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[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]

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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; 
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.

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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 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.

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 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 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.
    (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 http://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: http://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
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