[Federal Register Volume 80, Number 148 (Monday, August 3, 2015)]
[Proposed Rules]
[Pages 45900-45902]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-18865]


 ========================================================================
 Proposed Rules
                                                 Federal Register
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
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  Federal Register / Vol. 80, No. 148 / Monday, August 3, 2015 / 
Proposed Rules  

[[Page 45900]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0577; Directorate Identifier 2013-SW-042-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters Deutschland GmbH 
(Previously Eurocopter Deutschland GmbH) (Airbus Helicopters)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to revise airworthiness directive (AD) 2015-12-09 
for Airbus Helicopters Model EC135P1, EC135T1, EC135P2, EC135T2, 
EC135P2+, EC135T2+, and MBB-BK 117 C-2 helicopters. AD 2015-12-09 
currently requires inspecting certain washers for movement and making 
the appropriate repairs if the washers move. As published, AD 2015-12-
09 references an incorrect date for the service information in the 
Credit for Previous Actions section. This proposed AD would correct the 
error while retaining the requirements of AD 2015-12-09. These proposed 
actions are intended to prevent loss of concerned control axis and 
subsequent loss of control of the helicopter.

DATES: We must receive comments on this proposed AD by August 18, 2015.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations Office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the European 
Aviation Safety Agency (EASA) AD, the economic evaluation, any comments 
received and other information. The street address for the Docket 
Operations Office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.
    For service information identified in this proposed AD, contact 
Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; 
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at 
http://www.airbushelicopters.com/techpub. You may review service 
information at the FAA, Office of the Regional Counsel, Southwest 
Region, 10101 Hillwood Pkwy, Room 6N-321, Fort Worth, TX 76177.

FOR FURTHER INFORMATION CONTACT: Matt Wilbanks, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, 
Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; 
telephone (817) 222-5110; email [email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to participate in this rulemaking by submitting 
written comments, data, or views. We also invite comments relating to 
the economic, environmental, energy, or federalism impacts that might 
result from adopting the proposals in this document. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. To 
ensure the docket does not contain duplicate comments, commenters 
should send only one copy of written comments, or if comments are filed 
electronically, commenters should submit only one time.
    We will file in the docket all comments that we receive, as well as 
a report summarizing each substantive public contact with FAA personnel 
concerning this proposed rulemaking. Before acting on this proposal, we 
will consider all comments we receive on or before the closing date for 
comments. We will consider comments filed after the comment period has 
closed if it is possible to do so without incurring expense or delay. 
We may change this proposal in light of the comments we receive.

Discussion

    On June 18, 2015, at 80 FR 34831, the Federal Register published AD 
2015-12-09, Amendment 39-18184, for Airbus Helicopters Model EC135P1, 
EC135T1, EC135P2, EC135T2, EC135P2+, EC135T2+, and MBB-BK 117 C-2 
helicopters. AD 2015-12-09 requires inspecting certain washers for 
movement in the attachment hardware that connects the Smart Electro 
Mechanical Actuator (SEMA) and the control rod of the longitudinal, 
lateral, and yaw actuators. If a washer can be moved, AD 2015-12-09 
requires replacing the four screws, installing two additional washers, 
and torque-tightening the screws. AD 2015-12-09 was prompted by play 
found between the SEMA and the control rod during installation work on 
a helicopter. The requirements of AD 2015-12-09 are intended to prevent 
loss of concerned control axis and subsequent loss of control of the 
helicopter.
    AD 2015-12-09 was prompted by AD No. 2013-0176, dated August 7, 
2013, issued by EASA, which is the Technical Agent for the Member 
States of the European Union, to correct an unsafe condition for 
Eurocopter Deutschland GmbH Model EC 135 P1 (CDS), EC 135 P1 (CPDS), EC 
135 P2+, EC 135 P2 (CPDS), EC 135 T1 (CDS), EC 135 T1 (CPDS), EC 135 
T2+, EC 135 T2 (CPDS), EC 635 P2+, EC 635 T1 (CPDS), EC 635 T2+, and 
MBB-BK 117 C-2 helicopters. EASA advises that during installation work 
on a helicopter, it was discovered that it was not possible to install 
attachment hardware on a threaded blind borehole between the SEMA and 
the control rod without play. EASA advises that this condition, if not 
detected and corrected, could lead to loss of the concerned control 
axis, possibly resulting in loss of helicopter

[[Page 45901]]

control. For these reasons, EASA AD No. 2013-0176 requires a one-time 
inspection of the affected SEMA attachment hardware to detect improper 
connection and play and, depending on the findings, replacement of the 
affected hardware. After the issuance of EASA AD No. 2013-0176, 
Eurocopter Deutschland GmbH changed its name to Airbus Helicopters 
Deutschland GmbH.
    When AD 2015-12-09 was published, an incorrect reference to the 
date of Eurocopter Alert Service Bulletin (ASB) EC135-22A-015, Revision 
0, dated May 13, 2008, appeared in the text of the rule. Specifically, 
AD 2015-12-09 includes the following under paragraph (f), Credit for 
Previous Actions: ``If you performed the actions in Eurocopter Alert 
Service Bulletin EC135-22A-015, Revision 0, dated May 13, 2018, or 
Eurocopter Alert Service Bulletin MBB BK117 C-2-22A-009, Revision 0, 
May 13, 2008, before the effective date of this AD, you met the 
requirements of this AD.'' As published, the reference to May 13, 2018, 
is incorrect. The correct date for Eurocopter ASB EC135-22A-015, 
Revision 0, is May 13, 2008.
    The FAA has determined that it is appropriate to revise AD 2015-12-
09 to correct the date for Eurocopter ASB EC135-22A-015, Revision 0. 
Further, we are changing the physical address of the FAA Southwest 
Regional Office throughout the NPRM and the email address in paragraph 
(g), Alternative Methods of Compliance (AMOCs). Since AD 2015-12-09 was 
issued, the FAA Southwest Regional Office has relocated and a group 
email address has been established for requesting an FAA AMOC for a 
helicopter of foreign design. We are not proposing to change any other 
part of the preamble or regulatory information. The final rule would be 
reprinted in its entirety for the convenience of affected operators.

FAA's Determination

    These helicopters have been approved by the aviation authority of 
Germany and are approved for operation in the United States. Pursuant 
to our bilateral agreement with Germany, EASA, its technical 
representative, has notified us of the unsafe condition described in 
its AD. We are proposing this AD because we evaluated all known 
relevant information and determined that an unsafe condition is likely 
to exist or develop on other products of the same type design.

Related Service Information Under 1 CFR Part 51

    Eurocopter reported in ASBs EC135-22A-015, Revision 1, dated 
January 28, 2013, and MBB BK117 C-2-22A-009, Revision 1, dated August 
3, 2009, that it was discovered during the installation work on a 
helicopter that it was not possible to establish attachment hardware on 
a threaded blind borehole between the SEMA and the control rod without 
play. The ASBs state that ``unfavourable adding of the tolerances'' of 
the individual attachment hardware elements caused the screw to push 
against the bottom of the threaded blind borehole on the SEMA, 
preventing any clamping force on the screw head. The ASBs call for 
inspecting the SEMA attachment hardware connected to their respective 
control rods for play and making the proper adjustments to eliminate 
any play.
    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 of this 
proposed AD.

Proposed AD Requirements

    This proposed AD would continue to require, within 50 hours time-
in-service, inspecting whether the washers can be moved in the 
attachment hardware that connects the SEMA and the control rod of the 
longitudinal, lateral, and yaw actuators. For Model MBB BK117 C-2 
helicopters, this inspection is only for the hardware connecting the 
Yaw-SEMA and the Yaw-SEMA control rod. If none of the washers can be 
moved, then no further action is needed. If a washer can be moved, then 
this proposed AD would require replacing the four screws, installing 
two additional washers, and torque-tightening the screws to 5-6 Nm.

Differences Between This Proposed AD and the EASA AD

    The EASA AD applies to Eurocopter Model EC635P2+, EC635T1 and 
EC635T2+ helicopters. This proposed AD does not apply to these model 
helicopters because they have no FAA type certificate.

Costs of Compliance

    We estimate that this proposed AD would affect 385 helicopters of 
U.S. Registry and that labor costs would average $85 per work-hour. 
Based on these estimates, we expect the following costs:
     Inspecting for movement of the washers would require 1.5 
work-hours for a labor cost of $128 per helicopter and $49,280 for the 
U.S. fleet.
     Replacing the screws and related work would require an 
additional 0.5 work-hours for a labor cost of $43. Screws would cost $4 
each while washers would cost $10 each. We estimate the cost would be 
$79 per repair.

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.
    We are 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

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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, I certify this proposed regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska to the extent that 
it justifies making a regulatory distinction; and
    4. 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.
    We prepared an economic evaluation of the estimated costs to comply 
with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

[[Page 45902]]

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 removing Airworthiness Directive (AD) 
2015-12-09, Amendment 39-18184 (80 FR 34831, June 18, 2015), and adding 
the following new AD:

Airbus Helicopters Deutschland GmbH (Previously Eurocopter 
Deutschland GmbH) (Airbus Helicopters): Docket No. FAA-2014-0577; 
Directorate Identifier 2013-SW-042-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model EC135P1, EC135T1, 
EC135P2, EC135T2, EC135P2+, EC135T2+, and MBB-BK 117 C-2 
helicopters, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as loose attachment 
hardware between the Smart Electro Mechanical Actuator (SEMA) and a 
control rod. This condition could result in loss of the control axis 
and subsequent loss of control of the helicopter.

(c) Comments Due Date

    We must receive comments by August 18, 2015.

(d) 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.

(e) Required Actions

    (1) Within 50 hours time-in-service (TIS), for Model EC135P1, 
EC135T1, EC135P2, EC135T2, EC135P2+, and EC135T2+ helicopters, do 
the following:
    (i) Using Figure 1 and Figure 2 of Eurocopter Alert Service 
Bulletin EC135-22A-015, Revision 1, dated January 28, 2013 (ASB 
EC135-22A-015) as reference, inspect the attachment hardware between 
the SEMA and the longitudinal actuator control rod to determine 
whether any of the washers can be moved.
    (A) If no washer can be moved, no further action is needed.
    (B) If a washer can be moved, replace the four screws and 
install two additional washers, part number (P/N) EN2139-05016, to 
connect the SEMA with the control rod. Torque-tighten each screw to 
5-6 Nm.
    (ii) Using Figure 1 and Figure 2 of ASB EC135-22A-015 as 
reference, inspect the attachment hardware between the SEMA and the 
lateral actuator control rod to determine whether any of the washers 
can be moved.
    (A) If no washer can be moved, no further action is needed.
    (B) If a washer can be moved, replace the four screws and 
install two additional washers, P/N EN2139-05016, to connect the 
SEMA with the control rod. Torque-tighten each screw to 5-6 Nm.
    (iii) Using Figure 1, Figure 3, and Figure 4 of ASB EC135-22A-
015 as reference, inspect the attachment hardware between the SEMA 
and the yaw actuator control rod to determine whether any of the 
washers can be moved.
    (A) If no washer can be moved, no further action is needed.
    (B) If a washer can be moved, replace the four screws and 
install two additional washers, P/N EN2139-05016, to connect the 
SEMA with the control rod. Torque-tighten each screw to 5-6 Nm.
    (2) Within 50 hours TIS, for Model MBB BK117 C-2 helicopters, 
using Figure 1 of Eurocopter Alert Service Bulletin MBB BK117 C-2-
22A-009, Revision 1, dated August 3, 2009, as reference, inspect the 
attachment hardware between the Yaw-SEMA and the Yaw-SEMA control 
rod to determine whether any of the washers can be moved.
    (i) If no washer can be moved, no further action is needed.
    (ii) If a washer can be moved, replace the four screws and 
install two additional washers, P/N EN2139-05016, to connect the 
SEMA with the control rod. Torque-tighten each screw to 5-6 Nm and 
apply polyurethane lacquer onto the attachment hardware.

(f) Affected ADs

    This AD revises AD 2015-12-09, Amendment 39-18184 (80 FR 34831, 
June 18, 2015).

(g) Credit for Previous Actions

    If you performed the actions in Eurocopter Alert Service 
Bulletin EC135-22A-015, Revision 0, dated May 13, 2008, or 
Eurocopter Alert Service Bulletin MBB BK117 C-2-22A-009, Revision 0, 
May 13, 2008, before the effective date of this AD, you met the 
requirements of this AD.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Regulations and Policy Group, FAA, may approve 
AMOCs for this AD. Send your proposal to: Matt Wilbanks, Aviation 
Safety Engineer, Regulations and Policy Group, Rotorcraft 
Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; 
telephone (817) 222-5110; email [email protected].
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, we suggest 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.

(i) Additional Information

    The subject of this AD is addressed in the European Aviation 
Safety Agency (EASA) AD No. 2013-0176, dated August 7, 2013. You may 
view the EASA AD on the Internet at http://www.regulations.gov in 
Docket No. FAA-2014-0577.

(j) Subject

    Joint Aircraft Service Component (JASC) Code: 2213, Flight 
Controller

    Issued in Fort Worth, Texas, on July 24, 2015.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-18865 Filed 7-31-15; 8:45 am]
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