[Federal Register Volume 86, Number 126 (Tuesday, July 6, 2021)]
[Rules and Regulations]
[Pages 35387-35389]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-14258]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 

========================================================================


Federal Register / Vol. 86, No. 126 / Tuesday, July 6, 2021 / Rules 
and Regulations

[[Page 35387]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24733; Project Identifier MCAI-2021-00139-R; 
Amendment 39-21642; AD 2021-14-15]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters (Type Certificate 
Previously Held by Eurocopter France) and Eurocopter France Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2002-08-16 
for certain Eurocopter France SA341G, SA342J, and SA-360C helicopters. 
AD 2002-08-16 required removing certain main rotor head torsion tie 
bars (tie bars) from service and revising the limitations section of 
the existing maintenance manual for your helicopter by adding life 
limits for certain other tie bars. This AD was prompted by the 
determination that another part-numbered tie bar is affected by the 
same unsafe condition. This AD continues to require removing certain 
tie bars from service and establishing a life limit for certain other 
tie bars. The FAA is issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective August 10, 2021.

ADDRESSES: For Eurocopter service information identified in this final 
rule, contact Airbus Helicopters, 2701 North Forum Drive, Grand 
Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax 
(972) 641-3775; or at https://www.airbus.com/helicopters/services/technical-support.html. You may view this service information at the 
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.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2006-24733; or in person at 
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The AD docket contains this final rule, the 
Direction Generale De L'Aviation Civile (DGAC) ADs, any comments 
received, and other information. The address for Docket Operations is 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Hal Jensen, Aerospace Engineer, 
Operational Safety Branch, Compliance & Airworthiness Division, FAA, 
950 L'Enfant Plaza N SW, Washington, DC 20024; telephone (202) 267-
9167; email <a href="/cdn-cgi/l/email-protection#adc5ccc183c7c8c3dec8c3edcbcccc83cac2db"><span class="__cf_email__" data-cfemail="432b222f6d29262d30262d032522226d242c35">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a supplemental notice of proposed rulemaking (SNPRM) 
to amend 14 CFR part 39 to supersede AD 2002-08-16 (67 FR 19640, April 
23, 2002) (AD 2002-08-16). AD 2002-08-16 applied to Eurocopter France 
Model SA341G, SA342J, and SA-360C helicopters with a tie bar part 
number (P/N) 341A31-4904-00, -01, -02, -03; 341A31-4933-00, -01; or 
360A31-1097-02, -03, installed. The SNPRM published in the Federal 
Register on May 20, 2021 (86 FR 27323). The FAA preceded the SNPRM with 
a notice of proposed rulemaking (NPRM) that published in the Federal 
Register on May 10, 2006 (71 FR 27215). The SNPRM proposed to continue 
to require removing tie bar P/Ns 341A31-4904-00, -01, -02, and -03; and 
360A31-1097-02 and -03 from service. The SNPRM also proposed to 
prohibit installing those part-numbered tie bars on any helicopter. The 
SNPRM proposed to initially require removing tie bar P/Ns 341A31-4933-
00 and -01; and 704A33-633-270 from service if they have accumulated or 
exceeded the specified life limit, and thereafter removing those part-
numbered tie bars from service before accumulating the specified life 
limit.
    The SNPRM was prompted by a significant amount of time that had 
elapsed since issuance of the NPRM that required the FAA to reopen the 
comment period to allow the public a chance to comment on the proposed 
actions. Additional review also revealed necessary changes to address 
the unsafe condition. The SNPRM proposed to clarify that the compliance 
times of requirements continued from AD 2002-08-16 are effective after 
the effective date of AD 2002-08-16, clarify instances of life limits 
specified in calendar time that they are since initial installation of 
the tie bar on any helicopter, clarify one instance of a life limit 
that it is total hours time-in-service (TIS) or calendar time--
whichever occurs first, and add parts installation prohibitions. The 
SNPRM also updated the AD format. As a result, paragraph identifiers 
changed, editorial changes were made to meet current publishing 
requirements, and the proposed requirements were revised by removing 
unnecessary information.
    The NPRM was prompted by DGAC AD 2001-587-041(A) R2, dated January 
8, 2003 (DGAC AD 2001-587-041(A) R2), issued by the DGAC, which was the 
Technical Agent for France, to correct an unsafe condition for Model SA 
341/342 helicopters. The DGAC advised of another affected tie-bar P/N 
704A33-633-270 and additional flight restrictions for the newly-
affected tie bar. This condition, if not addressed, could result in 
failure of a tie bar and subsequent loss of control of the helicopter. 
Accordingly, DGAC AD 2001-587-041(A) R2, along with DGAC AD 2001-588-
047(A) R1, dated December 26, 2001 (DGAC AD 2001-588-047(A) R1), for 
Model SA 360 helicopters, require removing certain part-numbered tie 
bars from service and a life limit for certain other part-numbered tie 
bars.

Discussion of Final Airworthiness Directive

Comments

    The FAA received no comments on the SNPRM or on the determination 
of the costs.

Conclusion

    These helicopters have been approved by the European Union Aviation 
Safety

[[Page 35388]]

Agency (EASA) and are approved for operation in the United States. 
Pursuant to the FAA's bilateral agreement with the European Union, the 
FAA has been notified about the unsafe condition described in the DGAC 
ADs. The FAA reviewed the relevant data and determined that air safety 
requires adopting this AD as proposed. Accordingly, the FAA is issuing 
this AD to address the unsafe condition on these helicopters.

Related Service Information

    The FAA reviewed Eurocopter Alert Service Bulletin No. 01.29, 
Revision 0, dated December 4, 2002, and Eurocopter Alert Telex No. 
01.39, Revision 1, dated December 11, 2001. This service information 
specifies removing certain part-numbered tie bars at specified life 
limits.

Differences Between This AD and the DGAC ADs

    For an affected tie bar that has accumulated 7 or more years since 
initial installation on any helicopter, DGAC AD 2001-587-041(A) R2 
requires removing the tie bar before next flight, whereas this AD 
allows removal within 5 hours TIS instead.
    For an affected tie bar that has accumulated 15 or more years since 
initial installation on any helicopter, DGAC AD 2001-588-047(A) R1 
requires removing the tie bar before next flight, whereas this AD does 
not. For an affected tie bar that has accumulated 7 or more years since 
initial installation on any helicopter, DGAC AD 2001-588-047(A) R1 
requires removing the tie bar before next flight, whereas this AD 
allows removal within 5 hours TIS instead. DGAC AD 2001-588-047(A) R1 
allows a ferry flight not to exceed 5 hours to return the helicopter to 
a maintenance base, where as special flight permits are prohibited by 
this AD.

Costs of Compliance

    The FAA estimates that this AD affects 29 helicopters of U.S. 
Registry. Labor rates are estimated at $85 per work-hour. Based on 
these numbers, the FAA estimates the following costs to comply with 
this AD.
    Replacing a tie bar takes about 1.5 work-hours and parts cost about 
$9,579 for an estimated cost of $9,707 per tie bar.

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.
    The FAA is 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

    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) Will not affect intrastate aviation in Alaska, and
    (3) 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

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:
0
a. Removing Airworthiness Directive 2002-08-16, Amendment 39-12725 (67 
FR 19640, April 23, 2002); and
0
b. Adding the following new airworthiness directive:

2021-14-15 Airbus Helicopters (Type Certificate Previously Held by 
Eurocopter France) and Eurocopter France: Amendment 39-21642; Docket 
No. FAA-2006-24733; Project Identifier MCAI-2021-00139-R.

(a) Effective Date

    This airworthiness directive (AD) is effective August 10, 2021.

(b) Affected ADs

    This AD replaces AD 2002-08-16, Amendment 39-12725 (67 FR 19640, 
April 23, 2002) (AD 2002-08-16).

(c) Applicability

    This AD applies to Airbus Helicopters (type certificate 
previously held by Eurocopter France) Model SA341G and SA342J and 
Eurocopter France Model SA-360C helicopters, certificated in any 
category, with a main rotor head torsion tie bar (tie bar), part 
number (P/N) 341A31-4904-00, -01, -02, -03; 341A31-4933-00, -01; 
360A31-1097-02, -03; or 704A33-633-270, installed.

(d) Subject

    Joint Aircraft Service Component (JASC) Code: 6220, Main Rotor 
Head.

(e) Unsafe Condition

    This AD was prompted by an accident caused by the failure of a 
tie bar. The FAA is issuing this AD to prevent failure of a tie bar, 
which if not addressed, could result in loss of a main rotor blade 
and subsequent loss of control of the helicopter.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    (1) For tie bar P/N 341A31-4904-00, -01, -02, and -03; and 
360A31-1097-02 and -03, before further flight after May 8, 2002 (the 
effective date of AD 2002-08-16), remove the tie bar from service.
    (2) For each tie bar P/N 341A31-4933-00 and -01:
    (i) Before further flight after May 8, 2002 (the effective date 
of AD 2002-08-16), determine the date of initial installation on any 
helicopter, or if the date of initial installation cannot be 
determined, use the date of manufacture.
    (A) For a tie bar that has accumulated 7 or more years since 
initial installation on any helicopter, within 5 hours time-in-
service (TIS) after May 8, 2002 (the effective date of AD 2002-08-
16), remove the tie bar from service.
    (B) For a tie bar manufactured before 1995 that has accumulated 
less than 7 years since initial installation on any helicopter, 
before accumulating 7 years since initial installation on any 
helicopter, before accumulating 300 total hours TIS, or within 1 
year after May 8, 2002 (the effective date of AD 2002-08-16), 
whichever occurs first, remove the tie bar from service.
    (C) For a tie bar manufactured in 1995 or later that has 
accumulated less than 7 years since initial installation on any 
helicopter, before accumulating 7 years since initial installation 
on any helicopter, before accumulating 600 total hours TIS, or 
within 2 years after May 8, 2002 (the effective date

[[Page 35389]]

of AD 2002-08-16), whichever occurs first, remove the tie bar from 
service.
    (ii) Thereafter following paragraph (g)(2)(i) of this AD, remove 
any tie bar P/N 341A31-4933-00 and -01 from service as follows:
    (A) For a tie bar manufactured before 1995, remove the tie bar 
from service before accumulating 300 total hours TIS or 1 year since 
initial installation on any helicopter, whichever occurs first, and
    (B) For a tie bar manufactured in 1995 or later, remove the tie 
bar from service before accumulating 600 total hours TIS or 2 years 
since initial installation on any helicopter, whichever occurs 
first.
    (3) For tie bar P/N 704A33-633-270:
    (i) Before further flight after the effective date of this AD, 
determine the date of initial installation on any helicopter, or if 
the date of initial installation cannot be determined, use the date 
of manufacture.
    (ii) If the tie bar has accumulated 600 or more total hours TIS 
or 2 or more years since initial installation on any helicopter, 
whichever occurs first, before further flight, remove the tie bar 
from service.
    (iii) If the tie bar has accumulated less than 600 total hours 
TIS or 2 years since initial installation on any helicopter, 
whichever occurs first, remove the tie bar from service before 
accumulating 600 total hours TIS or 2 years since initial 
installation on any helicopter, whichever occurs first.
    (iv) Thereafter following paragraph (g)(3)(ii) or (iii) of this 
AD, remove any tie bar P/N 704A33-633-270 from service before 
accumulating 600 total hours TIS or 2 years since initial 
installation on any helicopter, whichever occurs first.
    (4) As of the effective date of this AD, do not install tie bar 
P/N 341A31-4904-00, -01, -02, or -03; or 360A31-1097-02 or -03, on 
any helicopter.

(h) Special Flight Permits

    Special flight permits are prohibited.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, International Validation Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Validation Branch, send 
it to the attention of the person identified in paragraph (j)(1) of 
this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#efd6c2aeb9bcc2aea6bdc2d8dcdfc2aea2a0acaf898e8ec1888099"><span class="__cf_email__" data-cfemail="d9e0f4988f8af498908bf4eeeae9f49894969a99bfb8b8f7beb6af">[email protected]</span></a>.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(j) Related Information

    (1) For more information about this AD, contact Hal Jensen, 
Aerospace Engineer, Operational Safety Branch, Compliance & 
Airworthiness Division, FAA, 950 L'Enfant Plaza N SW, Washington, DC 
20024; telephone (202) 267-9167; email <a href="/cdn-cgi/l/email-protection#f49c9598da9e919a87919ab4929595da939b82"><span class="__cf_email__" data-cfemail="b6ded7da98dcd3d8c5d3d8f6d0d7d798d1d9c0">[email protected]</span></a>.
    (2) The subject of this AD is addressed in Generale De 
L'Aviation Civile (France) AD 2001-588-047(A) R1, dated December 26, 
2001, and AD 2001-587-041(A) R2, dated January 8, 2003. You may view 
those ADs at https://www.regulations.gov in Docket No. FAA-2006-
24733.

    Issued on June 28, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-14258 Filed 7-2-21; 8:45 am]
BILLING CODE 4910-13-P


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