[Federal Register: November 28, 2007 (Volume 72, Number 228)]
[Rules and Regulations]
[Page 67245-67247]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr28no07-7]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26102; Directorate Identifier 2006-NE-36-AD;
Amendment 39-15272; AD 2007-24-06]
RIN 2120-AA64
Airworthiness Directives; Societe de Motorisations Aeronautiques
(SMA) SR305-230 and SR305-230-1 Reciprocating Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for the products listed above. This AD results from mandatory
continuing airworthiness information (MCAI) provided by the European
Aviation Safety Agency (EASA) to identify and correct an unsafe
condition on SMA SR305-230 and SR305-230-1 reciprocating engines. The
MCAI states the following:
Over a period of time, the alteration of one electronic control
unit (ECU) electronic component can cause a rapid uncontrolled power
increase. Several occurrences have already been reported during
engine start or during engine warm-up. This condition, if not
corrected, could result in the loss of control of the aircraft if
the pilot fails to react appropriately by switching to the
mechanical backup mode.
We are issuing this AD to prevent a rapid uncontrolled power
increase and possible loss of control of the airplane.
DATES: This AD becomes effective December 13, 2007. The Director of the
Federal Register approved the incorporation by reference of SMA Service
Bulletin (SB) No. SB-01-76-005, dated December 15, 2006, as of December
13, 2007.
We must receive comments on this AD by December 28, 2007.
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 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:
[[Page 67246]]
Discussion
On October 31, 2006, we issued AD 2006-23-08, Amendment 39-14820
(71 FR 65041, November 7, 2006). That AD required actions intended to
address an unsafe condition on the products listed above. Since we
issued AD 2006-23-08, SMA developed a terminating action for the unsafe
condition. EASA, which is the Technical Agent for the Member States of
the European Community, issued AD 2007-0033, dated February 13, 2007.
That AD supersedes EASA EAD 2006-0312-E, which mandated a temporary
corrective action to the rapid uncontrolled power increase. EASA AD
2007-0033 retains the requirements of EASA AD 2006-0312-E, and also
requires replacing all affected ECUs with a new part number ECU as
terminating action. EASA AD 2007-0033 states:
Over a period of time, the alteration of one electronic control
unit (ECU) electronic component can cause a rapid uncontrolled power
increase. Several occurrences have already been reported during
engine start or during engine warm-up. This condition, if not
corrected, could result in the loss of control of the aircraft if
the pilot fails to react appropriately by switching to the
mechanical backup mode.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
SMA issued SB No. SB-01-76-005, dated December 15, 2006. The
actions described in this service information are intended to correct
the unsafe condition identified in EASA AD 2007-0033.
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 SMA, and determined the unsafe condition exists
and is likely to exist or develop on other products of the same type
design. This AD requires replacing all affected ECUs with a new part
number ECU, as terminating action.
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 short compliance provided to correct the unsafe condition.
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-2006-26102; Directorate
Identifier 2006-NE-36-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://
www.regulations.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, 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]
2. The FAA amends Sec. 39.13 by removing Amendment 39-14820; (71
FR 65041, November 7, 2006) and adding the following new AD:
2007-24-06 Societe de Motorisations Aeronautiques (SMA): Amendment
39-15272; Docket No. FAA-2006-26102; Directorate Identifier 2006-NE-
36-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective December
13, 2007.
Affected ADs
(b) This AD supersedes AD 2006-23-08, Amendment 39-14820.
Applicability
(c) This AD applies to SMA SR305-230 and SR305-230-1 engines
equipped with an electronic control unit (ECU) having one of the
following part numbers (P/Ns): SF01160009-0, SF01160011-0,
SP01160013, SP01160051-0, SP01160051-1, SP01160051-2, SP01160051-3,
SP01160051-4, SP01160051-5, SP01160089-0, SP01160089-1, SP01160089-
2. These engines are installed on, but not limited to, Cessna 182
series airplanes with Supplemental Type Certificate SA03302AT
applied.
Reason
(d) European Aviation Safety Agency (EASA) AD 2007-0033, dated
February 13, 2007, states:
[[Page 67247]]
Over a period of time, the alteration of one electronic control
unit (ECU) electronic component can cause a rapid uncontrolled power
increase. Several occurrences have already been reported during
engine start or during engine warm-up. This condition, if not
corrected, could result in the loss of control of the aircraft if
the pilot fails to react appropriately by switching to the
mechanical backup mode.
We are issuing this AD to prevent a rapid uncontrolled power
increase and possible loss of control of the airplane.
Actions and Compliance
(e) Unless already done, do the following actions:
(1) Before further flight, check if the ECU has a P/N listed in
the Applicability section of this AD and a serial number (SN) of 131
or below, except SNs 70, 71, 83, and 88. If it does, then do not
operate the engine.
(2) Remove and replace the ECU with an ECU P/N SP01160089-3,
using SMA Service Bulletin (SB) No. SB-01-76-005, dated December 15,
2006.
(3) No later than 30 days after the effective date of this AD,
replace all remaining affected P/N ECUs with an ECU P/N SP01160089-
3, using SMA SB No. SB-01-76-005, dated December 15, 2006.
(4) After the effective date of this AD, do not install a spare
ECU having a P/N listed in the Applicability section of this AD as a
replacement part on any SMA SR305-230 or SR305-230-1 engine.
FAA AD Differences
(f) This AD differs from the Mandatory Continuing Airworthiness
Information (MCAI) and/or service information as follows:
(1) EASA AD No. 2007-0033 requires compliance with the AD by
March 31, 2007.
(2) This AD, written later, requires compliance within 30 days
after the effective date of the AD.
Other FAA AD Provisions
(g) Alternative Methods of Compliance: The Manager, Engine
Certification Office, FAA, 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
(h) Refer to EASA AD 2007-0033, dated February 13, 2007, for
related information.
(i) 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
(j) You must use Societe de Motorisations Aeronautiques Service
Bulletin No. SB-01-76-005, dated December 15, 2006, to do the
actions required by this AD, unless the AD specifies otherwise.
(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
Societe de Motorisations Aeronautiques, 10-12 Rue Didier Daurat, F-
18021 Bourges, France--Telephone +33 (0) 2 4867 5600; Fax: +33 (0) 2
4850 0141; e-mail: customer--services@smasr.com.
(3) You may review service information copies at the FAA, New
England Region, 12 New England Executive Park, Burlington, MA 01803;
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, MA, on November 15, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E7-22812 Filed 11-27-07; 8:45 am]
BILLING CODE 4910-13-P