Airworthiness Directives; Turbomeca Arriel 2B and 2B1 Turboshaft Engines

[Federal Register Volume 75, Number 23 (Thursday, February 4, 2010)]
[Rules and Regulations]
[Pages 5689-5690]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-1735]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0889; Directorate Identifier 2009-NE-35-AD; 
Amendment 39-16189; AD 2010-03-06]
RIN 2120-AA64


Airworthiness Directives; Turbomeca Arriel 2B and 2B1 Turboshaft 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) issued by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    Several events of uncoupling of the low-pressure (LP) fuel pump 
impeller and the high-pressure (HP) fuel pump shaft have been 
reported on Arriel 2 engines which do not incorporate Modification 
TU 147. In most cases the ``low fuel pressure switch'' enlightened, 
the pilot activated the aircraft booster pump in accordance with the 
Flight Manual Instructions and landed safely with no other incident. 
One case, on a single-engine helicopter, led to a sudden engine 
power loss. The uncoupling of the LP fuel pump impeller and the HP 
fuel pump shaft may lead to a limitation of engine power or, at 
worst, an uncommanded in-flight shutdown. On a single-engine 
helicopter, the result may be an emergency autorotation landing.

    We are issuing this AD to prevent a forced autorotation landing or 
an accident.

DATES: This AD becomes effective March 11, 2010. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in this AD as of March 11, 2010.

ADDRESSES: The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.
    Contact Turbomeca, 40220 Tarnos, France; telephone (33) 05 59 74 40 
00, fax (33) 05 59 74 45 15, for the service information identified in 
this AD.

FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
[email protected]; telephone (781) 238-7176; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on November 5, 2009 (74 
FR 57277). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states that:

    Several events of uncoupling of the LP fuel pump impeller and 
the HP fuel pump shaft have been reported on Arriel 2 engines which 
do not incorporate Modification TU 147. In most cases the ``low fuel 
pressure switch'' enlightened, the pilot activated the aircraft 
booster pump in accordance with the Flight Manual Instructions and 
landed safely with no other incident. One case, on a single-engine 
helicopter, led to a sudden engine power loss. The uncoupling of the 
LP fuel pump impeller and the HP fuel pump shaft may lead to a 
limitation of engine power or, at worst, an uncommanded in-flight 
shutdown. On a single-engine helicopter, the result may be an 
emergency autorotation landing.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received.
    One commenter, a private citizen, states that the labor rate of $80 
per work-hour referenced in the proposed AD is underestimated. He 
states that it should be at least $95 per work-hour.
    We partially agree. The work-hour labor rate estimate is 
established by the FAA's Regulatory Analysis Division which recently 
published a new rate; $85 per work-hour. We changed the AD to reflect 
this increase.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting the 
AD with the change described previously.

Differences Between This AD and the MCAI or Service Information

    The MCAI requires checking the transmissible torque between the LP 
pump impeller and the HP pump shaft within 550 engine flight hours from 
the effective date of the AD, but no later than June 30, 2010.
    This AD requires checking the transmissible torque between the LP 
pump impeller and the HP pump shaft within 550 engine flight hours from 
the effective date of the AD.

Costs of Compliance

    Based on the service information, we estimate that this AD will 
affect about 414 engines installed on helicopters of U.S. registry. We 
also estimate that it will take about 2.5 work-hours per engine to 
comply with this AD. The average labor rate is $85 per work-hour. 
Replacement HP/LP pump metering units (HMUs) will cost about $12,000 
per engine. Based on these figures, if all of the HMUs were to fail the 
check, we estimate the cost of the AD to U.S. operators to be 
$5,055,975.

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

[[Page 5690]]

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 above, 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 a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

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 regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is provided in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

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:

2010-03-06 Turbomeca: Amendment 39-16189. Docket No. FAA-2009-0889; 
Directorate Identifier 2009-NE-35-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective March 
11, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Turbomeca Arriel 2B and 2B1 turboshaft 
engines that have not incorporated Modification TU 147. These 
engines are installed on, but not limited to, Eurocopter AS 350 B3 
and EC 130 B4 helicopters.

Reason

    (d) This AD results from mandatory continuing airworthiness 
information (MCAI) issued by an aviation authority of another 
country to identify and correct an unsafe condition on an aviation 
product. We are issuing this AD to prevent a forced autorotation 
landing or an accident.

Actions and Compliance

    (e) Unless already done, do the following actions.
    (1) Within 550 engine flight hours from the effective date of 
this AD, check the transmissible torque between the low-pressure 
(LP) pump impeller and the high-pressure (HP) pump shaft of the HP/
LP pump metering unit (HMU). Use paragraph 2 of the Instructions to 
be Incorporated of Turbomeca Mandatory Service Bulletin No. A292 73 
2830, Version B, dated July 10, 2009, to do the check.
    (2) If the check is compliant, apply the nominal tightening 
torque to the screw of the LP pump impeller.
    (3) If the check is not compliant, replace the HP/LP pump HMU 
with a unit that has not incorporated Modification TU 147 but has 
passed the check, or with a unit that has incorporated Modification 
TU 147.

FAA AD Differences

    (f) This AD differs from the MCAI and/or service information as 
follows:
    (1) The MCAI requires the checking of the transmissible torque 
between the LP pump impeller and the HP pump shaft within 550 engine 
flight hours from the effective date of the AD, but no later than 
June 30, 2010.
    (2) This AD requires the checking of the transmissible torque 
between the LP pump impeller and the HP pump shaft within 550 engine 
flight hours from the effective date of this AD.

Alternative Methods of Compliance (AMOCs)

    (g) The Manager, Engine Certification Office, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19.

Related Information

    (h) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2009-0184, dated August 14, 2009, for related information.
    (i) Contact James Lawrence, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
[email protected]; telephone (781) 238-7176; fax (781) 238-
7199, for more information about this AD.

Material Incorporated by Reference

    (j) You must use Turbomeca Mandatory Service Bulletin No. A292 
73 2830, Version B, dated July 10, 2009, to do the transmissible 
torque check required by this AD.
    (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 
Turbomeca, 40220 Tarnos, France; telephone (33) 05 59 74 40 00, fax 
(33) 05 59 74 45 15.
    (3) You may review copies at the FAA, New England Region, 12 New 
England Executive Park, Burlington, MA; 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 Burlington, Massachusetts, on January 21, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2010-1735 Filed 2-3-10; 8:45 am]
BILLING CODE 4910-13-P

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