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[Federal Register Volume 79, Number 21 (Friday, January 31, 2014)]
[Proposed Rules]
[Pages 5321-5323]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-01951]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0038; Directorate Identifier 2013-SW-023-AD]
RIN 2120-AA64

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

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 
Airbus Model EC225LP helicopters. This proposed AD would require 
repetitive visual and tap test inspections of each main rotor blade 
(blade) leading edge stainless steel protective strip (strip) for a 
crack, cut, or blind or open debonding (debonding), and taking approved 
corrective measures. If there is a crack or if there is debonding that 
exceeds acceptable limits, this AD would require, before further 
flight, repairing or replacing the blade with an airworthy part. This 
proposed AD is prompted by suspected water seepage through a crack in 
the blade strip resulting in significant debonding. The proposed 
actions are intended to prevent loss of the blade strip, excessive 
vibrations induced by blade weight imbalance, and subsequent loss of 
control of the helicopter.

DATES: We must receive comments on this proposed AD by April 1, 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: Gary Roach, Aviation Safety Engineer, 
Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham 
Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email 
gary.b.roach@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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, issued EASA AD No. 
2013-0103, dated May 2, 2013, which supersedes EASA AD No. 2007-0180-E, 
dated June 29, 2007, to correct an unsafe condition for the Eurocopter 
Model EC225LP helicopters with certain blades installed. EASA advises 
that an investigation of significant debonding of a blade strip 
revealed rapidly progressing debonding caused by water seepage through 
a crack in the blade strip. EASA AD No. 2007-0180-E required repetitive 
inspections of the blade strip and accomplishing any corrective 
actions. After issuance of EASA AD No. 2007-0180-E, Eurocopter 
developed a modified strip and re-identified blade part numbers with 
the modified strip. Because these other blades with the modified strip 
are still susceptible to debonding, EASA issued superseding AD 2013-
0103 to extend the applicability to the new part-numbered blades.

FAA's Determination

    This helicopter has been approved by the aviation authority of 
France and is 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

    Eurocopter issued an Emergency Alert Service Bulletin (EASB) No. 
05A010, Revision 2, dated April 22, 2013, for the Model EC225LP 
helicopter and for the non-FAA typed certificated Model EC725AP 
military helicopter. The EASB specifies a visual check and tapping test 
of the bonding of the strip on the leading edge of the blades for 
cracks, cuts, and debonding and taking corrective actions as 
applicable. Revision 1 to the EASB changed the visual check and the 
tapping test so that they can be performed without removing the blades. 
Revision 2 extended the applicability to additional part-numbered 
blades with a modified strip installed.

Proposed AD Requirements

    This proposed AD would require:
     Within 15 hours time-in-service (TIS) and thereafter at 
intervals not to exceed 85 hours TIS, visually and tap

[[Page 5322]]

test inspecting each blade strip for a crack, a cut, or open or blind 
debonding. For purposes of this proposed AD, open debonding, also known 
as edge bond separation, occurs when a bonded part becomes unattached 
(debonded) leaving the surface under it exposed to open air around the 
periphery of the part. Blind debonding occurs when a bonded part 
becomes unattached internally yet remains bonded around its entire 
periphery.
     If there is debonding beyond acceptable limits or located 
outside a specific area, or if there is a crack, before further flight, 
repairing or replacing the blade.
     If there is a cut in the blade root polyurethane 
protective strip, tap test inspecting the area. If there is no 
debonding, tap test inspecting the blade strip every 15 hours TIS. If 
there is debonding beyond acceptable limits or located outside a 
specific area, before further flight, repairing or replacing the blade.

Differences Between This Proposed AD and the EASA AD

    If there is a crack in the blade leading edge, this proposed AD 
would require repairing or replacing the blade before further flight, 
while the EASA AD permits a re-inspection within 15 hours TIS.

Costs of Compliance

    We estimate that this proposed AD would affect 4 helicopters of 
U.S. Registry. We estimate that operators may incur the following costs 
in order to comply with this AD. Labor costs are estimated at $85 per 
work hour. We estimate 4 work hours to inspect the helicopter for a 
total of $340 per helicopter and $1,360 for the U.S. operator fleet per 
inspection cycle. If necessary, it would take 4 work hours to repair 
the blade and $600 for required parts for a total of $940 per 
helicopter. It would take about 5 work hours to replace a blade at a 
cost of $425 for labor. Parts would cost $315,495 to replace P/N 
332A11-0050-01 and $403,650 to replace P/N 332A11-0055-00, for a total 
cost of $315,920 and $404,075, respectively.

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 adding the following new airworthiness 
directive (AD):

Airbus Helicopters (Type Certificate previously held by Eurocopter 
France): Docket No. FAA-2014-0038; Directorate Identifier 2013-SW-
023-AD.

(a) Applicability

    This AD applies to Model EC225LP helicopters with a main rotor 
blade (blade), part number (P/N) 332A11.0050.00, 332A11.0055.00, 
332A11.0050.02, or 332A11.0055.02, installed, certificated in any 
category.

(b) Unsafe Condition

    This AD defines the unsafe condition as loss of a blade 
stainless steel protective strip (strip), which could result in 
excessive vibrations induced by blade weight imbalance and 
subsequent loss of control of the helicopter.

(c) Comments Due Date

    We must receive comments by April 1, 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

    Within 15 hours time-in-service (TIS) and thereafter at 
intervals not to exceed 85 hours TIS, visually and tap test inspect 
each blade strip for a crack, a cut, or open and blind debonding. 
For purposes of this AD, open debonding, also known as edge bond 
separation, occurs when a bonded part becomes unattached (debonded) 
leaving the surface under it exposed to open air around the 
periphery of the part. Blind debonding occurs when a bonded part 
becomes unattached internally yet remains bonded around its entire 
periphery.
    (1) If there is open or blind debonding within acceptable limits 
and the debonded area is located inside Area D of Figure 1 of 
Eurocopter Emergency Alert Service Bulletin No. 05A010, Revision 2, 
dated April 22, 2013 (EASB), no further action is required until the 
next inspection.
    (2) If there is open or blind debonding and the debonded area is 
located outside Area D of Figure 1 of the EASB, before further 
flight, repair or replace the blade.
    (3) If there is open or blind debonding beyond acceptable 
limits, before further flight, repair or replace the blade.
    (4) If there is a cut in the blade root polyurethane protective 
strip as depicted in Area A of Figure 2 of the EASB, tap test 
inspect the area.
    (i) If there is no open and blind debonding, at intervals not to 
exceed 15 hours TIS, tap test inspect the blade strip in the blade 
root area, in the stainless steel leading edge/neoprene junction 
area for open or blind debonding.
    (ii) If there is open or blind debonding within acceptable 
limits and the debonded area is located inside Area D of Figure 1 of 
the EASB, no further action is required until the next inspection.
    (iii) If there is open or blind and the debonded area is located 
outside Area D of Figure 1 of the EASB, before further flight, 
repair or replace the blade.

[[Page 5323]]

    (iv) If there is open or blind debonding beyond acceptable 
limits, before further flight, repair or replace the blade.
    (5) If there is a crack, before further flight, repair or 
replace the blade.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Gary Roach, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-
5110; email gary.b.roach@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.

(g) Additional Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) AD No. 2013-0103, dated May 2, 2013. You may view the 
EASA AD on the Internet in the AD Docket at www.regulations.gov.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6210 Main Rotor 
Blades.

    Issued in Fort Worth, Texas, on January 16, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-01951 Filed 1-30-14; 8:45 am]
BILLING CODE 4910-13-P
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