AD 2013-23-11

[Federal Register Volume 78, Number 227 (Monday, November 25, 2013)]
[Rules and Regulations]
[Pages 70205-70207]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2013-27638]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0487; Directorate Identifier 2010-SW-056-AD; 
Amendment 39-17666; AD 2013-23-11]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for 
Eurocopter France (Eurocopter) Model AS332L2 and EC225LP helicopters. 
This AD requires inspecting the torque value of the bolts that secure 
the front and rear main gearbox (MGB) suspension bar attaching 
fittings, and re-torqueing the bolts to the proper value if the torque 
value is out of tolerance. This AD also requires, if the torque value 
is out of tolerance by more than 20 percent, inspecting the bolts, 
frames, and related equipment for a crack and repairing or replacing 
them if cracked. This AD was prompted by reports of cracks on Frame 
5295 of Model AS332L2 helicopters. The actions of this AD are intended 
to detect the torque loss of the bolts that secure the MGB bar 
attaching fittings and to prevent cracks that could lead to failure of 
the MGB supporting structure, detachment of the MGB, and loss of 
helicopter control.

DATES: This AD is effective December 30, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of December 30, 
2013.

ADDRESSES: For service information identified in this AD, contact 
American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; 
or at <a href="http://www.eurocopter.com/techpub">http://www.eurocopter.com/techpub</a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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 foreign authority's 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 
<a href="/cdn-cgi/l/email-protection#0a6d6b787324682478656b69624a6c6b6b246d657c"><span class="__cf_email__" data-cfemail="01666073782f632f736e606269416760602f666e77">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Discussion

    On June 7, 2013, at 78 FR 34288, the Federal Register published our 
notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR 
part 39 to include an AD that would apply to Eurocopter Model AS332L2 
and EC225LP helicopters. The NPRM proposed to require inspecting the 
torque value of the bolts that secure the front and rear MGB suspension 
bar attaching fittings, and re-torqueing the bolts to the proper value 
if the torque value is out of tolerance. The NPRM also proposed to 
require that if the torque value is out of tolerance by more than 20 
percent, inspecting the bolts, frames, and related equipment for a 
crack and repairing or replacing them if cracked. The proposed 
requirements were intended to detect the torque loss of the bolts that 
secure the MGB bar attaching fittings and to prevent cracks that could 
lead to failure of the MGB supporting structure, detachment of the MGB, 
and loss of helicopter control.
    The NPRM was prompted by AD No. 2006-0163 R1, dated December 13, 
2007 (AD No. 2006-0163R1), issued by the European Aviation Safety 
Agency (EASA), which is the Technical Agent for the Member States of 
the European Community, to correct an unsafe condition in Model AS 332 
L2 and Model EC 225 LP helicopters. According to EASA, analysis of 
tightening torques revealed some cases of tightening torque loss, which 
can lead to the formation of a crack at the MGB bar attaching fittings. 
As a result, EASA AD No. 2006-0163R1 requires checking the bolts 
securing the front and rear of the MGB bar attaching fittings for 
tightening torque loss and, if the loss is equal to or greater than 20 
percent, readjusting the torque and checking the four bolts securing 
the MGB bar attaching fitting mounting plate, as well as the frame 
3855, for a crack. If there is a crack in at least one of the bolts, AD 
No. 2006-0163R1 requires replacing all four bolts. If there is a crack 
in frame 3855, AD No. 2006-0163R1 requires suspending all flights and 
contacting the manufacturer for corrective action.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we received no comments on the NPRM (78 FR 34288, June 7, 
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.

Differences Between This AD and the EASA AD

    This AD differs from the EASA AD in that we use the word 
``inspect'' to describe actions required by a mechanic versus the word 
``check,'' which is how we describe actions allowed by a pilot. We also 
require that if you find a crack in a frame or fitting, you repair or 
replace the cracked part instead of contacting the manufacturer. Also, 
we have different compliance times for the initial inspection for the 
tightening

[[Page 70206]]

torque of the bolts that secure the MGB attaching fitting.

Related Service Information

    We reviewed Eurocopter Alert Service Bulletin (ASB) No. 05.00.65, 
Revision 0, dated March 28, 2006, for Model AS332L2 helicopters, and 
ASB No. 05A002, Revision 1, dated December 6, 2007, for Model EC225LP 
helicopters. The ASBs specify inspecting the tightening torque of the 
bolts that secure the front and rear of the MGB bar attaching fittings. 
If more than a 20 percent tightening torque load loss is discovered, 
the ASBs require inspecting the frames 3855 and 5295 for a crack in the 
area of the MGB bar attaching fittings. EASA classified these ASBs as 
mandatory and issued EASA AD No. 2006-0163 R1 to ensure the continued 
airworthiness of these helicopters.

Costs of Compliance

    We estimate that this AD affects 4 helicopters of U.S. Registry and 
that labor costs average $85 a work-hour. Based on these estimates, we 
expect the following costs:
    <bullet> Inspecting the torque of each bolt that secures the front 
and rear MGB attaching fitting requires 1 work-hour and no parts for a 
total cost of $85 per helicopter, and $340 for the U.S. fleet.
    <bullet> Readjusting the torque adds another 0.25 work-hour for a 
total cost of about $21 per helicopter.
    <bullet> Replacing all four nuts and bolts of an attachment fitting 
requires 4 work-hours. Parts cost $1,000 for a total cost of $1,340 per 
helicopter.
    <bullet> Replacing the attachment fitting or plate requires 16 
work-hours respectively. Parts cost $2,000 respectively for a total 
cost of $3,360 to replace each part per helicopter.
    <bullet> Replacing frames 3855 and 5295 require 40 work-hours 
respectively. Parts cost $5,000 to replace each frame for a total cost 
of $8,400 per frame 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 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:

    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):

2013-23-11 Eurocopter France: Amendment 39-17666; Docket No. FAA-
2013-0487; Directorate Identifier 2010-SW-056-AD.

(a) Applicability

    This AD applies to Eurocopter France (Eurocopter) Model AS332L2 
and EC225LP helicopters, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as loss of tightening 
torque of a bolt that secures the front and rear main gearbox (MGB) 
suspension bar attaching fittings, which can change the loads on the 
frames and cause cracking. This condition could lead to failure of 
the MGB supporting structure, detachment of the MGB, and subsequent 
loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective December 30, 2013.

(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

    (1) Within 500 hours time-in-service (TIS), and thereafter at 
intervals not to exceed 825 hours TIS, inspect the tightening torque 
of each bolt that secures the front and rear MGB attaching fitting 
by using as reference Figure 1 of Eurocopter Alert Service Bulletin 
(ASB) No. 05.00.65, Revision 0, dated March 28, 2006, for the Model 
AS332L2 helicopters; and ASB No. 05A002, Revision 1, dated December 
6, 2007, for the Model EC225LP helicopters.
    (2) If the loss of tightening torque of a nut is less than or 
equal to 20 percent of the minimum tightening torque, before further 
flight, readjust the tightening torque.
    (3) If the loss of tightening torque of any nut (front or rear) 
is greater than 20 percent of the minimum tightening torque, before 
further flight:
    (i) Inspect each bolt and nut that secures the attachment 
fitting for a crack, and
    (ii) Inspect for a crack in the attachment area of the 
attachment fitting, the attachment plate, and Frame 3855 for the 
front fitting and Frame 5295 for the rear fitting.
    (A) If no crack exists, readjust the tightening torque.
    (B) If there is a crack in any nut or bolt, before further 
flight, replace all four nuts and bolts of the affected attachment 
fitting.
    (C) If there is a crack in the attachment area of the attachment 
fitting or the attachment plate, before further flight, replace the 
cracked attachment fitting or plate with an airworthy fitting or 
plate.
    (D) If there is a crack in Frame 3855 for the front fitting or 
Frame 5295 for the rear fitting, before further flight, repair or 
replace the frame.

(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 <a href="/cdn-cgi/l/email-protection#533432212a7d317d213c32303b133532327d343c25"><span class="__cf_email__" data-cfemail="caadabb8b3e4a8e4b8a5aba9a28aacababe4ada5bc">[email&#160;protected]</span></a>.
    (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

[[Page 70207]]

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 the European Aviation 
Safety Agency (EASA) AD No. 2006-0163 R1, dated December 13, 2007. 
You may view the EASA AD at <a href="http://www.regulations.gov">http://www.regulations.gov</a> in Docket No. 
FAA-2013-0487.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6330, Main Rotor 
Transmission Mount.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference 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 Alert Service Bulletin No. 05.00.65, Revision 0, 
dated March 28, 2006.
    (ii) Eurocopter Alert Service Bulletin No. 05A002, Revision 1, 
dated December 6, 2007.
    (3) For Eurocopter service information identified in this AD, 
contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand 
Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax 
(972) 641-3775; or at <a href="http://www.eurocopter.com/techpub">http://www.eurocopter.com/techpub</a>.
    (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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Fort Worth, Texas, on November 5, 2013.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2013-27638 Filed 11-22-13; 8:45 am]
BILLING CODE 4910-13-P