|Title:||Wing gear collapse, Boeing 747-228F, F-GCBG, January 3, 2002|
|Micro summary:||This Boeing 747 experienced a wing landing gear collapse.|
|Event Time:||2002-01-03 at 0446 CST|
|Publishing Agency:||National Transportation Safety Board (NTSB)|
|Site of event:||Houston Intercontinentl|
|Departure:||Lic. Benito Juárez International Airport, Mexico City, Mexico|
|Destination:||George Bush Intercontinental Airport, Houston, Texas, USA|
|Airplane Type(s):||Boeing 747-228F|
|Type of flight:||Cargo|
|Executive Summary:||On January 3, 2002, about 0446 central standard time, a Boeing 747-228F airplane, French registration F-GCBG, experienced a wing landing gear collapse after landing on runway 15L at the Houston Intercontinental Airport, Houston, Texas. The cargo configured airplane was registered to and operated by Air France. The flight crew (Captain, First Officer, and Flight Engineer) were not injured. Dark night visual meteorological conditions prevailed and an Instrument Flight Rules (IFR) flight plan was filed for the 14 Code of Federal Regulations Part 129 international cargo flight that originated from Mexico City, Mexico, at 0245.|
After touchdown and rollout, the airplane exited the runway onto a high-speed taxiway. The captain, noticed that the airplane was "dragging," to the right. The need for additional power for taxi seemed too great, so the crew stopped taxi and applied the parking brake. Two warning lights on the landing gear panel indicated that there was a problem with the right main wing gear. Additionally, the flight engineer's instrument panel confirmed an open hydraulic circuit (wheel brakes) on the right main wing gear. The airplane's engines were stopped, the APU was started, and ground personnel performed a visual inspection which revealed that the right wing landing gear assembly was partially collapsed and tilted inward toward the fuselage. The top of the right wing gear aft trunnion was found fractured and protruding upward through the top of the right wing surface. There was minor damage to surrounding wing structure and lines to the #4 hydraulic system (wheel brakes) were found ruptured.
On-site examination of the airplane by the NTSB investigator-in-charge, FAA air safety inspectors, Air France maintenance personnel, and a Boeing engineer confirmed that the right outboard main landing gear trunnion was completely fractured and separated several inches inboard of the aft trunnion bearing. Further visual inspection of the fractured area showed evidence of corrosion and what appeared to be a pre-existing crack on the upper portion of the outer cylinder of the trunnion. The lower portion of the outer cylinder was cut away to facilitate shipment of the parts to the NTSB Materials Laboratory, Washington, D.C., for detailed examination.
Examination of the parts was conducted at the Safety Board's Materials Laboratory on January 17-18, 2002. During the examination, the aft trunnion on the upper portion of the outer cylinder was found fractured through the outboard cross bolt hole. Very dark, thick deposits were noted on a portion of the fracture that intersected the cross bolt hole on a flat, 45-degree spiral plane. Evidence of pre-existing corrosion was found in the fractured surface of the outer cylinder. The predominate features of the fractures showed evidence of stress corrosion cracking (SCC). Typically, stress corrosion cracking propagates under sustained loading (not cyclic loading) which is the predominate loading that the outer cylinder is subjected to while resting on its landing gear. A detailed report of the materials examination is included as a supporting document to this report.
Historical information on the airplane and the landing gear assembly were provided by the operator. A review of the information provided revealed the following. The airplane's total time since new was 81,124 hours, and 15,988 cycles since new. The right wing landing gear assembly, P/N: 65B01464-34, S/N: CP001482, was installed on December 27, 1994 during a heavy "D" check. The assembly had accumulated 11,599 cycles since new, and 5,496 cycles since overhaul. The outer cylinder P/N: 65B01430-18, S/N: 3701, was installed together with the wing landing gear assembly on December 27, 1994. The cylinder had accumulated 5,496 cycles since overhaul.
Mandatory inspections of the wing landing gear assembly were outlined in Boeing Service Bulletin (SB) 747-32-2190 revision 7, and Alert Service Bulletin (ASB) 747-32A2465 revision 1. These service bulletins were respectively mandated by FAA Airworthiness Directives (AD) 90-06-18 R1, and AD 2001-17-25. AD 2001-17-25, issued on October 3, 2001, superceded AD 90-06-18 R1. Entries in the operators maintenance records showed that SB 747-32-2190 revision 7 was complied with during the wing landing gear replacement performed on December 27, 1994. Entries in the records also showed visual and eddy current inspections at 18-month intervals since December, 1994. According to the records, the last visual and eddy current inspection was performed on July 21, 2001, and did not reveal any defects.
The inspection criteria outlined in AD 90-06-18 R1 required the operator to perform a visual inspection, or a visual plus eddy current inspection of the wing landing gear at the trunnion, for cracks and corrosion. The inspection criteria outlined in AD 2001-17-25 required the operator to perform a detailed visual inspection using a bore scope to find cracking and corrosion of the aft trunnion outer cylinders of the wing landing gear, within 180 days from October 3, 2001. According to the operator's records, the bore scope inspection had not been performed, as per the AD, it was not due until April 3, 2002.
Historical review of Service Difficulty Reports (SDR's) revealed 19 occurrences of SCC associated with corrosion of the aft trunnion outer cylinder stressed areas. Due to these SDR data, the manufacturer issued ASB 747-32A2465 revision 1, which was mandated by a new FAA AD 2001-17-25. AD 2001-17-25 included a bore scope inspection of the affected area of the trunnion due to the fact that the propagation of SCC cracking was internal on the cylinder and not readily detected by visual or eddy current methods as per the original AD 90-06-18 R1.
|Learning Keywords:||Operations - Maintenance|
|Systems - Landing Gear|
|Systems - Landing Gear - MLG Collapse|
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