If you wish to contribute or participate in the discussions about articles you are invited to join SKYbrary as a registered user

 Actions

B772, Denver CO USA, 2001

From SKYbrary Wiki

Summary
On 5 September 2001, a British Airways Boeing 777-200 on the ground at Denver USA, was substantially damaged, and a refuelling operative killed, when a fire broke out following the failure of a refuelling coupling under pressure because of improper attachment.
Event Details
When September 2001
Actual or Potential
Event Type
Fire Smoke and Fumes, Ground Operations, Human Factors
Day/Night Day
Flight Conditions On Ground - Normal Visibility
Flight Details
Aircraft BOEING 777-200 / 777-200ER
Operator British Airways
Domicile United Kingdom
Type of Flight Public Transport (Passenger)
Origin London Heathrow Airport
Intended Destination Denver International Airport
Take off Commenced Yes
Flight Airborne Yes
Flight Completed Yes
Flight Phase Parked
Note
Location - Airport
Airport Denver International Airport
FIRE
Tag(s) Fire-Fuel origin
HF
Tag(s) Ineffective Monitoring,
Procedural non compliance
GND
Tag(s) Fuel Loading
Outcome
Damage or injury Yes
Aircraft damage Major
Non-aircraft damage Yes
Non-occupant casualties Yes ()
Causal Factor Group(s)
Group(s) Aircraft Technical
Safety Recommendation(s)
Group(s) None Made
Investigation Type
Type Independent

Description

On 5 September 2001, a British Airways Boeing 777-200 on the ground at Denver, Colorado, was substantially damaged, and a refuelling operative killed, when a fire broke out following the failure of a refuelling coupling under pressure because of improper attachment.

Synopsis

This is Summary and Probable Cause of the accident published by the National Transportation Safety Board (NTSB) (USA)

“During refuelling, with the airplane parked at the gate to unload passengers, a pressurized refuelling hose broke loose from the airplane and a fire erupted. The hose which broke loose was the inboard of two hoses which had been attached by the refueller to the left wing refuelling panel. Examination of the hose revealed that it came loose due to the fracture of the three refuelling adapter ring locking lugs on the airplane's inboard left wing refuelling port. Metallurgical examination of the inboard (fractured) adapter and the outboard adapter indicated that although the inboard adapter had a different microstructure and probably a different heat treatment history from the outboard adapter, they both met the applicable requirements for ultimate tensile strength and chemistry. Additionally, the metallurgical examination found the locking lug fractures to be the result of a one-time ductile overstress with no indications of pre-existing cracking, corrosion, or defects that would have degraded the load-carrying capacity of the adapter. Therefore, the failure of the adapter was the result of an overload applied at the time of the separation. The investigation revealed that the refueller had improperly positioned the hydrant truck in relation to the airplane's left wing refuelling panel prior to commencing refuelling operations. Because of this positioning, the lift platform's left railing obstructed the normal nozzle attachment procedure to the airplane's inboard manifold adapter. Subsequently, while attaching the nozzle, the refueller improperly routed the hose over the top of the front railing, around the left forward corner support of the railing structure, and aft to the airplane's inboard manifold adapter ring. The investigation also revealed evidence consistent with the refueler lowering the lift platform, for personal comfort during the long refueling, and the refueling hose then catching on the platform's left front railing and bumper. Vertical pull tests indicated that the three nozzle attachment lugs were capable of supporting a load in excess of 10,000 pounds if the load was applied along the nozzle centerline. However, the weight bearing capability of the lugs dropped off as the load was applied at increasing angles off the centerline. At an angle of 30 degrees off centerline, the lugs failed below 1,000 pounds of load. The refueler's improper routing of the fuel hose would have placed an off-axis load of approximately 52 degrees. The angular force applied to the manifold adapter ring was amplified when the refuelling hose was pressurized. The combination of the two forces resulted in the adapter ring's failure. Pressurized fuel discharged forming a fuel mist cloud that subsequently ignited. The resulting fire resulted in fatal injuries to the refueller. The airplane's lower leading edge panels, the refuelling control panel, and the outboard portions of the left engine fan cowl and thrust reverser were thermally damaged. The hydrant truck was destroyed in the fire. Since the accident, two companies have introduced modifications to help position hydrant dispenser trucks during single person operations, and industry groups are examining the need for changes to existing industry standards and practices of aircraft fuelling.

The National Transportation Safety Board determines the probable cause(s) of this accident as follows:

the overstress fracture of the airplane's refuelling adapter ring that resulted from the abnormal angular force applied to it. The applied angular force occurred due to the ground refueller inadequately positioning the hydrant fuel truck (in relation to the airplane), and his inattentiveness while lowering the refuelling lift platform, thus permitting the refuelling hose to become snagged and pulled at an angle. The fracture of the adapter ring during the refuelling led to the ignition of the pressurized (mist producing) spilled fuel and subsequent fire. "

Related Articles

Further Reading