AD 2013-07-06

[Federal Register Volume 78, Number 76 (Friday, April 19, 2013)]
[Rules and Regulations]
[Pages 23462-23465]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2013-08459]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0307; Directorate Identifier 2012-SW-079-AD; 
Amendment 39-17410; AD 2013-07-06]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Helicopters

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting an airworthiness directive (AD) for Eurocopter 
France (Eurocopter) Model AS332C, AS332L, and AS332L1 helicopters and 
superseding an AD for Model AS332L2 and EC225LP helicopters. This AD 
requires inspecting the chip detector and modifying the chip collector, 
both installed on the main gearbox (MGB). This AD is prompted by an 
investigation which showed a failure within the epicyclic reduction 
gear module (epicyclic module) resulted in the rupture of the MGB case 
and separation of the main rotor head of a Model AS332L2 helicopter. 
These actions are intended to prevent failure of the MGB and subsequent 
loss of control of the helicopter.

DATES: This AD becomes effective May 6, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of May 6, 2013.
    We must receive comments on this AD by June 18, 2013.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Docket: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a>. Follow the online instructions for sending your 
comments electronically.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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 <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 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 AD, contact American 
Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, Texas 
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.

FOR FURTHER INFORMATION CONTACT: Rao Edupuganti, Aerospace Engineer, 
FAA, Rotorcraft Directorate, Regulations and Policy Group, 2601 Meacham 
Blvd.,

[[Page 23463]]

Fort Worth, Texas 76137; telephone: (817) 222-4389; fax: (817) 222-
5961, email <a href="/cdn-cgi/l/email-protection#eb998a84c58e8f9e9b8a8c8a859f82ab8d8a8ac58c849d"><span class="__cf_email__" data-cfemail="7507141a5b101100051412141b011c351314145b121a03">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments prior to it becoming effective. However, 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 resulted 
from adopting this AD. The most helpful comments reference a specific 
portion of the AD, 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 them 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 rulemaking during the 
comment period. We will consider all the comments we receive and may 
conduct additional rulemaking based on those comments.

Discussion

    On December 28, 2011, we issued AD 2012-01-03, Amendment 39-16914 
(77 FR 5991, February 7, 2012) for Eurocopter Model AS332L2 and EC225LP 
helicopters. AD 2012-01-03, Amendment 39-16914 requires determining 
whether the ``CHIP'' detector light illuminated because of a metal 
particle on the chip detector of the epicyclic module, and whether the 
``CHIP'' detector light stayed illuminated after the ``CHIP'' detector 
switch was turned to the ``CHIP PULSE'' setting. If so, or if the 
maintenance records do not indicate which ``CHIP'' detector caused the 
``CHIP'' detector light to illuminate or whether the detector light 
stayed illuminated after the switch was turned, AD 2012-01-03 requires 
replacing the epicyclic module before further flight. AD 2012-01-03 
also requires replacing the epicyclic module if, thereafter, the 
``CHIP'' detector light illuminates, stays illuminated after the switch 
is turned, and there is a metal particle on the epicyclic module chip 
detector. Lastly, AD 2012-01-03 requires removing, modifying, re-
identifying, and reinstalling the chip collector within 50 hours time-
in-serivce (TIS) and before installing a MGB on any applicable 
helicopter.
    AD 2012-01-03, Amendment 39-16914 (77 FR 5991, February 7, 2012) 
was prompted by an investigation of an accident that showed a failure 
within the epicyclic reduction gear module of the MGB resulted in the 
rupture of the MGB case, which allowed the main rotor head to separate 
from the helicopter. The European Aviation Safety Agency (EASA), which 
is the Technical Agent for the Member States of the European Union, had 
issued EASA AD 2009-0099-E, dated April 23, 2009 (2009-0099-E) to 
correct an unsafe condition for Eurocopter Model AS332L2 and EC225LP 
helicopters, and notified us of the unsafe condition in its AD. The 
actions of AD 2012-01-03 are intended to prevent failure of the MGB and 
subsequent loss of control of the helicopter.

Actions Since Existing AD Was Issued

    Since we issued AD 2012-01-03, Amendment 39-16914 (77 FR 5991, 
February 7, 2012), EASA issued EASA AD No. 2012-0129-E, dated July 13, 
2012 (2012-0129-E), which superseded EASA AD 2009-0099-E, to correct an 
unsafe condition for Eurocopter Model AS332C, AS332C1, AS332L, AS332L1, 
AS332L2, and EC225LP helicopters. EASA advises that, based on the final 
accident report following investigation of the accident that prompted 
its original AD, it is necessary to standardize the inspection 
intervals for all electrical and non-electrical chip detectors, require 
the inspection for all models of the ``Super-Puma'' helicopter family, 
and expand the inspection to all rotor drive system gear boxes (the 
intermediate gearbox (IGB) and the tail gear box (TGB), in addition to 
the MGB. EASA AD 2012-0129-E retains the modification of the MGB 
epicyclic reduction gear module requirement of EASA AD 2009-0099-E, but 
expands the applicability and requires a recurring inspection of all 
electrical and non-electrical chip detectors installed on the MGB, IGB, 
and TGB.

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.

Related Service Information

    Eurocopter has issued Emergency ASB No. 05.00.81, Revision 3, dated 
July 13, 2012 (EASB 05.00.81), for Model AS332L2 helicopters and 
Emergency ASB No. 05A017, Revision 3, dated July 13, 2012 (EASB 05A017) 
for Model EC225LP helicopters. Both Emergency ASBs specify procedures 
for checking the chip detector on the MGB epicyclic module, modifying 
the main module chip collector, reidentifying the chip collector, and 
installing the chip detector.
    Eurocopter has also issued Alert Service Bulletin (ASB) No. AS332-
05.00.94, Revision 0, dated July 13, 2012 (ASB AS332-05.00.94), for 
Model AS332 C, C1, L, L1, and L2 helicopters and ASB No. EC225-05A29, 
Revision 0, dated July 13, 2012 (ASB EC225-05A29) for Model EC225 LP 
helicopters. Both ASBs standardize the time interval between chip 
detector inspections of the MGB, IGB, and TGB.
    EASA classified these ASBs as mandatory and issued EASA AD 2012-
0129-E to ensure continued airworthiness of these helicopters.

AD Requirements

    This AD retains the inspection and modification requirements of AD 
2012-01-03, Amendment 39-16914 (77 FR 5991, February 7, 2012), and adds 
the following requirements:
    <bullet> For AS332 helicopters with non-electrical chip detectors 
and electrical chip detectors without a caution light on the instrument 
panel, within 25 hours TIS and thereafter at intervals not exceeding 25 
hours TIS, inspecting the MGB, IGB, and TGB chip detectors for a chip 
or magnetic particle.
    <bullet> For AS332 helicopters with electrical chip detectors with 
a caution light on the instrument panel, within 50 hours TIS and 
thereafter at intervals not exceeding 50 hours TIS, inspecting the MGB, 
IGB, and TGB chip detectors for a chip or magnetic particle.
    <bullet> For EC225 helicopters, within 50 hours TIS and thereafter 
at intervals not exceeding 50 hours TIS, inspecting the MGB, IGB, and 
TGB chip detectors for a chip or magnetic particle. If there is a chip 
or magnetic particle, verifying that the ``CHIP'' caution light 
illuminates on the ``Vehicle'' page of the Vehicle Management System.

Costs of Compliance

    We estimate that this AD will affect 6 helicopters of U.S. 
Registry. Based on an average labor rate of $85 per work hour, we 
estimate that operators may incur the following costs in order to 
comply with this AD:

[[Page 23464]]

    <bullet> Inspecting maintenance records to determine if a ``CHIP'' 
light illuminated within the past 200 hours TIS will take about 1.0 
work-hour, for a total cost per helicopter of $85;
    <bullet> Removing, inspecting, and replacing an affected epicyclic 
module will require about 10 work-hours and required parts would cost 
approximately $512,318, for a total cost per helicopter of $513,168;
    <bullet> Removing, modifying, and reidentifying the ``CHIP'' 
collector will require about 14 work-hours, for a total cost per 
helicopter of $1,190; and
    <bullet> Inspecting the module magnetic chip detector circuit and 
the MGB, IGB, and TGB chip detectors will require about 2 work-hours, 
for a total cost per helicopter of $170 per inspection cycle.

FAA's Justification and Determination of the Effective Date

    The short compliance time involved is required because the 
previously-described unsafe condition can adversely affect both the 
structural integrity and controllability of the helicopter. Therefore, 
because these helicopters are primarily used for long-range offshore 
transportation and the inspection of the MGB, IGB, and TGB chip 
detectors is required within 25 hours TIS, a very short time period 
based on the average flight-hour utilization rate of these helicopters, 
this AD must be issued immediately.
    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we determined that notice and opportunity for 
public comment before issuing this AD are impracticable and that good 
cause exists for making this amendment effective in less than 30 days.

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 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, 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 removing airworthiness directive (AD) 
2012-01-03, Amendment 39-16914 (77 FR 5991, February 7, 2012) and 
adding the following new AD:

2013-07-06 Eurocopter France (Eurocopter): Amendment 39-17410; 
Docket No. FAA-2013-0307; Directorate Identifier 2012-SW-079-AD.

(a) Applicability

    This AD applies to Eurocopter Model AS332C, AS332L, AS332L1, 
AS332L2, and EC225LP helicopters, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as degradation of the 
epicyclic reduction gear module within a rotor drive system gearbox. 
This condition could result in failure of the main gearbox (MGB), 
intermediate gearbox (IGB), or tail gearbox (TGB) and subsequent 
loss of control of the helicopter.

(c) Affected ADs

    This AD supersedes AD 2012-01-03, Amendment No. 39-16914 (77 FR 
5991, February 7, 2012).

(d) Effective Date

    This AD becomes effective May 6, 2013.

(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 Model AS332L2 and EC225LP helicopters, before further 
flight:
    (i) Determine from the maintenance records whether, within the 
last 200 hours time-in-service (TIS), the ``CHIP'' detector light 
illuminated because of a metal particle on the chip detector of the 
MGB epicyclic module (module), and if so, whether the ``CHIP'' 
detector light stayed illuminated after the ``CHIP'' detector switch 
was turned to the ``CHIP PULSE'' setting to activate the ``fuzz 
burn-off'' feature.
    (A) If the maintenance records indicate that the ``CHIP'' 
detector light illuminated because of a metal particle on the chip 
detector of the module, and the ``CHIP'' detector light stayed 
illuminated after the ``CHIP'' detector switch was turned to the 
``CHIP PULSE'' setting, replace the module with an airworthy module 
before further flight.
    (B) If the maintenance records do not indicate which ``CHIP'' 
detector caused the ``CHIP'' detector light to illuminate, or 
whether the detector light stayed illuminated after the ``CHIP'' 
detector switch was turned to the ``CHIP PULSE'' setting, replace 
the module with an airworthy module before further flight.
    (ii) Inspect the module magnetic chip detector electrical 
circuit and determine whether the system is functioning properly, 
including whether the ``CHIP'' detector light annunciates on the 
instrument panel (Vehicle Monitoring System Screen).
    (iii) After accomplishing paragraph (f)(1)(i)-(ii) of this AD, 
thereafter, if the ``CHIP'' detector light illuminates, stays 
illuminated after the chip detector switch is turned to the ``CHIP 
PULSE'' setting, and there is a metal particle on the module 
magnetic chip detector (rather than the main reduction gear (lower 
MGB), the flared housing (mast assembly), the IGB, or the TGB chip 
detectors) that caused the ``CHIP'' detector light to illuminate, 
replace the module with an airworthy module.
    (iv) Within 50 hours TIS, remove, modify, reidentify, and 
reinstall the chip collector as shown in Figures 2 through 5, and in 
accordance with the Accomplishment Instructions, paragraph 2.B.1.b.1 
through 2.B.1.b.5, of Eurocopter Emergency Alert Service Bulletin 
(EASB) No. 05.00.81, Revision 3, dated July 13, 2012, or Eurocopter 
EASB No. 05A017, Revision 3,

[[Page 23465]]

dated July 13, 2012, for your model helicopter.
    (v) Before installing a MGB, modify, reidentify, and reinstall 
the chip collector in accordance with paragraph (f)(1)(iv) of this 
AD.
    (2) Within 25 hours TIS, and thereafter at intervals not 
exceeding 25 hours TIS:
    (i) For Model AS332C, L, and L1 helicopters with non-electrical 
chip detectors and electrical chip detectors without a caution light 
on the instrument panel, inspect the IGB, TGB, tapered housing, and 
MGB bottom casing chip detectors for a chip or metallic particle.
    (ii) For Model AS332L2 helicopters with non-electrical chip 
detectors and electrical chip detectors without a caution light on 
the instrument panel, inspect the module, main rotor mast tapered 
housing, IGB, and TGB chip detectors for a chip or metallic 
particle.
    (3) Within 50 hours TIS, and thereafter at intervals not 
exceeding 50 hours TIS:
    (i) For Model AS332C, L, and L1 helicopters with electrical chip 
detectors with a caution light on the instrument panel, inspect the 
MGB bottom casing, TGB, and IGB chip detectors for a chip or 
metallic particle.
    (ii) For Model AS332L2 helicopters with electrical chip 
detectors with a caution light on the instrument panel, inspect the 
MGB bottom casing chip detector for a chip or magnetic particle.
    (iii) For Model EC225LP helicopters, inspect the MGB, IGB, and 
TGB chip detectors for a chip or magnetic particle. If there is a 
chip or magnetic particle, determine whether the ``CHIP'' caution 
light illuminates on the ``Vehicle'' page of the Vehicle Management 
System. If the ``CHIP'' caution light does not illuminate on the 
``Vehicle'' page, perform a fault analysis.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Rao Edupuganti, Aerospace 
Engineer, FAA, Rotorcraft Directorate, Regulations and Policy Group, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone: (817) 222-
5110; fax: (817) 222-5961, email <a href="/cdn-cgi/l/email-protection#a1d3c0ce8fc4c5d4d1c0c6c0cfd5c8e1c7c0c08fc6ced7"><span class="__cf_email__" data-cfemail="99ebf8f6b7fcfdece9f8fef8f7edf0d9fff8f8b7fef6ef">[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 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

    (1) Eurocopter Alert Service Bulletin (ASB) No. AS332-05-00-94, 
Revision 0, dated July 13, 2012, and ASB No. EC225-05A29, Revision 
0, dated July 13, 2012, which are not incorporated by reference, 
contain additional information about the subject of this AD. For 
service information identified in this AD, contact American 
Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, Texas 
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 a copy 
of the service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas 76137.
    (2) The subject of this AD is addressed in European Aviation 
Safety Agency AD No. 2012-0129-E, dated July 13, 2012.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6320: Main Rotor 
Gearbox and 6520: Tail Rotor Gearbox.

(j) 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 (EASB) No. 
05.00.81, Revision 3, dated July 13, 2012.

    Note 1 to paragraph (j)(2)(i): Eurocopter EASB No. 05.00.81, 
Revision 3, dated July 13, 2012, and EASB No. 05.00.58, Revision 3, 
dated July 13, 2012, were published together as a single document. 
EASB No. 05.00.58, Revision 3, dated July 13, 2012 is not 
incorporated by reference.

    (ii) Eurocopter EASB No. 05A017, Revision 3, dated July 13, 
2012.

    Note 2 to paragraph (j)(2)(ii): Eurocopter EASB No. 05A017, 
Revision 3, dated July 13, 2012, and EASB No. 05A016, Revision 3, 
dated July 13, 2012, were published together as a single document. 
EASB No. 05A016, Revision 3, dated July 13, 2012 is not incorporated 
by reference.

    (3) For Eurocopter service information identified in this AD, 
contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand 
Prairie, Texas 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 March 27, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-08459 Filed 4-18-13; 8:45 am]
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