
[Federal Register Volume 77, Number 25 (Tuesday, February 7, 2012)]
[Rules and Regulations]
[Pages 5991-5994]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-1118]



[[Page 5991]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0005; Directorate Identifier 2010-SW-091-AD; 
Amendment 39-16914; AD 2012-01-03]
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 the 
Eurocopter France (ECF) Model AS332L2 helicopter and superseding an AD 
for the Model EC225LP helicopter. This AD is prompted by the 
manufacturer issuing additional corrective action to prevent failure of 
the main gearbox (MGB) due to the degradation of the epicyclic module 
of the MGB and expands the applicability to include the ECF Model 
AS332L2 helicopter because an investigation showed a failure within the 
epicyclic reduction gear module resulted in the rupture of the MGB case 
and separation of the main rotor head of a model AS332L2 helicopter in 
2009. These actions are intended to prevent failure of the MGB and 
subsequent loss of control of the helicopter.

DATES: This AD becomes effective February 22, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of February 22, 
2012.
    We must receive comments on this AD by April 9, 2012.

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 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 http://www.eurocopter.com/techpub. You may review copies of 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., Fort Worth, Texas 76137; telephone: (817) 222-4389; fax: (817) 
222-5961, email rao.edupaganti@faa.gov.

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

    We issued Emergency AD (EAD) 2009-09-51 on April 17, 2009, to all 
known owners and operators of the Eurocopter Model EC225LP helicopter, 
and published that EAD as Amendment 39-16101 (74 FR 65679, December 11, 
2009) to require determining whether or not the ``CHIP'' detector light 
on the instrument panel had previously illuminated. If the ``CHIP'' 
detector light had illuminated because of a metal particle on the chip 
detector of the module, or if you could not determine from the 
maintenance records which ``CHIP'' detector caused the ``CHIP'' 
detector light to illuminate, or if the chip detector light stayed 
illuminated after the ``CHIP'' detector switch was turned to the ``CHIP 
PULSE'' setting, you are required to replace the module with an 
airworthy module before further flight. You are also required, before 
further flight, to inspect the MGB 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. This condition, if not corrected, could result in 
failure of the MGB and loss of control of the helicopter.
    Since issuing that AD, we have determined the AD should also apply 
to the Model AS332L2 helicopters. We have also determined that we 
incorrectly described a part as ``magnetic plug'', and the correct 
nomenclature is ``chip detector.'' Finally, we have determined that 
modifying the chip collector and inspecting the chip detector should be 
required to enhance the early detection capability of the chip 
detectors of the gearbox sump and the epicyclic module.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Emergency AD No. 2009-0099-E, dated April 23, 2009 (EAD No. 2009-0099-
E), which supersedes AD No. 2009-0087-E, dated April 11, 2009 and AD 
No. 2009-0095-E, dated April 17, 2009, to correct an unsafe condition 
for the Eurocopter Model AS332L2 and EC225LP helicopters. EASA advises 
that early investigations showed that 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.

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, their technical 
representative, has notified us of the unsafe condition described in 
the EASA AD. We are issuing this AD

[[Page 5992]]

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 two Emergency Alert Service Bulletins (EASBs) 
with four numbers: No. 05.00.81 for FAA type-certificated Model AS332L2 
helicopters; No. 05.00.58 for non-FAA type-certificated military Model 
AS532A2 and U2 helicopters; No. 05A016 for non-FAA type-certificated 
military Model EC725AP helicopters; and No. 05A017 for FAA type-
certificated Model EC225LP helicopters. Both EASBs are Revision 2, and 
are dated April 23, 2009. The EASBs specify checking the chip detector 
on the MGB epicyclic module, modifying the main module chip collector, 
reidentifying the chip collector, and installing the chip collector 
(MOD 0752522). EASA classified these EASBs, or later approved versions, 
as mandatory and issued EAD No. 2009-0099-E to ensure continued 
airworthiness of these helicopters.

AD Requirements

    This AD requires:
     Determining 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 
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.
     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.
     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.
     Inspecting the MGB module magnetic chip detector 
electrical circuit and determining whether the system is functioning 
properly, including whether the ``CHIP'' detector light annunciates on 
the instrument panel (Vehicle Monitoring System Screen).
     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 epicyclic 
module chip detector, (rather than the main reduction gear (lower MGB), 
the flared housing (mast assembly), the intermediate gearbox, or the 
tail rotor gearbox chip detectors) that caused the ``CHIP'' detector 
light to illuminate, replace the module with an airworthy module.
     Unless accomplished previously, within 50 hours TIS, 
remove, modify, reidentify, and reinstall the chip collector.
     Before installing a MGB on any Eurocopter Model AS332L2 or 
EC225LP helicopter, modify, reidentify, and reinstall the chip 
collector in accordance with paragraph (f)(3) of this AD.

Differences Between This AD and the EASA AD

    The differences between this AD and the EASA AD are:
     We use the term ``hours time-in-service'' rather than 
``flight hours'' to describe compliance times.
     We use the term ``chip detector'' rather than ``magnetic 
plug'' to refer to the same part.
     If it is determined that within the past 200 hours TIS a 
``CHIP'' light was caused by a particle in the module, we require 
replacing the module with an airworthy module rather than inspecting it 
and returning the same module to service.
     We do not mandate a calendar time for complying with this 
AD.
     The EASA AD specifies, for Eurocopter Model AS332L2 
helicopters, checking the chip detector of the module after the last 
flight of the day, not to exceed 10 hours TIS, and for the Model 
EC225LP helicopters, complying with the maintenance manual each time a 
particle is detected. This AD requires treating both models the same, 
since both models have the same type of chip detectors and anticipate 
compliance with ``normal'' maintenance procedures each time a particle 
is detected after accomplishing paragraph (f)(3) of this AD.
     We do not require returning unairworthy parts or found 
particles to the manufacturer.

Costs of Compliance

    We estimate that this AD will affect 4 helicopters of U.S. 
registry. We estimate that it will take about 1.0 work hour to inspect 
maintenance records to determine if a ``CHIP'' light illuminated within 
the past 200 hours TIS; 10 work-hours to remove, inspect, and replace a 
module; 14 work-hours to remove, modify, and replace the module to 
incorporate the ``CHIP'' collector and flange modifications (MOD 
0752522); and 0.2 work-hour, per inspection, to conduct the initial and 
repetitive inspection of the chip detector for metal particles. The 
average labor rate is $85 per work-hour, and we estimate it will cost 
$85 to inspect the maintenance records; $850 to remove, inspect, and 
replace a module; $1,190 to incorporate MOD 0752522; and $408 to 
inspect the chip detector (assumes 24 inspections per year per 
helicopter), for an estimated total labor cost of $2,533 per 
helicopter. Required parts cost is approximately $512,318 to replace a 
module. Based on these figures, we estimate the cost of this AD on U.S. 
operators is $522,450, assuming all required inspections and 
modifications are completed on all helicopters and 1 helicopter 
requires a module replacement

FAA's Justification and Determination of the Effective Date

    The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect 
both the structural integrity and controllability of the helicopter. 
Therefore, because the determination of the ``CHIP'' light 
illumination, inspection, and replacement of the module (on condition) 
are required before further flight, 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

[[Page 5993]]

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 adding the following new AD:

2012-01-03 Eurocopter France: Amendment No. 39-16914; Docket No. 
FAA-2012-0005; Directorate Identifier 2010-SW-091-AD.

    (a) Applicability. This AD applies to Model 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 the main 
gearbox (MGB). This condition could result in failure of the MGB and 
subsequent loss of control of the helicopter.
    (c) Other Affected ADs. This AD supersedes AD 2009-09-51, 
Amendment 39-16101, Docket No. FAA-2009-1089, Directorate Identifier 
2009-SW-16-AD, (74 FR 65679, Dec. 11, 2009).
    (d) Effective Date. This airworthiness directive (AD) becomes 
effective February 22, 2012.
    (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. To prevent failure of the main gearbox 
(MGB) and loss of control of the helicopter:
    (1) 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).
    (2) After accomplishing paragraph (f)(1) 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 intermediate gearbox, or the tail rotor gearbox 
chip detectors) that caused the ``CHIP'' detector light to 
illuminate, replace the module with an airworthy module.
    (3) 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.3.b.1) through 2.B.3.b.5) of Eurocopter Emergency Alert Service 
Bulletin (EASB) No. 05.00.81, Revision 2, dated April 23, 2009, or 
Eurocopter EASB No. 05A017, Revision 2, dated April 23, 2009, for 
your model helicopter.
    (4) Before installing a MGB, modify, reidentify, and reinstall 
the chip collector in accordance with paragraph (f)(3) of this AD.

    Note 1 to paragraph (f) of this AD: Eurocopter has issued two 
EASBs with four different numbers (Nos. 05.00.81, 05.00.58, 05A017, 
and 05A016) that apply to 5 different Eurocopter model helicopters. 
EASB No. 05.00.58 is for Eurocopter military Model AS532A2, and U2 
helicopters, and EASB No. 05A016 is for Eurocopter military Model 
EC725AP helicopters that are non-FAA type-certificated. EASB No. 
05.00.81 is for FAA type-certificated Eurocopter Model AS332L2 
helicopters and EASB No. 05A017 is for FAA type-certificated 
Eurocopter Model EC225LP helicopters. This AD does not incorporate 
by reference EASB Nos. 05A016 or 05.00.58.

    (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-
4389; fax: (817) 222-5961, email rao.edupaganti@faa.gov.
    (2) For operations conducted under a Part 119 operating 
certificate or under 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 AD No. 2009-0099-E, dated April 
23, 2009.
    (i) Subject. JASC Code: 6300: Rotor Drive System.
    (j) Material Incorporated by Reference. You must use the 
following service information to do the actions required by this AD, 
unless the AD specifies otherwise. The Director of the Federal 
Register approved the incorporation by reference (IBR) of the 
following service information under 5 U.S.C. 552(a) and 1 CFR part 
51:
    (1) Eurocopter Emergency Alert Service Bulletin No. 05.00.81, 
Revision 2, dated April 23, 2009, for the model AS332L2; and
    (2) Eurocopter Emergency Alert Service Bulletin No. 05A017, 
Revision 2, dated April 23, 2009, for the model EC225LP helicopters.
    (3) 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 http://www.eurocopter.com/techpub.
    (4) You may review copies of the referenced service information 
at the FAA, Office of the Regional Counsel, Southwest Region, 2601 
Meacham Blvd., Room 663, Fort Worth Texas 76137 or 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/code_of_federal_regulations/ibr_locations.html.


[[Page 5994]]


    Issued in Fort Worth, Texas, on December 28, 2011.
M. Monica Merritt,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012-1118 Filed 2-6-12; 8:45 am]
BILLING CODE 4910-13-P


