Service difficulty report · Blade · Airbus A320231

Difficulty date
March 11, 2004
Submitted
March 15, 2004
Operation
Air carrier
Aircraft
N620AW
Make and model
Airbus A320231
Aircraft serial
052
Aircraft time
46,482 hours, 21,015 cycles
Engine
Iae V2500A1
Engine time
42,310 hours, 19,060 cycles
Part
Blade
Condition
Cracked
Location
Nr 2 Engine
Part time
42,310 hours, 19,060 cycles
Stage of operation
CL
How discovered
O
Nature of condition
R, J
Precautionary procedure
A

As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.

What was found

AFTER TAKEOFF, EN ROUTE. NR 2 ENG STALLED WITH EGT OVERTEMP OF 843 DEGREE, FOLLOWED ECAM & DECLARED EMERGENCY. MX R / R NR 2 ENG IAW T/C. BORESCOPE OF HPC REVEALED 1, 7TH STAGE BLADE FRACTURED ROOT, & A SECTION OF 7TH STAGE REAR DAMPER WIRE MISSING OVER A SPAN OF FRACTURED BLADE & 2 ADJACENT BLADES. EXAMINATION OF BLADE SURFACE FOUND FRACTURE INDICATIVE OF HIGH CYCLE FATIGUE WITH ORIGIN CLOSE TO LE CONCAVE CORNER AT TOP EDGE OF BEDDING. A SHARP CORNER FOUND AT LOCATION & BELIEVED TO BE PRESENT WHEN BLADE WAS NEW. STRESS ANALYSIS ON 7TH STAGE BLADE WITH REAR DAMPER WIRE LEFT OUT, FOUND LACK OF DAMPER WIRE CAUSED BENDING THAT INCREASES STRESS ON LEADING EDGE OF BLADE WHERE ORIGIN OF FRACTURE WAS FOUND.

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