Document ID: FAA-2015-3929-0004
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Helicopters
Posted Date: 2016-12-27T05:00Z

[Federal Register Volume 81, Number 248 (Tuesday, December 27, 2016)]
[Rules and Regulations]
[Pages 94954-94956]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-30048]

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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; 
Amendment 39-18746; AD 2016-25-20]
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 Model EC130B4, EC130T2, AS350B, AS350B1, AS350B2, AS350B3, 
AS350BA, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, 
AS355N, and AS355NP helicopters. This AD requires inspecting each bi-
directional suspension cross-bar (cross-bar). This AD was prompted by 
two reports of cracks in a cross-bar. These actions are intended to 
prevent the unsafe condition on these products.

DATES: This AD is effective January 31, 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.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. 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.

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 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 (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: 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: 

Discussion

    On April 11, 2016, at 81 FR 21284, 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 Helicopters 
Model EC130B4, EC130T2, AS350B, AS350B1, AS350B2, AS350B3, AS350BA, 
AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and 
AS355NP helicopters with a cross-bar part number (P/N) 350A38-1040-20 
or P/N 350A38-1040-00 installed. The NPRM proposed to require 
repetitively inspecting each cross-bar for a crack and replacing any 
cracked cross-bar before further flight. The proposed requirements were 
intended to detect cracks in a cross-bar and prevent failure of the 
cross-bar and subsequent loss of control of the helicopter.
    The NPRM was prompted by AD No. 2015-0094, dated May 29, 2015, 
issued by EASA, which is the Technical Agent

[[Page 94955]]

for the Member States of the European Union, 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 in helicopters equipped with a cargo hook that 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 increase stress loads 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.

Comments

    One commenter submitted comments supporting the NPRM (81 FR 21284, 
April 11, 2016).

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 
the EASA 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 applies to Airbus Helicopters Model AS350BB 
helicopters. This AD does not apply to the Model AS350BB because it 
does not have an FAA type certificate. However, this AD applies 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 AD does not require a florescent dye-penetrant inspection. The 
EASA AD requires returning the damaged bi-directional suspension cross-
bar to Airbus Helicopters, and this AD does not.

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.

Costs of Compliance

    We estimate that this AD affects 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 requires 16.5 work-hours 
for a labor cost of about $1,403. No parts are needed so that the cost 
for the U.S. fleet totals $1,588,196 per inspection cycle.
     Replacing the cross-bar costs $1,630 for parts. No 
additional labor costs are 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 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):

2016-25-20 Airbus Helicopters: Amendment 39-18746; 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.

[[Page 94956]]

 (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) Effective Date

    This AD becomes effective January 31, 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) 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)
------------------------------------------------------------------------
                                              Initial and recurrent
            Helicopter model                   inspection interval
------------------------------------------------------------------------
AS350B, AS350BA, AS350B1, AS350B2,       4,500 hours time-in-service
 AS350C, AS350D, and AS350D1.             (TIS) or 60,000 torque cycles,
                                          whichever occurs first.
AS350B3, AS355E, AS355F, AS355F1,        3,300 hours TIS or 60,000
 AS355F2, AS355N, and AS355 NP.           torque cycles, whichever
EC130B4................................   occurs first.
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 Permits

    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 
final rule. 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.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 
Docket No. FAA-2015-3929.

 (i) Subject

    Joint Aircraft Service Component (JASC) Code: 6300, Main Rotor 
Drive System.

    Issued in Fort Worth, Texas, on December 6, 2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-30048 Filed 12-23-16; 8:45 am]
 BILLING CODE 4910-13-P