Airworthiness Directives; Societe de Motorisations Aeronautiques (SMA) SR305-230 and SR305-230-1 Reciprocating Engines, 67245-67247 [E7-22812]

Download as PDF Federal Register / Vol. 72, No. 228 / Wednesday, November 28, 2007 / Rules and Regulations 67245 TABLE 1.—SBS ALLOWING PREVIOUS CREDIT—Continued (5) Engine—Accessory Gearbox Starter Pad Drain—Install the Open Starter Drain Adapter (23077526 or 23083403); RRC SB No. AE 3007C–72–223, dated January 19, 2006. Alternative Methods of Compliance (AMOC) (k) The Manager, Chicago Aircraft Certification Office, has the authority to approve AMOCs for this AD if requested using the procedures found in 14 CFR 39.19. (l) AMOCs currently approved for AD 99– 02–51 will remain in effect until the terminating action date for this AD, September 30, 2009. After that date, these AMOCs will expire and will not be approved as AMOCs for this AD. Office, Small Airplane Directorate, FAA, 2300 E. Devon Ave., Des Plaines, IL 60018; e-mail: kyri.zaroyiannis@faa.gov; telephone (847) 294–7836; fax (847) 294–7834, for more information about this AD. Material Incorporated by Reference (n) You must use the service information specified in Table 2 to perform the actions required by this AD. The Director of the Federal Register approved the incorporation by reference of the documents listed in Table 2 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact RollsRoyce Corporation, P.O. Box 420, Related Information (m) Contact Kyri Zaroyiannis, Aerospace Engineer, Chicago Aircraft Certification Indianapolis, IN 46206; telephone (317) 230– 3774; fax (317) 230–8084; e-mail: indy.pubs.services@rolls-royce.com, for a copy of this service information. You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; 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. TABLE 2.—INCORPORATION BY REFERENCE Service Bulletin No. Page AE 3007A–72–274 ............................................................................................... Total Pages—6 AE 3007A–72–321, AE 3007C–72–250 .............................................................. Total Pages—13 AE 3007A–72–330 ............................................................................................... Total Pages—6 AE 3007C–72–223 .............................................................................................. Total Pages—7 ALL ............................ 1 November 12, 2007. ALL ............................ 2 November 12, 2007. ALL ............................ 1 November 12, 2007. ALL ............................ 1 November 12, 2007. Issued in Burlington, Massachusetts, on November 14, 2007. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–22810 Filed 11–27–07; 8:45 am] BILLING CODE 4910–13–P 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 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. ebenthall on PRODPC61 with RULES AGENCY: SUMMARY: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing VerDate Aug<31>2005 17:13 Nov 27, 2007 Jkt 214001 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. PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 Revision Date • 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: E:\FR\FM\28NOR1.SGM 28NOR1 67246 Federal Register / Vol. 72, No. 228 / Wednesday, November 28, 2007 / Rules and Regulations 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. ebenthall on PRODPC61 with RULES 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 VerDate Aug<31>2005 17:13 Nov 27, 2007 Jkt 214001 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 PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 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 Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 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: E:\FR\FM\28NOR1.SGM 28NOR1 Federal Register / Vol. 72, No. 228 / Wednesday, November 28, 2007 / Rules and Regulations 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. ebenthall on PRODPC61 with RULES 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. VerDate Aug<31>2005 15:16 Nov 27, 2007 Jkt 214001 (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 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28987; Directorate Identifier 2007–NM–127–AD; Amendment 39–15269; AD 2007–24–03] RIN 2120–AA64 Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB–135ER, –135KE, –135KL, and –135LR Airplanes and Model EMB–145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: It has been found the development of cracks in the forward fuselage right hand (RH) side skin during full-scale fatigue tests. Those cracks may quickly reach their critical length, reducing the aircraft structural integrity, with possible rapid decompression of the aircraft. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective January 2, 2008. PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 67247 The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 2, 2008. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on August 16, 2007 (72 FR 45963). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: It has been found the development of cracks in the forward fuselage right hand (RH) side skin during full-scale fatigue tests. Those cracks may quickly reach their critical length, reducing the aircraft structural integrity, with possible rapid decompression of the aircraft. The corrective action includes rework of the aircraft structure on the forward fuselage LH (left-hand) and RH sides. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information EMBRAER has issued Service Bulletin 145–53–0067, Revision 02, dated August 28, 2007. We referred to EMBRAER Service Bulletin 145–53– 0067, Revision 01, dated February 27, 2007, as the appropriate source of service information for doing the actions specified in the NPRM. The procedures in Revision 02 of the service bulletin are essentially the same as those procedures in Revision 01. Revision 02 revises the illustrations and makes editorial changes. We have revised paragraph (f)(1) and Table 1 of this AD to also refer to Revision 02 of the service bulletin. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. Request To Extend Grace Period American Eagle Airlines requests that we extend the grace period specified in E:\FR\FM\28NOR1.SGM 28NOR1

Agencies

[Federal Register Volume 72, Number 228 (Wednesday, November 28, 2007)]
[Rules and Regulations]
[Pages 67245-67247]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-22812]


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

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