AD 2009-13-01 Airworthiness Directives; Sikorsky Aircraft Corporation Model S-92A Helicopters

Models named: S-92A. Read the applicability below — it usually turns on serial or part numbers too.

Model S-92A helicopters, certificated in any category.

Required as indicated, unless accomplished previously. To prevent failure of a main gearbox (MGB) filter bowl assembly mounting titanium stud (titanium stud), which could result in rapid loss of oil, failure of the MGB, and subsequent loss of control of the helicopter; and to clarify and emphasize certain Normal and Emergency procedures to give the crew the best available information in the event of certain MGB malfunctions, accomplish the following: (a) Before further flight, for all Model S-92A helicopters with a MGB housing assembly, part number (P/N) 92351-15110-042, -043, or -044, that is not marked with “TS-062-01” near the P/N: (1) Remove the titanium studs by following the Accomplishment Instructions in Sikorsky Alert Service Bulletin No. 92-63-014, Rev. A, dated March 20, 2009 (ASB), paragraph 3.A. Note 1: Figure 1 of the ASB contains guidance for removal and installation of the studs . (2) Visually inspect the tapped holes and the MGB housing lockring counterbore for damage. If you find damage in the tapped holes or in the MGB housing lockring counterbore, contact the Boston Aircraft Certification Office for an approved repair. (3) Install steel studs and mark the MGB housing as “TS-062-01” near the P/N by following the Accomplishment Instructions in the ASB, paragraph 3.C. (b) Within 10 hours time-in-service, for all helicopters regardless of MGB housing assembly P/N: (1) Revise the Normal and Emergency procedures sections of the Rotorcraft Flight Manual (RFM) by making the following changes, approved May 13, 2009:   RFM Remove Remove Insert SA S92A-RFM-000 Part I Temporary Revision (T-Rev) No. 1, Revised Main Gearbox Emergency Procedure Page 2-12, and Sub-Section 7 “Gear Box Malfunctions” from Section III Page 2-12, and Sub-Section 7 “Gear Box Malfunctions” from Section III of SA S92A-RFM-000, Revision No. 4. SA S92A-RFM-002 Part I T-Rev No. 5, Revised Main Gearbox Emergency Procedure Page 2-13, and Sub-Section 7 “Gear Box Malfunctions” from Section III Page 2-13, and Sub-Section 7 “Gear Box Malfunctions” from Section III of SA S92A-RFM-002, Revision No. 10. SA S92A-RFM-003 Part I T-Rev No. 4, Revised Main Gearbox Emergency Procedure Page 2-13, and Sub-Section 7 “Gear Box Malfunctions” from Section III Page 2-13, and Sub-Section 7 “Gear Box Malfunctions” from Section III of SA S92A-RFM-003, Revision No. 10. SA S92A-RFM-004 Part I T-Rev No. 4, Revised Main Gearbox Emergency Procedure Page 2-12, and Sub-Section 7 “Gear Box Malfunctions” from Section III Page 2-12, and Sub-Section 7 “Gear Box Malfunctions” from Section III of SA S92A-RFM-004, Revision No. 8. SA S92A-RFM-005 Part I T-Rev No. 3, Revised Main Gearbox Emergency Procedure Page 2-13, and Sub-Section 7 “Gear Box Malfunctions” from Section III Page 2-13, and Sub-Section 7 “Gear Box Malfunctions” from Section III of SA S92A-RFM-005, Revision No. 7. SA S92A-RFM-006 Part I T-Rev No. 2, Revised Main Gearbox Emergency Procedure Page 2-13, and Sub-Section 7 “Gear Box Malfunctions” from Section III Page 2-13, and Sub-Section 7 “Gear Box Malfunctions” from Section III of SA S92A-RFM-006, Revision No. 8. S92A-RFMS No. 3 N/A Sub-Section 7 “Gear Box Malfunctions” from Section III Sub-Section 7 “Gear Box Malfunctions” from Section III of S92A-RFM Supplement No. 3, Revision No. 2. All paragraphs of subsection 7 “Gear Box Malfunctions” starting with paragraph 7.0 are affected. Note 2: Inserting the following revisions, approved on May 13, 2009, and their associated Errata Sheets, dated June 4, 2009, into the RFM, as applicable, satisfies the requirements of this AD: (i) SA S92A-RFM-000 Revision No. 4, (ii) SA S92A-RFM-002 Revision No. 10, (iii) SA S92A-RFM-003 Revision No. 10, (iv) SA S92A-RFM-004 Revision No. 8, (v) SA S92A-RFM-005 Revision No. 7, (vi) SA S92A-RFM-006 Revision No. 8, and (vii) S92A-RFM Supplement No. 3, Revision No. 2. (c) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Boston Aircraft Certification Office, FAA, Attn: John M. Coffey, FAA, 12 New England Executive Park, Burlington, MA 01803, telephone (781) 238-7173, fax (781) 238-7170, for information about previously approved alternative methods of compliance. (d) Special flight permits will not be issued. (e) Remove and replace the titanium studs by following the specified portions of Sikorsky Alert Service Bulletin No. 92-63-014, Revision A, dated March 20, 2009. The Director of the Federal Register previously approved the incorporation by reference of this information on April 27, 2009 under 5 U.S.C. 552(a) and 1 CFR part 51 (74 FR 18977, April 27, 2009. Copies may be obtained from Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical Support, mailstop s581a, 6900 Main Street, Stratford, CT, telephone (203) 383-4866, e-mail address tsslibrary@sikorsky.com or at http://www.sikorsky.com. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas, or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. (f) This amendment becomes effective on July 1, 2009. Issued in Fort Worth, Texas, on June 9, 2009. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E9-14081 Filed 6-15-09; 8:45 am] BILLING CODE 4910-13-P