Airworthiness Directives; Eurocopter France (ECF) Model AS350B, B1, B2, B3, BA, and D; and AS355E, F, F1, F2, and N Helicopters

[Federal Register Volume 77, Number 15 (Tuesday, January 24, 2012)]
[Rules and Regulations]
[Pages 3380-3382]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-365]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0923; Directorate Identifier 2009-SW-20-AD; 
Amendment 39-16794; AD 2011-18-12]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France (ECF) Model AS350B, 
B1, B2, B3, BA, and D; and AS355E, F, F1, F2, and N Helicopters

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

ACTION: Final rule; request for comments.

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SUMMARY: We are superseding an existing airworthiness directive (AD) 
for the specified ECF model helicopters. This AD results from a 
mandatory continuing airworthiness information (MCAI) AD issued by the 
European Aviation Safety Agency (EASA), which is the Technical Agent 
for the Member States of the European Union. The MCAI AD states that 
some cracks have been discovered in the spar of the upper fin on Model 
AS355N helicopters. Due to the fin design similarity between AS350 and 
AS355 helicopters, this AD action applies to both helicopter models. 
Modifying the upper and lower fin attachment is intended to prevent 
failure of a spar, loss of a fin, a separated fin hitting a rotor, and 
subsequent loss of control of a helicopter.

DATES: This AD becomes effective on February 8, 2012.
    The incorporation by reference of certain publications is approved 
by the Director of the Federal Register as of February 8, 2012.
    We must receive comments on this AD by March 26, 2012.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting your 
comments electronically.
    <bullet> Fax: (202) 493-2251.
    <bullet> Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
    <bullet> Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    You may get the service information identified in this AD from 
American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 
75053-4005, telephone (972) 641-3460, fax (972) 641-3527, or at http://www.eurocopter.com.
    Examining The 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 stated in the 
ADDRESSES section of this AD. Comments will be available in the AD 
docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Jim Grigg, ASW-112, Aviation Safety 
Engineer, Rotorcraft Directorate, Safety Management Group, 2601 Meacham 
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5126, fax (817) 
222-5961.

SUPPLEMENTARY INFORMATION: 

Discussion

    On March 11, 1983, we issued AD 82-13-05 R1, Amendment 39-4567 (48 
FR 13406, March 31, 1983), which revised AD 82-13-05, Amendment 39-4401 
(47 FR 27244, June 24, 1982), which superseded AD 82-02-02, Amendment 
39-4294 (47 FR 1113, January 11, 1982). The current AD requires a 
visual check for a crack in the flanges of the upper vertical fin 
support before the first flight each day. It also requires an initial 
10 hours time-in-service (TIS) inspection and thereafter, at intervals 
not to exceed 50 hours TIS, repetitive dye-penetrant or equivalent 
inspections for a crack in the flange of the upper vertical fin 
support. Since we issued those ADs, there have been additional reports 
of cracks in the spar area of the upper tail fin of the ECF Model 
AS355N helicopters.
    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD No. 2009-0030, dated February 12, 
2009, which supersedes EASA AD 2008-0121, dated June 27, 2008, for the 
AS350 helicopters. EASA has also issued AD No. 2009-0029, dated 
February 12, 2009, which supersedes EASA AD 2008-0120, dated June 27, 
2008, for the AS355 helicopters. This latest unsafe condition results 
from additional cracks that have been discovered in the spar of the 
upper fin on Model AS355N helicopters. Due to the fin design similarity 
between AS350 and AS355 helicopters, the same corrective action applies 
to both model helicopters. Modifying the upper and lower fin attachment 
is intended to prevent failure of a spar, loss of a fin, a separated 
fin hitting a rotor, and subsequent loss of control of a helicopter.
    You may obtain further information by examining the MCAI and any 
related service information in the AD docket.

Related Service Information

    ECF has issued Alert Service Bulletin (ASB) No. 55.00.12, Revision 
1, dated January 5, 2009, specifying MOD 073330 for the Model AS355E, 
F, F1, F2, and N helicopters and No. 55.00.16, Revision 1, dated 
January 5, 2009, specifying MOD 073330 for the Model SA350B, B1, B2, 
B3, BA, BB, D, and L1 helicopters. ECF has also issued ASB No. 
55.00.11, Revision 2, dated February 28, 2008, specifying MOD 073288 
for the AS355 E, F, F1, F2, and N helicopters and No. 55.00.13, 
Revision 2, dated February 28, 2008, specifying MOD 073288 for the 
AS350B3 helicopters. These ASBs specify various inspections and 
modifications for improving or monitoring upper and lower fin 
attachments and improving the attachment strength for upper and lower 
tailboom fin. The actions described in the MCAI AD are intended to 
correct the same unsafe condition as that identified in the service 
information.

FAA's Evaluation and Unsafe Condition Determination

    These products 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, their technical agent, has 
notified us of the unsafe condition described in the MCAI AD. We are 
issuing this AD because we evaluated all information provided by the 
EASA and determined the unsafe condition exists and is likely to exist 
or develop on other ECF helicopters of these same type designs.

[[Page 3381]]

Differences Between This AD and the MCAI

    We refer to flight hours as hours time-in-service. The dates in the 
MCAI have already passed; therefore, we did not use them in this AD. 
Also, some of the requirements are out-of-date, and we have not 
included them in this AD. We have also made some minor editorial 
changes for clarity.

Costs of Compliance

    We estimate that this AD will affect about 791 helicopters of U.S. 
registry. We also estimate that it will take about 4 work-hours per 
helicopter to modify the upper and lower fins and the upper and lower 
fin attachments. The average labor rate is $85 per work-hour. Required 
parts will cost about $453. Based on these figures, we estimate the 
cost of this AD on U.S. operators will be $793 to modify each 
helicopter or $627,263 for the fleet, assuming every helicopter is 
modified.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this superseding AD. We find that the risk to the flying public 
justifies waiving notice and comment prior to adoption of this rule 
because of reported cracks in the spar of the upper fin on AS355N 
helicopters. The growth of a crack in a fin attachment spar might occur 
quickly and if not corrected, lead to failure of a spar, loss of a fin, 
a separated fin hitting a rotor, and subsequent loss of control of the 
helicopter. Therefore, we have determined that notice and opportunity 
for public comment before issuing this AD are impracticable and that 
good cause exists for making this amendment effective in fewer than 30 
days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. However, we invite you to send us any written data, views, or 
arguments concerning this AD. Send your comments to an address listed 
under the ADDRESSES section of this AD. Include ``Docket No. FAA-2011-
0923; Directorate Identifier 2009-SW-20-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this AD. We will 
consider all comments received by the closing date and may amend this 
AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

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 product(s) 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.
    Therefore, I certify this AD:
    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 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 AD:

2011-18-12 Eurocopter France: Amendment 39-16794. Docket No. FAA-
2011-0923; Directorate Identifier 2009-SW-20-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective on 
February 8, 2012.

Other Affected ADs

    (b) This AD supersedes AD 82-13-05R1, Amendment 39-4567, Docket 
No. 83-ASW-09 (48 FR 13406; March 31, 1983); which revised AD 82-13-
05, Amendment 39-4401 (47 FR 27244; June 24, 1982); which superseded 
AD 82-02-02, Amendment 39-4294 (47 FR 1113; January 11, 1982).

Applicability

    (c) This AD applies to Model AS350B, B1, B2, B3, BA, and D; and 
AS355E, F, F1, F2, and N helicopters with upper and lower fins 
assemblies, installed, that have a part number (P/N) as follows:
    (1) For the Model AS350B, B1, B2, B3, BA, and D helicopters, 
certificated in any category:

------------------------------------------------------------------------
      Upper fin assembly  P/N:             Lower fin assembly P/N:
------------------------------------------------------------------------
350A14-0020-00XX                     350A14-0021-00XX
350A14-0020-01XX                     350A14-0021-01XX
350A14-0020-02XX                     350A14-0021-02XX
350A14-0020-03XX                     350A14-0021-03XX
350A14-0020-08XX                     350A14-0021-04XX
350A14-0020-09XX                     ...................................
350A14-0020-10XX                     ...................................
350A14-0020-17XX                     ...................................
350A14-0020-18XX                     ...................................
350A14-0020-19XX                     ...................................
350A64-1144-00XX                     ...................................
------------------------------------------------------------------------

     (2) For the Model AS355E, F, F1, F2, and N helicopters, 
certificated in any category:

------------------------------------------------------------------------
      Upper fin assembly  P/N:             Lower fin assembly P/N:
------------------------------------------------------------------------
355A14-0522-00XX                     355A14-0521-00XX
355A14-0522-01XX                     355A14-0521-01XX
355A14-0522-02XX                     355A14-0521-02XX
355A14-0522-03XX                     355A14-0521-03XX
355A14-0522-13XX                     ...................................
355A14-0522-14XX                     ...................................
355A14-0522-15XX                     ...................................
------------------------------------------------------------------------

Reason

    (d) The mandatory continuing airworthiness information (MCAI) AD 
states that some cracks have been discovered in the spar of the 
upper fin on Model AS355N helicopters. Due to the fin design 
similarity between AS350 and AS355 helicopters, the

[[Page 3382]]

same corrective action applies to both types of helicopters.

Actions and Compliance

    (e) Within 30 days, unless accomplished previously:
    (1) For Model AS350 helicopters with part numbers listed in 
paragraph (c)(1) of this AD, modify each fin as depicted in Figure 1 
and by following the Accomplishment Instructions, paragraph 2.B.2., 
Eurocopter Model AS350 Alert Service Bulletin (ASB) No. 55.00.16, 
Revision 1, dated January 5, 2009.
    (2) For Model AS355 helicopters with part numbers listed in 
paragraph (c)(2) of this AD, modify each fin as depicted in Figure 1 
and by following the Accomplishment Instructions, paragraph 2.B.2., 
of Eurocopter AS 355 ASB 55.00.12, Revision 1, dated January 5, 
2009.

    Note: Eurocopter Safety Information Notice No. 2315-S-55, 
Revision 1, dated April 21, 2011, not incorporated by reference, 
contains information about the subject of this AD.

Differences Between This AD and the MCAI

    (f) We refer to flight hours as hours TIS. The dates in the MCAI 
have already passed; therefore, we did not use them in this AD. 
Also, some of the requirements are out-of-date, and we have not 
included them in this AD. We have also made some minor editorial 
changes for clarity.

Other Information

    (g) The Manager, Safety Management Group, Rotorcraft 
Directorate, ATTN: FAA Safety Management Group, Jim Grigg., ASW-112, 
Aviation Safety Engineer, 2601 Meacham Blvd., Fort Worth, Texas 
76137, telephone (817) 222-5126, fax (817) 222-5961, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19.
    (h) Special flight permits are prohibited.

Related Information

    (i) EASA MCAI Airworthiness Directive Nos. 2009-0029 and 2009-
0030, both dated February 12, 2009, contain related information.

Joint Aircraft System/Component Code

    (j) The Joint Aircraft System/Component (JASC) Code is: 5531--
Vertical stabilizer spar/rib structure.

Material Incorporated by Reference

    (k) You must use the specified portions of the service 
information specified in this AD to do the actions required. The 
Director of the Federal Register approved the incorporation by 
reference of this service information under 5 U.S.C. 552(a) and 1 
CFR part 51.
    (1) Eurocopter Model AS350 Alert Service Bulletin No. 55.00.16, 
Revision 1, dated January 5, 2009; and
    (2) Eurocopter Model AS 355 Alert Service Bulletin No. 55.00.12, 
Revision 1, dated January 5, 2009.
    (3) For service information identified in this AD, contact 
American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 
75053-4005, telephone (972) 641-3460, fax (972) 641-3527, or at 
http://www.eurocopter.com.
    (4) You may review copies at the DOT/FAA, Southwest Region, 
Office of the Regional Counsel, 2601 Meacham Blvd., Fort Worth, 
Texas 76137; or 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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on August 19, 2011.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012-365 Filed 1-23-12; 8:45 am]
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