I noticed that the inner right-wing flap track fairing is shorter than the one in the left wing. You can even see a grey-painted area, more or less what the left-wing fairing covers. In other pictures it is also seen:
I think Keta is referring to the Wing mounted part of the Fairing & not the Movable Aft part of the Fairing.
The Inboard RH side Fixed portion of the Fairing is Shorter in length compared to the Inboard LH Side Fixed Portion of the Fairing.
Probably it covers some component.
I too would be Interested to Know the reason.
Pihero From France, joined Jan 2005, 3496 posts, RR: 72 Reply 5, posted (7 years 6 months 2 days 8 hours ago) and read 4825 times:
An amazing piece of observation !
I see two reasons :
1/-the aerodynamic integration between the wing-engine pylon-flaps hasn't been frozen and AI is still comparing data from both sides, or
2/- the left fairing covers the EH actuator AI has been talking about for about four years. It could be the explanation as all three flying prototypes have it.
Pihero From France, joined Jan 2005, 3496 posts, RR: 72 Reply 10, posted (7 years 6 months 1 day 9 hours ago) and read 4736 times:
Better than my explanation,
3.1. What is an EHA?
A conventional actuator is connected to the central hydraulic system of the aircraft through pipes running from the aircraft’s hydraulic bay. It includes a servovalve which directs the hydraulic pressure (provided by the aircraft’s hydraulic pumps) to move the actuator shaft which is connected to the corresponding control surface (aileron, elevator, rudder, spoiler).
The EHA is connected to the aircraft’s electrical network (and not to the hydraulic system). It has a self contained electrical hydraulic pump, reservoir and accumulator which generate the hydraulic power required to move the same actuator shaft connected to the control surface. Therefore, the EHA is a real hydraulic actuator since the power to move the actuator shaft is hydraulic; however, since the hydraulic system is self-contained, it only requires electrical power from the aircraft’s network to operate.
EHA will allow to decentralize hydraulic system architectures. Kilometers of hydraulic pipes, pumps, reservoirs and accumulators which generate hydraulic power in a central location and then distribute this energy throughout the aircraft will be replaced by electrical wires and compact actuators which produce the energy required near the place where it is needed.