Service difficulty report · Door Frame · Airbus A320232

Difficulty date
November 3, 2018
Submitted
January 15, 2019
Operation
Air carrier
Aircraft
N504JB
Make and model
Airbus A320232
Aircraft serial
1156
Aircraft time
73,404 hours, 27,499 cycles
Part
Door Frame
Condition
Cracked
Location
Fuselage
Stage of operation
IN
How discovered
V
Nature of condition
O
Precautionary procedure
K

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

What was found

DURING HEAVY CHECK AT SAL, UNDERGOING REF /2/ INSPECTION WHEN CRACK DAMAGE WAS REPORTED AT FR16 LT JUST ABOVE DOOR STOP 7 ON HOLES A AND C. CONTACTED AND PROVIDED REF. /4/. HOLES A & C WERE REAMED, COLD WORKED, AND BUSHING AND DOUBLERS WERE INSTALLED. ADJACENT HOLES B & D WERE REAMED AND COLD WORKED ONLY. HOLES E & F WERE INSPECTED WITHOUT ANY FINDINGS. EC A18-845-01 IS ISSUED TO PROVIDE THE PERMANENT REPAIR INSTRUCTIONS PER REF /4/. EC A18-845-02 IS ISSUED TO PROVIDE THE POST-REPAIR INSTRUCTIONS FOR HOLES A & B, FROM TIME OF REPAIR EMBODIMENT. THRESHOLD = 6800FC (FH NOT RELEVANT) INTERVAL = 4383 FC (FH NOT RELEVANT). METHOD OF INSPECTION: (1) AT REPAIRED HOLE A: ROTOTEST INSPECTION AS PER NTM 51-10-01 AFTER FASTENER REMOVAL & NTM 51-10-18 AFTER BUSH REMOVAL (2) AT ASSOCIATED HOLE B: ROTOTEST INSPECTION AS PER NTM 51-10-01 AFTER FASTENER REMOVAL EC A18-845-03 IS ISSUED TO PROVIDE THE POST-REPAIR INSTRUCTIONS FOR HOLES C & D, FROM TIME OF REPAIR EMBODIMENT. THRESHOLD 6800FC (FH NOT RELEVANT), INTERVAL = 4742 FC. METHOD OF INSPECTION: (1) AT REPAIRED HOLE C: ROTOTEST INSPECTION AS PER NTM 51-10-01 AFTER FASTENER REMOVAL & NTM 51-10-18 AFTER BUSH REMOVAL AT ASSOCIATED HOLE D: ROTOTEST INSPECTION AS PER NTM 51-10-01 AFTER FASTENER REMOVAL; THIS REPAIR IS APPROVED PER REF. REF /3/ RDAS AND IS CLASSIFIED AS MAJOR CATEGORY 'B'.

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