Airworthiness Directives; Cessna Aircraft Company Models 182Q and 182R Airplanes, 67112-67115 [E8-26910]

Download as PDF 67112 Federal Register / Vol. 73, No. 220 / Thursday, November 13, 2008 / Proposed Rules on which Airbus Modifications 8888 and 8889 have not been accomplished. Unsafe Condition (d) This AD results from mandatory continuing airworthiness information originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. We are issuing this AD to detect and correct fatigue cracks and corrosion around and under the chafing plates of the wing root, which could result in reduced structural integrity of the airplane. 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. erowe on PROD1PC64 with PROPOSALS-1 Requirements of AD 2004–14–06 Repetitive Inspections and Corrective Actions (f) Except as provided by paragraphs (g), (k), and (l) of this AD: Within 4 years since date of manufacture, or within 12 months after June 3, 1998 (the effective date of AD 98–09–20, amendment 39–10501), whichever occurs later, perform an inspection to detect discrepancies around and under the chafing plates of the wing root, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310–53–2069, Revision 05, dated November 12, 2002; Revision 04, dated November 8, 2000; Revision 03, dated October 28, 1997; Revision 2, dated September 23, 1996; or Revision 1, dated September 19, 1995. If any discrepancy is found, prior to further flight, accomplish follow-on corrective actions (i.e., removal of corrosion, corrosion protection, high frequency eddy current inspection, x-ray inspection), as applicable, in accordance with the applicable service bulletin. Repeat the inspections thereafter at the intervals specified in the applicable service bulletin. After August 13, 2004 (the effective date of AD 2004–14–06), repeat the inspections thereafter at the intervals specified in Revision 04 or Revision 05 of the service bulletin. (g) If any discrepancy is found during any inspection required by paragraph (f) of this AD, and Airbus Service Bulletin A310–53– 2069, Revision 06, dated May 22, 2007; Revision 05, dated November 12, 2002; Revision 04, dated November 8, 2000; Revision 03, dated October 28, 1997; Revision 2, dated September 23, 1996; or Revision 1, dated September 19, 1995; as applicable; specifies to contact Airbus for appropriate action: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM– 116, FAA, Transport Airplane Directorate. Where differences in the compliance times or corrective actions exist between the service bulletin and this AD, the AD prevails. Optional Terminating Action (h) Except as provided by paragraph (i) of this AD: Accomplishment of the replacement of the stainless steel chafing plates with new chafing plates made of aluminum alloy, in accordance with Airbus Service Bulletin VerDate Aug<31>2005 14:38 Nov 12, 2008 Jkt 217001 A310–53–2070, Revision 2, dated November 8, 2000; Revision 1, dated September 23, 1996; or the original issue, dated October 3, 1994; constitutes terminating action for the repetitive inspections required by paragraph (f) of this AD. Continuation of Repetitive Inspections (i) Except as provided by paragraphs (k) and (l) of this AD: Within 30 days after August 13, 2004, do a review of the airplane maintenance records to determine if any corrosion was detected and reworked on the left and/or right side of frame 39, stringer 35, during the accomplishment of any corrective action or repair specified in paragraphs (f) or (g) of this AD. If any corrective action or repair has been accomplished in this area, perform an inspection for fatigue cracking of frame 39, stringer 35, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310–53–2069, Revision 05, dated November 12, 2002; or Revision 04, dated November 8, 2000. Do the initial inspection at the threshold specified in Figure 1 of the service bulletin, or within 30 days after August 13, 2004, whichever is later. Repeat the inspection thereafter at the intervals specified in Figure 1 of the service bulletin. If any discrepancy is found, prior to further flight, accomplish the applicable follow-on corrective actions, in accordance with the Accomplishment Instructions of the service bulletin. Submission of Information Not Required (j) Although the service bulletins referenced in this AD specify to submit information to the manufacturer, this AD does not include such a requirement. New Actions Required by This AD New Service Bulletin Revision (k) As of the effective date of this AD, use only the Accomplishment Instructions of Airbus Service Bulletin A310–53–2069, Revision 06, dated May 22, 2007, to do the inspections and corrective actions required by paragraphs (f) and (i) of this AD. Repetitive Inspections at Frame FR39, Stringer 35 at Reduced Intervals (l) As of the effective date of this AD, if any corrosion is found at frame FR39, stringer 35, during any inspection required by this AD, do the repetitive inspections required by paragraphs (f) and (i) of this AD, as applicable, at the earlier of the times specified in paragraphs (l)(1) and (l)(2) of this AD. Repeat the inspections thereafter at intervals specified in Figure 1, Sheets 4 and 5, of Airbus Service Bulletin A310–53–2069, Revision 06, dated May 22, 2007, except as provided by paragraph (m) of this AD. (1) At the next specified repeat interval specified in paragraph (f) of this AD. (2) At the later of the times specified in paragraphs (l)(2)(i) and (l)(2)(ii) of this AD, except as provided by paragraph (m) of this AD. (i) At the applicable threshold specified in Figure 1, Sheets 4 and 5, of Airbus Service Bulletin A310–53–2069, Revision 06, dated May 22, 2007. (ii) Within 900 flight cycles or 1,800 flight hours after the effective date of this AD, whichever occurs first. PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 (m) Where Figure 1, Sheets 4 and 5, of Airbus Service Bulletin A310–53–2069, Revision 06, dated May 22, 2007, specifies to contact Airbus, do the inspections at threshold and repeat intervals approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). Alternative Methods of Compliance (AMOCs) (n) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1138; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Related Information (o) European Aviation Safety Agency (EASA) airworthiness directive 2007–0292, dated November 27, 2007, also addresses the subject of this AD. Issued in Renton, Washington, on November 4, 2008. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–26914 Filed 11–12–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1205; Directorate Identifier 2008–CE–062–AD] RIN 2120–AA64 Airworthiness Directives; Cessna Aircraft Company Models 182Q and 182R Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 182Q and 182R airplanes that ´ are equipped with Societe de ´ Motorisations Aeronautiques (SMA) Aircraft Diesel Engine (ADE) Model SR305–230–1 or Model SR305–230 converted to Model SR305–230–1 installed under Supplemental Type E:\FR\FM\13NOP1.SGM 13NOP1 67113 Federal Register / Vol. 73, No. 220 / Thursday, November 13, 2008 / Proposed Rules Certificate (STC) SA03302AT. This proposed AD would require you to remove the intercooler and the intercooler inlet and outlet hoses, install a reworked intercooler and new intercooler inlet and outlet hoses, inspect hoses and clamp torques, and repetitively inspect installation of the intercooler outlet and inlet hose assemblies for any displacement or damage of clamps or hoses, and, if necessary, replace any damaged clamps or hoses. This proposed AD results from a report of two instances of induction hose disconnection occurring while in service, resulting in a loss of turbo boost and a significant loss of engine power. We are proposing this AD to detect and correct improper intercooler outlet and intercooler inlet hose assembly installations, which could result in loss of turbo boost and a significant loss of engine power. This failure could lead to an inability to maintain constant altitude in flight. DATES: We must receive comments on this proposed AD by January 12, 2009. ADDRESSES: Use one of the following addresses to comment on this proposed AD: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • 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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact SMA Customer Service, 10–12 Rue Didier Daurat, 18021 Bourges, France; telephone: +33 (0) 2 48 67 56 00; fax: +33 (0) 2 48 50 01 41; E-mail: customer_services@smasr.com; Web: https://www.smaengines.com. FOR FURTHER INFORMATION CONTACT: Don O. Young, Aerospace Engineer, ACE– 118A, Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix Blvd., Suite 450, Atlanta, Georgia 30349; telephone: (770) 703–6079; fax: (770) 703–6097. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments regarding this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number, ‘‘FAA–2008–1205; Directorate Identifier 2008–CE–062–AD’’ at the beginning 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:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive concerning this proposed AD. Discussion We have received a report of two instances of induction hose disconnection (due to incorrectly installed clamps securing the intercooler outlet and intercooler inlet hose assemblies) occurring while in service on the air inlet manifold circuit of Cessna Models 182Q and 182R airplanes equipped with SMA ADE Model SR305–230–1 or Model SR305– 230 converted to Model SR305–230–1 installed under STC SA03302AT. This induction hose disconnection resulted in a loss of turbo boost and a significant loss of engine power. SMA reports that these hoses and clamps are included in STC SA03302AT. This condition, if not corrected, could result in loss of turbo boost and a significant loss of engine power. This failure could lead to an inability to maintain constant altitude in flight. Relevant Service Information We have reviewed the following service information SMA SAFRAN Group Service Bulletin SB–C182–75– 004, Revision No. Basic Issue, dated July 8, 2008. The service information describes procedures for: • Removal of intercooler SF01170004–0; • Installation of reworked intercooler SF01170004–1; • Removal of intercooler and turbocharger inlet and outlet hoses; • Installation of new intercooler inlet hose SF01170083–0 and intercooler outlet hose SF01170048–0; and • Inspection procedures for installation of the intercooler hose assemblies. FAA’s Determination and Requirements of the Proposed AD We are proposing this AD because we evaluated all information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design. This proposed AD would require you to remove the intercooler and the intercooler inlet and outlet hoses, install a reworked intercooler and new intercooler inlet and outlet hoses, inspect hoses and clamp torques, and repetitively inspect installation of the intercooler outlet and inlet hose assemblies for any displacement or damage of clamps or hoses, and, if necessary, replace any damaged clamps or hoses. Costs of Compliance We estimate that this proposed AD would affect 7 airplanes in the U.S. registry. We estimate the following costs to do the proposed replacements: Parts cost Total cost per airplane Total cost on U.S. operators 4 work-hours × $80 per hour = $320 .......................................................................................... erowe on PROD1PC64 with PROPOSALS-1 Labor cost $3,436 $3,756 $26,292 We estimate the following costs to do any proposed inspection of the installation of the intercooler hose assembly that would be required: Labor cost Parts cost 2 work-hours × $80 per hour = $160 .............................................................................. Not Applicable ............................................ VerDate Aug<31>2005 14:38 Nov 12, 2008 Jkt 217001 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 E:\FR\FM\13NOP1.SGM 13NOP1 Total cost per airplane $160 67114 Federal Register / Vol. 73, No. 220 / Thursday, November 13, 2008 / Proposed Rules We have no way of determining the cost of any necessary replacement that may be required as a result of any proposed inspection. SMA will provide warranty credit as stated in SMA SAFRAN Group Service Bulletin SB–C182–75–004, Revision No. Basic Issue, dated July 8, 2008. 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. 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 proposed AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket that contains the proposed AD, the regulatory evaluation, any comments received, and other information on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5527) is located at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Cessna Aircraft Company: Docket No. FAA– 2008–1205; Directorate Identifier 2008– CE–062–AD. Comments Due Date (a) We must receive comments on this airworthiness directive (AD) action by January 12, 2009. Affected ADs (b) None. Applicability (c) This AD applies to Models 182Q and 182R airplanes, all serial numbers, certificated in any category, that are equipped with: ´ ´ (1) Societe de Motorisations Aeronautiques (SMA) aircraft diesel engine (ADE) Model SR305–230–1 installed under Supplemental Type Certificate (STC) SA03302AT; or (2) SMA ADE Model SR305–230 converted to Model SR305–230–1 (by incorporation of SMA Service Bulletin SB–01–76–002) installed under STC SA03302AT. Unsafe Condition (d) This AD results from a report of two instances of induction hose disconnection occurring while in service on the air inlet manifold circuit, resulting in a loss of turbo boost and a significant loss of engine power. We are issuing this AD to detect and correct improper intercooler hose assembly installation, which could result in loss of turbo boost and a significant loss of engine power. This failure could lead to an inability to maintain constant altitude in flight. Compliance 1. The authority citation for part 39 continues to read as follows: (e) To address this problem, you must do the following, unless already done: Authority: 49 U.S.C. 106(g), 40113, 44701. Compliance Procedures (1) Remove part number (P/N) intercooler SF01170004–0 and install reworked intercooler SF01170004–1 and remove intercooler inlet and outlet hoses and install new intercooler inlet hose SF01170083–0 and intercooler outlet hose SF01170048–0. (2) Inspect intercooler inlet and outlet hoses and clamps for displacement and re-torque clamps. If you find any displacement do the displacement recovery. (3) Inspect the installation of the intercooler outlet hose and intercooler inlet hose assembly for any displacement or damage of clamps or hoses. erowe on PROD1PC64 with PROPOSALS-1 Actions Before further flight as of the effective date of this AD. Follow SMA SAFRAN Group Service Bulletin SB–C182–75–004, Revision No. Basic Issue, dated July 8, 2008. Within the next 25 hours time-in-service (TIS) following installation required by paragraph (e)(1) of this AD. Follow SMA SAFRAN Group Service Bulletin SB–C182–75–004, Revision No. Basic Issue, dated July 8, 2008. Initially inspect within the next 100 hours TIS after the action required by paragraph (e)(1) of this AD or within the next 12 months after the action required by paragraph (e)(1) of this AD, whichever occurs first. Repetitively thereafter inspect at intervals not to exceed 100 hours TIS or 12 months, whichever occurs first. Follow SMA SAFRAN Group Service Bulletin SB–C182–75–004, Revision No. Basic Issue, dated July 8, 2008. VerDate Aug<31>2005 14:38 Nov 12, 2008 Jkt 217001 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 E:\FR\FM\13NOP1.SGM 13NOP1 Federal Register / Vol. 73, No. 220 / Thursday, November 13, 2008 / Proposed Rules 67115 Actions Compliance Procedures (4) If, as a result of any inspection required by paragraph (e)(3) of this AD, you find any displacement or damage of clamps or hoses, replace any damaged clamps and hoses. (5) Do not install any intercooler SF01170004– 0. Before further flight, after the inspection required by paragraph (e)(3) of this AD where you found any displacement or damage of clamps or hoses. As of the effective date of this AD ................... Follow SMA SAFRAN Group Service Bulletin SB–C182–75–004, Revision No. Basic Issue, dated July 8, 2008. Special Flight Permit DEPARTMENT OF TRANSPORTATION (SNPRM; 73 FR 47857, August 15, 2008), the FAA was contacted by members of the industry seeking clarification of our intent and the scope of specific provisions. A summary of that meeting has been placed in the docket for this rule. Issues raised at the meeting caused us to realize that the intent of the rule as stated in the preamble is inconsistent with the proposed rule text. We are restating the intent here and providing revised proposed rule text. While this preamble discussion uses part 121 as its reference, it also applies to parts 125 and 135 and their comparable sections. During our review, we also discovered that the SNPRM change to a separate section (proposed § 121.346) caused us to inadvertently omit an applicability reference for airplanes covered under § 121.344a. We have added that reference as part of this correction. The definition of filtering, proposed § 121.346(a), remains as it was in the SNPRM. Comments should address that section of the proposed rule as published in the SNPRM. Proposed § 121.346(b) now states that any parameter required to be recorded may be filtered as long as the recorded signal value continues to meet the requirements of Appendix M. Paragraph (c) contains a list of parameters that we consider critical from the standpoint of accuracy and accident investigation when complying with the required accuracy under the expanded definition of dynamic conditions in Appendix M. This list has not changed from the SNPRM. If any parameter in the paragraph (c) list is being filtered, and the filtered, recorded data do not meet Appendix M, then the certificate holder must choose one of the following courses of action: • Remove the filtering; or • Demonstrate by test and analysis that the original sensor signal value can be reconstructed from the recorded filtered data. If an operator attempts to show by test and analysis that the data can be reconstructed but the tests and analyses fail, or the results cannot be repeated, the filtering must be removed. The restructured language of the rule text has obviated the need for the second list of parameters. They are (f) Under 14 CFR part 39.23, we are limiting the special flight permits for this AD by the following conditions: (1) Before flight, an inspection of hoses and clamps by a properly certificated mechanic reveals no damaged or disconnected hoses or clamps; and (2) You fly by the most direct route to the site where the AD can be performed. Alternative Methods of Compliance (AMOCs) (g) The Manager, Atlanta Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to Attn: Don O. Young, Aerospace Engineer, ACE–118A, Atlanta ACO, One Crown Center, 1895 Phoenix Blvd., Suite 450, Atlanta, Georgia 30349; telephone: (770) 703–6079; fax: (770) 703–6097. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Related Information (h) To get copies of the service information referenced in this AD, contact SMA Customer Service, 10–12 Rue Didier Daurat, 18021 Bourges, France; telephone: +33 (0) 2 48 67 56 00; fax: +33 (0) 2 48 50 01 41; E-mail: customer_services@smasr.com; Web: https:// www.smaengines.com. To view the AD docket, go to U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12– 140, 1200 New Jersey Avenue, SE., Washington, DC 20590, or on the Internet at https://www.regulations.gov. Issued in Kansas City, Missouri, on November 6, 2008. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–26910 Filed 11–12–08; 8:45 am] erowe on PROD1PC64 with PROPOSALS-1 BILLING CODE 4910–13–P Federal Aviation Administration 14 CFR Parts 121, 125 and 135 [Docket No. FAA–2006–26135; Notice No. 08–08] RIN 2120–AI79 Filtered Flight Data; Technical Correction and Extension of Comment Period Federal Aviation Administration (FAA), DOT. ACTION: Supplemental notice of proposed rulemaking (SNPRM); correction and extension of comment period. AGENCY: SUMMARY: The FAA is correcting an SNPRM published in the Federal Register on August 15, 2008, regarding filtered flight data. Questions from industry caused us to conclude that the intent expressed in the preamble is inconsistent with the proposed rule language. This document will clarify our intent and the rule language. We are also extending the comment period to allow for consideration of this clarification by all interested parties. DATES: The comment period will close December 29, 2008. FOR FURTHER INFORMATION CONTACT: For technical questions concerning this proposed rule contact Brian A. Verna, Avionics Systems Branch, Aircraft Certification Service, AIR–130, Federal Aviation Administration, 800 Independence Avenue, SW., Washington, DC 20591; telephone (202) 385–4643; fax (202) 385–4651; e-mail brian.verna@faa.gov. For legal questions concerning this proposed rule contact Karen L. Petronis, Senior Attorney for Regulations, Regulations Division, Office of the Chief Counsel, AGC–200, Federal Aviation Administration, 800 Independence Avenue, SW., Washington, DC 20591; telephone (202) 267–3073; fax 202–267–7971; e-mail karen.petronis@faa.gov. Background Following the publication of a supplemental notice of proposed rulemaking on filtered flight data VerDate Aug<31>2005 14:38 Nov 12, 2008 Jkt 217001 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 Not Applicable. E:\FR\FM\13NOP1.SGM 13NOP1

Agencies

[Federal Register Volume 73, Number 220 (Thursday, November 13, 2008)]
[Proposed Rules]
[Pages 67112-67115]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-26910]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1205; Directorate Identifier 2008-CE-062-AD]
RIN 2120-AA64

Airworthiness Directives; Cessna Aircraft Company Models 182Q and
182R Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Cessna Aircraft Company (Cessna) Models 182Q and 182R airplanes
that are equipped with Societ[eacute] de Motorisations
A[eacute]ronautiques (SMA) Aircraft Diesel Engine (ADE) Model SR305-
230-1 or Model SR305-230 converted to Model SR305-230-1 installed under
Supplemental Type

[[Page 67113]]

Certificate (STC) SA03302AT. This proposed AD would require you to
remove the intercooler and the intercooler inlet and outlet hoses,
install a reworked intercooler and new intercooler inlet and outlet
hoses, inspect hoses and clamp torques, and repetitively inspect
installation of the intercooler outlet and inlet hose assemblies for
any displacement or damage of clamps or hoses, and, if necessary,
replace any damaged clamps or hoses. This proposed AD results from a
report of two instances of induction hose disconnection occurring while
in service, resulting in a loss of turbo boost and a significant loss
of engine power. We are proposing this AD to detect and correct
improper intercooler outlet and intercooler inlet hose assembly
installations, which could result in loss of turbo boost and a
significant loss of engine power. This failure could lead to an
inability to maintain constant altitude in flight.

DATES: We must receive comments on this proposed AD by January 12,
2009.

ADDRESSES: Use one of the following addresses to comment on this
proposed AD:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact SMA
Customer Service, 10-12 Rue Didier Daurat, 18021 Bourges, France;
telephone: +33 (0) 2 48 67 56 00; fax: +33 (0) 2 48 50 01 41; E-mail:
customer_services@smasr.com; Web: https://www.smaengines.com.

FOR FURTHER INFORMATION CONTACT: Don O. Young, Aerospace Engineer, ACE-
118A, Atlanta Aircraft Certification Office, One Crown Center, 1895
Phoenix Blvd., Suite 450, Atlanta, Georgia 30349; telephone: (770) 703-
6079; fax: (770) 703-6097.

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to send any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include the docket number, ``FAA-
2008-1205; Directorate Identifier 2008-CE-062-AD'' at the beginning 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://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive concerning this proposed AD.

Discussion

We have received a report of two instances of induction hose
disconnection (due to incorrectly installed clamps securing the
intercooler outlet and intercooler inlet hose assemblies) occurring
while in service on the air inlet manifold circuit of Cessna Models
182Q and 182R airplanes equipped with SMA ADE Model SR305-230-1 or
Model SR305-230 converted to Model SR305-230-1 installed under STC
SA03302AT. This induction hose disconnection resulted in a loss of
turbo boost and a significant loss of engine power.
SMA reports that these hoses and clamps are included in STC
SA03302AT.
This condition, if not corrected, could result in loss of turbo
boost and a significant loss of engine power. This failure could lead
to an inability to maintain constant altitude in flight.

Relevant Service Information

We have reviewed the following service information SMA SAFRAN Group
Service Bulletin SB-C182-75-004, Revision No. Basic Issue, dated July
8, 2008.
The service information describes procedures for:
Removal of intercooler SF01170004-0;
Installation of reworked intercooler SF01170004-1;
Removal of intercooler and turbocharger inlet and outlet
hoses;
Installation of new intercooler inlet hose SF01170083-0
and intercooler outlet hose SF01170048-0; and
Inspection procedures for installation of the intercooler
hose assemblies.

FAA's Determination and Requirements of the Proposed AD

We are proposing this AD because we evaluated all information and
determined the unsafe condition described previously is likely to exist
or develop on other products of the same type design. This proposed AD
would require you to remove the intercooler and the intercooler inlet
and outlet hoses, install a reworked intercooler and new intercooler
inlet and outlet hoses, inspect hoses and clamp torques, and
repetitively inspect installation of the intercooler outlet and inlet
hose assemblies for any displacement or damage of clamps or hoses, and,
if necessary, replace any damaged clamps or hoses.

Costs of Compliance

We estimate that this proposed AD would affect 7 airplanes in the
U.S. registry.
We estimate the following costs to do the proposed replacements:

----------------------------------------------------------------------------------------------------------------
Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
----------------------------------------------------------------------------------------------------------------
4 work-hours x $80 per hour = $320........................... $3,436 $3,756 $26,292
----------------------------------------------------------------------------------------------------------------

We estimate the following costs to do any proposed inspection of
the installation of the intercooler hose assembly that would be
required:

------------------------------------------------------------------------
Total cost
Labor cost Parts cost per
airplane
------------------------------------------------------------------------
2 work-hours x $80 per hour = $160. Not Applicable........ $160
------------------------------------------------------------------------

[[Page 67114]]

We have no way of determining the cost of any necessary replacement
that may be required as a result of any proposed inspection.
SMA will provide warranty credit as stated in SMA SAFRAN Group
Service Bulletin SB-C182-75-004, Revision No. Basic Issue, dated July
8, 2008.

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. 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 proposed AD and placed it in the AD docket.

Examining the AD Docket

You may examine the AD docket that contains the proposed AD, the
regulatory evaluation, any comments received, and other information on
the Internet at https://www.regulations.gov; or in person at the Docket
Management Facility between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Office (telephone (800) 647-5527)
is located at the street address stated in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

The Proposed Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA 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 AD:

Cessna Aircraft Company: Docket No. FAA-2008-1205; Directorate
Identifier 2008-CE-062-AD.

Comments Due Date

(a) We must receive comments on this airworthiness directive
(AD) action by January 12, 2009.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Models 182Q and 182R airplanes, all
serial numbers, certificated in any category, that are equipped
with:
(1) Societ[eacute] de Motorisations A[eacute]ronautiques (SMA)
aircraft diesel engine (ADE) Model SR305-230-1 installed under
Supplemental Type Certificate (STC) SA03302AT; or
(2) SMA ADE Model SR305-230 converted to Model SR305-230-1 (by
incorporation of SMA Service Bulletin SB-01-76-002) installed under
STC SA03302AT.

Unsafe Condition

(d) This AD results from a report of two instances of induction
hose disconnection occurring while in service on the air inlet
manifold circuit, resulting in a loss of turbo boost and a
significant loss of engine power. We are issuing this AD to detect
and correct improper intercooler hose assembly installation, which
could result in loss of turbo boost and a significant loss of engine
power. This failure could lead to an inability to maintain constant
altitude in flight.

Compliance

(e) To address this problem, you must do the following, unless
already done:

------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Remove part number (P/N) Before further Follow SMA SAFRAN
intercooler SF01170004-0 and flight as of the Group Service
install reworked intercooler effective date of Bulletin SB-C182-
SF01170004-1 and remove this AD. 75-004, Revision
intercooler inlet and outlet No. Basic Issue,
hoses and install new dated July 8,
intercooler inlet hose 2008.
SF01170083-0 and intercooler
outlet hose SF01170048-0.
(2) Inspect intercooler inlet Within the next 25 Follow SMA SAFRAN
and outlet hoses and clamps for hours time-in- Group Service
displacement and re-torque service (TIS) Bulletin SB-C182-
clamps. If you find any following 75-004, Revision
displacement do the installation No. Basic Issue,
displacement recovery. required by dated July 8,
paragraph (e)(1) 2008.
of this AD.
(3) Inspect the installation of Initially inspect Follow SMA SAFRAN
the intercooler outlet hose and within the next Group Service
intercooler inlet hose assembly 100 hours TIS Bulletin SB-C182-
for any displacement or damage after the action 75-004, Revision
of clamps or hoses. required by No. Basic Issue,
paragraph (e)(1) dated July 8,
of this AD or 2008.
within the next
12 months after
the action
required by
paragraph (e)(1)
of this AD,
whichever occurs
first.
Repetitively
thereafter
inspect at
intervals not to
exceed 100 hours
TIS or 12 months,
whichever occurs
first.

[[Page 67115]]

(4) If, as a result of any Before further Follow SMA SAFRAN
inspection required by flight, after the Group Service
paragraph (e)(3) of this AD, inspection Bulletin SB-C182-
you find any displacement or required by 75-004, Revision
damage of clamps or hoses, paragraph (e)(3) No. Basic Issue,
replace any damaged clamps and of this AD where dated July 8,
hoses. you found any 2008.
displacement or
damage of clamps
or hoses.
(5) Do not install any As of the Not Applicable.
intercooler SF01170004-0. effective date of
this AD.
------------------------------------------------------------------------

Special Flight Permit

(f) Under 14 CFR part 39.23, we are limiting the special flight
permits for this AD by the following conditions:
(1) Before flight, an inspection of hoses and clamps by a
properly certificated mechanic reveals no damaged or disconnected
hoses or clamps; and
(2) You fly by the most direct route to the site where the AD
can be performed.

Alternative Methods of Compliance (AMOCs)

(g) The Manager, Atlanta Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. Send information to
Attn: Don O. Young, Aerospace Engineer, ACE-118A, Atlanta ACO, One
Crown Center, 1895 Phoenix Blvd., Suite 450, Atlanta, Georgia 30349;
telephone: (770) 703-6079; fax: (770) 703-6097. Before using any
approved AMOC on any airplane to which the AMOC applies, notify your
appropriate principal inspector (PI) in the FAA Flight Standards
District Office (FSDO), or lacking a PI, your local FSDO.

Related Information

(h) To get copies of the service information referenced in this
AD, contact SMA Customer Service, 10-12 Rue Didier Daurat, 18021
Bourges, France; telephone: +33 (0) 2 48 67 56 00; fax: +33 (0) 2 48
50 01 41; E-mail: customer_services@smasr.com; Web: https://
www.smaengines.com. To view the AD docket, go to U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590, or
on the Internet at https://www.regulations.gov.

Issued in Kansas City, Missouri, on November 6, 2008.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.

[FR Doc. E8-26910 Filed 11-12-08; 8:45 am]
BILLING CODE 4910-13-P

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