[Federal Register Volume 75, Number 209 (Friday, October 29, 2010)]
[Rules and Regulations]
[Pages 66657-66659]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-26563]
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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;
Amendment 39-16486; AD 2010-22-07]
RIN 2120-AA64
Airworthiness Directives; Eurocopter Deutschland GmbH Model MBB-
BK 117 C-2 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD) for the Eurocopter Deutschland GmbH (ECD) Model MBB BK 117 C-2
helicopters. This amendment 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
[[Page 66658]]
control lever leading to considerable vibrations. A visual inspection
revealed that the threaded bolt of the control lever had broken off.
The actions specified by this AD are intended to prevent separation of
dynamic weights, severe vibration, and subsequent loss of control of
the helicopter.
DATES: Effective December 3, 2010.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 3, 2010.
ADDRESSES: You may get the service information identified in this 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, West Building Ground Floor, Room W12-140, 1200 New Jersey
Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
FOR FURTHER INFORMATION CONTACT: DOT/FAA Southwest Region, Sharon
Miles, ASW-111, Aviation Safety Engineer, Rotorcraft Directorate,
Regulations and Policy Group, 2601 Meacham Blvd., ASW-111, Fort Worth,
Texas 76137, telephone (817) 222-5122, fax (817) 222-5961.
SUPPLEMENTARY INFORMATION:
Discussion
A proposal to amend 14 CFR Part 39 by superseding AD 2006-26-51,
Amendment 39 14961 (72 FR 13679, March 23, 2007) for the specified ECD
model helicopters was published in the Federal Register on August 11,
2010 (75 FR 48617). AD 2006-26-51 requires 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 issuing 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.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposal or the FAA's determination of the cost to the public. We have
determined that air safety and the public interest require the adoption
of the rule as proposed.
Cost of Compliance
We estimate that this AD will affect 41 helicopters of U.S.
registry. We also estimate that it will 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, and required parts will cost
about $10,316 per helicopter. Based on these figures, we estimate the
total cost of this AD to U.S. operators to be $492,656, or $12,016 per
helicopter, assuming the control lever is replaced on the entire fleet.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will 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 above, I certify that the 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); 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 AD and placed it in the AD docket.
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 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. Section 39.13 is amended by removing Amendment 39 14961 (72 FR
13679, March 23, 2007), and by adding
[[Page 66659]]
a new airworthiness directive (AD), Amendment 39 16486, to read as
follows:
2010-22-07 Eurocopter Deutschland GmbH: Amendment 39-16486; Docket
No. FAA-2010-0780; Directorate Identifier 2009-SW-68-AD. Supersedes
AD 2006-26-51, Amendment 39 14961, Docket No. FAA-2006-26721,
Directorate Identifier 2006-SW-28-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective on
December 3, 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: ``European Aviation Safety Agency (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 Policy 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 Code
(l) The Joint Aircraft System/Component Code is 6400: Tail rotor
system-control lever.
Material Incorporated by Reference
(m) The actions shall be done in accordance with the specified
portions of Eurocopter Deutschland GmbH Alert Service Bulletin MBB
BK117 C-2-64A-002, Revision 2, dated August 6, 2007. The Director of
the Federal Register approved this incorporation by reference in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be
obtained from American Eurocopter Corporation, 2701 Forum Drive,
Grand Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972)
641-3527. Copies may be inspected at the FAA, Office of the Regional
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas, or at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Fort Worth, Texas, on October 12, 2010.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2010-26563 Filed 10-28-10; 8:45 am]
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