
[Federal Register Volume 79, Number 47 (Tuesday, March 11, 2014)]
[Rules and Regulations]
[Pages 13526-13528]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-04729]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0477; Directorate Identifier 2011-SW-015-AD; 
Amendment 39-17780; AD 2014-05-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters (Type Certificate 
Previously Held by Eurocopter France) (Airbus Helicopters)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding airworthiness directive (AD) 2010-11-51 for 
Eurocopter France (Eurocopter) Model AS350B, BA, B1, B2, C, D, and D1 
helicopters and Model AS355E, F, F1, F2, and N helicopters with certain 
part-numbered tail gearbox (TGB) control levers installed. AD 2010-11-
51 required repetitive visual inspections of the TGB control lever for 
a crack and replacing a cracked TGB control lever with an airworthy TGB 
control lever. This new AD retains the requirements of AD 2010-11-51 
and also requires inspecting other areas of the TGB control lever not 
previously inspected and at additional inspection intervals. This AD 
was prompted by several reports of cracking in a TGB control lever. The 
actions of this AD are intended to prevent failure of the TGB control 
lever, loss of tail rotor control, and subsequent loss of control of 
the helicopter.

DATES: This AD is effective April 15, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of April 15, 
2014.

ADDRESSES: For service information identified in this AD, contact 
Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; 
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at 
http://www.airbushelicopters.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 European Aviation Safety 
Agency (EASA) 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, Rotorcraft Directorate, Safety Management Group, 2601 Meacham 
Blvd., Fort Worth, TX 76137, telephone 817-222-5110, email 
robert.grant@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2010-11-51, Amendment 39-16396 (75 FR 50874, 
August 18, 2010). AD 2010-11-51 applied to Eurocopter Model AS350B, BA, 
B1, B2, C, D, and D1 helicopters and Model AS355E, F, F1, F2, and N 
helicopters with certain part-numbered tail gearbox (TGB) control 
levers installed. The NPRM published in the Federal Register on June 
17, 2013 (78 FR 36129). The NPRM proposed to retain the requirements in 
AD 2010-11-51 to perform repetitive visual inspections in a certain 
area on each TGB control lever not marked with an ``X'' and to replace 
a cracked part. Also, the NPRM proposed to require inspecting another 
area of each TGB control lever at additional intervals. The NPRM also 
proposed replacing each TGB control lever with a reworked TGB control 
lever marked with an ``X'' near the P/N or with a TGB control lever 
with a P/N not listed in the applicability of the AD. The proposed 
requirements were intended to prevent failure of the

[[Page 13527]]

TGB control lever, loss of tail rotor control, and subsequent loss of 
control of the helicopter.
    The NPRM was prompted by Emergency AD No. 2011-0038-E, dated March 
4, 2011 (AD No. 2011-0038-E), issued by EASA, which is the Technical 
Agent for the Member States of the European Union, to correct an unsafe 
condition for the Eurocopter Model AS350B, BA, BB, B1, B2, and D, and 
AS355E, F, F1, F2, and N helicopters. Emergency AD No. 2011-0038-E 
superseded EASA Emergency AD No. 2010-0082-E, dated April 27, 2010 (AD 
No. 2010-0082-E). EASA advises that since issuing its Emergency AD No. 
2010-0082-E, Eurocopter found additional cracks opposite the required 
inspection area on the affected control levers. EASA Emergency AD No. 
2011-0038-E retains the requirements of EASA Emergency AD No. 2010-082-
E and adds repetitive inspections for the area opposite the control 
levers.
    Since we issued the NPRM, Eurocopter France changed its name to 
Airbus Helicopters. This AD reflects that change and updates the 
contact information to obtain service documentation.

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 36129, 
June 17, 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 except for the name change 
previously described and correcting the date referenced for Revision 2 
of the Eurocopter Emergency Alert Service Bulletin (EASB). These 
changes are consistent with the intent of the proposals in the NPRM (78 
FR 36129, June 17, 2013) and will not increase the economic burden on 
any operator nor increase the scope of the AD.

Differences Between This AD and the EASA AD

    This AD differs from EASA Emergency AD No. 2011-0038-E as follows:
     We include the Model AS350C and AS350D1 helicopters that 
may contain the affected TGB control lever. We do not include the Model 
AS350BB helicopter because it is not type-certificated in the United 
States.
     We do not require an ``after last flight''of the day 
inspection.
     We do not allow a pilot to inspect for a crack.
     We do not require reworking noninstalled control levers.
     We do not include a calendar compliance time for reworking 
the TGB control lever if there is not a crack.
     We do not require you to contact Eurocopter (now Airbus 
Helicopters) if a crack is found during any inspection.

Related Service Information

    Eurocopter issued one EASB, Revision 2, dated March 1, 2011, with 
four different numbers. EASB No. 05.00.62 is for Model AS350 
helicopters; EASB No. 05.00.57 is for Model AS355 helicopters; EASB No. 
05.00.38 is for military Model AS550 helicopters; and EASB No. 05.00.35 
is for military Model AS555 helicopters. The military models are not 
type-certificated in the United States. The EASB specifies visually 
inspecting the TGB control lever for a crack at the last flight of each 
day, without exceeding 10 flying hours between inspections. The EASB 
also specifies a rework procedure for affected TGB control levers, to 
be done within 660 flying hours and no later than June 30, 2011, 
indicated by marking the control lever with a letter ``X.'' EASA 
classified this EASB as mandatory and issued AD No. 2011-0038-E to 
ensure the continued airworthiness of these helicopters.

Costs of Compliance

    We estimate that this AD will affect 791 helicopters of U.S. 
registry. We estimate that operators may incur the following costs in 
order to comply with this AD. The inspections for a crack in the TGB 
control lever will take a minimal amount of time. Replacing a control 
lever will take about 3 work hours at an average labor rate of $85 per 
work hour. Required parts will cost about $2,103 per helicopter. Based 
on these figures, we estimate the total cost of the AD on U.S. 
operators to be $2,358 per helicopter to replace the control lever.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on helicopters identified in this 
rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979);
    (3) Will not affect intrastate aviation in Alaska to the extent 
that it justifies making a regulatory distinction; and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared an economic evaluation of the estimated costs to comply 
with this AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:


[[Page 13528]]


    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2010-11-51, Amendment 39-16396 (75 FR 50874, August 18, 2010), and 
adding the following new AD:

2014-05-07 Airbus Helicopters (Type Certificate Previously Held by 
Eurocopter France): Amendment 39-17780; FAA-2013-0477; Directorate 
Identifier 2011-SW-015-AD.

(a) Applicability

    This AD applies to Model AS350B, BA, B1, B2, C, D, and D1 
helicopters and Model AS355E, F, F1, F2, and N helicopters, with a 
tail gearbox (TGB) control lever, part number (P/N) 350A33-1058-00, 
P/N 350A33-1058-01, P/N 350A33-1058-02, or P/N 350A33-1058-03, both 
with and without an ``X'' marked near the P/N, installed, 
certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in the TGB 
control lever. This condition could result in failure of the TGB 
control lever, loss of tail rotor control, and subsequent loss of 
control of the helicopter.

(c) Affected ADs

    This AD supersedes AD 2010-11-51, Amendment 39-16396 (75 FR 
50874, August 18, 2010).

(d) Effective Date

    This AD becomes effective April 15, 2014.

(e) 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.

(f) Required Actions

    (1) For helicopters with a lever not marked with an ``X'' near 
the P/N, within 10 hours time-in-service (TIS), and thereafter at 
intervals not to exceed 10 hours TIS, using a mirror and appropriate 
light source, visually inspect the TGB control lever for a crack as 
shown in area ``A'' of Figure 2 of Eurocopter Emergency Alert 
Service Bulletin No. 05.00.62, Revision 2, dated March 1, 2011 (EASB 
No. 05.00.62), for Model AS350 helicopters, and Eurocopter Emergency 
Alert Service Bulletin No. 05.00.57, Revision 2, dated March 1, 2011 
(EASB No. 05.00.57), for Model AS355 helicopters. If there is a 
crack, before further flight, replace each cracked TGB control lever 
with a TGB control lever with a P/N not listed in paragraph (a) of 
this AD.
    (2) For Model AS355N helicopters, within 110 hours TIS, or if 
the helicopter has reached 100 or more hours TIS, within the next 10 
hours TIS, and thereafter at intervals not to exceed 110 hours TIS, 
using a mirror and appropriate light source, inspect each TGB 
control lever for a crack as shown in area ``C'' of Figure 8 of EASB 
No. 05.00.62 or EASB No. 05.00.57, as applicable to your model 
helicopter.
    (3) Within 660 hours TIS, replace each TGB control lever with a 
reworked TGB control lever marked with an ``X'' near the P/N or with 
a TGB control lever with a P/N not listed in paragraph (a) of this 
AD.
    (4) For all model helicopters except Model AS355N, within 660 
hours TIS, or if the helicopter has reached 605 or more hours TIS 
within the next 55 hours TIS, and thereafter at intervals not to 
exceed 660 hours TIS, using a mirror and appropriate light source, 
inspect each TGB control lever for a crack as shown in area ``C'' of 
Figure 8 of EASB No. 05.00.62 or EASB No. 05.00.57, as applicable to 
your model helicopter.
    (5) If there is a crack, before further flight, replace each 
cracked TGB control lever with a TGB control lever with a P/N not 
listed in paragraph (a) of this AD.

(g) 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, FAA, Rotorcraft Directorate, Safety Management Group, 2601 
Meacham Blvd., Fort Worth, TX 76137, telephone (817) 222-5110, email 
robert.grant@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.

(h) Related Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) Emergency AD No. 2011-0038-E, dated March 4, 2011, and 
superseded EASA Emergency AD No. 2010-0082-E, dated April 27, 2010. 
You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA-2013-0477.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6720 Tail Rotor 
Control System.

(j) 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 (EASB), No. 
05.00.62,
    Revision 2, dated March 1, 2011.
    (ii) Eurocopter EASB No. 05.00.57, Revision 2, dated March 1, 
2011.

    Note 1 to paragraph (j)(2): Eurocopter EASB No. 05.00.62, 
Revision 2, dated March 1, 2011, and Eurocopter EASB No. 05.00.57, 
Revision 2, dated March 1, 2011, are co-published as one document 
along with Eurocopter EASB No. 05.00.38, Revision 2, dated March 1, 
2011, and Eurocopter EASB No. 05.00.35, Revision 2, dated March 1, 
2011, which are not incorporated by reference in this AD.

    (3) For Eurocopter service information identified in this AD, 
contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand 
Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax 
(972) 641-3775; or at http://www.airbushelicopters.com/techpub.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, 
Fort Worth, 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 February 26, 2014.
Bruce E. Cain,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-04729 Filed 3-10-14; 8:45 am]
BILLING CODE 4910-13-P


