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[Federal Register Volume 81, Number 2 (Tuesday, January 5, 2016)]
[Proposed Rules]
[Pages 191-193]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-33014]

========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

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Federal Register / Vol. 81, No. 2 / Tuesday, January 5, 2016 / 
Proposed Rules

[[Page 191]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3883; Directorate Identifier 2014-SW-029-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Airbus Helicopters Model AS332L2 and EC225LP helicopters. This 
proposed AD would require 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 proposed 
AD is prompted by reports of cracks on frame 5295 and on splices 
installed to prevent those cracks. The proposed actions are intended to 
detect a crack in frame 5295, which could lead to loss of the 
helicopter frame's structural integrity and consequently, loss of 
helicopter control.

DATES: We must receive comments on this proposed AD by March 7, 2016.

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-2015-
3883 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, 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, Texas 
76177.

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

SUPPLEMENTARY INFORMATION:

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, issued AD No. 2014-0098-E, dated April 25, 2014, to 
correct an unsafe condition for 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 detected 
on the reinforced frame during a scheduled inspection of a helicopter. 
According to EASA, the crack 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.

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 the same type design.

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

[[Page 192]]

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 Modification 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 Airbus Service Bulletin (SB) No. 53-003, Revision No. 
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 Service 
Bulletin 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.

Proposed AD Requirements

    This proposed AD would require the following before a splice 
reaches 1,700 hours time-in-service (TIS), within 50 hours TIS, or 
before the helicopter reaches 11,950 hours TIS, whichever occurs later:
     Installing the rail support cut-out and identifying the 
right-hand and left-hand junction profile.
     Inspecting each splice for a crack, and repairing or 
replacing the splice if there is a crack.
    This proposed AD would then require, at intervals not to exceed 110 
hours TIS, inspecting each splice for a crack, and repairing or 
replacing the splice if there is a crack.

Differences Between This Proposed AD and the EASA AD

    The EASA AD requires contacting Airbus Helicopters if there is a 
crack in the affected parts. This proposed AD would make no such 
requirement.
    The EASA AD sets various timelines for the repair or replacement of 
affected parts if a crack exists. This proposed AD would require the 
repair or replacement of affected parts before further flight if a 
crack exists.

Costs of Compliance

    We estimate that this proposed AD would affect 4 helicopters of 
U.S. Registry and that labor costs average $85 a work-hour. Based on 
these estimates, we expect the following costs:
    Installing the cut-outs on frame 5295 would require 40 work hours 
for a labor cost of $3,400. Parts would cost $5,000 for total cost per 
helicopter of $8,400 and $33,600 for the U.S. fleet.
    Inspecting helicopter frame 5295 would require 2 work-hours for a 
labor cost of $170 per helicopter. No parts would be needed for a total 
U.S. fleet cost of $680 per inspection cycle.

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:
    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-2015-3883; Directorate Identifier 
2014-SW-029-AD.

(a) Applicability

    This AD applies to Model AS332L2 and Model EC225LP helicopters 
with an extended aluminum splice installed on frame 5295, 
certificated in any category.

    Note 1 to paragraph (a) of this AD:  Helicopters with 
modification (MOD) 0726517 have an extended aluminum splice 
installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack on helicopter 
frame 5295. This condition could result in structural failure of the 
frame and subsequent loss of control of the helicopter.

(c) Comments Due Date

    We must receive comments by March 7, 2016.

(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) Before a splice reaches 1,700 hours time-in-service (TIS), 
within 50 hours TIS, or before the helicopter reaches 11,950 hours 
TIS, whichever occurs later, do the following:
    (i) Install the rail support cut-out and identify the right-hand 
and left-hand junction

[[Page 193]]

profile in accordance with the Accomplishment Instructions, 
paragraph 3.B.2, of Alert Service Bulletin (ASB) No. EC225-05A038, 
Revision 0, dated April 15, 2014 (ASB EC225-05A038), or ASB No. 
AS332-05.00.97, Revision 0, dated April 15, 2014 (ASB AS332-
05.00.97), whichever is applicable to your helicopter.
    (ii) Inspect each splice for a crack in the area depicted as 
Area Y in Figure 3 of ASB EC225-05A038 or ASB AS332-05.00.97, 
whichever is applicable to your helicopter. If a crack exists, 
repair or replace the splice before further flight.
    (2) Thereafter at intervals not to exceed 110 hours TIS, inspect 
each splice for a crack in the area depicted as Area Y in Figure 3 
of ASB EC225-05A038 or ASB AS332-05.00.97. If a crack exists, repair 
or replace the splice before further flight.

(f) Credit for Actions Previously Completed

    Installing rail support cut-outs in accordance with MOD 0728090 
or Airbus Helicopters Service Bulletin No. 05-019, Revision 4, dated 
September 22, 2014, before the effective date of this AD is 
considered acceptable for compliance with the corresponding actions 
specified in paragraph (e)(1)(i) of this AD.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Gary Roach, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
10101 Hillwood Pkwy., Fort Worth, Texas 76177; telephone (817) 222-
5110; 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.

(h) Additional Information

    (1) Airbus Helicopters Service Bulletin (SB) No. 05-019, 
Revision 4, dated September 22, 2014, and SB No. 53-003 and SB No. 
53.01.52, both Revision 4 and both dated July 12, 2010, which are 
not incorporated by reference, contain additional information about 
the subject of this AD. For service information identified in this 
AD, 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.
    (2) The subject of this AD is addressed in the European Aviation 
Safety Agency (EASA) AD No. 2014-0098-E, dated April 25, 2014. You 
may view the EASA AD on the Internet at http://www.regulations.gov 
in the AD Docket.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 5310, Fuselage 
Main, Structure.

    Issued in Fort Worth, Texas, on December 22, 2015.
Lance T. Gant,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2015-33014 Filed 1-4-16; 8:45 am]
 BILLING CODE 4910-13-P
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