Document ID: FAA-2009-1124-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Eurocopter France Model SA 330 F, G, and J Helicopters
Posted Date: 2009-12-14T05:00Z

[Federal Register: December 14, 2009 (Volume 74, Number 238)]
[Rules and Regulations]               
[Page 66045-66047]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14de09-8]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-1124; Directorate Identifier 2009-SW-35-AD; 
Amendment 39-16128; AD 2009-25-09]
RIN 2120-AA64

 
Airworthiness Directives; Eurocopter France Model SA 330 F, G, 
and J Helicopters

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

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for the 
specified Eurocopter France (Eurocopter) helicopters. This AD results 
from a mandatory continuing airworthiness information (MCAI) AD issued 
by the European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community. The MCAI 
Emergency AD states that there has been a report of the failure of a 
flexible coupling on one of the main gearbox (MGB) inputs, which may be 
the result of loss of the tightening torque load, or insufficient 
tightening of the nuts on the bolts fixing the discs of the flexible 
coupling to its sliding and fixed hinges. This condition, if not 
corrected, could result in failure of the coupling discs, and if this 
condition develops on both the left-hand (LH) and right-hand (RH) MGB 
inputs, a complete loss of power to the transmission and subsequent 
loss of control of the helicopter.

DATES: This AD becomes effective on December 29, 2009.
    The incorporation by reference of certain publications is approved 
by the Director of the Federal Register as of December 29, 2009.
    We must receive comments on this AD by February 12, 2010.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting your 
comments electronically.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    You may get the service information identified in this AD from 
American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 
75053-4005, telephone (800) 232-0323, fax (972) 641-3710, or at http://
www.eurocopter.com.
    Examining the 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 stated in the 
ADDRESSES section of this AD. Comments will be available in the AD 
docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: DOT/FAA Southwest Region, Ed Cuevas, 
Aviation Safety Engineer, Safety Management Group, Rotorcraft 
Directorate, 2601 Meacham Blvd., Fort Worth, TX 76137; telephone 817-
222-5355, fax 817-222-5961.

SUPPLEMENTARY INFORMATION:

Discussion

    The EASA, which is the Technical Agent for the Member States of the 
European Community, has issued EASA AD No. 2008-0049-E, dated March 3, 
2008 (Corrected: March 7, 2008), to correct an unsafe condition for 
Eurocopter Model SA 330 F, G, and J helicopters, all serial numbers, 
with MGB input flexible coupling sliding and fixed flanges assemblies 
installed that have been modified per MOD 0752416 and MOD 0752419, but 
have not been subject to maintenance scheduled inspection per Working 
Card 65.32.601 since new or since a complete overhaul of the MGB. There 
has been one report of the failure of a modified flexible coupling 
assembly on one of the MGB inputs, which EASA has deemed to be the 
result of the loss of the tightening torque load, or insufficient 
tightening of the nuts on the bolts attaching the disks of the flexible 
coupling to its sliding and fixed flanges. This condition, if not 
corrected, could result in progressive fatigue failure of the coupling 
discs, caused by extensive fretting on the faces and in the holes of 
the flexible coupling discs. If this unsafe condition develops on both 
the LH and RH MGB inputs, it could result in a complete loss of power 
to the transmission and subsequent loss of control of the helicopter.

Related Service Information

    Eurocopter has issued Emergency Alert Service Bulletin No. 05.95, 
dated March 3, 2008, which specifies readjusting or checking the 
tightening torque load of the nuts on the bolts attaching the flexible 
coupling to the sliding coupling flange and the bolts attaching the 
flexible coupling to the fixed coupling flange, in order to prevent any 
damage to the flexible couplings, which, over time, may lead to the 
loss of input drive to the MGB. The actions described in the MCAI are 
intended to correct the same unsafe conditions as those identified in 
the service information.

FAA's Evaluation and Unsafe Condition 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 Agent, has 
notified us of the unsafe condition described in the MCAI AD. We are 
issuing this AD because we evaluated all information provided by EASA 
and determined the unsafe conditions exist and are likely to exist or 
develop on other helicopters of these same type designs.

Differences Between This AD and the MCAI AD

    The MCAI AD uses the term ``flight hours'' instead of ``hours time-
in-service'', as we have used in this AD. Also, the MCAI AD allows 
``use of later approved revisions'' of the service information to 
comply with the MCAI AD. Our AD requires compliance in accordance with 
the Eurocopter EASB. Additionally, this AD requires ``inspections'' 
conducted by a qualified mechanic, instead of ``checks'', which we 
allow a pilot to do. Finally, contacting Eurocopter Technical Support 
is not required by this AD as it is by the MCAI AD.

Costs of Compliance

    We estimate that this AD will affect about 14 helicopters of U.S. 
registry. We also estimate that it will take about:
     8 work-hours per helicopter to remove the engine, re-
adjust the

[[Page 66046]]

tightening torque load, and re-install the engine for 10 helicopters in 
the fleet;
     10 work-hours per helicopter to remove the engine, measure 
the tightening torque load, and re-install the engine on 3 helicopters 
in the fleet; and
     12 work-hours to remove the engine, inspect and replace a 
damaged flexible coupling, and re-install the engine on 1 helicopter.

The average labor rate is $80 per work-hour. Costs to replace a damaged 
flexible coupling, if necessary, include $1,018 for 6 nuts, $838 for 1 
flexible coupling, $71 for 6 (6 each) bolts, and $624 for 12 washers. 
Based on these figures, we estimate the cost of this AD on U.S. 
operators will be $12,311, assuming that 1 flexible coupling is damaged 
and needs to be replaced.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. We find that the risk to the flying public justifies waiving 
notice and comment prior to adoption of this rule because loss of the 
tightening torque load or insufficient tightening of the nuts on the 
bolts attaching the disks of the flexible coupling to its sliding and 
fixed flanges could result in a complete loss of power to the 
transmission, and there are helicopters that will be required to comply 
with this AD within a short time period because of the criticality of 
this unsafe condition. Therefore, we have 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 fewer 
than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. However, we invite you to send us any written data, views, or 
arguments concerning this AD. Send your comments to an address listed 
under the ADDRESSES section of this AD. Include ``Docket No. FAA-2009-
1124; Directorate Identifier 2009-SW-35-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this AD. We will 
consider all comments received by the closing date and may amend this 
AD because of those comments.
    We will post all comments we receive, without change, to http://
www.regulations.gov including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

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

    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.
    Therefore, I certify this AD:
    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 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

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. The FAA amends Sec.  39.13 by adding the following new AD:

2009-25-09 Eurocopter France: Amendment 39-16128. Docket No. FAA-
2009-1124; Directorate Identifier 2009-SW-35-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective on 
December 29, 2009.

Other Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Model SA 330 F, G, and J helicopters, all 
serial numbers, with main gearbox (MGB) input flexible coupling 
flange assemblies, part number (P/N) 330A-32937401, installed that 
have been modified per MOD 0752416 and MOD 0752419, but have not 
been subject to a maintenance scheduled inspection per Working Card 
65.32.601 since new or since a complete overhaul of the MGB, 
certificated in any category.

Reason

    (d) The mandatory continuing airworthiness information (MCAI) AD 
states that there has been one report of disks failure of a flexible 
coupling on one of the MGB inputs, which may be the result of the 
loss of the tightening torque load, or insufficient tightening of 
the nuts on the bolts attaching the disks of the flexible coupling 
to its sliding and fixed flanges. This condition, if not corrected, 
could result in progressive fatigue failure of the coupling discs, 
caused by extensive fretting on the faces and in the holes of the 
flexible coupling discs. If this unsafe condition develops on both 
the LH and RH MGB inputs, a complete power loss to the transmission 
could occur, resulting in subsequent loss of control of the 
helicopter.

Actions and Compliance

    (e) Required as indicated, unless previously accomplished.
    (1) For MGB input flexible coupling flange assemblies with less 
than 50 hours time-in-service (TIS) since new or since a complete 
overhaul of the MGB, re-adjust the tightening torque load of the 6 
nuts on the flexible coupling-to-flange attachment bolts. Accomplish 
this re-adjustment between 50 hours TIS and 75 hours TIS since new 
or since a complete overhaul of the MGB in accordance with paragraph 
2.B.2.a. of Eurocopter Emergency Alert Service Bulletin No. 05.95, 
dated March 3, 2008 (EASB).
    (2) For MGB input flexible coupling flange assemblies with 50 
hours TIS and 75 or less hours TIS since new or since a complete 
overhaul of the MGB, either:
    (i) Upon or before reaching 75 hours TIS since new or since a 
complete overhaul of the MGB, re-adjust the tightening torque load 
of the 6 nuts on the flexible coupling-to-flange attachment bolts in 
accordance with paragraph 2.B.2.a. of the EASB; or
    (ii) Upon or before reaching 125 hours TIS since new or since a 
complete overhaul of the

[[Page 66047]]

MGB, inspect the tightening torque load of the 6 nuts on the 
flexible coupling-to-flange attachment bolts in accordance with 
paragraph 2.B.2.b. of the EASB, except you are not required to 
contact the manufacturer.
    (3) For MGB input flexible coupling flange assemblies that have 
more than 75 hours TIS since new or since a complete overhaul of the 
MGB, within the next 50 hours TIS, inspect the tightening torque 
load of the 6 nuts on the flexible coupling-to-flange attachment 
bolts, in accordance with paragraph 2.B.2.b. of the EASB, except you 
are not required to contact the manufacturer.
    (4) Prior to installing a MGB that contains an input flexible 
coupling flange assembly that has been modified per MOD 0752416 and 
MOD 0752419, you must comply with the provisions of this AD.

Differences Between This AD and the MCAI AD

    (f) The MCAI AD uses the term ``flight hours'' instead of 
``hours time-in-service'', as we have used in this AD. Also, the 
MCAI AD allows ``use of later approved revisions'' of the service 
information to comply with the MCAI AD. Our AD requires compliance 
in accordance with Eurocopter Emergency Alert Service Bulletin No. 
05.95, dated March 3, 2008. Additionally, this AD requires 
``inspections'' by a qualified mechanic instead of ``checks'', which 
we allow a pilot to do. Finally, this AD does not require you to 
contact Eurocopter Technical Support, which is required by the MCAI 
AD.

Other Information

    (g) Alternative Methods of Compliance (AMOCs): The Manager, 
Safety Management Group, Attn: DOT/FAA Southwest Region, Ed Cuevas, 
Aerospace Engineer, Rotorcraft Directorate, 2601 Meacham Blvd., Fort 
Worth, Texas 76137; telephone (817) 222-5355, fax (817) 222-5961, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19.
    (h) European Aviation Safety Agency MCAI Airworthiness Directive 
No. 2009-0049-E, dated March 3, 2008 (Corrected: March 7, 2008), 
contains related information.

Joint Aircraft System/Component Code

    (i) JASC Code 6310: Engine/Transmission Coupling.

Material Incorporated by Reference

    (j) You must use the specified portions of Eurocopter Emergency 
Alert Service Bulletin No. 05.95, dated March 3, 2008, to do the 
actions required.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 
75053-4005, telephone (800) 232-0323, fax (972) 641-3710, or at 
http://www.eurocopter.com.
    (3) You may review copies at the FAA, Office of the Regional 
Counsel, Southwest Region, 2601 Meacham Blvd., 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/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on November 18, 2009.
Gary B. Roach,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E9-29424 Filed 12-11-09; 8:45 am]

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