Document ID: FAA-2012-1018-0001
Agency: faa
Document Type: Rule
Title: Airworthiness DIrectives: Eurocopter France Helicopters
Posted Date: 2012-09-25T04:00Z

[Federal Register Volume 77, Number 186 (Tuesday, September 25, 2012)]
[Rules and Regulations]
[Pages 58925-58930]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-23448]

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  Federal Register / Vol. 77, No. 186 / Tuesday, September 25, 2012 / 
Rules and Regulations  

[[Page 58925]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1018; Directorate Identifier 2011-SW-052-AD; 
Amendment 39-17204; AD 2012-19-09]
RIN 2120-AA64

Airworthiness Directives; Eurocopter France Helicopters

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for 
Eurocopter France (Eurocopter) Model EC 155B, EC155B1, SA-365N1, AS-
365N2 and AS 365 N3 helicopters to require visually inspecting the tail 
rotor hub (TRH) for a crack and removing the TRH if a crack exists. 
This AD is prompted by reports of cracks on two TRHs. These actions are 
intended to prevent the tail rotor from jamming, which could lead to 
reduced or loss of control of the helicopter.

DATES: This AD becomes effective October 10, 2012.
    We must receive comments on this AD by November 26, 2012.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Examining the AD Docket: You may examine the AD docket on the 
Internet at http://www.regulations.gov or in person at the Docket 
Operations Office between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The AD docket contains this AD, the economic 
evaluation, any comments received, and other information. The street 
address for the Docket Operations Office (telephone 800- 647-5527) is 
in the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.
    For service information identified in this AD, contact American 
Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 75052; 
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at 
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: Robert Grant, Aviation Safety 
Engineer, Standards Staff, Rotorcraft Directorate, FAA, 2601 Meacham 
Blvd., Fort Worth, Texas 76137; telephone 817-222-5328; email 
robert.grant@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

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

Discussion

    We are adopting a new AD for Eurocopter EC 155B, EC155B1, SA-365N1, 
AS-365N2 and AS 365 N3 helicopters. Eurocopter reported that a 
technician found cracks on the TRH during an inspection of a Model AS-
365 helicopter equipped with a 10-blade TRH. This AD requires 
repetitive visual inspections of the TRH for a crack. Eurocopter 
initially required a visual inspection of the TRH every 110 hours, but 
reduced that requirement to 55 flight hours after cracks were found on 
a second hub. Eurocopter is investigating the cause of the cracks.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
No. 2011-0144, dated July 26, 2011, to correct this unsafe condition 
for Eurocopter Model EC 155B, EC155B1, SA-365N1, AS-365N2 and AS 365 N3 
helicopters. EASA states that if a TRH crack is not detected and 
corrected, the tail rotor could jam, leading to a reduction or loss of 
control of the helicopter. Pending further investigation, the EASA AD 
requires repetitive inspections of the TRH every 55 flight hours. EASA 
considers the actions in its AD to be interim measures and expects 
further AD actions will follow.

FAA's Determination

    These helicopters have been approved by the aviation authority of 
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 issuing this AD because we evaluated all 
information provided by EASA and determined the unsafe condition exists 
and is likely to exist or develop on other helicopters of these same 
type designs.

Related Service Information

    Following the report of cracks found on the TRH of a Model AS-365 
helicopter, Eurocopter issued Alert Service Bulletin (ASB) No. EC 155-
05A021, Revision 0, dated April 11, 2011, for Model EC 155B and EC155B1 
helicopters, and ASB No. AS365-

[[Page 58926]]

05.00.60, Revision 0, dated April 11, 2011, for Model SA-365N1, AS-
365N2 and AS 365 N3 and some military helicopters. After a second 
report of TRH cracks, the ASBs were revised, dated July 20, 2011, to 
mandate and reduce the repetitive inspection interval from 110 flight 
hours to 55 flight hours.
    The ASBs call for visually inspecting the TRH for cracks and, if 
cracks are found, removing the TRH. EASA classified these ASBs as 
mandatory and issued AD No. 2011-0144 to ensure the continued 
airworthiness of these helicopters.

AD Requirements

    This AD requires visually inspecting the TRH for a crack within 55 
hours time in service (TIS) and, if a crack exists, removing the TRH 
from service. This inspection must be repeated at intervals not to 
exceed 55 hours TIS.

Interim Action

    We consider this AD to be an interim action because Eurocopter is 
investigating the cause of TRH cracks. If a final action is later 
identified, we might consider additional rulemaking.

Costs of Compliance

    We estimate that this AD will affect 34 helicopters of U.S. 
Registry and that labor costs will average $85 a work-hour. We expect 
that it will take 1 work-hour to visually inspect the TRH for a crack, 
and that helicopters will average 5 inspections per year. Thus, we 
estimate a total annual cost of $425 per helicopter, and $14,450 for 
the U.S. operator fleet.

FAA's Justification and Determination of the Effective Date

    Providing an opportunity for public comments prior to adopting 
these AD requirements would delay implementing the safety actions 
needed to correct this known unsafe condition. Therefore, we find that 
the risk to the flying public justifies waiving notice and comment 
prior to the adoption of this rule, because the required corrective 
actions must be accomplished within 55 hours TIS, a very short time 
period based on the average utilization rate of the highest usage 
helicopter model.
    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we determined that notice and opportunity for 
public comment before issuing this AD are impractical and contrary to 
the public interest and that good cause exists for making this 
amendment effective in less than 30 days.

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2012-19-09 Eurocopter Helicopters: Amendment 39-17204; Docket No. 
FAA-2012-1018; Directorate Identifier 2011-SW-052-AD.

(a) Applicability

    This AD applies to Eurocopter Model EC 155B, EC155B1, SA-365N1, 
AS-365N2 and AS 365 N3 helicopters, with a tail rotor hub (TRH) part 
number 365A33351100, 365A33351101, or 365A33351102 installed, 
certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in the TRH that 
could lead to a tail rotor jam, and subsequent reduced or loss of 
control of the helicopter.

(c) Effective Date

    This AD becomes effective October 10, 2012.

(d) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time.

(e) Required Actions

    (1) Within 55 hours time-in-service (TIS), and thereafter at 
intervals not to exceed 55 hours TIS, using a light, visually 
inspect the TRH for a crack in the entire area shown as Area C of 
the TRH (a) in Figure 1 to paragraph (e)(1) of this AD. The 
inspection area is on the tail gearbox (TGB) side of the TRH. The 
TGB is shown as (c) in Figures 2 and 3 to paragraph (e)(1) of this 
AD. You must pay particular attention to the area around the screws, 
shown as (e) in Figure 3 to paragraph (e)(1) of this AD, and the TRH 
between the lower part of the TGB and its fairing, shown as (d) in 
Figures 2 and 3 to paragraph (e)(1) of this AD, using details D and 
E of Figure 3 to paragraph (e)(1) of this AD. You must turn the tail 
rotor by hand to inspect the entire Area C.
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    (2) If there is a crack on the TRH, remove the TRH from service.

(f) Special Flight Permits

    No special flight permits will be permitted.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Robert Grant, Aviation Safety 
Engineer, Standards Staff, Rotorcraft Directorate, FAA, 2601 Meacham 
Blvd., Fort Worth, Texas 76137; telephone 817-222-5328; email 
robert.grant@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

[[Page 58930]]

certificate holding district office, before operating any aircraft 
complying with this AD through an AMOC.

(h) Additional Information

    (1) Eurocopter Alert Service Bulletin (ASB) No. AS365-05.00.60, 
Revision 1, dated July 20, 2011, and Eurocopter ASB No. EC 155-
05A021, Revision 1, dated July 20, 2011, which are not incorporated 
by reference, contain additional information about the subject of 
this AD. For service information identified in this AD, contact 
American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, 
TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-
3775; or at http://www.eurocopter.com/techpub. You may review a copy 
of the 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 European Aviation 
Safety Agency (EASA) AD No. 2011-0144, dated July 26, 2011.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6420, Tail Rotor 
Head.

    Issued in Fort Worth, Texas, on September 14, 2012.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012-23448 Filed 9-24-12; 8:45 am]
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