DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3883; Product Identifier 2014-SW-029-AD; Amendment
39-19289; AD 2018-11-01]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus
Helicopters Model AS332L2 and EC225LP helicopters. This AD requires
installing a cut-out for the left-hand (LH) and right-hand (RH) rail
support junction profiles and inspecting splices, frame 5295, and
related equipment for a crack. This AD was prompted by reports of
cracks on frame 5295 and on splices installed to prevent those cracks.
The actions of this AD are intended to prevent an unsafe condition on
these products.

DATES: This AD is effective June 27, 2018.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of June 27, 2018.

ADDRESSES: For service information identified in this final rule,
contact Airbus Helicopters, Inc., 2701 N Forum Drive, Grand Prairie, TX
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775;
or at http://www.airbushelicopters.com/techpub. You may review the
referenced service information at the FAA, Office of the Regional
Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort
Worth, TX 76177. It is also available on the internet at http://www.
regulations.gov by searching for and locating Docket No. FAA-2015-
3883.

Examining the AD Docket

You may examine the AD docket on the internet at http://www.regulations.
gov by searching for and locating Docket No. FAA-2015-
3883; or in person at Docket Operations 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
Docket Operations (phone: 800-647-5527) is U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Gary Roach, Aviation Safety Engineer,
Regulations & Policy Section, Rotorcraft Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email
gary.b.roach@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

On January 5, 2016, at 81 FR 191, the Federal Register published
our notice of proposed rulemaking (NPRM), which proposed to amend 14
CFR part 39 by adding an AD that would apply to Model AS332L2 and Model
EC225LP helicopters with an extended aluminum splice installed on frame
5295. The NPRM proposed to require installing a cut-out for the LH and
RH rail support junction profiles and inspecting splices, frame 5295,
and related equipment for a crack. The proposed requirements were
intended to detect a crack in frame 5295, which could lead to
structural failure of the frame and loss of control of the helicopter.
The NPRM was prompted by AD No. 2014-0098-E, dated April 25, 2014,
issued by EASA, which is the Technical Agent for the Member States of
the European Union, to correct an unsafe condition for Model AS332L2
and EC225LP helicopters. EASA AD No. 2014-0098-E applies to helicopters
with a frame 5295 that have been reinforced by installing aluminium
splices on the RH and LH fuselage external skins. EASA advises of a
report of a crack that initiated on a splice in an area hidden by the
overlapping junction profile of the cabin sliding door rail support and
then spread to the frame.
EASA states that a crack in frame 5295, if not detected and
corrected, could lead to loss of structural integrity of the helicopter
frame and subsequent loss of control of the helicopter. To address this
condition, EASA issued AD No. 2014-0098-E to require repetitive
inspections of the splices for a crack, as well as cutting out the rail
support junction profiles to provide a convenient access to identify
cracks in a splice.
Since the NPRM was issued, the FAA's Aircraft Certification Service
has changed its organizational structure. The new structure replaces
product directorates with functional divisions. We have revised some of
the office titles and nomenclature throughout this Final rule to
reflect the new organizational changes. Additional information about
the new structure can be found in the Notice published on July 25, 2017
(82 FR 34564).

Comments

After our NPRM was published, we received comments from a commenter
who raised three issues.

Request

The commenter requested that we revise the applicability of the AD
to exempt helicopters that are ``post mod 07 26493 or RDAS 332-1284-
13.''
We partially agree. Modification (MOD) 0726493 or repair design
approval sheet (RDAS) 332-1284-13 specify installing a stainless steel
doubler to reduce stress in the splice and frame, thereby eliminating
the unsafe condition. We disagree with exempting ``post mod''
helicopters, however, as the stainless steel doubler could be removed
(subjecting the helicopter again to the unsafe condition) and the
helicopter would still be in a ``post mod'' configuration. Instead, we
have changed the applicability to exempt helicopters with the steel
splice kit installed that pertains to MOD 0726493.
The commenter requested that we revise the compliance time of the
AD to include the flow charts from the Airbus Helicopters service
information. The commenter states that this information would explain
the steps involved to operators to eliminate the unsafe condition. The
commenter also requested that we clarify the compliance times as
discussed in the preamble of the NPRM, because they appear different
from those in the service information and the EASA AD.
We disagree. The commenter is correct that the compliance times in
our AD are different, in some measure, to those in the EASA AD. But the
compliance times in the AD are clear as written. The requested change
is unnecessary.

The commenter requested that we withdraw the AD because all
helicopters in the U.S. fleet have either installed the cut-out or are
scheduled for installation of the cut-out.
We disagree. The FAA has determined that an unsafe condition
exists. AD action is required to mandate corrective action for this
unsafe condition. In addition, if additional helicopters are imported
into the United States, AD action is necessary to require that those
helicopters accomplish the corrective actions before operating in this
country.

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, reviewed the relevant information,
considered the comments received, 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 with the change described
previously and with a revision to the estimated costs of complying with
this AD. These changes are consistent with the intent of the proposals
in the NPRM and will not increase the economic burden on any operator
nor increase the scope of the AD.

Differences Between This AD and the EASA AD

The EASA AD requires contacting Airbus Helicopters if there is a
crack in the affected parts. This AD makes no such requirement.
The EASA AD sets various timelines for repairing affected parts if
a crack exists. This AD requires repairing affected parts before
further flight if a crack exists.

Related Service Information Under 1 CFR Part 51

We reviewed Airbus Helicopters Alert Service Bulletin (ASB) No.
EC225-05A038 for Model EC225LP helicopters and ASB No. AS332-05.00.97
for Model AS332L2 helicopters. The ASBs, both Revision 0 and both dated
April 15, 2014, report cracks were found in the splice and frame 5295
on a Model AS332L2 helicopter during a major inspection. The splice had
been added in compliance with MOD 0726517. Had an optional rail support
cut-out been accomplished on the aircraft to allow for a visual check
of the splice for frame 5295, it would have revealed the crack in the
splice, prompting its repair and consequently limiting the damage to
frame 5295. As a result, the ASBs call for the rail support cut-out on
the RH and LH side of the frame as well as periodic visual inspections
of frame 5295 and related equipment.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.

Other Related Service Information

We reviewed Eurocopter Helicopters (now Airbus Helicopters) Service
Bulletin (SB) No. 53-003, Revision 4, for Model EC225LP helicopters and
SB No. 53.01.52, Revision 5, for Model AS332L2 helicopters, both dated
July 23, 2010. The SBs specify procedures to reinforce frame 5295 by
installing a new titanium plate underneath the fitting and a new
widened aluminum splice below the upper corner of the door. We also
reviewed Airbus Helicopters SB No. 05-019, Revision 4, dated September
22, 2014, for Model EC225LP helicopters, which proposes that you cut
out the junction profiles to perform periodic visual inspections.

Costs of Compliance

We estimate that this AD affects 4 helicopters of U.S. Registry. We
estimate that operators may incur the following costs in order to
comply with this AD. Labor costs average $85 a work-hour. Based on
these estimates, we expect the following costs:
Installing the cut-outs on frame 5295 requires 40 work-hours for a
labor cost of $3,400. Parts cost $5,000 for total cost per helicopter
of $8,400 and $33,600 for the U.S. fleet.
Inspecting helicopter frame 5295 requires 2 work-hours for a labor
cost of $170 per helicopter. No parts are needed for a total U.S. fleet
cost of $680 per inspection cycle.
Repairing a splice requires 40 work-hours and a parts cost of
$5,000 for a total cost of $8,400 per 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 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;
(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

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):