Here is the NTSB description of the CO DC-10 incident earlier this year. It's not a pretty sight. Upon landing the ground crew was apparently shocked the the condition of the engines.
From the report: "Examination of the airplane revealed that all three General Electric CF6-50C2 engines were damaged. "
If the engines had sustained any more any more damage the a/c probably would have ended up on the NJ Turnpike. Kudos to the CO crew for their good work.
The 767-400s can't arrive early enough.
NTSB Identification: NYC00FA122
Scheduled 14 CFR 121 operation of CONTINENTAL AIRLINES, INC.
Accident occurred APR-25-00 at NEWARK, NJ
Aircraft: McDonnell Douglas DC10-30, registration: N39081
Injuries: 234 Uninjured.
This is preliminary information, subject to change, and may contain errors. Any errors in this report will be corrected when the final report has been completed.
On April 25, 2000, at 1942 Eastern Daylight Time, a McDonnell-Douglas DC10-30, N39081, operating as Continental Airlines flight 60, was substantially damaged when an uncontained engine event occurred during takeoff from Newark International Airport (EWR), Newark, New Jersey. The 3-man cockpit crew, 11-person cabin crew, and 220 passengers were not injured. Visual meteorological conditions prevailed at the time of the accident. An instrument flight rules flight plan had been filed for the flight, between Newark and Brussels Airport (BRU), Brussels, Belgium. The scheduled passenger flight was conducted under 14 CFR Part 121. The captain stated that he conducted a crew briefing prior to boarding the airplane. Startup and taxi were normal, and during the taxi, the captain again briefed the cockpit crew, and included engine failures and non-reject situations. The airplane lined up on Runway 04L, and the captain applied takeoff power slowly and smoothly. At takeoff decision speed (V1), there was a loud explosion. A white "engine fail" light illuminated in front of the captain, and the number 1 engine N1 decreased by 30 percent. Number 2 and number 3 engines appeared normal. The captain continued the takeoff, and the landing gear was raised. A red, left main landing gear warning light illuminated on the front panel. The airplane turned to a heading of 010, and slowly climbed to 3,000 feet. During the climb, an airframe vibration developed. After level-off, the crew began to troubleshoot the emergency, and found that when the number 3 engine N1 was reduced to about 25 percent, the vibration disappeared. Both the number 1 and the number 3 engines remained at approximately 25 percent N1 for the rest of the flight. Air traffic control provided vectors for a return to Newark. During the return, the crew dumped about 90,000 pounds of fuel. The crew also ran both 1-engine, and 2-engine inoperative checklists, and prepared data cards for both scenarios. The captain flew the ILS glideslope down to a full-stop landing, on Runway 04R. The ACARS recorded the landing at 2016. After the initial stop, the brakes would not release, so the crew shut down the engines on the runway, and the passengers and crew disembarked through the normal deplaning doors. The airplane was later towed to a ramp. According to the captain, the use of crew resource management (CRM) by both the cockpit and cabin crews was a major factor in the successful handling of the emergency. Examination of the airplane revealed that all three General Electric CF6-50C2 engines were damaged. The number 1 (left) engine "low pressure turbine" case was breached in the vicinity of the second stage nozzles, from approximately the 3 o'clock, to the 9 o'clock position. The breach was about the width of the second stage nozzle segments, and all of the segments were missing from the engine. Each segment consisted of six nozzle blades. Nine of the 16 nozzle segments were recovered intact, and additional portions of segments were found, for a total recovery of about 85 percent of the nozzle blades. The majority of nozzle material was found on the departure runway; however, one nozzle segment was found in the left main landing gear wheel well. One of the eight anti-rotation nozzle locks was recovered. The threaded stud from that lock had been sheared from the plate, and the engagement tangs exhibited wear and damage. The first stage low pressure turbine blades had minor trailing edge airfoil damage, and the second stage low pressure turbine blades exhibited circumferential rub marks on the inner platform leading edge, and on the airfoils near the blade root. The number 2 (center) engine exhibited leading edge damage to two fan blades. The number 3 (right) engine had leading edge damage to all fan blades, consisting of tears, rips and material loss. Pieces of fan blade, and material similar to that of the second stage nozzles from the number 1 engine, were found embedded in the engine inlet acoustic panels. The left main landing gear, front inboard tire, was ruptured, and the front outboard tire exhibited tread separation, but remained inflated. Impact marks were noted on the outboard side of the left engine pylon, the left wing outboard flap, the underside of the fuselage, the left main landing gear access door, the left side of the fuselage aft of the left wing, and a right wing panel outboard of the flap actuator housing. The installation of upgraded nozzle locks, per Service Bulletin 721082, was accomplished in 1997.