AD 2013-20-15

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.

(1) Before further flight, for each part listed in Table 1 to paragraph (f) of this AD:

(i) Remove any part that has reached or exceeded its newly established or revised retirement life.

(ii) Record the newly established or revised retirement life for each part on the component history card or equivalent record.

(iii) Make pen and ink changes or insert a copy of this AD into the Airworthiness Limitations section of the maintenance manual to establish or revise the retirement life for each part that is listed in Table 1 to paragraph (f) of this AD.

(2) Before further flight, remove from service any part with a P/N listed in Table 2 to Paragraph (f) of this AD, regardless of the part's TIS. The part numbers listed in Table 2 to paragraph (f)(2) of this AD are not eligible for installation on any helicopter.

(3) Within 20 hours TIS, and thereafter at intervals not to exceed 20 hours TIS, visually inspect each M/R servo and control arm assembly, P/N S1565-20421-10, -11, -041, or -043, and determine if there is any oil leaking from the M/R tandem servo housing assembly (servo housing), P/N S1565-20252-2. If there is any oil leaking from the servo housing, before further flight, replace the M/R servo and control arm assembly.

(4) Within 20 hours TIS or before reaching 1,120 hours TIS, whichever occurs later, and thereafter at intervals not to exceed 200 hours TIS or 12 months, whichever occurs first, ultrasonic (UT) inspect each M/R hub horizontal hinge pin (hinge pin), P/N S1510-23099-1 or P/N S1510-23099-001, for a crack in accordance with the Accomplishment Instructions, paragraphs 2.A through 2.C, of Erickson Service Bulletin No. 64B10-3, Revision D, dated October 15, 2007, except you are not required to contact Erickson nor send hinge pins to them. A non-destructive testing (NDT) UT Level I Special, Level II, or Level III inspector who is qualified under the guidelines established by ASNT SNT-TC-1A, ISO 9712, or an FAA-accepted equivalent qualification standard for NDT inspection and evaluation, must perform the UT inspection.

(5) Within 150 hours TIS or before reaching 1,450 hours TIS, whichever occurs later, perform a fluorescent-magnetic particle inspection (MPI) of each second stage planetary plate assembly, P/N 6435-20231-016, for a crack.

(6) Within 150 hours TIS or before reaching 1,450 hours TIS, whichever occurs later, and thereafter at intervals not to exceed 650 hours TIS, perform an MPI of each M/R shaft, P/N 6435-20078-104, for a crack, paying particular attention to the lower spline area.

(7) Within 150 hours TIS or before reaching 1,450 hours TIS, whichever occurs later, and thereafter at intervals not to exceed 1,450 hours TIS, perform an MPI of each M/R shaft, P/N 6435-20078-105, for a crack, paying particular attention to the lower spline area.

(8) Within 150 hours TIS or before reaching 3,375 hours TIS, whichever occurs later, and thereafter at intervals not to exceed 3,375 hours TIS, perform a fluorescent penetrant inspection of each housing lug on each servo housing, P/N S1565-20252-2, for a crack.

(9) At each overhaul of the main gearbox assembly, P/N 6435-20400-053, -054, -058, -060, -062, -063, -064, -065, or -066, perform an MPI of the entire shaft of each M/R shaft assembly, P/N 6435-20078-014, -015, or -016, for a crack, paying particular attention to the rotating swashplate spherical bearing ball travel area, which is located approximately ten inches above the upper roller bearing journal shoulder.

(10) If there is a crack in any part, before further flight, replace the cracked part.

(11) At each overhaul of the damper assembly, P/N 6410-26200-042, replace the following parts with airworthy parts that have zero (0) hours TIS:

(i) All Air Force-Navy Aeronautical Standard (AN), Aerospace Standard (AS), Military Standard (MS), and National Aerospace Standard (NAS) nuts, bolts, washers, and packings, except packing, P/N MS28775-011, installed on stud, P/N SHF111-11SN-12A;

(ii) Lock washer, P/N SS5073-2;

(iii) Nut, P/N SS5081-05;

(iv) Felt seal, P/N S1510-26017;

(v) Retaining ring, P/N UR106L; and

(vi) Nut, P/N 6410-26214-101.