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Federal Register / Vol. 86, No. 126 / Tuesday, July 6, 2021 / Rules and Regulations
Agency EASA and are approved for operation in the United States. Pursuant to the FAAs 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 2001587041A 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 2001588047A 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 2001588
047A R1 requires removing the tie bar before next flight, whereas this AD
allows removal within 5 hours TIS
instead. DGAC AD 2001588047A 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.

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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 FAAs 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
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detail the scope of the Agencys 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 39AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:

Authority: 49 U.S.C. 106g, 40113, 44701.
39.13

Amended
2. The FAA amends 39.13 by:
a. Removing Airworthiness Directive 20020816, Amendment 3912725 67
FR 19640, April 23, 2002; and b. Adding the following new airworthiness directive:

20211415 Airbus Helicopters Type Certificate Previously Held by Eurocopter France and Eurocopter France: Amendment 3921642; Docket
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No. FAA200624733; Project Identifier MCAI202100139R.
a Effective Date This airworthiness directive AD is effective August 10, 2021.
b Affected ADs This AD replaces AD 20020816, Amendment 3912725 67 FR 19640, April 23, 2002 AD 20020816.
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 341A31490400, 01, 02, 03; 341A31493300, 01;
360A31109702, 03; or 704A33633270, 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 341A31490400, 01, 02, and 03; and 360A31109702 and 03, before further flight after May 8, 2002 the effective date of AD 20020816, remove the tie bar from service.
2 For each tie bar P/N 341A31493300
and 01:
i Before further flight after May 8, 2002
the effective date of AD 20020816, 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 20020816, 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 200208
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
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