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Attributes | |
ACN | 613739 |
Time | |
Date | 200403 |
Day | Thu |
Local Time Of Day | 0601 To 1200 |
Place | |
Locale Reference | airport : zzz.airport |
State Reference | US |
Altitude | agl single value : 0 |
Aircraft 1 | |
Operator | common carrier : air carrier |
Make Model Name | A320 |
Operating Under FAR Part | Part 121 |
Flight Phase | ground : maintenance |
Flight Plan | IFR |
Person 1 | |
Affiliation | company : air carrier |
Function | maintenance : technician |
Qualification | technician : airframe technician : powerplant |
Experience | maintenance technician : 15 |
ASRS Report | 613739 |
Person 2 | |
Affiliation | company : air carrier |
Function | maintenance : technician |
Qualification | technician : airframe technician : powerplant |
Experience | maintenance technician : 15 |
ASRS Report | 611593 |
Events | |
Anomaly | aircraft equipment problem : critical other anomaly other |
Independent Detector | other other : person 1 |
Resolutory Action | none taken : detected after the fact |
Consequence | other other |
Factors | |
Maintenance | contributing factor : work cards contributing factor : manuals performance deficiency : scheduled maintenance |
Supplementary | |
Problem Areas | Aircraft Chart Or Publication |
Primary Problem | Aircraft |
Narrative:
After removing vertical stabilizer panel 321AL to inspect wiring harnesses per our job card, we noticed small cracks propagating from 2 hi-lok fasteners on the front spar next to the transverse load fittings. We informed inspection and they made a write-up. At this time engineering is still trying to decide what to do. There is no type of ndt that will tell us how deep the cracks are. Callback conversation with reporter revealed the following information: the reporter stated the job card being worked was to check the electrical braided conduit that was attached to the vertical stabilizer forward spar. The reporter said two hi-lok fasteners on a diagonal brace appeared to have cracks radiating from the holes drilled in the web of the spar. The reporter stated one hole had two cracks and the other hole had only one. The reporter said the cracks were approximately .001 inch in length and were written up for inspector and engineering fillip. The reporter stated the inspectors were able to finesse a borescope in the two holes and believe the cracks went through the .50 inch web. The reporter said the spar is of composite construction and no non-destructive testing methods or instruments are presently available and no repair procedures are in the structural repair manual. Callback conversation with reporter acn 611593 revealed the following information: the reporter stated the cracks were found on a job card that inspected the braided conduit on the forward vertical stabilizer spar. The reporter said the hi-lok fasteners were attached to a diagonal support near the transverse load fittings. The reporter stated the hi-lok fasteners were removed and one hole had two cracks and the other one crack. The reporter said all the cracks were estimated to be about .001 inch in length and appeared to be through the web, which is .50 inch thick. The reporter stated the structural repair manual does not address this situation for testing or repair.
Original NASA ASRS Text
Title: AN AIRBUS 320 DURING MAINT CHECK WAS FOUND TO HAVE 3 CRACKS APPROX .001 INCH IN LENGTH FROM HI-LOK FASTENER HOLES IN THE VERTICAL STABILIZER FORWARD SPAR.
Narrative: AFTER REMOVING VERT STAB PANEL 321AL TO INSPECT WIRING HARNESSES PER OUR JOB CARD, WE NOTICED SMALL CRACKS PROPAGATING FROM 2 HI-LOK FASTENERS ON THE FRONT SPAR NEXT TO THE TRANSVERSE LOAD FITTINGS. WE INFORMED INSPECTION AND THEY MADE A WRITE-UP. AT THIS TIME ENGINEERING IS STILL TRYING TO DECIDE WHAT TO DO. THERE IS NO TYPE OF NDT THAT WILL TELL US HOW DEEP THE CRACKS ARE. CALLBACK CONVERSATION WITH RPTR REVEALED THE FOLLOWING INFO: THE RPTR STATED THE JOB CARD BEING WORKED WAS TO CHECK THE ELECTRICAL BRAIDED CONDUIT THAT WAS ATTACHED TO THE VERT STAB FORWARD SPAR. THE RPTR SAID TWO HI-LOK FASTENERS ON A DIAGONAL BRACE APPEARED TO HAVE CRACKS RADIATING FROM THE HOLES DRILLED IN THE WEB OF THE SPAR. THE RPTR STATED ONE HOLE HAD TWO CRACKS AND THE OTHER HOLE HAD ONLY ONE. THE RPTR SAID THE CRACKS WERE APPROX .001 INCH IN LENGTH AND WERE WRITTEN UP FOR INSPECTOR AND ENGINEERING FILLIP. THE RPTR STATED THE INSPECTORS WERE ABLE TO FINESSE A BORESCOPE IN THE TWO HOLES AND BELIEVE THE CRACKS WENT THROUGH THE .50 INCH WEB. THE RPTR SAID THE SPAR IS OF COMPOSITE CONSTRUCTION AND NO NON-DESTRUCTIVE TESTING METHODS OR INSTRUMENTS ARE PRESENTLY AVAILABLE AND NO REPAIR PROCS ARE IN THE STRUCTURAL REPAIR MANUAL. CALLBACK CONVERSATION WITH RPTR ACN 611593 REVEALED THE FOLLOWING INFO: THE RPTR STATED THE CRACKS WERE FOUND ON A JOB CARD THAT INSPECTED THE BRAIDED CONDUIT ON THE FORWARD VERT STABILIZER SPAR. THE RPTR SAID THE HI-LOK FASTENERS WERE ATTACHED TO A DIAGONAL SUPPORT NEAR THE TRANSVERSE LOAD FITTINGS. THE RPTR STATED THE HI-LOK FASTENERS WERE REMOVED AND ONE HOLE HAD TWO CRACKS AND THE OTHER ONE CRACK. THE RPTR SAID ALL THE CRACKS WERE ESTIMATED TO BE ABOUT .001 INCH IN LENGTH AND APPEARED TO BE THROUGH THE WEB, WHICH IS .50 INCH THICK. THE RPTR STATED THE STRUCTURAL REPAIR MANUAL DOES NOT ADDRESS THIS SITUATION FOR TESTING OR REPAIR.
Data retrieved from NASA's ASRS site as of July 2007 and automatically converted to unabbreviated mixed upper/lowercase text. This report is for informational purposes with no guarantee of accuracy. See NASA's ASRS site for official report.