
[Federal Register Volume 79, Number 159 (Monday, August 18, 2014)]
[Proposed Rules]
[Pages 48707-48709]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-19524]



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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) 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
Airbus Helicopters Model EC135P1, EC135T1, EC135P2, EC135T2, EC135P2+, 
EC135T2+, and MBB-BK 117 C-2 helicopters. This proposed AD would 
require inspecting certain washers for movement and making appropriate 
repairs if the washers move. This proposed AD is prompted by play found 
between the Smart Electro Mechanical Actuator (SEMA) and the control 
rod during installation work on a helicopter. The 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 October 17, 
2014.

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 the referenced 
service information at the FAA, Office of the Regional Counsel, 
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 
76137.

FOR FURTHER INFORMATION CONTACT: Matt Wilbanks, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; 
email matt.wilbanks@faa.gov.

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

    EASA, which is the Technical Agent for the Member States of the 
European Union, issued EASA AD No. 2013-0176, dated August 7, 2013, 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. According 
to EASA, the loose attachment hardware was caused by an ``unfavourable 
adding of the tolerances'' of the individual attachment hardware 
elements. EASA states that as a result, the screw pushed against the 
bottom of the threaded blind borehole on the SEMA, and no clamping 
force could be achieved on the screw head. 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 
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.
    Since the issuance of EASA AD No. 2013-0176, Eurocopter Deutschland 
GmbH has changed its name to Airbus Helicopters Deutschland GmbH.

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

    Eurocopter reported in Alert Service Bulletins (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

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respective control rods for play and making the proper adjustments to 
eliminate any play.

Proposed AD Requirements

    This proposed AD would 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. The 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 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 proposed 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:

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 adding the following new airworthiness 
directive (AD):

Airbus Helicopters Deutschland GmbH (Previously Eurocopter 
Deutschland GmbH) (Airbus Helicopters) 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 October 17, 2014.

(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

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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) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Matt Wilbanks, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-
5110; email matt.wilbanks@faa.gov.
    (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.

(g) 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.

 (i) Subject

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

     Issued in Fort Worth, Texas, on August 8, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-19524 Filed 8-15-14; 8:45 am]
BILLING CODE 4910-13-P


