Shorts Skyvan
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Join Date: May 2005
Location: Sydney, Australia
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Shorts Skyvan
Hi everyone. In my first post on PPRuNe I though it seemed necessary to beg for some help
I've got a uni project an the above aircraft and need a few bits of data that I've been unable to find anywhere else. Hopefully I'm asking in the right forum, and hopefully some of you helpful people can help
Thanks in advance.
P.S. Yes, I have noticed that I tend to be using smilie faces as substitutes for punctuation. What can I say, I'm young and stupid!
I've got a uni project an the above aircraft and need a few bits of data that I've been unable to find anywhere else. Hopefully I'm asking in the right forum, and hopefully some of you helpful people can help
Thanks in advance.
P.S. Yes, I have noticed that I tend to be using smilie faces as substitutes for punctuation. What can I say, I'm young and stupid!
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Oh sorry, I was just testing the waters first.
I may have left something out, but here goes:
*Max load factor or angle of bank allowed
*Structural info:
- Fuselage construction (ribs, skin .etc)
-Wing structure (No. of spars.etc)
*Some sort of cutaway or structural diagram.
*Engine shaft horsepower
*Undercarriage contruction
Sorry about the vagueness of this request, but I'm just a poor little first year student without a clue.
I may have left something out, but here goes:
*Max load factor or angle of bank allowed
*Structural info:
- Fuselage construction (ribs, skin .etc)
-Wing structure (No. of spars.etc)
*Some sort of cutaway or structural diagram.
*Engine shaft horsepower
*Undercarriage contruction
Sorry about the vagueness of this request, but I'm just a poor little first year student without a clue.
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Why the Skyvan??? Anyway . . .
This info comes from the flight manual for the SC-7 Skyvan Series 3A Variant 100 and from the conversion training notes.
*Max load factor or angle of bank allowed
3.12g flaps up 2.0g flaps down
*Structural info:
- Fuselage construction (ribs, skin .etc)
The fuselage is essentially a box-like structure with conventional frames supporting double skin panels in which a smooth outer skin is bonded to a corrugated inner sheet. The nose portion (built using a more conventional skin and stringer construction) contains the flight compartment and the nose undercarriage and mounting.The underside of the fuselage aft of the main section is upswept to the tailplane. This upswept surface consists almost entirely of a large door which is hinged at the rear end and opens upwards into the fuselage allowing direct loading from the rear of the aircraft. It is possible to open and close the door during flight.
Length: 12.22m Height: 4.59m
-Wing structure (No. of spars.etc)
The wing comprises a spar-box structure, a leading edge and trailing edge, a wing tip and slotted type flaps and ailerons. The wing is braced by an external bracing strut which is not structurally part of the wing. The main spars, extending from root to tip and a leading edge spar, extending from outboard of the powerplant mounting and covered top and bottom by a double skin, constitute the spar-box structure. The skins are structurally continuous along the complete length, and consist of a corrugated inner skin bonded to an outer skin which reduces in gauge toward the tip. The corrugations are semi-circular in shape and run parallel to the spars.
Span 19.79m Wing area (Gross): 35.12 sq m
*Some sort of cutaway or structural diagram - tricky
*Engine shaft horsepower
The powerplants are Garrett AiResearch TPE-331-2-201A turboprops rated at 715 shaft horsepower and 755 ESHP (includes contribution from jet thrust). Propellers are Hartzell HC-B3TN-5C or –5E three blade or Hartzell HC-BT4N-5C (4 blade) metal props using single action hydraulic control and rotating clockwise viewed from the rear.
*Undercarriage construction
The aircraft is fitted with a non-retractable tricycle undercarriage. The nosewheel is steerable and of standard oleo-pneumatic design. The mainwheels are of the training link type and can be braked differentially for steering. Typical tyre pressure is 42 psi all round.
This info comes from the flight manual for the SC-7 Skyvan Series 3A Variant 100 and from the conversion training notes.
*Max load factor or angle of bank allowed
3.12g flaps up 2.0g flaps down
*Structural info:
- Fuselage construction (ribs, skin .etc)
The fuselage is essentially a box-like structure with conventional frames supporting double skin panels in which a smooth outer skin is bonded to a corrugated inner sheet. The nose portion (built using a more conventional skin and stringer construction) contains the flight compartment and the nose undercarriage and mounting.The underside of the fuselage aft of the main section is upswept to the tailplane. This upswept surface consists almost entirely of a large door which is hinged at the rear end and opens upwards into the fuselage allowing direct loading from the rear of the aircraft. It is possible to open and close the door during flight.
Length: 12.22m Height: 4.59m
-Wing structure (No. of spars.etc)
The wing comprises a spar-box structure, a leading edge and trailing edge, a wing tip and slotted type flaps and ailerons. The wing is braced by an external bracing strut which is not structurally part of the wing. The main spars, extending from root to tip and a leading edge spar, extending from outboard of the powerplant mounting and covered top and bottom by a double skin, constitute the spar-box structure. The skins are structurally continuous along the complete length, and consist of a corrugated inner skin bonded to an outer skin which reduces in gauge toward the tip. The corrugations are semi-circular in shape and run parallel to the spars.
Span 19.79m Wing area (Gross): 35.12 sq m
*Some sort of cutaway or structural diagram - tricky
*Engine shaft horsepower
The powerplants are Garrett AiResearch TPE-331-2-201A turboprops rated at 715 shaft horsepower and 755 ESHP (includes contribution from jet thrust). Propellers are Hartzell HC-B3TN-5C or –5E three blade or Hartzell HC-BT4N-5C (4 blade) metal props using single action hydraulic control and rotating clockwise viewed from the rear.
*Undercarriage construction
The aircraft is fitted with a non-retractable tricycle undercarriage. The nosewheel is steerable and of standard oleo-pneumatic design. The mainwheels are of the training link type and can be braked differentially for steering. Typical tyre pressure is 42 psi all round.
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Thats great, I can't thank you enough!
The lecturer isn't that clear with what we have to do, so if I need anything else Oddsoft, can I message you?
Why the Skyvan? I think I missed the bit where everyone else got to study shiny 747's, A340's and the like.
Did I say thank you yet?
The lecturer isn't that clear with what we have to do, so if I need anything else Oddsoft, can I message you?
Why the Skyvan? I think I missed the bit where everyone else got to study shiny 747's, A340's and the like.
Did I say thank you yet?
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Once had a Trislander pilot give us abuse in the Shed, something along the lines of "..with the box in sight etc.." To which the only reply I could come up with was "We're not just a box, compared your thing we're a turbo box GTI!"
Any aircraft a Trislander pilot can take the p*** out of really has to be ugly! The Skyvan is the real ugly duckling of the Shorts family, though I'm not sure if what it grew into (SD 3-60) was any better!! Certainly no swan....
Any aircraft a Trislander pilot can take the p*** out of really has to be ugly! The Skyvan is the real ugly duckling of the Shorts family, though I'm not sure if what it grew into (SD 3-60) was any better!! Certainly no swan....
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I used to fly one around Europe on the skydiving circuit and at least when you went away for the weekend you could take your car with you................
Try that in a Trislander!
Seem to remember it was great fun to fly out of short strips but it did not barrel roll particularly well
Try that in a Trislander!
Seem to remember it was great fun to fly out of short strips but it did not barrel roll particularly well
