AD 60-17-03 R1 ACTIVE

60-17-03 R1 SIKORSKY: Amendment 191 as amended by Amendment 495, Amendment 747, Amendment 199, Amendment 39-1552, Amendment 39-2212, and Amendment 39-2743 is further amended by Amendment 39-6097.

Applicability: All S-58 series helicopters. (Docket No. 88-ASW-49)

Compliance: Required as indicated unless already accomplished.

As a result of a fatigue failure of the main rotor blade spar the following must be accomplished:

(a) All main rotor blade assemblies (less cuff) P/N's S1615-20100, -2, -4, -5, -6, S1615-20201-1, -2, -7, -8, -13 and -14, with 1,330 or more hours' time in service shall be removed from service before further flight.

(b) An X-ray inspection covering the complete cross sectional area of the spar from the root section to the tip of the blade must be conducted for cracks, internal flaws on inclusions in the material of the spar on all main rotor blade assemblies P/N'S S1615-20100, -2, -4, -5, -6, S1615-20201-1, -2, -7, -8, -13, -14, within the following time specified:

(1) All main rotor blades with 800 or more hours' time in service, prior to the next flight.

(2) All main rotor blades with less than 800 hours' time in service, within the next 100 hours' time in service except no rotor blade shall exceed 800 hours' time in service before X-ray inspection is conducted.

(c) Pending completion of the X-ray inspection in paragraph (b)(2), a daily visual inspection must be conducted on the spar of all blades with 500 or more hours' time in service as follows:

(1) Using a magnifying glass of not less than 8-power, inspect the external surface of the spar from the root section to the tip of the blade for cracks.

(2) Inspection of the upper surface of the spar must be conducted with the blade in normal static position.

(3) Inspection of the lower surface of the spar must be conducted by disconnecting the pitch controls and rotating the blade 180 degrees in pitch so that the surface beinginspected is in tension due to the blades own dead weight.

(d) If any cracks, internal flaws or inclusions are found in the spar material the blade must be replaced prior to further flight.

(e) The service life limit specified in (a) may be extended to 3,200 hours' total time in service for S1615-20201-7, -8, and -14 main rotor blade assemblies (less cuff) and S1615-20100, -2, -4, -5, -6, S1615-20201-1, -2, and -13 main rotor blade assemblies modified to S1615-20201-7, -8, or -14 assemblies, provided the blade assemblies are inspected at the times and in the manner set forth in Sikorsky Service Bulletin No. 58B15-4K, dated July 16, 1976 or later FAA approved revisions and, if low pressure is indicated, the cause is determined and corrected before further flight in accordance with that service bulletin.

NOTE: The check for black or red color indication on the pressure indicator for the main rotor blades, as specified in Part IV (Items 1 and 2) of the accomplishment instructions of Sikorsky Service Bulletin No. 58B15-4, may be accomplished by a properly trained pilot. Results of the requirements of checks must be recorded in accordance with the requirements of FAR Section 43.9.

(f) Upon request an alternate means of compliance which provides an equivalent level of safety with the requirements of this AD may be used when approved by the Manager, Rotorcraft Standards Staff, Aircraft Certification Service, ASW-110, FAA, Fort Worth, Texas 76193-0110.

(g) In accordance with Sections 21.197 and 21.199, the helicopter may be flown to a base where compliance may be accomplished.

This amendment amends Amendment 191 (25 FR 8026), AD 60-17-03, as amended by Amendment 495 (27 FR 10117), Amendment 747 (29 FR 7668), Amendment 199 (31 FR 3064), and Amendment 39-1552 (37 FR 23711), Amendment 39-2212 (40 FR 22249), and Amendment 39-2743 (41 FR 44998) which was effective October 26, 1976.

This amendment (39-6097, AD 60-17-03 R1) becomes effective February 2, 1989.