Airworthiness Directives; Eurocopter France Model SA-365N, SA-365N1, AS-365N2, AS-365N3, SA-366G1, EC 155B, EC155B1, SA-365C, SA-365C1, SA-365C2, SA-360C Helicopters

[Federal Register Volume 75, Number 194 (Thursday, October 7, 2010)]
[Rules and Regulations]
[Pages 61980-61982]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-24725]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0610; Directorate Identifier 2009-SW-47-AD; 
Amendment 39-16455; AD 2010-20-20]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SA-365N, SA-
365N1, AS-365N2, AS-365N3, SA-366G1, EC 155B, EC155B1, SA-365C, SA-
365C1, SA-365C2, SA-360C Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD) for the specified Eurocopter France (Eurocopter) helicopters. That 
AD requires repetitively inspecting the main gearbox (MGB) planet gear 
carrier for a crack and replacing any MGB that has a cracked planet 
gear carrier before further flight. This action requires the same 
inspections required by the existing AD, but shortens the initial 
inspection interval. This AD is prompted by the discovery of another 
crack in a MGB planet gear carrier and additional analysis that 
indicates that the initial inspection interval must be shortened. The 
actions specified by this AD are intended to detect a crack in the web 
of the planet gear carrier, which could lead to a MGB seizure and 
subsequent loss of control of the helicopter.

DATES: Effective November 12, 2010.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 12, 2010.

ADDRESSES: You may examine the docket that contains this AD, any 
comments, and other information on the Internet at http://www.regulations.gov, or at the Docket Operations office, West Building 
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, 
DC.
    You may get the service information identified in this AD from 
American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 
75053-4005, telephone (972) 641-3460, fax (972) 641-3527.
    Examining the Docket: You may examine the docket that contains this 
AD, any comments, and other information on the Internet at http://www.regulations.gov, or at the Docket Operations office, West Building 
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, 
DC.

FOR FURTHER INFORMATION CONTACT: Gary Roach, Aerospace Engineer, FAA, 
Regulations and Policy Group, 2601 Meacham Blvd., ASW-111, Fort Worth, 
Texas 76137; telephone: (817) 222-5130; fax: 817-222-5961.

SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 by 
superseding AD 2005-03-09, Amendment 39-13965 (70 FR 7382, February 14, 
2005), for the specified Eurocopter France (Eurocopter) model 
helicopters was published in the Federal Register on June 28, 2010 (75 
FR 36581). The action proposed to require shortening the initial 
inspection required by AD 2005-03-09 from 265 hours time-in-service 
(TIS) to 35 hours TIS and retaining the 50-hour TIS recurring 
inspections. That proposal was prompted by the finding of an additional 
crack in the MGB planet gear carrier of a Eurocopter Model EC 155 
helicopter. That crack was caused by a progressive fatigue failure 
caused by scoring in the blend radius between the pin and the web. An 
additional analysis indicates that the initial inspection must be 
shortened. Therefore, this AD shortens the initial inspection from 265 
hours time-in-service (TIS) to 35 hours TIS. The recurring 50 hour-TIS 
inspections would remain the same.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for France, has issued EASA Emergency Airworthiness Directive No. 
2007-0288-E, dated November 15, 2007. EASA states that cracks were 
discovered in the web of the MGB planet gear carrier. ``The two 
affected MGB units had been removed for overhaul/repair, subsequent to 
the detection of metal chips at the magnetic plugs.'' Investigation of 
the first case showed a failure of the head of a screw that secures the 
sun gear bearing. The screw head was caught by the planet gear/fixed 
ring gear/sun gear drive train. The second case was discovered by the 
manufacturer and did not seem to be associated with any other failure. 
You may obtain further information by examining the MCAI and any 
related service information in the AD docket.

Related Service Information

    Eurocopter France has issued the following Emergency Alert Service 
Bulletins:
    <bullet> No. 05A007, Revision 2, for the Model EC155 helicopters;
    <bullet> No. 05.00.48, Revision 3, for the Model AS365 helicopters;

[[Page 61981]]

    <bullet> No. 05.26, Revision 2, for the Model SA360 and SA365 
helicopters; and
    <bullet> No. 05.33, Revision 2, for the SA366 helicopters.

Each Emergency Alert Service Bulletin (EASB) at the stated revision 
level is dated November 16, 2009 and describes the discovery of a 
progressive fatigue failure of the planet gear carrier. The EASBs 
specify inspecting the MGB planet gear carrier for a crack and removing 
the MGB and contacting the manufacturer before the next flight if a 
crack is found.

FAA's Evaluation and Unsafe Condition Determination

    These products 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 MCAI AD. We are proposing 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 products of these same type 
designs. This AD requires inspecting the MGB planet gear carrier for a 
crack and replacing the MGB before further flight if a crack is found. 
The actions must be accomplished by following the specified portions of 
the EASBs described previously.

Differences Between This Proposed AD and the MCAI AD

    The MCAI AD references the service information rather than stating 
compliance times as we have done in this AD. Unlike the MCAI AD, we 
have structured our compliance times based on a 250-hour TIS threshold. 
Also, this AD does not require you to report cracks in the planet gear 
carrier to the manufacturer.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.

Costs of Compliance

    We estimate that this AD will affect 145 helicopters of U.S. 
registry. We also estimate that it will take about 1 work-hour per 
helicopter for each borescope inspection and 12 work-hours for each 
visual inspection. Replacing the MGB, if necessary, will take about 16 
work-hours. The average labor rate is $85 per work-hour. Required parts 
will cost about $66,780 per MGB. Based on these figures, we estimate 
the cost of this AD on U.S. operators is $3,486,760, assuming that a 
borescope inspection is done on the entire fleet 12 times a year, that 
no visual inspections are done, and that 49 MGBs are replaced.

Regulatory Findings

    We have 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 above, I certify that the 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); and
    3. 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. See the AD docket to examine the economic evaluation.

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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
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. Section 39.13 is amended by removing Amendment 39-13965 (70 FR 7382, 
February 14, 2005), and by adding a new airworthiness directive (AD), 
Amendment 39-16455, to read as follows:

2010-20-20 Eurocopter France: Amendment 39-16455; Docket No. FAA-
2010-0610; Directorate Identifier 2009-SW-47-AD. Supersedes AD 2005-
03-09; Amendment 39-13965; Docket No. FAA-2005-20294; Directorate 
Identifier 2004-SW-39-AD.

    Applicability: Model EC 155B, EC155B1, SA-360C, SA-365C, SA-
365C1, SA-365C2, SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-
366G1 helicopters, certificated in any category.
    Compliance: Required as indicated.

------------------------------------------------------------------------
   For a main gearbox (MGB) that has:                Inspect:
------------------------------------------------------------------------
(1) Less than 250 hours time-in-service  On or before the MGB reaches 35
 (TIS) since new or last overhaul.        hours TIS, unless accomplished
                                          previously, and thereafter at
                                          intervals not to exceed 50
                                          hours TIS.
(2) 250 or more hours TIS since new or   Within 15 hours TIS, unless
 last overhaul.                           accomplished previously, and
                                          thereafter at intervals not to
                                          exceed 50 hours TIS.
------------------------------------------------------------------------

    To detect a crack in the web of the planet gear carrier, which 
could lead to a MGB seizure and subsequent loss of control of the 
helicopter, accomplish the following:
    (a) Either borescope inspect the web of the MGB planet gear 
carrier for a crack in accordance with the Operational Procedure, 
paragraphs 2.B.2. through 2.B.2.a.1, of Eurocopter Emergency Alert 
Service Bulletin (EASB) No. 05A007, Revision 2; No. 05.00.48, 
Revision 3; No. 05.26, Revision 2; or No. 05.33, Revision 2; as 
applicable to

[[Page 61982]]

your model helicopter, or visually inspect the MGB planet gear 
carrier in accordance with the Operational Procedure, paragraphs 
2.B.3. through paragraph 2.B.3.a.1, of the EASB applicable to your 
model helicopter. Each EASB at the stated revision level is dated 
November 16, 2009.
    (b) If a crack is found in the planet gear carrier, replace the 
MGB with an airworthy MGB before further flight.
    (c) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Manager, Safety Management Group, FAA, Attn: Gary Roach, 
Aviation Safety Engineer, Rotorcraft Directorate, FAA, 2601 Meacham 
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5130, fax (817) 
222-5961, for information about previously approved alternative 
methods of compliance.
    (d) The Joint Aircraft System/Component (JASC) Code is 6320: 
Main Rotor Gearbox.
    (e) The inspections shall be done in accordance with the 
specified portions of Eurocopter Emergency Alert Service Bulletin 
No. 05A007, Revision 2, No. 05.00.48, Revision 3, No. 05.26, 
Revision 2, or No. 05.33, Revision 2. Each service bulletin at the 
stated revision level is dated November 16, 2009. The Director of 
the Federal Register approved this incorporation by reference in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be 
obtained from American Eurocopter Corporation, 2701 Forum Drive, 
Grand Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 
641-3527. Copies may be inspected at the FAA, Office of the Regional 
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas, 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.
    (f) This amendment becomes effective on November 12, 2010.

    Note:  The subject of this AD is addressed in European Aviation 
Safety Agency AD No. 2007-0288-E, dated November 15, 2007.


    Issued in Fort Worth, Texas, on September 22, 2010.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2010-24725 Filed 10-6-10; 8:45 am]
BILLING CODE 4910-13-P

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