85-18-05 R2 SIKORSKY AIRCRAFT: Amendment 39-5129 as amended by Amendment 39-5525 is further amended by Amendment 39-6098.
Applicability: Model S-61L, S-61N, S-61NM, and S-61R series helicopters, certificated in all categories, and S-61A (S/N's 61083, 61087, 61094, and 61161) and S-61V (S/N 61271) helicopters, certificated in the restricted category, which are engaged in more than six external cargo lifts per flight hour under Part 133, Class B, Rotorcraft external load combination operations.
Compliance: Required as indicated (unless already accomplished).
To prevent operation with a main rotor spar crack and possible loss of the helicopter, accomplish the following:
(a) Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, remove main rotor blades from the rotorcraft that are not approved for use in Part 133 (Class B, Rotorcraft-external load combination operations), and replace with approved blades. The approved main rotor blades are as follows:
(1) The following blades are approved for Model S-61L, transport category helicopters operating up to a combined vehicle and cargo gross weight of 22,000 lbs., provided the main rotor blades have been altered and maintained in accordance with Service Bulletin (SB) 61B15-6, Rev. P, or later FAA-approved revisions, excluding Section 2, Part II:
(i) P/N's S6115-20501-041 and -042.
(ii) P/N's S6115-20601-042, -047, and -048.
(iii) P/N's 61170-20201-055, -056, -058, -059, -060, -061, -062, -065, and -067.
(iv) P/N's S6117-20101-041, -046, -050, -051, -054, -055, -056, -057, and 058.
(2) The following blades are approved for Model S-61N, transport category helicopters operating up to a combined vehicle and cargo gross weight of 22,000 lbs., or Model S-61NM, transport category helicopters operating up to a combined vehicle and cargo gross weight of 20,500 lbs., provided the main rotor blades have been altered and maintained in accordance with SB No. 61B15-6, Rev. P, or later FAA-approved revisions, excluding Section 2, Part II:
(i) P/N's S6115-20501-041, and -042.
(ii) P/N's S6115-20601-041, -042, -045, -046, -047, and -048.
(iii) P/N's S6188-15001-041 and -045.
(iv) P/N's 61170-20201-054, -055, -056, 058, -059, 060, -061, -062, -065, -067.
(v) P/N's S6117-20101-041, -046, -050, -051, -054, -055, -056, -057, and -058.
(3) P/N's 61170-20201-062 blades are approved for the Model S-61A (S/N's 61083 and 61094), restricted category helicopters, operating up to a combined vehicle and cargo gross weight of 22,000 lbs.
(4) P/N's S6115-20201-2 and -3 blades are approved for the Model S-61A (S/N's 61087 and 61161), restricted category helicopter, operating up to a combined vehicle and cargo gross weight of 19,000 lbs.
(5) P/N 61170-20201-060 blades are approved for the Model S-61V (S/N 61271), restricted category helicopter, operating up to a combined vehicle and cargo gross weight of 19,100 lbs.
(6) The following blades are approved for Model S-61R transport category helicopters operating up to a combined aircraft and cargo gross weight of 19,500 pounds:
(i) P/N's S6115-20501-041 and -042.
(ii) P/N's S6115-20601-042, and -045 through -048.
(iii) P/N's S6117-20101-041, -050, -051, -054, -056, -057, and -058.
(iv) P/N's 61170-20201-055, -056, -058 through -062, -064, -065, and -067.
(b) Within the next 1 1/2 hours time in service after the effective date of this AD, unless already accomplished, inspect main rotor blades equipped with approved visual blade pressure indicators (VBIM) but not equipped with an in-cockpit blade inspection system (CBIM) in accordance with paragraph (c). After the initial inspection, conduct further inspections in accordance with paragraph (c) prior to the first flight of each day and conduct subsequent visual inspections of the VBIM indicators in accordance with Section 2, Part IV, paragraph la of Sikorsky Service Bulletin No. 61B15-6, Revision P, or later FAA-approved revisions, at intervals not to exceed 1 1/2 hours time in service from the last inspection.
(c) Inspect the VBIM indicators of the main rotor blades in accordance with procedures set forth in Section 2, Part IV, of Sikorsky SB No. 61B15-6 Rev. P, or later FAA-approved revisions.
(1) Conduct visual inspection of blade-mounted VBIM indicators from the transmission work platform of the helicopter or equivalent to ensure that an accurate visual check is conducted.
(2) The visual inspection of blade-mounted VBIM indicators shall be conducted by either an individual who holds a pilot certificate with appropriate rating, or a mechanic certificate with airframe rating, or by an appropriately certificated maintenance entity. The person performing this inspection or check shall make entries of the results in the aircraft maintenance record including a description and date of the inspection and the name of the individual performing the inspection along with the certificate number, kind of certificate, and signature.
(d) For helicopters equipped with in-cockpit CBIM (reference Sikorsky SB No. 61B15-20D).
(1) Prior to the first flight of the day, after the effective date of this AD, unless already accomplished, and every 8 hours time in service thereafter.
(i) Visually inspect the main rotor blade VBIM pressure indicators in accordance with paragraph (c).
(ii) Test the VBIM pressure indicators and the in-cockpit CBIM transducers in accordance with the procedures set forth in Section 2, Part IV, of Sikorsky SB No. 61B15-6, Rev. P, or later FAA-approved revisions.
(2) Check the in-cockpit blade inspection system electrical circuit and CBIM warning light in flight by activating the (cockpit) BIM test switch located on the left overhead quarter panel at least once each (1) hour time in service during flight operations in accordance with the Rotorcraft Flight Manual (RFM).
(i) If the (cockpit) BIM warning light illuminates, continue operations in a normal manner.
(ii) If the (cockpit) BIM warning light does not illuminate, immediately check the BIM circuit breaker and reset if tripped.
(A) Repeat check of (cockpit) BIM test switch to verify if warning light illuminates. Continue with normal operations if BIM warning light functions properly.
(B) If the (cockpit) BIM warning light fails to illuminate, discontinue external load operations and land as soon as practical. Investigate and correct malfunction prior to further flight.
(3) If the (cockpit) BIM warning light illuminates during flight, discontinue external load operations and follow the appropriate emergency flight procedures in Part I, Section III, of the SA 4045-30 (S-61L) SA4045-100 (S-61L), or SA4045-82 (S-61N) RFM's.
NOTE: For Model S-61 helicopters not engaged in Part 133 external load operations, AD 74-20-07, Rev. 5, main rotor blade inspection requirements are applicable.
(e) Each blade with any black or red indication visible in the blade VBIM pressure indicator (or whose transducer activates the cockpit BIM warning light) is restricted from further flight until the cause of the indication is determined and corrected in accordance with procedures given in Sikorsky SB 61B15-6, Rev. P, or later FAA-approved revisions.
(f) Alternate inspections, repairs, modifications, or other means of compliance which provide an equivalent level of safety may be approved by the Manager, Boston Aircraft Certification Office, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803.
(g) Rotorcraft may be flown in accordance with the provisions of FAR Sections 21.197 and 21.199 to a base where the AD can be accomplished, except when a VBIM or CBIM indication exists.
The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552 (a) (1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Sikorsky Aircraft, Division of United Technologies, North Main Street, Stratford, Connecticut 06601, Attn: S-61 Commercial Product Support Department. These documents also may be examined at the Office of the Regional Counsel, Southwest Region, FAA, Bldg. 3B, 4400 Blue Mound Road, Fort Worth, Texas 76106.
This amendment revises Amendment 39-5129 (50 FR 38506; September 23, 1985), AD 85-18-05, as amended by Amendment 39-5525 (52 FR 8582; March 19, 1987), AD 85-18-05 R1 which was effective on April 13, 1987.
This amendment (39-6098, AD 85-18-05 R2) becomes effective February 8, 1989.