[Federal Register Volume 79, Number 21 (Friday, January 31, 2014)]
[Rules and Regulations]
[Pages 5247-5249]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-01461]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0501; Directorate Identifier 2011-SW-036-AD; 
Amendment 39-17732; AD 2014-02-04]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for 
Eurocopter France (Eurocopter) Model EC 155B and EC155B1 helicopters. 
This AD requires repetitively inspecting the lower and upper front and 
rear fittings (fittings) that attach the upper fin to the fenestron for 
a crack and, if there is a crack, removing all four fittings from 
service. This AD also requires, within a specified time, removing all 
fittings from service, and the fittings would not be eligible to be 
installed on any

[[Page 5248]]

helicopter. This AD was prompted by the loss of an upper fin in flight. 
The actions of this AD are intended to detect a crack in the fittings 
to prevent loss of the upper fin and subsequent loss of control of the 
helicopter.

DATES: This AD is effective March 7, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of March 7, 2014.

ADDRESSES: 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.

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 European Aviation Safety 
Agency (EASA) AD, any incorporated-by-reference service information, 
the economic evaluation, any comments received, and other information. 
The street address for the Docket Operations Office (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations Office, 
M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue 
SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, 
Texas 76137; telephone 817-222-5110; email [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    On June 11, 2013, at 78 FR 34960, the Federal Register published 
our notice of proposed rulemaking (NPRM), which proposed to amend 14 
CFR part 39 to include an AD that would apply to Model EC 155B and 
EC155B1 helicopters. The NPRM proposed inspecting certain part-numbered 
fittings for a crack and, if there is a crack, removing the fittings 
from service before further flight. Also, the NPRM proposed removing 
certain part-numbered fittings from service within 180 hours time-in-
service (TIS) and prohibiting the fittings from being eligible for 
installation on any helicopter. The proposed requirements were intended 
to detect a crack in the fittings to prevent loss of the upper fin and 
subsequent loss of control of the helicopter.
    The NPRM was prompted by AD No. 2011-0108, dated June 7, 2011, 
issued by EASA, which is the Technical Agent for the Member States of 
the European Union, to correct an unsafe condition for Eurocopter Model 
EC 155B and EC155B1 helicopters. EASA advises of an in-flight loss of a 
fin on a Model EC155B1 helicopter. According to EASA, a crack in the 
fittings attaching the upper fin to the fenestron (tail rotor assembly) 
was discovered during an investigation. As a result, EASA issued an 
emergency AD to mandate repetitive inspections of the upper fin 
attachment fittings. EASA states that Eurocopter developed modification 
(MOD) 0754B40 to increase the strength of the fuselage-fin junction 
fittings by installing two reinforced single-piece fittings to replace 
the affected fittings, which is terminating action for the repetitive 
inspection requirements. EASA subsequently issued AD No. 2011-0108, 
which superseded its emergency AD, to require installation of MOD 
0754B40 and to retain the repetitive inspection requirements until the 
MOD is installed.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we did not receive any comments on the NPRM (78 FR 34960, 
June 11, 2013).

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 and that air safety and the public interest require 
adopting the AD requirements as proposed.

Differences Between this AD and the EASA AD

    This AD does not require replacing the upper fin to fenestron 
fittings with reinforced fittings in accordance with MOD 0754B40 within 
6 calendar months as stated in the EASA AD, but rather requires 
removing the affected fittings from service within the equivalent 180 
hours TIS.

Related Service Information

    Eurocopter has issued Emergency Alert Service Bulletin No. 05A017, 
Revision 2, dated December 9, 2010, which specifies repetitively 
inspecting the fittings for a crack and replacing each fitting if there 
is a crack. Eurocopter has also issued Service Bulletin No. 53-029, 
Revision 1, dated March 10, 2011, which specifies replacing the 
fittings with reinforced fittings in accordance with MOD 0754B40.

Costs of Compliance

    We estimate that this AD will affect 9 helicopters of U.S. 
Registry. We estimate that operators will incur the following costs in 
order to comply with this AD based on an average labor rate of $85 per 
work hour. It will take 1 work hour to inspect the fittings and about 3 
inspections before replacement. It will take 8 work hours to replace 
the fittings, and required parts will cost $3,311. Based on these 
figures, the total cost will be $4,246 per helicopter and $38,214 for 
the U.S. fleet.

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 helicopters identified in this 
rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;

[[Page 5249]]

    (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):

    2014-02-04 Eurocopter France Helicopters: Amendment 39-17732; 
Docket No. FAA-2013-0501; Directorate Identifier 2011-SW-036-AD.

(a) Applicability

    This AD applies to Model EC 155B and EC155B1 helicopters with 
lower front fitting part number (P/N) 365A23-4240-01, upper front 
fitting P/N 365A23-4242-01, lower rear fitting P/N 365A23-4241-01, 
or upper rear fitting P/N 365A23-4243-01 (fittings), installed, 
certificated in any category.

 (b) Unsafe Condition

    This AD defines the unsafe condition as a crack in a fitting. 
This condition could result in loss of the upper fin during flight 
and subsequent loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective March 7, 2014.

(d) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

(e) Required Actions

    (1) Within 15 hours time-in-service (TIS) and thereafter at 
intervals not to exceed 55 hours TIS:
    (i) Using an appropriate light source and a 10x or higher power 
magnifying glass, inspect each front (item c) and rear (item d) 
upper fitting and each front (item e) and rear (item f) lower 
fitting for a crack as depicted in Detail A of Figure 1 of 
Eurocopter Emergency Alert Service Bulletin No. 05A017, Revision 2, 
dated December 9, 2010 (ASB). Inspect the hatched area as depicted 
in Details B, C, and D of Figure 2 of the ASB. A high-resolution 
(more than 2 million pixels) digital camera or dye-penetrant 
inspection may be used to facilitate the crack inspection.
    (ii) If there is a crack in any fitting, before further flight, 
remove all four fittings from service.
    (2) Within 180 hours TIS, remove the fittings from service.
    (3) Do not install lower front fitting P/N 365A23-4240-01, upper 
front fitting P/N 365A23-4242-01, lower rear fitting P/N 365A23-
4241-01, and upper rear fitting P/N 365A23-4243-01 on any 
helicopter.

(f) Credit for Actions Previously Completed

    Inspections accomplished before the effective date of this AD in 
accordance with the procedures specified in Eurocopter Emergency 
Alert Service Bulletin No. 05A017, Revision 2, dated December 9, 
2010; Revision 1, dated January 27, 2010; and Revision 0, dated 
September 28, 2007, are considered acceptable for compliance with 
the initial inspection specified in paragraph (e)(1) of this AD.

(g) Special flight permits

    Special flight permits will not be issued.

(h) 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, Safety Management Group, FAA, 2601 Meacham Blvd., Fort 
Worth, Texas 76137; telephone 817-222-5110; email 
[email protected].
    (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.

(i) Additional Information

    (1) Eurocopter Service Bulletin No. 53-029, Revision 1, dated 
March 10, 2011, which is not incorporated by reference, contains 
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 the referenced 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 AD No. 2011-0108, dated June 7, 2011, which can be 
found in Docket No. FAA-2013-0501 on the Internet at http://www.regulations.gov.

(j) Subject

    Joint Aircraft Service Component (JASC) Code: 5530 Vertical 
Stabilizer Structure.

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Eurocopter Emergency Alert Service Bulletin No. 05A017, 
Revision 2, dated December 9, 2010.
    (ii) Reserved.
    (3) For Eurocopter 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.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137. For information on the availability of this 
material at the FAA, call (817) 222-5110.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on January 16, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-01461 Filed 1-30-14; 8:45 am]
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