Airworthiness Directives; Eurocopter France Helicopters, 44509-44511 [2012-18454]

Download as PDF Federal Register / Vol. 77, No. 146 / Monday, July 30, 2012 / Proposed Rules PART 741—REQUIREMENTS FOR INSURANCE 1. The authority citation for part 741 continues to read as follows: Authority: 12 U.S.C. 1757, 1766(a), 1781– 1790, and 1790d; 31 U.S.C. 3717. 2. Amend part 741 by adding a new § 741.12 to read as follows: * * * * * srobinson on DSK4SPTVN1PROD with PROPOSALS § 741.12 Access to Emergency Liquidity. (a) Any credit union insured pursuant to Title II of the Act which has assets of less than $10 million must maintain a basic written policy that provides a credit union board-approved framework for managing liquidity and a list of contingent liquidity sources that can be employed under adverse circumstances. (b) Any credit union which is insured pursuant to Title II of the Act which has assets of $10 million or more must establish and document a contingency funding plan (CFP) that meets the requirements of paragraph (d). (c) In addition to the requirement specified in paragraph (b) to establish and maintain a CFP, any credit union which is insured pursuant to Title II of the Act and which has assets of $100 million or more must establish and document access to at least one contingent federal liquidity source for use in times of financial emergency and distressed economic circumstances. Credit unions must conduct advance planning and periodic testing to ensure that contingent funding sources are readily available when needed. A credit union may demonstrate access to a contingent federal liquidity source by: (1) Maintaining Regular membership in the Central Liquidity Facility (Facility), as described in part 725 of this chapter; (2) Maintaining membership in the Facility through an Agent, as described in part 725 of this chapter; or (3) Establishing borrowing access at the Federal Reserve Discount Window. (d) CFP. A credit union must have a written CFP commensurate with its complexity, risk profile, and scope of operations that sets out strategies for addressing liquidity shortfalls in emergency situations. The CFP may be a separate policy or may be incorporated into an existing policy such as an asset/ liability policy, a funds management policy, or a business continuity policy. The CFP must address, at a minimum, the following: (1) The sufficiency of the institution’s liquidity sources to meet normal operating requirements as well as contingent events; (2) The identification of contingent liquidity sources; VerDate Mar<15>2010 16:37 Jul 27, 2012 Jkt 226001 (3) Policies to manage a range of stress environments, identification of some possible stress events, and identification of likely liquidity responses to such events; (4) Lines of responsibility within the institution to respond to liquidity events; (5) Management processes that include clear implementation and escalation procedures for liquidity events; and (6) The frequency that the institution will test and update the plan. (e) A FICU is subject to the requirements of paragraphs (b) or (c) of this section when two consecutive Call Reports show its assets to be at least $10 million or $100 million, respectively. A FICU then has 120 days from the effective date of that second Call Report to meet the new requirements. [FR Doc. 2012–18565 Filed 7–27–12; 8:45 am] BILLING CODE 7535–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0795; Directorate Identifier 2008–SW–53–AD] RIN 2120–AA64 Airworthiness Directives; Eurocopter France Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS332C, L, and L1 helicopters to require a one-time inspection of the main rotor head (MRH) swash-plate upper bearing (bearing) for a nonsmooth point (friction point). This proposed AD is prompted by a report of the premature deterioration of the MRH bearing of the rotating star installed on a Model AS332L1 helicopter. The proposed actions are intended to detect deterioration of the MRH bearing and to prevent overloading the scissor links which drive the main rotor system, failure of the scissors links, and subsequent loss of control of the helicopter. SUMMARY: We must receive comments on this proposed AD by September 28, 2012. DATES: You may send comments by any of the following methods: ADDRESSES: PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 44509 • Federal eRulemaking Docket: Go to https://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 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 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 American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053–4005; telephone (800) 232–0323; or at https:// www.eurocopter.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. FOR FURTHER INFORMATION CONTACT: Gary Roach, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email gary.b.roach@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 filed electronically, commenters should submit only one time. We will file in the docket all comments that we receive, as well as a E:\FR\FM\30JYP1.SGM 30JYP1 44510 Federal Register / Vol. 77, No. 146 / Monday, July 30, 2012 / Proposed Rules 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 The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Emergency AD No. 2008–0172–E, dated September 9, 2008 (EAD No. 2008–0172–E), for the Eurocopter Model AS 332 C, C1, L, and L1 helicopters, with an MRH, part number (P/N) 332A31–0001–05 or P/N 332A31–0001–06, having a serial number (S/N) of M172, M216, M261, M308, M547, M677, M811, or M936, and having ‘‘logged less than 275 flight hours since the last overhaul or repair.’’ EASA states that Eurocopter received a report of deterioration of an MRH bearing on an MRH that was installed on an AS 332 L1 helicopter. The AS 332 L1 helicopter had logged 72 flight hours since the last overhaul. The EASA states that there was an onset of vibrations in flight and these vibrations were due to premature deterioration of the upper bearing of the MRH swash-plate. They state that this condition, if not corrected, ‘‘could lead to failure of the scissors links and consequently to the control loss of the helicopter.’’ srobinson on DSK4SPTVN1PROD with PROPOSALS FAA’s Determination These helicopters have been approved by the aviation authority of the France and are approved for operation in the United States. Pursuant to our bilateral agreement with France, EASA, its technical representative, has notified us of the unsafe condition described in the EASA AD. We are proposing this AD because we evaluated all information provided by EASA and determined that an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Related Service Information Eurocopter has issued one Emergency Alert Service Bulletin (EASB) with two different numbers, both Revision 0, and both dated September 8, 2008: EASB No. 62.00.73 for Model AS332C, L, and L1 helicopters and non-FAA type certificated Model C1 helicopters; and EASB No. 62.00.30 for non-FAA type certificated Model 532 UC, AC, UL, AL, SC, and UE military helicopters. EASB VerDate Mar<15>2010 16:37 Jul 27, 2012 Jkt 226001 No. 62.00.73 specifies checking for the absence of a friction point in the MRH bearing. If there is no friction point, EASB No. 62.00.73 specifies checking the condition of the grease in the swashplate assembly by lubricating the swashplate, rotating it by hand, and determining if the expelled grease contains traces of metal particles. If the expelled grease does not contain traces of metal particles, EASB No. 62.00.73 specifies checking the swash-plate ‘‘rotation torque’’ using a spring scale. If the rotation torque is less than 5.5 kg, EASB No. 62.00.73 specifies checking the bearing for vertical play. If there is a friction point, the expelled grease contains traces of metal particles, the rotation torque is equal to or greater than 5.5 kg, or there is vertical play in the bearing, EASB No. 62.00.73 specifies removing the MRH and sending it to an approved repair station. EASA classified this EASB as mandatory and issued EAD No. 2008–0172–E to ensure the continued airworthiness of these helicopters. Proposed AD Requirements This proposed AD would require, within 5 hours time-in-service (TIS), for the specified model helicopters having less than 275 hours TIS since the last MRH overhaul, the following: • Inspect the MRH bearing for a nonsmooth point (friction point) by rotating the MRH swash-plate and: Æ If there is a friction point in the bearing, before further flight, replace the MRH with an airworthy MRH. Æ If there is not a friction point in the bearing, lubricate the MRH swash-plate and rotate it until grease is expelled; inspect the expelled grease for metal particles. • If there is a metal particle in the grease, before further flight, replace the MRH with an airworthy MRH. • If there is not a metal particle in the grease, measure the force required to rotate the MRH swash-plate using a spring scale attached to the pitch change rod attachment yokes. Æ If the force to rotate the MRH swash-plate is equal to or greater than 5.5 kg, before further flight, replace the MRH with an airworthy MRH. Æ If the force to rotate the MRH swash-plate is less than 5.5 kg, inspect the MRH swash-plate assembly for vertical play in the bearing. If there is vertical play in the bearing, before further flight, replace the MRH with an airworthy MRH. • Before installing an MRH, P/N 332A31–0001–05 or P/N 332A31–001– 06, with S/N M172, M216, M261, M308, M547, M561, M677, M811, M859, M935, M936, M938, or M942 on any PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 helicopter, inspect the MRH in accordance with the requirements of this AD. Differences Between This Proposed AD and the EASA AD The EASA Emergency AD includes Model AS332C1 helicopters. This proposed AD does not include this model helicopter since it is not type certificated in the U.S. The EASA AD does not include S/Ns M561, M859, M935, M938, and M942, whereas this proposed AD does include those S/Ns. The EASA Emergency AD requires operators to comply with the requirements no later than the ‘‘next last flight of the day.’’ Our proposed AD would require the actions to be accomplished within 5 hours TIS. Also, the EASA Emergency AD is applicable to the specified helicopters having logged less than 275 flight hours since the last overhaul or repair, whereas our proposed AD would only be applicable to the specified helicopters having less than 275 hours TIS since the last overhaul of the MRH. Costs of Compliance We estimate that this proposed AD would affect 6 helicopters of U.S. registry. We estimate that operators may incur the following costs in order to comply with this AD. It would take approximately 1 work-hour per helicopter to accomplish the inspection of the MRH bearing for a friction point, inspection of the swash-plate grease for any metal particles, measurement of the swash-plate force to rotate, and inspection of the bearing for vertical play. It would take approximately 60 work-hours to replace the MRH. These proposed actions would be accomplished at an average labor rate of $85 per work-hour. We estimate the parts cost of replacing an MRH would be approximately $20,000. Based on these figures, we estimate the total cost of the proposed AD on U.S. operators to be $25,610, assuming that all affected helicopters are inspected and that one MRH in the fleet would need to be replaced. 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 E:\FR\FM\30JYP1.SGM 30JYP1 Federal Register / Vol. 77, No. 146 / Monday, July 30, 2012 / Proposed Rules 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: PART 39—AIRWORTHINESS DIRECTIVES srobinson on DSK4SPTVN1PROD with PROPOSALS 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): Eurocopter France (Eurocopter): Docket No. FAA–2012–0795; Directorate Identifier 2008–SW–53–AD. VerDate Mar<15>2010 16:37 Jul 27, 2012 Jkt 226001 (a) Applicability This AD applies to Eurocopter Model AS332C, L, and L1 helicopters with a main rotor head (MRH), part number (P/N) 332A31–0001–05 or P/N 332A31–0001–06, with a serial number (S/N) M172, M216, M261, M308, M547, M561, M677, M811, M859, M935, M936, M938, or M942 installed; having less than 275 hours time-inservice (TIS) since the last overhaul of the MRH; certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as deterioration of the MRH swash-plate upper bearing (bearing), which could result in overloading the scissor links which drive the main rotor system, failure of the scissors links, 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 5 hours TIS: (1) Inspect the MRH bearing for a nonsmooth point (friction point) by rotating the MRH swash-plate and: (i) If there is a friction point in the bearing, before further flight, replace the MRH with an airworthy MRH. (ii) If there is not a friction point in the bearing, lubricate the MRH swash-plate and rotate it until grease is expelled; inspect the expelled grease for metal particles. (A) If there is a metal particle in the grease, before further flight, replace the MRH with an airworthy MRH. (B) If there is not a metal particle in the grease, measure the force required to rotate the MRH swash-plate using a spring scale attached to the pitch change rod attachment yokes. (1) If the force to rotate the MRH swashplate is equal to or greater than 5.5 kg, before further flight, replace the MRH with an airworthy MRH. (2) If the force to rotate the MRH swashplate is less than 5.5 kg, inspect the MRH swash-plate assembly for vertical play in the bearing. If there is vertical play in the bearing, before further flight, replace the MRH with an airworthy MRH. (2) Before installing an MRH, P/N 332A31– 0001–05 or P/N 332A31–001–06, with S/N M172, M216, M261, M308, M547, M561, M677, M811, M859, M935, M936, M938, or M942 on any helicopter, inspect the MRH in accordance with paragraph (d)(1) of this AD. (e) Alternative Methods of Compliance (AMOC) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Gary Roach, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email gary.b.roach@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 44511 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. (f) Additional Information (1) Eurocopter Emergency Alert Service Bulletin, No. 62.00.73, Revision 0, dated September 8, 2008, which is not incorporated by reference, contains additional information about the subject of this AD. For this service information, contact American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053–4005; telephone (800) 232–0323; or at https://www.eurocopter.com. You may review this service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. (2) The subject of this AD is addressed in the European Aviation Safety Agency (France) Emergency AD No. 2008–0172–E, dated September 9, 2008. (g) Subject Joint Aircraft Service Component (JASC) Code: 6400,Tail Rotor System. Issued in Fort Worth, Texas, on July 20, 2012. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2012–18454 Filed 7–27–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0798; Directorate Identifier 2012–CE–023–AD] RIN 2120–AA64 Airworthiness Directives; Alpha Aviation Concept Limited Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of Proposed Rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for Alpha Aviation Concept Limited Model R2160 Airplanes. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as possible installation of non-conforming air filter elements that are not fitted with metallic mesh and could internally collapse resulting in SUMMARY: E:\FR\FM\30JYP1.SGM 30JYP1

Agencies

[Federal Register Volume 77, Number 146 (Monday, July 30, 2012)]
[Proposed Rules]
[Pages 44509-44511]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-18454]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0795; Directorate Identifier 2008-SW-53-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
Eurocopter France (Eurocopter) Model AS332C, L, and L1 helicopters to 
require a one-time inspection of the main rotor head (MRH) swash-plate 
upper bearing (bearing) for a non-smooth point (friction point). This 
proposed AD is prompted by a report of the premature deterioration of 
the MRH bearing of the rotating star installed on a Model AS332L1 
helicopter. The proposed actions are intended to detect deterioration 
of the MRH bearing and to prevent overloading the scissor links which 
drive the main rotor system, failure of the scissors links, and 
subsequent loss of control of the helicopter.

DATES: We must receive comments on this proposed AD by September 28, 
2012.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to https://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 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 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 
American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 
75053-4005; telephone (800) 232-0323; or at https://www.eurocopter.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.

FOR FURTHER INFORMATION CONTACT: Gary Roach, Aviation Safety Engineer, 
Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham 
Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email 
gary.b.roach@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 filed 
electronically, commenters should submit only one time.
    We will file in the docket all comments that we receive, as well as 
a

[[Page 44510]]

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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Emergency AD No. 2008-0172-E, dated September 9, 2008 (EAD No. 2008-
0172-E), for the Eurocopter Model AS 332 C, C1, L, and L1 helicopters, 
with an MRH, part number (P/N) 332A31-0001-05 or P/N 332A31-0001-06, 
having a serial number (S/N) of M172, M216, M261, M308, M547, M677, 
M811, or M936, and having ``logged less than 275 flight hours since the 
last overhaul or repair.'' EASA states that Eurocopter received a 
report of deterioration of an MRH bearing on an MRH that was installed 
on an AS 332 L1 helicopter. The AS 332 L1 helicopter had logged 72 
flight hours since the last overhaul. The EASA states that there was an 
onset of vibrations in flight and these vibrations were due to 
premature deterioration of the upper bearing of the MRH swash-plate. 
They state that this condition, if not corrected, ``could lead to 
failure of the scissors links and consequently to the control loss of 
the helicopter.''

FAA's Determination

    These helicopters have been approved by the aviation authority of 
the France and are approved for operation in the United States. 
Pursuant to our bilateral agreement with France, EASA, its technical 
representative, has notified us of the unsafe condition described in 
the EASA AD. We are proposing this AD because we evaluated all 
information provided by EASA and determined that an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Related Service Information

    Eurocopter has issued one Emergency Alert Service Bulletin (EASB) 
with two different numbers, both Revision 0, and both dated September 
8, 2008: EASB No. 62.00.73 for Model AS332C, L, and L1 helicopters and 
non-FAA type certificated Model C1 helicopters; and EASB No. 62.00.30 
for non-FAA type certificated Model 532 UC, AC, UL, AL, SC, and UE 
military helicopters. EASB No. 62.00.73 specifies checking for the 
absence of a friction point in the MRH bearing. If there is no friction 
point, EASB No. 62.00.73 specifies checking the condition of the grease 
in the swash-plate assembly by lubricating the swash-plate, rotating it 
by hand, and determining if the expelled grease contains traces of 
metal particles. If the expelled grease does not contain traces of 
metal particles, EASB No. 62.00.73 specifies checking the swash-plate 
``rotation torque'' using a spring scale. If the rotation torque is 
less than 5.5 kg, EASB No. 62.00.73 specifies checking the bearing for 
vertical play. If there is a friction point, the expelled grease 
contains traces of metal particles, the rotation torque is equal to or 
greater than 5.5 kg, or there is vertical play in the bearing, EASB No. 
62.00.73 specifies removing the MRH and sending it to an approved 
repair station. EASA classified this EASB as mandatory and issued EAD 
No. 2008-0172-E to ensure the continued airworthiness of these 
helicopters.

Proposed AD Requirements

    This proposed AD would require, within 5 hours time-in-service 
(TIS), for the specified model helicopters having less than 275 hours 
TIS since the last MRH overhaul, the following:
     Inspect the MRH bearing for a non-smooth point (friction 
point) by rotating the MRH swash-plate and:
    [cir] If there is a friction point in the bearing, before further 
flight, replace the MRH with an airworthy MRH.
    [cir] If there is not a friction point in the bearing, lubricate 
the MRH swash-plate and rotate it until grease is expelled; inspect the 
expelled grease for metal particles.
     If there is a metal particle in the grease, before further 
flight, replace the MRH with an airworthy MRH.
     If there is not a metal particle in the grease, measure 
the force required to rotate the MRH swash-plate using a spring scale 
attached to the pitch change rod attachment yokes.
    [cir] If the force to rotate the MRH swash-plate is equal to or 
greater than 5.5 kg, before further flight, replace the MRH with an 
airworthy MRH.
    [cir] If the force to rotate the MRH swash-plate is less than 5.5 
kg, inspect the MRH swash-plate assembly for vertical play in the 
bearing. If there is vertical play in the bearing, before further 
flight, replace the MRH with an airworthy MRH.
     Before installing an MRH, P/N 332A31-0001-05 or P/N 
332A31-001-06, with S/N M172, M216, M261, M308, M547, M561, M677, M811, 
M859, M935, M936, M938, or M942 on any helicopter, inspect the MRH in 
accordance with the requirements of this AD.

Differences Between This Proposed AD and the EASA AD

    The EASA Emergency AD includes Model AS332C1 helicopters. This 
proposed AD does not include this model helicopter since it is not type 
certificated in the U.S. The EASA AD does not include S/Ns M561, M859, 
M935, M938, and M942, whereas this proposed AD does include those S/Ns. 
The EASA Emergency AD requires operators to comply with the 
requirements no later than the ``next last flight of the day.'' Our 
proposed AD would require the actions to be accomplished within 5 hours 
TIS. Also, the EASA Emergency AD is applicable to the specified 
helicopters having logged less than 275 flight hours since the last 
overhaul or repair, whereas our proposed AD would only be applicable to 
the specified helicopters having less than 275 hours TIS since the last 
overhaul of the MRH.

Costs of Compliance

    We estimate that this proposed AD would affect 6 helicopters of 
U.S. registry. We estimate that operators may incur the following costs 
in order to comply with this AD. It would take approximately 1 work-
hour per helicopter to accomplish the inspection of the MRH bearing for 
a friction point, inspection of the swash-plate grease for any metal 
particles, measurement of the swash-plate force to rotate, and 
inspection of the bearing for vertical play. It would take 
approximately 60 work-hours to replace the MRH. These proposed actions 
would be accomplished at an average labor rate of $85 per work-hour. We 
estimate the parts cost of replacing an MRH would be approximately 
$20,000. Based on these figures, we estimate the total cost of the 
proposed AD on U.S. operators to be $25,610, assuming that all affected 
helicopters are inspected and that one MRH in the fleet would need to 
be replaced.

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

[[Page 44511]]

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:

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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

Eurocopter France (Eurocopter): Docket No. FAA-2012-0795; 
Directorate Identifier 2008-SW-53-AD.

(a) Applicability

    This AD applies to Eurocopter Model AS332C, L, and L1 
helicopters with a main rotor head (MRH), part number (P/N) 332A31-
0001-05 or P/N 332A31-0001-06, with a serial number (S/N) M172, 
M216, M261, M308, M547, M561, M677, M811, M859, M935, M936, M938, or 
M942 installed; having less than 275 hours time-in-service (TIS) 
since the last overhaul of the MRH; certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as deterioration of the MRH 
swash-plate upper bearing (bearing), which could result in 
overloading the scissor links which drive the main rotor system, 
failure of the scissors links, 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 5 hours TIS:
    (1) Inspect the MRH bearing for a non-smooth point (friction 
point) by rotating the MRH swash-plate and:
    (i) If there is a friction point in the bearing, before further 
flight, replace the MRH with an airworthy MRH.
    (ii) If there is not a friction point in the bearing, lubricate 
the MRH swash-plate and rotate it until grease is expelled; inspect 
the expelled grease for metal particles.
    (A) If there is a metal particle in the grease, before further 
flight, replace the MRH with an airworthy MRH.
    (B) If there is not a metal particle in the grease, measure the 
force required to rotate the MRH swash-plate using a spring scale 
attached to the pitch change rod attachment yokes.
    (1) If the force to rotate the MRH swash-plate is equal to or 
greater than 5.5 kg, before further flight, replace the MRH with an 
airworthy MRH.
    (2) If the force to rotate the MRH swash-plate is less than 5.5 
kg, inspect the MRH swash-plate assembly for vertical play in the 
bearing. If there is vertical play in the bearing, before further 
flight, replace the MRH with an airworthy MRH.
    (2) Before installing an MRH, P/N 332A31-0001-05 or P/N 332A31-
001-06, with S/N M172, M216, M261, M308, M547, M561, M677, M811, 
M859, M935, M936, M938, or M942 on any helicopter, inspect the MRH 
in accordance with paragraph (d)(1) of this AD.

(e) Alternative Methods of Compliance (AMOC)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Gary Roach, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-
5110; email gary.b.roach@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.

(f) Additional Information

    (1) Eurocopter Emergency Alert Service Bulletin, No. 62.00.73, 
Revision 0, dated September 8, 2008, which is not incorporated by 
reference, contains additional information about the subject of this 
AD. For this service information, contact American Eurocopter 
Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005; 
telephone (800) 232-0323; or at https://www.eurocopter.com. You may 
review this service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas 76137.
    (2) The subject of this AD is addressed in the European Aviation 
Safety Agency (France) Emergency AD No. 2008-0172-E, dated September 
9, 2008.

(g) Subject

    Joint Aircraft Service Component (JASC) Code: 6400,Tail Rotor 
System.


    Issued in Fort Worth, Texas, on July 20, 2012.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012-18454 Filed 7-27-12; 8:45 am]
BILLING CODE 4910-13-P
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