[Federal Register Volume 79, Number 110 (Monday, June 9, 2014)]
[Proposed Rules]
[Pages 32881-32883]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-13261]


 ========================================================================
 Proposed Rules
                                                 Federal Register
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
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  Federal Register / Vol. 79, No. 110 / Monday, June 9, 2014 / Proposed 
Rules  

[[Page 32881]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0364; Directorate Identifier 2013-SW-041-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters (Previously 
Eurocopter France) (Airbus Helicopters) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede airworthiness directive (AD) 2013-21-
01 that currently applies to Eurocopter France Model AS350B, AS350BA, 
AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, 
AS355F1, AS355F2, AS355N, and AS355NP helicopters. AD 2013-21-01 
currently requires certain inspections of each tail rotor pitch horn 
assembly (pitch horn) for a crack and, if there is a crack, before 
further flight, replacing the pitch horn with an airworthy pitch horn. 
AD 2013-21-01 also requires a one-time visual inspection for pitch 
horns above certain hours time-in-service (TIS). This NPRM would retain 
the requirements of AD 2013-21-01 but would require a repetitive visual 
inspection for all pitch horns regardless of hours TIS, which requires 
allowing the public an opportunity to comment. These proposed actions 
are intended to detect a crack in the pitch horn to prevent failure of 
the pitch horn, loss of the anti-torque function, and subsequent loss 
of control of the helicopter.

DATES: We must receive comments on this proposed AD by August 8, 2014.

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 foreign 
authority's 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 
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.

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 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

    On October 7, 2013, we issued AD 2013-21-01, Amendment 39-17625 (78 
FR 63853, October 25, 2013) for Eurocopter France (now Airbus 
Helicopters) Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, 
AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP 
helicopters. AD 2013-21-01 requires a one-time visual inspection of 
each pitch horn with 135 or more hours TIS for a crack and, if there is 
a crack, before further flight, replacing the pitch horn with an 
airworthy pitch horn. It also requires a dye-penetrant inspection of 
any pitch horn before it is installed. AD 2013-21-01 was prompted by a 
report of a crack in the yoke of a pitch horn and is intended to detect 
a crack in the pitch horn to prevent failure of the pitch horn, loss of 
the anti-torque function, and subsequent loss of control of the 
helicopter.
    AD 2013-21-01 was prompted by AD No. 2013-0133, dated June 28, 
2013, issued by the European Aviation Safety Agency (EASA), which is 
the Technical Agent for the Member States of the European Union. EASA 
issued AD No. 2013-0133 to correct an unsafe condition for Model 
AS350B, AS350BA, AS350BB, AS350B1, AS350B2, AS350B3, AS350D, AS355E, 
AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. EASA advises 
of an ongoing investigation of a crack in the yoke of a pitch horn for 
which a cause has not been determined. The EASA AD requires repetitive 
visual inspections of each pitch horn for a crack and replacing the 
pitch horn with a serviceable assembly if a crack is found. EASA states 
that its AD is an

[[Page 32882]]

interim action and further action may follow.
    This NPRM would retain the actions in AD 2013-12-01 but would 
require the visual inspection for all pitch horns regardless of hours 
TIS. This NPRM would also require repeating the visual inspection every 
165 hours TIS. This NPRM would also change the requirement for the dye 
penetration inspection so that it only applies to pitch horns that are 
not new. Also, since we issued AD 2013-12-01, Eurocopter France has 
changed its name to Airbus Helicopters. This NPRM reflects that change.

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 proposing this AD because we evaluated all known 
relevant information and determined that an unsafe condition is likely 
to exist or develop on other helicopters of the same type design.

Related Service Information

    We reviewed a Eurocopter (now Airbus Helicopters) Emergency Alert 
Service Bulletin, Revision 1, dated June 25, 2013 (EASB), with four 
different numbers. EASB No.05.00.74 is for Model AS350B, B1, B2, B3, 
BA, and D; the non-FAA type certificated Model AS350BB; and the non-FAA 
type certificated military Model AS350L1 helicopters. EASB No. 05.00.49 
is for non-FAA type certificated military Model AS550A2, C2, C3, and U2 
helicopters. EASB No. 05.00.65 is for Model AS355E, F, F1, F2, N, and 
NP helicopters. EASB No. 05.00.44 is for non-FAA type certificated 
military Model AS555AF, AN, SN, UF, and UN helicopters. Airbus 
Helicopters has been informed of a case of a crack on the yoke of a 
pitch horn, which may lead to failure of the pitch horn, resulting in 
loss of the anti-torque function. The EASB specifies a check for cracks 
on the yokes of the two pitch horns and specifies replacing any cracked 
pitch horn. The EASB states that it may be necessary to modify the log 
card of the tail rotor blade assembly due to some of the pitch horn 
part numbers being recorded incorrectly.
    EASA classified this EASB as mandatory and issued EASA AD No. 2013-
0133, dated June 28, 2013, to ensure the continued airworthiness of 
these helicopters.

Proposed AD Requirements

    This proposed AD would require:
     For parts with 155 or less hours TIS, before exceeding 165 
hours TIS, or for parts with more than 155 hours TIS, within 10 hours 
TIS, visually inspecting each pitch horn for a crack.
     Thereafter, at intervals not to exceed 165 hours TIS, 
visually inspecting each pitch horn for a crack.
     After each inspection, if there is a crack, before further 
flight, replacing the pitch horn with an airworthy pitch horn.
     Before installing any pitch horn, P/N 350A121368, with 
more than 0 hours TIS, dye penetrant inspecting it for a crack.

Differences Between the Proposed AD and the EASA AD

    The EASA AD applies to Eurocopter Model AS350BB that does not have 
an FAA type certificate and therefore is not a part of this proposed 
AD. The EASA AD does not apply to Eurocopter Model AS350C or AS350D1, 
but this proposed AD would because those models have an FAA type 
certificate and may have the applicable pitch horn installed. The 
proposed AD would require a dye-penetrant inspection before installing 
a pitch horn; the EASA AD does not.

Interim Action

    We consider this AD to be an interim action. If final action is 
later identified, we might consider further rulemaking then.

Costs of Compliance

    We estimate that this proposed AD would affect 938 helicopters of 
U.S. Registry. We estimate that operators may incur the following costs 
in order to comply with this proposed AD. Labor costs are estimated at 
$85 per work hour. We estimate .1 work hour to visually inspect a pitch 
horn for a total cost of $8.50 per helicopter or $7,973 for the fleet, 
per inspection cycle. We estimate 1 work hour to do a dye-penetrant 
inspection, for a total cost of $85 per helicopter. We estimate 1 work 
hour to replace a part, if necessary, and a cost for required parts of 
$1,946, for a total cost of $2,031 per helicopter.

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, 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 removing airworthiness directive (AD) 
2013-21-01, Amendment 39-17625 (78 FR 63853, October 25, 2013), Docket 
No. FAA-2013-0878, Directorate Identifier

[[Page 32883]]

2013-SW-033-AD, and adding the following new AD:

Airbus Helicopters (Previously Eurocopter France Helicopters) 
(Airbus Helicopters): Docket No. FAA-2014-0364; Directorate 
Identifier 2013-SW-041-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model AS350B, AS350BA, 
AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, 
AS355F1, AS355F2, AS355N, and AS355NP helicopters with tail rotor 
hub pitch horn (pitch horn) assembly, part number (P/N) 
350A121368.01, 350A121368.02, 350A121368.03, or 350A121368.04, with 
a pitch horn, P/N 350A121368.XX, where XX stands for a two-digit 
dash number, installed, certificated in any category. The pitch horn 
may be marked with either the pitch horn assembly P/N or pitch horn 
P/N.

(b) Unsafe Condition

    This AD defines the unsafe condition a crack in the yoke of a 
pitch horn. This condition could result in failure of a pitch horn, 
loss of the anti-torque function, and subsequent loss of control of 
the helicopter.

(c) Affected ADs

    This AD supersedes AD 2013-21-01, Amendment 39-17625 (78 FR 
63853, October 25, 2013).

(d) Comments Due Date

    We must receive comments by August 8, 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 parts with 155 or less hours time-in-service (TIS), 
before exceeding 165 hours TIS, or for parts with more than 155 
hours TIS, within 10 hours TIS, and thereafter at intervals not to 
exceed 165 hours TIS, visually inspect each pitch horn for a crack 
in the areas shown in Figure 1 of Eurocopter Emergency Alert Service 
Bulletin (EASB) No. 05.00.74 or No. 05.00.65, both Revision 1 and 
both dated June 25, 2013, as appropriate for your model helicopter.
    (2) If there is a crack, before further flight, replace the 
pitch horn with an airworthy pitch horn.
    (3) Do not install a pitch horn, P/N 350A121368 (any dash 
number), with more than 0 hours TIS on any helicopter unless it has 
passed a dye penetrant inspection for a crack in the areas shown in 
Figure 1 of Eurocopter EASB No. 05.00.74 or No. 05.00.65, both 
Revision 1 and both dated June 25, 2013, as appropriate for your 
model helicopter.

(g) Special Flight Permits

    Special flight permits are prohibited.

(h) 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 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.

(i) Additional Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) AD No. 2013-0133, dated June 28, 2013. You may view 
the EASA AD on the Internet at http://www.regulations.gov in Docket 
No. FAA-2014-0364.

(j) Subject

    Joint Aircraft Service Component (JASC) Code: 6400 Tail Rotor.

    Issued in Fort Worth, Texas, on May 30, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-13261 Filed 6-6-14; 8:45 am]
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