Document ID: FAA-2009-0330-0006
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Turbomeca S.A. Turboshaft Engines
Posted Date: 2011-12-13T05:00Z

[Federal Register Volume 76, Number 239 (Tuesday, December 13, 2011)]
[Proposed Rules]
[Pages 77446-77448]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-31798]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0330; Directorate Identifier 2008-NE-43-AD]
RIN 2120-AA64

Airworthiness Directives; Turbomeca S.A. Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to Turbomeca S.A. Arrius 2F turboshaft engines with 
P3 air pipe (first section) part number (P/N) 0 319 71 918 0, 
installed. The existing AD currently requires inspections of the P3 air 
pipe (first section) and right-hand (RH) rear half-wall for proper 
clearance, and readjustment of the pipe if necessary. Since we issued 
that AD, Turbomeca S.A. has redesigned the RH rear half-wall to ensure 
sufficient clearance between the P3 air pipe (first section) and RH 
rear half-wall. This proposed AD would require the same inspections for 
installed engines, eliminate readjusting of the P3 air pipe (first 
section), require replacement of the RH rear half-wall under certain 
conditions, and adding an optional terminating action. We are proposing 
this AD to prevent an uncommanded power loss to flight idle, which 
could result in an emergency autorotation landing or accident.

DATES: We must receive comments on this proposed AD by February 13, 
2012.

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 comments.
     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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Turbomeca, 
40220 Tarnos, France; phone: 33 (0)5 59 74 40 00; telex 570 042; fax 33 
(0)5 59 74 45 15. You may review copies of the referenced service 
information at the FAA, Engine & Propeller Directorate, 12 New England 
Executive Park, Burlington, MA. For information on the availability of 
this material at the FAA, call (781) 238-7125.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
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 Office (phone: (800) 647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Mark Riley, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; phone: (781) 238-7758; 
fax: (781) 238-7199; email: mark.riley@faa.gov.

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-2009-0330; 
Directorate Identifier 2008-NE-43-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 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 proposed AD.

Discussion

    On June 30, 2009, we issued AD 2009-14-11, Amendment 39-15961 (74 
FR 34221, July 15, 2009), for Turbomeca S.A. Arrius 2F turboshaft 
engines with P3 air pipe (first section), P/N 0 319 71 918 0, 
installed. That AD requires inspections of the P3 air pipe (first 
section) and RH rear half-wall for sufficient clearance. That AD 
resulted from Turbomeca S.A. concluding that the tolerance of assembly 
established during the system design, could result in some rubbing 
between parts. Rubs between the pipe and the RH rear half-wall may lead 
to premature wearing and finally rupture of the P3 air pipe (first 
section). The loss of P3 air pressure would then force the fuel control 
system to idle, which could have a detrimental effect in critical 
phases of flight. We issued that AD to prevent an uncommanded power 
loss, which could result in an emergency autorotation landing or 
accident.

Actions Since Existing AD Was Issued

    Since we issued AD 2009-14-11 (74 FR 34221, July 15, 2009), 
Turbomeca determined that the clearance between the P3 air pipe (first 
section) and the RH rear half-wall might change during installation of 
the engine on the helicopter. Also since we issued that AD, Turbomeca 
introduced a new redesigned RH rear half-wall that ensures clearance 
with the P3 air pipe (first section). Also since we issued that AD, the 
European Aviation Safety Agency (EASA) superseded AD 2008-0134R1, dated 
February 17, 2009, EASA's new AD, AD 2011-0182, dated September 22, 
2011, required the same corrective actions as this proposed AD.

Relevant Service Information

    We reviewed Turbomeca S.A. Mandatory Service Bulletin (MSB) No. 319 
75 4810, Version B, dated January 25, 2011. The MSB describes 
procedures for inspecting the clearance between the P3 air pipe (first 
section) and the RH rear half-wall. The MSB also requires replacing the 
RH rear half-wall with a redesigned RH rear half-wall, P/N 0319 99 008 
0 for engines with no clearance between the P3 air pipe (first section) 
and the RH rear half-wall. Also, installation of the redesigned RH rear 
half-wall on any engine is terminating action to the inspections. EASA 
classified the MSB as mandatory and issued AD 2011-0182, dated 
September 22, 2011.

FAA's Determination

    We are proposing this AD supersedure, because we evaluated all the 
relevant information and

[[Page 77447]]

determined the unsafe condition described previously is likely to exist 
or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require inspections of the clearance between 
the P3 air pipe (first section) and RH rear half-wall for installed 
engines with RH rear half-wall, P/N 0319 99 824 0. This proposed AD 
would also eliminate readjustment of the P3 air pipe (first section), 
and define installation of the redesigned RH rear half-wall as optional 
terminating action to the inspections.

Costs of Compliance

    We estimate that this proposed AD would affect about 120 Arrius 2F 
turboshaft engines installed on helicopters of U.S. registry. We also 
estimate that it would take about 2 work-hours per engine to comply 
with this proposed AD. The average labor rate is $85 per work-hour. 
Required parts would cost about $2,565 per engine. Based on these 
figures, we estimate the cost of the proposed AD on U.S. operators to 
be $328,200. 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 have 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 that the 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),
    (3) Will not affect intrastate aviation in Alaska, 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.

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 removing airworthiness directive 
(AD) 2009-14-11, Amendment 39-15961 (74 FR 34221), and adding the 
following new AD:

Turbomeca S.A.: Docket No. FAA-2009-0330; Directorate Identifier 
2008-NE-43-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by February 13, 
2012.

(b) Affected ADs

    This AD supersedes AD 2009-14-11, Amendment 39-15961 (74 FR 
34221, July 15, 2009).

(c) Applicability

    This AD applies to Turbomeca S.A. Arrius 2F turboshaft engines 
with right-hand (RH) rear half-wall, part number (P/N) 0319 99 824 
0, installed.

(d) Unsafe Condition

    The P3 air pipe (first section) and the RH rear half-wall could 
rub each other. Rubbing between the pipe and the RH rear half-wall 
may lead to rupture of the P3 air pipe (first section), which could 
cause an uncommanded power loss to flight idle. We are issuing this 
AD to prevent an uncommanded power loss to flight idle, which could 
result in an emergency autorotation landing or accident.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) For installed engines, within 100 engine hours (EH) after 
the effective date of this AD:
    (i) Inspect the clearance between the P3 air pipe (first 
section) and the RH rear half-wall for sufficient clearance (0.5 mm 
or more).
    (ii) Use paragraph 2.B.(1) of Turbomeca Mandatory Service 
Bulletin (MSB) No. 319 75 4810, Version B, dated January 25, 2011 to 
do the inspection.
    (2) Thereafter, repeat the inspections in paragraphs (e)(1)(i) 
through (e)(1)(ii) of this AD as follows:
    (i) At every installation of a RH rear half-wall P/N 0 319 99 
824 0 on an installed engine, and
    (ii) After every installation or reinstallation of an engine 
with a RH rear half-wall P/N 0 319 99 824 0 installed.
    (3) If the P3 air pipe (first section) or the RH rear half-wall 
P/N 0 319 99 824 0 is found damaged, then before further flight, 
replace the damaged part(s) with parts eligible for installation.
    (4) If the P3 air pipe (first section) and the RH rear half-wall 
P/N 0 319 99 824 0 are found contacting each other but are not 
damaged, replace the RH rear half-wall with a RH rear half-wall 
eligible for installation.
    (5) If both the P3 air pipe (first section) and the RH rear 
half-wall are found not damaged during the inspections specified in 
paragraph (e)(1) or (e)(2) of this AD, and the clearance between 
them is less than 0.5 mm, but they are not contacting each other, 
then repeat the inspection in paragraphs (e)(1)(i) and (e)(1)(ii) of 
this AD within every 100 EH.
    (6) Installation of RH rear half-wall, P/N 0 319 99 008 0, is 
terminating action to the inspections required by paragraph (e) of 
this AD.
    (7) Once a RH rear half-wall, P/N 0 319 99 008 0, is installed 
on an engine, do not install a RH rear half-wall, P/N 0 319 99 824 
0, on that engine.

(f) Definition

    For the purpose of this AD, parts eligible for installation is 
defined as:
    (1) An undamaged P3 air pipe (first section).
    (2) An undamaged RH rear half-wall P/N 0 319 99 824 0.
    (3) A new design RH rear half-wall P/N 0 319 99 008 0.

(g) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, may approve 
alternative methods of compliance for this AD. Use the procedures 
found in 14 CFR 39.19 to make your request.

(h) Related Information

    (1) For more information about this AD, contact Mark Riley, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: (781) 238-7758; fax: (781) 238-7199; email: 
mark.riley@faa.gov.
    (2) European Aviation Safety Agency AD 2011-0182, dated 
September 22, 2011, pertains to the subject of this AD.

[[Page 77448]]

    (3) For service information identified in this AD, contact 
Turbomeca, 40220 Tarnos, France; telephone 33 (0)5 59 74 40 00; 
telex 570 042; fax 33 (0)5 59 74 45 15. You may review copies of the 
referenced service information at the FAA, Engine & Propeller 
Directorate, 12 New England Executive Park, Burlington, MA. For 
information on the availability of this material at the FAA, call 
(781) 238-7125.

    Issued in Burlington, Massachusetts, on December 5, 2011.
Peter A. White,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-31798 Filed 12-12-11; 8:45 am]
BILLING CODE 4910-13-P