Document ID: FAA-2007-0004-0053
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Societe de Motorisations Aeronautiques (SMA) SR305-230 and SR305-230-1 Reciprocating Engines
Posted Date: 2007-09-21T04:00Z

[Federal Register: September 21, 2007 (Volume 72, Number 183)]
[Rules and Regulations]               
[Page 53935-53937]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr21se07-11]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28365; Directorate Identifier 2007-NE-26-AD; 
Amendment 39-15185; AD 2007-18-05]
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.

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SUMMARY: We are adopting a new airworthiness directive (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 SMA SR305-230 and 
SR305-230-1 reciprocating engines. The MCAI states the following:

    Several occurrences of cracks on the exhaust collector assembly 
have been reported in service. Failure of the engine primary exhaust 
can lead to a loss of engine manifold pressure and may result in a 
loss of engine power. In some recent occurrences, cracking has 
appeared near the weld of the Turbine Inlet Temperature (TIT) probe 
support. This eventually led to an open hole in the exhaust 
collector assembly. The resulting loss of engine power was not 
compatible with the continuation of the flight and an immediate 
landing was necessary.

We are issuing this AD to prevent failure of the engine primary 
exhaust, which could result in loss of engine power and inability to 
maintain safe flight.

DATES: This AD becomes effective October 9, 2007.
    We must receive comments on this AD by October 22, 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 & 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 EASA 
Airworthiness Directive 2007-0127, dated May 7, 2007, to correct an 
unsafe condition for the specified products. The EASA AD states:

    Several occurrences of cracks on the exhaust collector assembly 
have been reported in service. Failure of the engine primary exhaust 
can lead to a loss of engine manifold pressure and may result in a 
loss of engine power. In some recent occurrences, cracking has 
appeared near the weld of the Turbine Inlet Temperature (TIT) probe 
support. This eventually led to an open hole in the exhaust 
collector assembly. The resulting loss of engine power was not 
compatible with the continuation of the flight and an immediate 
landing was necessary.

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

[[Page 53936]]

Relevant Service Information

    SMA has issued Service Bulletin SB-01-78-001, dated March 27, 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 above. We are issuing this AD because we evaluated 
all the information provided by the Direction Generale De L'Aviation 
Civile, which is the airworthiness authority for France, and determined 
the unsafe condition exists and is likely to exist or develop on other 
products of the same type design.

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 
compliance times do not afford opportunity to gather public comment. 
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-2007-28365; Directorate 
Identifier 2007-NE-26-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 adding the following new AD:

2007-18-05 Societe de Motorisations Aeronautiques: Amendment 39-
15185. Docket No. FAA-2007-28365; Directorate Identifier 2007-NE-26-
AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective October 
9, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Societe de Motorisations Aeronautiques 
(SMA) SR305-230 and SR305-230-1 reciprocating engines with exhaust 
collector assembly part number (P/N) SF01080014-0. These engines are 
installed on, but not limited to, Cessna 182 series airplanes 
modified to supplemental type certificate AS03302AT.

Reason

    (d) Several occurrences of cracks on the exhaust collector 
assembly have been reported in service. Failure of the engine 
primary exhaust can lead to a loss of engine manifold pressure and 
may result in a loss of engine power. In some recent occurrences, 
cracking has appeared near the weld of the Turbine Inlet Temperature 
(TIT) probe support. This eventually led to an open hole in the 
exhaust collector assembly. The resulting loss of engine power was 
not compatible with the continuation of the flight and an immediate 
landing was necessary.
    We are issuing this AD to prevent failure of the engine primary 
exhaust, which could result in loss of engine power and inability to 
maintain safe flight.

Actions and Compliance

Initial Inspection

    (e) Unless already done, do the following actions.
    (1) Within 30 hours time-since-new (TSN), visually inspect the 
exhaust collector assembly, P/N SF01080014-0 in the area of the TIT 
probe mount weld for cracks.
    (2) Before further flight, replace exhaust collector assemblies 
found cracked with a serviceable part.

Repetitive Inspections

    (3) Within 10 hours time-since-last inspection (TSLI), repeat 
the actions specified in paragraph (e)(1) and (e)(2) of this AD.

Replace Exhaust Collector Assembly

    (4) Within 50 hours TSN, replace the exhaust collector assembly 
with a serviceable part.

Continuing Action

    (5) Continue to inspect and replace exhaust collector assemblies 
as specified in paragraphs (e)(1) through (e)(4) of this AD.

Definitions

    (6) For the purpose of this AD, a serviceable exhaust collector 
assembly is a new exhaust collector assembly, or an

[[Page 53937]]

exhaust collector assembly with fewer than 50 operating hours and no 
cracks.

FAA AD Differences

    (f) This AD differs from the Mandatory Continuing Airworthiness 
Information (MCAI) and/or service information as follows:
    (1) We require the initial inspection within 30 hours TSN 
instead of at 30 hours TSN.
    (2) We require the repetitive inspections within 10 hours TSLI 
instead of at 40 hours TSN.
    (3) We define a serviceable part.

Other FAA AD Provisions

    (g) 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.
    (h) Special Flight Permits: We will allow a special flight 
permit to comply with paragraph (e)(4) of this AD.

Related Information

    (i) Refer to MCAI EASA Airworthiness Directive 2007-0127, dated 
May 7, 2007, and SMA Service Bulletin SB-01-78-78-001, dated March 
27, 2007, for related information.
    (j) Contact Christopher Spinney, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & 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

    (k) None.

    Issued in Burlington, Massachusetts, on September 11, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. E7-18412 Filed 9-20-07; 8:45 am]

BILLING CODE 4910-13-P