
[Federal Register Volume 80, Number 86 (Tuesday, May 5, 2015)]
[Rules and Regulations]
[Pages 25589-25591]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-09548]


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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; 
Amendment 39-18146; AD 2015-09-01]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus 
Model EC225LP helicopters. This AD requires 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 requires, before further flight, repairing or replacing 
the blade with an airworthy part. This AD was prompted by suspected 
water seepage through a crack in the blade strip resulting in 
significant debonding. The actions of this AD 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: This AD is effective June 9, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of June 9, 2015.

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. It is also available on the Internet at http://www.regulations.gov in Docket No. FAA-2014-0038.

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: 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:

Discussion

    On January 31, 2014, at 79 FR 5321, 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 Airbus Helicopters. The 
NPRM proposed to require repetitive visual and tap test inspections of 
each blade strip for a crack, cut, or debonding. If there is a crack or 
if there is debonding beyond acceptable limits or located outside a 
specific area, the NPRM proposed to require, before further flight, 
repairing or replacing the blade with an airworthy part. If there is a 
cut in the blade root polyurethane protective strip, the NPRM proposed 
to require tap test inspecting the blade for debonding. The proposed 
requirements were intended to prevent loss of the blade strip, 
excessive vibrations induced by blade weight imbalance, and subsequent 
loss of control of the helicopter.
    The NPRM was prompted by AD No. 2013-0103, dated May 2, 2013, 
issued

[[Page 25590]]

by EASA, which is the Technical Agent for the Member States of the 
European Union, to correct an unsafe condition for Eurocopter (now 
Airbus Helicopters) 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 issued AD 2013-0103 
requiring repetitive inspections of the blade strip to correct this 
condition.

Comments

    After our NPRM (79 FR 5321, January 31, 2014) was published, we 
received comments from 2 commenters.

Request

    Two commenters requested that a helicopter be allowed to operate 
with a crack in the leading edge blade strip as long as the crack is 
within the limits prescribed by the manufacturer. The commenters stated 
that EASA and the manufacturer allow for a helicopter to fly if the 
blade strip has a crack that is within limits because the blade strip 
is sacrificial and nonstructural. The commenters state that requiring 
repairing or replacing the blade strip if there is a crack results in a 
higher cost and greater out-of-service time for operators without a 
justifiable or measured increase in safety.
    We agree with allowing a crack in the blade strip that is within 
limits and has been properly sealed. Therefore, we have changed 
paragraph (e)(5) of the AD to require sealing the crack instead of 
repairing or replacing the blade if there is a crack within acceptable 
limits.

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 issuing this AD because we evaluated all 
information provided by EASA, reviewed the relevant information, 
considered the comments received, and determined the unsafe condition 
exists and is likely to exist or develop on other helicopters of this 
same type design and that air safety and the public interest require 
adopting the AD requirements as proposed with the change described 
previously. This change is consistent with the intent of the proposals 
in the NPRM (79 FR 5321, January 31, 2014) and will not increase the 
economic burden on any operator nor increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Eurocopter issued Emergency Alert Service Bulletin No. 05A010, 
Revision 2, dated April 22, 2013 (EASB), 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 blade strip installed. This information is 
reasonably available at http://www.regulations.gov in Docket No. FAA-
2014-0038. Or see ADDRESSES for other ways to access this service 
information.

Costs of Compliance

    We estimate that this AD affects 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 will take 4 work hours to repair the blade and $600 
for required parts for a total of $940 per helicopter. It will take 
about 5 work hours to replace a blade at a cost of $425 for labor. 
Parts will cost $315,495 to replace part number (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.

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):

2015-09-01 Airbus Helicopters (Type Certificate previously held by 
Eurocopter France): Amendment 39-18146, 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 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) Effective Date

    This AD becomes effective June 9, 2015.

(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.

[[Page 25591]]

    (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.
    (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 within acceptable limits, before further 
flight, seal the crack. If there is a crack beyond the acceptable 
limits, 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 at www.regulations.gov in Docket No. FAA-
2014-0038.

 (h) Subject

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

(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. 05A010, 
Revision 2, dated April 22, 2013.
    (ii) Reserved.
    (3) 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.
    (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 April 16, 2015.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-09548 Filed 5-4-15; 8:45 am]
 BILLING CODE 4910-13-P


