[Federal Register Volume 86, Number 111 (Friday, June 11, 2021)]
[Rules and Regulations]
[Pages 31101-31103]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-12228]



[[Page 31101]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0113; Product Identifier 2017-SW-140-AD; Amendment 
39-21584; AD 2021-11-22]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters Deutschland GmbH 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2016-11-21 
for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model 
EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and EC135T2+ helicopters. 
AD 2016-11-21 required revising the life limit of certain parts and 
removing each part that has reached its life limit. This AD continues 
to require revising the life limits for certain parts and removing each 
part that has reached or exceeded its life limit and expands the 
applicability to include Model EC135P3 and EC135T3 helicopters. This AD 
was prompted by the certification of new helicopter models since AD 
2016-11-21 was issued. The FAA is issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective July 16, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of July 16, 
2021.

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 
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. It is also available at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0113.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2019-0113; 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 
European Aviation Safety Agency (now European Union Aviation Safety 
Agency) (EASA) AD, any service information that is incorporated by 
reference, 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: Matt Fuller, AD Program Manager, 
Operational Safety Branch, Airworthiness Products Section, General 
Aviation & Rotorcraft Unit, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 
76177; telephone 817-222-5110; email matthew.fuller@faa.gov.

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2016-11-21, Amendment 39-18548 (81 FR 
36137, June 6, 2016), (AD 2016-11-21) which applied to Airbus 
Helicopters Model EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and 
EC135T2+ helicopters. The NPRM published in the Federal Register on 
March 8, 2021 (86 FR 13237). In the NPRM, the FAA proposed to require, 
before further flight, establishing a life limit for the tail rotor hub 
body of 27,400 hours time-in-service (TIS) or using Airbus Helicopters 
service information if the history of the tail rotor hub body is not 
known or cannot be identified. The NPRM also proposed to require 
establishing life limits for certain swashplate and mixing lever gear 
unit parts in the Airworthiness Limitations Section (ALS) of the 
existing maintenance manual for your helicopter, and recording the 
revised life limit on the component history card or equivalent record. 
Additionally, the NPRM proposed to require continuing to record the 
life limit of certain parts that have not reached their life limit. 
Finally, the NPRM proposed to require removing from service any part 
that reached or exceeded its life limit.
    The NPRM was prompted by EASA AD 2017-0243, dated December 6, 2017 
(EASA AD 2017-0243), issued by EASA, which is the Technical Agent for 
the Member States of the European Union, to correct an unsafe condition 
Airbus Helicopters Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, 
EC135T2, EC135T2+, EC135T3, EC635P2+, EC635P3, EC635T1, EC635T2+, and 
EC635T3 helicopters. EASA AD 2017-0243 superseded EASA AD 2013-0178, 
dated August 7, 2013 (EASA AD 2013-0178), which was prompted by Airbus 
Helicopters revising the airworthiness limitations for the Model EC135 
and EC635 helicopters' type design as published in the Master Servicing 
Manual (MSM) EC135 Chapter 04--ALS documents. Revision 14 of the MSM 
contains these new airworthiness limitations. EASA stated that failure 
to comply with these limitations could result in failure of a critical 
part, which could result in loss of control of the helicopter. 
Accordingly, EASA AD 2013-0178 required revising the ALS to include the 
new life limits and replacing each part that has reached its life 
limit. Superseding EASA AD 2017-0243 expands the applicability to 
include Airbus Helicopters Model EC135P3, EC135T3, EC635P3, and EC635T3 
helicopters. New life limits were also added for some parts.

Comments

    The FAA received comments from one commenter. The following 
presents the comments received on the NPRM and the FAA's response.
    The individual commented that the NPRM sets the life limit for the 
hinged support part number (P/N) L671M7003210 at 8,400 hours TIS but 
that the life limit of this component is at 19,000 hours per ALS Rev 01 
chapter 04-10-00. The individual also commented that the NPRM sets the 
life limit for the bolt P/N L671M7001220 at 8,400 hours TIS but that 
the life limit of this component is at 19,000 hours per ALS Rev 01 
chapter 04-10-00. The FAA agrees and has changed this AD to the revise 
the life limit to 19,000 hours TIS for the hinged support and the bolt.

Conclusion

    These helicopters have been approved by EASA and are approved for 
operation in the United States. Pursuant to the FAA's bilateral 
agreement with the European Union, EASA has notified the FAA about the 
unsafe condition described in its AD. The FAA reviewed the relevant 
data, considered the comments received, and determined that air safety 
requires adopting this AD as proposed except for increasing the life 
limit for the hinged support and bolt. These changes will neither 
increase the scope of the AD nor increase the economic burden on any 
operator. Accordingly, the FAA is issuing this AD to address the unsafe 
condition on these helicopters.

[[Page 31102]]

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Airbus Helicopters Alert Service Bulletin ASB 
EC135-04A-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 type-certificated. The EASA AD requires 
revising the Aircraft Maintenance Program with new or revised life 
limitations within 12 months after the EASA AD's 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.

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 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 (AD) 2016-11-21, Amendment 39-18548 
(81 FR 36137, June 6, 2016); and
0
b. Adding the following new AD:

2021-11-22 Airbus Helicopters Deutschland GmbH: Amendment 39-21584; 
Docket No. FAA-2019-0113; Product Identifier 2017-SW-140-AD.

(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.

(c) Affected ADs

    This AD replaces AD 2016-11-21, Amendment 39-18548 (81 FR 36137, 
June 6, 2016).

(d) Effective Date

    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 body's 
TIS, follow the instructions in Table 1, Examples and Calculations, 
Effectivity: The history of the hub body is not known or can't be 
identified, in Airbus Helicopters Alert Service Bulletin ASB EC135-
04A-012, 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 (f)(2)(i) 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 (two-part), 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 (f)(1) and (2) of this AD that has reached or exceeded 
its revised life limit.
    (4) Thereafter, for any part listed in paragraphs (f)(1) 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 (f)(1) 
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.

[[Page 31103]]

(h) 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 (i)(1) of 
this AD. Information may be emailed to: 9-AVS-AIR-730-AMOC@faa.gov.
    (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.

(i) Additional Information

    (1) For more information about this AD, contact Matt Fuller, AD 
Program Manager, Operational Safety Branch, Airworthiness Products 
Section, General Aviation & Rotorcraft Unit, FAA, 10101 Hillwood 
Pkwy., Fort Worth, TX 76177; telephone 817-222-5110; email 
matthew.fuller@faa.gov.
    (2) The subject of this AD is addressed in European Aviation 
Safety Agency (now European Union Aviation Safety Agency) (EASA) AD 
2017-0243, dated December 6, 2017. You may view the EASA AD at 
https://www.regulations.gov in Docket No. FAA-2019-0113.

(j) Subject

    Joint Aircraft Service Component (JASC) Code: 6400, Tail Rotor 
System.

(k) 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) Airbus Helicopters Alert Service Bulletin ASB EC135-04A-012, 
Revision 0, dated September 11, 2017.
    (ii) [Reserved]
    (3) For Airbus Helicopters service information identified in 
this AD, 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 https://www.airbus.com/helicopters/services/technical-support.html.
    (4) 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.
    (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, email: fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on May 21, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2021-12228 Filed 6-10-21; 8:45 am]
BILLING CODE 4910-13-P


