Document ID: FAA-2008-0935-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Turbomeca Arriel 2B and 2B1 Turboshaft Engines
Posted Date: 2008-10-30T04:00Z

[Federal Register: October 30, 2008 (Volume 73, Number 211)]
[Proposed Rules]               
[Page 64566-64568]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr30oc08-16]                         

========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================

[[Page 64566]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0935; Directorate Identifier 2008-NE-28-AD]
RIN 2120-AA64

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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed 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 cases of loss of internal components from the Hydro 
Mechanical Unit (HMU) low fuel pressure switch Hydra-Electric part 
number (P/N) 9 550 17 956 0 into the fuel system, have been reported 
on Arriel 2 engines.
    The loss of internal components from the low fuel pressure 
switch into the fuel system may lead to a rupture of the HP-LP pumps 
drive shaft shear pin, and thus to a possible uncommanded in-flight 
shutdown (IFSD). On a single-engine helicopter, an uncommanded IFSD 
results in an emergency autorotation landing and in certain 
conditions may lead to an accident.

    We are proposing this AD to prevent forced autorotation landing, or 
an accident.

DATES: We must receive comments on this proposed AD by December 1, 
2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue, SE., West Building Ground 
Floor, Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: (202) 493-2251.

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

FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0935; 
Directorate Identifier 2008-NE-28-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on 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 
with FAA personnel concerning this proposed AD. Using the search 
function of the Web site, anyone can find and read the comments in any 
of our dockets, including, if provided, the name of the individual who 
sent the comment (or signed the comment on behalf of an association, 
business, labor union, etc.). You may review the DOT's complete Privacy 
Act Statement in the Federal Register published on April 11, 2000 (65 
FR 19477-78).

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2008-0077, dated April 28, 2008 (and corrected May 6, 2008) 
(referred to after this as ``the MCAI''), to correct an unsafe 
condition for the specified products. The MCAI states:

    Several cases of loss of internal components from the HMU low 
fuel pressure switch Hydra-Electric P/N 9 550 17 956 0 into the fuel 
system, have been reported on Arriel 2 engines.
    The loss of internal components from the low fuel pressure 
switch into the fuel system may lead to a rupture of the HP-LP pumps 
drive shaft shear pin, and thus to a possible uncommanded IFSD. On a 
single-engine helicopter, an uncommanded IFSD results in an 
emergency autorotation landing and in certain conditions may lead to 
an accident.
    The evaluation of this condition prompts the issuance of this 
AD, which requires the following actions for the HMUs installed on 
Arriel 2 single-engine applications in order to:
     Verify the part number of the low fuel pressure switch;
     If installed, replace the Hydra-Electric low fuel 
pressure switch P/N 9 550 17 956 0 (with either of two different P/N 
low fuel pressure switches, referenced in the MCAI).
     In case a Hydra-Electric switch P/N 9 550 17 956 0 is 
installed or may have been installed on the HMU, verify that no 
parts are found in the chamber of the HMU body where the base of the 
low fuel pressure switch has been installed.

    You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Turbomeca has issued Mandatory Service Bulletin No. 292 73 2826, 
dated March 13, 2008. The actions described in this service information 
are intended to correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of France, 
and is approved for operation in the United States. Pursuant to our 
bilateral

[[Page 64567]]

agreement with France, they have notified us of the unsafe condition 
described in the EASA AD and service information referenced above. 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 the same type design. This proposed AD 
would require a one-time inspection for affected low fuel pressure 
switches, for evidence of an affected switch previously installed and 
inspection for switch parts missing or fallen into the HMU well.

Difference Between This Proposed AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. We have proposed to not reference 
the P/Ns of the serviceable low pressure switch as the MCAI does, in 
order to follow FAA policies. This difference is described in a 
separate paragraph of the proposed AD. This requirement, if ultimately 
adopted, will take precedence over the actions in the MCAI.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 414 products installed on helicopters of U.S. 
registry. We also estimate that it would take about 1 work-hour per 
product to comply with this proposed AD. The average labor rate is $80 
per work-hour. Required parts would cost about $256 per product. Based 
on these figures, we estimate the cost of the proposed AD on U.S. 
operators to be $139,104. Our cost estimate is exclusive of possible 
warranty coverage.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
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 a regulatory evaluation of the estimated costs to 
comply with this proposed 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    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]

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

Turbomeca: Docket No. FAA-2008-0935; Directorate Identifier 2008-NE-
28-AD.

Comments Due Date

    (a) We must receive comments by December 1, 2008.

Affected Airworthiness Directives (ADs)

    (b) None.

Applicability

    (c) This AD applies to Turbomeca Arriel 2B and 2B1 turboshaft 
engines. These engines are installed on, but not limited to, 
Eurocopter France AS350B3 and EC130 B4 helicopters.

Reason

    (d) European Aviation Safety Agency (EASA) AD No. 2008-0077, 
dated March 13, 2006 (and corrected May 6, 2008), states:

    Several cases of loss of internal components from the Hydro 
Mechanical Unit (HMU) low fuel pressure switch Hydra-Electric part 
number (P/N) 9 550 17 956 0 into the fuel system, have been reported 
on Arriel 2 engines.
    The loss of internal components from the low fuel pressure 
switch into the fuel system may lead to a rupture of the HP-LP pumps 
drive shaft shear pin, and thus to a possible uncommanded in-flight 
shutdown (IFSD). On a single-engine helicopter, an uncommanded IFSD 
results in an emergency autorotation landing and in certain 
conditions may lead to an accident.

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

Actions and Compliance

    (e) Unless already done, do the following actions.
    (1) No later than September 30, 2009, perform a one-time 
inspection of the HMU, using paragraph 2 of Turbomeca Mandatory 
Service Bulletin (MSB) No. 292 73 2826, dated March 13, 2008, to 
identify the low fuel pressure switch installed on the adjusted HMU.
    (2) If a Hydra-Electric low fuel pressure switch, part number 
(P/N) 9 550 17 956 0 is installed:
    (i) Inspect the low fuel pressure switch and chamber of the HMU 
body.
    (ii) If any parts from the low fuel pressure switch are missing 
or found in the HMU chamber, replace the HMU with a new or 
overhauled HMU equipped with a serviceable low fuel pressure switch.
    (iii) If not, replace only the low fuel pressure switch with a 
serviceable low fuel pressure switch.
    (3) If a low fuel pressure switch other than a Hydra-Electric 
low fuel pressure switch, P/N 9 550 17 956 0 is installed, and that 
is the only type of low fuel pressure switch that has been installed 
since new, repair, or overhaul, no further action is required.
    (4) If a Hydra-Electric switch, P/N 9 550 17 956 0, has been or 
may have been installed previously, and the conditions of paragraph 
(e)(3) of this AD are not met:
    (i) Inspect the chamber of the HMU body.
    (ii) If any parts are found in the HMU chamber, replace the HMU 
with a new or overhauled HMU equipped with a serviceable low fuel 
pressure switch.

FAA AD Difference

    (f) This AD differs from the Mandatory Continuing Airworthiness 
Information (MCAI) and/or service information, by not referencing 
the P/Ns of the serviceable low fuel pressure switch, and, defining 
a serviceable low fuel pressure switch, for the purpose of this AD.

Definition

    (g) For the purpose of this AD, a serviceable low fuel pressure 
switch is a switch that has a P/N other than P/N 9 550 17 956 0.

[[Page 64568]]

Alternative Methods of Compliance (AMOCs)

    (h) 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

    (i) Refer to MCAI EASA AD 2008-0077, dated April 28, 2008 (and 
corrected May 6, 2008), for related information.
    (j) Contact James Lawrence, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-
7199, for more information about this AD.

    Issued in Burlington, Massachusetts, on October 23, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E8-25887 Filed 10-29-08; 8:45 am]

BILLING CODE 4910-13-P