Airworthiness Directives; Eurocopter Deutschland GmbH Helicopters, 75073-75075 [2012-30588]
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Federal Register / Vol. 77, No. 244 / Wednesday, December 19, 2012 / Proposed Rules
wreier-aviles on DSK5TPTVN1PROD with
Dissipation is rapid dilution of the
smoke by ventilation air. Mobility is
rapid movement of the smoke into and
out of the occupied area. In no case
should a light haze indicative of
stagnant airflow form, as this indicates
that the ventilation system is failing to
meet the requirements of 14 CFR 25.831,
iii. The smoke from a source below
the main deck must not rise above
armrest height on the main deck, and
iv. The smoke from a source in the
main deck must dissipate rapidly via
dilution with fresh air and be evacuated
from the airplane. The Airplane Flight
Manual (AFM) must include procedures
to evacuate smoke from the occupied
areas. To demonstrate that the quantity
of smoke is small, a flight test must be
conducted which simulates the
emergency procedures used in the event
of a fire during flight, including the use
of VMO/MMO descent profiles and a
simulated landing, if such conditions
are specified in the emergency
procedure.
2. Requirement for smoke or fire
detection in electrical/electronic
equipment bays: A smoke or fire
detection system compliant with
§§ 25.855(a), (b), (c), and (d); and
§ 25.858 must be provided for each
electrical/electronic equipment bay in
the pressurized cabin. Each system must
provide a visual indication to the flight
deck within one minute after the start of
a fire. Airplane flight tests must be
conducted to show compliance with
these requirements, and the
performance of the detectors must be
shown in accordance with Advisory
Circular 25–9A, Smoke Detection,
Penetration, and Evacuation Tests and
Related Flight Manual Emergency
Procedures, or other means acceptable
to the FAA.
3. Requirement for AFM procedures
safety analysis: It shall be demonstrated
that the AFM procedures to shut down
electrical/electronic equipment bays, or
part of them, in case of smoke/fire
detection, do not compromise the safe
operation of the aircraft. If a procedure
requests to shut down only part of the
equipment, the remaining equipment
shall be incorporated with safety
precautions against fire propagation.
Issued in Renton, Washington, on
December 13, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2012–30493 Filed 12–18–12; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–1285; Directorate
Identifier 2010–SW–073–AD]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
Deutschland GmbH Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Supplemental notice of
proposed rulemaking (SNPRM);
reopening of comment period.
AGENCY:
We are revising an earlier
proposed airworthiness directive (AD)
for Eurocopter Deutschland GmbH
(Eurocopter) Model BO–105A, BO–
105C, BO–105LS A–1, BO–105LS A–3,
and BO–105S helicopters, which
proposed inspecting for debonding of
the erosion protective shell (abrasion
strip) on the leading edge of each main
rotor blade. This SNPRM proposes to
revise those inspection requirements by
identifying specific dates of replacement
of the applicable parts and identifying a
specific inspection method for
debonding of an abrasion strip.
DATES: We must receive comments on
this proposed AD by February 4, 2013.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://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.
SUMMARY:
75073
For service information identified in
this proposed AD, contact American
Eurocopter Corporation, 2701 N. Forum
Drive, Grand Prairie, Texas 75052;
telephone (972) 641–0000 or (800) 232–
0323; fax (972) 641–3775; or at https://
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, Texas 76137.
FOR FURTHER INFORMATION CONTACT: Jim
Grigg, Manager, Safety Management
Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
jim.grigg@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.
Examining the AD Docket
Discussion
You may examine the AD docket on
the Internet at https://
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.
On November 29, 2011, we issued a
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
include an AD that would apply to
Eurocopter Model BO–105A, BO–105C,
BO–105LS A–1, BO–105LS A–3, and
BO–105S helicopters with a main rotor
blade, part number (P/N) 105–15103,
105–15141, 105–15141V001, 105–
15143, 105–15150, 105–15150V001,
105–15152, 105–81013, 105–87214,
1120–15101, or 1120–15103; where the
main rotor blade erosion protective shell
was replaced between September 2006
PO 00000
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75074
Federal Register / Vol. 77, No. 244 / Wednesday, December 19, 2012 / Proposed Rules
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and March 2010. This proposal was
published in the Federal Register as a
notice of proposed rulemaking (NPRM)
on December 6, 2011 (76 FR 76068). The
NPRM proposed to require a one-time
inspection of each main rotor blade for
debonding of the erosion protective
shell within 50 hours time-in-service
(TIS). If debonding was detected during
the inspection, the NPRM proposed
replacing the main rotor blade with an
airworthy main rotor blade before
further flight. The proposed
requirements were intended to detect
debonding of the main rotor blade
erosion protective shell, which could
lead to an unbalanced main rotor, high
vibration, damage to the tail boom or
tail rotor, and loss of control of the
helicopter.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Emergency AD
No. 2010–0216–E, dated October 21,
2010 (corrected October 29, 2010),
applicable to Eurocopter Model BO105
A, BO105 C, BO105 D, BO105 LS A–1,
BO105 LS A–3, and BO105 S
helicopters, all variants (except variants
CB–5 and DBS–5). EASA advises that
during an inspection on a BO105
helicopter, debonding was found on the
erosion protective shell of a main rotor
blade, and investigation showed the
debonding was caused by incorrect
installation of the erosion protective
shell. In addition, EASA states that an
incident occurred where a second
BO105 helicopter lost its erosion
protective shell during hover flight.
EASA advises that this condition, if not
corrected, could result in loss of the
main rotor blade erosion protective shell
during flight, leading to an unbalanced
main rotor and high vibrations, which
could damage the tail boom or tail rotor
or result in loss of tail rotor control and
loss of control of the helicopter.
Actions Since Previous NPRM Was
Issued
Since we issued the previous NPRM
(76 FR 76068, December 6, 2011), we
discovered the need for identifying
specific dates of replacement of the
applicable parts and identifying that a
tap inspection would be the required
method for inspecting for debonding of
an abrasion strip. The previous NPRM
stated the proposed AD would apply to
certain part-numbered main rotor blades
with a main rotor blade abrasion strip
that was replaced between September
2006 and March 2010. This
supplemental NPRM proposes clarifying
the date range to be inclusive of
September 1, 2006 through March 31,
2010. The previous NPRM also
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proposed to require inspecting for
debonding of the abrasion strip along
the leading edge of each main rotor
blade. This supplemental NPRM
clarifies that the proposed inspection
method is a tap inspection.
Because these proposed changes
expand the applicability and may
increase the economic burden on some
operators, the FAA will reopen the
comment period to provide additional
opportunity for public comment.
FAA’s Determination
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 helicopters of these
same type designs. Certain changes
described above expand the scope of the
original NPRM (76 FR 76068, December
6, 2011). As a result, we have
determined that it is necessary to reopen
the comment period to provide
additional opportunity for the public to
comment.
Related Service Information
Eurocopter has issued Emergency
Alert Service Bulletin (ASB) No. ASB
BO105–10–124, dated July 14, 2010, for
the Model BO105 helicopter, with a
main rotor blade, P/N 105–15103, 105–
15141, 105–15141V001, 105–15143,
105–15150, 105–15150V001, 105–
15152, 105–81013, 105–87214, 1120–
15101, or 1120–15103, where the main
rotor blade erosion protective shell was
replaced between September 2006 and
March 2010. Eurocopter also issued
Emergency ASB No. ASB–BO105LS–
10–12, dated July 14, 2010, for the
Model BO105LS A–3 helicopter, with a
main rotor blade, P/N 105–15141, where
the main rotor blade erosion protective
shell was replaced between September
2006 and March 2010. Both Emergency
ASBs exclude helicopters from this
inspection if each main rotor blade was
inspected at the last 600 flight hour
inspection and no debonding was
detected during the inspection. Both
Emergency ASBs specified a one-time
inspection of the main rotor blades
within the next 50 flight hours to
determine if debonding of the main
rotor blade erosion protective shell has
occurred.
Eurocopter subsequently issued
Emergency ASB No. ASB BO105–10–
124, Revision 1, dated October 18, 2010,
and Emergency ASB No. ASB–
BO105LS–10–12, Revision 1, dated
October 20, 2010. These service
bulletins specify the same inspection
requirements as the original service
bulletins, but revise the inspection
compliance time from 50 flight hours to
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10 flight hours. EASA classified these
service bulletins as mandatory and
issued EASA Emergency AD No. 2010–
0216–E, dated October 21, 2010
(corrected October 29, 2010) to ensure
the continued airworthiness of these
helicopters.
Proposed Requirements of the
Supplemental NPRM
This proposed AD would require,
within 50 hours TIS, inspecting for
debonding by tap testing the abrasion
strip of the leading edge of each main
rotor blade. If there is debonding in any
area of the abrasion strip, this proposed
AD would require, before further flight,
replacing the main rotor blade.
Differences Between This Supplemental
NPRM and the EASA AD
The differences between this
proposed AD and the EASA AD are:
• The EASA AD allows compliance
within ‘‘10 flight hours, or 4 flight
cycles, or 4 weeks, whichever occurs
first,’’ and this proposed AD would
require compliance within 50 hours TIS.
• The EASA AD allows you to replace
the main rotor blade erosion protective
shell if debonding is detected, and this
proposed AD would require you to
replace the main rotor blade with an
airworthy main rotor blade if debonding
is detected.
• The EASA AD is applicable to the
Model BO105 D helicopter; however,
this proposed AD would not include
this model because it does not have a
type certificate in the U.S.
Costs of Compliance
We estimate that this AD would affect
97 helicopters of U.S. Registry. We
estimate that operators may incur the
following costs in order to comply with
this proposed AD. It would take about
1.0 work-hour per helicopter to perform
the inspection at an average labor rate
of $85 per work-hour. Based on these
figures, we estimate the cost of the
inspection on U.S. operators would be
$8,245 or $85 per helicopter. If there is
debonding, we estimate that it would
take about 2 work-hours to replace a
main rotor blade and required parts
would cost $114,182, for a total cost of
$114,352 per blade. We have no way of
determining how many operators will
incur replacement costs.
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
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Federal Register / Vol. 77, No. 244 / Wednesday, December 19, 2012 / Proposed Rules
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
wreier-aviles on DSK5TPTVN1PROD with
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.
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§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Eurocopter Deutschland GmbH: Docket No.
FAA–2011–1285; Directorate Identifier
2010–SW–073–AD.
(a) Applicability
This AD applies to Model BO–105A, BO–
105C, BO–105LS A–1, BO–105LS A–3, and
BO–105S helicopters, with a main rotor
blade, part number 105–15103, 105–15141,
105–15141V001, 105–15143, 105–15150,
105–15150V001, 105–15152, 105–81013,
105–87214, 1120–15101, or 1120–15103;
where the main rotor blade erosion protective
shell (abrasion strip) was replaced between
September 1, 2006 and March 31, 2010,
inclusive; certificated in any category.
75075
0000 or (800) 232–0323; fax (972) 641–3775;
or at https://www.eurocopter.com/techpub.
You may review a copy of the service
information at the FAA, Office of the
Regional Counsel, Southwest Region, 2601
Meacham Blvd., Room 663, Fort Worth,
Texas 76137.
(2) The subject of this AD is addressed in
European Aviation Safety Agency Emergency
AD No. 2010–0216–E, dated October 21, 2010
(corrected October 29, 2010).
(g) Subject
Joint Aircraft Service Component (JASC)
Code: 6210, Main Rotor Blades.
Issued in Fort Worth, Texas, on December
12, 2012.
S. Frances Cox,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
(b) Unsafe Condition
This AD defines the unsafe condition as
debonding of a main rotor blade erosion
protective shell (abrasion strip). This
condition could result in loss of the abrasion
strip and an unbalanced main rotor, high
vibration, damage to the tail boom or tail
rotor, and loss of control of the helicopter.
[FR Doc. 2012–30588 Filed 12–18–12; 8:45 am]
(c) 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.
21 CFR Part 1308
(d) Required Actions
(1) Within 50 hours time-in-service,
inspect the main rotor blade for debonding of
the erosion protective shell by tap testing the
abrasion strip of the leading edge of each
main rotor blade.
(2) If the abrasion strip is debonding in any
area, before further flight, replace the main
rotor blade.
(e) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Jim Grigg,
Manager, Safety Management Group,
Rotorcraft Directorate, FAA, 2601 Meacham
Blvd., Fort Worth, Texas 76137; telephone
(817) 222–5110; email jim.grigg@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.
(f) Additional Information
(1) Eurocopter Emergency Alert Service
Bulletin No. ASB BO105–10–124, Revision 1,
dated October 18, 2010, and No. ASB–
BO105LS–10–12, Revision 1, dated October
20, 2010, which are not incorporated by
reference, contain additional information
about the subject of this AD. For this service
information, contact American Eurocopter
Corporation, 2701 N. Forum Drive, Grand
Prairie, Texas 75052; telephone (972) 641–
PO 00000
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BILLING CODE 4910–13–P
DEPARTMENT OF JUSTICE
Drug Enforcement Administration
[Docket No. DEA–369]
Schedules of Controlled Substances:
Placement of Lorcaserin Into
Schedule IV
Drug Enforcement
Administration, Department of Justice.
ACTION: Notice of proposed rulemaking.
AGENCY:
The Drug Enforcement
Administration (DEA) proposes placing
the substance lorcaserin, including its
salts, isomers, and salts of isomers
whenever the existence of such salts,
isomers, and salts of isomers is possible,
into Schedule IV of the Controlled
Substances Act (CSA). This proposed
action is based on a recommendation
from the Assistant Secretary for Health
of the Department of Health and Human
Services (HHS) and on an evaluation of
all other relevant data by DEA. If
finalized, this action would impose the
regulatory controls and criminal
sanctions of Schedule IV on the
manufacture, distribution, dispensing,
importation, exportation, and
possession of lorcaserin and products
containing lorcaserin.
DATES: DEA will permit interested
persons to file written comments on this
proposal pursuant to 21 CFR 1308.43(g).
Electronic comments must be submitted
and written comments must be
postmarked on or before January 18,
2013. Commenters should be aware that
the electronic Federal Docket
Management System will not accept
comments after midnight Eastern Time
on the last day of the comment period.
SUMMARY:
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Agencies
[Federal Register Volume 77, Number 244 (Wednesday, December 19, 2012)]
[Proposed Rules]
[Pages 75073-75075]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-30588]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-1285; Directorate Identifier 2010-SW-073-AD]
RIN 2120-AA64
Airworthiness Directives; Eurocopter Deutschland GmbH Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening
of comment period.
-----------------------------------------------------------------------
SUMMARY: We are revising an earlier proposed airworthiness directive
(AD) for Eurocopter Deutschland GmbH (Eurocopter) Model BO-105A, BO-
105C, BO-105LS A-1, BO-105LS A-3, and BO-105S helicopters, which
proposed inspecting for debonding of the erosion protective shell
(abrasion strip) on the leading edge of each main rotor blade. This
SNPRM proposes to revise those inspection requirements by identifying
specific dates of replacement of the applicable parts and identifying a
specific inspection method for debonding of an abrasion strip.
DATES: We must receive comments on this proposed AD by February 4,
2013.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to https://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 https://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,
Texas 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-
3775; or at https://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,
Texas 76137.
FOR FURTHER INFORMATION CONTACT: Jim Grigg, Manager, Safety Management
Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth,
Texas 76137; telephone (817) 222-5110; email jim.grigg@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
On November 29, 2011, we issued a proposal to amend part 39 of the
Federal Aviation Regulations (14 CFR part 39) to include an AD that
would apply to Eurocopter Model BO-105A, BO-105C, BO-105LS A-1, BO-
105LS A-3, and BO-105S helicopters with a main rotor blade, part number
(P/N) 105-15103, 105-15141, 105-15141V001, 105-15143, 105-15150, 105-
15150V001, 105-15152, 105-81013, 105-87214, 1120-15101, or 1120-15103;
where the main rotor blade erosion protective shell was replaced
between September 2006
[[Page 75074]]
and March 2010. This proposal was published in the Federal Register as
a notice of proposed rulemaking (NPRM) on December 6, 2011 (76 FR
76068). The NPRM proposed to require a one-time inspection of each main
rotor blade for debonding of the erosion protective shell within 50
hours time-in-service (TIS). If debonding was detected during the
inspection, the NPRM proposed replacing the main rotor blade with an
airworthy main rotor blade before further flight. The proposed
requirements were intended to detect debonding of the main rotor blade
erosion protective shell, which could lead to an unbalanced main rotor,
high vibration, damage to the tail boom or tail rotor, and loss of
control of the helicopter.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Emergency AD No. 2010-0216-E, dated October 21, 2010 (corrected October
29, 2010), applicable to Eurocopter Model BO105 A, BO105 C, BO105 D,
BO105 LS A-1, BO105 LS A-3, and BO105 S helicopters, all variants
(except variants CB-5 and DBS-5). EASA advises that during an
inspection on a BO105 helicopter, debonding was found on the erosion
protective shell of a main rotor blade, and investigation showed the
debonding was caused by incorrect installation of the erosion
protective shell. In addition, EASA states that an incident occurred
where a second BO105 helicopter lost its erosion protective shell
during hover flight. EASA advises that this condition, if not
corrected, could result in loss of the main rotor blade erosion
protective shell during flight, leading to an unbalanced main rotor and
high vibrations, which could damage the tail boom or tail rotor or
result in loss of tail rotor control and loss of control of the
helicopter.
Actions Since Previous NPRM Was Issued
Since we issued the previous NPRM (76 FR 76068, December 6, 2011),
we discovered the need for identifying specific dates of replacement of
the applicable parts and identifying that a tap inspection would be the
required method for inspecting for debonding of an abrasion strip. The
previous NPRM stated the proposed AD would apply to certain part-
numbered main rotor blades with a main rotor blade abrasion strip that
was replaced between September 2006 and March 2010. This supplemental
NPRM proposes clarifying the date range to be inclusive of September 1,
2006 through March 31, 2010. The previous NPRM also proposed to require
inspecting for debonding of the abrasion strip along the leading edge
of each main rotor blade. This supplemental NPRM clarifies that the
proposed inspection method is a tap inspection.
Because these proposed changes expand the applicability and may
increase the economic burden on some operators, the FAA will reopen the
comment period to provide additional opportunity for public comment.
FAA's Determination
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 helicopters of these same type designs. Certain
changes described above expand the scope of the original NPRM (76 FR
76068, December 6, 2011). As a result, we have determined that it is
necessary to reopen the comment period to provide additional
opportunity for the public to comment.
Related Service Information
Eurocopter has issued Emergency Alert Service Bulletin (ASB) No.
ASB BO105-10-124, dated July 14, 2010, for the Model BO105 helicopter,
with a main rotor blade, P/N 105-15103, 105-15141, 105-15141V001, 105-
15143, 105-15150, 105-15150V001, 105-15152, 105-81013, 105-87214, 1120-
15101, or 1120-15103, where the main rotor blade erosion protective
shell was replaced between September 2006 and March 2010. Eurocopter
also issued Emergency ASB No. ASB-BO105LS-10-12, dated July 14, 2010,
for the Model BO105LS A-3 helicopter, with a main rotor blade, P/N 105-
15141, where the main rotor blade erosion protective shell was replaced
between September 2006 and March 2010. Both Emergency ASBs exclude
helicopters from this inspection if each main rotor blade was inspected
at the last 600 flight hour inspection and no debonding was detected
during the inspection. Both Emergency ASBs specified a one-time
inspection of the main rotor blades within the next 50 flight hours to
determine if debonding of the main rotor blade erosion protective shell
has occurred.
Eurocopter subsequently issued Emergency ASB No. ASB BO105-10-124,
Revision 1, dated October 18, 2010, and Emergency ASB No. ASB-BO105LS-
10-12, Revision 1, dated October 20, 2010. These service bulletins
specify the same inspection requirements as the original service
bulletins, but revise the inspection compliance time from 50 flight
hours to 10 flight hours. EASA classified these service bulletins as
mandatory and issued EASA Emergency AD No. 2010-0216-E, dated October
21, 2010 (corrected October 29, 2010) to ensure the continued
airworthiness of these helicopters.
Proposed Requirements of the Supplemental NPRM
This proposed AD would require, within 50 hours TIS, inspecting for
debonding by tap testing the abrasion strip of the leading edge of each
main rotor blade. If there is debonding in any area of the abrasion
strip, this proposed AD would require, before further flight, replacing
the main rotor blade.
Differences Between This Supplemental NPRM and the EASA AD
The differences between this proposed AD and the EASA AD are:
The EASA AD allows compliance within ``10 flight hours, or
4 flight cycles, or 4 weeks, whichever occurs first,'' and this
proposed AD would require compliance within 50 hours TIS.
The EASA AD allows you to replace the main rotor blade
erosion protective shell if debonding is detected, and this proposed AD
would require you to replace the main rotor blade with an airworthy
main rotor blade if debonding is detected.
The EASA AD is applicable to the Model BO105 D helicopter;
however, this proposed AD would not include this model because it does
not have a type certificate in the U.S.
Costs of Compliance
We estimate that this AD would affect 97 helicopters of U.S.
Registry. We estimate that operators may incur the following costs in
order to comply with this proposed AD. It would take about 1.0 work-
hour per helicopter to perform the inspection at an average labor rate
of $85 per work-hour. Based on these figures, we estimate the cost of
the inspection on U.S. operators would be $8,245 or $85 per helicopter.
If there is debonding, we estimate that it would take about 2 work-
hours to replace a main rotor blade and required parts would cost
$114,182, for a total cost of $114,352 per blade. We have no way of
determining how many operators will incur replacement costs.
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 75075]]
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
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 adding the following new
airworthiness directive (AD):
Eurocopter Deutschland GmbH: Docket No. FAA-2011-1285; Directorate
Identifier 2010-SW-073-AD.
(a) Applicability
This AD applies to Model BO-105A, BO-105C, BO-105LS A-1, BO-
105LS A-3, and BO-105S helicopters, with a main rotor blade, part
number 105-15103, 105-15141, 105-15141V001, 105-15143, 105-15150,
105-15150V001, 105-15152, 105-81013, 105-87214, 1120-15101, or 1120-
15103; where the main rotor blade erosion protective shell (abrasion
strip) was replaced between September 1, 2006 and March 31, 2010,
inclusive; certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as debonding of a main
rotor blade erosion protective shell (abrasion strip). This
condition could result in loss of the abrasion strip and an
unbalanced main rotor, high vibration, damage to the tail boom or
tail rotor, and loss of control of the helicopter.
(c) 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.
(d) Required Actions
(1) Within 50 hours time-in-service, inspect the main rotor
blade for debonding of the erosion protective shell by tap testing
the abrasion strip of the leading edge of each main rotor blade.
(2) If the abrasion strip is debonding in any area, before
further flight, replace the main rotor blade.
(e) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Jim Grigg, Manager, Safety
Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd.,
Fort Worth, Texas 76137; telephone (817) 222-5110; email
jim.grigg@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.
(f) Additional Information
(1) Eurocopter Emergency Alert Service Bulletin No. ASB BO105-
10-124, Revision 1, dated October 18, 2010, and No. ASB-BO105LS-10-
12, Revision 1, dated October 20, 2010, which are not incorporated
by reference, contain additional information about the subject of
this AD. For this service information, contact American Eurocopter
Corporation, 2701 N. Forum Drive, Grand Prairie, Texas 75052;
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or
at https://www.eurocopter.com/techpub. You may review a copy of the
service information at the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas
76137.
(2) The subject of this AD is addressed in European Aviation
Safety Agency Emergency AD No. 2010-0216-E, dated October 21, 2010
(corrected October 29, 2010).
(g) Subject
Joint Aircraft Service Component (JASC) Code: 6210, Main Rotor
Blades.
Issued in Fort Worth, Texas, on December 12, 2012.
S. Frances Cox,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2012-30588 Filed 12-18-12; 8:45 am]
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