DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0419; Product Identifier 2015-SW-077-AD; Amendment
39-18991; AD 2017-17-01]
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 (Airbus) Model AS332L2 and EC225LP helicopters. This AD requires
inspections of the main rotor (M/R) blade attachment pins (attachment
pins).
This AD was prompted by a report of three cracked attachment pins. The
actions of this AD are intended to detect and prevent an unsafe condition
on
these products.
DATES: This AD is effective September 25, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of September 25,
2017.
ADDRESSES: For service information identified in this final rule,
contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775;
or at http://www.helicopters.airbus.com/Website/en/ref/Technical-Support_
73.html. 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-2017-0419.
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-2017-
0419; 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: David Hatfield, Aviation Safety
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5116;
email david.hatfield@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On May 11, 2017, at 82 FR 21956, 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 Airbus Model AS332L2
helicopters with an attachment pin part number (P/N) 332A31-2123-00 or
P/N 332A31-2115-20 installed and Model EC225LP helicopters with an
attachment pin P/N 332A31-3204-20 installed. The NPRM proposed to
require an initial and recurring inspection of each attachment pin for
corrosion, a crack, and any pitting. If there is a crack or any
pitting, the NPRM proposed to require replacing the attachment pin. If
there is corrosion, the NPRM proposed to require removing the corrosion
up to a maximum of four times. The NPRM also proposed to require
performing these inspections prior to installing an attachment pin. The
proposed requirements were intended to detect corrosion or a crack in
an attachment pin and prevent loss of an M/R blade and subsequent loss
of control of the helicopter.
The NPRM was prompted by AD No. 2015-0016, dated January 30, 2015,
issued by EASA, which is the Technical Agent for the Member States of
the European Union, to correct an unsafe condition for Airbus Model AS
332 L2 and EC 225 LP helicopters with certain part-numbered attachment
pins installed. EASA advises of three cracked attachment pins on a
Model AS 332 L2 helicopter, which resulted from a combination of
factors including corrosion that had initiated in the inner diameter
area of the attachment pin chamfer. EASA states that if this condition
is not detected and corrected, it may lead to failure of the attachment
pin with loss of control of the helicopter. Due to design similarity,
Model EC225LP helicopters are also affected by this issue.
For these reasons, EASA AD No. 2015-0016 requires repetitive
inspections of the attachment pins for corrosion.
Comments
We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM.
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
its 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
The EASA AD does not require an inspection of the protective
coating of each attachment pin for Model EC225LP helicopters. This AD
requires inspecting the protective coating of each attachment pin for
both model helicopters. The EASA AD requires ensuring there are no
corrosion pits without a corresponding corrective action. This AD
requires replacing an attachment pin that has any pitting. The EASA AD
requires a non-destructive inspection if in doubt about whether there
is a crack, while this AD does not. Lastly, the EASA AD requires
contacting and returning to Airbus Helicopters any attachment pin with
a crack, and this AD does not.
Related Service Information Under 1 CFR Part 51
We reviewed Airbus Helicopters Alert Service Bulletin (ASB) No.
AS332-05.00.99, Revision 0, dated December 22, 2014 (AS332-05.00.99),
for Model AS332L2 helicopters and Airbus Helicopters ASB No. EC225-
05A040, Revision 0, dated December 22, 2014 (EC225-05A040), for Model
EC225LP helicopters. Airbus Helicopters advises of cracks discovered in
attachment pins that resulted from a combination of factors, but mainly
corrosion which initiated in the inner diameter at the chamfer. This
service information specifies repetitively inspecting for corrosion and
cracks and ensuring there are no corrosion pits in the attachment pins.
If there is corrosion, this service information allows an attachment
pin to be reworked up to four times before removing it from service. If
there is a crack, this service information specifies contacting and
sending the attachment pin to Airbus Helicopters.
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.
Costs of Compliance
We estimate that this AD affects 5 helicopters of U.S. Registry. We
estimate that operators may incur the following costs in order to
comply with this AD. Labor costs are estimated at $85 per work-hour.
For Model AS332L2 helicopters, there are no costs of compliance
with this AD because there are no helicopters with this type
certificate on the U.S. Registry.
For Model EC225LP helicopters, which have ten attachment pins
installed, inspecting the attachment pins takes about 1 work-hour for
a
total cost of $85 per helicopter and $425 for the U.S. fleet. Removing
corrosion takes about 1 work-hour for a total cost of $85 per
attachment pin. Replacing an attachment pin takes negligible additional
labor time and required parts would cost about $5,720.
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):
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