# NTSB LAX07LA280: Root Sherpa, N1415B, Scappoose, OR, September 18, 2007 - Type: NTSB accident investigation - Classification: Accident · Serious injuries · Limited investigation · Final report - Date: September 17, 2007, 17:45 local (Sep 18, 2007, 00:45 UTC) - Place: Scappoose, OR - Coordinates: 45.7738888888889, -122.85 - Nearby events: https://openairdocs.org/map.md?lat=45.7739&lon=-122.8500&mi=10 - Phase of flight: [Approach](https://openairdocs.org/ntsb-phases/500) (OpenAirDocs' grouping) - Highest injury: Serious injuries - Injuries: 1 serious, 1 minor - Status: Completed, report December 24, 2008 - Report: Approved by Office Director - Parties: Federal Aviation Administration - NTSB case key (mKey): 66765 - NTSB case page: https://web.ntsb.gov/investigations/?ntsbnumber=LAX07LA280 - NTSB report (PDF, downloads): https://data.ntsb.gov/carol-repgen/api/Aviation/ReportMain/GenerateNewestReport/66765/pdf - Page: https://openairdocs.org/ntsb/LAX07LA280 ## Probable cause A loss of aircraft pitch control due to the fatigue failure of the fuselage tube structure at the flight control stick gimbal mechanism due to an incomplete weld penetration at the root of the weld. ## Sequence of events In NTSB's coding before 2008 (https://www.ntsb.gov/GILS/Documents/codman.pdf). - Loss of control - in flight, approach - vfr pattern - final approach - flt control syst,elevator control - improper/poor weld (cause) - maintenance,installation - inadequate, owner/builder (cause) - flt control syst,elevator control - fatigue (cause) - In flight collision with terrain/water, descent - uncontrolled - terrain condition - runway ## Analysis The pilot was a potential buyer of the airplane and was flying it on short final approach. He said that he attempted to correct for a sink rate, which included pulling back full aft on the control stick to arrest the descent. The airplane's nose then abruptly pitched down about 45 degrees and the airplane struck the runway. A visual examination of the airplane's flight control system by Federal Aviation Administration (FAA) inspectors revealed that the flight control stick gimbal mechanism had fractured and the control stick was separated from the mechanism. The flight control stick gimbal mechanism and a portion of the fuselage structure were shipped to the Safety Board's Materials Laboratory for a metallurgical examination. According to the metallurgical examination, the fatigue cracking of the fuselage tube structure in the area of the control stick gimbal mechanism emanated from the root of a weld in an area between tube joints. The Safety Board's senior metallurgist reported that the fatigue had propagated through approximately 30 percent of the wall thickness. The fatigue crack was located near an area of the fuselage tube that contained a 0.7-inch-long region of incomplete weld penetration at the root of the weld. ## Factual narrative On September 17, 2007, about 1745 Pacific daylight time, an amateur-built experimental Root Sherpa, impacted runway 33 at the Scappoose Industrial Airpark, Scappoose, Oregon. The commercial pilot operated the borrowed airplane under the provisions of 14 Code of Federal Regulations Part 91 as a personal flight. The airplane sustained substantial damage. The pilot received minor injuries, and the pilot rated passenger was seriously injured. Visual meteorological conditions prevailed for the local flight, and no flight plan had been filed. According to the pilot it was a demonstration flight. He was interested in purchasing the airplane. He had flown the accident airplane the day prior to the accident with no problems, but with some concerns. He noted that the tail surface seemed "over-sensitive" and the airplane oscillated "very easily." The pilot reported that he was concerned about the low speed oscillations regarding the pitch attitude, as well as the need for "much" elevator down trim. In the pilot's submitted written report, he indicated that on base for runway 33, the airspeed was 60 miles per hour (mph) with 30 degrees of flaps. After turning on final, he input another 10 degrees of flaps, and reported that the indicated airspeed was between 55 to 60 mph, with some light to moderate turbulence present. The pilot stated that while on final, the sink rate began to increase for no apparent reason. He increased the throttle slightly to arrest the sink rate, which had a momentary effect. However, the sink rate began to increase again and did not stop when he applied power. At this point he was on short final, and he pulled the stick aft, which also had no effect on the sink rate or the pitch attitude of the airplane. Shortly thereafter, the airplane struck the runway in a nose down attitude. The pilot reported that the passenger had not been wearing his seatbelt. When the airplane hit the ground, the passenger came forward and struck the pilot's seat, pushing the pilot into the control stick and instrument panel. Federal Aviation Administration (FAA) inspectors responded to the accident site to examine the airplane. They noted the following damage to the flight control gimbal mechanism: internal corrosion with the presence of grease, oil, and dirt that was not as a result of the accident, paint peeling and corrosion under the paint in the area of the flight control gimbal mechanism separations. Their review of the maintenance history of the airplane revealed a previous accident history, and that the failure may have been caused during a previous event and had not been detected during repair. A review of the airplane logbooks revealed no entry for the installation of a new tail or wings. However, the FAA inspectors reported that a redesigned tail and wing sections were installed on the accident airplane prior to the accident. The purpose of the redesigned tail and wings were to lower the stall speed, improve slow flight handling characteristics, and to carry more fuel. TESTS AND RESEARCH The flight control stick gimbal mechanism and fuselage tube structure were shipped to the Safety Board's Materials Laboratory, Washington, D.C., for a metallurgical examination. According to the manufacturer's drawings for the airplane's elevator control system, when intact, the control stick is attached to the gimbal assembly, and a rod end is attached to the bottom of the gimbal assembly; these components are attached to the fuselage tube structure. A visual examination of the fuselage assembly by the FAA revealed that the control stick was not attached to the gimbal assembly, and the threaded portion of the rod end had fractured. The Safety Board's senior metallurgist also noted four tubes had fractured in the general area of the gimbal assembly that was part of the retaining bracket for the gimbal assembly. One of the tube's (identified as number 4 on the attached metallurgical report) showed a fatigue fracture that emanated from the inner surface at the root of the weld. The Safety Board's metallurgist reported that the fatigue had propagated through approximately 30 percent of the wall thickness. The fatigue crack was located near an area of the fuselage tube that contained a 0.7-inch-long region of incomplete weld penetration at the root of the weld. ## Aircraft - Registration: [N1415B](https://openairdocs.org/aircraft/N1415B), registered now, S/N 0012, built 1993 (OpenAirDocs) - Reported make and model: Root Sherpa - Registry model: [Root Byron L SHERPA](https://openairdocs.org/model/root-byron-l-sherpa) (registry code 05623QX) (OpenAirDocs) - Registry engine: [Lycoming IO-720 series](https://openairdocs.org/engine/lycoming-io-720-series) (registry code 41546, reciprocating) (OpenAirDocs) - Category: Airplane, amateur-built - Serial number: 0012 - Engines: Lycoming IO-720 400 horsepower reciprocating - Damage: Substantial damage - Flight: Personal, Part 91 - Registered owner: Byron L. Root - Airworthiness certificate: Special, Experimental (Special) - Departed: SPB, Scappoose, OR - Destination: SPB, Scappoose, OR - Airport: SPB, Scappoose Industrial Airpark, runway 33, 5,100 × 100 ft, asphalt ## Flight crew As NTSB recorded them. NTSB leaves out names. - Pilot; age 54; injuries: minor; private; airplane ratings: multi-engine land, single-engine land; instrument ratings: airplane; medical: class 3, with waivers/limitations; last flight review November 22, 2006; seat: front; flight hours: 1,247 total, 2 in this make and model, 1,158 as pilot in command, 47 in the last 90 days, 8 in the last 30 days, 1 in the last 24 hours ## Weather - Conditions: Visual (VMC), Day - Wind: 290° at 7 knots - Visibility: 10 statute miles - Lowest ceiling: 6,000 ft overcast - Temperature: 64 °F, dew point 39 °F - Altimeter: 30.12 inHg - Observed at: SPB ## 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 20070917020859A](https://openairdocs.org/incident/20070917020859A), Sep 17, 2007: Amtr ROOTSHERPA, Scappoose, OR, Substantial damage. (-23) The pilot [privacy data omitted] was in process possibly buying this experimental aircraft, sherpa by name, manufactured by [privacy data omitted] in… ## Other investigations on N1415B (1) 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. - [NTSB SEA00LA145](https://openairdocs.org/ntsb/SEA00LA145), Jul 28, 2000: Root Sherpa (N1415B), Helena, MT, substantial damage. Probable cause: The pilot's failure to maintain directional control while landing. 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.