Airworthiness Directives; Sikorsky Aircraft Corporation Model S-76A, B, and C Helicopters, 30247-30249 [E7-10126]

Download as PDF Federal Register / Vol. 72, No. 104 / Thursday, May 31, 2007 / Rules and Regulations in accordance with the provisions of Article V of the Federal Credit Union Bylaws’’. PART 722—APPRAISALS 13. The authority citation for part 722 continues to read as follows: I Authority: 12 U.S.C. 1766, 1789, and 3339. 14. Section 722.3(d) is amended by adding ‘‘and (a)(5)’’ after the words ‘‘paragraphs (a)(1).’’ I PART 723—MEMBER BUSINESS LOANS 15. The authority citation for part 723 continues to read as follows: I Authority: 12 U.S.C. 1756, 1757, 1757A, 1766, 1785, 1789. 16. Section 723.7(a) introductory text is amended by changing the reference to ‘‘§ 723.4’’ to read ‘‘§ 723.3’’. I PART 742—REGULATORY FLEXIBILITY PROGRAM 17. The authority citation for part 742 continues to read as follows: I Authority: 12 U.S.C. 1756 and 1766. 18. Section 742.4(a)(3) is amended by removing ‘‘(b) and (c)’’ after ‘‘701.36(a)’’. I [FR Doc. E7–10392 Filed 5–30–07; 8:45 am] BILLING CODE 7535–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28241; Directorate Identifier 2007–SW–07–AD; Amendment 39– 15062; AD 2007–11–05] RIN 2120–AA64 Airworthiness Directives; Sikorsky Aircraft Corporation Model S–76A, B, and C Helicopters Federal Aviation Administration, DOT. ACTION: Final rule; request for comments. cprice-sewell on PRODPC61 with RULES AGENCY: SUMMARY: This amendment adopts a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S–76A, B, and C helicopters. This action requires a one-time ultrasonic inspection of the main rotor shaft assembly (M/R shaft) for cracking. This amendment is prompted by the discovery of cracking that occurred during the manufacturing of certain M/ R shafts. The actions specified in this VerDate Aug<31>2005 14:52 May 30, 2007 Jkt 211001 AD are intended to detect cracking in the M/R shaft, which could result in separation of the main rotor and subsequent loss of control of the helicopter. DATES: Effective June 15, 2007. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of June 15, 2007. Comments for inclusion in the Rules Docket must be received on or before July 30, 2007. ADDRESSES: Use one of the following addresses to submit comments on this AD: • DOT Docket Web site: Go to http:// dms.dot.gov and follow the instructions for sending your comments electronically; • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically; • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, Room PL–401, Washington, DC 20590; • Fax: (202) 493–2251; or • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. You may get the service information identified in this AD from Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical Support, mailstop s581a, 6900 Main Street, Stratford, Connecticut, phone (203) 383–4866, e-mail address tsslibrary@sikorsky.com. Examining the Docket: You may examine the docket that contains the AD, any comments, and other information on the Internet at http:// dms.dot.gov, or in person at the Docket Management System (DMS) Docket Offices between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them. FOR FURTHER INFORMATION CONTACT: Kirk Gustafson, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine and Propeller Directorate, FAA, 12 New England Executive Park, Burlington, MA 01803, telephone (781) 238–7190, fax (781) 238–7170. SUPPLEMENTARY INFORMATION: This amendment adopts an AD for Sikorsky PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 30247 Model S–76A, B, and C helicopters. This action requires, within 75 hours time-in-service (TIS), a one-time ultrasonic inspection of the M/R shaft for cracking. This amendment is prompted by the manufacturer’s discovery of cracking that occurred during the manufacturing of certain M/ R shafts. During a heat-treatment process of these M/R shafts, inadequate time was allowed for the M/R shafts to cool to a proper temperature between the heat-treatment cycles, which reduced the M/R shaft’s ductility (capability of the M/R shaft being fashioned into a new form), and increased the potential for cracking to occur during subsequent cold-work forming of the M/R shaft. The actions specified in this AD are intended to detect cracking in the M/R shaft, which could result in separation of the main rotor and subsequent loss of control of the helicopter. We have reviewed the following alert service bulletins: • Sikorsky Alert Service Bulletin (ASB) No. 76–66–45A, Revision A, which is applicable to all S–76 model helicopters, with a M/R shaft, P/N 76351–09630–041, with certain serial numbers, installed; and • Sikorsky ASB No. 76–66–46, which is applicable to all Model S–76A helicopters, with a M/R shaft, P/N 76351–09030-all dash numbers, with certain serial numbers, installed. Both ASBs are dated February 7, 2007, and both describe a one-time ultrasonic inspection of the M/R shaft for cracking, for main gear box (MGB) assemblies installed on helicopters, for MGB assemblies not installed on a helicopter, and for M/R shafts not installed on MGBs. This unsafe condition is likely to exist or develop on other helicopters of the same type design. Therefore, this AD is being issued to detect cracking in the M/ R shaft, which could result in separation of the main rotor and subsequent loss of control of the helicopter. This AD requires a one-time ultrasonic inspection of the M/R shaft for cracking, instructions for reassembly of the lower bearing housing assembly installation of the MGB and performance of a ground run leak test. Accomplish the inspection by following specified portions of the ASBs described previously. The ultrasonic inspection of the M/R shaft must be performed by a Level II or Level III inspector, qualified under the guidelines established by MIL–STD– 410E, ATA Specification 105, AIA– NAS–410, or an FAA-accepted equivalent for qualification standards of Nondestructive Testing inspection/ evaluation personnel. Recurrent training E:\FR\FM\31MYR1.SGM 31MYR1 cprice-sewell on PRODPC61 with RULES 30248 Federal Register / Vol. 72, No. 104 / Thursday, May 31, 2007 / Rules and Regulations and examinations are part of the qualification requirements. The short compliance time involved is required because the previously described critical unsafe condition can adversely affect the controllability or structural integrity of the helicopter. The Model S–76 helicopter fleet is comprised of a large number of aircraft operating in an off-shore logistics support role for the petroleum industry. As such, many aircraft operate at high utilization rates approaching 200 hours TIS per month and this rate could translate to a higher potential for cracks that may have formed during manufacturing to propagate, leading to failure of the M/R shaft. Therefore, performing a one-time ultrasonic inspection of the M/R shaft for cracking within 75 hours TIS, which may equate to less than 2 weeks time-in-service, along with replacing any cracked M/R shaft with an airworthy M/R shaft before further flight, justify issuance of this AD immediately. Since a situation exists that requires the immediate adoption of this regulation, it is found that notice and opportunity for prior public comment hereon are impracticable, and that good cause exists for making this amendment effective in less than 30 days. We estimate that this AD will affect 41 M/R shafts—20 M/R shafts to be removed from helicopters, 16 M/R shafts to be inspected before they are assembled into the MGB for installation on a helicopter, 5 M/R shafts that must be removed from a MGB for inspection before installation on a helicopter. We estimate that, at a labor rate of $80 per work hour, it will take approximately: • 100 work hours for the entire fleet of operators to determine whether they have an affected M/R shaft; • For the 20 M/R shafts installed in helicopters—80 work hours to remove the MGB and M/R shaft for inspection; 80 work hours to reinstall the M/R shaft and MGB; and 12 work hours to return the aircraft to service; • For the 5 M/R shafts installed in a MGB, but not installed in a helicopter— 2 work hours to remove the M/R shaft from the MGB; and • 4 work hours to ultrasonic inspect each of the 41 M/R shafts. Also, we estimate that for the 25 M/ R shafts that must be removed from a MGB for inspection, reassembly will require $100 in consumable parts for each MGB. Based on these figures, we estimate that the total cost impact of the AD on U.S. operators will be $299,620, assuming that operators do not find a M/R shaft with a crack. VerDate Aug<31>2005 14:52 May 30, 2007 Jkt 211001 Comments Invited This AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any written data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–2007–28241; Directorate Identifier 2007–SW–07–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD. We will consider all comments received by the closing date and may amend the AD in light of those comments. We will post all comments we receive, without change, to http:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this AD. Using the search function of our docket Web site, you can find and read the comments to any of our dockets, including the name of the individual who sent the comment. You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit http://dms.dot.gov. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared an economic evaluation of the estimated costs to comply with this AD. See the DMS to examine the economic evaluation. the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: I 2007–11–05 Sikorsky Aircraft Corporation: Amendment 39–15062. Docket No. FAA–2007–28241; Directorate Identifier 2007–SW–07–AD. Applicability: Model S–76A, B and C helicopters with a main rotor shaft assembly (M/R shaft) listed in the following table installed, certificated in any category. M/R shaft part No. Serial No. 76351–09030– all dash numbers. B015–00782 through B015– 00791; B015–00811 through B015–00816; E015–00844 through E015–00865; andE015– 00908 through E015– 00918. C213–00436 through C213– 00454; D213–00537 through D213–00545; andD213–00575 through D213–00585. 76351–09630– 041. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 Compliance: Required within 75 hours time-in-service, unless accomplished previously. E:\FR\FM\31MYR1.SGM 31MYR1 cprice-sewell on PRODPC61 with RULES Federal Register / Vol. 72, No. 104 / Thursday, May 31, 2007 / Rules and Regulations To detect cracking in the M/R shaft, which could result in separation of the main rotor and subsequent loss of control of the helicopter, accomplish the following: (a) Perform a one-time ultrasonic inspection of the M/R shaft for cracking in accordance with Nondestructive Testing/ Inspection Technique, Ultrasonic Technique (UT) Number 5043, latest version. The ultrasonic inspection of the M/R shaft must be performed by a Level II or Level III inspector, qualified under the guidelines established by MIL–STD–410E, ATA Specification 105, AIA–NAS–410, or an FAA-accepted equivalent for qualification standards of Nondestructive Testing inspection/evaluation personnel. Recurrent training and examinations are part of the qualification requirements. (1) For Model S–76A, B and C helicopters with a M/R shaft, P/N 76351–09630–041, installed, remove and inspect the M/R shaft in accordance with the Accomplishment Instructions, paragraphs 3.B.(1)(a) through 3.B.(1)(d)5 of Sikorsky Alert Service Bulletin (ASB) No. 76–66–45A, Revision A, dated February 7, 2007. (2) For Model S–76A helicopters with a M/R shaft, P/N 76351–09030—all dash numbers, installed, remove and inspect the M/R shaft in accordance with the Accomplishment Instructions, paragraphs 3.B.(1)(a) through 3.B.(1)(d)5 of Sikorsky ASB No. 76–66–46, dated February 7, 2007. (3) If a crack is found, replace the M/R shaft with an airworthy M/R shaft that has been ultrasonically inspected in accordance with paragraph (a) of this AD before further flight. (4) Reassemble the lower bearing housing assembly, install the main gear box, and perform the ground run leak test in accordance with the Accomplishment Instructions, paragraphs 3.B.(1)(f) through 3.B.(1)(l) of either ASB No. 76–66–45A, Revision A or ASB No. 76–66–46, both dated February 7, 2007, as appropriate for your part-numbered M/R shaft. (b) Before installing an affected M/R shaft, ultrasonically inspect the M/R shaft and reassemble the lower bearing housing assembly, install the main gear box, and perform the ground run leak test in accordance with the requirements of paragraph (a) of this AD. (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: Kirk Gustafson, Aviation Safety Engineer, 12 New England Executive Park, Burlington, MA 01803, telephone (781) 238–7190, fax (781) 238–7170, for information about previously approved alternative methods of compliance. (d) The ultrasonic inspection shall be done in accordance with the specified portions of Sikorsky Alert Service Bulletin (ASB) No. 76–66–45A, Revision A, and Sikorsky ASB No. 76–66–46, both dated February 7, 2007. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical Support, mailstop VerDate Aug<31>2005 14:52 May 30, 2007 Jkt 211001 s581a, 6900 Main Street, Stratford, Connecticut, phone (203) 383–4866, e-mail address tsslibrary@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. (e) This amendment becomes effective on June 15, 2007. Issued in Fort Worth, Texas, on May 16, 2007. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E7–10126 Filed 5–30–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24171; Directorate Identifier 2006–NE–08–AD; Amendment 39– 15075; AD 2007–11–18] RIN 2120–AA64 Airworthiness Directives; General Electric Company CF6–50C Series Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) CF6– 50C series turbofan engines. This AD requires reworking certain forward fan stator cases and installing a fan module secondary containment shield. This AD results from reports of uncontained fan blade failures causing damage and separation of airplane hydraulic lines. We are issuing this AD to prevent uncontained fan blade failures, which can result in separation of airplane hydraulic lines, damage to critical airplane systems, and possible loss of airplane control. DATES: This AD becomes effective July 5, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of July 5, 2007. ADDRESSES: You can get the service information identified in this AD from General Electric Company via GEAviation, Attn: Distributions, 111 Merchant St., Room 230, Cincinnati, PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 30249 Ohio 45246, telephone (513) 552–3272; fax (513) 552–3329. You may examine the AD docket on the Internet at http://dms.dot.gov or in Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC. FOR FURTHER INFORMATION CONTACT: Tara Chaidez, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: tara.chaidez@faa.gov; telephone (781) 238–7773; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to GE CF6–50C series turbofan engines. We published the proposed AD in the Federal Register on April 17, 2006 (71 FR 19661). That action proposed to require reworking certain forward fan stator cases and installing a fan module secondary containment shield. Examining the AD Docket You may examine the docket that contains the AD, any comments received, and any final disposition in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Reworked and Re-Identified Fan Stator Cases A private citizen states that some fan stator cases with certain part numbers (P/Ns) listed in the proposed AD might have been be reworked and re-identified to different P/Ns, per GE Service Bulletin (SB) No. CF6–50 S/B 72–0277. The commenter feels that the rework P/ Ns should also be listed in the AD. We agree. We added P/Ns 9173M37G01, G02, G03, G04, G05, and G06 to the list of affected fan stator cases in the AD. Updated Service Bulletin Since we issued the proposed AD, GE issued Revision 2 to the SBs incorporated by reference in this AD. These revisions contain minor formatting changes to the text, E:\FR\FM\31MYR1.SGM 31MYR1

Agencies

[Federal Register Volume 72, Number 104 (Thursday, May 31, 2007)]
[Rules and Regulations]
[Pages 30247-30249]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-10126]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28241; Directorate Identifier 2007-SW-07-AD; 
Amendment 39-15062; AD 2007-11-05]
RIN 2120-AA64


Airworthiness Directives; Sikorsky Aircraft Corporation Model S-
76A, B, and C Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
Sikorsky Aircraft Corporation (Sikorsky) Model S-76A, B, and C 
helicopters. This action requires a one-time ultrasonic inspection of 
the main rotor shaft assembly (M/R shaft) for cracking. This amendment 
is prompted by the discovery of cracking that occurred during the 
manufacturing of certain M/R shafts. The actions specified in this AD 
are intended to detect cracking in the M/R shaft, which could result in 
separation of the main rotor and subsequent loss of control of the 
helicopter.

DATES: Effective June 15, 2007.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 15, 2007.
    Comments for inclusion in the Rules Docket must be received on or 
before July 30, 2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically;
     Government-wide rulemaking Web site: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically;
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401, 
Washington, DC 20590;
     Fax: (202) 493-2251; or
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    You may get the service information identified in this AD from 
Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical 
Support, mailstop s581a, 6900 Main Street, Stratford, Connecticut, 
phone (203) 383-4866, e-mail address tsslibrary@sikorsky.com.
    Examining the Docket: You may examine the docket that contains the 
AD, any comments, and other information on the Internet at http://
dms.dot.gov, or in person at the Docket Management System (DMS) Docket 
Offices between 9 a.m. and 5 p.m., Monday through Friday, except 
Federal holidays. The Docket Office (telephone (800) 647-5227) is 
located on the plaza level of the Department of Transportation Nassif 
Building at the street address stated in the ADDRESSES section. 
Comments will be available in the AD docket shortly after the DMS 
receives them.

FOR FURTHER INFORMATION CONTACT: Kirk Gustafson, Aviation Safety 
Engineer, Boston Aircraft Certification Office, Engine and Propeller 
Directorate, FAA, 12 New England Executive Park, Burlington, MA 01803, 
telephone (781) 238-7190, fax (781) 238-7170.

SUPPLEMENTARY INFORMATION: This amendment adopts an AD for Sikorsky 
Model S-76A, B, and C helicopters. This action requires, within 75 
hours time-in-service (TIS), a one-time ultrasonic inspection of the M/
R shaft for cracking. This amendment is prompted by the manufacturer's 
discovery of cracking that occurred during the manufacturing of certain 
M/R shafts. During a heat-treatment process of these M/R shafts, 
inadequate time was allowed for the M/R shafts to cool to a proper 
temperature between the heat-treatment cycles, which reduced the M/R 
shaft's ductility (capability of the M/R shaft being fashioned into a 
new form), and increased the potential for cracking to occur during 
subsequent cold-work forming of the M/R shaft. The actions specified in 
this AD are intended to detect cracking in the M/R shaft, which could 
result in separation of the main rotor and subsequent loss of control 
of the helicopter.
    We have reviewed the following alert service bulletins:
     Sikorsky Alert Service Bulletin (ASB) No. 76-66-45A, 
Revision A, which is applicable to all S-76 model helicopters, with a 
M/R shaft, P/N 76351-09630-041, with certain serial numbers, installed; 
and
     Sikorsky ASB No. 76-66-46, which is applicable to all 
Model S-76A helicopters, with a M/R shaft, P/N 76351-09030-all dash 
numbers, with certain serial numbers, installed. Both ASBs are dated 
February 7, 2007, and both describe a one-time ultrasonic inspection of 
the M/R shaft for cracking, for main gear box (MGB) assemblies 
installed on helicopters, for MGB assemblies not installed on a 
helicopter, and for M/R shafts not installed on MGBs.
    This unsafe condition is likely to exist or develop on other 
helicopters of the same type design. Therefore, this AD is being issued 
to detect cracking in the M/R shaft, which could result in separation 
of the main rotor and subsequent loss of control of the helicopter. 
This AD requires a one-time ultrasonic inspection of the M/R shaft for 
cracking, instructions for reassembly of the lower bearing housing 
assembly installation of the MGB and performance of a ground run leak 
test. Accomplish the inspection by following specified portions of the 
ASBs described previously. The ultrasonic inspection of the M/R shaft 
must be performed by a Level II or Level III inspector, qualified under 
the guidelines established by MIL-STD-410E, ATA Specification 105, AIA-
NAS-410, or an FAA-accepted equivalent for qualification standards of 
Nondestructive Testing inspection/evaluation personnel. Recurrent 
training

[[Page 30248]]

and examinations are part of the qualification requirements.
    The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
controllability or structural integrity of the helicopter. The Model S-
76 helicopter fleet is comprised of a large number of aircraft 
operating in an off-shore logistics support role for the petroleum 
industry. As such, many aircraft operate at high utilization rates 
approaching 200 hours TIS per month and this rate could translate to a 
higher potential for cracks that may have formed during manufacturing 
to propagate, leading to failure of the M/R shaft. Therefore, 
performing a one-time ultrasonic inspection of the M/R shaft for 
cracking within 75 hours TIS, which may equate to less than 2 weeks 
time-in-service, along with replacing any cracked M/R shaft with an 
airworthy M/R shaft before further flight, justify issuance of this AD 
immediately.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.
    We estimate that this AD will affect 41 M/R shafts--20 M/R shafts 
to be removed from helicopters, 16 M/R shafts to be inspected before 
they are assembled into the MGB for installation on a helicopter, 5 M/R 
shafts that must be removed from a MGB for inspection before 
installation on a helicopter. We estimate that, at a labor rate of $80 
per work hour, it will take approximately:
     100 work hours for the entire fleet of operators to 
determine whether they have an affected M/R shaft;
     For the 20 M/R shafts installed in helicopters--80 work 
hours to remove the MGB and M/R shaft for inspection; 80 work hours to 
reinstall the M/R shaft and MGB; and 12 work hours to return the 
aircraft to service;
     For the 5 M/R shafts installed in a MGB, but not installed 
in a helicopter--2 work hours to remove the M/R shaft from the MGB; and
     4 work hours to ultrasonic inspect each of the 41 M/R 
shafts.
    Also, we estimate that for the 25 M/R shafts that must be removed 
from a MGB for inspection, reassembly will require $100 in consumable 
parts for each MGB. Based on these figures, we estimate that the total 
cost impact of the AD on U.S. operators will be $299,620, assuming that 
operators do not find a M/R shaft with a crack.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any written data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2007-28241; 
Directorate Identifier 2007-SW-07-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD. We will consider 
all comments received by the closing date and may amend the AD in light 
of those comments.
    We will post all comments we receive, without change, to http://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. Using the search function of our docket 
Web site, you can find and read the comments to any of our dockets, 
including the name of the individual who sent the comment. You may 
review the DOT's complete Privacy Act Statement in the Federal Register 
published on April 11, 2000 (65 FR 19477-78), or you may visit http://
dms.dot.gov.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national Government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared an economic evaluation of the estimated costs to comply 
with this AD. See the DMS to examine the economic evaluation.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2007-11-05 Sikorsky Aircraft Corporation: Amendment 39-15062. Docket 
No. FAA-2007-28241; Directorate Identifier 2007-SW-07-AD.
    Applicability: Model S-76A, B and C helicopters with a main 
rotor shaft assembly (M/R shaft) listed in the following table 
installed, certificated in any category.

------------------------------------------------------------------------
            M/R shaft part No.                       Serial No.
------------------------------------------------------------------------
76351-09030-all dash numbers..............  B015-00782 through B015-
                                             00791; B015-00811 through
                                             B015-00816; E015-00844
                                             through E015-00865; andE015-
                                             00908 through E015-00918.
76351-09630-041...........................  C213-00436 through C213-
                                             00454; D213-00537 through
                                             D213-00545; andD213-00575
                                             through D213-00585.
------------------------------------------------------------------------

    Compliance: Required within 75 hours time-in-service, unless 
accomplished previously.

[[Page 30249]]

    To detect cracking in the M/R shaft, which could result in 
separation of the main rotor and subsequent loss of control of the 
helicopter, accomplish the following:
    (a) Perform a one-time ultrasonic inspection of the M/R shaft 
for cracking in accordance with Nondestructive Testing/Inspection 
Technique, Ultrasonic Technique (UT) Number 5043, latest version. 
The ultrasonic inspection of the M/R shaft must be performed by a 
Level II or Level III inspector, qualified under the guidelines 
established by MIL-STD-410E, ATA Specification 105, AIA-NAS-410, or 
an FAA-accepted equivalent for qualification standards of 
Nondestructive Testing inspection/evaluation personnel. Recurrent 
training and examinations are part of the qualification 
requirements.
    (1) For Model S-76A, B and C helicopters with a M/R shaft, P/N 
76351-09630-041, installed, remove and inspect the M/R shaft in 
accordance with the Accomplishment Instructions, paragraphs 
3.B.(1)(a) through 3.B.(1)(d)5 of Sikorsky Alert Service Bulletin 
(ASB) No. 76-66-45A, Revision A, dated February 7, 2007.
    (2) For Model S-76A helicopters with a M/R shaft, P/N 76351-
09030--all dash numbers, installed, remove and inspect the M/R shaft 
in accordance with the Accomplishment Instructions, paragraphs 
3.B.(1)(a) through 3.B.(1)(d)5 of Sikorsky ASB No. 76-66-46, dated 
February 7, 2007.
    (3) If a crack is found, replace the M/R shaft with an airworthy 
M/R shaft that has been ultrasonically inspected in accordance with 
paragraph (a) of this AD before further flight.
    (4) Reassemble the lower bearing housing assembly, install the 
main gear box, and perform the ground run leak test in accordance 
with the Accomplishment Instructions, paragraphs 3.B.(1)(f) through 
3.B.(1)(l) of either ASB No. 76-66-45A, Revision A or ASB No. 76-66-
46, both dated February 7, 2007, as appropriate for your part-
numbered M/R shaft.
    (b) Before installing an affected M/R shaft, ultrasonically 
inspect the M/R shaft and reassemble the lower bearing housing 
assembly, install the main gear box, and perform the ground run leak 
test in accordance with the requirements of paragraph (a) of this 
AD.
    (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: Kirk Gustafson, Aviation Safety Engineer, 12 New England 
Executive Park, Burlington, MA 01803, telephone (781) 238-7190, fax 
(781) 238-7170, for information about previously approved 
alternative methods of compliance.
    (d) The ultrasonic inspection shall be done in accordance with 
the specified portions of Sikorsky Alert Service Bulletin (ASB) No. 
76-66-45A, Revision A, and Sikorsky ASB No. 76-66-46, both dated 
February 7, 2007. The Director of the Federal Register approved this 
incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 
CFR part 51. Copies may be obtained from Sikorsky Aircraft 
Corporation, Attn: Manager, Commercial Technical Support, mailstop 
s581a, 6900 Main Street, Stratford, Connecticut, phone (203) 383-
4866, e-mail address tsslibrary@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.
    (e) This amendment becomes effective on June 15, 2007.

    Issued in Fort Worth, Texas, on May 16, 2007.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E7-10126 Filed 5-30-07; 8:45 am]
BILLING CODE 4910-13-P