Airworthiness Directives; Sikorsky Aircraft Corporation (Sikorsky) Model Helicopters, 37160-37162 [2013-14699]

Download as PDF 37160 Federal Register / Vol. 78, No. 119 / Thursday, June 20, 2013 / Proposed Rules 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Bell Helicopter Textron Canada: Docket No. FAA–2013–0526; Directorate Identifier 2008–SW–14–AD. (a) Applicability This AD applies to Model 206L–4 and 407 helicopters, with a freewheel aft bearing cap (cap), part number (P/N) 406–040–509–101, with a serial number with a prefix of ‘‘A–’’ and Nos. 1833 through 1912, installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as certain caps being manufactured without a lubrication channel to allow oil flow into the aft bearing support assembly, which could result in failure of the freewheel unit and subsequent loss of control of the helicopter. 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) Additional Information The subject of this AD is addressed in Transport Canada Civil Aviation AD No. CF– 2004–17R1, dated February 11, 2005. (h) Subject Joint Aircraft Service Component (JASC) Code: 6300: Main Rotor Drive System. Issued in Fort Worth, Texas, on June 13, 2013. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2013–14693 Filed 6–19–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 (c) Comments Due Date We must receive comments by August 19, 2013. [Docket No. FAA–2013–0514; Directorate Identifier 2012–SW–068–AD] (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. Airworthiness Directives; Sikorsky Aircraft Corporation (Sikorsky) Model Helicopters mstockstill on DSK4VPTVN1PROD with PROPOSALS (e) Required Actions Within 50 hours time-in-service (TIS): (1) Remove and disassemble each freewheel assembly. (2) Replace the sprag and retainer (item 7), the output shaft (item 10), and the aft seal (item 3), as depicted in Figure 2 of Bell Alert Service Bulletin (ASB) No. 206L–04–129 for the Model 206L–4 and ASB No. 407–04–66 for the Model 407, both Revision A, and both dated December 1, 2004. (3) Visually inspect the remaining freewheel part details for a missing channel. (4) If the channel is missing, replace or rework the cap assembly by following the instructions depicted in Figure 3 of ASB 206L–04–129 or ASB 407 04–66, as applicable for your model helicopter. Using a vibrating stylus, mark the letter ‘‘R’’ at the end of the serial number on the cap assembly. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Eric Haight, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Policy Group, Fort Worth, Texas 76137, telephone (817) 222–5110, email: eric.haight@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 VerDate Mar<15>2010 16:29 Jun 19, 2013 Jkt 229001 RIN 2120–AA64 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for Sikorsky Model S–76A, B, and C helicopters to require certain inspections of each spindle cuff assembly or blade fold cuff assembly for a crack. If there is a crack, this proposed AD would require replacing the cracked part. If there is no crack, this AD would require applying white paint to the inspection area to enhance the existing inspection procedure. This proposed AD is prompted by the discovery of cracks in the spindle cuffs. The proposed actions are intended to prevent failure of a spindle cuff assembly or blade fold cuff assembly, loss of a rotor blade, and subsequent loss of control of the helicopter. DATES: We must receive comments on this proposed AD by August 19, 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. SUMMARY: PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 • 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 proposed 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 service information identified in this proposed AD, contact Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical Support, mailstop s581a, 6900 Main Street, Stratford, CT 06614; telephone (800) 562–4409; email tsslibrary@sikorsky.com; or at http:// www.sikorsky.com; http:// www.eurocopter.com/techpub. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. FOR FURTHER INFORMATION CONTACT: Nicholas Faust, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, Massachusetts 01803; telephone (781) 238–7763; email nicholas.faust@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited 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 might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, 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 E:\FR\FM\20JNP1.SGM 20JNP1 Federal Register / Vol. 78, No. 119 / Thursday, June 20, 2013 / Proposed Rules filed electronically, commenters should submit 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 proposed rulemaking. Before acting on this proposal, we will consider all comments we receive on or before the closing date for comments. We will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. We may change this proposal in light of the comments we receive. Discussion We propose to adopt a new AD for Sikorsky Model S–76A, B, and C helicopters. This proposed AD would require, depending on the hours timein-service (TIS) of each part, either a one-time nondestructive inspection (NDI) or a visual inspection of each spindle cuff assembly or blade fold cuff assembly for a crack. If there is a crack, this proposed AD would require replacing the cracked part. If there is no crack, this proposed AD would require applying white paint to a portion of each spindle cuff assembly or blade fold cuff assembly lower cuff plate to enhance the existing inspection procedure. This proposed AD is prompted by the discovery of five cracked spindle cuffs found during aircraft overhaul. The proposed actions are intended to prevent failure of a spindle cuff assembly or blade fold cuff assembly, loss of a rotor blade, and subsequent loss of control of the helicopter. mstockstill on DSK4VPTVN1PROD with PROPOSALS FAA’s Determination We are proposing this AD because we evaluated all known relevant information and determined that an unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs. Related Service Information Sikorsky issued S–76 Alert Service Bulletin ASB 76–65–67A, Revision A, dated July 18, 2012 (ASB), which specifies performing an NDI of the upper and lower cuff plate on each spindle cuff assembly or blade fold cuff assembly for a crack, either by eddy current, fluorescent penetrant, or ultrasonic inspection. If a crack indication is detected and not verified, the ASB specifies performing a different NDI to verify a crack. If there is a crack, the ASB specifies removing the spindle cuff assembly or blade fold cuff assembly from service. If a crack cannot be verified, the ASB specifies contacting VerDate Mar<15>2010 16:29 Jun 19, 2013 Jkt 229001 Sikorsky for further instruction. Finally, if no crack is found, the ASB specifies applying white paint to a portion of the spindle cuff assembly or blade fold cuff assembly lower cuff plate to enhance the existing inspection procedure. Proposed AD Requirements This proposed AD would require within 150 hours TIS: • For each spindle cuff assembly or blade cuff assembly with 1,900 or more hours TIS, conducting an NDI by a qualified inspector by following specified portions of the ASB. • For each spindle cuff assembly or blade cuff assembly with less than 1,900 hours TIS, visually inspecting each white paint application area for a crack by using a 5x or higher power magnifying glass. • If there is a crack, before further flight, replacing each cracked spindle cuff assembly or cracked blade fold cuff assembly with an airworthy assembly. • If there is no crack, applying white paint by following specified portions of the ASB. This proposed AD also prohibits installing an affected spindle cuff assembly or blade cuff fold assembly on any helicopter unless it has been inspected in accordance with the requirements of this AD. 37161 it would take 2.5 work hours and an estimated parts cost of $54,000, for a total cost of $54,212 for each helicopter. 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. Differences Between This Proposed AD and the Service Information The ASB specifies contacting the manufacturer if suspect cracks are not confirmed in the spindle cuff assembly or blade fold cuff assembly; this proposed AD would not require contacting the manufacturer. This proposed AD applies to spindle cuff assembly, part number (P/N) 76102– 08001–043, which was inadvertently omitted in the ASB. The manufacturer has stated that they will issue an ASB in the future that will also apply to this spindle cuff assembly. The ASB applies to spare parts; this proposed AD does not. Costs of Compliance We estimate that this proposed AD would affect 181 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD, based on an average labor cost of $85 per work hour: It would take 2.5 work hours to do an NDI and 2 work hours to apply the white paint. It would cost $15 in materials for the paint for each helicopter. Based on these estimates, it would cost a total of $398 per helicopter and $72,038 for the fleet. If it is necessary to replace a spindle cuff assembly or a blade cuff assembly, Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed 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); 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 proposed 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. PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: E:\FR\FM\20JNP1.SGM 20JNP1 37162 Federal Register / Vol. 78, No. 119 / Thursday, June 20, 2013 / Proposed Rules 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Sikorsky Aircraft Corporation: Docket No. FAA–2013–0514; Directorate Identifier 2012–SW–068–AD. (a) Applicability This AD applies to Model S–76A, S–76B, and S–76C helicopters with a serial number up to and including 760822 and with a spindle cuff assembly, part number (P/N) 76102–08001–043, –045 or –046, or a blade fold cuff assembly, P/N 76150–09601–041, installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a crack in a spindle cuff assembly or blade fold cuff assembly. This condition could result in failure of a spindle cuff assembly or blade fold cuff assembly, loss of a rotor blade, and subsequent loss of control of the helicopter. mstockstill on DSK4VPTVN1PROD with PROPOSALS (c) 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. (d) Required Actions Within 150 hours time-in-service (TIS): (1) For each spindle cuff assembly or blade cuff assembly with 1,900 or more hours TIS, conduct a nondestructive (NDI) inspection by following the Accomplishment Instructions, paragraph 3.B., of Sikorsky S–76 Alert Service Bulletin ASB 76–65–67A, Revision A, dated July 18, 2012 (ASB), except this AD does not require you to contact Sikorsky Aircraft Corporation. This inspection must be done by a level 2 or higher technician with National Aerospace Standard 410 or equivalent certification. (2) For each spindle cuff assembly or blade cuff assembly with less than 1,900 hours TIS, visually inspect the area indicated in Figure 4 of the ASB as ‘‘white paint application area’’ for a crack by using a 5x or higher power magnifying glass. (3) If there is a crack, before further flight, replace the cracked part. (4) If there is no crack, apply white paint by following the Accomplishment Instructions, paragraph 3.D., of the ASB. (5) Do not install an affected spindle cuff assembly or blade fold cuff assembly on any helicopter unless it has been inspected in accordance with paragraphs (d)(1) through (d)(4) of this AD. (e) Special Flight Permit Special flight permits will not be issued. (f) Alternative Methods of Compliance (AMOC) (1) The Manager, Boston Aircraft Certification Office, FAA, may approve VerDate Mar<15>2010 16:29 Jun 19, 2013 Jkt 229001 AMOCs for this AD. Send your proposal to: Nicholas Faust, Aviation Safety Engineer, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, Massachusetts 01803; telephone (781) 238– 7763; email nicholas.faust@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) Additional Information For service information identified in this AD, contact Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical Support, mailstop s581a, 6900 Main Street, Stratford, CT 06614; telephone (800) 562– 4409; email tsslibrary@sikorsky.com; or at http://www.sikorsky.com. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. (h) Subject Joint Aircraft Service Component (JASC) Code: 6220 Main Rotor Head. Issued in Fort Worth, Texas, on June 12, 2013. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2013–14699 Filed 6–19–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0518; Directorate Identifier 2009–SW–021–AD] RIN 2120–AA64 Airworthiness Directives; Agusta S.p.A. (Type Certificate Currently Held by AgustaWestland S.p.A) (Agusta) Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for Agusta Model A109A, A109AII, and A109C helicopters with a certain third stage turbine wheel installed. This proposed AD would require installing a placard on the instrument panel and revising the limitations section of the rotorcraft flight manual (RFM). This proposed AD is prompted by several incidents of third stage engine turbine wheel failures, which were caused by SUMMARY: PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 excessive vibrations at certain engine speeds during steady-state operations. The proposed actions are intended to alert pilots to avoid certain engine speeds during steady-state operations, prevent failure of the third stage engine turbine, engine power loss, and subsequent loss of control of the helicopter. We must receive comments on this proposed AD by August 19, 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. DATES: 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 proposed 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 service information identified in this proposed AD, contact Agusta Westland, Customer Support & Services, Via Per Tornavento 15, 21019 Somma Lombardo (VA) Italy, ATTN: Giovanni Cecchelli; telephone 39–0331–711133; fax 39 0331 711180; or at http:// www.agustawestland.com/technicalbullettins. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. FOR FURTHER INFORMATION CONTACT: Chinh Vuong, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email chinh.vuong@faa.gov. SUPPLEMENTARY INFORMATION: E:\FR\FM\20JNP1.SGM 20JNP1

Agencies

[Federal Register Volume 78, Number 119 (Thursday, June 20, 2013)]
[Proposed Rules]
[Pages 37160-37162]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-14699]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0514; Directorate Identifier 2012-SW-068-AD]
RIN 2120-AA64


Airworthiness Directives; Sikorsky Aircraft Corporation 
(Sikorsky) Model Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
Sikorsky Model S-76A, B, and C helicopters to require certain 
inspections of each spindle cuff assembly or blade fold cuff assembly 
for a crack. If there is a crack, this proposed AD would require 
replacing the cracked part. If there is no crack, this AD would require 
applying white paint to the inspection area to enhance the existing 
inspection procedure. This proposed AD is prompted by the discovery of 
cracks in the spindle cuffs. The proposed actions are intended to 
prevent failure of a spindle cuff assembly or blade fold cuff assembly, 
loss of a rotor blade, and subsequent loss of control of the 
helicopter.

DATES: We must receive comments on this proposed AD by August 19, 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 proposed 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 service information identified in this proposed AD, contact 
Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical 
Support, mailstop s581a, 6900 Main Street, Stratford, CT 06614; 
telephone (800) 562-4409; email tsslibrary@sikorsky.com; or at http://www.sikorsky.com; http://www.eurocopter.com/techpub. You may review the 
referenced service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas 76137.

FOR FURTHER INFORMATION CONTACT: Nicholas Faust, Aviation Safety 
Engineer, Boston Aircraft Certification Office, Engine & Propeller 
Directorate, 12 New England Executive Park, Burlington, Massachusetts 
01803; telephone (781) 238-7763; email nicholas.faust@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    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 might 
result from adopting the proposals in this document. The most helpful 
comments reference a specific portion of the proposal, 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

[[Page 37161]]

filed electronically, commenters should submit 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 proposed rulemaking. Before acting on this proposal, we 
will consider all comments we receive on or before the closing date for 
comments. We will consider comments filed after the comment period has 
closed if it is possible to do so without incurring expense or delay. 
We may change this proposal in light of the comments we receive.

Discussion

    We propose to adopt a new AD for Sikorsky Model S-76A, B, and C 
helicopters. This proposed AD would require, depending on the hours 
time-in-service (TIS) of each part, either a one-time nondestructive 
inspection (NDI) or a visual inspection of each spindle cuff assembly 
or blade fold cuff assembly for a crack. If there is a crack, this 
proposed AD would require replacing the cracked part. If there is no 
crack, this proposed AD would require applying white paint to a portion 
of each spindle cuff assembly or blade fold cuff assembly lower cuff 
plate to enhance the existing inspection procedure. This proposed AD is 
prompted by the discovery of five cracked spindle cuffs found during 
aircraft overhaul. The proposed actions are intended to prevent failure 
of a spindle cuff assembly or blade fold cuff assembly, loss of a rotor 
blade, and subsequent loss of control of the helicopter.

FAA's Determination

    We are proposing this AD because we evaluated all known relevant 
information and determined that an unsafe condition exists and is 
likely to exist or develop on other helicopters of these same type 
designs.

Related Service Information

    Sikorsky issued S-76 Alert Service Bulletin ASB 76-65-67A, Revision 
A, dated July 18, 2012 (ASB), which specifies performing an NDI of the 
upper and lower cuff plate on each spindle cuff assembly or blade fold 
cuff assembly for a crack, either by eddy current, fluorescent 
penetrant, or ultrasonic inspection. If a crack indication is detected 
and not verified, the ASB specifies performing a different NDI to 
verify a crack. If there is a crack, the ASB specifies removing the 
spindle cuff assembly or blade fold cuff assembly from service. If a 
crack cannot be verified, the ASB specifies contacting Sikorsky for 
further instruction. Finally, if no crack is found, the ASB specifies 
applying white paint to a portion of the spindle cuff assembly or blade 
fold cuff assembly lower cuff plate to enhance the existing inspection 
procedure.

Proposed AD Requirements

    This proposed AD would require within 150 hours TIS:
     For each spindle cuff assembly or blade cuff assembly with 
1,900 or more hours TIS, conducting an NDI by a qualified inspector by 
following specified portions of the ASB.
     For each spindle cuff assembly or blade cuff assembly with 
less than 1,900 hours TIS, visually inspecting each white paint 
application area for a crack by using a 5x or higher power magnifying 
glass.
     If there is a crack, before further flight, replacing each 
cracked spindle cuff assembly or cracked blade fold cuff assembly with 
an airworthy assembly.
     If there is no crack, applying white paint by following 
specified portions of the ASB.
    This proposed AD also prohibits installing an affected spindle cuff 
assembly or blade cuff fold assembly on any helicopter unless it has 
been inspected in accordance with the requirements of this AD.

Differences Between This Proposed AD and the Service Information

    The ASB specifies contacting the manufacturer if suspect cracks are 
not confirmed in the spindle cuff assembly or blade fold cuff assembly; 
this proposed AD would not require contacting the manufacturer. This 
proposed AD applies to spindle cuff assembly, part number (P/N) 76102-
08001-043, which was inadvertently omitted in the ASB. The manufacturer 
has stated that they will issue an ASB in the future that will also 
apply to this spindle cuff assembly. The ASB applies to spare parts; 
this proposed AD does not.

Costs of Compliance

    We estimate that this proposed AD would affect 181 helicopters of 
U.S. Registry.
    We estimate that operators may incur the following costs in order 
to comply with this AD, based on an average labor cost of $85 per work 
hour: It would take 2.5 work hours to do an NDI and 2 work hours to 
apply the white paint. It would cost $15 in materials for the paint for 
each helicopter. Based on these estimates, it would cost a total of 
$398 per helicopter and $72,038 for the fleet.
    If it is necessary to replace a spindle cuff assembly or a blade 
cuff assembly, it would take 2.5 work hours and an estimated parts cost 
of $54,000, for a total cost of $54,212 for each helicopter.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 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);
    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 proposed 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

[[Page 37162]]

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):

Sikorsky Aircraft Corporation: Docket No. FAA-2013-0514; Directorate 
Identifier 2012-SW-068-AD.

(a) Applicability

    This AD applies to Model S-76A, S-76B, and S-76C helicopters 
with a serial number up to and including 760822 and with a spindle 
cuff assembly, part number (P/N) 76102-08001-043, -045 or -046, or a 
blade fold cuff assembly, P/N 76150-09601-041, installed, 
certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in a spindle 
cuff assembly or blade fold cuff assembly. This condition could 
result in failure of a spindle cuff assembly or blade fold cuff 
assembly, loss of a rotor blade, and subsequent loss of control of 
the helicopter.

(c) 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.

(d) Required Actions

    Within 150 hours time-in-service (TIS):
    (1) For each spindle cuff assembly or blade cuff assembly with 
1,900 or more hours TIS, conduct a nondestructive (NDI) inspection 
by following the Accomplishment Instructions, paragraph 3.B., of 
Sikorsky S-76 Alert Service Bulletin ASB 76-65-67A, Revision A, 
dated July 18, 2012 (ASB), except this AD does not require you to 
contact Sikorsky Aircraft Corporation. This inspection must be done 
by a level 2 or higher technician with National Aerospace Standard 
410 or equivalent certification.
    (2) For each spindle cuff assembly or blade cuff assembly with 
less than 1,900 hours TIS, visually inspect the area indicated in 
Figure 4 of the ASB as ``white paint application area'' for a crack 
by using a 5x or higher power magnifying glass.
    (3) If there is a crack, before further flight, replace the 
cracked part.
    (4) If there is no crack, apply white paint by following the 
Accomplishment Instructions, paragraph 3.D., of the ASB.
    (5) Do not install an affected spindle cuff assembly or blade 
fold cuff assembly on any helicopter unless it has been inspected in 
accordance with paragraphs (d)(1) through (d)(4) of this AD.

(e) Special Flight Permit

    Special flight permits will not be issued.

(f) Alternative Methods of Compliance (AMOC)

    (1) The Manager, Boston Aircraft Certification Office, FAA, may 
approve AMOCs for this AD. Send your proposal to: Nicholas Faust, 
Aviation Safety Engineer, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, Massachusetts 01803; telephone 
(781) 238-7763; email nicholas.faust@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) Additional Information

    For service information identified in this AD, contact Sikorsky 
Aircraft Corporation, Attn: Manager, Commercial Technical Support, 
mailstop s581a, 6900 Main Street, Stratford, CT 06614; telephone 
(800) 562-4409; email tsslibrary@sikorsky.com; or at http://www.sikorsky.com. You may review the referenced service information 
at the FAA, Office of the Regional Counsel, Southwest Region, 2601 
Meacham Blvd., Room 663, Fort Worth, Texas 76137.

 (h) Subject

    Joint Aircraft Service Component (JASC) Code: 6220 Main Rotor 
Head.

    Issued in Fort Worth, Texas, on June 12, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-14699 Filed 6-19-13; 8:45 am]
BILLING CODE 4910-13-P