62-22-03 VICKERS: Amdt. 491 Part 507 Federal Register October 5, 1962. Applies to All Viscount 700 Series Aircraft.
Compliance required as indicated.
As a result of wing flap attachment difficulties the following is required for both flap assemblies:
(a) (1) Replace bolts P/N's 72403-2445, 70103-2645, and 70103-2639, at flap support bracket units Nos. 2 and 3 respectively, right and left side with new bolts every 1,500 landings.
(2) Replace bolts P/N's 70003-2359 and 70107-467, at flap support bracket units Nos. 1 and 4 respectively, right and left side with new bolts every 2,500 landings.
(3) When Modification D.2175 is incorporated and provided the bolts referred to in paragraphs (a)(1) and (a)(2) are replaced with new bolts at the same time, the life of these new bolts is extended as specified in the overhaul schedule listed below:
Part Number 72403-2445 - Retirement time 4,500 landings
Part Number 70103-2645 - Retirement time 4,500 landings
PartNumber 70103-2639 - Retirement time 4,500 landings
Part Number 70003-2359 - Retirement time 7,500 landings
Part Number 70107-467 - Retirement time 7,500 landings
(b) Flap beam (supporting bracket) attachment fitting at wing trailing edge false spar member inspection.
(1) Within the next 135 hours' time in service after the effective date of this AD and each 135 hours' time in service thereafter, visually inspect for cracks all four lower flap support attachment fittings aft of the wing trailing edge member (false spar) on the right and left sides. The initial inspection is not required if these fittings were thoroughly examined at the time of bolt replacement of paragraph (a).
(2) Within the next 385 hours' time in service after the effective date of this AD and each 1,080 hours' time in service thereafter, visually inspect for cracks all the flap support attachment fittings forward of the trailing edge member (false spar), top and bottom, right and left sides at flap positions 2 and 3.
(3) Within the next 385 hours' time in service after the effective date of this AD and each 385 hours' time in service thereafter, visually inspect for cracks all top beam attachment fittings aft of the trailing edge member (false spar) on the right and left sides.
(c) Replace cracked fittings.
(d) Incorporated Vickers Modification D.2175 within the next 400 hours' time in service after the effective date of this AD on aircraft exceeding 3,000 landings, or within 400 hours' time in service upon the accumulation of 3,000 landings on aircraft not exceeding 3,000 landings on the effective date of this AD. Upon incorporation of this modification, the inspections called for in (b)(1), (b)(2), and (b)(3) may be discontinued.
(Vickers Viscount 700 Series PTL No. 151, Issue 4 covers this subject.)
This supersedes AD 57-07-03.
This directive effective November 6, 1962.