AD 47-35-02

Active

Tail Rotor Gearbox Brace

Key Information
47-35-02
Active
Not specified
Not specified
Unknown
N/A
Applicability
["Aircraft"]
["Rotorcraft"]
Holmes, Douglas W.
R-4B (Army)
Regulatory Text

47-35-02\tSIKORSKY: (Was Mandatory Note 2 of AD-7L-1.) Applies to Model R-4B AAF Helicopter Serial Numbers 43-46500 and 43-46504 to 43-46567 Inclusive. \n\nCompliance required prior to November 15, 1947. \n\nTo compensate for an increased overhang of the tail rotor gearbox, a diagonal brace that changes the aft boom load distribution shall be installed in accordance with the following instructions: \n\n(a)\tFit the two tube brace assemblies, Sikorsky P/N S38566 and S38567, in telescopic position, to lower right longeron and upper left longeron. (See Figures 2 and 3.) \n\n\nAD 47-35-02 \n\n(1)\tInsert bolts, P/N AN 4-13, into halves of clamp of each section of brace; attach washers, P/N AN 960-416, and nuts, P/N AN 310-4. \n\n(2)\tLocate brace so that its center and that of vertical tube, P/N S38505-23, forward of it, are a maximum of 1 1/8 inches apart. (See Figure 2.) \n\n(3)\tTighten securely four bolts, P/N AN 4-13, which hold subject brace in position. \n\n(4)\tSecure nuts, P/N AN 310-4, with cotter pins. \n\n(b)\tMark with a pencil the overlap of tube brace assembly, P/N S38566, on assembly P/N S38567. (See Figure 3.) \n\n\n\nAD 47-35-02 \n\n(c)\tFashion a wedge, using a piece of wood 1 x 3 x 14 inches, and "V" notch both ends. (See Figure 4.) \n\n(d)\tInsert wedge approximately parallel to telescopic brace. \n\n(1)\tTap alternately the ends of wedge forcing the subject assembly to extend 1/16 inch beyond the pencil line requested in paragraph (b). (Extra extension of 1/16 inch permits brace to assume the desired stress load.) \n\n(2)\tWrap longerons with friction tape at point of wedge contact, or insert cardboard or any suitable material at ends of wood wedge to prevent paint abrasion. \n\n(e)\tWith wedge securely in position, using drill No. 40 (0.098-inch), drill two holes through brace at 90 degrees to each other. (See Figure 3.) \n\n(1)\tEnlarge holes, using drill No. C (0.242 inch) and ream to 0.250 inch. \n\n(f)\tBolt two sections of brace together with bolts, P/N AN 24-17, nuts, P/N AN 320- 4, and secure with cotter pins. \n\n(g)\tRemove the wood wedge. \n\n(h)\tIf paint on longerons of tail fuselage has been damaged, touch up with paint. \n\n(Sikorsky Service Bulletin R-4B No. 8 and Army Technical Order 01-230HA-11 also cover this same alteration.)

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References
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--- - Part 39
FAA Documents