N2, the loss of 100 percent power turbine governor control, and speed oscillations. A Rolls-Royce test mechanic determined that the 3-inch in line accumulator installed on the engine was a post factory shipping modification and requested the test be conducted with the 6-inch accumulator that is in accordance with the current standard C20B new production shipping configuration. The 6-inch accumulator was installed and the engine run was repeated. The engine was able to maintain 100 percent N2 speed at 188 foot-pounds of torque. A new 3-inch accumulator was installed on the engine and the test was run again with similar results from the first engine run. A fourth engine run involving the original 3-inch accumulator that came with the engine produced the same loss of turbine power governor performance as was observed in the first engine run. The governor (part number 23065121, serial number BR37539) and fuel control unit (part number 2524644-29, serial number BR53162) were removed from the engine and retained for further examination. Rolls-Royce On-site and engine test report is attached as an addendum to this report. The fuel control unit and governor were examined at Honeywell Engine Systems and Accessories, South Bend, Indiana, on September 6, 2001. Visual inspections and flow testing of both components revealed no anomalies. Honeywell's test report is attached as an addendum to this report. The FAA, Rolls Royce Corporation, and Honeywell Engine Systems and Accessories were parties to the investigation. All wreckage was released and returned to representatives of the helicopter's owner. FACTUAL REPORT - AVIATION Page 1a This space for binding National Transportation Safety Board NTSB ID: CHI01LA119 Occurrence Date: 04/18/2001 Occurrence Type: Accident FACTUAL REPORT AVIATION Landing Facility/Approach Information Airport Name Airport ID: Airport Elevation Ft. MSL Runway Used Runway Length Runway Width Runway Surface Type: Unknown Runway Surface Condition: Vegetation Approach/Arrival Flown: NONE VFR Approach/Landing: Forced Landing Aircraft Information Aircraft Manufacturer Model/Series Serial Number Hughes Airworthiness Certificate(s): Normal; Utility 369D 370096D Landing Gear Type: Skid Amateur Built Acft? No Engine Type: Number of Seats: 1 Certified Max Gross Wt. Engine Manufacturer: 3550 LBS Model/Series: Number of Engines: 1 Rated Power: Turbo Shaft - Aircraft Inspection Information Type of Last Inspection Allison Date of Last Inspection 250-C20B 420 HP Airframe Total Time Time Since Last Inspection 100 Hour - Emergency Locator Transmitter (ELT) Information ELT Installed?/Type Yes / 04/2001 29 Hours 9427 Hours ELT Operated? Yes ELT Aided in Locating Accident Site? No Owner/Operator Information Registered Aircraft Owner Street Address 7074 RAMSEY FORD ROAD AERIAL SOLUTIONS, INC. City State Zip Code TABOR CITY Street Address Operator of Aircraft NC 28463 7074 RAMSEY FORD ROAD City State Zip Code AERIAL SOLUTIONS, INC. Operator Does Business As: TABOR CITY Operator Designator Code: NC 28463 - Type of U.S. Certificate(s) Held: Air Carrier Operating Certificate(s): Operating Certificate: Regulation Flight Conducted Under: Part 133: Rotorcraft Ext. Load Type of Flight Operation Conducted: Other Work Use Operator Certificate: Aircraft External Load FACTUAL REPORT - AVIATION Page 2 This space for binding National Transportation Safety Board NTSB ID: CHI01LA119 Occurrence Date: 04/18/2001 Occurrence Type: Accident FACTUAL REPORT AVIATION First Pilot Information Name City State Date of Birth Age On File Sex: M Seat Occupied: Left On File Occupational Pilot? Civilian Pilot On File Certificate Number: 43 Certificate(s): Flight Instructor; Commercial Airplane Rating(s): Single-engine Land Rotorcraft/Glider/LTA: Helicopter Instrument Rating(s): Airplane; Helicopter Instructor Rating(s): Helicopter Current Biennial Flight Review? 08/2000 Medical Cert.: Class 2 Medical Cert. Status: Valid Medical--w/ waivers/lim. Date of Last Medical Exam: 03/2001 - Flight Time Matrix Total Time Pilot In Command(PIC) Instructor Instruction Received Last 90 Days Last 30 Days Last 24 Hours All A/C This Make and Model Airplane Single Engine Airplane Mult-Engine Night Actual Instrument Simulated Rotorcraft Glider Lighter Than Air 4840 4475 250 110 4 2400 2395 20 110 4 210 132 65 62 10 3 5 85 85 4530 4406 250 110 4 Seatbelt Used? Yes Shoulder Harness Used? Yes Toxicology Performed? No Second Pilot? No Flight Plan/Itinerary Type of Flight Plan Filed: None Departure Point State Airport Identifier Departure Time Time Zone Same as Accident/Incident Location Destination State Airport Identifier 1330 CDT Local Flight Type of Clearance: None Type of Airspace: Class G Weather Information Source of Wx Information: No record of briefing FACTUAL REPORT - AVIATION Page 3 This space for binding National Transportation Safety Board NTSB ID: CHI01LA119 Occurrence Date: 04/18/2001 Occurrence Type: Accident FACTUAL REPORT AVIATION Weather Information WOF ID Observation Time Time Zone WOF Elevation WOF Distance From Accident Site Direction From Accident Site CGI 1353 CDT 336 Ft. MSL Ft. AGL Ft. AGL Visibility: 53 NM Condition of Light: Day SM Altimeter: 194 Deg. Mag. Sky/Lowest Cloud Condition: Clear Lowest Ceiling: None Temperature: Wind Direction: 260 Visibility (RVR): Precip and/or Obscuration: Ft. 10 30.30 "Hg 15 ° C Dew Point: Wind Speed: 7 Visibility (RVV) -1 ° C Weather Conditions at Accident Site: Visual Conditions Wind Gusts: SM Accident Information Aircraft Damage: Destroyed Aircraft Fire: None Aircraft Explosion None - Injury Summary Matrix First Pilot Second Pilot Student Pilot Flight Instructor Check Pilot Flight Engineer Cabin Attendants Other Crew Passengers - TOTAL ABOARD Other Ground - GRAND TOTAL - Fatal Serious Minor None TOTAL 1 1 1 1 1 1 FACTUAL REPORT - AVIATION Page 4 This space for binding National Transportation Safety Board NTSB ID: CHI01LA119 Occurrence Date: 04/18/2001 Occurrence Type: Accident FACTUAL REPORT AVIATION Administrative Information Investigator-In-Charge (IIC) DAVID C. BOWLING Additional Persons Participating in This Accident/Incident Investigation: DAVID L SLAYBAUGH FEDERAL AVIATION ADMINISTRATION SPRINGFIELD, IL MICHAEL A WEBER ROLLS-ROYCE CORPORATION INDIANAPOLIS, IN LEE G FISHER HONEYWELL ENGINE SYSTEMS AND ACCESSORIES SOUTH BEND, IN FACTUAL REPORT - AVIATION Page 5