Airworthiness Directives; Sikorsky Aircraft Corporation (Sikorsky) Model Helicopters, 71087-71089 [2012-28427]

Download as PDF Federal Register / Vol. 77, No. 230 / Thursday, November 29, 2012 / Rules and Regulations (d) Reason DEPARTMENT OF TRANSPORTATION This AD was prompted by a report of a low-pressure compressor (LPC) fan blade separation. We are issuing this AD to detect cracks in the LPC fan blades, which could lead to uncontained failure of the LPC fan blades and LPC fan disc, and damage to the airplane. (e) Actions and Compliance Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–1206; Directorate Identifier 2012–SW–021–AD; Amendment 39–17269; AD 2012–23–13] RIN 2120–AA64 Unless already done, do the following actions: (1) Before further flight after the effective date of this AD, perform a visual inspection and ultrasonic inspection of the LPC fan blades to determine general condition and/or the presence of cracks. (2) Thereafter, perform the inspections specified in paragraph (e)(1) of this AD within every additional 1,500 flight hours (FHs), but not fewer than 1,000 FHs. (3) If any fan blade is found cracked, replace the LPC fan blade set and the LPC fan disc before further flight. (f) Terminating Action Replacing the LPC fan blade set and the LPC fan disc is terminating action to the repetitive inspections required by this AD. (g) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs to this AD. Use the procedures found in 14 CFR 39.19 to make your request. (h) Related Information Airworthiness Directives; Sikorsky Aircraft Corporation (Sikorsky) Model Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for Sikorsky Model S–70, S–70A, and S– 70C helicopters, which are restricted category helicopters derived from the military Model UH–60 helicopter. This AD would require reducing or establishing life limits for certain listed helicopter parts. This AD is prompted by a review of the United States Army’s analysis of their Model UH–60 fleet, which determined it necessary to establish or reduce the life limits of certain parts. The actions are intended to prevent fatigue failure of a part and subsequent loss of control of the helicopter. SUMMARY: This AD becomes effective December 14, 2012. We must receive comments on this AD by January 28, 2013. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. (1) For more information about this AD, contact Frederick Zink, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; email: Frederick.zink@faa.gov; phone: 781– 238–7779; fax: 781–238–7199. (2) Refer to European Aviation Safety Agency AD 2012–0185–E, dated September 12, 2012, and RRD Alert Service Bulletin TAY–72–A1775, Revision 1, dated September 12, 2012, for related information. (3) For service information identified in this AD, contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlewitz, 15827 Blankenfelde-Mahlow, Germany; telephone: 49 0 33–7086–1944; fax: 49 0 33–7086–3276. (4) You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. DATES: (i) Material Incorporated by Reference Examining the AD Docket pmangrum on DSK3VPTVN1PROD with RULES None. Issued in Burlington, Massachusetts, on November 19, 2012. Robert J. Ganley, Acting Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2012–28638 Filed 11–28–12; 8:45 am] BILLING CODE 4910–13–P VerDate Mar<15>2010 13:45 Nov 28, 2012 Jkt 229001 You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the economic evaluation, any comments received, and other information. The street address for PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 71087 the Docket Operations Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Michael Davison, Flight Test Engineer, New England Regional Office, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: (781) 238–7156, email: michael.davison@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments prior to it becoming effective. However, we invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that resulted from adopting this AD. The most helpful comments reference a specific portion of the AD, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit them only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this rulemaking during the comment period. We will consider all the comments we receive and may conduct additional rulemaking based on those comments. Discussion We are adopting a new AD for Sikorsky Model S–70, S–70A and S–70C helicopters. This AD requires reducing or establishing life limits for the main rotor blade, tail rotor blade, planetary carrier assembly, tail rotor servo, elastomeric sleeve bearing, main landing gear shock strut piston cylinder, crossfeed valve, oil cooler axial fan ball bearing assembly, dowel pins, main rotor hub, and right tie rod attach bolt. This AD is prompted by the need to reduce life limits on the specified parts. This determination is based on a review of analysis by the U.S. Army of certain parts installed on the military Model UH–60 helicopters, which shows that the life limits of those parts need to be reduced. The Sikorsky Model S–70, S– 70A and S–70C helicopters are restricted category helicopters derived from the military Model UH–60 helicopter. The actions are intended to E:\FR\FM\29NOR1.SGM 29NOR1 71088 Federal Register / Vol. 77, No. 230 / Thursday, November 29, 2012 / Rules and Regulations establish life limits for certain parts to prevent fatigue failure of a part and subsequent loss of control of the helicopter. FAA’s Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other helicopters of these same type designs. AD Requirements This AD requires, before further flight, establishing or reducing life limits for certain parts and removing from service each part that has reached its life limit. Costs of Compliance We estimate that this AD will affect nine helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. It will take about 4.7 work hours at $85 per work hour to replace each part plus the required costs per helicopter as follows: • $70,000 for the main rotor blade, • $30,000 for the tail rotor blade, • $490 for the elastomeric sleeve bearing, • $233 for the right tie rod attach bolt, • $40,000 for the main rotor hub, • $12,000 for the main landing gear shock strut piston system, • $44,000 for the tail rotor servo, • $200 for the crossfeed breakaway valve, • $59,000 for the main module planetary carrier assembly, and • $3,700 for the dowel pins (11 total). Based on these figures, the total estimated cost is $2,372,607 to replace all the parts for the entire U.S. fleet. pmangrum on DSK3VPTVN1PROD with RULES FAA’s Justification and Determination of the Effective Date Since a part must be replaced before further flight if it has reached its life limit and some of the parts may have exceeded or be close to reaching the life limit, this AD must be issued immediately. Since an unsafe condition exists that requires the immediate adoption of this AD, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in less than 30 days. 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 VerDate Mar<15>2010 13:45 Nov 28, 2012 Jkt 229001 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. Regulatory Findings We 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, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; and 4. 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 and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by Reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2012–23–13 Sikorsky Aircraft Corporation: Amendment 39–17269; Docket No. FAA–2012–1206; Directorate Identifier 2012–SW–021–AD. (a) Applicability This AD applies to Model S–70, S–70A, and S–70C helicopters, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as fatigue failure of a main rotor blade, tail rotor blade, planetary carrier assembly, tail rotor servo, elastomeric sleeve bearing, main landing gear shock strut piston cylinder, crossfeed valve, oil cooler axial fan ball bearing assembly, dowel pin, main rotor hub, or right tie attach bolt remaining in service beyond its life limit. This condition could result in loss of control of the helicopter. (c) Effective Date This AD becomes effective December 14, 2012. (d) Compliance 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. (e) Required Action Before further flight: (1) Establish or reduce the retirement life of the following parts listed in Table 1–1 of the Sikorsky Technical Manual TM 1–70– 23AW–2, change 3, section 1.1, Airworthiness Limitations, by inserting a copy of Table 1–1 into the Airworthiness Limitations section of TM 1–70–23AW–2 or by making the following pen and ink changes to the Airworthiness Limitations of the maintenance manual: (i) For each dowel pin on the main transmission housing, part number (P/N) NAS607–10–12P, NAS607–12–14P, and NAS607–12–18P, establish a life limit of 3,000 hours time-in-service (TIS). (ii) For elastomeric sleeve bearing, P/N SB5203–202, establish a life limit of 720 hours TIS. (iii) For right tie rod attach bolt, P/N SS5025–04H010, establish a life limit of 3,500 hours TIS. (iv) For right tie rod attach bolt, P/N SS5025–04H10, establish a life limit of 5,000 hours TIS. (v) For oil cooler axial fan ball bearing, P/N 210SFFC, installed in oil cooler axial fans, P/N 70361–03005–103 through –106, establish a life limit of 2,000 hours TIS; and for bearings installed in oil cooler axial fan, P/N 70361–03005–107, establish a life limit of 2,500 hours TIS. (vi) For oil cooler axial fan ball bearing, P/N 210SFFC–0129, installed in oil cooler axial fan, 70361–03005–103 through –106, establish a life limit of 2,000 hours TIS; and for bearings installed in oil cooler axial fan, P/N 70361–03005–107, establish a life limit of 2,500 hours TIS. E:\FR\FM\29NOR1.SGM 29NOR1 Federal Register / Vol. 77, No. 230 / Thursday, November 29, 2012 / Rules and Regulations pmangrum on DSK3VPTVN1PROD with RULES (vii) For main rotor hub, P/N 70070– 10046–055, establish a life limit of 5,100 hours TIS. (viii) For main rotor blade, P/N 70080– 15001–041, establish a life limit of 5,000 hours TIS. (ix) For tail rotor blade, P/N 70080–15002– 041, establish a life limit of 5,000 hours TIS. (x) For main rotor blade, P/N 70080– 15003–041, establish a life limit of 5,000 hours TIS. (xi) For tail rotor blades, P/N 70080– 15004–041 and P/N 70080–15005–041, establish a life limit of 5,000 hours TIS. (xii) For main landing gear shock strut piston assembly, P/N 70250–12067–102, establish a life limit of 9,000 hours TIS. (xiii) For Number 2 crossfeed breakaway valve, P/N 70307–03600–103, establish a life limit of 1,500 hours TIS; (xiv) For main module planetary carrier assembly, P/N 70351–08175–043, –044, and –045, establish a life limit of 1,400 hours TIS; and for P/N 70351–08175–046 establish a life limit of 12,000 hours TIS. (xv) For dowel pins, P/N 70351–08404– 101, –102, and –103 on main transmission housings, P/N 70351–08110–044 and –045, establish a life limit of 3,000 hours TIS; for dowel pins, P/N 70351–08404–101, –102, –103, and –104 on main transmission housings, P/N 70351–28110–043 and –044, establish a life limit of 7,300 hours TIS; for dowel pins, P/N 70351–08404–101, –103, and –104, on main transmission housings, P/N 70351–38110–043, –044, and –045, establish a life limit of 11,000 hours TIS. (xvi) For dowel pin, flight control support mounting to main transmission housing, P/N 70531–04805–101, 70531–04805–102, and 70531–08405–103, establish a life limit of 3,000 hours TIS. (xvii) For dowel pin, flight control support mounting to transmission case, P/N 70351– 28404–101, on main transmission housings, P/N 70351–08110–044 and –045, reduce the life limit from 4,300 hours TIS to 3,000 hours TIS. (xviii) For main module planetary carrier assembly, P/N 70351–38175–041, establish a life limit of 6,500 hours TIS. (xvix) For dowel pin, flight control support mounting to transmission case, P/N 70351– 38404–101, on main transmission housings, P/N 70351–38110–043, –044, and –045, reduce the life limit from 20,000 hours TIS to 11,000 hours TIS. (xx) For the tail rotor servo, P/N 70410– 06520–044, –045, and –046, establish a life limit of 15,000 hours TIS. (2) Remove from service any part with a number of hours time-in-service equal to or greater than the part’s retirement life as stated in paragraph (e)(1) of this AD. (f) Special Flight Permit Special flight permits to allow flight in excess of life limits will not be issued. (g) Alternative Methods of Compliance (AMOC) (1) The Manager, Boston Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Michael Davison, Flight Test Engineer, New England Regional Office, 12 New England VerDate Mar<15>2010 13:45 Nov 28, 2012 Jkt 229001 Executive Park, Burlington, MA 01803; phone: (781) 238–7156; email: michael.davison@faa.gov. (2) For operations conducted under 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (h) Subject Joint Aircraft Service Component (JASC) Codes: 7921 Engine Oil Cooler, 6210 Main Rotor Blades, 6320 Tail Rotor Head, 6410 Tail Rotor Blades, 6720 Tail Rotor Control System, 3213 Main Landing Gear Strut/Axle/ Truck, 2824 Fuel Transfer Valve, and 1430 Fasteners. Issued in Fort Worth, Texas, on November 2, 2012. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2012–28427 Filed 11–28–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 43 [Docket No. FAA–2011–0763; Amendment No. 43–45] RIN 2120–AJ91 Pilot Loading of Aeronautical Database Updates Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: This action amends the maintenance regulations by removing from the preventive maintenance category the task of updating databases used in self-contained, front-panel or pedestal-mounted navigation equipment. Further, we are adding text to the maintenance regulations that describes which equipment and, under which conditions, may have aeronautical databases updated by pilots as a non-maintenance function. Equipment which does not meet the criteria outlined in the new regulation will continue to be updated as a maintenance function. This revision will ensure that pilots using specified avionics equipment have the most current and accurate data and thereby increase aviation safety. DATES: This rule becomes effective January 28, 2013. FOR FURTHER INFORMATION CONTACT: For technical questions about this SUMMARY: PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 71089 rulemaking action, contact Chris Parfitt, Flight Standards Service, Aircraft Maintenance Division—Avionics Maintenance Branch, AFS–360, Federal Aviation Administration, 950 L’Enfant Plaza SW., Washington, DC 20024; telephone (202) 385–6398; facsimile (202) 385–6474; email chris.parfitt@faa.gov. For legal questions about this action, contact Viola M. Pando, Office of the Chief Counsel, International Law, Legislation, and Regulations Division— Policy and Adjudication Branch, AGC– 210, Federal Aviation Administration, 800 Independence Ave. SW., Washington DC 20591; telephone (202) 493–5293; email viola.pando@faa.gov. SUPPLEMENTARY INFORMATION: Authority for This Rulemaking The FAA’s authority to issue rules on aviation safety is found in Title 49 of the United States Code. 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. This rulemaking is promulgated under the authority described in Subtitle VII, Part A, Subpart III, section 44701(a)(1), section 44703(b)(1)(D), and section 44711(a)(2). In section 44701(a)(1), the FAA is charged with prescribing regulations and minimum standards in the interest of safety for the manner of servicing of aircraft appliances. In section 44703(b)(1)(D), the FAA is charged with specifying the capacity in which the holder of a certificate may serve as an airman with respect to an aircraft. Section 44711(a)(2) prohibits any person from serving in any capacity as an airman with respect to a civil aircraft or aircraft appliance used, or intended for use, in air commerce without an airman certificate authorizing the airman to serve in the capacity for which the certificate was issued. This regulation is within the scope of the cited authority. I. Overview of the Final Rule This final rule allows all pilots operating aircraft equipped with certificated avionics equipment as described herein to perform updates of aeronautical databases. In 1996, the FAA updated the regulations defining preventive maintenance to include updating the navigation database of selfcontained, front-panel or pedestalmounted navigation equipment. This allowed the holder of a pilot certificate issued under part 61 to perform the database upload on any aircraft owned or operated by that pilot not used under parts 121, 129, or 135 (hereafter refered to as ‘‘restricted operations’’). The safety E:\FR\FM\29NOR1.SGM 29NOR1

Agencies

[Federal Register Volume 77, Number 230 (Thursday, November 29, 2012)]
[Rules and Regulations]
[Pages 71087-71089]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-28427]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1206; Directorate Identifier 2012-SW-021-AD; 
Amendment 39-17269; AD 2012-23-13]
RIN 2120-AA64


Airworthiness Directives; Sikorsky Aircraft Corporation 
(Sikorsky) Model Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for 
Sikorsky Model S-70, S-70A, and S-70C helicopters, which are restricted 
category helicopters derived from the military Model UH-60 helicopter. 
This AD would require reducing or establishing life limits for certain 
listed helicopter parts. This AD is prompted by a review of the United 
States Army's analysis of their Model UH-60 fleet, which determined it 
necessary to establish or reduce the life limits of certain parts. The 
actions are intended to prevent fatigue failure of a part and 
subsequent loss of control of the helicopter.

DATES: This AD becomes effective December 14, 2012.
    We must receive comments on this AD by January 28, 2013.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations Office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the economic evaluation, any 
comments received, and other information. The street address for the 
Docket Operations Office (telephone 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Michael Davison, Flight Test Engineer, 
New England Regional Office, FAA, 12 New England Executive Park, 
Burlington, MA 01803; phone: (781) 238-7156, email: 
michael.davison@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments prior to it becoming effective. However, we 
invite you to participate in this rulemaking by submitting written 
comments, data, or views. We also invite comments relating to the 
economic, environmental, energy, or federalism impacts that resulted 
from adopting this AD. The most helpful comments reference a specific 
portion of the AD, explain the reason for any recommended change, and 
include supporting data. To ensure the docket does not contain 
duplicate comments, commenters should send only one copy of written 
comments, or if comments are filed electronically, commenters should 
submit them only one time. We will file in the docket all comments that 
we receive, as well as a report summarizing each substantive public 
contact with FAA personnel concerning this rulemaking during the 
comment period. We will consider all the comments we receive and may 
conduct additional rulemaking based on those comments.

Discussion

    We are adopting a new AD for Sikorsky Model S-70, S-70A and S-70C 
helicopters. This AD requires reducing or establishing life limits for 
the main rotor blade, tail rotor blade, planetary carrier assembly, 
tail rotor servo, elastomeric sleeve bearing, main landing gear shock 
strut piston cylinder, crossfeed valve, oil cooler axial fan ball 
bearing assembly, dowel pins, main rotor hub, and right tie rod attach 
bolt. This AD is prompted by the need to reduce life limits on the 
specified parts. This determination is based on a review of analysis by 
the U.S. Army of certain parts installed on the military Model UH-60 
helicopters, which shows that the life limits of those parts need to be 
reduced. The Sikorsky Model S-70, S-70A and S-70C helicopters are 
restricted category helicopters derived from the military Model UH-60 
helicopter. The actions are intended to

[[Page 71088]]

establish life limits for certain parts to prevent fatigue failure of a 
part and subsequent loss of control of the helicopter.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other helicopters of these same type 
designs.

AD Requirements

    This AD requires, before further flight, establishing or reducing 
life limits for certain parts and removing from service each part that 
has reached its life limit.

Costs of Compliance

    We estimate that this AD will affect nine helicopters of U.S. 
Registry. We estimate that operators may incur the following costs in 
order to comply with this AD.
    It will take about 4.7 work hours at $85 per work hour to replace 
each part plus the required costs per helicopter as follows:
     $70,000 for the main rotor blade,
     $30,000 for the tail rotor blade,
     $490 for the elastomeric sleeve bearing,
     $233 for the right tie rod attach bolt,
     $40,000 for the main rotor hub,
     $12,000 for the main landing gear shock strut piston 
system,
     $44,000 for the tail rotor servo,
     $200 for the crossfeed breakaway valve,
     $59,000 for the main module planetary carrier assembly, 
and
     $3,700 for the dowel pins (11 total).

Based on these figures, the total estimated cost is $2,372,607 to 
replace all the parts for the entire U.S. fleet.

FAA's Justification and Determination of the Effective Date

    Since a part must be replaced before further flight if it has 
reached its life limit and some of the parts may have exceeded or be 
close to reaching the life limit, this AD must be issued immediately.
    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we determined that notice and opportunity for 
public comment before issuing this AD are impracticable and that good 
cause exists for making this amendment effective in less than 30 days.

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.

Regulatory Findings

    We 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, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska to the extent that 
it justifies making a regulatory distinction; and
    4. 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 and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2012-23-13 Sikorsky Aircraft Corporation: Amendment 39-17269; Docket 
No. FAA-2012-1206; Directorate Identifier 2012-SW-021-AD.

(a) Applicability

    This AD applies to Model S-70, S-70A, and S-70C helicopters, 
certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as fatigue failure of a 
main rotor blade, tail rotor blade, planetary carrier assembly, tail 
rotor servo, elastomeric sleeve bearing, main landing gear shock 
strut piston cylinder, crossfeed valve, oil cooler axial fan ball 
bearing assembly, dowel pin, main rotor hub, or right tie attach 
bolt remaining in service beyond its life limit. This condition 
could result in loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective December 14, 2012.

(d) Compliance

    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.

(e) Required Action

    Before further flight:
    (1) Establish or reduce the retirement life of the following 
parts listed in Table 1-1 of the Sikorsky Technical Manual TM 1-70-
23AW-2, change 3, section 1.1, Airworthiness Limitations, by 
inserting a copy of Table 1-1 into the Airworthiness Limitations 
section of TM 1-70-23AW-2 or by making the following pen and ink 
changes to the Airworthiness Limitations of the maintenance manual:
    (i) For each dowel pin on the main transmission housing, part 
number (P/N) NAS607-10-12P, NAS607-12-14P, and NAS607-12-18P, 
establish a life limit of 3,000 hours time-in-service (TIS).
    (ii) For elastomeric sleeve bearing, P/N SB5203-202, establish a 
life limit of 720 hours TIS.
    (iii) For right tie rod attach bolt, P/N SS5025-04H010, 
establish a life limit of 3,500 hours TIS.
    (iv) For right tie rod attach bolt, P/N SS5025-04H10, establish 
a life limit of 5,000 hours TIS.
    (v) For oil cooler axial fan ball bearing, P/N 210SFFC, 
installed in oil cooler axial fans, P/N 70361-03005-103 through -
106, establish a life limit of 2,000 hours TIS; and for bearings 
installed in oil cooler axial fan, P/N 70361-03005-107, establish a 
life limit of 2,500 hours TIS.
    (vi) For oil cooler axial fan ball bearing, P/N 210SFFC-0129, 
installed in oil cooler axial fan, 70361-03005-103 through -106, 
establish a life limit of 2,000 hours TIS; and for bearings 
installed in oil cooler axial fan, P/N 70361-03005-107, establish a 
life limit of 2,500 hours TIS.

[[Page 71089]]

    (vii) For main rotor hub, P/N 70070-10046-055, establish a life 
limit of 5,100 hours TIS.
    (viii) For main rotor blade, P/N 70080-15001-041, establish a 
life limit of 5,000 hours TIS.
    (ix) For tail rotor blade, P/N 70080-15002-041, establish a life 
limit of 5,000 hours TIS.
    (x) For main rotor blade, P/N 70080-15003-041, establish a life 
limit of 5,000 hours TIS.
    (xi) For tail rotor blades, P/N 70080-15004-041 and P/N 70080-
15005-041, establish a life limit of 5,000 hours TIS.
    (xii) For main landing gear shock strut piston assembly, P/N 
70250-12067-102, establish a life limit of 9,000 hours TIS.
    (xiii) For Number 2 crossfeed breakaway valve, P/N 70307-03600-
103, establish a life limit of 1,500 hours TIS;
    (xiv) For main module planetary carrier assembly, P/N 70351-
08175-043, -044, and -045, establish a life limit of 1,400 hours 
TIS; and for P/N 70351-08175-046 establish a life limit of 12,000 
hours TIS.
    (xv) For dowel pins, P/N 70351-08404-101, -102, and -103 on main 
transmission housings, P/N 70351-08110-044 and -045, establish a 
life limit of 3,000 hours TIS; for dowel pins, P/N 70351-08404-101, 
-102, -103, and -104 on main transmission housings, P/N 70351-28110-
043 and -044, establish a life limit of 7,300 hours TIS; for dowel 
pins, P/N 70351-08404-101, -103, and -104, on main transmission 
housings, P/N 70351-38110-043, -044, and -045, establish a life 
limit of 11,000 hours TIS.
    (xvi) For dowel pin, flight control support mounting to main 
transmission housing, P/N 70531-04805-101, 70531-04805-102, and 
70531-08405-103, establish a life limit of 3,000 hours TIS.
    (xvii) For dowel pin, flight control support mounting to 
transmission case, P/N 70351-28404-101, on main transmission 
housings, P/N 70351-08110-044 and -045, reduce the life limit from 
4,300 hours TIS to 3,000 hours TIS.
    (xviii) For main module planetary carrier assembly, P/N 70351-
38175-041, establish a life limit of 6,500 hours TIS.
    (xvix) For dowel pin, flight control support mounting to 
transmission case, P/N 70351-38404-101, on main transmission 
housings, P/N 70351-38110-043, -044, and -045, reduce the life limit 
from 20,000 hours TIS to 11,000 hours TIS.
    (xx) For the tail rotor servo, P/N 70410-06520-044, -045, and -
046, establish a life limit of 15,000 hours TIS.
    (2) Remove from service any part with a number of hours time-in-
service equal to or greater than the part's retirement life as 
stated in paragraph (e)(1) of this AD.

(f) Special Flight Permit

    Special flight permits to allow flight in excess of life limits 
will not be issued.

(g) Alternative Methods of Compliance (AMOC)

    (1) The Manager, Boston Aircraft Certification Office, FAA, may 
approve AMOCs for this AD. Send your proposal to: Michael Davison, 
Flight Test Engineer, New England Regional Office, 12 New England 
Executive Park, Burlington, MA 01803; phone: (781) 238-7156; email: 
michael.davison@faa.gov.
    (2) For operations conducted under 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, we suggest that you 
notify your principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office or 
certificate holding district office before operating any aircraft 
complying with this AD through an AMOC.

 (h) Subject

    Joint Aircraft Service Component (JASC) Codes: 7921 Engine Oil 
Cooler, 6210 Main Rotor Blades, 6320 Tail Rotor Head, 6410 Tail 
Rotor Blades, 6720 Tail Rotor Control System, 3213 Main Landing Gear 
Strut/Axle/Truck, 2824 Fuel Transfer Valve, and 1430 Fasteners.

    Issued in Fort Worth, Texas, on November 2, 2012.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-28427 Filed 11-28-12; 8:45 am]
BILLING CODE 4910-13-P