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2017-17-01 AIRBUS HELICOPTERS: Amendment 39-18991; Docket No. FAA-2017-0419; Product Identifier 2015-SW-077-AD.
(a) APPLICABILITY

    This AD applies to the following helicopters, certificated in any cat-
    egory:

(1) Model AS332L2 helicopters with a main rotor (M/R) blade attachment pin
    (attachment pin) part number (P/N) 332A31-2123-00 or  P/N 332A31-2115-
    20 installed; and

(2) Model EC225LP helicopters  with  an  attachment pin P/N 332A31-3204-20
    installed.

(b) UNSAFE CONDITION

    This AD defines  the unsafe condition  as corrosion or  a crack in  an
    attachment pin.  This  condition could result  in loss of an M/R blade
    and subsequent loss of control of the helicopter.

(c) EFFECTIVE DATE

    This AD becomes effective September 25, 2017.

(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) For Model AS332L2 helicopters, within 410 hours time-in-service (TIS),
    and for Model  EC225LP helicopters within 660 hours TIS,  remove  each
    attachment pin and inspect the protective coating on the inside of the
    attachment pin for scratches and missing protective coating.

(i) If there is a scratch  or  any  missing protective coating,  sand  the
    attachment pin to remove the varnish in the area depicted as  "Area A"
    in Figure  1 of  Airbus Helicopters  Alert Service  Bulletin (ASB) No.
    AS332-05.00.99, Revision 0, dated December 22, 2014  (AS332-05.00.99),
    or Airbus Helicopters ASB No. EC225-05A040, Revision 0, dated December
    22, 2014 (EC225-05A040), as applicable to your model helicopter.

(ii) Using a 10X  or  higher power magnifying glass, inspect for corrosion
     and pitting at  the chamfer. An  example of pitting  is shown in  the
     Accomplishment  Instructions,  paragraph  3.B.3.,  Note  1,  of AS332
     -05.00.99, and paragraph 3.B.2., Note 1, of EC225-05A040. If there is
     any corrosion, remove the corrosion. If there is any pitting, replace
     the  attachment pin.  Do  not  sand the  attachment pin  to remove  a
     corrosion pit.

(iii) Using a 10X or higher power magnifying glass, inspect the inside and
      outside of the attachment pin for  a crack in the areas depicted  as
      "Area A" and "Area B" in Figure 1 of AS332-05.00.99 or EC225-05A040,
      as applicable to your model helicopter. Pay particular attention  to
      the chamfer in "Area A." If there is a crack, remove the  attachment
      pin from service.

(2) Thereafter, for Model AS332L2 helicopters,  at intervals not to exceed
    825 hours  TIS or  26 months,  whichever occurs  first; and  for Model
    EC225LP helicopters, at intervals not to exceed 1,320 hours TIS or  26
    months,  whichever  occurs  first; perform  the  actions  specified in
    paragraph  (e)(1)  of  this  AD.  Corrosion  may  be  removed  from an
    attachment  pin as  specified in  paragraph (e)(1)(ii)  of  this  AD a
    maximum of four times. If there is a fifth occurrence of corrosion  on
    an attachment pin,  before further flight,  remove the attachment  pin
    from service.

(3) Do not install an attachment pin P/N 332A31-2123-00,  P/N 332A31-2115-
    20,  or  P/N 332A31-3204-20 on any helicopter unless you have complied
    with the actions in paragraph (e)(1) of this AD.

(f) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(1) The Manager, Safety Management Section, FAA,  may  approve  AMOCs  for
    this  AD.  Send  your proposal  to:  David  Hatfield, Aviation  Safety
    Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA,
    10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817)  222-5116;
    email 9-ASW-FTW-AMOC-Requests@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  certificate holding
    district office, before operating any aircraft complying with this  AD
    through an AMOC.

(g) ADDITIONAL INFORMATION

    The subject of this AD is addressed in European Aviation Safety Agency
    (EASA) No. 2015-0016, dated January 30, 2015. You may view the EASA AD
    on the Internet at  http://www.regulations.gov in Docket No.  FAA-2017
    -0419.

(h) SUBJECT

    Joint Aircraft Service Component (JASC) Code: 6200, Main Rotor System.

(i) MATERIAL INCORPORATED BY REFERENCE

(1) The  Director  of  the  Federal Register approved the incorporation by
    reference 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) Airbus Helicopters  Alert Service Bulletin  (ASB)  No. AS332-05.00.99,
    Revision 0, dated December 22, 2014.

(ii) Airbus Helicopters ASB No. EC225-05A040,  Revision 0,  dated December
     22, 2014.

(3) For Airbus Helicopters service information identified in this AD, con-
    tact 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.

(4) You may view this service information  at FAA,  Office of the Regional
    Counsel,  Southwest Region,  10101 Hillwood Pkwy.,  Room 6N-321,  Fort
    Worth, TX 76177.  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  August 7, 2017.  Scott A. Horn, Deputy
Director for Regulatory  Operations,  Compliance & Airworthiness Division,
Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT: David Hatfield, Aviation Safety Engineer,
Safety Management Section,  Rotorcraft Standards Branch,  FAA, 10101 Hill-
wood Pkwy., Fort Worth, TX 76177;  telephone (817) 222-5116;  email david.
hatfield@faa.gov.
PREAMBLE 

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.

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

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):