Airworthiness Directives; Eurocopter Deutschland GmbH Helicopters, 52410-52412 [2013-19442]
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Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations
(i) Aerazur SB No. 25–69–58, dated March
14, 2011, which is attached as an appendix
to Eurocopter ASB No. EC130–25A042,
Revision 0, dated July 11, 2011.
(ii) Aerazur SB No. 25–69–87, dated March
14, 2011, which is attached as an appendix
to Eurocopter ASB No. EC120–25A026,
Revision 0, dated July 11, 2011.
(iii) Eurocopter ASB No. 05A008, Revision
0, dated June 8, 2009.
(iv) Eurocopter ASB No. 05A011, Revision
0, dated June 8, 2009.
(3) For Eurocopter and Aerazur service
information identified in this 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 https://
www.eurocopter.com/techpub.
(4) You may view this service information
that is incorporated by reference in the AD
Docket on the Internet at https://
www.regulations.gov.
(5) You may also view this service
information that is incorporated by reference
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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Fort Worth, Texas, on August 2,
2013.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
[FR Doc. 2013–19438 Filed 8–22–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0887; Directorate
Identifier 2009–SW–02–AD; Amendment 39–
17551; AD 2013–16–13]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
Deutschland GmbH Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for
Eurocopter Deutschland GmbH (ECD)
Model BO–105A, BO–105C, BO–105S,
BO–105LS A–1, BO–105LS A–3, MBB–
BK 117 A–1, MBB–BK 117 A–3, MBB–
BK 117 A–4, MBB–BK 117 B–1, MBB–
BK–117 B–2, and MBB–BK 117 C–1
helicopters to require inspections for
corrosion or thread damage to each tail
rotor balance weight (weight) and each
tail rotor control lever (lever). This AD
was prompted by a European Aviation
Safety Agency (EASA) AD and a
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SUMMARY:
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Jkt 229001
Transport Canada Civil Aviation (TCCA)
AD, both issued based on a report that
corrosion was detected on a weight in
the area of the attachment thread on a
model BO–105 helicopter. The actions
of this AD are intended to detect
corrosion and thread damage in the
threaded area of the weight and lever,
and to prevent failure of a weight or
lever, separation of tail rotor parts,
severe vibration, and subsequent loss of
control of the helicopter.
DATES: This AD is effective September
27, 2013.
The Director of the Federal Register
approved the incorporation by reference
of certain documents listed in this AD
as of September 27, 2013.
ADDRESSES: For service information
identified in this 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 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, TX 76137.
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 AD, the EASA and
TCCA ADs, any incorporated-byreference service information, the
economic evaluation, any comments
received, and other information. The
street address for the Docket Operations
Office (phone: 800–647–5527) is U.S.
Department of Transportation, Docket
Operations Office, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Sharon Miles, Aviation Safety Engineer,
Regulations and Policy Group,
Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, TX 76137;
telephone (817) 222–5110; email
sharon.y.miles@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On August 29, 2012, at 77 FR 52265,
the Federal Register published our
notice of proposed rulemaking (NPRM),
which proposed to amend 14 CFR part
39 to include an AD that would apply
to ECD Model BO–105A, BO–105C, BO–
105S, BO–105LS A–1, BO–105LS A–3,
MBB–BK 117 A–1, MBB–BK 117 A–3,
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MBB–BK 117 A–4, MBB–BK117 B–1,
MBB–BK 117 B–2, and MBB–BK 117 C–
1 helicopters with certain levers and
weights installed. The NPRM proposed
to require conducting repetitive visual
inspections of each weight and lever
and proposed procedures for installing
a weight or lever. Additionally, the
NPRM proposed allowable tolerances
for corrosion or thread damage on the
threaded portion of a weight or lever
and proposed to require that a part with
corrosion or mechanical damage in
excess of allowable tolerances be
replaced with an airworthy part. The
proposed requirements were intended to
detect corrosion and thread damage in
the threaded area of a weight or lever,
to prevent failure of a weight or lever,
separation of tail rotor parts, severe
vibration, and subsequent loss of control
of the helicopter.
The NPRM was prompted by AD No.
2008–0206, dated November 25, 2008,
issued by EASA, which is the Technical
Agent for the Member States of the
European Union, and AD No. CF–2009–
12, dated March 24, 2009, issued by the
TCCA, which is the aviation authority
for Canada. EASA issued AD No. 2008–
0206 to correct the unsafe condition for
ECD Model BO 105 A, BO 105 C, BO
105 LS A–1, BO 105 D, BO 105 DS, BO
105 DB, BO 105 DBS, BO 105 DB–4, BO
105 DBS–4, BO 105 DBS–5, BO 105 S,
MBB–BK 117 A–1, MBB–BK 117 A–3,
MBB–BK 117 A–4, MBB–BK 117 B–1,
MBB–BK 117 B–2, and MBB–BK 117 C–
1 helicopters. The TCCA issued AD No.
CF–2009–12 to correct the unsafe
condition for Eurocopter Model BO 105
LS A–3 helicopters. These ADs state
that during a periodical inspection,
corrosion was detected on the weights
in the area of the attachment thread.
Since the issuance of the Canadian AD,
the type certificate for the Model BO
105 LS A–3 has been transferred from
Eurocopter Canada Limited to
Eurocopter Deutschland (Germany).
Comments
We gave the public the opportunity to
participate in developing this AD, but
we did not receive any comments on the
NPRM (77 FR 52265, August 29, 2012).
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 the
EASA AD. We are issuing this AD
because we evaluated all information
provided by EASA and determined the
unsafe condition exists and is likely to
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Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations
exist or develop on other helicopters of
these same type designs and that air
safety and the public interest require
adopting the AD requirements as
proposed, except we are updating some
of the contact information to obtain
service information from American
Eurocopter Corporation and we are
incorporating the two figures by
reference instead of including them in
our AD to meet current publication
requirements. These minor changes are
consistent with the intent of the
proposals in the NPRM (77 FR 52265,
August 29, 2012) and will not increase
the economic burden on any operator
nor increase the scope of this AD.
Differences Between This AD and the
EASA and TCCA ADs
This AD does not provide an extra 60
flight hours or 6 months beyond the
repetitive compliance time of 600 flight
hours or 48 months for the repetitive
inspections. This AD only applies to
those model helicopters typecertificated in the United States.
emcdonald on DSK67QTVN1PROD with RULES
Related Service Information
Eurocopter issued Alert Service
Bulletin (ASB) No. ASB–MBB–BK117–
30–113, dated September 23, 2008, for
all MBB BK117 model ‘‘A–1 to C–1’’
helicopters; ASB No. ASB BO105–30–
116, dated September 23, 2008, for all
Model BO105 helicopters ‘‘including
BO105 CB–3 and BO105 CBS–5 KLH;’’
and Eurocopter Canada Limited issued
ASB No. ASB BO 105 LS 30–12, dated
December 12, 2008, for Model BO 105
LS A–3 helicopters. These ASBs specify
visually inspecting the weights and
levers to detect corrosion or mechanical
damage; corrosion at an advanced stage
could destroy the threads. These ASBs
also specify replacing damaged weights
and levers that exceed certain limits.
The actions described in the mandatory
EASA and TCCA ADs are intended to
correct the unsafe condition, identified
in these ASBs, to ensure the continued
airworthiness of these helicopters.
Costs of Compliance
We estimate that this AD will affect
33 helicopters of U.S. Registry. We
estimate that operators may incur the
following costs in order to comply with
this AD. It will take approximately 4
work-hours per helicopter to remove,
inspect, and install 2 lever assemblies
and 4 weights per helicopter at an
average labor rate of $85 per work-hour.
Based on these figures, we estimate the
inspection cost of this AD will cost $340
per helicopter or $11,220 on U.S.
operators per inspection cycle. The
required parts will cost about $5,332 per
helicopter. We estimate the cost for
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16:22 Aug 22, 2013
Jkt 229001
replacement will be $5,672 per
helicopter, assuming both lever
assemblies and all 4 weights are
replaced.
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
helicopters identified in this rulemaking
action.
Regulatory Findings
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 this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
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 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.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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52411
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2013–16–13 Eurocopter Deutschland GmbH
(ECD): Amendment 39–17551; Docket
No. FAA–2012–0887; Directorate
Identifier 2009–SW–02–AD.
(a) Applicability
This AD applies to Model BO–105A, BO–
105C, BO–105S, and BO–105LS A–1
helicopters, with a tail rotor control lever
(lever), part number (P/N) 105–317231, 105–
317365, 105–31736, 105–31767, 105–31728,
or 1121–31730, with tail rotor balance weight
(weight) P/N 117–31715.01, 117–31715.02,
105–31728.03, 105–31732.07, or 105–
31732.08; Model BO–105LS A–3 helicopters,
with lever P/N 105–31736 or 105–31767,
with weight P/N 117–31715.01, 117–
31715.02, B642M1011 201, or 105–
317171.10; and Model MBB–BK 117 A–1,
MBB–BK 117 A–3, MBB–BK 117 A–4, MBB–
BK117 B–1, MBB–BK 117 B–2, and MBB–BK
117 C–1 helicopters, with lever P/N 117–
31730, 117–317361, or 105–31736, with
weight P/N 117–31714.07, 117–31715.01,
117–31720.01, or 117–31730.02, certificated
in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as
corrosion or thread damage in the threaded
area of a lever or weight. This condition
could result in failure of a weight or lever,
separation of a tail rotor part, severe tail rotor
vibration, and subsequent loss of control of
the helicopter.
(c) Effective Date
This AD becomes effective September 27,
2013.
(d) 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.
(e) Required Actions
Within 100 hours time-in-service (TIS) or
2 months, whichever occurs first, and
thereafter at intervals not to exceed 600 hours
TIS or 48 months, whichever occurs first:
(1) Remove the weights from the lever as
depicted in Figure 1 of Eurocopter Alert
Service Bulletin (ASB) No. ASB–MBB–
BK117–30–113, dated September 23, 2008;
ASB No. ASB BO105–30–116, dated
September 23, 2008; or ASB No. ASB BO 105
LS 30–12, dated December 12, 2008; as
applicable to your model helicopter. Apply
marks to the weights before they are removed
in order to be able to re-establish the correct
assignment and the old installation position
towards the lever when the weights are
installed.
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Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations
emcdonald on DSK67QTVN1PROD with RULES
(2) Visually inspect each weight and lever
for corrosion and damage in the threaded
areas as depicted in Figure 2 of ASB No.
ASB–MBB–BK117–30–113, dated September
23, 2008; ASB No. ASB BO105–30–116,
dated September 23, 2008; or ASB No. ASB
BO 105 LS 30–12, dated December 12, 2008;
as applicable to your model helicopter.
(i) If there is no corrosion or thread damage
on either the weight or lever, before further
flight, reinstall the weight by following
paragraph (e)(3) of this AD.
(ii) If there is corrosion or thread damage
on the threaded portion of a weight:
(A) If the total area of corrosion or thread
damage, or both, covers less than 25 percent
of the length of the threaded area, the weight
can be threaded (screwed) onto the lever, and
the cylindrical mating surface has no
damage, before further flight, remove the
corrosion and reinstall the weight by
following paragraph (e)(3) of this AD.
(B) If the total area of corrosion or thread
damage, or both, covers 25 percent or more
of the length of the threaded area, the weight
cannot be threaded (screwed) onto the lever,
or the cylindrical mating surface has damage,
before further flight, replace the weight with
an airworthy weight by following paragraph
(e)(3) of this AD.
(iii) If there is corrosion or thread damage
on the threaded portion of the lever, polish
out the corrosion and thread damage using a
polishing cloth 600 and:
(A) If the thread depth does not exceed 0.3
millimeter (mm) and the diameter of the
lever in the area before the threaded area is
not less than 9.95 mm after polish out, before
further flight, install airworthy weights to the
lever by following paragraph (e)(3) of this
AD.
(B) If the thread depth is 0.3 mm or greater
or the diameter of the lever in the area before
the threaded area is less than 9.95 mm after
polish out, before further flight, replace the
lever with an airworthy lever.
(3) Apply corrosion preventive paste onto
the thread of the lever and install weights to
the lever as depicted in Figure 1 of ASB No.
ASB–MBB–BK117–30–113, dated September
23, 2008; ASB No. ASB BO105–30–116,
dated September 23, 2008; or ASB No. ASB
BO 105 LS 30–12, dated December 12, 2008;
as applicable to your model helicopter.
Ensure during installation of the weights that
the weights are correctly assigned and
installed to the control lever in accordance
with the applied marks.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Sharon Miles,
Aviation Safety Engineer, Regulations and
Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, TX 76137;
telephone (817) 222–5110; email
sharon.y.miles@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
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16:22 Aug 22, 2013
Jkt 229001
operating any aircraft complying with this
AD through an AMOC.
DEPARTMENT OF TRANSPORTATION
(g) Additional Information
Federal Aviation Administration
The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2008–0206, dated November 25, 2008,
and in Transport Canada Civil Aviation
(TCCA) AD No. CF–2009–12, dated March
24, 2009. You may view the EASA and the
TCCA AD on the Internet at https://
www.regulations.gov in Docket No. FAA–
2012–0887.
14 CFR Part 39
(h) Subject
AGENCY:
[Docket No. FAA–2013–0020; Directorate
Identifier 2010–SW–107–AD; Amendment
39–17558; AD 2013–16–20]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
Deutschland GmbH (ECD) Helicopters
Joint Aircraft Service Component (JASC)
Code: 6420, Tail Rotor Head.
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
(i) Material Incorporated by Reference
SUMMARY:
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Eurocopter Alert Service Bulletin (ASB)
No. ASB–MBB–BK117–30–113, dated
September 23, 2008.
(ii) Eurocopter ASB No. ASB BO105–30–
116, dated September 23, 2008.
(iii) Eurocopter ASB No. ASB BO 105 LS
30–12, dated December 12, 2008.
(3) For Eurocopter service information
identified in this 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 https://www.eurocopter.com/
techpub.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, TX 76137. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(5) You may view this service information
that is incorporated by reference 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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Fort Worth, Texas, on August 2,
2013.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
We are adopting a new
airworthiness directive (AD) for ECD
Model MBB–BK 117 C–2 helicopters.
This AD requires inspecting the rigging
of the power-boosted control system
and, if there is a nonparallel gap
between the rigging wedges and the
inner sleeves, performing a rigging
procedure. This AD was prompted by
the discovery, during rigging of the
main rotor controls, of movement of the
longitudinal main rotor actuator piston
after shut-down of the external pump
drive. Such movement could cause
incorrect rigging results. The actions of
this AD are intended to prevent
incorrect rigging results, which could
impair freedom of movement of the
upper controls and subsequent reduced
control of the helicopter.
DATES: This AD is effective September
27, 2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain document listed in this AD
as of September 27, 2013.
ADDRESSES: For service information
identified in this 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 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.
Examining the AD Docket
[FR Doc. 2013–19442 Filed 8–22–13; 8:45 am]
BILLING CODE 4910–13–P
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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 AD, any
incorporated-by-reference service
information, the foreign authority’s AD,
the economic evaluation, any comments
received, and other information. The
E:\FR\FM\23AUR1.SGM
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]]>Agencies
[Federal Register Volume 78, Number 164 (Friday, August 23, 2013)]
[Rules and Regulations]
[Pages 52410-52412]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-19442]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0887; Directorate Identifier 2009-SW-02-AD;
Amendment 39-17551; AD 2013-16-13]
RIN 2120-AA64
Airworthiness Directives; Eurocopter Deutschland GmbH Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for
Eurocopter Deutschland GmbH (ECD) Model BO-105A, BO-105C, BO-105S, BO-
105LS A-1, BO-105LS A-3, MBB-BK 117 A-1, MBB-BK 117 A-3, MBB-BK 117 A-
4, MBB-BK 117 B-1, MBB-BK-117 B-2, and MBB-BK 117 C-1 helicopters to
require inspections for corrosion or thread damage to each tail rotor
balance weight (weight) and each tail rotor control lever (lever). This
AD was prompted by a European Aviation Safety Agency (EASA) AD and a
Transport Canada Civil Aviation (TCCA) AD, both issued based on a
report that corrosion was detected on a weight in the area of the
attachment thread on a model BO-105 helicopter. The actions of this AD
are intended to detect corrosion and thread damage in the threaded area
of the weight and lever, and to prevent failure of a weight or lever,
separation of tail rotor parts, severe vibration, and subsequent loss
of control of the helicopter.
DATES: This AD is effective September 27, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of September 27,
2013.
ADDRESSES: For service information identified in this 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 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, TX 76137.
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 AD, the EASA and TCCA ADs, any
incorporated-by-reference service information, the economic evaluation,
any comments received, and other information. The street address for
the Docket Operations Office (phone: 800-647-5527) is U.S. Department
of Transportation, Docket Operations Office, M-30, West Building Ground
Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222-5110;
email sharon.y.miles@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On August 29, 2012, at 77 FR 52265, the Federal Register published
our notice of proposed rulemaking (NPRM), which proposed to amend 14
CFR part 39 to include an AD that would apply to ECD Model BO-105A, BO-
105C, BO-105S, BO-105LS A-1, BO-105LS A-3, MBB-BK 117 A-1, MBB-BK 117
A-3, MBB-BK 117 A-4, MBB-BK117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1
helicopters with certain levers and weights installed. The NPRM
proposed to require conducting repetitive visual inspections of each
weight and lever and proposed procedures for installing a weight or
lever. Additionally, the NPRM proposed allowable tolerances for
corrosion or thread damage on the threaded portion of a weight or lever
and proposed to require that a part with corrosion or mechanical damage
in excess of allowable tolerances be replaced with an airworthy part.
The proposed requirements were intended to detect corrosion and thread
damage in the threaded area of a weight or lever, to prevent failure of
a weight or lever, separation of tail rotor parts, severe vibration,
and subsequent loss of control of the helicopter.
The NPRM was prompted by AD No. 2008-0206, dated November 25, 2008,
issued by EASA, which is the Technical Agent for the Member States of
the European Union, and AD No. CF-2009-12, dated March 24, 2009, issued
by the TCCA, which is the aviation authority for Canada. EASA issued AD
No. 2008-0206 to correct the unsafe condition for ECD Model BO 105 A,
BO 105 C, BO 105 LS A-1, BO 105 D, BO 105 DS, BO 105 DB, BO 105 DBS, BO
105 DB-4, BO 105 DBS-4, BO 105 DBS-5, BO 105 S, MBB-BK 117 A-1, MBB-BK
117 A-3, MBB-BK 117 A-4, MBB-BK 117 B-1, MBB-BK 117 B-2, and MBB-BK 117
C-1 helicopters. The TCCA issued AD No. CF-2009-12 to correct the
unsafe condition for Eurocopter Model BO 105 LS A-3 helicopters. These
ADs state that during a periodical inspection, corrosion was detected
on the weights in the area of the attachment thread. Since the issuance
of the Canadian AD, the type certificate for the Model BO 105 LS A-3
has been transferred from Eurocopter Canada Limited to Eurocopter
Deutschland (Germany).
Comments
We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM (77 FR 52265,
August 29, 2012).
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
the EASA AD. We are issuing this AD because we evaluated all
information provided by EASA and determined the unsafe condition exists
and is likely to
[[Page 52411]]
exist or develop on other helicopters of these same type designs and
that air safety and the public interest require adopting the AD
requirements as proposed, except we are updating some of the contact
information to obtain service information from American Eurocopter
Corporation and we are incorporating the two figures by reference
instead of including them in our AD to meet current publication
requirements. These minor changes are consistent with the intent of the
proposals in the NPRM (77 FR 52265, August 29, 2012) and will not
increase the economic burden on any operator nor increase the scope of
this AD.
Differences Between This AD and the EASA and TCCA ADs
This AD does not provide an extra 60 flight hours or 6 months
beyond the repetitive compliance time of 600 flight hours or 48 months
for the repetitive inspections. This AD only applies to those model
helicopters type-certificated in the United States.
Related Service Information
Eurocopter issued Alert Service Bulletin (ASB) No. ASB-MBB-BK117-
30-113, dated September 23, 2008, for all MBB BK117 model ``A-1 to C-
1'' helicopters; ASB No. ASB BO105-30-116, dated September 23, 2008,
for all Model BO105 helicopters ``including BO105 CB-3 and BO105 CBS-5
KLH;'' and Eurocopter Canada Limited issued ASB No. ASB BO 105 LS 30-
12, dated December 12, 2008, for Model BO 105 LS A-3 helicopters. These
ASBs specify visually inspecting the weights and levers to detect
corrosion or mechanical damage; corrosion at an advanced stage could
destroy the threads. These ASBs also specify replacing damaged weights
and levers that exceed certain limits. The actions described in the
mandatory EASA and TCCA ADs are intended to correct the unsafe
condition, identified in these ASBs, to ensure the continued
airworthiness of these helicopters.
Costs of Compliance
We estimate that this AD will affect 33 helicopters of U.S.
Registry. We estimate that operators may incur the following costs in
order to comply with this AD. It will take approximately 4 work-hours
per helicopter to remove, inspect, and install 2 lever assemblies and 4
weights per helicopter at an average labor rate of $85 per work-hour.
Based on these figures, we estimate the inspection cost of this AD will
cost $340 per helicopter or $11,220 on U.S. operators per inspection
cycle. The required parts will cost about $5,332 per helicopter. We
estimate the cost for replacement will be $5,672 per helicopter,
assuming both lever assemblies and all 4 weights are replaced.
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 helicopters identified in this
rulemaking action.
Regulatory Findings
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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under 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 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.
Adoption of the Amendment
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. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2013-16-13 Eurocopter Deutschland GmbH (ECD): Amendment 39-17551;
Docket No. FAA-2012-0887; Directorate Identifier 2009-SW-02-AD.
(a) Applicability
This AD applies to Model BO-105A, BO-105C, BO-105S, and BO-105LS
A-1 helicopters, with a tail rotor control lever (lever), part
number (P/N) 105-317231, 105-317365, 105-31736, 105-31767, 105-
31728, or 1121-31730, with tail rotor balance weight (weight) P/N
117-31715.01, 117-31715.02, 105-31728.03, 105-31732.07, or 105-
31732.08; Model BO-105LS A-3 helicopters, with lever P/N 105-31736
or 105-31767, with weight P/N 117-31715.01, 117-31715.02, B642M1011
201, or 105-317171.10; and Model MBB-BK 117 A-1, MBB-BK 117 A-3,
MBB-BK 117 A-4, MBB-BK117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1
helicopters, with lever P/N 117-31730, 117-317361, or 105-31736,
with weight P/N 117-31714.07, 117-31715.01, 117-31720.01, or 117-
31730.02, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as corrosion or thread
damage in the threaded area of a lever or weight. This condition
could result in failure of a weight or lever, separation of a tail
rotor part, severe tail rotor vibration, and subsequent loss of
control of the helicopter.
(c) Effective Date
This AD becomes effective September 27, 2013.
(d) 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.
(e) Required Actions
Within 100 hours time-in-service (TIS) or 2 months, whichever
occurs first, and thereafter at intervals not to exceed 600 hours
TIS or 48 months, whichever occurs first:
(1) Remove the weights from the lever as depicted in Figure 1 of
Eurocopter Alert Service Bulletin (ASB) No. ASB-MBB-BK117-30-113,
dated September 23, 2008; ASB No. ASB BO105-30-116, dated September
23, 2008; or ASB No. ASB BO 105 LS 30-12, dated December 12, 2008;
as applicable to your model helicopter. Apply marks to the weights
before they are removed in order to be able to re-establish the
correct assignment and the old installation position towards the
lever when the weights are installed.
[[Page 52412]]
(2) Visually inspect each weight and lever for corrosion and
damage in the threaded areas as depicted in Figure 2 of ASB No. ASB-
MBB-BK117-30-113, dated September 23, 2008; ASB No. ASB BO105-30-
116, dated September 23, 2008; or ASB No. ASB BO 105 LS 30-12, dated
December 12, 2008; as applicable to your model helicopter.
(i) If there is no corrosion or thread damage on either the
weight or lever, before further flight, reinstall the weight by
following paragraph (e)(3) of this AD.
(ii) If there is corrosion or thread damage on the threaded
portion of a weight:
(A) If the total area of corrosion or thread damage, or both,
covers less than 25 percent of the length of the threaded area, the
weight can be threaded (screwed) onto the lever, and the cylindrical
mating surface has no damage, before further flight, remove the
corrosion and reinstall the weight by following paragraph (e)(3) of
this AD.
(B) If the total area of corrosion or thread damage, or both,
covers 25 percent or more of the length of the threaded area, the
weight cannot be threaded (screwed) onto the lever, or the
cylindrical mating surface has damage, before further flight,
replace the weight with an airworthy weight by following paragraph
(e)(3) of this AD.
(iii) If there is corrosion or thread damage on the threaded
portion of the lever, polish out the corrosion and thread damage
using a polishing cloth 600 and:
(A) If the thread depth does not exceed 0.3 millimeter (mm) and
the diameter of the lever in the area before the threaded area is
not less than 9.95 mm after polish out, before further flight,
install airworthy weights to the lever by following paragraph (e)(3)
of this AD.
(B) If the thread depth is 0.3 mm or greater or the diameter of
the lever in the area before the threaded area is less than 9.95 mm
after polish out, before further flight, replace the lever with an
airworthy lever.
(3) Apply corrosion preventive paste onto the thread of the
lever and install weights to the lever as depicted in Figure 1 of
ASB No. ASB-MBB-BK117-30-113, dated September 23, 2008; ASB No. ASB
BO105-30-116, dated September 23, 2008; or ASB No. ASB BO 105 LS 30-
12, dated December 12, 2008; as applicable to your model helicopter.
Ensure during installation of the weights that the weights are
correctly assigned and installed to the control lever in accordance
with the applied marks.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Sharon Miles, Aviation Safety
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222-5110;
email sharon.y.miles@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.
(g) Additional Information
The subject of this AD is addressed in European Aviation Safety
Agency (EASA) AD No. 2008-0206, dated November 25, 2008, and in
Transport Canada Civil Aviation (TCCA) AD No. CF-2009-12, dated
March 24, 2009. You may view the EASA and the TCCA AD on the
Internet at https://www.regulations.gov in Docket No. FAA-2012-0887.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6420, Tail Rotor
Head.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Eurocopter Alert Service Bulletin (ASB) No. ASB-MBB-BK117-
30-113, dated September 23, 2008.
(ii) Eurocopter ASB No. ASB BO105-30-116, dated September 23,
2008.
(iii) Eurocopter ASB No. ASB BO 105 LS 30-12, dated December 12,
2008.
(3) For Eurocopter service information identified in this 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 https://www.eurocopter.com/techpub.
(4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663,
Fort Worth, TX 76137. For information on the availability of this
material at the FAA, call (817) 222-5110.
(5) You may view this service information that is incorporated
by reference 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Fort Worth, Texas, on August 2, 2013.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2013-19442 Filed 8-22-13; 8:45 am]
BILLING CODE 4910-13-P
