Aesma wrote:Draken21fx wrote:d. Also I do understand that engines are not designed to take that kind of impact but can an engine expert comment which part of the engine is most likely to be damaged with an impact like that?
I'm not expert so just speculating : fuel lines and control cables should be on the top of the engine. With those two an engine should continue to run (or try to run) unless commanded to stop. We saw in some instances (Qantas A380) that even without control lines engines continue to run.
Now, I imagine some oil lines could be at the bottom of the engine. If they're damaged, the engine could lose all oil. It can't run without oil for long, stuff overheats, metal expands, parts don't fit anymore, and the engine seizes.
nmcalba : good find/memory !
From the report from the Tallinn accident :-
Left engine (engine #1):
Damage observed on the nacelle, fan cowls, AGB, TGB and thrust reversers. Attrition lining was scrapped off at 6 to 7 o clock position. Inlet cowl inner barrel aft panel was missing trailing edge material, eroded by the fan blades. AGB lower surface was heavily abraded perforated and no more oil was present inside, internal parts were found damaged. AGB was seized and the N2 rotor was stuck.
Several pipes at 6 to 7 o clock position crushed. Drain mast at the rear of the thrust reverser cowl was damaged with its lower part missing. Inlet cowl aft bulkhead at 6 o clock was distorted with several stiffeners bent and rivets sheared. Most fan blades had tip curl and edge rubbing (Figure 32). Magnetic contaminator indicator was popped up.
All damage was consistent with an impact with the ground.
Right engine (engine #2):
Pylon fairing was cracked. Inlet cowl lip skin was dented, perforated and torn. Inlet cowl outer barrel casing has impact damage from airport approach lighting. Aft bulkhead was buckled, inner barrel surfaces were perforated and dented in several locations. Inlet cowl attrition lining was worn through to the metal at 6 to 7 o clock position. Fan blades had tip curl and evidence of FOD (Figure 33). Right fan cowl door and thrust reverser presented fire traces, engine core, ECU and harness were damaged by fire. The AGB and TGB had lower surface abrasion. The thrust reversers halves and fan cowls had evidence of fire and impact damage. All compressor blades showed signs of tip rub, with material build- up at blade tips.
All damage was consistent with an impact with the ground.
Edit :- Link to accident investigation report - https://www.ojk.ee/et/system/files/fail ... report.pdf