Airworthiness Directives; Sikorsky Aircraft Corporation (Sikorsky) Helicopters, 3303-3305 [2013-31459]

Download as PDF Federal Register / Vol. 79, No. 13 / Tuesday, January 21, 2014 / Rules and Regulations final rule because the Commission was not required to publish a notice of proposed rulemaking or to seek public comment under 5 U.S.C. 553 or any other laws. 5 U.S.C. 603(a), 604(a). Therefore, no regulatory flexibility analysis is required. List of Subjects in 11 CFR Part 111 For the reasons set out in the preamble, the Federal Election Commission amends Subchapter A of Chapter I of Title 11 of the Code of Federal Regulations as follows: Authority: 2 U.S.C. 432(i), 437g, 437d(a), 438(a)(8); 28 U.S.C. 2461 nt; 31 U.S.C. 3701, 3711, 3716–3719, and 3720A, as amended; 31 CFR parts 285 and 900–904. 2. Revise § 111.30 to read as follows: When will subpart B apply? Subpart B applies to violations of the reporting requirements of 2 U.S.C. 434(a) committed by political committees and their treasurers that relate to the reporting periods that begin on or after July 14, 2000, and that end on or before the date specified by 2 U.S.C. 437g(a)(4)(C)(v). This subpart, however, does not apply to reports that relate to reporting periods that end between January 1, 2014, and January 21, 2014. ■ 3. Remove and reserve § 111.41. Dated: January 13, 2014. On behalf of the Commission. Lee E. Goodman, Chairman, Federal Election Commission. [FR Doc. 2014–00960 Filed 1–17–14; 8:45 am] BILLING CODE 6715–01–P Airworthiness Directives; Sikorsky Aircraft Corporation (Sikorsky) Helicopters We are adopting a new airworthiness directive (AD) for Sikorsky Model S–70, S–70A, and S– 70C helicopters. This AD establishes a new life limit based on a prorated formula for certain identified components (parts) installed on Model S–70, S–70A, and S–70C helicopters after being previously installed on certain military model helicopters. This AD was prompted by the discovery that certain parts have been interchanged between military helicopter models with different life limits and the possibility that these same parts can be interchanged with civilian models with different life limits. The actions are intended to establish a pro-rated in service life limit for each identified part to prevent fatigue failure of a part and subsequent loss of control of the helicopter. SUMMARY: 1. The authority citation for part 111 continues to read as follows: [Removed and Reserved] [Docket No. FAA–2013–0636; Directorate Identifier 2012–SW–065–AD; Amendment 39–17709; AD 2013–25–13] Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ■ § 111.41 14 CFR Part 39 AGENCY: PART 111—COMPLIANCE PROCEDURE (2 U.S.C. 437g, 437d(a)) § 111.30 Federal Aviation Administration RIN 2120–AA64 Administrative practice and procedure, Elections, Law enforcement, Penalties. ■ DEPARTMENT OF TRANSPORTATION This AD is effective February 25, 2014. The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD as of February 25, 2014. ADDRESSES: For service information identified in this AD, contact Sikorsky Aircraft Corporation, Customer Service Engineering, 124 Quarry Road, Trumbull, CT 06611; telephone 1–800– Winged–S or 203–416–4299; email sikorskywcs@sikorsky.com. You may review a copy of the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. DATES: tkelley on DSK3SPTVN1PROD with RULES Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 VerDate Mar<15>2010 16:01 Jan 17, 2014 Jkt 232001 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 3303 other information. The street address for the Docket Operations Office (phone: 800–647–5527) is U.S. Department of Transportation, Docket Operations Office, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Michael Davison, Flight Test Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, Massachusetts 01803; telephone (781) 238–7156; email michael.davison@ faa.gov. SUPPLEMENTARY INFORMATION: Discussion On July 23, 2013, at 78 FR 44045, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 by adding an AD that would apply to Sikorsky Model S–70, S–70A, and S– 70C helicopters. The NPRM proposed inserting the component life prorating formula into the airworthiness limitation section of the maintenance manual or instructions for continued airworthiness, calculating the new life limit for each part by applying the formula, and establishing life limits for certain parts without applying the formula. Furthermore, the NPRM proposed updating the component log or equivalent record with the new inservice life limit and replacing each part that has reached or exceeded its new life limit with an airworthy part. Lastly, the NPRM proposed prohibiting installation of any applicable part on a Model S–70, S–70A, or S–70C helicopter if the number of hours is unknown or if certain parts have been previously installed on a Model UH–60M helicopter. The NPRM was prompted by the discovery that certain parts with identical part numbers but different life limits have been interchanged between military helicopter models and the possibility that these same parts can be interchanged with civilian models with different life limits. The proposed requirements were intended to establish a pro-rated in service life limit for each identified part to prevent fatigue failure of a part and subsequent loss of control of the helicopter. Comments We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM (78 FR 44045, July 23, 2013). FAA’s Determination We have reviewed the relevant information and determined that an E:\FR\FM\21JAR1.SGM 21JAR1 3304 Federal Register / Vol. 79, No. 13 / Tuesday, January 21, 2014 / Rules and Regulations unsafe condition exists and is likely to exist or develop on other products of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed. Costs of Compliance We estimate that this AD affects 9 helicopters of U.S. Registry. We estimate that the cost to insert pages into the aircraft’s airworthiness limitation section is negligible. (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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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 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 this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (a) Applicability This AD applies to Model S–70, S–70A, and S–70C helicopters, certificated in any category, with the following parts installed: (1) Spindle and liner assembly, part number (P/N) 38023–10374–041; (2) Main Rotor Hub, P/N 70070–10046–055 and –056; (3) Main Rotor Spindle nut, P/N 70102– 08105–102; (4) Main Rotor Control Horn, P/N 70102– 08111–047; (5) Main Rotor Hub, P/N 70103–08112–041 and –047; (6) Rotating Swashplate, P/N 70104– 08001–044 and –045; 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 (b) Unsafe Condition This AD defines the unsafe condition as a critical part remaining in service beyond its life limit due to previously being installed on a different helicopter model with higher usage and flight loads. This condition could result in fatigue failure of a critical part and subsequent loss of control of the helicopter. (c) Effective Date 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 (7) Main Rotor Shaft Extension, P/N 70351–08186–043; (8) Main Rotor Gear Box Housing, P/N 70351–38110–043, –044, and –045; (9) Main Rotor Shaft, P/N 70351–38131– 042; (10) Output Bevel Gear and Shaft, P/N 70358–06620–101 and –102; (11) Left Tie Rod Assembly, P/N 70400– 08115–043, –045, –046, and –047; (12) Forward Bellcrank Support Assembly, P/N 70400–08162–042; (13) Lateral Servo Bellcrank, P/N 70400– 08166–041; or (14) Tail Rotor Servo Assembly, P/N 70410–06520–044 through –046. [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2013–25–13 Sikorsky Aircraft Corporation (Sikorsky): Amendment 39–17709; Docket No. FAA–2013–0636; Directorate Identifier 2012–SW–065–AD. This AD becomes effective February 25, 2014. (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 Actions (1) Within 25 hours time-in-service (TIS): (i) Insert into the airworthiness limitation section of the maintenance manual or instructions for continued airworthiness the component life prorating formula in Section 1.1.3, Component Life Prorating, pages 1–25 and 1–26, of Sikorsky Technical Manual TM 1–70–23AW–2, Change 3, dated April 15, 2012. (ii) Using the service life limits in Table 1 to Paragraph (e) of this AD, apply the component life prorating formula and calculate the new life limit for each specified part. If the number of hours of a part is unknown, that part cannot be installed on a Sikorsky Model S–70, S–70A, or S–70C helicopter. Do not calculate a new life limit for the part where the Model SH–60 life limit is higher than the life limit on Models S–70, S–70A, and S–70C. TABLE 1 TO PARAGRAPH (e) P/N tkelley on DSK3SPTVN1PROD with RULES 38023–10374–041 70070–10046–055 70102–08105–102 70102–08111–047 S–70, S–70A, S–70C service life Part description .......................................... and –056 .......................... .......................................... .......................................... Spindle and Liner Assembly .......................... Main Rotor Hub .............................................. Main Rotor Spindle Nut .................................. Main Rotor Control Horn ................................ 70103–08112–041 and –047 .......................... 70104–08001–044–045 .................................. 70351–08186–043 .......................................... 70351–38110–043, –044, and –045 ............... 70351–38131–042 .......................................... 70358–06620–101 and –102 .......................... Main Rotor Hub .............................................. Rotating Swashplate ...................................... Main Rotor Shaft Extension ........................... Main Rotor Gear Box Housing ....................... Main Rotor Shaft ............................................ Output Bevel Gear and Shaft ........................ VerDate Mar<15>2010 16:01 Jan 17, 2014 Jkt 232001 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 8,000 5,100 8,000 20,000/1,300 2/ 2,500 2 5,100 11,000 14,000 11,000 17,000 5,000 E:\FR\FM\21JAR1.SGM 21JAR1 UH–60M service life SH–60B/F service life 6,400 3,100 6,400 10,000 10,000 1N/A 10,000 1 N/A 3,100 4,600 4,900 4,000 5,200 1,800 1 N/A 9,600 16,000 9,000 19,000 1 N/A Federal Register / Vol. 79, No. 13 / Tuesday, January 21, 2014 / Rules and Regulations 3305 TABLE 1 TO PARAGRAPH (e)—Continued P/N Part description S–70, S–70A, S–70C service life 70400–08115–043, –045, –046, and –047 .... 70400–08162–042 .......................................... 70400–08166–041 .......................................... 70410–06520–044 through –046 .................... Left Tie Rod Assembly ................................... Forward Bellcrank Support Assembly ............ Lateral Servo Bellcrank .................................. Tail Rotor Servo Assembly ............................ 14,000 14,000/2,500 3 20,000 15,000 UH–60M service life 4,600 5,600 11,000 11,000 SH–60B/F service life 6,300 7,600 14,000 1 N/A 1 There is no service life limit listed because the parts on Model SH–60B/F have a different P/N than the parts on Models S–70, S–70A, and S–70C. 2 For serial number (S/N) 32479930 through 324791859, with CAGE code 60078, the life limit is 1,300 hours TIS. For S/N A241–07543 through A241–07594, A241–07706 through A241–07755, A241–07768 through A241–07771, A241–07800 through A241–07831, R241–00101 through R241–00355, R241–00701 through R241–00966, and R241–01001 through R241–01166, the life limit is 2,500 hours TIS. 3 For S/N A–367–00001 through A367–00035, with CAGE code 78286, the life limit is 2,500 hours TIS. (iii) Record the newly-established life limit of each part on the part’s component log card or equivalent record. (2) After establishing the new life limit, replace each part that has reached or exceeded its new life limit with an airworthy part before further flight. (3) Do not install the following parts on a Model S–70, S–70A, or S–70C helicopter if they have been previously installed on a Model UH–60M helicopter: (i) Bolt, self retaining, P/N 70103–08801– 102; (ii) Bifilar, P/N 70107–08400–046; (iii) Aft Bellcrank, P/N 70400–08102–045; (iv) Aft Walking Beam Assembly, P/N 70400–08104–048; or (v) Close Tolerance Bolt, P/N 70400– 26802–102 and –103. (f) 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, Boston Aircraft Certification Office, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, Massachusetts 01803; telephone (781) 238–7156; email michael.davison@faa.gov. (2) For operations conducted under a 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. tkelley on DSK3SPTVN1PROD with RULES (g) Subject Joint Aircraft Service Component (JASC) Code: 6220 Main Rotor Hub, 6230 Main Rotor Mast/Swashplate, 6320 Main Rotor Gearbox, 6310 Engine/Transmission Coupling, 6510 Tail Rotor Drive Shaft. (h) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. VerDate Mar<15>2010 16:01 Jan 17, 2014 Jkt 232001 (i) Pages 1–25 and 1–26, Section 1.1.3, Component Life Prorating, of Sikorsky Technical Manual TM 1–70–23AW–2, Change 3, dated April 15, 2012. (ii) Reserved. (3) For Sikorsky service information identified in this AD, contact Sikorsky Aircraft Corporation, Customer Service Engineering, 124 Quarry Road, Trumbull, CT 06611; telephone 1–800–Winged–S or 203– 416–4299; email sikorskywcs@sikorsky.com. (4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. For information on the availability of this material at the FAA, call (817) 222–5110. (5) You may view this service information that is incorporated by reference 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Fort Worth, Texas, on December 5, 2013. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2013–31459 Filed 1–17–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2012–0661; Airspace Docket No. 09–AWA–4] RIN 2120–AA66 Amendment to Class B Airspace; Detroit, MI Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: This action modifies the Detroit, MI, Class B airspace area to contain aircraft conducting published instrument procedures at Detroit SUMMARY: PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 Metropolitan Wayne County Airport (DTW), Detroit, MI, within Class B airspace. The FAA is taking this action to support containment of aircraft operations using the three existing dual Simultaneous Independent Instrument Landing System (SIILS) configurations, runways 22R/21L, runways 4L/3R and runways 27L/27R, as well as support containment of aircraft operations for triple SIILS operations to runways 4L/ 4R/3R and runways 21L/22L/22R. This action will enhance safety, improve the flow of air traffic, and reduce the potential for midair collisions in the DTW terminal area, while accommodating the concerns of all airspace users. Furthermore, this effort supports the FAA’s national airspace redesign goal of optimizing terminal and enroute airspace areas to reduce aircraft delays and improve system capacity. DATES: Effective Date: 0901 UTC, April 3, 2014. The Director of the Federal Register approves this incorporation by reference action under 3 CFR part 51, subject to the annual revision of FAA Order 7400.9 and publication of conforming amendments. FOR FURTHER INFORMATION CONTACT: Colby Abbott, Airspace Policy and Regulations Group, Office of Airspace Services, Federal Aviation Administration, 800 Independence Avenue SW., Washington, DC 20591; telephone: (202) 267–8783. SUPPLEMENTARY INFORMATION: History On August 14, 2012, the FAA published in the Federal Register a notice of proposed rulemaking (NPRM) to modify the Detroit Class B airspace area (77 FR 48476). This action proposed to expand the lateral and vertical limits of the Detroit Class B airspace area to provide additional airspace needed to contain dual SIILS procedures and associated traffic patterns supporting runways 22R/21L, runways 4L/3R, and runways 27L/27R E:\FR\FM\21JAR1.SGM 21JAR1

Agencies

[Federal Register Volume 79, Number 13 (Tuesday, January 21, 2014)]
[Rules and Regulations]
[Pages 3303-3305]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-31459]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0636; Directorate Identifier 2012-SW-065-AD; 
Amendment 39-17709; AD 2013-25-13]
RIN 2120-AA64


Airworthiness Directives; Sikorsky Aircraft Corporation 
(Sikorsky) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for 
Sikorsky Model S-70, S-70A, and S-70C helicopters. This AD establishes 
a new life limit based on a prorated formula for certain identified 
components (parts) installed on Model S-70, S-70A, and S-70C 
helicopters after being previously installed on certain military model 
helicopters. This AD was prompted by the discovery that certain parts 
have been interchanged between military helicopter models with 
different life limits and the possibility that these same parts can be 
interchanged with civilian models with different life limits. The 
actions are intended to establish a pro-rated in service life limit for 
each identified part to prevent fatigue failure of a part and 
subsequent loss of control of the helicopter.

DATES: This AD is effective February 25, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of February 25, 
2014.

ADDRESSES: For service information identified in this AD, contact 
Sikorsky Aircraft Corporation, Customer Service Engineering, 124 Quarry 
Road, Trumbull, CT 06611; telephone 1-800-Winged-S or 203-416-4299; 
email sikorskywcs@sikorsky.com. You may review a copy of the referenced 
service information at the FAA, Office of the Regional Counsel, 
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 
76137.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://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 (phone: 800-647-5527) is U.S. Department of 
Transportation, Docket Operations Office, M-30, West Building Ground 
Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Michael Davison, Flight Test Engineer, 
Boston Aircraft Certification Office, Engine & Propeller Directorate, 
12 New England Executive Park, Burlington, Massachusetts 01803; 
telephone (781) 238-7156; email michael.davison@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    On July 23, 2013, at 78 FR 44045, the Federal Register published 
our notice of proposed rulemaking (NPRM), which proposed to amend 14 
CFR part 39 by adding an AD that would apply to Sikorsky Model S-70, S-
70A, and S-70C helicopters. The NPRM proposed inserting the component 
life prorating formula into the airworthiness limitation section of the 
maintenance manual or instructions for continued airworthiness, 
calculating the new life limit for each part by applying the formula, 
and establishing life limits for certain parts without applying the 
formula. Furthermore, the NPRM proposed updating the component log or 
equivalent record with the new in-service life limit and replacing each 
part that has reached or exceeded its new life limit with an airworthy 
part. Lastly, the NPRM proposed prohibiting installation of any 
applicable part on a Model S-70, S-70A, or S-70C helicopter if the 
number of hours is unknown or if certain parts have been previously 
installed on a Model UH-60M helicopter. The NPRM was prompted by the 
discovery that certain parts with identical part numbers but different 
life limits have been interchanged between military helicopter models 
and the possibility that these same parts can be interchanged with 
civilian models with different life limits.
    The proposed requirements were intended to establish a pro-rated in 
service life limit for each identified part to prevent fatigue failure 
of a part and subsequent loss of control of the helicopter.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we did not receive any comments on the NPRM (78 FR 44045, 
July 23, 2013).

FAA's Determination

    We have reviewed the relevant information and determined that an

[[Page 3304]]

unsafe condition exists and is likely to exist or develop on other 
products of these same type designs and that air safety and the public 
interest require adopting the AD requirements as proposed.

Costs of Compliance

    We estimate that this AD affects 9 helicopters of U.S. Registry.
    We estimate that the cost to insert pages into the aircraft's 
airworthiness limitation section is negligible.

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

    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 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.

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):

2013-25-13 Sikorsky Aircraft Corporation (Sikorsky): Amendment 39-
17709; Docket No. FAA-2013-0636; Directorate Identifier 2012-SW-065-
AD.

(a) Applicability

    This AD applies to Model S-70, S-70A, and S-70C helicopters, 
certificated in any category, with the following parts installed:
    (1) Spindle and liner assembly, part number (P/N) 38023-10374-
041;
    (2) Main Rotor Hub, P/N 70070-10046-055 and -056;
    (3) Main Rotor Spindle nut, P/N 70102-08105-102;
    (4) Main Rotor Control Horn, P/N 70102-08111-047;
    (5) Main Rotor Hub, P/N 70103-08112-041 and -047;
    (6) Rotating Swashplate, P/N 70104-08001-044 and -045;
    (7) Main Rotor Shaft Extension, P/N 70351-08186-043;
    (8) Main Rotor Gear Box Housing, P/N 70351-38110-043, -044, and 
-045;
    (9) Main Rotor Shaft, P/N 70351-38131-042;
    (10) Output Bevel Gear and Shaft, P/N 70358-06620-101 and -102;
    (11) Left Tie Rod Assembly, P/N 70400-08115-043, -045, -046, and 
-047;
    (12) Forward Bellcrank Support Assembly, P/N 70400-08162-042;
    (13) Lateral Servo Bellcrank, P/N 70400-08166-041; or
    (14) Tail Rotor Servo Assembly, P/N 70410-06520-044 through -
046.

(b) Unsafe Condition

    This AD defines the unsafe condition as a critical part 
remaining in service beyond its life limit due to previously being 
installed on a different helicopter model with higher usage and 
flight loads. This condition could result in fatigue failure of a 
critical part and subsequent loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective February 25, 2014.

(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 Actions

    (1) Within 25 hours time-in-service (TIS):
    (i) Insert into the airworthiness limitation section of the 
maintenance manual or instructions for continued airworthiness the 
component life prorating formula in Section 1.1.3, Component Life 
Prorating, pages 1-25 and 1-26, of Sikorsky Technical Manual TM 1-
70-23AW-2, Change 3, dated April 15, 2012.
    (ii) Using the service life limits in Table 1 to Paragraph (e) 
of this AD, apply the component life prorating formula and calculate 
the new life limit for each specified part. If the number of hours 
of a part is unknown, that part cannot be installed on a Sikorsky 
Model S-70, S-70A, or S-70C helicopter. Do not calculate a new life 
limit for the part where the Model SH-60 life limit is higher than 
the life limit on Models S-70, S-70A, and S-70C.

                                            Table 1 to Paragraph (e)
----------------------------------------------------------------------------------------------------------------
                                                                  S-70, S-70A, S-
                  P/N                       Part description        70C service       UH-60M         SH-60B/F
                                                                       life        service life    service life
----------------------------------------------------------------------------------------------------------------
38023-10374-041.......................  Spindle and Liner                  8,000           6,400          10,000
                                         Assembly.
70070-10046-055 and -056..............  Main Rotor Hub..........           5,100           3,100          \1\N/A
70102-08105-102.......................  Main Rotor Spindle Nut..           8,000           6,400          10,000
70102-08111-047.......................  Main Rotor Control Horn.    20,000/1,300          10,000         \1\ N/A
                                                                   \2\/2,500 \2\
70103-08112-041 and -047..............  Main Rotor Hub..........           5,100           3,100         \1\ N/A
70104-08001-044-045...................  Rotating Swashplate.....          11,000           4,600           9,600
70351-08186-043.......................  Main Rotor Shaft                  14,000           4,900          16,000
                                         Extension.
70351-38110-043, -044, and -045.......  Main Rotor Gear Box               11,000           4,000           9,000
                                         Housing.
70351-38131-042.......................  Main Rotor Shaft........          17,000           5,200          19,000
70358-06620-101 and -102..............  Output Bevel Gear and              5,000           1,800         \1\ N/A
                                         Shaft.

[[Page 3305]]

 
70400-08115-043, -045, -046, and -047.  Left Tie Rod Assembly...          14,000           4,600           6,300
70400-08162-042.......................  Forward Bellcrank           14,000/2,500           5,600           7,600
                                         Support Assembly.                   \3\
70400-08166-041.......................  Lateral Servo Bellcrank.          20,000          11,000          14,000
70410-06520-044 through -046..........  Tail Rotor Servo                  15,000          11,000         \1\ N/A
                                         Assembly.
----------------------------------------------------------------------------------------------------------------
\1\ There is no service life limit listed because the parts on Model SH-60B/F have a different P/N than the
  parts on Models S-70, S-70A, and S-70C.
\2\ For serial number (S/N) 32479930 through 324791859, with CAGE code 60078, the life limit is 1,300 hours TIS.
For S/N A241-07543 through A241-07594, A241-07706 through A241-07755, A241-07768 through A241-07771, A241-07800
  through A241-07831, R241-00101 through R241-00355, R241-00701 through R241-00966, and R241-01001 through R241-
  01166, the life limit is 2,500 hours TIS.
\3\ For S/N A-367-00001 through A367-00035, with CAGE code 78286, the life limit is 2,500 hours TIS.

    (iii) Record the newly-established life limit of each part on 
the part's component log card or equivalent record.
    (2) After establishing the new life limit, replace each part 
that has reached or exceeded its new life limit with an airworthy 
part before further flight.
    (3) Do not install the following parts on a Model S-70, S-70A, 
or S-70C helicopter if they have been previously installed on a 
Model UH-60M helicopter:
    (i) Bolt, self retaining, P/N 70103-08801-102;
    (ii) Bifilar, P/N 70107-08400-046;
    (iii) Aft Bellcrank, P/N 70400-08102-045;
    (iv) Aft Walking Beam Assembly, P/N 70400-08104-048; or
    (v) Close Tolerance Bolt, P/N 70400-26802-102 and -103.

(f) 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, Boston Aircraft Certification Office, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, 
Massachusetts 01803; telephone (781) 238-7156; email 
michael.davison@faa.gov.
    (2) For operations conducted under a 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.

(g) Subject

    Joint Aircraft Service Component (JASC) Code: 6220 Main Rotor 
Hub, 6230 Main Rotor Mast/Swashplate, 6320 Main Rotor Gearbox, 6310 
Engine/Transmission Coupling, 6510 Tail Rotor Drive Shaft.

(h) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Pages 1-25 and 1-26, Section 1.1.3, Component Life 
Prorating, of Sikorsky Technical Manual TM 1-70-23AW-2, Change 3, 
dated April 15, 2012.
    (ii) Reserved.
    (3) For Sikorsky service information identified in this AD, 
contact Sikorsky Aircraft Corporation, Customer Service Engineering, 
124 Quarry Road, Trumbull, CT 06611; telephone 1-800-Winged-S or 
203-416-4299; email sikorskywcs@sikorsky.com.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137. For information on the availability of this 
material at the FAA, call (817) 222-5110.
    (5) You may view this service information that is incorporated 
by reference 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on December 5, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-31459 Filed 1-17-14; 8:45 am]
BILLING CODE 4910-13-P

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