Bell/Boeing V-22 'Osprey'

  Base model:V-22
  Designation System:U.S. Air Force
  Designation Period:1956-Present
  Basic role:V/STOL

  Length: 56' 10" 17.3 m
  Height:20' 2" 6.1 m
  Wingspan: 38' 0" 11.5 m
  Wingarea: 2,268.2 sq ft 210.7 sq m
  Max Weight: 55,000 lb 24,943 kg

  No. of Engines: 2
  Powerplant: General Electric T64-GE-717
  Horsepower (each): 4855

  Range: 915 miles 1,473 km
  Max Speed: 300 mph 483 km/h 261 kt

Known serial numbers
164389 / 164400, 164939 / 164944

Examples of this type may be found at
American Helicopter MuseumWest ChesterPennsylvania

V-22 on display

American Helicopter Museum


Recent comments by our visitors
 , CO
I think this whould be a good sex.
10/09/2007 @ 07:56 [ref: 18142]
 Kerry Cox
 Gold Coast, GA
I would like to see some close up visual on the folding hinges on the blades as I recently built a 1/48 Scale V-22 built it in the "folded" position and had great difficulty in replicating the hinges from what material I could find. It looked OK though.
09/30/2006 @ 15:23 [ref: 14337]
 Norm Taylor
 Sumter,, SC
I've been an aviation photographer for around 60 years and have seen only one MV-22 up close enough to take photos of. Would like to get additional photo coverage, but don't know who to contact, can some one at Bell help. I live l5 minutes from Shaw AFB and about 2 and a half hours from MCAS New River, NC.
01/06/2005 @ 18:24 [ref: 9070]
 Mike Letalien
 Lubbock, TX
Another good reference site for the V-22 project is the "Nav-Air" home:
05/17/2004 @ 17:42 [ref: 7422]
 H.Gokhan GULTEK
 Antakya-Hatay, OTH
I've been still waiting for an answer. What happened to the first prototype 163911 (c/n 90001) ? What does "ex.std.KNCA" mean? If somebody knows and e-mail me I'll be very glad. Thank you.

12/30/2002 @ 09:29 [ref: 6227]
 Gokhan Gultek
 Antakya-Hatay, OTH
I want to learn what happened to 163911 (c/n 90001). In a web site it says "ex std KNCA". What does it mean ? Thank you.
07/06/2002 @ 09:35 [ref: 5253]
 Paul H.
 Auckland, NZ, OTH
I think a lot of the questions posted about the V-22 are answered in these pages:
02/13/2002 @ 00:47 [ref: 4300]
 , FL
Several of your numbers are incorrect or crossed up
2268 is disk area
661.9 tip speed in flight
780 is approx hover tip speed
38ft rotor diameter
261.52 blade area
47500lb, max t.o vertical Gr Wt
Excerpt fro Boeing Spec Chart
12/16/2001 @ 22:43 [ref: 3847]
 Captain Dave Linsley
 Barnardsville, NC
It would appear that the V-22 is not meeting design expectations or is being mismanaged. Is this too critical
a comment at this stage. Could we see some time from design to operational flight comparisons with other aircraft in the military arsenal -- e.g. Bell Huey-1 & 2, Sikorsky H-53 A thru E, Kaman HOK-1 and HUK-1, Sikorsky H-76?

It appears this aircraft is far beyond prior time frmaes from design to operational status.

Is there a prescribed limit anywhere in the appropriations process which acts essentially as a STOP to this program?

How much tax money has thus far been devoted to this project

--- Dave Linsley
Air Gabon (Africa) - retired 1997
United Airlines - retired ('67-'97)
USMC - Active duty '56='67
USMC H-34 pilot, Danang, Vietnam '63
12/14/2001 @ 09:12 [ref: 3827]
 Louis Pike McCasland Jr.
 Castroville, TX
Dear Sir:

I have been trying to get some information concerning the Osprey V-22. Possibly some of the readers can respond with accurate information. Thank you!!

1) What is the wheel base of the aircraft?
2) What is the wheel track main gear center to center?
3) what is the range of the mlg oleos full up and full down, and what does the maintenance manual state the setting should be?
4) what does each engine with associated assemblies weigh each? (all weight from the outboard point of the wing.)
5) what is the height of the lowest point of the nacelles from the ground when the aircraft is level and when the MLG oleos are set at manufacturer recommendations?
6) What is the temperature of the engine exhaust at ramp level and when when engine at flight idle, and maximum power? Can the engine exhaust start a grass fire when maximum power at ground level?
7) when in the airplane mode, and transitioning to helicopter mode, at what speed does the wing stall out, and what happens when this happens?
8) if you had one rotor in ground effect and the other is not in ground effect (as landing on a ship or offshore heliport) can one rotor system produce more lift than the other and still maintain level flight?
9) do the rotor systems have swash plates the same as helicopters?
10) can the aircraft do a vertical autorotation, the same as a helicopter?
11) what is the rotor rpm in helicopter mode?
12) what is the autorotation rotor speed with collective full down? At what IAS?
13) what is the sink rate while in an optimum IAS?
14) What is the optimum autorotation speed full of fuel and no cargo or passenger, just basic crew and full mission fuel load.
15) does the rotor systems put a download on the horizontal stabilizer when in a hover?
16) can the aircraft get into ground resonance?
17) I have read where the controls are at maximum throw when in a crosswind on a ship, what do you do when you run out of control movement? Isn't the the aircraft subject to go out of control at that time, possibly moving sideways and run into something?
18) If there is an engine failure and one engine is driving both rotors, does the rotor free wheel from the dead engine?
19) does the aircraft derive any lift from the exhaust when in the helicopter mode? What percentage of lift?

I hope this is not too much to be answered. I have many more questions, but will see if anyone can answer these.
Thank you,
Lou McCasland
(former USMCR and Air America, Inc.)

12/13/2001 @ 17:55 [ref: 3822]


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