# NTSB LAX04LA253: Anderson Harmon Rocket II, N28BE, Seal Beach, CA, July 7, 2004 - Type: NTSB accident investigation - Classification: Accident · Fatal · Limited investigation · Final report - Date: July 7, 2004, 08:11 local (15:11 UTC) - Place: Seal Beach, CA - Coordinates: 33.780834, -118.100555 - Nearby events: https://openairdocs.org/map.md?lat=33.7808&lon=-118.1006&mi=10 - Phase of flight: [Enroute](https://openairdocs.org/ntsb-phases/400) (OpenAirDocs' grouping) - Highest injury: Fatal - Injuries: 1 fatal, 3 minor; on the ground: 3 minor - Status: Completed, report December 20, 2005 - Report: Approved by Office Director - Parties: Lycoming, Federal Aviation Administration, Harmon Rocket - NTSB case key (mKey): 59586 - NTSB case page: https://web.ntsb.gov/investigations/?ntsbnumber=LAX04LA253 - NTSB report (PDF, downloads): https://data.ntsb.gov/carol-repgen/api/Aviation/ReportMain/GenerateNewestReport/59586/pdf - Page: https://openairdocs.org/ntsb/LAX04LA253 ## Probable cause the in-flight separation of the elevator, which resulted in a loss of airplane control and an uncontrolled descent. The underlying cause and mechanism of the elevator separation could not be determined. ## Sequence of events In NTSB's coding before 2008 (https://www.ntsb.gov/GILS/Documents/codman.pdf). - Airframe/component/system failure/malfunction, cruise - flight control,elevator - separation (cause) - flight control,rudder - separation (cause) - Loss of control - in flight, cruise - aircraft control - not possible, pilot in command (cause) - flight control,elevator - lack of - In flight collision with terrain/water, descent - uncontrolled - object - residence ## Analysis The airplane collided with a residence following an in-flight separation of the vertical stabilizer, elevator, and upper rudder, which resulted in an uncontrolled descent. The pilot, who was also the builder of the airplane, was on an instrument flight. While established in cruise flight at an elevation of approximately 5,000 feet mean sea level and 200 knots, radar contact was suddenly lost when the airplane entered a rapid descent. Review of the aircraft's radar data revealed primary radar returns were located near the aircraft's mode C returns near the time of the upset. Aerial and ground searches using trajectory data analysis on the primary radar returns commenced; however, no additional components were located. During a post-accident examination of the wreckage, investigators were unable to identify the stabilizer. The day prior to the accident the pilot indicated that he was experiencing control problems with the elevator trim system on the airplane. A manufacturer of another experimental aircraft kit, similar in design to the accident airplane kit, performed structural testing of his kit. These tests indicated that the flight loading could exceed the structural strength of the horizontal and vertical stabilizer control surface so modifications were made in his model to increase the structural strength. These structural modifications were not completed in the accident airplane, nor were they required. There is no requirement for experimental aircraft manufacturers or kit suppliers to analyze the structural integrity of the airplane throughout its operating envelope, nor does a builder have to establish the adequacy of the design during flight tests. The pilot's immediate family had a history of sudden death due to aneurisms and heart failure. Due to the circumstances of the accident, no usable medical data could be obtained to discern the pilot's medical condition at the time of the accident. ## Factual narrative HISTORY OF FLIGHT On July 7, 2004, at 0811 Pacific daylight time, an experimental Anderson Harmon Rocket II, N28BE, impacted a residence in Seal Beach, California, following an uncontrolled descent. Impact forces and a post crash fire destroyed the airplane. The airline transport pilot, who was also the builder and registered owner, was operating the airplane under the provisions of 14 CFR Part 91. The pilot, the sole occupant, was fatally injured; three people on the ground sustained minor injuries. The airplane departed Zamperini Field, Torrance, California, at 0802, and was flying a tower en route control (TEC) instrument clearance to the Chino Airport, Chino, California. A combination of instrument and visual meteorological conditions prevailed along the route of flight that was being flown under instrument flight rules (IFR). According to the Federal Aviation Administration (FAA), air traffic control cleared the pilot to climb to 5,000 feet mean sea level (msl), and proceed direct to the Seal Beach VHF Omni-directional Range/Tactical Air Navigation (VORTAC). Recorded radar data depected the aircraft's target return in cruise flight with a mode C report of 5,300 feet msl, and then radar contact was lost. According to a witness riding his bicycle southbound on a bike path, he heard a noise that "made the hairs on the back of my neck stand up." He looked over his left shoulder and saw the airplane coming out of the 600-foot cloud layer in a 75-degree nose-down attitude. The airplane impacted about 100 yards from the witness's location. The witness was an engineer, and a former glider pilot with about 800 flight hours. Another witness stated that the airplane was flying north and the engine noise was increasing. The airplane was approximately 200 feet above ground level (agl). The wing was almost perpendicular to ground level. The airplane then arched downward and impacted the ground nose-first. This occurred over a period of about 3 seconds. PERSONNEL INFORMATION The pilot held an airline transport pilot certificate for single and multiengine airplanes. He also held a repairman experimental aircraft builder certificate for the Harmon Rocket II, serial number 017 (the accident airplane). The pilot's most recent third-class medical was issued on April 29, 2003. The personal logbooks of the pilot were not recovered. The pilot's family reported that he carried his logbook in the airplane when he flew. Based on an insurance application obtained from the pilot's family, dated June 9, 2004, he had a total flight time of 5,000 hours. Two hundred hours were in the past 12 months; 50 hours were in the past 90 days. The pilot had experience in the following categories, as listed on the insurance application: tailwheel, 550; retractable gear, 4,000; multiengine, 2,300; jet, 3,200; 1,000 instrument (actual and simulated); and a type rating for a Cessna Citation issued in 1977. The pilot had also flown P-51, T-6, and T-28 airplanes. Throughout his career in the United States Navy he flew additional military aircraft as well. From 2002 to 2003 he attended aerobatics training at a local airport. AIRCRAFT INFORMATION The Harmon Rocket II airplane was a low-wing, single engine, experimental airplane, constructed by the pilot over a period of 13 years. The last inspection was completed on May 27, 2004, and was in accordance with the scope and detail to 14 CFR Part 43, appendix D. At the time of the accident the airplane had accrued approximately 250 hours. The airplane was equipped with a Lycoming IO-540-C4B5 engine, serial number L-26847-48A, modified so that it was for experimental use only. The two-bladed propeller was a Hartzell HC-M2YR-1BF/F8475J-4, serial number EN 995B. The week prior to the accident, the pilot and his wife flew to Jackson Hole, Wyoming, in the accident airplane. The entire trip was flown under visual flight rules. According to the pilot's wife, she was not aware of any mechanical issues with the airplane during or following the flight. On the day of the accident, a witness, who was a retired mechanical engineer, was waiting for his friend to arrive at the Chino Airport about 1200. While he was waiting he walked to Square One Aviation, a P-51 restoration company owned by the pilot. As he was walking toward the Square One Aviation hangar, he noticed N28BE parked on the ramp. There was a man lying down on the asphalt under the empennage section of the airplane. The man's hands were reaching inside of the airplane but the witness could not see any tools on the ground surrounding him. The day prior to the accident, the pilot told the general manager of Square One Aviation that he was having trim system problems with the airplane. During the morning's flight from Torrance to Chino, he was required to hold the stick in the full aft position. The electric trim would travel in one direction but not in the other. The pilot was looking at the airplane between 1200 and 1330. A receipt dated July 6, 2004, was acquired from Aircraft Spruce and Specialty Company. The receipt listed the following purchases: SAF-Air Drain Valves; RAC Servo Relay Deck; RAC Clevis/Pushrod; and RAC Servo Only. Following the accident, all of the purchased parts were located in the pilot's hangar except for the RAC Servo Relay Deck. According to the Aircraft Spruce and Specialty Company catalog, the purpose of the servo relay deck is to convert the SPST (single-pole, singe -throw) momentary contact action of any pair of switches, or a 4-way switch, into a DPDT (double-pole, double-throw) action that is necessary to operate R.A. [RAC] servos. The two internal relays are wired special for this and rated at 1 amp. According to a builder of a Harmon Rocket II airplane, if a builder uses normal switches to operate the RAC trim servos, they need to be wired through the servo relay deck. The Ray Allen Company, manufacturer of the RAC Servo Relay Deck, did not report any known malfunctions of the relay deck or of the associated components based on customer service reports. According to the owner of Harmon Rocket, LLC., he supplies parts to convert the RV-4, home-built kit, offered by Van's Aircraft, Inc., to a Harmon Rocket. The airplane modification kit was structurally tested through dive tests. The flight testing of the Harmon Rocket II consisted of flutter testing up to 300 miles per hour (mph), stability testing on the ailerons and elevators, g-load testing to 6 positive, and aerobatics training that included loops, rolls, and spins. No drawings were created for the tests. The single change made to the empennage section was an increase in the metal skin thickness from 0.016 to 0.020 inches. At the time of this report's writing, approximately 214 kits have been sold and 108 airplanes are currently flying. The F-1 Rocket, also an experimental aircraft, is a similar design to the Harmon Rocket II. The F-1 has the same engine and is based on the RV-4 airframe design. The owner of F-1 had his airframe vendor company perform analytical testing on the structural components of the airframe to ensure adequate structural design of the RV-4 during increased airspeeds. As a result of the analytical calculations, the following findings and/or changes were made to the aircraft design: - The middle hinge on the elevator could be overloaded at increased airspeeds; however, the hinge was not changed due to the fact that there have been no previously reported problems. - The horizontal stabilizer's spar channel was changed from a material thickness of 0.032 inches to 0.040 inches. - The vertical fin's forward spar attachment (where it attached to the horizontal stabilizer) was enlarged and a doubler was placed on the spar to aid in side load tolerances. - The vertical stabilizer and the rudder were increased in length approximately 5 inches. METEOROLOGICAL INFORMATION The routine auto ## Aircraft - Registration: [N28BE](https://openairdocs.org/deregistered/N28BE-2005-08-11), registration cancelled 2005-08-11, S/N 017, built 2003 (OpenAirDocs) - Reported make and model: Anderson Harmon Rocket II - Registry model: [Anderson Ross K HARMON ROCKET II](https://openairdocs.org/model/anderson-ross-k-harmon-rocket-ii) (registry code 05614NG) (OpenAirDocs) - Registry engine: [Lycoming IO-540 series](https://openairdocs.org/engine/lycoming-io-540-series) (registry code 41530, reciprocating) (OpenAirDocs) - Category: Airplane, amateur-built - Serial number: 017 - Airframe hours: 250 - Engines: Lycoming IO-540-EXP 250 horsepower reciprocating - Damage: Destroyed - Fire: On-Ground - Flight: Personal, Part 91 - Registered owner: Ross Anderson - Airworthiness certificate: Special, Experimental (Special) - Last inspection: Continuous airworthiness, May 1, 2004 - Departed: TOA, Torrance, CA - Destination: CNO, Chino, CA - Flight plan: IFR ## Flight crew As NTSB recorded them. NTSB leaves out names. - Pilot; age 62; injuries: fatal; airline transport; airplane ratings: multi-engine land, single-engine land; instrument ratings: airplane; medical: class 3, valid medical--w/ waivers/lim; last flight review July 1, 2003; seat: front; toxicology performed; flight hours: 5,000 total, 250 in this make and model ## Weather - Conditions: Instrument (IMC), Day - Visibility: 7 statute miles - Lowest ceiling: 1,600 ft overcast - Temperature: 66 °F, dew point 59 °F - Altimeter: 29.98 inHg - Observed at: LGB, 4 nm away ## FAA reports on this event (1) The FAA's own accident and incident reports, matched to the aircraft by N-number and date (OpenAirDocs). - [Accident 20040707015489A](https://openairdocs.org/incident/20040707015489A), Jul 7, 2004: Amtr HARMONRCKTII, Seal Beach, CA, Destroyed, 1 fatal. (-23) Aircraft was operating under provisions of 14 CFR part 91, with IFR flight plan toa/cno. At approximately 0809PDT, N28BE, an experimental two place… From the NTSB's public API. Aircraft are matched to registry aircraft by N-number and event date, checked against the reported serial number, make and model; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model. --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.