What happened
The FAA’s narrative, in sentence case. The FAA writes it in capitals and removes private details.
Narrative: shortly after takeoff from abe en route to pit as flt 1544, crew noticed aircraft vibration going through 100 KTS. Crew suspected blown tire. Left main gear green light was also observed as inoperative. After discussions with dispatch, crew elected to divert to phl where aircraft landed without incident. Crf responded as a precautionary. Subsequent inspection of the aircraft revealed damage caused by the separation of the number two tire recap from the wheel assembly. Recap struck tail flap, trailing edge panel causing 6X6 inch hole puncture through both sides of trailing edge flap panel along with pulled fasteners along the rear spar of lower chord vertical flange. Two internal ribs were bent along vertical web section and 12 rivets had been sheared along the rear spar lower vertical chord flange. The rear spar chord flange was also noted as slightly bent. Additional damage noted at the left main gear down lock switch, switch harness, and switch assembly. All these parts, including both left main wheel assemblies were removed and replaced. A landing gear ret/ext check was performed satisfactorily. Damage to the trailing flap assembly consisted of: replacement of trail flap tab assembly and inspection and temporary repair to lower cord vertical flange in accordance with usair ea 33663, dated: September 25, 1996. Repair due reinspect every 125 hrs. Final repair scheduled not to exceed 500 hrs. Aircraft was released for revenue service. Aea-fsdo considers this investigation closed.
As the FAA filed it
NARRATIVE: SHORTLY AFTER TAKEOFF FROM ABE EN ROUTE TO PIT AS FLT 1544, CREW NOTICED AIRCRAFT VIBRATION GOING THROUGH 100 KTS. CREW SUSPECTED BLOWN TIRE. LEFT MAIN GEAR GREEN LIGHT WAS ALSO OBSERVED AS INOPERATIVE. AFTER DISCUSSIONS WITH DISPATCH, CREW ELECTED TO DIVERT TO PHL WHERE AIRCRAFT LANDED WITHOUT INCIDENT. CRF RESPONDED AS A PRECAUTIONARY. SUBSEQUENT INSPECTION OF THE AIRCRAFT REVEALED DAMAGE CAUSED BY THE SEPARATION OF THE NUMBER TWO TIRE RECAP FROM THE WHEEL ASSEMBLY. RECAP STRUCK TAIL FLAP, TRAILING EDGE PANEL CAUSING 6X6 INCH HOLE PUNCTURE THROUGH BOTH SIDES OF TRAILING EDGE FLAP PANEL ALONG WITH PULLED FASTENERS ALONG THE REAR SPAR OF LOWER CHORD VERTICAL FLANGE. TWO INTERNAL RIBS WERE BENT ALONG VERTICAL WEB SECTION AND 12 RIVETS HAD BEEN SHEARED ALONG THE REAR SPAR LOWER VERTICAL CHORD FLANGE. THE REAR SPAR CHORD FLANGE WAS ALSO NOTED AS SLIGHTLY BENT. ADDITIONAL DAMAGE NOTED AT THE LEFT MAIN GEAR DOWN LOCK SWITCH, SWITCH HARNESS, AND SWITCH ASSEMBLY. ALL THESE PARTS, INCLUDING BOTH LEFT MAIN WHEEL ASSEMBLIES WERE REMOVED AND REPLACED. A LANDING GEAR RET/EXT CHECK WAS PERFORMED SATISFACTORILY. DAMAGE TO THE TRAILING FLAP ASSEMBLY CONSISTED OF: REPLACEMENT OF TRAIL FLAP TAB ASSEMBLY AND INSPECTION AND TEMPORARY REPAIR TO LOWER CORD VERTICAL FLANGE IN ACCORDANCE WITH USAIR EA 33663, DATED: SEPTEMBER 25, 1996. REPAIR DUE REINSPECT EVERY 125 HRS. FINAL REPAIR SCHEDULED NOT TO EXCEED 500 HRS. AIRCRAFT WAS RELEASED FOR REVENUE SERVICE. AEA-FSDO CONSIDERS THIS INVESTIGATION CLOSED.
Other reports on N931VJ · 2
Matched to the same aircraft by N-number and date.