Airworthiness Directives; Eurocopter France (Eurocopter) Model Helicopters, 47230-47233 [2013-18854]
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Federal Register / Vol. 78, No. 150 / Monday, August 5, 2013 / Proposed Rules
We prepared a regulatory 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Thielert Aircraft Engines GmbH: Docket No.
FAA–2013–0561; Directorate Identifier
2013–NE–23–AD.
(a) Comments Due Date
We must receive comments by October 4,
2013.
(b) Affected ADs
None.
the procedures found in 14 CFR 39.19 to
make your request.
(g) Related Information
(1) For more information about this AD,
contact Frederick Zink, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
phone: 781–238–7779; fax: 781–238 7199;
email: frederick.zink@faa.gov.
(2) Refer to European Aviation Safety
Agency Airworthiness Directive 2013–0109,
dated May 22, 2013, for related information.
You may examine the AD on the Internet at
https://ad.easa.europa.eu/ad/2013–0109.
(3) Thielert Aircraft Engines GmbH Service
Bulletin No. TM TAE 125–0022, dated
August 8, 2012, which is not incorporated by
reference in this AD, can be obtained from
Thielert Aircraft Engines GmbH, using the
contact information in paragraph (g)(4) of this
AD.
(4) For service information identified in
this AD, contact Thielert Aircraft Engines
GmbH, Platanenstrasse 14 D–09350,
Lichtenstein, Germany, telephone: +49–
37204–696–0; fax: +49–37204–696–55; email:
info@centurion-engines.com. You may view
this service information at the FAA, Engine
& Propeller Directorate, 12 New England
Executive Park, Burlington, MA. For
information on the availability of this
material at the FAA, call 781–238–7125.
Issued in Burlington, Massachusetts, on
July 25, 2013.
Thomas A. Boudreau,
Acting Assistant Manager, Engine & Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 2013–18797 Filed 8–2–13; 8:45 am]
(d) Reason
This AD was prompted by a report of
engine power loss due to engine coolant
contaminating the engine clutch. The design
of the engine allows the crankcase assembly
opening to be susceptible to contamination
from external sources. We are issuing this AD
to prevent in-flight engine power loss, which
could result in loss of control of, and damage
to, the airplane.
emcdonald on DSK67QTVN1PROD with PROPOSALS
(c) Applicability
This AD applies to all Thielert Aircraft
Engines GmbH TAE 125–01 reciprocating
engines.
DEPARTMENT OF TRANSPORTATION
BILLING CODE 4910–13–P
(e) Actions and Compliance
Unless already done, do the following
actions.
(1) After the effective date of this AD at the
next annual or 100-hour inspection,
whichever comes first, apply sealant to close
the engine clutch housing (crankcase
assembly) opening.
(2) Thereafter, reapply sealant to the engine
clutch housing (crankcase assembly)
opening, whenever the sealant is found to be
not liquid-tight, or is removed.
(3) Guidance on the sealant and
application can be found in Thielert Aircraft
Engines GmbH Service Bulletin No.TM TAE
125–0022, dated August 8, 2012.
(f) Alternative Methods of Compliance
(AMOCs)
The Manager, Engine Certification Office,
FAA, may approve AMOCs to this AD. Use
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Jkt 229001
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0679; Directorate
Identifier 2009–SW–015–AD]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France (Eurocopter) Model Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for
Eurocopter Model AS350B, AS350BA,
AS350B1, AS350B2, AS350B3, AS350C,
AS350D, and AS350D1 helicopters. This
proposed AD would require 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 proposed AD is
SUMMARY:
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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 proposed actions are intended to
prevent the collective from becoming
inadvertently locked in the low position
and subsequent loss of control of the
helicopter.
DATES: We must receive comments on
this proposed AD by October 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, 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.
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:
Comments Invited
We invite you to participate in this
rulemaking by submitting written
comments, data, or views. We also
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Federal Register / Vol. 78, No. 150 / Monday, August 5, 2013 / Proposed Rules
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.
emcdonald on DSK67QTVN1PROD with PROPOSALS
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD No. 2009–
0019, dated February 3, 2009, 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.
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 its
AD. 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 products of the same
type design.
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
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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.
Proposed AD Requirements
The proposed AD would require
measuring the clearance between the
collective locking stud and the locking
strip. If insufficient clearance exists,
corrective actions are defined based on
the installed locking strip and locking
stud designs. Corrective actions include
restoring the original profile of certain
locking strips and adjusting the length
of certain collective locking studs.
Differences Between This Proposed AD
and the EASA AD
The EASA AD does not apply to
Model AS350C or AS350D1 helicopters,
and the proposed AD would apply to
these models because they have a
similarly-designed collective pitch lock.
The EASA AD applies to the Model
AS350BB, and the proposed AD does
not because that model does not have a
U.S. type certificate. The proposed AD
would require an initial inspection
within 100 hours time-in-service, while
the EASA AD requires this inspection
‘‘after the last flight of the day.’’
Costs of Compliance
We estimate that this proposed AD
would affect 651 helicopters of U.S.
Registry.
We estimate that operators may incur
the following costs in order to comply
with this AD. It would take 1 work hour
to measure the clearance and repair the
locking stud and locking strip at $85 per
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47231
work hour. Required parts would cost
$95 per helicopter. Based on these
estimates, the total cost per helicopter
would be $180, and the total cost for the
fleet would 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
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,
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47232
Federal Register / Vol. 78, No. 150 / Monday, August 5, 2013 / Proposed Rules
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Eurocopter France: 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, 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) Comments Due Date
We must receive comments by October 4,
2013.
emcdonald on DSK67QTVN1PROD with PROPOSALS
(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 the EASB.
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16:53 Aug 02, 2013
Jkt 229001
(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 the EASB.
(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 the EASB, except you are not
required to comply with paragraph 2.B.4 of
the EASB.
(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 the EASB, except you are not
required to comply with paragraph 2.B.4 of
the EASB.
(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 the EASB, except you are not
required to comply with paragraph 2.B.4 of
the EASB.
(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 the EASB.
(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 the EASB.
(A) If the grommet is not seated against the
console, restore the original profile of the
locking strip by doing the following:
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(1) Clamp the locking strip in a vice with
soft jaws and applying 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.
(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.
(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 time-in-service 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 Emergency Alert Service
Bulletin (EASB) No. 05.00.58, Revision 0,
dated January 12, 2008, is co-published in
one document with EASB No. 05.00.35,
which is not incorporated by reference in this
AD. 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.
(2) 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
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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.
(3) 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 at https://
www.regulations.gov by searching for and
locating it in Docket No. FAA–2013–0679.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6710 Main Rotor Control.
Issued in Fort Worth, Texas, on July 26,
2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2013–18854 Filed 8–2–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0670; Directorate
Identifier 2013–NM–081–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 737–600,
–700, –800, –900, and –900ER airplanes
modified by particular supplemental
type certificates (STC). This proposed
AD was prompted by reports of cracks
found during inspections of the in-flight
entertainment system radome assembly.
This proposed AD would require
repetitive detailed inspections for cracks
in the radome assembly, and
replacement of the radome if necessary.
We are proposing this AD to detect and
correct cracks in the radome assembly,
which could result in the radome (or
pieces) separating from the airplane and
striking the tail, and consequently
reducing the controllability of the
airplane.
emcdonald on DSK67QTVN1PROD with PROPOSALS
SUMMARY:
We must receive comments on
this proposed AD by September 19,
2013.
DATES:
You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
ADDRESSES:
VerDate Mar<15>2010
16:53 Aug 02, 2013
Jkt 229001
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Live TV, 8900
Hangar Boulevard, Orlando, FL 32827;
telephone 407–812–2600; fax 407–812–
2526; Internet https://www.livetv.net.
You may review copies of the
referenced service information at the
FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton,
Washington. For information on the
availability of this material at the FAA,
call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; 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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Barry Culler, Aerospace Engineer,
Airframe Branch, ACE–117A, FAA,
Atlanta Aircraft Certification Office
(ACO), 1701 Columbia Avenue, College
Park, GA 30337; phone: 404–474–5546;
fax: 404–474–5605; email:
william.culler@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2013–0670; Directorate Identifier 2013–
NM–081–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
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Sfmt 4702
47233
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We received reports of cracks in 26
radomes. The cracks were found during
inspections of the radome assembly of
various Model 737 series airplanes that
had in-flight entertainment systems
installed using certain STC issued to
Live TV. The STC numbers are STC
ST00284BO, https://rgl.faa.gov/
Regulatory_and_Guidance_Library/
rgstc.nsf/0/
3ecc2e5e5f408bc1862579b30048ed60/
$FILE/ST00284BO.pdf; and STC
ST02887AT, https://rgl.faa.gov/
Regulatory_and_Guidance_Library/
rgstc.nsf/0/
9bf85b85ea3e295d8625735600721055/
$FILE/ST02887AT.pdf. Investigation of
the cause of the cracks revealed that
lack of dimensional controls on the
radome manufacturing drawings can
result in the introduction of preload
stress on the radome during its assembly
with the skirt fairing. Preload stress
combined with flight or handling stress,
such as maintenance personnel stepping
on the radome fairing assembly, might
initiate a crack. The radome
manufacturing drawings were revised
on September 13, 2010, to add a control
dimension, which was incorporated into
production at radome serial number
498. Cracks in the radome, if not
corrected, could result in the radome (or
pieces) separating from the airplane and
striking the tail, and consequently
reducing the controllability of the
airplane.
Relevant Service Information
We reviewed Live TV Service Bulletin
B737–53–0011, dated March 29, 2013.
The service information describes
procedures for repetitive inspections for
cracks in the outer ply of the radome
and replacing the radome if any crack is
found.
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
Proposed AD Requirements
This proposed AD would require
accomplishing the actions specified in
the service information described
previously, except as discussed under
‘‘Differences Between the Proposed AD
and the Service Information.’’ In
E:\FR\FM\05AUP1.SGM
05AUP1
]]>Agencies
[Federal Register Volume 78, Number 150 (Monday, August 5, 2013)]
[Proposed Rules]
[Pages 47230-47233]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-18854]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0679; Directorate Identifier 2009-SW-015-AD]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France (Eurocopter) Model
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
Eurocopter Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C,
AS350D, and AS350D1 helicopters. This proposed AD would require
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 proposed AD is 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
proposed actions are intended to prevent the collective from becoming
inadvertently locked in the low position and subsequent loss of control
of the helicopter.
DATES: We must receive comments on this proposed AD by October 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, 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.
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:
Comments Invited
We invite you to participate in this rulemaking by submitting
written comments, data, or views. We also
[[Page 47231]]
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
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
No. 2009-0019, dated February 3, 2009, 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.
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
its AD. 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 products of the same type design.
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.
Proposed AD Requirements
The proposed AD would require measuring the clearance between the
collective locking stud and the locking strip. If insufficient
clearance exists, corrective actions are defined based on the installed
locking strip and locking stud designs. Corrective actions include
restoring the original profile of certain locking strips and adjusting
the length of certain collective locking studs.
Differences Between This Proposed AD and the EASA AD
The EASA AD does not apply to Model AS350C or AS350D1 helicopters,
and the proposed AD would apply to these models because they have a
similarly-designed collective pitch lock. The EASA AD applies to the
Model AS350BB, and the proposed AD does not because that model does not
have a U.S. type certificate. The proposed AD would require an initial
inspection within 100 hours time-in-service, while the EASA AD requires
this inspection ``after the last flight of the day.''
Costs of Compliance
We estimate that this proposed AD would affect 651 helicopters of
U.S. Registry.
We estimate that operators may incur the following costs in order
to comply with this AD. It would take 1 work hour to measure the
clearance and repair the locking stud and locking strip at $85 per work
hour. Required parts would cost $95 per helicopter. Based on these
estimates, the total cost per helicopter would be $180, and the total
cost for the fleet would 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 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,
[[Page 47232]]
the FAA proposes to amend 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):
Eurocopter France: 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, 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) Comments Due Date
We must receive comments by October 4, 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
(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 the EASB.
(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 the EASB.
(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 the EASB, except
you are not required to comply with paragraph 2.B.4 of the EASB.
(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 the
EASB, except you are not required to comply with paragraph 2.B.4 of
the EASB.
(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
the EASB, except you are not required to comply with paragraph 2.B.4
of the EASB.
(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 the EASB.
(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 the EASB.
(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
applying 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.
(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.
(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 time-in-service 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 Emergency Alert Service Bulletin (EASB) No.
05.00.58, Revision 0, dated January 12, 2008, is co-published in one
document with EASB No. 05.00.35, which is not incorporated by
reference in this AD. 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.
(2) 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
[[Page 47233]]
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.
(3) 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 at https://www.regulations.gov by searching for
and locating it in Docket No. FAA-2013-0679.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6710 Main Rotor
Control.
Issued in Fort Worth, Texas, on July 26, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2013-18854 Filed 8-2-13; 8:45 am]
BILLING CODE 4910-13-P
