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Federal Register / Vol. 86, No. 111 / Friday, June 11, 2021 / Rules and Regulations
Related Service Information Under 1
CFR Part 51
The FAA reviewed Airbus Helicopters Alert Service Bulletin ASB EC13504A
012, Revision 0, dated September 11, 2017, which specifies incorporating life limits for the tail rotor hub body into the tail rotor hub log card and into the list of life-limited parts. Airbus Helicopters reports the addition of the tail rotor hub body into the tail rotor hub log card was prompted by a new, recently manufactured, serial-numbered hub.
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.
Differences Between This AD and the EASA AD
The EASA AD applies to Model EC635P2+, EC635P3, EC635T2+, and EC635T3 helicopters, whereas this AD
does not because these model helicopters are not FAA typecertificated. The EASA AD requires revising the Aircraft Maintenance Program with new or revised life limitations within 12 months after the EASA ADs effective date. This AD
requires revising the life limit for certain parts in the ALS of the existing maintenance manual for your helicopter before further flight.

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Costs of Compliance The FAA estimates that this AD
affects 272 helicopters of U.S. Registry.
The FAA estimates that operators may incur the following costs in order to comply with this AD. Labor costs are estimated at $85 per work-hour.
Revising the component history card or equivalent record will take about 2
work-hours, for an estimated cost of $170 per helicopter and $46,240 for the U.S. fleet.
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 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
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that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.

c Affected ADs
Regulatory Findings
d Effective Date
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 AD 20161121, Amendment 39
18548 81 FR 36137, June 6, 2016; and b. Adding the following new AD:

20211122 Airbus Helicopters Deutschland GmbH: Amendment 39
21584; Docket No. FAA20190113;
Product Identifier 2017SW140AD.
a Applicability This airworthiness directive AD applies Airbus Helicopters Deutschland GmbH
Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters, certificated in any category.
b Unsafe Condition The FAA is issuing this AD to prevent certain parts from remaining in service beyond their fatigue life, resulting in failure of the part and subsequent loss of control of the helicopter.

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This AD replaces AD 20161121, Amendment 3918548 81 FR 36137, June 6, 2016.
This AD is effective July 16, 2021.
e 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.
f Required Actions 1 Before further flight, establish a life limit for the tail rotor hub body hub body, part number P/N L642A2003102, of 27,400
hours time-in-service TIS. If you cannot determine the hub bodys TIS, follow the instructions in Table 1, Examples and Calculations, Effectivity: The history of the hub body is not known or cant be identified, in Airbus Helicopters Alert Service Bulletin ASB EC13504A012, Revision 0, dated September 11, 2017, except where the service information specifies that you contact the manufacturer, you are required to remove the part from service instead.
2 Before further flight, revise the life limit for each part listed in paragraphs f2i and ii of this AD in the Airworthiness Limitations Section ALS of the existing maintenance manual for your helicopter and record the revised life limit on the component history card or equivalent record as follows:
i For swashplate parts:
A The life limit for the ring control ring, P/N L623M2001213, is 10,700 hours TIS.
B The life limit for the cardan ring twopart, P/N L623M2005205, is 14,300 hours TIS.
C The life limit for the bolt control ring, P/N L671M7001215, is 14,300 hours TIS.
D The life limit for the bolt sliding sleeve, P/N L623M2006206 and P/N
L623M2006213, is 14,300 hours TIS.
ii For mixing lever gear unit parts:
A The life limit for the forked lever assembly, P/N L671M3012102, is 10,400
hours TIS.
B The life limit for the hinged support, P/N L671M7003210, is 19,000 hours TIS.
C The life limit for the bolt, P/N
L671M7001220, is 19,000 hours TIS.
3 Before further flight, remove from service any part listed in paragraphs f1
and 2 of this AD that has reached or exceeded its revised life limit.
4 Thereafter, for any part listed in paragraphs f1 and 2 of this AD that has not reached or exceeded its life limit, continue to record the life limit of the part on its component history card or equivalent record and remove any part listed in paragraphs f1 and 2 of this AD from service before the part has reached or exceeded its revised life limit.
g Special Flight Permits Special flight permits are limited to a onetime flight to a maintenance facility to replace a part that has reached its life limit.

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