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[Federal Register Volume 79, Number 146 (Wednesday, July 30, 2014)]
[Proposed Rules]
[Pages 44142-44144]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-17928]

========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

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.

========================================================================


Federal Register / Vol. 79, No. 146 / Wednesday, July 30, 2014 / 
Proposed Rules

[[Page 44142]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0498; Directorate Identifier 2013-SW-052-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters (Previously 
Eurocopter France) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to supersede airworthiness directive (AD) 2010-21-
07 for Eurocopter France (now Airbus Helicopters) Model AS350B3 and 
EC130B4 helicopters. AD 2010-21-07 currently requires inspecting the 
pilot's and co-pilot's throttle twist for proper operation of the 
contactors. This proposed AD would retain the requirements of AD 2010-
21-07, include additional inspection procedures, and revise the 
inspection interval. These proposed actions are intended to prevent 
unintended touchdown during a practice autorotation at a flight-idle 
power setting, damage to the helicopter, and injury to occupants.

DATES: We must receive comments on this proposed AD by September 29, 
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 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: George Schwab, Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 
Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email 
george.schwab@faa.gov.

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 September 29, 2010, we issued AD 2010-21-07, Amendment 39-16467 
(75 FR 63052, October 14, 2010), for Eurocopter France (now Airbus 
Helicopters) Model AS350B3 and EC130B4 helicopters with certain 
equipment installed. AD 2010-21-07 requires repetitively inspecting the 
pilot's and co-pilot's throttle twist for proper operation of the 
contactors, which provide for changes between the ``IDLE'' and 
``FLIGHT' positions of the throttle twist grip control, by complying 
with Eurocopter's service information. AD 2010-21-07 was prompted by a 
dormant failure of one of the two contactors 53Ka or 53Kb following the 
installation of modification (MOD) 073254 on Model AS350B3 helicopters 
and the installation of MOD 073773 on Model EC130B4 helicopters. Those 
actions were intended to prevent an unintended touchdown to the ground 
during a practice autorotation at a flight-idle power setting, damage 
to the helicopter, and injury to the occupants.

Actions Since AD 2010-21-07 Was Issued

    Since we issued AD 2010-21-07, Amendment 39-16467 (75 FR 63052, 
October 14, 2010), Eurocopter designed MOD 074263 to address the unsafe 
condition, and we issued two letters approving MOD 074263 as an 
Alternate Method of Compliance for AD 2010-21-07. A subsequent accident 
occurred involving power loss in flight of a Model AS350B3 helicopter 
with MOD 074263 installed. As a result, Eurocopter revised its service 
information and the European Aviation Safety Agency (EASA), which is 
the Technical Agent for the Member States of the European Union, issued 
EASA Emergency AD No. 2013-0191-E, dated August 22, 2013. EASA advises 
the switches in the engine ``IDLE'' or ``FLIGHT'' control system could 
be affected by the corrosive effects of a salt-laden atmosphere, which 
could lead to engine

[[Page 44143]]

power loss. EASA states that because these corrosive effects are not 
prevented by MOD 074263, it no longer considers MOD 074263 terminating 
action for the required repetitive maintenance actions.
    This NPRM would retain the repetitive inspections in AD 2010-21-07 
but would also include the additional inspection requirements in the 
Eurocopter service information. Also, since we issued AD 2010-21-07, 
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 
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

    We reviewed one co-published Eurocopter Emergency Alert Service 
Bulletin (EASB) containing 3 numbers: No. 05.00.61, Revision 2, dated 
August 13, 2013, for Model AS350B3 helicopters; No. 05.00.41, Revision 
1, dated August 13, 2013, for the non-FAA type-certificated Model 
AS550C3 helicopter; and No. 05A009, Revision 2, dated August 13, 2013, 
for Model EC130B4 helicopters. The EASB describes procedures for a 
functional check and installation of a protection for micro-contacts 
53Ka, 53Kb, and 65K (IDLE/FLIGHT mode). EASA classified this EASB as 
mandatory and issued EASA Emergency AD No. 2013-0191-E, dated August 
22, 2013, to ensure the continued airworthiness of these helicopters.

Proposed AD Requirements

    This proposed AD would retain the inspection requirements of AD 
2010-21-07 (78 FR 63052, October 14, 2010) but would also include 
additional requirements to inspect for proper operation of contactors 
53Ka and 53Kb and the pilot and copilot throttle twist grip controls 
for proper functioning. This proposed AD would require the inspections 
to be done at intervals not to exceed 300 hours time-in-service (TIS), 
compared to the 600-hour TIS intervals required by AD 2010-21-07. 
Issuing this proposed AD would also invalidate the two letters dated 
December 19, 2012, and July 18, 2013, approving AMOCs for AD 2010-21-
07.

Differences Between the Proposed AD and the EASA AD

    This AD requires the inspections to be done at intervals not to 
exceed 300 hours TIS, and the EASA AD applies different intervals based 
on certain conditions.

Interim Action

    We consider this AD interim action. The design approval holder is 
currently developing a modification that will address the unsafe 
condition identified in this proposed AD. Once this modification is 
developed, approved, and available, we might consider additional 
rulemaking.

Costs of Compliance

    We estimate that this proposed AD would affect 517 helicopters of 
U.S. Registry.
    We estimate that operators may incur the following costs in order 
to comply with this AD. The average labor rate is $85 per work hour. It 
would take about 4 work hours for the inspections and any necessary 
maintenance, for a total cost of $340 per helicopter and $175,780 for 
the U.S. fleet per inspection cycle.

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. Amend Sec.  39.13 by removing Airworthiness Directive (AD) 2010-21-
07, Amendment 39-16467 (75 FR 63052, October 14, 2010), and adding the 
following new AD:

Airbus Helicopters (Previously Eurocopter France) Helicopters: 
Docket No. FAA-2014-0498; Directorate Identifier 2013-SW-052-AD.

(a) Applicability

    This AD applies to Model AS350B3 and EC130B4 helicopters, 
certificated in any category, with the ARRIEL 2B1 engine with the 
two-channel Full Authority Digital Engine Control (FADEC) and with 
new twist grip modification (MOD) 073254 for the Model AS350B3 
helicopter or MOD 073773 for the Model EC130B4 helicopter, 
installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as failure of one of the 
two contactors, 53Ka or 53Kb, which can prevent switching from 
``IDLE'' mode to ``FLIGHT'' mode during autorotation training making 
it impossible to recover from the practice autorotation and 
compelling the pilot to continue the autorotation to the ground. 
This condition could result in unintended touchdown to the

[[Page 44144]]

ground at a flight-idle power setting during a practice 
autorotation, damage to the helicopter, and injury to occupants.

(c) Affected ADs

    This AD supersedes AD 2010-21-07, Amendment 39-16467 (75 FR 
63052, October 14, 2010).

(d) Comments Due Date

    We must receive comments by September 29, 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

    Before the next practice autorotation or on or before 100 hours 
time-in-service (TIS), whichever occurs first, and thereafter at 
intervals not to exceed 300 hours TIS, inspect the wiring, perform 
an insulation test, inspect the pilot and copilot throttle twist 
grip controls, and test the pilot and copilot throttle twist grip 
controls for proper functioning by following the Accomplishment 
Instructions, paragraphs 3.B.1 through 3.B.6, of Eurocopter 
Emergency Alert Service Bulletin (EASB) No. 05.00.61, Revision 2, 
dated August 13, 2013, for Model AS350B3 helicopters or EASB No. 
05A009, Revision 2, dated August 13, 2013, for Model EC130B4 
helicopters, as appropriate for your model helicopter.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: George Schwab, Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 
Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; 
email george.schwab@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) Additional Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) Emergency AD No. 2013-0191-E, dated August 22, 2013. 
You may view the EASA AD at http://www.regulations.gov in Docket No. 
FAA-2014-0498.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 76 Engine 
Controls.

    Issued in Fort Worth, Texas, on July 18, 2014.
S. Frances Cox,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-17928 Filed 7-29-14; 8:45 am]
BILLING CODE 4910-13-P
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