Airworthiness Directives; Eurocopter France (Eurocopter) Helicopters, 5251-5254 [2014-01467]
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Federal Register / Vol. 79, No. 21 / Friday, January 31, 2014 / Rules and Regulations
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:
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
emcdonald on DSK67QTVN1PROD with RULES
2014–02–02 Bell Helicopter Textron
Canada Limited: Amendment 39–17730;
Docket No. FAA–2013–0525; Directorate
Identifier 2011–SW–063–AD.
17:58 Jan 30, 2014
Jkt 232001
(c) Effective Date
This AD becomes effective March 7, 2014.
(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) Actions Required
Within 100 hours time-in-service (TIS):
(1) For each M/R blade with an S/N listed
in Table 1 of the ASB, measure the M/R blade
spar spacer by following the
Accomplishment Instructions, Part II A),
paragraphs 1 through 3, of the ASB. If the
spar spacer measures more than 1.018 inches
(25.86 millimeters), reidentify the blade by
following Part II A, paragraph 5.a. and Table
3, of the ASB.
(2) For each M/R blade with an S/N listed
in Table 2 of the ASB, measure the M/R blade
spar spacer by following the
Accomplishment Instructions, Part II B,
paragraphs 1 through 3, of the ASB. If the
spar spacer measures more than 1.018 inches
(25.86 millimeters), reidentify the blade by
following Part II B, paragraph 5 and Table 4,
of the ASB.
(3) For each reidentified blade, reduce the
life limit from 3,600 hours TIS to 2,300 hours
TIS, and make an entry on the component
history card or equivalent record.
(4) Before further flight, remove any blade
that exceeds the new retirement life of 2,300
hours TIS.
(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) Bell Helicopter Alert Service Bulletin
No. 206L–09–163, Revision A, dated April
19, 2012.
(ii) Reserved.
(3) For Bell Helicopter service information
identified in this AD, contact Bell Helicopter
Textron Canada Limited, 12,800 Rue de
l’Avenir, Mirabel, Quebec J7J1R4; telephone
(450) 437–2862 or (800) 363–8023; fax (450)
433–0272; or at https://
www.bellcustomer.com/files/.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 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 January 15,
2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
[FR Doc. 2014–01466 Filed 1–30–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Sharon Miles,
Aerospace Engineer, FAA, Rotorcraft
Directorate, Regulations and Policy Group,
2601 Meacham Blvd., Fort Worth, Texas
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.
Federal Aviation Administration
(g) Additional Information
(a) Applicability
This AD applies to Model 206L, L–1, L–3,
and L–4 helicopters with a main rotor (M/R)
blade, part number (P/N) 206–015–001–115,
–117, –119, or –121, with a serial number (S/
N) listed in Table 1 or 2 of Bell Helicopter
Alert Service Bulletin [No. 206L–09–163,
Revision A, dated April 19, 2012 (ASB),
certificated in any category.
VerDate Mar<15>2010
This AD defines the unsafe condition as
the manufacture of an M/R blade with an
oversized spar spacer. This condition could
result in failure of an M/R blade and
subsequent loss of control of the helicopter.
(f) Alternative Methods of Compliance
(AMOCs)
PART 39—AIRWORTHINESS
DIRECTIVES
§ 39.13
(b) Unsafe Condition
5251
The subject of this AD is addressed in
Transport Canada Civil Aviation (TCCA) AD
CF–2011–43, dated November 10, 2011. You
may view the TCCA AD on the internet at
https://www.regulations.gov in Docket No.
FAA–2013–0525.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6210 Main Rotor Blades.
PO 00000
Frm 00029
Fmt 4700
Sfmt 4700
14 CFR Part 39
[Docket No. FAA–2013–0679; Directorate
Identifier 2009–SW–015–AD; Amendment
39–17733; AD 2014–02–05]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France (Eurocopter) Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for
Eurocopter Model AS350B, AS350BA,
AS350B1, AS350B2, AS350B3, AS350C,
AS350D, and AS350D1 helicopters. This
AD requires measuring the distance
between the end of the main rotor
collective pitch lever (collective)
locking stud (locking stud) and the
locking strip and repairing the locking
stud if the clearance is insufficient. This
SUMMARY:
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Federal Register / Vol. 79, No. 21 / Friday, January 31, 2014 / Rules and Regulations
AD was prompted by a report that
insufficient distance between the
locking stud and the locking strip may
cause the collective to become
inadvertently locked in the low pitch
(low) position. The actions of this AD
are intended to prevent the collective
from becoming inadvertently locked in
the low position and subsequent loss of
control of the helicopter.
DATES: This AD is effective March 7,
2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain document listed in this AD
as of March 7, 2014.
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.
emcdonald on DSK67QTVN1PROD with RULES
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 foreign
authority’s AD, 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:
Robert Grant, Aviation Safety Engineer,
Safety Management Group, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone 817–222–5110; email
robert.grant@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On August 5, 2013, at 78 FR 47230,
the Federal Register published our
notice of proposed rulemaking (NPRM),
which proposed to amend 14 CFR part
39 by adding an AD that would apply
to Eurocopter Model AS350B,
AS350BA, AS350B1, AS350B2,
AS350B3, AS350C, AS350D, and
AS350D1 helicopters. The NPRM
proposed to require measuring the
distance between the end of the
VerDate Mar<15>2010
17:58 Jan 30, 2014
Jkt 232001
collective locking stud and the locking
strip and repairing the locking stud if
the clearance is insufficient. The
proposed requirements were intended to
prevent the collective from becoming
inadvertently locked in the low position
and subsequent loss of control of the
helicopter.
The NPRM was prompted by AD No.
2009–0019, dated February 3, 2009,
issued by the European Aviation Safety
Agency (EASA), which is the Technical
Agent for the Member States of the
European Union, to correct an unsafe
condition for the Eurocopter Model
AS350 helicopters. EASA advises that
the clearance between the collective
locking stud and the locking strip may
be insufficient when the collective is
positioned in the low pitch stop. During
an autorotation test flight, the collective
rubbed against the locking strip in the
low pitch position. The rubbing was due
to inadequate clearance and could result
in the collective being inadvertently
locked in the low pitch position.
Comments
We gave the public the opportunity to
participate in developing this AD, but
we did not receive any comments on the
NPRM (78 FR 47230, August 5, 2013).
FAA’s Determination
These helicopters have been approved
by the aviation authority of France and
are approved for operation in the United
States. Pursuant to our bilateral
agreement with France, 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
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.
Differences Between This AD and the
EASA AD
The EASA AD does not apply to
Model AS350C or AS350D1 helicopters,
and this AD applies to these models
because they have a similarly-designed
collective pitch lock. The EASA AD
applies to the Model AS350BB, and this
AD does not because that model does
not have a U.S. type certificate. This AD
requires an initial inspection within 100
hours time-in-service, while the EASA
AD requires this inspection ‘‘after the
last flight of the day.’’
Related Service Information
Eurocopter issued Service Bulletin
No. 67.00.37, Revision 2, dated
PO 00000
Frm 00030
Fmt 4700
Sfmt 4700
December 2, 2008, originally issued on
September 27, 2007, and also identified
as modification (MOD) 073237, which
contains procedures for replacing the
locking stud on the collective levers
with a new locking stud with higher
wear resistance. The new locking stud is
longer than the previous one and has
reduced the distance between the
locking stud and the locking strip. In
some cases, the reduced distance is
insufficient when the collective is
positioned in the low pitch position
causing the collective to lock in that
position. As a result, Eurocopter has
issued one Emergency Alert Service
Bulletin (EASB), Revision 0, dated
January 12, 2008, with two numbers.
EASB No. 05.00.58 is for civil Model
AS350B, BA, BB, B1, B2, B3, and D
helicopters and military Model
AS350L1 helicopters. EASB No.
05.00.35 is for military Model AS550A2,
C2, C3, and U2 helicopters. The EASB
specifies measuring to ensure a required
minimum distance between the locking
stud and the locking strip and specifies
a repair solution in case the distance is
insufficient. As a precaution, Eurocopter
extended the measure and repair to
helicopters with locking studs before
MOD 073237. Eurocopter also revised
Service Bulletin No. 67.00.37 to include
these procedures.
Costs of Compliance
We estimate that this AD will affect
651 helicopters of U.S. Registry. We
estimate that operators may incur the
following costs to comply with this AD.
We estimate 1 work hour to measure the
clearance and repair the locking stud
and locking strip at $85 per work hour.
Required parts will cost $95 per
helicopter. Based on these estimates, the
total cost per helicopter will be $180,
and the total cost for the fleet will be
$117,180.
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
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Federal Register / Vol. 79, No. 21 / Friday, January 31, 2014 / Rules and Regulations
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
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):
■
emcdonald on DSK67QTVN1PROD with RULES
2014–02–05 Eurocopter France Helicopters:
Amendment 39–17733; Docket No.
FAA–2013–0679; Directorate Identifier
2009–SW–015–AD.
(a) Applicability
This AD applies to Eurocopter Model
AS350B, AS350BA, AS350B1, AS350B2,
AS350B3, AS350C, AS350D, and AS350D1
helicopters, certificated in any category,
without modification (MOD) 073175
installed; with MOD 073237 installed in
accordance with Eurocopter Service Bulletin
No. 67.00.37, Revision 0, dated September
VerDate Mar<15>2010
17:58 Jan 30, 2014
Jkt 232001
27, 2007, or Revision 1, dated February 6,
2008; or with one of the following serial
numbers: 3972, 3973, 3982, 3987, 4003, 4023,
4046, 4050, 4086, 4120, 4122, 4132, 4143,
4152, 4172, 4194, 4259, 4314, 4324, 4378,
4392, 4447, 4452, 4477, 4489, 4490, 4501,
4523, 4546, 4560, 4589, 4594, 4599, 4632,
4659, 4666, or 4671.
(b) Unsafe Condition
This AD defines the unsafe condition as
the main rotor collective pitch lever
(collective) locking stud (locking stud)
inadvertently locking in the low pitch (low)
position, which could result in subsequent
loss of control of the helicopter.
(c) Effective Date
This AD becomes effective March 7, 2014.
(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
(1) For helicopters with MOD 073237
installed, within 100 hours time-in-service
(TIS):
(i) With the collective (item b) in the low
position but not locked on the locking strip
(item a), measure the distance between the
end of the locking stud (item c) and the
locking strip as indicated by dimension ‘‘J’’
in Figure 2 of Eurocopter Emergency Alert
Service Bulletin No. 05.00.58, Revision 0,
dated January 12, 2008 (EASB 05.00.58).
(ii) If the distance between the end of the
locking stud and the locking strip is equal to
or more than 3 millimeters (mm), no further
action is required.
(iii) If the distance between the end of the
locking stud and the locking strip is less than
3 mm and MOD 073175 is not installed,
inspect to determine whether the grommet in
the locking strip is seated against the console
as shown in Figure 2 of EASB 05.00.58.
(A) If the grommet is not seated against the
console, restore the original profile of the
locking strip by doing the following:
(1) Clamp the locking strip in a vice with
soft jaws and apply load progressively to the
locking strip to restore the original profile of
the locking strip.
(2) With the collective in the low position
but not locked on the locking strip, measure
the distance between the end of the locking
stud and the locking strip as indicated by
dimension ‘‘J’’ in Figure 2 of EASB 05.00.58.
(3) If the distance between the end of the
locking stud and the locking strip is equal to
or more than 3 mm, no further action is
required.
(4) If the distance between the end of the
locking stud and the locking strip is less than
3 mm, adjust the length of the locking stud
and re-identify the locking stud by following
the Accomplishment Instructions, paragraph
2.B.2.c., of EASB 05.00.58, except you are not
required to comply with paragraph 2.B.4 of
EASB 05.00.58.
(B) If the grommet is seated against the
console, adjust the length of the locking stud
and re-identify the locking stud by following
the Accomplishment Instructions, paragraph
2.B.2.c, of EASB 05.00.58, except you are not
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Fmt 4700
Sfmt 4700
5253
required to comply with paragraph 2.B.4 of
EASB 05.00.58.
(iv) If the distance between the end of the
locking stud and the locking strip is less than
3 mm and MOD 073175 is installed, adjust
the length of the locking stud and re-identify
the locking stud by following the
Accomplishment Instructions, paragraph
2.B.2.c., of EASB 05.00.58, except you are not
required to comply with paragraph 2.B.4 of
EASB 05.00.58.
(v) After adjusting the length of the locking
stud in accordance with paragraph 2.B.2.c of
the EASB, determine whether the distance
between the end of the locking stud and the
locking strip is equal to or more than 3 mm.
(A) If the distance between the end of the
locking stud and the locking strip is equal to
or more than 3 mm, no further action is
required.
(B) If the distance between the end of the
locking stud and the locking strip is less than
3 mm, do not approve the helicopter for
return to service until the distance between
the end of the locking stud and the locking
strip is equal to or more than 3 mm.
(2) For helicopters without MOD 073237
installed, within 100 hours TIS:
(i) With the collective in the low position
but not locked on the locking strip, measure
the distance between the end of the locking
stud and the locking strip as indicated by
dimension ‘‘J’ in Figure 2 of EASB 05.00.58.
(ii) If the distance between the end of the
locking stud and the locking strip is equal to
or more than 3 mm, no further action is
needed.
(iii) If the distance between the end of the
locking stud and the locking strip is less than
3 mm and MOD 073175 is not installed,
inspect to determine whether the grommet in
the locking strip is seated against the console
as shown in Figure 2 of EASB 05.00.58.
(A) If the grommet is not seated against the
console, restore the original profile of the
locking strip by doing the following:
(1) Clamp the locking strip in a vice with
soft jaws and apply load progressively to the
locking strip.
(2) With the collective in the low position
but not locked on the locking strip, measure
the distance between the end of the locking
stud and the locking strip as indicated by
dimension ‘‘J’’ in Figure 2 of the EASB
05.00.58.
(3) If the distance between the end of the
locking stud and the locking strip is equal to
or more than 3 mm, no further action is
required.
(4) If the distance between the end of the
locking stud and the locking strip is less than
3 mm, do not approve the helicopter for
return to service until the distance between
the end of the locking stud and the locking
strip is equal to or more than 3 mm.
(B) If the grommet is seated against the
console, do not approve the helicopter for
return to service until the distance between
the end of the locking stud and the locking
strip is equal to or more than 3 mm.
(iv) If the distance between the end of the
locking stud and the locking strip is less than
3 mm and MOD 073175 is installed, do not
approve the helicopter for return to service
until the distance between the end of the
locking stud and the locking strip is equal to
or more than 3 mm.
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(3) Repeat the measurement requirement in
paragraphs (e)(1) or (e)(2) of this AD as
applicable to your helicopter each time the
collective, locking stud, or locking strip is
replaced; each time the locking strip setting
is readjusted; or at intervals not exceeding
660 hours TIS or 2 years, whichever occurs
first.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Robert Grant,
Aviation Safety Engineer, Safety Management
Group, FAA, 2601 Meacham Blvd., Fort
Worth, Texas 76137; telephone 817–222–
5110; email robert.grant@faa.gov.
(2) For operations conducted under 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
(1) Eurocopter Service Bulletin (SB) No.
67.00.21, Revision 1, dated June 21, 2006,
and SB No. 67.00.37, Revision 2, dated
December 2, 2008, which are not
incorporated by reference, contain additional
information about the subject of this AD. 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.
(2) The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2009–0019, dated February 3, 2009. You
may view the EASA AD on the Internet at
https://www.regulations.gov in Docket No.
FAA–2013–0679.
emcdonald on DSK67QTVN1PROD with RULES
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6710 Main Rotor Control.
(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 Emergency Alert Service
Bulletin No. 05.00.58, Revision 0, dated
January 12, 2008.
(ii) Reserved.
Note 1 to paragraph (i)(2): Eurocopter
Emergency Alert Service Bulletin (EASB) No.
05.00.58, Revision 0, dated January 12, 2008,
is co-published in one document with
Eurocopter EASB No. 05.00.35, Revision 0,
dated January 12, 2008, which is not
incorporated by reference in this AD.
VerDate Mar<15>2010
17:58 Jan 30, 2014
Jkt 232001
(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.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 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 January 16,
2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
of a certain publication listed in this AD
as of March 7, 2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of January 18, 2012 (77 FR
2439, January 18, 2012).
ADDRESSES: For service information
identified in this AD, contact Beechcraft
Corporation at P.O. Box 85, Wichita,
Kansas 67201–0085; telephone: (800)
429–5372 or (316) 676–3140; Internet:
https://www.beechcraft.com. Beechcraft
Corporation publishes service
information for the Beechcraft
Corporation airplanes affected by this
AD action. You may review copies of
the referenced service information at the
FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106.
For information on the availability of
this material at the FAA, call (816) 329–
4148.
[FR Doc. 2014–01467 Filed 1–30–14; 8:45 am]
Examining the AD Docket
BILLING CODE 4910–13–P
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2013–
0611; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Don
Ristow, Aerospace Engineer, Wichita
Aircraft Certification Office, FAA, 1801
Airport Road, Room 100, Wichita,
Kansas 67209; telephone: (316) 946–
4120; fax: (316) 946–4107; email:
donald.ristow@faa.gov.
SUPPLEMENTARY INFORMATION:
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0611; Directorate
Identifier 2013–CE–019–AD; Amendment
39–17731; AD 2014–02–03]
RIN 2120–AA64
Airworthiness Directives; Beechcraft
Corporation Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2011–27–
51 for certain Beechcraft Corporation
Models 1900, 1900C, and 1900D
airplanes. AD 2011–27–51 required
inspecting the elevator bob-weight and
attaching linkage for correct installation
and for damage or deformation to the
weight and/or weight bracket with
corrective action as necessary. This AD
requires installation of the secondary
elevator bob-weight stop bolt. The
elevator bob-weight (stabilizer weight)
traveling past its stop bolt may allow the
attaching linkage to move over-center
and lead to reduced nose down elevator
control. We are issuing this AD to
correct the unsafe condition on these
products.
SUMMARY:
This AD is effective March 7,
2014.
The Director of the Federal Register
approved the incorporation by reference
DATES:
PO 00000
Frm 00032
Fmt 4700
Sfmt 4700
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2011–27–51,
Amendment 39–16915 (77 FR 2439,
January 18, 2012), (‘‘AD 2011–27–51’’).
AD 2011–27–51 applied to certain
Beechcraft Corporation Models 1900,
1900C, and 1900D airplanes. The NPRM
published in the Federal Register on
July 17, 2013 (78 FR 42724). The NPRM
proposed to retain all of the
requirements of AD 2011–27–51 and
add the requirement to install the
secondary elevator bob-weight stop bolt,
Kit 114–5060. We are issuing this AD to
E:\FR\FM\31JAR1.SGM
31JAR1
]]>Agencies
[Federal Register Volume 79, Number 21 (Friday, January 31, 2014)]
[Rules and Regulations]
[Pages 5251-5254]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-01467]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0679; Directorate Identifier 2009-SW-015-AD;
Amendment 39-17733; AD 2014-02-05]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France (Eurocopter)
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for
Eurocopter Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C,
AS350D, and AS350D1 helicopters. This AD requires measuring the
distance between the end of the main rotor collective pitch lever
(collective) locking stud (locking stud) and the locking strip and
repairing the locking stud if the clearance is insufficient. This
[[Page 5252]]
AD was prompted by a report that insufficient distance between the
locking stud and the locking strip may cause the collective to become
inadvertently locked in the low pitch (low) position. The actions of
this AD are intended to prevent the collective from becoming
inadvertently locked in the low position and subsequent loss of control
of the helicopter.
DATES: This AD is effective March 7, 2014.
The Director of the Federal Register approved the incorporation by
reference of a certain document listed in this AD as of March 7, 2014.
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
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 foreign authority's AD,
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: Robert Grant, Aviation Safety
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth,
Texas 76137; telephone 817-222-5110; email robert.grant@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On August 5, 2013, at 78 FR 47230, the Federal Register published
our notice of proposed rulemaking (NPRM), which proposed to amend 14
CFR part 39 by adding an AD that would apply to Eurocopter Model
AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, and AS350D1
helicopters. The NPRM proposed to require measuring the distance
between the end of the collective locking stud and the locking strip
and repairing the locking stud if the clearance is insufficient. The
proposed requirements were intended to prevent the collective from
becoming inadvertently locked in the low position and subsequent loss
of control of the helicopter.
The NPRM was prompted by AD No. 2009-0019, dated February 3, 2009,
issued by the European Aviation Safety Agency (EASA), which is the
Technical Agent for the Member States of the European Union, to correct
an unsafe condition for the Eurocopter Model AS350 helicopters. EASA
advises that the clearance between the collective locking stud and the
locking strip may be insufficient when the collective is positioned in
the low pitch stop. During an autorotation test flight, the collective
rubbed against the locking strip in the low pitch position. The rubbing
was due to inadequate clearance and could result in the collective
being inadvertently locked in the low pitch position.
Comments
We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM (78 FR 47230,
August 5, 2013).
FAA's Determination
These helicopters have been approved by the aviation authority of
France and are approved for operation in the United States. Pursuant to
our bilateral agreement with France, 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 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.
Differences Between This AD and the EASA AD
The EASA AD does not apply to Model AS350C or AS350D1 helicopters,
and this AD applies to these models because they have a similarly-
designed collective pitch lock. The EASA AD applies to the Model
AS350BB, and this AD does not because that model does not have a U.S.
type certificate. This AD requires an initial inspection within 100
hours time-in-service, while the EASA AD requires this inspection
``after the last flight of the day.''
Related Service Information
Eurocopter issued Service Bulletin No. 67.00.37, Revision 2, dated
December 2, 2008, originally issued on September 27, 2007, and also
identified as modification (MOD) 073237, which contains procedures for
replacing the locking stud on the collective levers with a new locking
stud with higher wear resistance. The new locking stud is longer than
the previous one and has reduced the distance between the locking stud
and the locking strip. In some cases, the reduced distance is
insufficient when the collective is positioned in the low pitch
position causing the collective to lock in that position. As a result,
Eurocopter has issued one Emergency Alert Service Bulletin (EASB),
Revision 0, dated January 12, 2008, with two numbers. EASB No. 05.00.58
is for civil Model AS350B, BA, BB, B1, B2, B3, and D helicopters and
military Model AS350L1 helicopters. EASB No. 05.00.35 is for military
Model AS550A2, C2, C3, and U2 helicopters. The EASB specifies measuring
to ensure a required minimum distance between the locking stud and the
locking strip and specifies a repair solution in case the distance is
insufficient. As a precaution, Eurocopter extended the measure and
repair to helicopters with locking studs before MOD 073237. Eurocopter
also revised Service Bulletin No. 67.00.37 to include these procedures.
Costs of Compliance
We estimate that this AD will affect 651 helicopters of U.S.
Registry. We estimate that operators may incur the following costs to
comply with this AD. We estimate 1 work hour to measure the clearance
and repair the locking stud and locking strip at $85 per work hour.
Required parts will cost $95 per helicopter. Based on these estimates,
the total cost per helicopter will be $180, and the total cost for the
fleet will be $117,180.
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
[[Page 5253]]
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):
2014-02-05 Eurocopter France Helicopters: Amendment 39-17733; Docket
No. FAA-2013-0679; Directorate Identifier 2009-SW-015-AD.
(a) Applicability
This AD applies to Eurocopter Model AS350B, AS350BA, AS350B1,
AS350B2, AS350B3, AS350C, AS350D, and AS350D1 helicopters,
certificated in any category, without modification (MOD) 073175
installed; with MOD 073237 installed in accordance with Eurocopter
Service Bulletin No. 67.00.37, Revision 0, dated September 27, 2007,
or Revision 1, dated February 6, 2008; or with one of the following
serial numbers: 3972, 3973, 3982, 3987, 4003, 4023, 4046, 4050,
4086, 4120, 4122, 4132, 4143, 4152, 4172, 4194, 4259, 4314, 4324,
4378, 4392, 4447, 4452, 4477, 4489, 4490, 4501, 4523, 4546, 4560,
4589, 4594, 4599, 4632, 4659, 4666, or 4671.
(b) Unsafe Condition
This AD defines the unsafe condition as the main rotor
collective pitch lever (collective) locking stud (locking stud)
inadvertently locking in the low pitch (low) position, which could
result in subsequent loss of control of the helicopter.
(c) Effective Date
This AD becomes effective March 7, 2014.
(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
(1) For helicopters with MOD 073237 installed, within 100 hours
time-in-service (TIS):
(i) With the collective (item b) in the low position but not
locked on the locking strip (item a), measure the distance between
the end of the locking stud (item c) and the locking strip as
indicated by dimension ``J'' in Figure 2 of Eurocopter Emergency
Alert Service Bulletin No. 05.00.58, Revision 0, dated January 12,
2008 (EASB 05.00.58).
(ii) If the distance between the end of the locking stud and the
locking strip is equal to or more than 3 millimeters (mm), no
further action is required.
(iii) If the distance between the end of the locking stud and
the locking strip is less than 3 mm and MOD 073175 is not installed,
inspect to determine whether the grommet in the locking strip is
seated against the console as shown in Figure 2 of EASB 05.00.58.
(A) If the grommet is not seated against the console, restore
the original profile of the locking strip by doing the following:
(1) Clamp the locking strip in a vice with soft jaws and apply
load progressively to the locking strip to restore the original
profile of the locking strip.
(2) With the collective in the low position but not locked on
the locking strip, measure the distance between the end of the
locking stud and the locking strip as indicated by dimension ``J''
in Figure 2 of EASB 05.00.58.
(3) If the distance between the end of the locking stud and the
locking strip is equal to or more than 3 mm, no further action is
required.
(4) If the distance between the end of the locking stud and the
locking strip is less than 3 mm, adjust the length of the locking
stud and re-identify the locking stud by following the
Accomplishment Instructions, paragraph 2.B.2.c., of EASB 05.00.58,
except you are not required to comply with paragraph 2.B.4 of EASB
05.00.58.
(B) If the grommet is seated against the console, adjust the
length of the locking stud and re-identify the locking stud by
following the Accomplishment Instructions, paragraph 2.B.2.c, of
EASB 05.00.58, except you are not required to comply with paragraph
2.B.4 of EASB 05.00.58.
(iv) If the distance between the end of the locking stud and the
locking strip is less than 3 mm and MOD 073175 is installed, adjust
the length of the locking stud and re-identify the locking stud by
following the Accomplishment Instructions, paragraph 2.B.2.c., of
EASB 05.00.58, except you are not required to comply with paragraph
2.B.4 of EASB 05.00.58.
(v) After adjusting the length of the locking stud in accordance
with paragraph 2.B.2.c of the EASB, determine whether the distance
between the end of the locking stud and the locking strip is equal
to or more than 3 mm.
(A) If the distance between the end of the locking stud and the
locking strip is equal to or more than 3 mm, no further action is
required.
(B) If the distance between the end of the locking stud and the
locking strip is less than 3 mm, do not approve the helicopter for
return to service until the distance between the end of the locking
stud and the locking strip is equal to or more than 3 mm.
(2) For helicopters without MOD 073237 installed, within 100
hours TIS:
(i) With the collective in the low position but not locked on
the locking strip, measure the distance between the end of the
locking stud and the locking strip as indicated by dimension ``J' in
Figure 2 of EASB 05.00.58.
(ii) If the distance between the end of the locking stud and the
locking strip is equal to or more than 3 mm, no further action is
needed.
(iii) If the distance between the end of the locking stud and
the locking strip is less than 3 mm and MOD 073175 is not installed,
inspect to determine whether the grommet in the locking strip is
seated against the console as shown in Figure 2 of EASB 05.00.58.
(A) If the grommet is not seated against the console, restore
the original profile of the locking strip by doing the following:
(1) Clamp the locking strip in a vice with soft jaws and apply
load progressively to the locking strip.
(2) With the collective in the low position but not locked on
the locking strip, measure the distance between the end of the
locking stud and the locking strip as indicated by dimension ``J''
in Figure 2 of the EASB 05.00.58.
(3) If the distance between the end of the locking stud and the
locking strip is equal to or more than 3 mm, no further action is
required.
(4) If the distance between the end of the locking stud and the
locking strip is less than 3 mm, do not approve the helicopter for
return to service until the distance between the end of the locking
stud and the locking strip is equal to or more than 3 mm.
(B) If the grommet is seated against the console, do not approve
the helicopter for return to service until the distance between the
end of the locking stud and the locking strip is equal to or more
than 3 mm.
(iv) If the distance between the end of the locking stud and the
locking strip is less than 3 mm and MOD 073175 is installed, do not
approve the helicopter for return to service until the distance
between the end of the locking stud and the locking strip is equal
to or more than 3 mm.
[[Page 5254]]
(3) Repeat the measurement requirement in paragraphs (e)(1) or
(e)(2) of this AD as applicable to your helicopter each time the
collective, locking stud, or locking strip is replaced; each time
the locking strip setting is readjusted; or at intervals not
exceeding 660 hours TIS or 2 years, whichever occurs first.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Robert Grant, Aviation Safety
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort
Worth, Texas 76137; telephone 817-222-5110; email
robert.grant@faa.gov.
(2) For operations conducted under 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
(1) Eurocopter Service Bulletin (SB) No. 67.00.21, Revision 1,
dated June 21, 2006, and SB No. 67.00.37, Revision 2, dated December
2, 2008, which are not incorporated by reference, contain additional
information about the subject of this AD. 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.
(2) The subject of this AD is addressed in European Aviation
Safety Agency (EASA) AD No. 2009-0019, dated February 3, 2009. You
may view the EASA AD on the Internet at https://www.regulations.gov
in Docket No. FAA-2013-0679.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6710 Main Rotor
Control.
(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 Emergency Alert Service Bulletin No. 05.00.58,
Revision 0, dated January 12, 2008.
(ii) Reserved.
Note 1 to paragraph (i)(2): Eurocopter Emergency Alert Service
Bulletin (EASB) No. 05.00.58, Revision 0, dated January 12, 2008, is
co-published in one document with Eurocopter EASB No. 05.00.35,
Revision 0, dated January 12, 2008, which is not incorporated by
reference in this AD.
(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.
(4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 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 January 16, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2014-01467 Filed 1-30-14; 8:45 am]
BILLING CODE 4910-13-P
