Document ID: FAA-2017-0419-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Helicopters
Posted Date: 2017-05-11T04:00Z

[Federal Register Volume 82, Number 90 (Thursday, May 11, 2017)]
[Proposed Rules]
[Pages 21956-21958]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-09378]

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0419; Directorate Identifier 2015-SW-077-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
Airbus Helicopters (Airbus) Model AS332L2 and EC225LP helicopters. This 
proposed AD would require inspections of the main rotor (M/R) blade 
attachment pins (attachment pins). This proposed AD is prompted by a 
report of three cracked attachment pins. The proposed actions are 
intended to detect and prevent an unsafe condition on these products.

DATES: We must receive comments on this proposed AD by July 10, 2017.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

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 proposed AD, the European Aviation Safety Agency (EASA) 
AD, the economic evaluation, any comments received, and other 
information. The street address for the Docket Operations Office 
(telephone 800-647-5527) is in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.
    For service information identified in this proposed 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.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.

FOR FURTHER INFORMATION CONTACT: David Hatfield, Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 
Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222-5116; email 
david.hatfield@faa.gov.

SUPPLEMENTARY INFORMATION: 

[[Page 21957]]

Comments Invited

    We invite you to participate in this rulemaking by submitting 
written comments, data, or views. We also invite comments relating to 
the economic, environmental, energy, or federalism impacts that might 
result from adopting the proposals in this document. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. To 
ensure the docket does not contain duplicate comments, commenters 
should send only one copy of written comments, or if comments are filed 
electronically, commenters should submit only one time.
    We will file in the docket all comments that we receive, as well as 
a report summarizing each substantive public contact with FAA personnel 
concerning this proposed rulemaking. Before acting on this proposal, we 
will consider all comments we receive on or before the closing date for 
comments. We will consider comments filed after the comment period has 
closed if it is possible to do so without incurring expense or delay. 
We may change this proposal in light of the comments we receive.

Discussion

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD No. 2015-0016, dated January 30, 
2015, 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. According to EASA, the cracks 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.

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 proposing this AD because we evaluated all known 
relevant information and determined that an unsafe condition is likely 
to exist or develop on other products of these same type designs.

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.

Proposed AD Requirements

    This proposed AD would 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, this proposed AD would require 
replacing the attachment pin. If there is corrosion, this proposed AD 
would require removing the corrosion up to a maximum of four times. 
This proposed AD would also require performing these inspections prior 
to installing an attachment pin.

Differences Between This Proposed 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 
proposed AD would require 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 proposed AD would require 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 proposed AD would 
not. Lastly, the EASA AD requires contacting and returning to Airbus 
Helicopters any attachment pin with a crack, and this proposed AD would 
not.

Costs of Compliance

    We estimate that this proposed AD would affect 5 helicopters of 
U.S. Registry. We estimate that operators may incur the following costs 
in order to comply with this proposed AD. Labor costs are estimated at 
$85 per work-hour.
    For Model AS332L2 helicopters, there would be no costs of 
compliance with this proposed 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 would take about 1 work-hour 
for a total cost of $85 per helicopter and $425 for the U.S. fleet. 
Removing corrosion would take about 1 work-hour for a total cost of $85 
per attachment pin. Replacing an attachment pin would take 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 products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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, I certify this proposed regulation:

[[Page 21958]]

    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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 proposed 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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):

Airbus Helicopters: Docket No. FAA-2017-0419; Directorate 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) Comments Due Date

    We must receive comments by July 10, 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 Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: David Hatfield, Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, 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) AD No. 2015-0016, dated January 30, 2015. You may view 
the EASA AD on the Internet at http://www.regulations.gov in the AD 
Docket.

(h) Subject

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

    Issued in Fort Worth, Texas, on April 27, 2017.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2017-09378 Filed 5-10-17; 8:45 am]
BILLING CODE 4910-13-P