[Federal Register Volume 81, Number 71 (Wednesday, April 13, 2016)]
[Rules and Regulations]
[Pages 21713-21716]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-07979]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-5914; Directorate Identifier 2014-SW-056-AD; 
Amendment 39-18472; AD 2016-07-27]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters (formerly Eurocopter 
France)

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 SA341G and SA342J helicopters. This AD requires 
repetitive inspections of a certain part-numbered main rotor hub 
torsion bar (torsion bar). This AD was prompted by several cases of 
corrosion in the metal strands of the torsion bar. The actions of this 
AD are intended to detect corrosion and prevent failure of the torsion 
bar, loss of a main rotor blade, and subsequent loss of control of the 
helicopter.

DATES: This AD is effective May 18, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of May 18, 2016.

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. It is also on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
5914.

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-
5914; 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: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 10101 Hillwood Pkwy, Fort 
Worth, Texas 76177; telephone (817) 222-5110; email 
[email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    On November 19, 2015, at 80 FR 72390, 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 Model SA341G 
and SA342J helicopters with a torsion bar part number 704A33633274 
installed. The NPRM proposed to require removing and performing 
repetitive inspections of each torsion bar for a crack in the 
polyurethane (PU) coating, the dimension of the angle between the 
bushings, corrosion on the inside diameter of each bushing, the 
thickness of each bushing, the size of the inside diameter of each 
bushing, and missing varnish on the two faces of each bushing. The NPRM 
also proposed to require replacing the torsion bar before further 
flight if there is a crack in the PU coating of a torsion bar that 
matches or exceeds the damage criteria, if the angle of the torsion bar 
is 7 degrees or more, if any corrosion on a bushing cannot be removed 
by rubbing it with an abrasive pad, if the thickness of a bushing is 
less than 37.520 mm (1.477 in), or if the diameter of a bushing is 
larger than 21,040 mm (.828 in). If varnish is missing from more than 
15 percent of the surface area from a face of a bushing, the NPRM 
proposed to require removing all varnish, finishing with an abrasive 
pad, and applying a coat of paint to the face of the bushing. The 
proposed requirements were intended to detect corrosion and prevent 
failure of the

[[Page 21714]]

torsion bar, loss of a main rotor blade, and subsequent loss of control 
of the helicopter.
    The NPRM was prompted by AD No. 2014-0216, dated September 24, 
2014, issued by EASA, which is the Technical Agent for the Member 
States of the European Union, to correct an unsafe condition for Airbus 
Helicopters Model SA341G and SA342J helicopters. EASA advises that 
several cases of cracks were found on the PU coating of part-numbered 
704A33633274 torsion bars installed on military Model SA341 
helicopters. EASA states that these parts can also be installed on 
civilian Model SA341 and SA342 helicopters. According to EASA, analysis 
of the cracked torsion bars showed small areas of superficial corrosion 
on the strands inside the bars can also develop during the 
manufacturing process. EASA states that cracking of the PU coating near 
these areas and the associated penetration of water can lead to further 
and deeper development of the corrosion. EASA advises that this 
condition, if not detected and corrected, allows water to penetrate 
into the torsion bar causing corrosion and failure of the metal strands 
inside the bar. Failure of the metal strands could lead to torsion bar 
failure, resulting in an in-flight loss of a main rotor blade and 
consequent loss of control of the helicopter.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we did not receive any comments on the NPRM (80 FR 72390, 
November 19, 2015).

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.

Interim Action

    We consider this AD to be an interim action. If final action is 
later identified, we might consider further rulemaking.

Differences Between This AD and the EASA AD

    This AD requires you to replace a torsion bar instead of returning 
it to the manufacturer for examination.

Related Service Information Under 1 CFR Part 51

    Eurocopter (now Airbus Helicopters) has issued Gazelle Inspection--
Check 65.12.607, ``Main Rotor Head: Torsion Tie-Back Check (Post MOD 
076171),'' dated August 2008, of the Eurocopter Gazelle Helicopter 
Maintenance Manual, Tome 1, which describes inspecting the torsion bars 
for a crack in the PU coating and for corrosion and thickness of the 
bushings.
    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

    Airbus Helicopters has also issued Alert Service Bulletin No. 
SA341/SA342-05.40, Revision 0, dated April 28, 2014 (ASB), for Model 
SA341G and SA342J helicopters certificated by the FAA, and military 
Model SA341B, C, D, E, F, and H and SA342K, L, L1, M, M1, and Ma 
helicopters. The ASB specifies repetitively inspecting the torsion bars 
in accordance with certain work cards, including work card 65.12.607. 
These inspections are part of Airbus Helicopters' current maintenance 
program, and the ASB revises the compliance time interval for the 
inspections.

Costs of Compliance

    We estimate that this AD affects 33 helicopters of U.S. Registry. 
We estimate that operators may incur the following costs in order to 
comply with this AD. We estimate $85 per work-hour for labor. We 
estimate 8 work-hours to inspect each helicopter at an estimated cost 
of $680 per helicopter and $22,440 for the U.S. fleet per inspection 
cycle. Replacing a torsion bar will cost $7,020 for required parts; no 
additional labor is necessary.

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):

2016-07-27 Airbus Helicopters (formerly Eurocopter France): 
Amendment 39-18472; Docket No. FAA-2015-5914; Directorate Identifier 
2014-SW-056-AD.

[[Page 21715]]

(a) Applicability

    This AD applies to Model SA341G and SA342J helicopters with a 
main rotor head torsion bar (torsion bar) part number 704A33633274 
installed, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in the coating 
of the torsion bar resulting in corrosion. This condition could 
result in failure of a torsion bar, loss of a main rotor blade, and 
subsequent loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective May 18, 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) For each torsion bar with less than 5 years since the first 
date of installation on any helicopter, within the compliance time 
shown in Table 1 to paragraph (e)(1) of this AD:
    (i) Remove the torsion bar and, using a magnifying glass with a 
maximum magnification level of 10X, visually inspect for a crack in 
the polyurethane (PU) coating of the torsion bar as depicted in 
Figure 1 of Gazelle Inspection--Check 65.12.607, ``Main Rotor Head: 
Torsion Tie-Back Check (Post MOD 076171),'' dated August 2008, of 
the Eurocopter Gazelle Helicopter Maintenance Manual, Tome 1. This 
type of task is commonly called a ``work card'' and will be 
referenced in this AD as ``the work card.'' Consider two cracks that 
are less than 5 mm (.196 in) apart as a single crack. If there is a 
crack in the PU coating that is more than 5 mm (.196 in), replace 
the torsion bar before further flight. Do not rework the PU coating 
of the torsion bar in any way.
    (ii) Inspect the angle, dimension alpha, as depicted in View on 
Arrow F of Figure 1 of the work card. If the angle is 7 or more 
degrees, replace the torsion bar before further flight.
    (iii) Inspect each bushing for corrosion on the inside diameter. 
If any corrosion cannot be removed by rubbing it with an abrasive 
pad, replace the torsion bar before further flight.
    (iv) Using an outside micrometer, measure the thickness, 
dimension a, of each bushing as depicted in Detail AA of Figure 1 of 
the work card. If the thickness is less than 37.520 mm (1.477 in), 
replace the torsion bar before further flight.
    (v) Using an inside micrometer, measure the inside diameter, 
dimension b, of each bushing as depicted in Detail AA of Figure 1 of 
the work card. If the diameter is larger than 21.040 mm (.828 in), 
replace the torsion bar before further flight.
    (vi) Inspect the two faces of each bushing for missing varnish. 
If varnish is missing from more than 15% of the surface area on a 
face of a bushing, before further flight, remove all varnish using 
400-grit abrasive paper. Finish with an abrasive pad and apply a 
coat of P05 paint to the face of the bushing.

                       Table 1 to Paragraph (e)(1)
------------------------------------------------------------------------
    Time accumulated on torsion bar              Compliance time
------------------------------------------------------------------------
(i) Less than 320 hours time-in-service  Before accumulating 420 hours
 (TIS) since new and has never been       TIS since new or within 24
 inspected in accordance with Airbus      months since the date of first
 Helicopters 341G--342J Airworthiness     installation on any
 Limitations, Revision 18, dated June     helicopter, whichever occurs
 2014 (limitations inspection).           first.
(ii) 320 or more hours TIS since new     Within 100 hours TIS, or before
 and has never had a limitations          accumulating 600 hours TIS
 inspection.                              since new, or within 24 months
                                          since the date of first
                                          installation on any
                                          helicopter, whichever occurs
                                          first.
(iii) Less than 320 hours TIS since the  Before accumulating 420 hours
 last limitations inspection.             TIS since the last limitations
                                          inspection or within 24 months
                                          since the last limitations
                                          inspection, whichever occurs
                                          first.
(iv) 320 or more hours TIS since the     Within 100 hours TIS, or before
 last limitations inspection.             accumulating 600 hours TIS
                                          since the last limitations
                                          inspection, or within 24
                                          months since the last
                                          limitations inspection,
                                          whichever occurs first.
------------------------------------------------------------------------

    (2) For each torsion bar with 5 or more years since the first 
date of installation on any helicopter, within the compliance time 
shown in Table 2 to paragraph (e)(2) of this AD, do the inspections 
required by paragraphs (e)(1)(i) through (vi) of this AD.

                       Table 2 to Paragraph (e)(2)
------------------------------------------------------------------------
    Time accumulated on torsion bar              Compliance time
------------------------------------------------------------------------
(i) Less than 320 hours TIS since new,   Before accumulating 420 hours
 and less than 6 months since the date    TIS since new or within 12
 of first installation on any             months since the date of first
 helicopter, and has never had a          installation on any
 limitations inspection.                  helicopter, whichever occurs
                                          first.
(ii) 320 or more hours TIS since new or  Within 100 hours TIS, or within
 more than 6 months since the date of     6 months, or before
 first installation on any helicopter,    accumulating 600 hours TIS
 and has never had a limitations          since new, or within 24 months
 inspection.                              since the date of first
                                          installation on any
                                          helicopter, whichever occurs
                                          first.
(iii) Less than 320 hours TIS since      Before accumulating 420 hours
 last limitations inspection and less     TIS since last limitations
 than 6 months since the last             inspection or 12 months since
 limitations inspection.                  last limitations inspection,
                                          whichever occurs first.
(iv) 320 or more hours TIS since last    Within 100 hours TIS, or within
 limitations inspection or 6 or more      6 months, or before
 months since the last limitations        accumulating 600 hours TIS
 inspection.                              since the last limitations
                                          inspection, or within 24
                                          months since the last
                                          limitations inspection,
                                          whichever occurs first.
------------------------------------------------------------------------

    (3) Repeat the inspections required by paragraphs (e)(1)(i) 
through (vi) of this AD as follows:
    (i) For torsion bars with less than 6 years since the date of 
installation on any helicopter, at intervals not to exceed 420 hours 
TIS or 24 months, whichever occurs first.
    (ii) For torsion bars with 6 or more years since the date of 
installation on any helicopter, at intervals not to exceed 420 hours 
TIS or 12 months, whichever comes first.

(f) 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

[[Page 21716]]

Worth, TX 76177; telephone (817) 222-5110; 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

    (1) Airbus Helicopters Alert Service Bulletin ASB No. SA341/
SA342-05.40, Revision 0, dated April 28, 2014, which is not 
incorporated by reference, contains additional information about the 
subject of this final rule. For Airbus Helicopters 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 a copy of the 
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. 2014-0216, dated September 24, 2014. You 
may view the EASA AD on the Internet at http://www.regulations.gov 
in Docket No. FAA-2015-5914.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6700, Main Rotor.

(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.
    (i) Gazelle Inspection--Check 65.12.607, ``Main Rotor Head: 
Torsion Tie-Back Check (Post MOD 076171),'' dated August 2008, of 
the Eurocopter Gazelle Helicopter Maintenance Manual, Tome 1.
    (ii) Reserved.
    (3) For Eurocopter 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.
    (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 March 31, 2016.
James A. Grigg,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-07979 Filed 4-12-16; 8:45 am]
 BILLING CODE 4910-13-P