I ran parts of the pdf through an ocr and google translate. Results are poor, but better than nothing.
I don't know what a "traction automaton" is. It's called "автомат тяги" in russian. Russian wiki mentiones it as a part of ABSU: "ABSU functionally consists of a servo drive system (SSP), a steering control system (SSU), an automatic control system (ACS), an automatic and a director approach system (trajectory control system - STU ), integrated control systems (ICS), a traction automaton )." Bing translates it as "thruster's machine".
"from itself" means forward, away from the pilot
steering wheel - yoke
Translation:
When the speed of 133 to 134 knots was reached, the traction automaton increased the mode
engine performance up to 75% M! with a further increase in the regime (by the time
autopilot off) to 95% M]. When approaching the aircraft to the entry point in
glissatsu, at a speed of about 130 uclov. The crew began to release the flaps 30 °.
The increase in the operating mode of the engines was accompanied by an increase in tanto,
the transition of the aircraft to a smooth climb and a drop in the instrument speed.
During the release of flaps at 30 °, a trip was made
autopilot. By the time the autopilot was turned off, the pitch of the aircraft was 19 °,
speed 128 knots. Disabling the autopilot and deflecting the steering wheel "from itself"
was accompanied by the transfer of engines of engines to reduce the mode of operation,
without switching off the traction automat.
Thereafter, the steering wheel was alternately turned
This pitch has increased to 45 ° (the maximum achieved value). what
accompanied by a warning shaking npturvala (triggering sgik-
shaker), the drop in the instrument speed is less than 100 knots, the roll
reached 95? The engines of the aircraft due to the operation of the traction automat on
the maximum mode is up to 95% MP.
After increasing the pitch to 45 °, the steering wheel was deflected "from itself" and
was held in this position (with a smooth decrease in deviation) to the conclusion
plane from a complex spatial position. The withdrawal of the aircraft from
complex position (pitch and roll) was produced without
exceeding the restrictions on overload and flight speed in the landing
configuration. In the process of developing a special airplane, the aircraft gained a height of 750
meters and was put into normal flight mode (completion of the decline, the beginning
missed approach) at an altitude of 350 meters.
Re-entry and landing did not take place. AT
As a result of a serious incident, no one was hurt. aircraft damage is not
got. A serious incident is being investigated.