[Federal Register Volume 82, Number 160 (Monday, August 21, 2017)]
[Rules and Regulations]
[Pages 39506-39509]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-17084]


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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

[[Page 39507]]

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 [email protected].

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

[[Page 39508]]

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

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):

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 category:
    (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 [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.

(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.

[[Page 39509]]

    (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, 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.
    (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.
[FR Doc. 2017-17084 Filed 8-18-17; 8:45 am]
 BILLING CODE 4910-13-P