No fatalities

British Midland Airbus A321 In-Flight Engine Failure (G-MIDL)

FIR Lisboa, PT

On August 1, 2008, an Airbus A321-231 (registration G-MIDL) was involved in an aviation accident near FIR Lisboa, PT. No fatalities were reported. Investigators recorded the probable cause as: The initial damage to the high-pressure compressor was caused by foreign object damage (FOD) combined with organic impact ingested into the engine core during a previous flight. This summary draws on records from the Portuguese Office for the Prevention and Investigation of Accidents in Civil Aviation and Rail (GPIAAF).

Sourcesthe Portuguese Office for the Prevention and Investigation of Accidents in Civil Aviation and Rail (GPIAAF)Primary reportUpdated 2026-10-18Data APIEditorial standards
Aircraft registered G-MIDL
Aircraft registered G-MIDL. Photo: Björn Strey / CC BY-SA 2.0, via Wikimedia Commons

On August 1, 2008, British Midland Airbus A321-231 G-MIDL experienced an in-flight engine failure at FL350 in the Lisbon FIR. The crew shut down the right engine and diverted to Faro, Portugal, where the aircraft landed safely with no injuries.

Incident Overview and Flight History On August 1, 2008, British Midland operated an international passenger flight from East Midlands Airport in Great Britain to Tenerife South Airport in the Canary Islands, Spain. The aircraft, an Airbus A321-231 registered as G-MIDL, was operating as callsign BMA 7851 with 199 people on board, including two pilots, six cabin flight attendants, and 191 passengers. During steady cruise at flight level 350 in the Lisbon Flight Information Region, approximately 105 nautical miles west of Faro VOR, the flight crew reported an audible abnormal engine noise and noticed airframe vibrations. These symptoms were immediately followed by an “ENG2 STALL” message displayed on the Electronic Centralized Aircraft Monitor (ECAM). The crew performed the appropriate checklist and reduced the right engine power, which caused the stalls and indicator variations to disappear. However, attempting to increase thrust again brought back the abnormal engine behavior. Consequently, the crew decided to shut down engine number 2 and divert the aircraft to Faro International Airport in Portugal. The pilot-in-command performed an uneventful one-engine-inoperative landing at 09:27 UTC. The weather at Faro Airport was clear with no significant weather, calm winds, a QNH of 1020, and a temperature of 18°C. There were no personal injuries, and damage to the aircraft was confined to internal components of engine number 2.

Probable cause

The initial damage to the high-pressure compressor was caused by foreign object damage (FOD) combined with organic impact ingested into the engine core during a previous flight. This impact initiated cracks in a high-pressure compressor stage 6 rotor blade and a stator vane. The crack in the rotor blade propagated over time, leading to the release of the airfoil on July 30, 2008, which caused the first engine stall. The liberated airfoil then initiated a crack in a second rotor blade, and both the second rotor blade and the stator vane eventually released, causing further downstream damage. On August 1, 2008, the damaged and deteriorated high-pressure compressor was responsible for the second stall event during cruise, preventing the engine from operating above idle for the remainder of the flight.

Frequently asked questions

What happened in the 1 Aug 2008 Airbus A321-231 accident near FIR Lisboa, PT?

On August 1, 2008, British Midland Airbus A321-231 G-MIDL experienced an in-flight engine failure at FL350 in the Lisbon FIR. The crew shut down the right engine and diverted to Faro, Portugal, where the aircraft landed safely with no injuries.

Were there any fatalities in the 1 Aug 2008 Airbus A321-231 accident?

No fatalities were recorded in this accident.

What aircraft was involved and where did it happen?

The accident on 1 Aug 2008 involved an Airbus A321-231, registration G-MIDL, at FIR Lisboa, PT.

What was the probable cause of the accident?

The initial damage to the high-pressure compressor was caused by foreign object damage (FOD) combined with organic impact ingested into the engine core during a previous flight. This impact initiated cracks in a high-pressure compressor stage 6 rotor blade and a stator vane. The crack in the rotor blade propagated…