N1098F

HISTORY OF FLIGHT

On August 30, 2007, at 1235 Pacific daylight time, a Raytheon A36, N1098F, descended into terrain during the takeoff initial climb from Cameron Air Park, Cameron Park, California. The airplane was operated by the commercial pilot under the provisions of 14 Code of Federal Regulations Part 91. The pilot and one passenger were seriously injured, two passengers were fatally injured, and the airplane was substantially damaged. Visual meteorological conditions prevailed, and a flight plan had not been filed.

A television news crew was filming airplane operations at the Cameron Park Airport and captured the accident on video. A Federal Aviation Administration (FAA) inspector and the National Transportation Safety Board investigator-in-charge (IIC) viewed the video of the event. The video depicted the airplane on its takeoff roll, accelerating almost 2/3 down runway 31 before getting airborne. Once airborne, the airplane climbed to approximately 40 feet and the wings began to wobble and it settled back down towards the ground. The airplane settled into the rising terrain off the end of the runway, slid on the ground, and abruptly flipped over on to its back.

The pilot stated to the Safety Board IIC that he was very familiar with this airplane and had flown it often. He topped the airplane off with fuel, had mentally performed a weight and balance, and had done a takeoff over a 50-foot obstacle calculation for a 100-degree Fahrenheit (F) day at this airport in the past. He stated that the engine run-up was normal, and the outside air temperature (OAT) was 35 Celsius (C) (95 F). The takeoff roll was a little longer than normal and the acceleration felt normal except for a momentary shudder about 1/3 the way down the runway. During the initial climb the airplane was accelerating. At some point the airplane stopped climbing, the airspeed indicated 84 knots, and the rate of climb had dropped off. He lowered the nose and felt a gust of wind from the left side, at which point the wings started to wobble. He cut the power just as the airplane was settling in to the rising terrain/runway overrun.

The pilot and passenger in the cockpit sustained serious injuries. The two passengers in seats that were positioned forward in the cabin and faced aft were fatally injured.

PERSONNEL INFORMATION

The pilot, age 64, held a commercial pilot certificate issued on December 10, 1989, with single engine land, single engine sea, multiengine land, multiengine sea, helicopter, gyroplane, and airplane instrument ratings. The pilot also held a flight instructor certificate issued on May 20, 2007, with instructor ratings in single and multiengine airplane, instrument airplane, rotorcraft helicopter and gyroplane. The pilot held a third-class airman medical issued in June 2006, with the limitation that he must wear corrective lenses for near and distant vision. The pilot reported a total fight time of 2,000 hours, of which 1,700 hours were pilot-in-command, and 1,000 hours as an instructor. He had flown 16 hours in the accident airplane make and model within the last 30 days.

AIRCRAFT INFORMATION

The four seat, low-wing, retractable-gear airplane, serial number E-3059, was manufactured in 1996. The airplane's original production configuration was equipped with six seats, however, the two furthest aft seats were removed from this airplane. It was powered by a Teledyne-Continental Motors IO-550-B, 300 brake horsepower engine, and equipped with a McCauley model D3A32C409-C propeller. A review of the airframe maintenance logbook records showed that an annual inspection was completed October 9, 2006, at an airframe total time (AFTT) of 1031.5 hours. At this time a turbonormalizing system was installed on the engine in accordance with Engine Technologies, Inc, supplemental type certificate (STC) number SE5222NM. The engine maintenance logbook records showed the annual inspection had been complied with on October 9, 2006, at AFTT 1031.5 hours, and Engine Time Since Overhaul (ETSO) of 679.1 hours. The Hobbs meter read 1,108.3 at the accident site.

The pilot operating handbook (POH) contained a section titled; Airplane Flight Manual Supplement - 550, Aircraft With Turbonormalizer Systems installed after August 1, 2000. Page 5 of the supplement stated "Your aircraft has been approved for increased maximum takeoff weights and landing weights in accordance with the following chart. All operations above the original maximum weight listed in the Aircraft Flight Manual are to be NORMAL CATEGORY operations." The tables that followed contained flight load factor limits for the A36 in the 'normal category' as 3.8 positive g's, 1.5 negative g's, flaps up, and 2.7 positive g's, 0 negative g's, flaps down. Page 6 contained the increased weight and balance envelope load for the A36 as 4,000 lbs (NORMAL CATEGORY ONLY above 3,650 lbs), between stations +85.5 in to +87.7 in. Page 26 of the supplement stated "However, when operating at the increased weights authorized when operations are conducted in the NORMAL CATEGORY expect:

A. Increased Takeoff Distance of up to: 30%

B. Decreased Rate-of-Climb of up to: 13%

C. Increased Stall Speed of up to: 7%

D. Increased Landing Distance of up to: 15%

E. Increased Takeoff & Approach Speeds: Increase 2 kts

F. Increase Vx and Vy speeds: Increase 2 kts

The most recent airplane weight and balance sheet was dated October 9, 2006, and copies were located in the maintenance records and in the POH. The empty weight of the airplane was stated to be 2,630 pounds. Using the following weights; removal of rear seats (32 lbs), full fuel load (431 lbs), pilot (162 lbs), right front seat (204 lbs), 3 rd seat occupant (195 lbs), 4th seat occupant (234 lbs), and baggage/cargo (271 lbs), the total takeoff weight was approximately 4,095 lbs at a CG of +86.15 in.

Utilizing the above information, pressure altitude of 1,293 feet, and OAT of 35C; the takeoff performance charts provided in the POH were used to calculate the takeoff ground roll and distance to clear a 50-foot obstacle. The ground roll plus 30 percent was 2,210 feet. The takeoff distance to clear a 50-foot obstacle plus 30 percent was 4,030 feet, and takeoff speed plus 2 knots was 86 knots.

Utilizing topographical information from Google Earth, the horizontal distance between the point the airplane lifted from the runway and the location of the highest terrain directly ahead was approximately 2,128 feet. The elevation difference between these two points is 80 feet. Total distance from the start of the takeoff roll to the highest terrain directly ahead is about 4,860 feet.

METEOROLOGICAL INFORMATION

Cameron Airpark does not have a weather recording system. The exact wind conditions at the time of the accident are not known. The pilot reported that his OAT gauge read 35 degrees C (95 degrees F) just prior to takeoff, and the EDM 800 (engine analyzer) recorded OAT between 95 and 97 F (~36C) during takeoff.

The closest airfield with an aviation meteorological recording system is Sacramento Mather Airport, Sacramento, California, 17 miles southwest of Cameron Park. Mather Airport has an AWOS-3 (aviation weather observation system) that recorded an atmospheric pressure of 29.89 inches of mercury (inHg) at 1245.

The calculated density altitude for Cameron Airpark at the time of the accident was 4,125 feet msl.

The video shows the windsock at the southeast end of the runway limp as the airplane accelerated past it, but immediately after the accident at the northwest end of the runway bush branches can be observed waving in a moderate breeze. The video also depicts the airplane crabbing to the northwest immediately after takeoff, while the airplane's shadow stayed positioned on the runway.

AERODROME INFORMATION

Cameron Air Park is located in a slight geographical bowl, with rising terrain at both ends of the runway. Field elevation is 1,293 feet msl. The single runway is marked 31 and 13, and is 4,051 feet long. Trees and buildings ring the airport.

WRECKAGE AND IMPACT INFORMATION

The wreckage was examined on-scene by the Safety Board IIC, with technical assistance provided by representatives from the FAA, Hawker-Beechcraft, and Teledyne-Continental Motors. The wreckage was located about 719 feet north of the end of runway 31, on the runway extended centerline, at an elevation of 1,330 feet msl. The terrain slopes up gradually to the north and is covered with dry grass, shrubs, and a few boulders. The initial point of contact with terrain was about 500 feet from the end of the runway at an elevation of 1,314 feet msl. The total distance from the initial point of impact to the main wreckage was 365 feet. At the 246-foot point a large boulder had been dislodged from the earth and traveled 60 feet to come to rest next to the wreckage.

The main wreckage was inverted, generally facing the direction it came from, and was oriented on a bearing of 130 degrees. The forward portion of the cockpit occupiable space had been compromised by a large dent on the bottom of the fuselage that went from the nose wheel through the center of the cabin to the aft wing spar, deforming the air conditioning condenser. The cabin contained four seats; the forward facing pilot and copilot seats, and two aft facing passenger seats. The forward windscreen was shattered and generally not present except for where it attaches to the airframe. The firewall had been pushed back into the cockpit and the engine was detached from the engine mount and lay next to the nose cowling. The left wing was attached to the fuselage at the forward and aft attach fittings, the right wing remained attached at the forward attach fitting. Fifty-three gallons of bluish fluid was extracted from the wing fuel bladders during the recovery of the wreckage.

Examination of the cockpit revealed that the landing gear handle was down, the flap handle was up, and t...