Hi Tony, yes, reference your post (#2).
We did have an ADD system then (Acceptable Deferred Defect).
I was servicing the Victors during the Falklands & they were coming in with 13 pages full and leaving with 11…
Well Boeing has been known to moan about ‘unlawful tax breaks’ that competitors ‘get’. The fact that some of their own Government orders were on the strength of a nod and a wink is by the by.
Well, if you can’t fly the Walter, you could use it as a snow blower..
I don’t know about the ’40’s but later type specific engine tools were in section 63. If I remember correctly RR Conway tools (Victor K2) were 63AE.
Looks very nice.
A couple of photos of XL232 should look good as well.
For the trolley acc, have you tried a local commercial vehicle workshop? They might have some reasonable acc’s available.
Frankenplane?
Fibreglass on the oil cooler intakes. Was that there already?
Being as they are displayed outdoors I wonder how often water ingress in the joint freezes over the years. Water expands when it freezes and can cause internal stress loading.
I cannot find any photos anymore. I can tell you it landed with the u/c up because I saw it happen. I was outside walking the wings of a Lightning just out of storage and saw it skidding down the runway. The pilot departed in a great hurry, he also left the Station that way..
It was lifted and the u/c was dropped then towed into our hangar (ASF) where it was repaired. The ventral and a wing tip had the most damage. XR752 was the first production F6 built, first as the interim (F3a) then later fully modded to F6.
And yet it happened.
XR752.
I’ve seen a couple of types land with no u/c. Lightning, Jaguar..
A total of 3 Meteors were used by RR for reheat development starting in 1947 to about 1953
XS422 is on the way?
Because the engines had been upgraded with a higher mass flow, the intake couldn’t allow enough air into the engines in a static state. They therefore limited the engine speed and full reheat until it reached Mn 1.4.
As I pointed out, the mass air flow sea-level static state (SLS) was 150lbs per second through the 200’s and 170lbs per second through the 300’s. That was of course, data measured on the thrust rigs at RR.