The elevators on the MD-80 series are not powered, but rather of the servo tab variety. This means that they are free to flap with the wind on the ground, and are moved in flight by the servo tab increasing or decreasing the lift on that surface..moving the elevator up or down and again controlling the aircraft.
http://www.airliners.net/open.file/382601/M/
The control checks on the MD-80 series elevators apparently needs to be done at a minimun taxi speed of 10-15kts.
That still doesn’t explain why they move independantly of each other on the ground. In the picture you linked to you can see that the right side of the elevator doesn’t match with the left. You can see the deflection of the servo tab don’t match either. The deflection should always be the same right since both tabs are directly connected by cable to the pilot yoke? Even if the wind should push one elevator and it’s tab upward the resulting movement would move the yoke and in turn move the other servo tab.
Our stabilator is similar but doesn’t have the split. The wind can bounce the control surface around but it also moves the yoke since movement of the elevator moves the servo tab and then moves the yoke.
The elevators on the MD-80 series are not powered, but rather of the servo tab variety. This means that they are free to flap with the wind on the ground, and are moved in flight by the servo tab increasing or decreasing the lift on that surface..moving the elevator up or down and again controlling the aircraft.
http://www.airliners.net/open.file/382601/M/
The control checks on the MD-80 series elevators apparently needs to be done at a minimun taxi speed of 10-15kts.
That still doesn’t explain why they move independantly of each other on the ground. In the picture you linked to you can see that the right side of the elevator doesn’t match with the left. You can see the deflection of the servo tab don’t match either. The deflection should always be the same right since both tabs are directly connected by cable to the pilot yoke? Even if the wind should push one elevator and it’s tab upward the resulting movement would move the yoke and in turn move the other servo tab.
Our stabilator is similar but doesn’t have the split. The wind can bounce the control surface around but it also moves the yoke since movement of the elevator moves the servo tab and then moves the yoke.
This sure is quite a turn of events for you and your airline. You obviously have quite a vision for the future of Alpha1 and it seems to already be paying off. Well done.
Needless to say, our fleet is no longer going to involved PA-31s!
Can you give us any hints of your future fleet plans? Turboprops? Turbojets?
How about saving a jumpseat or 2 for your fellow forum supports. 😉 😀
This sure is quite a turn of events for you and your airline. You obviously have quite a vision for the future of Alpha1 and it seems to already be paying off. Well done.
Needless to say, our fleet is no longer going to involved PA-31s!
Can you give us any hints of your future fleet plans? Turboprops? Turbojets?
How about saving a jumpseat or 2 for your fellow forum supports. 😉 😀
I wonder what the hydraulic system has to do with it. This diagram shows the #1 system providing pressure for the elevator (I’d assume some sort of boost pump). Perhaps the hydraulics aren’t activated on the ground leaving the 2 halves to flap in the wind.
I’ve pondered this a few times as we taxi behind a MD-80. 🙂
I wonder what the hydraulic system has to do with it. This diagram shows the #1 system providing pressure for the elevator (I’d assume some sort of boost pump). Perhaps the hydraulics aren’t activated on the ground leaving the 2 halves to flap in the wind.
I’ve pondered this a few times as we taxi behind a MD-80. 🙂
Wow, this thread got short in a hurry.
Wow, this thread got short in a hurry.
You’ll see it on the 146 as well. Controls all work conventionally in flight.
But what allows them to act in unison in flight? Is there some sort of system activation prior to takeoff that slaves the 2 elevator halves together?
You’ll see it on the 146 as well. Controls all work conventionally in flight.
But what allows them to act in unison in flight? Is there some sort of system activation prior to takeoff that slaves the 2 elevator halves together?
I think it’s an excellent idea to test your aircraft at a safe altitude especially with the scenerio that we’re discussing here. With that being said, I would still be hesitant to turn 180 for the field unless terrain required me to or I was easily at a safe altitude. There will still be variables that practicing can’t take into account and such practice might give one a false sense of ability if an engine was to give up the ghost on a departure. Variables such as weight, weather, winds, terrain, temperature, other departing aircraft, etc. All of those could negatively impact a risky 180 turn for the runway.
Personally I would test the aircraft to get a rough idea of the altitude loss then take that number and double it. If you could expect a 500′ loss in a turn I would give myself at least 1000′ before I would consider such a turn. Chances are though if you had such altitude that there would be other/safer options available. I would rather land in a field with a headwind then attempt to land on a runway with a nice tailwind.
As this is GA forum, if we consider very much average types such as Cessna 150/PA-28 they will descend in a glide at about 750 ft per minute on thereabouts (going from memory a bit ) if flown at best glide speed. Surely, in excess of a minute is sufficient time to execute a 180 degree change a heading – in a Cub I can do that in well under 10 seconds, probably 5-6 if really well-motivated.
I think this is the assumption that a lot of pilots make and it ends up getting them in trouble (stall/spin accidents). In order to maintain a given IAS through a turn you must actually lower the nose which in turn increases your decent rate (this is in an engine-out situation). You can assume that such pilots who don’t survive their turn back to the runway steepened their bank to expedite the turn back to the safety of the runway BUT also kept the nose at the pitch attitude for Best Glide speed in straight-level flight. You can understand one’s apprehension to lower the nose and increase their decent rate when attempting to glide back to the airport but without doing so they encounter an accelerated stall and suffer the resulting spin.
The quicker/tighter you plan on making that 180 degree turn back to the runway the more you have to lower the nose and suffer the resulting increase in decent rate. Remember, as your bank angle increases your Lift Vector decreases. Some of this is masked under normal situations where you have power available unlike in such emergency situations.
You are correct when looking at the situation as measured by time left resulting from your decent rate at Best Glide. But as soon as you begin manuveuring with turns that time aloft becomes greatly shortened. For that reason the often mentioned procedure is to establish your Best Glide speed and continue forward. Doing so gives you the most time to prepare for the eventual landing.
Now I’m not saying that turning back towards the runway isn’t an option but it has a lot of unknown variables that you don’t have time to weigh in such emergencies.
The “Nova” program had a show all about the quest to break the sound barrier. You can find a lot of the information in this online Teacher’s Guide they provide.
http://www.pbs.org/wgbh/nova/barrier/

The “Nova” program had a show all about the quest to break the sound barrier. You can find a lot of the information in this online Teacher’s Guide they provide.
http://www.pbs.org/wgbh/nova/barrier/

Sounds like he’s been bitten be the Airbus Bug. 🙂