AD 64-13-03 ACTIVE

64-13-03 LOCKHEED: Amdt. 745 Part 507 Federal Register June 12, 1964. Applies to All Models 49, 149, 649, 649A, 749, 749A, 1049-54, 1049C, 1049D, 1049E, 1049G and 1049H Series Aircraft.

Compliance required as indicated.

As a result of a number of reported cracks and one failure in the nose landing gear retract cylinder rod terminal end, accomplish the following:

(a) Aircraft on which the nose landing gear retract cylinder rod terminal ends, P/N's 404052 or 1005032 have accumulated 4,500 or more landings on the effective date of this AD, shall be inspected in accordance with (d) within 100 landings after the effective date of this AD, unless already accomplished within the last 250 landings, and thereafter at intervals not to exceed 350 landings. If the rod terminal end is reworked in accordance with (g) the reworked part shall be inspected in accordance with (d) within 700 landings after the rework is accomplished, and thereafter at intervals not to exceed 700 landings.(b) Aircraft on which the nose landing gear retract cylinder rod terminal ends have accumulated less than 4,500 landings on the effective date of this AD, shall be inspected in accordance with (d) prior to the accumulation of 4,600 landings and thereafter at intervals not to exceed 350 landings. If the rod terminal end is reworked in accordance with (g), prior to accumulation of 4,500 landings the initial compliance with (d) is required prior to the accumulation of 5,200 landings and thereafter at intervals not to exceed 700 landings.

(c) For those operators maintaining records of hours' time in service in order to ascertain compliance with this AD, the number of landings required in (a) and (b) may be replaced with an equal number of hours' time in service. For those operators maintaining records of landing, in order to ascertain compliance with this AD where past records of landings are unavailable the number of landings prior to the effective date of this AD may be estimatedby substituting one landing for each hour of time in service.

(d) Inspect the rod terminal end in the area between the threaded shank and the fork legs on P/N 404052 and from the edge of the chrome plated rod area to the fork legs on P/N 1005032 for fatigue cracks by ultrasonic method, magnetic particle method or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region.

(e) Replace cracked P/N 404052 rod terminal ends before further flight. Used, uncracked parts may be used as replacements in lieu of new parts but must be inspected in accordance with (d) immediately prior to installation, and thereafter at intervals not to exceed the reinspection intervals of (a) and (b). Part Number 1005032, when used to replace P/N 404052, shall be installed in accordance with Lockheed Service Bulletin 49/SB-767 for Models 49 through 749A aircraft and Lockheed Service Bulletin 1049/SB-2144 for Models 1049-54 through 1049H Series aircraft.

(f) Replace crackedP/N 1005032 rods before further flight with parts of the same part number. Used, uncracked parts may be used as replacements in lieu of new parts but must be inspected in accordance with (d) immediately prior to installation, and thereafter at intervals not to exceed the reinspection intervals of (a) and (b).

(g) Uncracked retract cylinder terminal rod ends may be reworked as follows to qualify for the increased inspection intervals afforded in (a) and (b):

(1) Polish the radius areas between the shank and the fork legs to remove all evidence of corrosion and machine marks.

(2) Shot peen the radius areas between the shank and the fork legs to 0.012- 0.016 Almen A2 intensity using 0.019-0.028 cast steel shot.

(3) Cadmium plate the polished and shot peened areas per process specification QQ-P-416, Type II, Class B, and bake at 375-400 degrees F. for a minimum of three hours immediately after plating.

(4) Identify the rework by stamping "A" after the original partnumber.

(h) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, 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.

(Lockheed Service Bulletins 49/SB-767 and 1049/SB-2144 pertain, in part, to this subject.)

This directive effective June 12, 1964.