Pilot Debrief

AIRBUS A319 132 near Greenville, TX — 2013-10-15

Final reportENG14IA001
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Date
2013-10-15
Location
Greenville, TX, USA
Airport
DFW
Aircraft
AIRBUS A319 132
Registration
N516NK
Category
Airplane
Highest injury
None
Fatalities
0
Phase of flight
Climb

Probable cause

A high pressure turbine 2nd stage blade separation due to stress corrosion cracking in the J channel cooling cavity. The failed blade entered the gas path and caused substantial damage to the low pressure turbine. The engine was subsequently left at a high power setting for approximately four minutes, exposing the turbine hardware to temperatures that exceeded the material annealing temperature and resulted in in failure and separation of multiple engine components.

NTSB narrative

Based on metallurgical analysis, a No. 1 engine high pressure turbine (HPT) 2nd stage blade separated below the blade platform due to stress corrosion cracking in the blade J-channel cooling air cavity. The liberated blade entered the gas path and caused extensive damage to the HPT and low pressure turbine (LPT) hardware and cases. The damaged engine was left at a high power setting for about four minutes until the crew received a No. 1 engine fire warning. During this time the turbine was exposed to temperatures that exceeded the material annealing temperature and resulted in failure and separation of multiple components including the LPT 3rd and 4th stage disks, turbine exhaust case center body, and the No. 5 bearing housing. The engine nacelle was not breached and all separated engine components traveled out the back of the engine.

Analysis

Primary failure mode
Mechanical failure
First missed decision gate
Crew could have shut down the No. 1 engine earlier after EGT over limit warning.

NTSB coding

  • Powerplant sys/comp malf/fail · Enroute-climb to cruise

Evidence available

  • CVR
  • FDR / data
  • Photos
  • 10 docket documents
View NTSB final reportView NTSB docket

Docket documents10

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