62-01-02 LOCKHEED: Amdt. 384 Part 507 Federal Register January 9, 1962. Applies to All Models 49, 149, 649, 749, and 1049 Series Aircraft Incorporating Cleveland Pneumatic Tool Company Main Landing Gear Cylinders, P/N's 9040-2, 9040A-2, 9106-2, 9291-2, 9291B-2, 9291B-2B, or 9291D-2.
Compliance required as indicated.
As a result of failures of the cap weld on main landing gear cylinders which have been returned to service following compliance with the provisions of AD 59-07-03, as amended, all aircraft shall be inspected and/or modified as follows:
(a) Within the next 400 hours' time in service after the effective date of this AD, unless already accomplished, all landing gear cylinders with cap welds which previously have been inspected by the double-wall gamma radiographic technique in compliance with AD 59-07-03 shall be reinspected in accordance with (c), or shall be replaced with cylinders which have been inspected in accordance with (c) and found to exhibit no evidence of cracks.
(b) Within the next 1,200 hours' time in service after the effective date of this AD, unless already accomplished, all landing gear cylinders with cap welds which previously have been radiographically inspected by a method other than the double-wall gamma technique in compliance with AD 59-07-03, shall be reinspected in accordance with (c), or shall be replaced with cylinders which have been inspected in accordance with (c) and found to exhibit no evidence of cracks.
(c) The inspection techniques and procedures to be applied to all cylinders noted in (a) and (b) shall be those prescribed by Section B of Lockheed Field Service Letter No. FS/254049L, dated August 29, 1961, or FAA engineering approved equivalent. The entire periphery of the cap weld shall be inspected.
(d) Any cylinder with a cap weld which is found to exhibit any evidence of cracks when inspected as required by (a) or (b), shall be replaced prior to further flight of the aircraft. Cracked cylinders are not eligible for any further use in certificated aircraft.
(e) The cap welds on all cylinders which have been installed or which have been inspected, found to exhibit no evidence of cracks, and returned to service in accordance with (a) or (b), shall be reinspected in accordance with (c), at periods thereafter not to exceed 5,000 hours' time in service. The first periodic reinspection of any cylinder in service which, prior to the effective date of this AD, was inspected in the manner prescribed by (c) shall be accomplished within 5,000 hours' time in service following the date of that inspection.
(f) Cylinders with the cap welds which exhibit any evidence of cracks during any of these periodic reinspections shall be replaced prior to further flight of the aircraft. Cracked cylinders are not eligible for any further use in certificated aircraft.
(g) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator.
(h) When the cylinders described are replaced with new cylinders, TPC Co. P/N's 9040A-2A, 9106-2A, and 9291D-2A, incorporating flash welded caps, the inspections specified in (a) through (g), may be discontinued.
(Lockheed Field Service Letter FS/254049L covers this same subject.)
This supersedes AD 59-07-03.
This directive effective January 9, 1962.