[Federal Register Volume 78, Number 150 (Monday, August 5, 2013)]
[Proposed Rules]
[Pages 47230-47233]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-18854]
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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).
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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 http://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 http://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 http://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 [email protected].
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
[email protected].
(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 http://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 http://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