[Federal Register Volume 80, Number 60 (Monday, March 30, 2015)]
[Proposed Rules]
[Pages 16603-16606]
[FR Doc No: 2015-06806]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0674; Directorate Identifier 2014-SW-019-AD]
RIN 2120-AA64

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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede airworthiness directive (AD) 2014-05-
06 for certain Eurocopter Deutschland GmbH (ECD) (now Airbus
Helicopters Deutschland GmbH) Model EC135 and MBB-BK 117 C-2
helicopters to correct an error. AD 2014-05-06 currently requires
inspecting the flight-control bearings repetitively, replacing any
loose bearing with an airworthy flight-control bearing, and installing
bushings and washers. This proposed AD would require the same actions.
This proposed AD results from the discovery of an error in the
compliance time for AD 2014-05-06. These proposed actions are intended
to prevent the affected control lever from shifting, contacting the
helicopter structure, and reducing control of the helicopter.

DATES: We must receive comments on this proposed AD by May 29, 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:<PHONE_NUMBER>.
     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<PHONE_NUMBER>) 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<PHONE_NUMBER> or<PHONE_NUMBER>; fax<PHONE_NUMBER>; or at
http://www.airbushelicopters.com/techpub. You may review service
information at the FAA, Office of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. It is
also available on the Internet at http://www.regulations.gov by
searching for and locating Docket No. FAA-2015-0674.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas 76137; telephone<PHONE_NUMBER>; email
<EMAIL_ADDRESS>
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 February 20, 2014, we issued AD 2014-05-06, Amendment 39-17779
(79 FR 13196, March 10, 2014), for certain ECD (now Airbus Helicopters
Deutschland GmbH) Model EC135 and MBB-BK 117 C-2 helicopters. AD 2014-
05-06 requires inspecting the flight-control bearings repetitively,
replacing any loose bearing with an airworthy flight-control bearing,
and installing bushings and washers. AD 2014-05-06 was prompted by the
discovery of loose flight control bearings because of incorrect
installation. This condition, if not corrected, could result in the
affected control lever shifting, contacting the helicopter structure,
and reducing control of the helicopter.

Actions Since AD 2014-05-06 Was Issued

    Since we issued AD 2014-05-06 (79 FR 13196, March 10, 2014), we
discovered an error regarding the compliance time for certain model
helicopters. Paragraph (e)(1)(i) should have required that certain
actions be accomplished within the next 100 hours time-in-service or at
the next annual inspection, whichever occurs first. However, we omitted
the word ``first'' from that sentence, which changes the meaning of the
required compliance time.
    Also since we issued AD 2014-05-06, ECD changed its name to Airbus
Helicopters Deutschland GmbH. This proposed AD reflects that change and
updates the contact information to obtain service documentation.

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

    ECD, now called Airbus Helicopters, has issued Alert Service
Bulletin (ASB) MBB BK117 C-2-67A-010, Revision 3, dated February 8,
2010, and ASB EC135-67A-019, Revision 3, dated December 16, 2009. These
ASBs specify:
     Within the next 50 flight hours (FHs), inspecting the
affected bearings and, if necessary, rebonding any affected bearings or
replacing the lever assembly.
     Within 12 months, retrofitting bushings and washers on the
levers to prevent movement of the bearings.
     After the retrofit, repeating the inspection every 800 FHs
or 36 months for the Model EC135 helicopters, whichever comes first,
and 600 FHs or 24 months, whichever comes first, for the Model MBB-BK
117 C-2 helicopters.
    EASA classified these ASBs as mandatory and issued AD No. 2010-0058
to ensure the continued airworthiness of these helicopters. 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 NPRM.

Proposed AD Requirements

    For Airbus Model EC135 P1, P2, P2+, T1, T2, and T2+ helicopters
this proposed AD would require:
     Within the next 100 hours time-in-service (TIS) or at the
next annual inspection, whichever occurs first, modifying the left-hand
(LH) and right-hand (RH) guidance units and the cyclic shaft by
installing bushings and washers to prevent shifting of the bearings in
the axial direction.
     At intervals not to exceed 800 hours TIS or 36 months,
whichever occurs first, inspecting the bearings in the LH guidance
unit, RH guidance unit, cyclic control, upper guidance unit, and linear
voltage differential transducer plate for play. If any bearing is
loose, replacing the affected bearing with an airworthy bearing.
    For Model MBB-BK 117 C-2 helicopters, this proposed AD would
require:
     Within the next 100 hours TIS or at the next annual
inspection, whichever occurs first, modifying the LH and RH guidance
units and the lateral control lever by installing bushings and washers
to prevent shifting of the bearings in the axial direction.
     At intervals not to exceed 600 hours TIS or 24 months,
whichever occurs first, inspecting the bearings in the RH guidance
unit, LH guidance unit, and lateral control guidance unit for play. If
any bearing is loose, replacing the affected bearing with an airworthy
bearing.

Differences Between This Proposed AD and the EASA AD

    Differences between this proposed AD and the EASA AD are:
     The EASA AD is applicable to the EC 635 helicopter,
whereas this proposed AD is not because the EC 635 helicopter is not
type certificated in the U.S.
     The EASA AD requires an initial inspection within 50
flight hours or one

month, whichever occurs first after May 31, 2008, and a modification
within the next 12 months. This proposed AD would require the
modification within 100 hours TIS or at the next annual inspection,
whichever occurs first, and no inspection until after the modification
has been accomplished.
     The EASA AD applies to all EC135 and MBB-BK 117 C-2
helicopters, while this proposed AD would apply to certain serial-
numbered Model EC135 and Model MBB-BK 117 C-2 helicopters, as
recommended by the appropriate ECD ASB.

Costs of Compliance

    We estimate that this proposed AD would affect 175 Model EC135 and
112 Model MBB-BK 117 C-2 helicopters of U.S. Registry and that labor
costs would average $85 per work-hour. Based on these estimates, we
expect the following costs:
     For EC135 helicopters, it would take about 32 work-hours
to perform the modification. Parts would cost about $312. The total
cost for the modification would be about $3,032 per helicopter and
$530,600 for the U.S. operator fleet. The repetitive inspections would
require 6.5 work-hours for a cost of about $553 per helicopter and
about $96,775 for the fleet per inspection cycle.
     For MBB-BK 117 C-2 helicopters, it would take about 32
work-hours to perform the modification. Parts would cost about $396.
The total cost for the modification would be $3,116 per helicopter and
$348,992 for the U.S. operator fleet. The cost for the repetitive
inspections thereafter would be about $85 per helicopter and $9,520 for
the fleet per inspection cycle.

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:

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)
2014-05-06, Amendment 39-17779 (79 FR 13196, March 10, 2014), and
adding the following new AD:

Airbus Helicopters Deutschland GmbH (Previously Eurocopter
Deutschland GmbH): Docket No. FAA-2015-0674; Directorate Identifier
2014-SW-019-AD.

(a) Applicability

    This AD applies to the following helicopters, certificated in
any category:
    (1) Model EC135 P1, P2, P2+, T1, T2, and T2+ helicopters, serial
number (S/N) 0005 through 00829, with a tail rotor control lever,
part number (P/N) L672M2802205 or L672M1012212; cyclic control
lever, P/N L671M1005250; collective control lever assembly, P/N
L671M2020108; or collective control plate, P/N L671M5040207;
installed; and
    (2) Model MBB-BK 117 C-2 helicopters, S/N 9004 through 9310,
with a tail rotor control lever assembly, P/N B672M1007101 or
B672M1807101; tail rotor control lever, P/N B672M1002202 or
L672M2802205; or lateral control lever assembly, P/N B670M1008101,
installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as incorrectly installed
flight control bearings. This condition could cause the affected
control lever to shift and contact the helicopter structure,
resulting in reduced control of the helicopter.

(c) Affected ADs

    This AD supersedes AD 2014-05-06, Amendment 39-17779 (79 FR
13196, March 10, 2014).

(d) Comments Due Date

    We must receive comments by May 29, 2015.

(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) For Model EC135 P1, P2, P2+, T1, T2, and T2+ helicopters:
    (i) Within the next 100 hours time-inservice (TIS) or at the
next annual inspection, whichever occurs first, modify the left-hand
(LH) and right-hand (RH) guidance units and the cyclic shaft by
installing bushings and washers to prevent shifting of the bearings
in the axial direction as follows:
    (A) Remove and disassemble the LH guidance unit and install a
bushing, P/N L672M1012260, between the bearing block and the lever
of the LH guidance unit as depicted in Detail A of Figure 5 of
Eurocopter Alert Service Bulletin EC135-67A-019, Revision 3, dated
December 16, 2009 (EC135 ASB).
    (B) For helicopters without a yaw brake, remove and disassemble
the RH guidance unit and install a bushing, P/N L672M1012260,
between the bearing block and the lever as depicted in Detail B of
Figure 5 of EC135 ASB.
    (C) Remove and disassemble the cyclic shaft and install a
washer, P/N L671M1005260, between the bearing block and the lever as
depicted in Detail C of Figure 6 of EC135 ASB.
    (D) Remove the collective control rod from the bellcrank and
install a washer, P/N L221M1042208, on each side of the collective
control rod and bellcrank as depicted in Detail D of Figure 6 of
EC135 ASB.
    (E) At intervals not to exceed 800 hours TIS or 36 months,
whichever occurs first, inspect the bearings in the LH guidance
unit, RH guidance unit, cyclic control, upper guidance unit, and
linear voltage differential transducer plate for play. If any
bearing is

loose, replace the affected bearing with an airworthy bearing.
    (2) For Model MBB-BK 117 C-2 helicopters:
    (i) Within the next 100 hours TIS or at the next annual
inspection, whichever occurs first, modify the LH and RH guidance
units and the lateral control lever by installing bushings and
washers to prevent shifting of the bearings in the axial direction
as follows:
    (A) Remove and disassemble the RH guidance unit and install a
bushing, P/N L672M1012260, between the lever and the bracket as
depicted in Detail B of Figure 4 of Eurocopter Alert Service
Bulletin MBB BK117 C-2-67A-010, Revision 3, dated February 8, 2010
(BK117 ASB). Remove and disassemble the LH guidance unit and install
a bushing, P/N L672M1012260, between the lever and the bracket as
depicted in Detail C of Figure 4 of BK117 ASB.
    (B) Remove the lateral control lever and install new bushings in
accordance with the Accomplishment Instructions, paragraphs
3.C(9)(a) through 3.C(9)(g), of BK 117 ASB.
    (C) Identify the modified lever assembly by writing ``MBB BK117
C-2-67A-010'' on the lever with permanent marking pen and protect
with a single layer of lacquer (CM 421 or equivalent).
    (D) Apply corrosion preventive paste (CM 518 or equivalent) on
the shank of the screws and install airworthy parts as depicted in
Figure 5 of BK117 ASB.
    (E) At intervals not to exceed 600 hours TIS or 24 months,
whichever occurs first, inspect the bearings in the RH guidance
unit, LH guidance unit, and lateral control guidance unit for play.
If any bearing is loose, replace the affected bearing with an
airworthy bearing.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Matt Fuller, Senior Aviation
Safety Engineer, Safety Management Group, Rotorcraft Directorate,
FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817)
222-5110; email<EMAIL_ADDRESS>    (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.

(h) Additional Information

    The subject of this AD is addressed in European Aviation Safety
Agency (EASA) AD No. 2010-0058, dated March 30, 2010. You may view
the EASA AD on the Internet at http://www.regulations.gov in Docket
No. FAA-2015-0674.

 (i) Subject

    Joint Aircraft Service Component (JASC) Code: 6710, Main Rotor
Control.

    Issued in Fort Worth, Texas, on March 18, 2015.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2015-06806 Filed 3-27-15; 8:45 am]
 BILLING CODE 4910-13-P