[Federal Register Volume 78, Number 128 (Wednesday, July 3, 2013)]
[Proposed Rules]
[Pages 40047-40050]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-15956]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0555; Directorate Identifier 2010-SW-047-AD]
RIN 2120-AA64
Airworthiness Directives; Eurocopter Deutschland GmbH 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
Eurocopter Deutschland GmbH (ECD) Model EC135 and MBB-BK 117 C-2
helicopters. This proposed AD is prompted by the discovery during a
routine inspection of loose flight control bearings because of
incorrect installation. This proposed AD would require inspecting the
flight-control bearings repetitively, replacing any loose bearing with
an airworthy flight-control bearing, and installing bushings and
washers. The 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 September 3,
2013.
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 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
American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775;
or at http://www.eurocopter.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, TX 76137.
[[Page 40048]]
FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, TX 76137; 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
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued AD No.
2010-0058, dated March 30, 2010, (AD 2010-0058), to correct an unsafe
condition for the ECD Model MBB-BK 117 C-2, EC 135 and EC 635
helicopters. EASA advises that during an inspection of an MBB-BK 117 C-
2, ``bearings were detected which had not been correctly fixed.'' As
some bearings on the EC 135 and MBB-BK 117 C-2 type designs are
installed with the same procedure, they are equally affected by the
possibility of the unsafe condition. EASA states that this condition,
if not corrected, could result in the affected control lever shifting
in the axial direction, contacting the helicopter structure, and
subsequently reducing control of the helicopter.
FAA's Determination
These helicopters have been approved by the aviation authority of
the Federal Republic 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
exists and is likely to exist or develop on other products of these
same type designs.
Related Service Information
Eurocopter 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 on the levers to
prevent movement of the bearings.
After the retrofit, repeating the inspection every 800 FHs
or 36 months for the Model EC 135 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 2010-0058 to
ensure the continued airworthiness of these helicopters.
Proposed AD Requirements
For EC135 helicopters, this proposed AD would require, within 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 in the axial direction. This proposed AD would require
at intervals not to exceed 800 hours TIS or 36 months, whichever occurs
first, inspecting the bearings in the LH guidance unit, the RH guidance
unit, cyclic control, upper guidance unit, and linear voltage
differential transducer plate for play. If any bearing is loose, the
proposed AD would require replacing the affected bearing with an
airworthy bearing.
For MBB-BK 117 C-2 helicopters, this proposed AD would require,
within 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. This proposed AD also would require 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, the proposed AD would require 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 provides requirements for certain spare parts,
whereas this proposed AD does not.
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 average $85 per work-hour. Based on these estimates, we would
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
[[Page 40049]]
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 adding the following new airworthiness
directive (AD):
Eurocopter Deutschland GmbH: Docket No. FAA-2013-0555; Directorate
Identifier 2010-SW-047-AD.
(a) Applicability
This AD applies to the following helicopters, certificated in
any category:
(1) Eurocopter Deutschland GmbH (ECD) 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) Comments Due Date
We must receive comments by September 3, 2013.
(d) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time.
(e) Required Actions
(1) For Model EC135 P1, P2, P2+, T1, T2, and T2+ helicopters:
(i) Within the next 100 hours time-in-service (TIS) or at the
next annual inspection, whichever occurs, 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.
(f) Alternative Methods of Compliance (AMOC)
(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, TX 76137; 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.
(g) Additional Information
The subject of this AD is addressed in European Aviation Safety
Agency (EASA) AD
[[Page 40050]]
No. 2010-0058, dated March 30, 2010. You may view the EASA AD at
http://www.regulations.gov in Docket No. FAA-2013-0555.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6710, Main Rotor
Control.
Issued in Fort Worth, Texas, on June 18, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2013-15956 Filed 7-2-13; 8:45 am]
BILLING CODE 4910-13-P