▁the ▁horizontal ▁stabil izer ▁to ▁a ▁nose ▁down ▁position , ▁from ▁- 2 . 5 ▁deg ▁( 6 . 5 ▁units ) ▁to ▁+ 2 . 5 ▁deg ▁( 1 . 5 ▁units ). ▁The ▁F DR ▁recorded ▁that ▁nose ▁down ▁stabil izer ▁trim ming , ▁from ▁the ▁stabil izer ▁trim ▁switch es ▁on ▁the ▁control ▁wheel , ▁last ing ▁ 1 2 ▁seconds . ▁The ▁CV R ▁also ▁recorded ▁the ▁specific ▁noise ▁of ▁rotation ▁of ▁the ▁trim ▁whe els , ▁located ▁on ▁both ▁sides ▁of ▁the ▁central ▁ped est al . ▁ ▁The ▁result ▁was ▁that ▁after ▁the ▁aircraft ▁clim bed ▁to ▁about ▁ 1 0 0 0 ▁m , ▁it ▁then ▁began ▁a ▁rapid ▁descent ▁with ▁negative ▁vertical ▁acceleration ▁of ▁- 1 g . ▁The ▁subsequent ▁crew ▁attempts ▁to ▁recover ▁were ▁not ▁sufficient ▁to ▁avoid ▁an ▁impact ▁with ▁the ▁ground . ▁ ▁At ▁ 0 0 : 4 1 : 4 9 , ▁the ▁aircraft ▁hit ▁the ▁run way ▁approximately ▁ 1 2 0 ▁m ▁from ▁the ▁threshold ▁with ▁a ▁speed ▁of ▁over ▁ 6 0 0   km / h ▁and ▁a ▁nose ▁down ▁pitch ▁exceed ing ▁ 5 0 ▁degrees . ▁The ▁impact ▁destroyed ▁the ▁aircraft , ▁instantly ▁killing ▁all ▁on ▁board . ▁ ▁Final ▁report ▁ ▁On ▁ 2 6 ▁November ▁ 2 0 1 9 ▁the ▁I AC ▁published ▁the ▁final ▁report ▁stating ▁that ▁the ▁crash ▁was ▁caused ▁by ▁an ▁incorrect ▁aircraft ▁configuration ▁and ▁incorrect ▁crew ▁pil oting , ▁and ▁the ▁subsequent ▁loss ▁of ▁the ▁pilot ▁in