Casualties unknown

2005-08-21: MD 82 (ZS-TRD) — During climb at Cape Town International Airport, ZA

During climb at Cape Town International Airport, ZA

On August 21, 2005, a MD 82 (registration ZS-TRD) was involved in an aviation accident near During climb at Cape Town International Airport, ZA. Investigators recorded the probable cause as: The engine failure was caused by foreign object damage (FOD) impacting the engine components. This summary draws on records from the South African Civil Aviation Authority (SACAA) Accident and Incident Investigations Division.

Sourcesthe South African Civil Aviation Authority (SACAA) Accident and Incident Investigations DivisionPrimary reportUpdated 1785104676Data APIEditorial standards
Aircraft registered ZS-TRD
Aircraft registered ZS-TRD. Photo: Simisa ( talk · contribs ) / CC BY-SA 3.0, via Wikimedia Commons

An MD 82 experienced a contained engine failure during its initial climb from Cape Town International Airport due to foreign object damage.

What happened

On 21 August 2005, a domestic scheduled flight operated by an MD 82, registration ZS-TRD, departed from Cape Town International Airport (FACT) bound for OR Tambo International Airport (FAJS). During the takeoff roll, the crew observed that the right-hand engine's N2 and exhaust gas temperature (EGT) were slightly higher than those of the left-hand engine.

As the aircraft climbed through 3,000 feet above mean sea level, the crew heard several loud bangs, followed by the right-hand engine spooling down. In response, the automatic reserve thrust (ART) engaged on the left-hand engine. The crew subsequently shut down the right-hand engine and successfully returned to Cape Town for a safe landing. There were 0 fatalities and 0 injuries among the passengers and crew.

The investigation

Investigators examined the right-hand engine to determine the source of the failure. A borescope inspection performed by the South African Technical Maintenance Control Centre revealed significant internal damage. The inspection identified a nick on one fan blade located 5.5 inches from the blade root.

Further examination of the engine's internal components showed that several low-pressure compressor (LPC) blades had sustained severe damage to their trailing edges. Additionally, the high-pressure compressor (HPC) exhibited extensive damage to the blade leading edges and instances of tip separation caused by impact. The first-stage turbine blades of the high-pressure turbine (HPT) also showed evidence of leading-edge damage.

Probable cause

The engine failure was caused by foreign object damage (FOD) impacting the engine components.