[Federal Register Volume 75, Number 154 (Wednesday, August 11, 2010)]
[Proposed Rules]
[Pages 48617-48618]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-19817]
[[Page 48617]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0780; Directorate Identifier 2009-SW-68-AD]
RIN 2120-AA64
Airworthiness Directives; Eurocopter Deutschland GmbH (ECD) Model
MBB-BK 117 C-2 Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to supersede an existing airworthiness directive
(AD) for ECD Model MBB-BK 117 C-2 helicopters. This proposed AD results
from a mandatory continuing airworthiness information (MCAI) AD issued
by the European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community. The MCAI AD
states there was an in-flight incident in which a dynamic weight broke
off the control lever leading to considerable vibrations. A visual
inspection revealed that the threaded bolt of the control lever had
broken off. The proposed actions are intended to prevent separation of
dynamic weights, severe vibration, and subsequent loss of control of
the helicopter.
DATES: We must receive comments on this proposed AD by September 10,
2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
You may get the service information identified in this proposed AD
from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie,
Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527.
Examining the 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
stated in the ADDRESSES section of this proposal. Comments will be
available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: DOT/FAA Southwest Region, Sharon
Miles, ASW-111, Aviation Safety Engineer, Rotorcraft Directorate,
Regulations and Guidance Group, 2601 Meacham Blvd., Fort Worth, Texas
76137, telephone (817) 222-5122, fax (817) 222-5961.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written data, views, or arguments about
this proposed AD. Send your comments to an address listed in the
ADDRESSES section of this proposal. Include ``Docket No. FAA-2010-0780;
Directorate Identifier 2009-SW-68-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On March 14, 2007, we issued AD 2006-26-51, Amendment 39-14961 (72
FR 13679, March 23, 2007). That AD required actions intended to address
an unsafe condition on the Model MBB-BK 117 C-2 helicopters. Since we
issued AD 2006-26-51, the manufacturer has modified the control lever
and dynamic weights, which when installed on the helicopter will
constitute terminating action for the requirements in AD 2006-26-51.
EASA, which is the technical agent for the Member States of the
European Community, has issued EASA AD No. 2007-0237, dated August 31,
2007, to correct an unsafe condition for the Model MBB-BK 117 C-2
helicopters. The MCAI AD states: ``EASA was informed by the
manufacturer of an in-flight incident in which a dynamic weight broke
off the control lever subsequently leading to considerable vibrations.
A visual inspection revealed that the threaded bolt of the control
lever had broken off.''
You may obtain further information by examining the MCAI AD and
service information in the AD docket.
Related Service Information
ECD has issued ECD Alert Service Bulletin MBB BK117 C-2-64A-002,
Revision 2, dated August 6, 2007. The actions described in the MCAI AD
are intended to correct the same unsafe condition as that identified in
the service information.
FAA's Evaluation and Unsafe Condition Determination
This helicopter has been approved by the aviation authority of the
Federal Republic of Germany and is approved for operation in the United
States. Pursuant to our bilateral agreement with the Federal Republic
of Germany, EASA, their Technical Agent, has notified us of the unsafe
condition described in the MCAI AD. We are proposing this AD because we
evaluated all information provided by EASA and determined the unsafe
condition exists and is likely to exist or develop on other helicopters
of this same type design.
Differences Between the AD and the MCAI AD
We refer to flight hours as hours time-in-service. We do not refer
to a date of October 31, 2007, for replacing the levers because the
date has passed.
Costs of Compliance
We estimate that this proposed AD would affect 41 helicopters of
U.S. registry. We also estimate that it would take about 20 work-hours
per helicopter to inspect and replace the tail rotor control lever. The
average labor rate is $85 per work-hour. Required parts would cost
about $10,316 per helicopter. Based on these figures, we estimate the
cost of this AD to the U.S. operators to be $492,656 or $12, 016 per
helicopter, assuming the control lever is replaced on the entire fleet.
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:
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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 product(s)
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.
Therefore, I certify this proposed AD:
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); 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.
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
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]
2. The FAA amends Sec. 39.13 by removing Amendment 39-14961 (72 FR
13679, dated March 23, 2007) and adding the following new AD:
Eurocopter Deutschland GmbH: Docket No. FAA-2010-0780; Directorate
Identifier 2009-SW-68-AD.
Comments Due Date
(a) We must receive your comments by September 10, 2010.
Other Affected ADs
(b) This AD supersedes AD 2006-26-51, Amendment 39-14961, Docket
No. FAA 2006-26721, Directorate Identifier 2006-SW-28-AD.
Applicability
(c) This AD applies to Model MBB-BK 117 C-2 helicopters with a
tail rotor control lever B642M1009103, installed, certificated in
any category.
Reason
(d) The mandatory continued airworthiness information (MCAI) AD
states: ``EASA was informed by the manufacturer of an in-flight
incident in which a dynamic weight broke off the control lever
subsequently leading to considerable vibrations. A visual inspection
revealed that the threaded bolt of the control lever had broken
off.'' This AD requires actions that are intended to prevent
separation of dynamic weights, severe vibration, and subsequent loss
of control of the helicopter.
Actions and Compliance
(e) Before further flight, unless already done, mark the
position of the weights, remove the split pins, remove the weights,
and visually inspect the tail rotor control lever in the area around
the split pin bore for score marks, notching, scratching, or a
crack. Inspect by following the Accomplishment Instructions,
paragraph 3.A.(1) through 3.A.(3) and Figure 1, of Eurocopter Alert
Service Bulletin MBB BK 117 C-2-64A-002, Revision 2, dated August 6,
2007 (ASB).
(1) If done previously, within the next 8 hours time-in-service
(TIS) or before reaching 25 hours TIS after the last inspection, and
thereafter at intervals not to exceed 8 hours TIS, repeat the visual
inspection of the tail rotor control lever as required by paragraph
(e) of this AD.
(2) If you find a score mark, a notch, or a scratch that exceeds
the maintenance manual limits, or find a crack, before further
flight:
(i) Replace the tail rotor control lever with an airworthy tail
rotor control lever; and
(ii) Reidentify the tail rotor head, head assembly, and drive
system with the new part numbers by following the Accomplishment
Instructions, paragraph 3.B.(1) through 3.B.(8) and 3.C.(1) through
3.C.(2), of the ASB.
(f) Within 100 hours TIS, unless already done, replace the
control levers and reidentify the tail rotor head, head assembly,
and drive system with the new part numbers by following the
Accomplishment Instructions, paragraph 3.B.(1) through 3.B.(8) and
3.C.(1) through 3.C.(2), of the ASB.
(g) Replacing the control levers and reidentifying the part
numbers is terminating action for the requirements of this AD.
Differences Between the FAA AD and the MCAI AD
(h) We refer to flight hours as hours TIS. We do not refer to a
date of October 31, 2007, for replacing the levers because the date
has passed.
Other Information
(i) Alternative Methods of Compliance (AMOCs): The Manager,
Safety Management Group, ATTN: DOT/FAA Southwest Region, Sharon
Miles, ASW-111, Aviation Safety Engineer, Rotorcraft Directorate,
Regulations and Guidance Group, 2601 Meacham Blvd., Fort Worth,
Texas 76137, telephone (817) 222-5122, fax (817) 222-5961, has the
authority to approve AMOCs for this AD, if requested, using the
procedures found in 14 CFR 39.19.
(j) Special flight permits are prohibited.
Related Information
(k) MCAI EASA Airworthiness Directive No. 2006-0237, dated
August 31, 2007, which supersedes EASA Emergency AD 2007-0189-E,
dated July 12, 2007, contains related information.
Joint Aircraft System/Component (JASC) Code
(l) The JASC Code is 6400: Tail rotor system-control lever.
Issued in Fort Worth, Texas, on August 3, 2010.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2010-19817 Filed 8-10-10; 8:45 am]
BILLING CODE 4910-13-P