PPRuNe Forums - View Single Post - American Airlines Flight 742 "flight control system" problems
Old 25th Mar 2013, 08:38
  #108 (permalink)  
Clandestino
 
Join Date: Feb 2005
Location: Correr es mi destino por no llevar papel
Posts: 1,422
Received 1 Like on 1 Post
Originally Posted by sevenstrokeroll
First off, if you are going to hit the engines on a DC9 (and they have been), you have to get by the fuselage, they aren't just sticking out in front of the wing.
Any engine that provides thrust by sucking in air and imparting it momentum as it is ejected needs clear and ample supply of aforementioned air, therefore any jet engine equipped with intake is prone to birdstrikes. If fuselage or wing get into position to shield the engine from birdstrike, they also shield it from uninterrupted airflow and that's something that usually causes big and expensive engine buuurp at high power settings. Protections that PWC150 or Klimov RD-33 enjoy are just impossible to apply on civil turbofans.

Originally Posted by CONFiture
The airplane reached 9 deg of AoA when the alpha-protection threshold value was still at 8 deg.
Originally Posted by NTSB
According to FDR data, the airplane touched down on the Hudson River at an airspeed of 125 KCAS with a pitch angle of 9.5° and a right roll angle of 0.4°. Calculations indicated that the airplane ditched with a descent rate of 12.5 fps, a flightpath angle of -3.4°, an AOA between 13° and 14°, and a side slip angle of 2.2°.
Originally Posted by CONFiture
Now, how do you call an "attenuation of pilot's controls that accompanies the alpha prot mode which could limit the ability to get more than 9 deg pitch in the time available for flare starting from 50 ft" if not a restriction ?
Aerodynamics.


Originally Posted by CONFiture
Adequate margin was in the aerodynamics as alpha max was still 4 deg away.
Maybe in Robert Zemeckis' movies or Michael Crichton's novels. Real life NTSB mentioned that the FBW helped wrung out as much performance as it was possible. Too bad that it doesn't fit "Airbus baaaaad" theory.

Originally Posted by CONfiture
Also the benefit from the CI rise over the Cd rise is exactly what is needed for the short term
Below Cl/Cd max Cd rises faster than Cl but then it is not enough to understand just aerodynamics to know that. One has to be versed in basic arithmetics also.
Clandestino is offline