Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters, 82305-82307 [2020-27808]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 85, Number 244 (Friday, December 18, 2020)]
[Rules and Regulations]
[Pages 82305-82307]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-27808]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0572; Product Identifier 2017-SW-056-AD; Amendment 
39-21358; AD 2020-26-03]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters Deutschland GmbH 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2007-26-51 
which applied to certain Airbus Helicopters Deutschland GmbH Model 
EC135 helicopters. AD 2007-26-51 required inspecting the tail rotor 
control rod (control rod) and ball pivot and, depending on findings, 
replacing those parts. This new AD requires inspecting certain ball 
pivots, applying corrosion preventative compound on the ball pivot, and 
corrective action, as applicable. This AD also requires replacing the 
control rod with a newly developed control rod. This AD was prompted by 
the manufacturer's development of a new control rod, which the FAA has 
determined must be installed in order to address the identified unsafe 
condition. The actions of this AD are intended to address an unsafe 
condition on these products.

DATES: This AD is effective January 22, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 22, 
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. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0572.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov in Docket No. FAA-2020-0572; 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 AD, 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 street 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: David Hatfield, Aviation Safety 
Engineer, Aircraft Systems Section, Technical Innovation Policy Branch, 
FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-
5116; email [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to remove AD 2007-26-51, Amendment 39-15357 (73 FR 6008, 
February 1, 2008) (AD 2007-26-51), and add a new AD. AD 2007-26-51 
applied to certain Airbus Helicopters Deutschland GmbH (type 
certificate previously held by Eurocopter Deutschland GmbH) Model EC135 
helicopters, serial number (S/N) 0005 up to and including S/N 0444, 
except S/N 0028, and with control rod part number (P/N) L672M2005207, 
installed. The NPRM was published in the Federal Register on June 18, 
2020 (85 FR 36816). The NPRM proposed to require inspecting certain 
ball pivots for damage and freedom of movement, applying corrosion 
preventative compound on the ball pivot, and corrective action, as 
applicable. The NPRM also proposed to require replacing the control rod 
with the newly developed control rod that the FAA determined was 
necessary to address the unsafe condition.
    The NPRM was prompted by EASA AD No. 2010-0227R1, dated April 7, 
2017 (referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''), issued by EASA, which is the Technical 
Agent for the Member States of the European Union, to correct an unsafe 
condition for all Model EC135 P1, EC135 P2, EC135 P2+, EC135 T1, EC 135 
T2, and EC135 T2+ helicopters; and Model EC635 T1, EC635 P2+, and EC635 
T2+ helicopters. EASA advises that in 2007 an accident occurred on an 
EC135 helicopter in Japan. Preliminary investigation results indicated 
that loss of control was due to failure of the control rod. EASA issued 
EASA Emergency AD 2007-0301-E, dated December 13, 2007 (EASA AD 2007-
0301-E) to inspect the affected control rod P/N L672M2005207 and the 
ball pivot (which correspond to the actions required by AD 2007-26-51). 
EASA AD 2007-0301-E was subsequently superseded by EASA AD 2007-0313, 
dated December 21, 2007, to require repetitive inspections and, 
depending on findings, the replacement of the control rod and ball 
pivot, only for helicopters not equipped with an automatic flight 
control system (AFCS). After review of the inspection results, EASA 
issued EASA AD 2008-0064, dated April 4, 2008, and later revised to 
EASA AD 2008-0064 R1, dated April 15, 2008 (EASA AD 2008-0064 R1), to 
apply the requirements to helicopters equipped with an AFCS.
    EASA also advises that after EASA AD 2008-0064R1 was issued, 
Eurocopter Deutschland GmbH developed a new control rod P/N 
L672M2006101, installation of which constituted terminating action for 
the repetitive inspections. Consequently, EASA issued EASA AD 2010-
0227, dated November 3, 2010, and corrected November 8, 2010, retaining 
the requirements of EASA AD 2008-0064R1, and requiring the replacement 
of control rod P/N L672M2005207 with the new control rod P/N 
L672M2006101. The FAA has determined that this new control rod must be 
installed in order to address the unsafe condition.
    In addition, EASA advises that following a review of data and 
feedback received from in-service helicopters, it

[[Page 82306]]

has been determined that the repetitive inspections of the ball pivot 
are no longer required to address the unsafe condition. The repetitive 
inspections of the ball pivot are now included in Chapter 05 of the 
aircraft maintenance manual. Therefore, EASA issued EASA AD 2010-0227R1 
to remove the requirement for repetitive inspections of the control rod 
and of the ball pivot.
    You may examine the MCAI in the AD docket on the internet at 
https://www.regulations.gov by searching for and locating Docket No. 
FAA-2020-0572.

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule, but the FAA did not receive any comments on 
the NPRM or on the determination of the cost to the public.

FAA's Determination

    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 of the 
unsafe condition described in its AD. The FAA is issuing this AD after 
evaluating all of the information provided by EASA and determining the 
unsafe condition exists and is likely to exist or develop on other 
helicopters of the same type designs and that air safety and the public 
interest require adopting the AD requirements as proposed.

Differences Between This AD and the MCAI or Service Information

    The MCAI includes a compliance time of 50 flight hours for the 
inspection of a certain ball pivot; 100 flight hours or 43 days for the 
inspection of a certain other ball pivot; and 400 flight hours or 12 
months for the replacement of the control rod. This AD requires all 
actions be accomplished within 50 hours time-in-service.
    The MCAI applies to Airbus Helicopters Deutschland GmbH Model EC635 
T1, EC635 P2+, and EC635 T2+ helicopters. Model EC635 T1, EC635 P2+, 
and EC635 T2+ helicopters are not certified by the FAA and are not 
included on the U.S. type certificate data sheet except where the U.S. 
type certificate data sheet explains that the Model EC635T2+ helicopter 
having serial number 0858 was converted from Model EC635T2+ to Model 
EC135T2+; this AD therefore does not include those Model EC 635 
helicopters in the applicability.
    Additionally, although the MCAI and service information specify to 
contact the manufacturer, this AD does not include that requirement.

Related Service Information Under 1 CFR Part 51

    Airbus Helicopters has issued Alert Service Bulletin ASB EC135-67A-
017, Revision 4, dated April 3, 2017, including the Appendix 
(watermarked as Appendix to SB EC135-67A-017 Revision 4). This service 
information describes procedures for, among other actions, an 
inspection of ball pivots, P/Ns 92-201-00 and 92-207-00, for freedom of 
movement, and for damage (e.g., cracks, missing hardware, loose 
bearing, or play), application of corrosion preventative compound, and 
corrective actions. Corrective actions include replacing the ball pivot 
and the control rod with serviceable parts, and applying corrosion 
preventative compound.
    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

    Eurocopter has issued Service Bulletin EC135-67-018, Revision 01, 
dated May 15, 2008, which describes procedures for replacing the 
control rod having P/N L672M2005207 with a control rod having P/N 
L672M2006101.
    Eurocopter has also issued Alert Service Bulletin EC135-67A-017, 
Revision 03, dated July 26, 2010, which describes procedures for ball 
pivot inspections and replacements.

Costs of Compliance

    The FAA estimates that this AD affects 311 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.
    Inspecting the ball pivot takes about 1 work-hour, for an estimated 
cost of $85 per helicopter and $26,435 for the U.S. fleet. If 
applicable, applying corrosion preventative compound takes a minimal 
amount of additional time for a nominal cost.
    Replacing the control rod takes about 3 work-hours, and parts cost 
about $800 for an estimated cost of $1,055 per helicopter and $328,105 
for the U.S. fleet.
    Replacing the control rod and ball pivot takes up to about 6 work-
hours, and parts cost up to about $2,150 for an estimated cost of up to 
$2,660 per helicopter.

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

    The FAA has determined that 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.

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:
0
a. Removing Airworthiness Directive (AD) 2007-26-51, Amendment 39-

[[Page 82307]]

15357 (73 FR 6008, February 1, 2008), and
0
b. Adding the following new AD:

2020-26-03 Airbus Helicopters Deutschland GmbH: Amendment 39-21358; 
Docket No. FAA-2020-0572; Product Identifier 2017-SW-056-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective January 22, 
2021.

(b) Affected ADs

    This AD replaces AD 2007-26-51, Amendment 39-15357 (73 FR 6008, 
February 1, 2008) (AD 2007-26-51).

(c) Applicability

    This AD applies to Airbus Helicopters Deutschland GmbH Model 
EC135P1, EC135T1, EC135P2, EC135T2, EC135P2+, EC135T2+, EC135P3, and 
EC135T3 helicopters, certificated in any category, all serial 
numbers.

(d) Subject

    Joint Aircraft Service Component (JASC) Code: 6700, Rotorcraft 
Flight Control.

(e) Reason

    This AD was prompted by an accident involving the failure of a 
tail rotor control rod. The FAA is issuing this AD to address 
failure of a tail rotor control rod and subsequent loss of control 
of the helicopter.

(f) 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.

(g) Definitions

    (1) Group 1: Helicopters that, on the effective date of this AD, 
have a tail rotor control rod installed having part number (P/N) 
L672M2005207.
    (2) Group 2: Helicopters that, on the effective date of this AD, 
do not have a tail rotor control rod installed having P/N 
L672M2005207.

(h) Ball Pivot Inspection

    Within 50 hours time-in-service after the effective date of this 
AD: Inspect the ball pivot, P/N 92-201-00 and P/N 92-207-00, for 
damage and freedom of movement, in accordance with step 3.C.(3) or 
step 3.D.(3), as applicable, of the Accomplishment Instructions of 
the Appendix (watermarked as Appendix to SB EC135-67A-017 Revision 
4) to Airbus Helicopters Alert Service Bulletin ASB EC135-67A-017, 
Revision 4, dated April 3, 2017. For purposes of this inspection, 
damage to the ball pivot may be indicated by cracks, missing 
hardware, loose bearings, or play.

(i) Corrective Action

    If, during the inspection required by paragraph (h) of this AD, 
there is any damage on any ball pivot or the ball pivot cannot be 
moved: Before further flight, replace the ball pivot in accordance 
with step 3.C.(3) or step 3.D.(3), as applicable, of the 
Accomplishment Instructions of the Appendix (watermarked as Appendix 
to SB EC135-67A-017 Revision 4) to Airbus Helicopters Alert Service 
Bulletin ASB EC135-67A-017, Revision 4, dated April 3, 2017, and the 
tail rotor control rod as required by paragraph (j) of this AD.

(j) Tail Rotor Control Rod Replacement

    Group 1: Unless already done as required by paragraph (i) of 
this AD, within 50 hours time-in-service after the effective date of 
this AD, replace the tail rotor control rod having P/N L672M2005207 
with a tail rotor control rod having P/N L672M2006101.
    Note 1 to paragraph (j): Guidance for replacing the tail rotor 
control rod can be found in Eurocopter Service Bulletin EC135-67-
018, Revision 01, dated May 15, 2008.

(k) Parts Installation Prohibition

    (1) Group 1: After modification of a helicopter as required by 
paragraphs (i) or (j) of this AD, no person may install on any 
helicopter a tail rotor control rod having P/N L672M2005207.
    (2) Group 2: As of the effective date of this AD, no person may 
install on any helicopter a tail rotor control rod having P/N 
L672M2005207.

(l) Credit for Previous Actions

    This paragraph provides credit for the inspection and ball pivot 
replacements required by paragraphs (h) and (i) of this AD, if those 
actions were performed before the effective date of this AD using 
Eurocopter Alert Service Bulletin EC135-67A-017, Revision 03, dated 
July 26, 2010.

(m) Special Flight Permit

    Special flight permits, as described in 14 CFR 21.197 and 
21.199, are not allowed.

(n) No Reporting Requirement

    Although the Appendix (watermarked as Appendix to SB EC135-67A-
017 Revision 4) to Airbus Helicopters Alert Service Bulletin ASB 
EC135-67A-017, Revision 4, dated April 3, 2017, specifies to contact 
the manufacturer, this AD does not include that requirement.

(o) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Strategic Policy Rotorcraft, FAA, may approve 
AMOCs for this AD. Send your proposal to: David Hatfield, Aviation 
Safety Engineer, Aircraft Systems Section, Technical Innovation 
Policy Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; 
telephone 817-222-5116; email [email protected].
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, the FAA suggests 
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.

(p) Related Information

    (1) The subject of this AD is addressed in European Aviation 
Safety Agency (now European Union Aviation Safety Agency) (EASA) AD 
No. 2010-0227R1, dated April 7, 2017. This EASA AD may be found in 
the AD docket on the internet at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2020-0572.
    (2) For 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. 
You may view 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.

(q) 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 EC135-67A-017, 
Revision 4, dated April 3, 2017.
    (ii) [Reserved]
    (3) For 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 [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on December 8, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-27808 Filed 12-17-20; 8:45 am]
BILLING CODE 4910-13-P