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[Federal Register Volume 81, Number 69 (Monday, April 11, 2016)]
[Proposed Rules]
[Pages 21284-21286]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-07986]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3929; Directorate Identifier 2015-SW-031-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 
Airbus Helicopters Model EC130B4, EC130T2, AS350B, AS350B1, AS350B2, 
AS350B3, AS350BA, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, 
AS355F2, AS355N, and AS355NP helicopters. This proposed AD would 
require inspecting each bi-directional suspension cross-bar (cross-bar) 
for a crack. This proposed AD is prompted by two reports of cracks in a 
cross-bar. The proposed actions are intended to detect cracks in a 
cross-bar and prevent failure of the cross-bar and subsequent loss of 
control of the helicopter.

DATES: We must receive comments on this proposed AD by June 10, 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-
3929 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, 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: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 10101 Hillwood Pkwy., Fort 
Worth, TX 76177; telephone (817) 222-5110; email robert.grant@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

[[Page 21285]]

Union, has issued EASA AD No. 2015-0094, dated May 29, 2015, to correct 
an unsafe condition for Airbus Helicopters Model AS350B, AS350BA, 
AS350BB, AS350B1, AS350B2, AS350B3, AS350D, AS355E, AS355F, AS355F1, 
AS355F2, AS355N, AS355NP, EC130B4, and EC130T2 helicopters. EASA 
advises that two cases of cracks in a cross-bar were reported on 
AS350B3 helicopters. The cracks were found at the transmission deck 
attachment fitting holes during a maintenance check, EASA states. 
According to EASA, in both cases, the helicopters were equipped with a 
cargo hook and had completed missions with a significant number of 
torque cycles. Because of common design features, cracks may also occur 
on other Model AS350-series, AS355-series, and EC130-series 
helicopters. EASA advises that crack growth may lead to failure of one 
of the four yokes and significantly increased stress load on the 
remaining yokes. This condition, if not detected or corrected, could 
lead to cracks on the remaining yokes and increased load on the cross-
bar, possibly resulting in cross-bar failure and consequently loss of 
the helicopter. To correct this condition, EASA AD No. 2015-0094 
requires repetitive cross-bar inspections and, depending on the 
findings, replacing the cross-bar.

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

    Airbus Helicopters has issued Alert Service Bulletin (ASB) No. 
EC130-05A021 for Model EC130B4 helicopters; ASB No. EC130-05A022 for 
Model EC130T2 helicopters; ASB No. AS350-05.00.84 for Model AS350B, 
AS350B1, AS350B2, AS350B3, AS350BA, AS350BB, AS350D, and military Model 
AS350L1 helicopters; and ASB No. 355-05.00.73 for Model AS355E, AS355F, 
AS355F1, AS355F2, AS355N, and AS355 NP helicopters (ASBs). All of the 
ASBs are Revision 0 and dated May 21, 2015. The ASBs specify visually 
inspecting the cross-bar. If there is any doubt after the visual 
inspection, the ASBs call for a dye-penetrant inspection to make sure 
there are no cracks. If a crack is detected, the ASBs call for 
replacing the cross-bar before further flight and sending the damaged 
cross-bar to Airbus Helicopters.

Proposed AD Requirements

    This proposed AD would require, within certain initial inspection 
times or the next time any maintenance of the helicopter involves 
removing the main gearbox, whichever comes first, inspecting each 
cross-bar for a crack. If there is a crack, this proposed AD would 
require replacing the cross-bar before further flight. This proposed AD 
would also require repeating these inspections at the same intervals as 
the initial inspection. The compliance times in this proposed AD 
include torque cycles, which are defined for purposes of this AD, as 
one landing with or without stopping the rotor or one external load-
carrying operation. An external load-carrying operation occurs each 
time a helicopter picks up an external load and drops it off.

Differences Between This Proposed AD and the EASA AD

    The EASA AD applies to Airbus Helicopters Model AS350BB 
helicopters. This proposed AD would not apply to the Model AS350BB 
because it has no FAA type certificate. However, this proposed AD would 
apply to Model AS350C and AS350D1 helicopters, while the EASA AD does 
not. The EASA AD requires a florescent dye-penetrant inspection if the 
visual inspection of the bi-directional suspension cross-bar causes 
doubts. This proposed AD would not require a florescent dye-penetrant 
inspection. The EASA AD requires returning the damaged bi-directional 
suspension cross-bar to Airbus Helicopters, and this proposed AD would 
not.

Costs of Compliance

    We estimate that this proposed AD would affect 1,132 helicopters of 
U.S. Registry and that labor costs average $85 a work-hour. Based on 
these estimates, we expect the following costs:
     Visually inspecting the cross-bar would require 16.5 work-
hours for a labor cost of about $1,403. No parts would be needed so 
that the cost for the U.S. fleet would total $1,588,196 per inspection 
cycle.
     Replacing the cross-bar would cost $1,630 for parts. No 
additional labor costs would be needed.

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.

[[Page 21286]]

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-2015-3929; Directorate Identifier 
2015-SW-031-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model EC130B4, EC130T2, 
AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS350C, AS350D, AS350D1, 
AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters 
with a bi-directional suspension cross-bar (cross-bar) part number 
(P/N) 350A38-1040-20 or P/N 350A38-1040-00 installed, certificated 
in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in a bi-
directional cross-bar, which could result in failure of a cross-bar 
and loss of control of the helicopter.

(c) Comments Due Date

    We must receive comments by June 10, 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) Within the initial inspection times shown in Table 1 to 
paragraph (e) of this AD or the next time maintenance of the 
helicopter involves removing the main gearbox, whichever comes 
first; and thereafter at intervals not to exceed the compliance 
times shown in Table 1 to paragraph (e) of this AD, inspect each 
cross-bar for a crack. For purposes of this AD, a torque cycle is 
defined as one landing with or without stopping the rotor or one 
external load-carrying operation; an external load-carrying 
operation occurs each time a helicopter picks up an external load 
and drops it off.

                        Table 1 to Paragraph (e)
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                                              Initial and recurrent
            Helicopter model                   inspection interval
------------------------------------------------------------------------
AS350B, AS350BA, AS350B1, AS350B2,       4,500 hours time-in-service
 AS350C, AS350D, AS350D1.                 (TIS) or 60,000 torque cycles,
                                          whichever occurs first.
AS350B3, AS355E, AS355F, AS355F1,        3,300 hours TIS or 60,000
 AS355F2, AS355N, or AS355 NP.            torque cycles, whichever
                                          occurs first.
EC130B4.
EC130T2................................  3,300 hours TIS or 40,000
                                          torque cycles, whichever
                                          occurs first.
------------------------------------------------------------------------

    (2) If there is a crack, before further flight, replace the 
cross-bar.

(f) Special Flight Permit

    Special flight permits are prohibited.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 10101 Hillwood Pkwy., Fort 
Worth, TX 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 Alert Service Bulletin No. EC130-05A021, 
No. EC130-05A022, No. AS350-05.00.84, and No. AS355-05.00.73, all 
Revision 0 and all dated May 21, 2015, which are not incorporated by 
reference, contain additional information about the subject of this 
proposed rule. 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.
    (2) The subject of this AD is addressed in European Aviation 
Safety Agency (EASA) AD No. 2015-0094, dated May 29, 2015. 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: 6300, Main Rotor 
Drive.

    Issued in Fort Worth, Texas, on March 31, 2016.
James A. Grigg,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-07986 Filed 4-8-16; 8:45 am]
 BILLING CODE 4910-13-P
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