What happened
The FAA’s narrative, in sentence case. The FAA writes it in capitals and removes private details.
Narrative: on 01/24/96 at approximately 0800 EST, aala flt 1425 phl to sju, experienced a #1 engine power loss during takeoff at 1000 feet AGL. The aircraft returned to phl and landed without incident. There was no fire or injuries reported to the 255 passengers and nine crew memebers. The preliminary field investigation and engine inspection results indicate a possible turbine failure. External damage was noted to inboard near turbine case, (uncontained) there was an exit hole approximately five inches wide by thirteen inches high noted at the three o'clock position looking forward. Holes and damage consistent with turbine blade separations were noted to the internal turbine shroud at the 3, 4, 6, 11 and 12 o'clock positions. Damage to the aircraft was noted as follows, the left inboard aileron small dents and holes, left inboard flap/cowling small dents and holes, and small nicks to the leading edge of the left horizontal stabilizer. Note: engine model/general electric CF6-80-C2A5 serial #695308 total hours per aala records: 3539 at time of incident. An additional limited engine inspection was conducted at aala's maintenance facility at jfk int'l airport, the following items were noted. (1) the low pressure compressor (lpc) could not be rotated due to the damage in the low pressure turbine (lpt) section therefore, only the blades adjacent to the borescope access plug were viewed. (2) lpc 1st stage fan blades had no major damage. (3) stage 1 blades and vanes of the lpt that could be seen through the 3 o'clock borescope access plug normal. (4) lpt stage 2 blades and vanes had heavy damage as seen through the 3 o'clock borescope access plug. (5) lpt stages 3 through 6 blades and vanes had heavy damage as seen through the tailpipe and lpt 3 o'clock borescope access plug. (6) the high pressure compressor (hpc) section could be rotated and the 1st, 2nd, 6th, and 13th stage blades were all found clean along with the vanes that could be viewed through the 3 o'clock borescope access. (7) the borescope of the high pressure turbine (hpt) stages 1 and 2 blades revealed only minor erosion of the coating on the leading edge of the blades. The vanes in the area of the 3 o'clock borescope access were normal
As the FAA filed it
NARRATIVE: ON 01/24/96 AT APPROXIMATELY 0800 EST, AALA FLT 1425 PHL TO SJU, EXPERIENCED A #1 ENGINE POWER LOSS DURING TAKEOFF AT 1000 FEET AGL. THE AIRCRAFT RETURNED TO PHL AND LANDED WITHOUT INCIDENT. THERE WAS NO FIRE OR INJURIES REPORTED TO THE 255 PASSENGERS AND NINE CREW MEMEBERS. THE PRELIMINARY FIELD INVESTIGATION AND ENGINE INSPECTION RESULTS INDICATE A POSSIBLE TURBINE FAILURE. EXTERNAL DAMAGE WAS NOTED TO INBOARD NEAR TURBINE CASE, (UNCONTAINED) THERE WAS AN EXIT HOLE APPROXIMATELY FIVE INCHES WIDE BY THIRTEEN INCHES HIGH NOTED AT THE THREE O'CLOCK POSITION LOOKING FORWARD. HOLES AND DAMAGE CONSISTENT WITH TURBINE BLADE SEPARATIONS WERE NOTED TO THE INTERNAL TURBINE SHROUD AT THE 3, 4, 6, 11 AND 12 O'CLOCK POSITIONS. DAMAGE TO THE AIRCRAFT WAS NOTED AS FOLLOWS, THE LEFT INBOARD AILERON SMALL DENTS AND HOLES, LEFT INBOARD FLAP/COWLING SMALL DENTS AND HOLES, AND SMALL NICKS TO THE LEADING EDGE OF THE LEFT HORIZONTAL STABILIZER. NOTE: ENGINE MODEL/GENERAL ELECTRIC CF6-80-C2A5 SERIAL #695308 TOTAL HOURS PER AALA RECORDS: 3539 AT TIME OF INCIDENT. AN ADDITIONAL LIMITED ENGINE INSPECTION WAS CONDUCTED AT AALA'S MAINTENANCE FACILITY AT JFK INT'L AIRPORT, THE FOLLOWING ITEMS WERE NOTED. (1) THE LOW PRESSURE COMPRESSOR (LPC) COULD NOT BE ROTATED DUE TO THE DAMAGE IN THE LOW PRESSURE TURBINE (LPT) SECTION THEREFORE, ONLY THE BLADES ADJACENT TO THE BORESCOPE ACCESS PLUG WERE VIEWED. (2) LPC 1ST STAGE FAN BLADES HAD NO MAJOR DAMAGE. (3) STAGE 1 BLADES AND VANES OF THE LPT THAT COULD BE SEEN THROUGH THE 3 O'CLOCK BORESCOPE ACCESS PLUG NORMAL. (4) LPT STAGE 2 BLADES AND VANES HAD HEAVY DAMAGE AS SEEN THROUGH THE 3 O'CLOCK BORESCOPE ACCESS PLUG. (5) LPT STAGES 3 THROUGH 6 BLADES AND VANES HAD HEAVY DAMAGE AS SEEN THROUGH THE TAILPIPE AND LPT 3 O'CLOCK BORESCOPE ACCESS PLUG. (6) THE HIGH PRESSURE COMPRESSOR (HPC) SECTION COULD BE ROTATED AND THE 1ST, 2ND, 6TH, AND 13TH STAGE BLADES WERE ALL FOUND CLEAN ALONG WITH THE VANES THAT COULD BE VIEWED THROUGH THE 3 O'CLOCK BORESCOPE ACCESS. (7) THE BORESCOPE OF THE HIGH PRESSURE TURBINE (HPT) STAGES 1 AND 2 BLADES REVEALED ONLY MINOR EROSION OF THE COATING ON THE LEADING EDGE OF THE BLADES. THE VANES IN THE AREA OF THE 3 O'CLOCK BORESCOPE ACCESS WERE NORMAL