[Federal Register: September 18, 2007 (Volume 72, Number 180)]
[Rules and Regulations]
[Page 53112-53114]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr18se07-8]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27009; Directorate Identifier 2007-NE-02-AD;
Amendment 39-15200; AD 2007-19-09]
RIN 2120-AA64
Airworthiness Directives; Turbomeca Arriel 2B1 Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
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SUMMARY: We are superseding an existing airworthiness directive (AD) by
adopting a new AD for the products listed above. This AD results from
mandatory continuing airworthiness information (MCAI) provided by the
aviation authority of France to identify and correct an unsafe
condition on Turbomeca Arriel 2B1 turboshaft engines. The MCAI states
the following:
This AD is prompted by several reported cases of rupture of the
constant delta pressure valve diaphragm on Arriel 2B1 engines, due
to the wear of the delta P diaphragm fabric. Rupture can result in
the loss of the automatic control mode of the helicopter,
accompanied with a deterioration of the behavior of the auxiliary
back-up mode (emergency mode). On a single-engine helicopter, the
result may be an emergency landing or, at worst, an accident.
This AD supersedes European Aviation Safety Agency (EASA) AD
2007-0006 which required the removal from service of all the delta
pressure valve diaphragms logging more than 2,000 hours-since-new.
Since issuance of EASA AD 2007-0006, no further case of rupture
of the constant delta pressure valve diaphragm has been reported on
Arriel 2 engines. However, about 40 additional diaphragms returning
from service have been inspected by Turbomeca, and some signs of
wear have been detected on diaphragms having logged less than 2,000
hours. Based on the inspection results, it has been decided to
decrease this limit from 2,000 hours to 1,500 hours in order to
further reduce the probability of delta P diaphragm rupture.
We are issuing this AD to prevent forced autorotation landing, or an
accident.
DATES: This AD becomes effective October 3, 2007.
We must receive comments on this AD by October 18, 2007.
ADDRESSES: You may send comments by any of the following methods:
DOT Docket Web Site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
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.
Fax: (202) 493-2251.
Federal eRulemaking Portal: http://www.regulations.gov.
Follow the instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on the Internet at http://dms.dot.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 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: Christopher Spinney, Aerospace
Engineer, Engine Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803; e-
mail: christopher.spinney@faa.gov; telephone (781) 238-7175, fax (781)
238-7199.
SUPPLEMENTARY INFORMATION:
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued AD
2007-0126, dated May 7, 2007, to correct an unsafe condition for the
specified products. The EASA AD states:
This AD is prompted by several reported cases of rupture of the
constant delta pressure valve diaphragm on Arriel 2B1 engines, due
to the wear of the delta P diaphragm fabric. Rupture can result in
the loss of the automatic control mode of the helicopter,
accompanied with a deterioration of the behavior of the auxiliary
back-up mode (emergency mode). On a single-engine helicopter, the
result may be an emergency landing or, at worst, an accident.
This AD supersedes AD EASA AD 2007-0006 which required the
removal from service of all the delta pressure valve diaphragms
logging more than 2,000 hours-since-new.
Since issuance of EASA AD 2007-0006, no further case of rupture
of the constant delta pressure valve diaphragm has been reported on
Arriel 2 engines. However, about 40 additional diaphragms returning
from service have been inspected by Turbomeca, and some signs of
wear have been detected on
[[Page 53113]]
diaphragms having logged less than 2,000 hours. Based on the
inspection results, it has been decided to decrease this limit from
2,000 hours to 1,500 hours in order to further reduce the
probability of delta P diaphragm rupture.
The loss of automatic control mode coupled with the deteriorated
performance of the backup mode can lead to the inability to continue
safe flight, forced autorotation landing, or an accident. You may
obtain further information by examining the EASA AD in the AD docket.
This AD supersedes AD 2007-03-14, Amendment 39-14925 (72 FR 4948,
February 2, 2007), which we issued in response to EASA AD 2007-0006,
dated January 9, 2007.
Relevant Service Information
Turbomeca has issued Mandatory Service Bulletin No. 292 73 2818,
Original Issue, dated October 18, 2006, and Update No. 1, dated April
3, 2007. 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 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 agreement with France, they have notified us of the unsafe
condition described in the EASA AD and service information referenced
above. We are issuing this AD because we evaluated all the 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 AD requires initial and repetitive replacement of the HMU with a
serviceable HMU every 1,500 hours-in-service.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because of
the high risk to engines that could experience a ruptured delta P
diaphragm with HMUs that have accumulated over 1,500 operating hours.
Therefore, we 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. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2007-27009; Directorate
Identifier 2007-NE-02-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://dms.dot.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 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, 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 removing Amendment 39-14925 (72 FR
4948, February 2, 2007) and by adding the following new AD:
2007-19-09 Turbomeca: Amendment 39-15200; Docket No. FAA-2007-27009;
Directorate Identifier 2007-NE-02-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective October
3, 2007.
Affected ADs
(b) This AD supersedes AD 2007-03-14.
Applicability
(c) This AD applies to Turbomeca Arriel 2B1 turboshaft engines.
These engines are installed on, but not limited to, Eurocopter AS
350 B3 and EC 130 B4 helicopters.
Reason
(d) European Aviation Safety Agency (EASA) AD No. 2007-0126,
dated May 7, 2007, states:
This AD is prompted by several reported cases of rupture of the
constant delta pressure valve diaphragm on Arriel 2B1 engines, due
to the wear of the delta P diaphragm fabric. Rupture can result in
the loss of the automatic control mode of the helicopter,
accompanied with a deterioration of the behavior of the auxiliary
back-up mode (emergency mode). On a single-engine helicopter, the
result may be an emergency landing or, at worst, an accident.
This AD supersedes EASA AD 2007-0006 which required the removal
from service of all the delta pressure valve diaphragms logging more
than 2,000 hours-since-new.
Since issuance of EASA AD 2007-0006, no further case of rupture
of the constant delta pressure valve diaphragm has been reported on
Arriel 2 engines. However, about 40 additional diaphragms returning
from service have been inspected by Turbomeca, and
[[Page 53114]]
some signs of wear have been detected on diaphragms having logged
less than 2,000 hours. Based on the inspection results, it has been
decided to decrease this limit from 2,000 hours to 1,500 hours in
order to further reduce the probability of delta P diaphragm
rupture.
The loss of automatic control mode coupled with the deteriorated
performance of the backup mode can lead to the inability to continue
safe flight, forced autorotation landing, or an accident.
Actions and Compliance
(e) Unless already done, do the following actions.
(1) Replace the HMU with a serviceable HMU before the HMU
accumulates 1,500 hours-since-new, since-last-overhaul, or since-
incorporation of Turbomeca Service Bulletin (SB) No. 292 73 2105; or
by July 30, 2007, whichever occurs later.
(2) Thereafter, replace HMUs with a serviceable HMU at every
1,500 hours-since-new, since-last-overhaul, or since-incorporation
of Turbomeca SB No. 292 73 2105, whichever occurs later.
(3) For the purposes of this AD, a serviceable HMU is an HMU
fitted with a new constant delta P diaphragm in accordance with
Turbomeca Service Bulletin (MSB) No. 292 73 2818, Original Issue,
dated October 18, 2006, or Update No. 1, dated April 3, 2007.
Other FAA AD Provisions
(f) Alternative Methods of Compliance (AMOCs): 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
(g) Contact Christopher Spinney, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
christopher.spinney@faa.gov; telephone (781) 238-7175, fax (781)
238-7199, for more information about this AD.
Material Incorporated by Reference
(h) None.
Issued in Burlington, Massachusetts, on September 11, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. E7-18337 Filed 9-17-07; 8:45 am]
BILLING CODE 4910-13-P