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11.2.2 11.2.2.1
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[d] Reconstruction, separately, of other groups of materials of particular importance (front compartment of the hydraulic system, etc.).
2. The places of wreckage mentioned under pOint l were systematically and carefully exammed by specialized technicians after being S'llhlelded into three prinCipal groups, namely: structure of the aircraft, engines, various inboard installations.
3. In the examination of the materials mentioned under pomt 1 and in the evaluation of the damage suffered by them, consideration was given to all those hypotheses which, directly or indirectly, might relate to the possible causes of the accident and to all uses previously made of the plane (see par. 11.2.3.7).
Examination of the engines Condition of each engine assembly at the spot where it fell Assembly No. 1
This assembly became detached from the left wring at the firewall and struck the ground almost vertically with its front portion, embedding itself in the ground almost 2 meters deep; the result was considerable damage and breakage, espeCially to the front and rear ("power egg") areas.
Specifically, the force of the impact caused the front portion of the assembly, including part of the reduction gear housing, the propeller, and part of the propeller shaft, to break off and separate; two propeller blades broke off near the hub. All these parts were found together with the engine in the hole. The assemny showed no Visible signs of fire or damage from fire.
The pitch of blades 1, 2 and 3 was found to be, respectively, 33°, 3h° and 27°.
Assembly No. 2
This assembly remained attached to the main wreckage and, on striking the ground, penetrated into the front part of the fuselage.
The rear part of the engine suffered very evere damage from the fire that followed the crash; the propeller remained attached to the engine, with the exception of one of the blades, which broke off at the hub and was buried under the wreckage.
Th3 pitch of blades 1, 2 and 3 was found to be, respectively, 28 , 25°, and 27°.
