Airworthiness Directives; Turbomeca Arriel 2B Series Turboshaft Engines, 12150-12151 [E6-3352]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 71, Number 46 (Thursday, March 9, 2006)]
[Proposed Rules]
[Pages 12150-12151]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-3352]


========================================================================
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.

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Federal Register / Vol. 71, No. 46 / Thursday, March 9, 2006 / 
Proposed Rules

[[Page 12150]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23809; Directorate Identifier 2005-NE-52-AD]
RIN 2120-AA64


Airworthiness Directives; Turbomeca Arriel 2B Series Turboshaft 
Engines

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for Turbomeca Arriel 2B, 2B1, and 2B1A turboshaft engines. This 
proposed AD would require visually inspecting the splines of the high-
pressure (HP) pump drive gear shaft and coupling shaft assembly for 
wear. This proposed AD results from reports of uncommanded in-flight 
shutdowns of engines. We are proposing this AD to detect wear on the 
splines of the HP pump drive gear shaft and coupling shaft assembly, 
which could interrupt the fuel flow and cause an uncommanded in-flight 
shutdown of the engine on a single-engine helicopter. The in-flight 
shutdown of the engine could result in a forced autorotation landing or 
accident.

DATES: We must receive any comments on this proposed AD by April 10, 
2006.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.
     DOT Docket Web site: Go to http: //dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Turbomeca, 40220 Tarnos--France; Tel (33) 05 59 74 40 00; 
Telex 570 042; Fax (33) 05 59 74 45 15 for the service information 
identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace 
Engineer, Engine Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803; 
telephone (781) 238-7175; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send us any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2006-23809; 
Directorate Identifier 2005-NE-52-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.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 
DMS Web site, anyone can find and read the comments in any of our 
dockets, including 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) or you 
may visit https://dms.dot.gov.

Examining the AD Docket

    You may examine the docket that contains the proposal, any comments 
received, and any final disposition in person at the Docket Management 
Facility Docket Office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Office (telephone (800) 
647-5227) is on the plaza level of the Department of Transportation 
Nassif Building at the street address stated in ADDRESSES. Comments 
will be available in the AD docket shortly after the Docket Management 
Facility receives them.

Discussion

    The Direction g[eacute]n[eacute]rale de l'aviation civile (DGAC), 
which is the airworthiness authority for France, recently notified us 
that an unsafe condition may exist on Turbomeca Arriel 2B, 2B1, and 
2B1A turboshaft engines. The DGAC advises that they have received two 
reports of uncommanded in-flight engine shutdowns. Worn splines on the 
drive shaft of the HP pump assembly caused an interruption of the fuel 
flow to the engine and caused the engine to shutdown.

Relevant Service Information

    We have reviewed and approved the technical contents of Turbomeca 
Mandatory Service Bulletin (MSB) No. 292 73 2812, Update No. 2, dated 
June 28, 2005. That MSB describes procedures for visually inspecting 
the splines of the coupling shaft assembly and the splines of the HP 
pump drive gear shaft for wear. The DGAC classified this MSB as 
mandatory and issued airworthiness directive F-2005-188, dated November 
23, 2005, in order to ensure the airworthiness of these Turbomeca 
Arriel 2B series turboshaft engines in France.

FAA's Determination and Requirements of the Proposed AD

    These engines, manufactured in France, are type-certificated for 
operation in the United States under the provisions of section 21.29 of 
the Federal Aviation Regulations (14 CFR 21.29) and the applicable 
bilateral airworthiness agreement. In keeping with this bilateral 
airworthiness agreement, the DGAC kept us informed of the situation 
described above. We have examined the DGAC's findings, reviewed all 
available information, and determined that AD action is necessary for 
products of this type design that are certificated for operation in the 
United

[[Page 12151]]

States. For this reason, we are proposing this AD, which would require:
     For hydromechanical units (HMUs) that have accumulated 450 
hours or more on the effective date of the proposed AD, an initial 
visual inspection of the splines of the coupling shaft assembly and HP 
pump drive gear shaft for wear within 50 hours after the effective date 
of the proposed AD, and
     For HMUs that have fewer than 450 hours on the effective 
date of the proposed AD, an initial visual inspection of the splines of 
the coupling shaft assembly and HP pump drive gear shaft for wear after 
accumulating 450 hours, but before accumulating 500 hours, and
     A repetitive visual inspection of the splines of the 
coupling shaft assembly and HP pump drive gear shaft for wear every 
time you remove or install the HMU, and
     Replacing the HMU and coupling shaft assembly if worn 
beyond limits.

The proposed AD would require you to use the service information 
described previously to perform these actions.

Costs of Compliance

    We estimate that this proposed AD would affect 107 engines 
installed on helicopters of U.S. registry. We also estimate that it 
would take about 1.0 work hours per engine to perform the proposed 
actions, and that the average labor rate is $65 per work hour. There 
are no required parts. Based on these figures, we estimate the total 
cost of the proposed AD to U.S. operators to be $6,955.

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); and
    3. Would 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. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Under the authority delegated to me by the Administrator, the 
Federal Aviation Administration 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 
airworthiness directive:

Turbomeca: Docket No. FAA-2006-23809; Directorate Identifier 2005-
NE-52-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by April 10, 
2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Turbomeca Arriel 2B, 2B1, and 2B1A 
turboshaft engines. These engines are installed on, but not limited 
to, Eurocopter AS350B3 and EC130B4 helicopters.

Unsafe Condition

    (d) This AD results from reports of uncommanded in-flight 
shutdowns of engines. We are issuing this AD to detect wear on the 
splines of the high-pressure (HP) pump drive gear shaft and the 
coupling shaft assembly, which could interrupt the fuel flow and 
cause an uncommanded in-flight shutdown of the engine on a single-
engine helicopter. The in-flight shutdown of the engine could result 
in a forced autorotation landing or accident.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

Initial Visual Inspection

    (f) Perform an initial visual inspection of the splines of the 
coupling assembly and the HP pump drive gear shaft for wear. Use 
2.A. through 2.C.(2) of the Instructions to be Incorporated of 
Turbomeca Mandatory Service Bulletin (MSB) No. 292 73 2812, Update 
No. 2, dated June 28, 2005, as follows:
    (1) For hydraulic mechanical units (HMUs) that have accumulated 
450 or more hours time-since-new (TSN) or time-since-overhaul (TSO) 
on the effective date of this AD, inspect within 50 hours after the 
effective date of this AD. Replace the HMU if worn beyond limits.
    (2) For HMUs that have fewer than 450 hours TSN or TSO on the 
effective date of this AD, inspect after accumulating 450 hours TSN 
or TSO, but before accumulating 500 hours TSN or TSO. Replace the 
HMU if worn beyond limits.

Repetitive Visual Inspections

    (g) Thereafter, perform a visual inspection of the splines of 
the coupling shaft assembly and the HP pump drive gear shaft for 
wear every time you remove or install the HMU. Use 2.A. through 
2.C.(2) of the Instructions to be Incorporated of Turbomeca MSB No. 
292 73 2812, Update No. 2, dated June 28, 2005. Replace the HMU and 
coupling shaft assembly if worn beyond limits.

Alternative Methods of Compliance

    (h) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD if 
requested using the procedures found in 14 CFR 39.19.

Related Information

    (i) DGAC airworthiness directive F-2005-188, dated November 23, 
2005, also addresses the subject of this AD.

    Issued in Burlington, Massachusetts, on March 2, 2006.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E6-3352 Filed 3-8-06; 8:45 am]
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