Airworthiness Directives; Piper Aircraft, Inc. (Type Certificate Previously Held by The New Piper Aircraft, Inc.) Models PA-46-310P, PA-46-350P, and PA-46R-350T Airplanes, 82329-82333 [2010-32959]

Download as PDF Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Proposed Rules the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. Related Information (i) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2010–0031, dated March 3, 2010; and Dassault Mandatory Service Bulletin 7X–065, dated July 24, 2009; for related information. Issued in Renton, Washington, on December 17, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–32999 Filed 12–29–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–1295; Directorate Identifier 2010–CE–060–AD] RIN 2120–AA64 Airworthiness Directives; Piper Aircraft, Inc. (Type Certificate Previously Held by The New Piper Aircraft, Inc.) Models PA–46–310P, PA– 46–350P, and PA–46R–350T Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede an existing airworthiness directive (AD) that applies to certain Piper Aircraft, Inc. Models PA–46–310P and PA–46– 350P airplanes that are equipped with a Lewis or Transicoil turbine inlet temperature (T.I.T.) gauge and associated probe. The existing AD currently requires calibrating the T.I.T. system; replacing any T.I.T. system that fails the calibration test; repetitively replacing the T.I.T. probe on certain Model PA–46–350P airplanes; and inserting a copy of the AD into the pilot’s operating handbook (POH) for certain airplanes. Since we issued that AD, the manufacturer has revised related service information and added srobinson on DSKHWCL6B1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 17:52 Dec 29, 2010 Jkt 223001 an airplane model to the list of affected airplanes. This proposed AD would retain the actions required by AD 99– 15–04 R1, add certain Model PA–46R– 350T airplanes to the Applicability section, expand the applicability to include other T.I.T. systems, and incorporate new service information. We are proposing this AD to prevent improper engine operation caused by improperly calibrated T.I.T. indicators or defective T.I.T. probes, which could result in engine damage/failure with consequent loss of control of the airplane. DATES: We must receive comments on this proposed AD by February 14, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida 32960; telephone: (772) 567–4361; fax: (772) 978–6573; Internet: http:// www.newpiper.com/company/ publications.asp. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust St., Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. Examining the AD Docket You may examine the AD docket on the Internet at http:// 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 AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Darby Mirocha, Aerospace Engineer, FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park, Georgia 30337; phone: (404) 474– 5573; fax: (404) 474–5605; e-mail: darby.mirocha@faa.gov. PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 82329 SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2010–1295; Directorate Identifier 2010–CE–060–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed 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 proposed AD. Discussion On May 17, 2000, we issued AD 99– 15–04 R1, Amendment 39–11747 (65 FR 33745, May 25, 2000), for certain Piper Aircraft, Inc. (type certificate previously held by The New Piper Aircraft, Inc.) Models PA–46–310P and PA–46–350P airplanes that are equipped with a Lewis or Transicoil turbine inlet temperature (T.I.T.) gauge and associated probe. That AD required calibrating the T.I.T. system; replacing any T.I.T. system that fails the calibration test; repetitively replacing the T.I.T. probe on Model PA–46–350P airplanes; and inserting a copy of the AD into the Emergency Procedures section of the POH for certain airplanes. That AD resulted from field reports that indicated service accuracy problems with the existing T.I.T. system on certain Piper Aircraft, Inc. Models PA– 46–310P and PA–46–350P. We issued that AD to prevent improper engine operation caused by improperly calibrated T.I.T. indicators or defective T.I.T. probes, which could result in engine damage/failure with consequent loss of control of the airplane. Actions Since Existing AD Was Issued Since we issued AD 99–15–04 R1, the manufacturer has revised related service information and has added an airplane model to the list of affected airplanes. We have also determined that the scope of this proposed AD goes beyond only airplanes equipped with Lewis or Transicoil gauges and/or probes. Relevant Service Information We reviewed Piper Aircraft, Inc. Service Bulletin No. 995C, dated E:\FR\FM\30DEP1.SGM 30DEP1 82330 Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Proposed Rules develop in other products of the same type design. November 17, 2009. The service information describes procedures for calibrating the T.I.T. system and replacing the probe. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or systems, and incorporate new service information. Proposed AD Requirements This proposed AD would retain the requirements of AD 99–15–04 R1. This proposed AD would also add certain Model PA–46R–350T airplanes to the Applicability section, expand the applicability to include other T.I.T. Costs of Compliance We estimate that this proposed AD affects 898 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Clean and inspect the turbine inlet temperature gauge and probe for certain Models PA–46–310P and PA–46– 350P airplanes. Calibrate the turbine inlet temperature gauge for certain Models PA–46–310P and PA–46–350P airplanes. Incorporate emergency procedures into POH. Cost per product Parts cost Cost on U.S. operators 1 work-hour × $85 per hour = $85. Not applicable ......... $85 $85 × 780 affected airplanes = $66,300. 4 work-hours × $85 per hour = $340. Not applicable ......... 340 $340 × 427 $145,180. 1 workhour × $85 per hour = $85. Not applicable ......... 85 The requirements of this proposed AD add no additional economic burden other than the addition of an airplane model to the Applicability section. We estimate the following costs to do any necessary replacements that would be required based on the results of the proposed inspection. We have no way of affected airplanes = $85 × 898 affected airplanes = $76,330. determining the number of aircraft that might need these replacements: ON-CONDITION COSTS Labor cost Replace probe ........................................................................................... srobinson on DSKHWCL6B1PROD with PROPOSALS Action 1 work-hour × $85 per hour = $85. 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. 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), (3) Will not affect intrastate aviation in Alaska, and (4) 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. Regulatory Findings The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not VerDate Mar<15>2010 17:52 Dec 29, 2010 Jkt 223001 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 Parts cost $384 Cost per product $469 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 99–15–04 R1, Amendment 39–11747 (65 FR 33745, May 25, 2000), and adding the following new AD: Piper Aircraft, Inc. (Type Certificate Previously Held by The New Piper Aircraft, Inc.): Docket No. FAA–2010– 1295; Directorate Identifier 2010–CE– 060–AD. Comments Due Date (a) The FAA must receive comments on this AD action by February 14, 2011. Affected ADs (b) This AD supersedes AD 99–15–04 R1, Amendment 39–11747. Applicability (c) This AD applies to the following Piper Aircraft, Inc. (type certificate previously held by The New Piper Aircraft, Inc.) Models PA– E:\FR\FM\30DEP1.SGM 30DEP1 82331 Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Proposed Rules 46–310P, PA–46–350P, and PA–46R–350T airplanes that: (1) Are certificated in any category; and (2) Equipped with a turbine inlet temperature (T.I.T.) system identified in table 1 of this AD. Relief from this AD is available only if the gauge and probe are replaced through STC and not if a second turbine inlet temperature gauge was installed while retaining the Lewis or Transicoil T.I.T. gauge and probe. GROUP 1—AIRPLANES PREVIOUSLY AFFECTED BY AD 99–15–04 R1 Models PA–46–310P (Malibu). PA–46–350P (Malibu Mirage). Serial Numbers (S/N) 46–8408001 through 46– 8608067 and 4608001 through 4608140. 4622001 through 4622200 and 4636001 through 4636020. GROUP 2—AIRPLANES NOT VIOUSLY AFFECTED BY AD PRE99–15– 04 R1 Models PA–46–350P (Malibu Mirage). PA–46R–350T (Matrix). Serial Numbers (S/N) 4636021 and subsequent. 4692001 and subsequent. TABLE 1—AFFECTED AIRPLANE MODELS AND CORRESPONDING AFFECTED LEWIS OR TRANSICOIL PART NUMBERS (P/NS) Models S/N Indication System P/N Probe P/N PA–46–310P ............... Lewis T.I.T. analog indicators P/N 471–008 .. 471–009 or 481–387. PA–46–350P ............... 46–8408001 through 46–8608067 and 4608001 through 4608140. 4622001 through 4622200 and 4636001 through 4636020. Lewis T.I.T. analog indicators P/N 471–008 .. PA–46–350P ............... 4636021 through 4636374 .............................. Lewis T.I.T. digital indicators P/N 548–811 .... PA–46–350P ............... 4636375 and subsequent ............................... PA–46R–350T ............. 4692001 and subsequent ............................... Avidyne Entegra or other Electronic Flight Information System (EFIS) display. Avidyne Entegra or other EFIS display .......... 481–389 or 481–392 or 686–216 (preferred). 481–389 or 481–392 or 686–216 (preferred). 686–216. Subject (d) Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 77, Engine Indicating. Unsafe Condition (e) This AD was prompted by field reports that indicated service accuracy problems with the existing turbine inlet temperature system on certain Models PA–46–310P, PA– 46–350P, and PA–46R–350T airplanes. We are issuing this AD to prevent improper engine operation caused by improperly calibrated turbine inlet temperature indicators or defective turbine inlet temperature probes, which could result in 686–216. engine damage/failure with consequent loss of control of the airplane. Compliance (f) For Group 1 airplanes: Comply with this AD within the compliance times specified, unless already done. TABLE 2—GROUP 1 AIRPLANES [Airplanes previously affected by AD 99–15–04 R1] Compliance Procedures (1) Clean and inspect the turbine inlet temperature gauge and probe. Within the next 100 hours time-inservice (TIS) after August 31, 1999 (the effective date retained from AD 99–15–04). (2) Calibrate the turbine inlet temperature system. srobinson on DSKHWCL6B1PROD with PROPOSALS Actions Within the next 100 hours TIS after August 31, 1999 (the effective date retained from AD 99– 15–04). (3) If the turbine inlet temperature probe fails the inspection required in paragraph (f)(1) of this AD and/or the turbine inlet temperature system indicator cannot be calibrated as required in paragraph (f)(2) of this AD, replace any failed parts with a serviceable part listed in table 1 of this AD as long as it has been inspected and properly calibrated. Before further flight after the cleaning and inspection required in paragraph (f)(1) and the calibration required in paragraph (f)(2) of this AD. Follow Piper Airplane Maintenance Manual PA–46–310P/PA–46–350P Part Number 761–783, Chapter 77–20– 00, section A.(1)(d), pages 1 and 2; and Piper Airplane Maintenance Manual PA–46–350P Part Number 761–876, Chapter 77– 20–00, section 1.C, pages 1 and 2, as applicable. Follow Piper Airplane Maintenance Manual PA–46–310P/PA–46–350P Part Number 761–783, Chapter 77–20– 00, section A.(1)(g), pages 3 and 4; and Piper Airplane Maintenance Manual PA–46–350P Part Number 761–876, Chapter 77– 20–00, section 1.F, pages 2 through 4, as applicable; or Piper Service Bulletin No. 995C, dated November 17, 2009. Follow Piper Airplane Maintenance Manual PA–46–310P/PA–46–350P Part Number 761–783, Chapter 77–20– 00, section A.(1)(f), page 2; and Piper Airplane Maintenance Manual PA–46–350P Part Number 761–876, Chapter 77–20–00, section 1.E., page 2, as applicable; or Piper Service Bulletin No. 995C, dated November 17, 2009. VerDate Mar<15>2010 17:52 Dec 29, 2010 Jkt 223001 PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 E:\FR\FM\30DEP1.SGM 30DEP1 82332 Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Proposed Rules TABLE 2—GROUP 1 AIRPLANES—Continued [Airplanes previously affected by AD 99–15–04 R1] Actions Compliance Procedures (4) Incorporate the information from Appendix 1 and Appendix 2, as applicable, of this AD into the Emergency Procedures section of the pilot operating handbook (POH). This may be done by inserting a copy of this AD into the POH. (5) Only install a part listed in table 1 of this AD after it has been inspected and properly calibrated. (6) Model PA–46–350P airplanes only: Replace the turbine inlet temperature probe with a new part number 481–389, 481–392, or 686–216 probe preferred). This action is not required for Model PA–46–310P. Within the next 100 hours TIS after August 31, 1999 (the effective date retained from AD 99– 15–04). Not applicable. As of July 28, 2000 (the effective date of AD 99–15–04 R1). Not applicable. Upon accumulating 250 hours TIS on the currently installed turbine inlet temperature probe or within the next 100 hours TIS after August 31, 1999 (the effective date retained from AD 99–15–04), whichever occurs later, and thereafter at intervals not to exceed 250 hours TIS. For serial numbers 4622001 through 4622200: Follow Piper Airplane Maintenance Manual PA–46–310P/PA–46–350P Part Number 761–783, Chapter 77–20–00, section A.(1)(f), page 2; or Piper Service Bulletin No. 995C, dated November 17, 2009. For serial numbers 4636001 through 4636020: Follow Piper Airplane Maintenance Manual PA–46–350P Part Number 761–876, Chapter 77–20–00, section 1.E., page 2: or Piper Service Bulletin No. 995C, dated November 17, 2009. (g) For Group 2 airplanes: Comply with this AD within the compliance times specified, unless already done. TABLE 3—GROUP 2 AIRPLANES [Airplanes not previously affected by AD 99–15–04 R1] Compliance Procedures (1) Model PA–46–350P airplanes, S/Ns 4636021 through 4636374 only: Clean and inspect the turbine inlet temperature gauge and probe. (2) Model PA–46–350P airplanes, S/Ns 4636021 through 4636374 only: If the turbine inlet temperature probe fails the inspection required in paragraph (g)(1) of this AD and/or the turbine inlet temperature system indicator cannot be calibrated as required in paragraph (g)(2) of this AD, replace any failed parts with a serviceable part listed in table 1 of this AD as long as it has been inspected and properly calibrated. (3) All Group 2 airplanes: Replace the turbine inlet temperature probe with a new part number 686–216 probe. srobinson on DSKHWCL6B1PROD with PROPOSALS Actions Within the next 100 hours TIS after the effective date of this AD. Follow Piper Airplane Maintenance Manual PA–46–350P Part Number 761–876, Chapter 77–20–00, section 1.C, pages 1 and 2, as applicable. Follow Piper Service Bulletin No. 995C, dated November 17, 2009. (4) All Group 2 airplanes: Incorporate the information from Appendix 2 of this AD into the Emergency Procedures section of the POH. This may be done by inserting a copy of this AD into the POH. (5) All Group 2 airplanes: Only install a part listed in table 1 of this AD after it has been inspected and properly calibrated. VerDate Mar<15>2010 17:52 Dec 29, 2010 Jkt 223001 Before further flight after the cleaning and inspection required in paragraph (g)(1) and the calibration required in paragraph (g)(2) of this AD. Upon accumulating 250 hours TIS on the currently installed turbine inlet temperature probe or within the next 100 hours TIS after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 250 hours TIS. Within the next 100 hours TIS after the effective date of this AD. Piper Service Bulletin No. 995C, dated November 17, 2009. As of the effective date of this AD ................... Not applicable. PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 Not applicable. E:\FR\FM\30DEP1.SGM 30DEP1 Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Proposed Rules Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, Atlanta Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. (2) Before using any approved AMOC, notify your Principal Maintenance Inspector or Principal Avionics Inspector, as appropriate, or lacking a principal inspector, your local Flight Standards District Office. (3) AMOCs approved for AD 99–15–04 R1 are approved as AMOCs for this AD. Related Information (i) For more information about this AD, contact Darby Mirocha, Aerospace Engineer, FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park, Georgia 30337; phone: (404) 474–5573; fax: (404) 474–5605; e-mail: darby.mirocha@faa.gov. (j) For service information identified in this AD, contact Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida 32960; telephone: (772) 567–4361; fax: (772) 978–6573; Internet: http://www.piper.com/home/pages/ publications.cfm. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust St., Kansas City, MO 64106. For information on the availability of this material at the FAA, call (816) 329–4148. Appendix 1 to Docket No. FAA–2010–1295 Model PA–46–310P (Mailbu)—Emergency Procedures for the Pilot’s Operating Handbook (POH) (1) If the turbine inlet temperature indication fails or is suspected of failure during takeoff, climb, descent, or landing, maintain FULL RICH mixture to assure adequate fuel flow for engine cooling. (2) If the turbine inlet temperature indication fails or is suspected of failure after cruise power has been set, maintain cruise power setting and lean to 6 gallons per hour (GPH) fuel flow above that specified in the Power Setting Table in Section 5 of the AFM/ POH. Continually monitor engine cylinder head and oil temperatures to avoid exceeding temperature limits. srobinson on DSKHWCL6B1PROD with PROPOSALS Appendix 2 to Docket No. FAA–2010–1295 Model PA–46–350P (Malibu Mirage) and Model PA–46R–350T (Matrix)—Emergency Procedures for the Pilot’s Operating Handbook (POH) (1) If the turbine inlet temperature indication fails or is suspected of failure during takeoff, climb, descent or landing, set power per the POH Section 5 Power Setting Table and then lean to the approximate POH Power Setting Table fuel flow plus 4 GPH. (2) If the turbine inlet temperature indication fails or is suspected of failure after cruise power has been set, maintain the power setting and increase indicated fuel VerDate Mar<15>2010 17:52 Dec 29, 2010 Jkt 223001 flow by 1 GPH. Continually monitor engine cylinder head and oil temperatures to avoid exceeding temperature limits. Issued in Kansas City, Missouri on December 22, 2010. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–32959 Filed 12–29–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–1206; Directorate Identifier 2009–NM–216–AD] RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Corporation Model DC–10–10, DC–10–10F, and MD–10–10F Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Model DC–10–10, DC–10–10F, and MD– 10–10F airplanes. This proposed AD would require repetitive inspections for cracking on the lower cap of the rear spar of the left and right wings between stations Xors=417 and the outboard edge of the lower cap splice of the wing rear spar at station Xors=400; temporary and permanent repairs if necessary; and repetitive inspections of repaired areas and corrective actions if necessary. This proposed AD results from reports of three instances of fuel leaks in the lower cap splice of the wing rear spar at station Xors=409. We are proposing this AD to detect and correct cracking on the lower cap of the rear spar of the left and right wings between stations Xors=417 and the outboard edge of the lower cap splice of the wing rear spar at station Xors=400, which could result in fuel leaks or cracking of the lower wing skin and structure, causing possible inability of the structure to sustain the limit load adversely affecting the structural integrity of the airplane. DATES: We must receive comments on this proposed AD by February 14, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, SUMMARY: PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 82333 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 Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, California 90846–0001; telephone 206–544–5000, extension 2; fax 206–766–5683; e-mail dse.boecom@ boeing.com; Internet https://www.my boeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket You may examine the AD docket on the Internet at http://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 AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Nenita Odesa, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; phone: (562) 627–5234; fax: (562) 627–5210; e-mail: nenita.odesa@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2010–1206; Directorate Identifier 2009–NM–216–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. E:\FR\FM\30DEP1.SGM 30DEP1

Agencies

[Federal Register Volume 75, Number 250 (Thursday, December 30, 2010)]
[Proposed Rules]
[Pages 82329-82333]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-32959]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1295; Directorate Identifier 2010-CE-060-AD]
RIN 2120-AA64


Airworthiness Directives; Piper Aircraft, Inc. (Type Certificate 
Previously Held by The New Piper Aircraft, Inc.) Models PA-46-310P, PA-
46-350P, and PA-46R-350T Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to certain Piper Aircraft, Inc. Models PA-46-310P and 
PA-46-350P airplanes that are equipped with a Lewis or Transicoil 
turbine inlet temperature (T.I.T.) gauge and associated probe. The 
existing AD currently requires calibrating the T.I.T. system; replacing 
any T.I.T. system that fails the calibration test; repetitively 
replacing the T.I.T. probe on certain Model PA-46-350P airplanes; and 
inserting a copy of the AD into the pilot's operating handbook (POH) 
for certain airplanes. Since we issued that AD, the manufacturer has 
revised related service information and added an airplane model to the 
list of affected airplanes. This proposed AD would retain the actions 
required by AD 99-15-04 R1, add certain Model PA-46R-350T airplanes to 
the Applicability section, expand the applicability to include other 
T.I.T. systems, and incorporate new service information. We are 
proposing this AD to prevent improper engine operation caused by 
improperly calibrated T.I.T. indicators or defective T.I.T. probes, 
which could result in engine damage/failure with consequent loss of 
control of the airplane.

DATES: We must receive comments on this proposed AD by February 14, 
2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Piper 
Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida 32960; telephone: 
(772) 567-4361; fax: (772) 978-6573; Internet: http://www.newpiper.com/company/publications.asp. You may review copies of the referenced 
service information at the FAA, Small Airplane Directorate, 901 Locust 
St., Kansas City, Missouri 64106. For information on the availability 
of this material at the FAA, call (816) 329-4148.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://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 AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Darby Mirocha, Aerospace Engineer, 
FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, 
College Park, Georgia 30337; phone: (404) 474-5573; fax: (404) 474-
5605; e-mail: darby.mirocha@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-1295; 
Directorate Identifier 2010-CE-060-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed 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 proposed AD.

Discussion

    On May 17, 2000, we issued AD 99-15-04 R1, Amendment 39-11747 (65 
FR 33745, May 25, 2000), for certain Piper Aircraft, Inc. (type 
certificate previously held by The New Piper Aircraft, Inc.) Models PA-
46-310P and PA-46-350P airplanes that are equipped with a Lewis or 
Transicoil turbine inlet temperature (T.I.T.) gauge and associated 
probe. That AD required calibrating the T.I.T. system; replacing any 
T.I.T. system that fails the calibration test; repetitively replacing 
the T.I.T. probe on Model PA-46-350P airplanes; and inserting a copy of 
the AD into the Emergency Procedures section of the POH for certain 
airplanes. That AD resulted from field reports that indicated service 
accuracy problems with the existing T.I.T. system on certain Piper 
Aircraft, Inc. Models PA-46-310P and PA-46-350P. We issued that AD to 
prevent improper engine operation caused by improperly calibrated 
T.I.T. indicators or defective T.I.T. probes, which could result in 
engine damage/failure with consequent loss of control of the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 99-15-04 R1, the manufacturer has revised 
related service information and has added an airplane model to the list 
of affected airplanes. We have also determined that the scope of this 
proposed AD goes beyond only airplanes equipped with Lewis or 
Transicoil gauges and/or probes.

Relevant Service Information

    We reviewed Piper Aircraft, Inc. Service Bulletin No. 995C, dated

[[Page 82330]]

November 17, 2009. The service information describes procedures for 
calibrating the T.I.T. system and replacing the probe.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would retain the requirements of AD 99-15-04 R1. 
This proposed AD would also add certain Model PA-46R-350T airplanes to 
the Applicability section, expand the applicability to include other 
T.I.T. systems, and incorporate new service information.

Costs of Compliance

    We estimate that this proposed AD affects 898 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                 Cost per       Cost on U.S.
              Action                    Labor cost            Parts cost         product          operators
----------------------------------------------------------------------------------------------------------------
Clean and inspect the turbine      1 work-hour x $85     Not applicable......          $85  $85 x 780 affected
 inlet temperature gauge and        per hour = $85.                                          airplanes =
 probe for certain Models PA-46-                                                             $66,300.
 310P and PA-46-350P airplanes.
Calibrate the turbine inlet        4 work-hours x $85    Not applicable......          340  $340 x 427 affected
 temperature gauge for certain      per hour = $340.                                         airplanes =
 Models PA-46-310P and PA-46-350P                                                            $145,180.
 airplanes.
Incorporate emergency procedures   1 workhour x $85 per  Not applicable......           85  $85 x 898 affected
 into POH.                          hour = $85.                                              airplanes =
                                                                                             $76,330.
----------------------------------------------------------------------------------------------------------------

    The requirements of this proposed AD add no additional economic 
burden other than the addition of an airplane model to the 
Applicability section.
    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed inspection. 
We have no way of determining the number of aircraft that might need 
these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace probe.................................  1 work-hour x $85 per hour =                $384            $469
                                                 $85.
----------------------------------------------------------------------------------------------------------------

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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

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 removing airworthiness directive 
(AD) 99-15-04 R1, Amendment 39-11747 (65 FR 33745, May 25, 2000), and 
adding the following new AD:

Piper Aircraft, Inc. (Type Certificate Previously Held by The New 
Piper Aircraft, Inc.): Docket No. FAA-2010-1295; Directorate 
Identifier 2010-CE-060-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by February 
14, 2011.

Affected ADs

    (b) This AD supersedes AD 99-15-04 R1, Amendment 39-11747.

Applicability

    (c) This AD applies to the following Piper Aircraft, Inc. (type 
certificate previously held by The New Piper Aircraft, Inc.) Models 
PA-

[[Page 82331]]

46-310P, PA-46-350P, and PA-46R-350T airplanes that:
    (1) Are certificated in any category; and
    (2) Equipped with a turbine inlet temperature (T.I.T.) system 
identified in table 1 of this AD. Relief from this AD is available 
only if the gauge and probe are replaced through STC and not if a 
second turbine inlet temperature gauge was installed while retaining 
the Lewis or Transicoil T.I.T. gauge and probe.

        Group 1--Airplanes Previously Affected by AD 99-15-04 R1
------------------------------------------------------------------------
                 Models                        Serial Numbers (S/N)
------------------------------------------------------------------------
PA-46-310P (Malibu)....................  46-8408001 through 46-8608067
                                          and 4608001 through 4608140.
PA-46-350P (Malibu Mirage).............  4622001 through 4622200 and
                                          4636001 through 4636020.
------------------------------------------------------------------------
------------------------------------------------------------------------


      Group 2--Airplanes Not Previously Affected by AD 99-15-04 R1
------------------------------------------------------------------------
                 Models                        Serial Numbers (S/N)
------------------------------------------------------------------------
PA-46-350P (Malibu Mirage).............  4636021 and subsequent.
PA-46R-350T (Matrix)...................  4692001 and subsequent.
------------------------------------------------------------------------


      Table 1--Affected Airplane Models and Corresponding Affected Lewis or Transicoil Part Numbers (P/Ns)
----------------------------------------------------------------------------------------------------------------
                Models                           S/N             Indication System P/N          Probe P/N
----------------------------------------------------------------------------------------------------------------
PA-46-310P...........................  46-8408001 through 46-   Lewis T.I.T. analog      471-009 or 481-387.
                                        8608067 and 4608001      indicators P/N 471-008.
                                        through 4608140.
PA-46-350P...........................  4622001 through 4622200  Lewis T.I.T. analog      481-389 or 481-392 or
                                        and 4636001 through      indicators P/N 471-008.  686-216 (preferred).
                                        4636020.
PA-46-350P...........................  4636021 through 4636374  Lewis T.I.T. digital     481-389 or 481-392 or
                                                                 indicators P/N 548-811.  686-216 (preferred).
PA-46-350P...........................  4636375 and subsequent.  Avidyne Entegra or       686-216.
                                                                 other Electronic
                                                                 Flight Information
                                                                 System (EFIS) display.
PA-46R-350T..........................  4692001 and subsequent.  Avidyne Entegra or       686-216.
                                                                 other EFIS display.
----------------------------------------------------------------------------------------------------------------

Subject

    (d) Joint Aircraft System Component (JASC)/Air Transport 
Association (ATA) of America Code 77, Engine Indicating.

Unsafe Condition

    (e) This AD was prompted by field reports that indicated service 
accuracy problems with the existing turbine inlet temperature system 
on certain Models PA-46-310P, PA-46-350P, and PA-46R-350T airplanes. 
We are issuing this AD to prevent improper engine operation caused 
by improperly calibrated turbine inlet temperature indicators or 
defective turbine inlet temperature probes, which could result in 
engine damage/failure with consequent loss of control of the 
airplane.

Compliance

    (f) For Group 1 airplanes: Comply with this AD within the 
compliance times specified, unless already done.

                       Table 2--Group 1 Airplanes
            [Airplanes previously affected by AD 99-15-04 R1]
------------------------------------------------------------------------
            Actions                 Compliance           Procedures
------------------------------------------------------------------------
(1) Clean and inspect the       Within the next    Follow Piper Airplane
 turbine inlet temperature       100 hours time-    Maintenance Manual
 gauge and probe.                in-service (TIS)  PA-46-310P/PA-46-350P
                                 after August 31,   Part Number 761-783,
                                 1999 (the          Chapter 77-20-00,
                                 effective date     section A.(1)(d),
                                 retained from AD   pages 1 and 2; and
                                 99-15-04).         Piper Airplane
                                                    Maintenance Manual
                                                    PA-46-350P Part
                                                    Number 761-876,
                                                    Chapter 77-20-00,
                                                    section 1.C, pages 1
                                                    and 2, as
                                                    applicable.
(2) Calibrate the turbine       Within the next    Follow Piper Airplane
 inlet temperature system.       100 hours TIS      Maintenance Manual
                                 after August 31,  PA-46-310P/PA-46-350P
                                 1999 (the          Part Number 761-783,
                                 effective date     Chapter 77-20-00,
                                 retained from AD   section A.(1)(g),
                                 99-15-04).         pages 3 and 4; and
                                                    Piper Airplane
                                                    Maintenance Manual
                                                    PA-46-350P Part
                                                    Number 761-876,
                                                    Chapter 77-20-00,
                                                    section 1.F, pages 2
                                                    through 4, as
                                                    applicable; or Piper
                                                    Service Bulletin No.
                                                    995C, dated November
                                                    17, 2009.
(3) If the turbine inlet        Before further     Follow Piper Airplane
 temperature probe fails the     flight after the   Maintenance Manual
 inspection required in          cleaning and      PA-46-310P/PA-46-350P
 paragraph (f)(1) of this AD     inspection         Part Number 761-783,
 and/or the turbine inlet        required in        Chapter 77-20-00,
 temperature system indicator    paragraph (f)(1)   section A.(1)(f),
 cannot be calibrated as         and the            page 2; and Piper
 required in paragraph (f)(2)    calibration        Airplane Maintenance
 of this AD, replace any         required in        Manual PA-46-350P
 failed parts with a             paragraph (f)(2)   Part Number 761-876,
 serviceable part listed in      of this AD.        Chapter 77-20-00,
 table 1 of this AD as long as                      section 1.E., page
 it has been inspected and                          2, as applicable; or
 properly calibrated.                               Piper Service
                                                    Bulletin No. 995C,
                                                    dated November 17,
                                                    2009.

[[Page 82332]]

 
(4) Incorporate the             Within the next    Not applicable.
 information from Appendix 1     100 hours TIS
 and Appendix 2, as              after August 31,
 applicable, of this AD into     1999 (the
 the Emergency Procedures        effective date
 section of the pilot            retained from AD
 operating handbook (POH).       99-15-04).
 This may be done by inserting
 a copy of this AD into the
 POH.
(5) Only install a part listed  As of July 28,     Not applicable.
 in table 1 of this AD after     2000 (the
 it has been inspected and       effective date
 properly calibrated.            of AD 99-15-04
                                 R1).
(6) Model PA-46-350P airplanes  Upon accumulating  For serial numbers
 only: Replace the turbine       250 hours TIS on   4622001 through
 inlet temperature probe with    the currently      4622200: Follow
 a new part number 481-389,      installed          Piper Airplane
 481-392, or 686-216 probe       turbine inlet      Maintenance Manual
 preferred). This action is      temperature        PA-46-310P/PA-46-
 not required for Model PA-46-   probe or within    350P Part Number 761-
 310P.                           the next 100       783, Chapter 77-20-
                                 hours TIS after    00, section
                                 August 31, 1999    A.(1)(f), page 2; or
                                 (the effective     Piper Service
                                 date retained      Bulletin No. 995C,
                                 from AD 99-15-     dated November 17,
                                 04), whichever     2009.
                                 occurs later,
                                 and thereafter
                                 at intervals not
                                 to exceed 250
                                 hours TIS.
                                                   For serial numbers
                                                    4636001 through
                                                    4636020: Follow
                                                    Piper Airplane
                                                    Maintenance Manual
                                                    PA-46-350P Part
                                                    Number 761-876,
                                                    Chapter 77-20-00,
                                                    section 1.E., page
                                                    2: or Piper Service
                                                    Bulletin No. 995C,
                                                    dated November 17,
                                                    2009.
------------------------------------------------------------------------

     (g) For Group 2 airplanes: Comply with this AD within the 
compliance times specified, unless already done.

                       Table 3--Group 2 Airplanes
          [Airplanes not previously affected by AD 99-15-04 R1]
------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Model PA-46-350P          Within the next 100   Follow Piper
 airplanes, S/Ns 4636021       hours TIS after the   Airplane
 through 4636374 only: Clean   effective date of     Maintenance Manual
 and inspect the turbine       this AD.              PA-46-350P Part
 inlet temperature gauge and                         Number 761-876,
 probe.                                              Chapter 77-20-00,
                                                     section 1.C, pages
                                                     1 and 2, as
                                                     applicable.
(2) Model PA-46-350P          Before further        Follow Piper Service
 airplanes, S/Ns 4636021       flight after the      Bulletin No. 995C,
 through 4636374 only: If      cleaning and          dated November 17,
 the turbine inlet             inspection required   2009.
 temperature probe fails the   in paragraph (g)(1)
 inspection required in        and the calibration
 paragraph (g)(1) of this AD   required in
 and/or the turbine inlet      paragraph (g)(2) of
 temperature system            this AD.
 indicator cannot be
 calibrated as required in
 paragraph (g)(2) of this
 AD, replace any failed
 parts with a serviceable
 part listed in table 1 of
 this AD as long as it has
 been inspected and properly
 calibrated.
(3) All Group 2 airplanes:    Upon accumulating     Piper Service
 Replace the turbine inlet     250 hours TIS on      Bulletin No. 995C,
 temperature probe with a      the currently         dated November 17,
 new part number 686-216       installed turbine     2009.
 probe.                        inlet temperature
                               probe or within the
                               next 100 hours TIS
                               after the effective
                               date of this AD,
                               whichever occurs
                               later, and
                               thereafter at
                               intervals not to
                               exceed 250 hours
                               TIS.
(4) All Group 2 airplanes:    Within the next 100   Not applicable.
 Incorporate the information   hours TIS after the
 from Appendix 2 of this AD    effective date of
 into the Emergency            this AD.
 Procedures section of the
 POH. This may be done by
 inserting a copy of this AD
 into the POH.
(5) All Group 2 airplanes:    As of the effective   Not applicable.
 Only install a part listed    date of this AD.
 in table 1 of this AD after
 it has been inspected and
 properly calibrated.
------------------------------------------------------------------------


[[Page 82333]]

Alternative Methods of Compliance (AMOCs)

    (h)(1) The Manager, Atlanta Aircraft Certification Office, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the ACO, send it to the attention of the 
person identified in the Related Information section of this AD.
    (2) Before using any approved AMOC, notify your Principal 
Maintenance Inspector or Principal Avionics Inspector, as 
appropriate, or lacking a principal inspector, your local Flight 
Standards District Office.
    (3) AMOCs approved for AD 99-15-04 R1 are approved as AMOCs for 
this AD.

Related Information

    (i) For more information about this AD, contact Darby Mirocha, 
Aerospace Engineer, FAA, Atlanta Aircraft Certification Office, 1701 
Columbia Avenue, College Park, Georgia 30337; phone: (404) 474-5573; 
fax: (404) 474-5605; e-mail: darby.mirocha@faa.gov.
    (j) For service information identified in this AD, contact Piper 
Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida 32960; 
telephone: (772) 567-4361; fax: (772) 978-6573; Internet: http://www.piper.com/home/pages/publications.cfm. You may review copies of 
the referenced service information at the FAA, Small Airplane 
Directorate, 901 Locust St., Kansas City, MO 64106. For information 
on the availability of this material at the FAA, call (816) 329-
4148.

Appendix 1 to Docket No. FAA-2010-1295

Model PA-46-310P (Mailbu)--Emergency Procedures for the Pilot's 
Operating Handbook (POH)

    (1) If the turbine inlet temperature indication fails or is 
suspected of failure during takeoff, climb, descent, or landing, 
maintain FULL RICH mixture to assure adequate fuel flow for engine 
cooling.
    (2) If the turbine inlet temperature indication fails or is 
suspected of failure after cruise power has been set, maintain 
cruise power setting and lean to 6 gallons per hour (GPH) fuel flow 
above that specified in the Power Setting Table in Section 5 of the 
AFM/POH. Continually monitor engine cylinder head and oil 
temperatures to avoid exceeding temperature limits.

Appendix 2 to Docket No. FAA-2010-1295

Model PA-46-350P (Malibu Mirage) and Model PA-46R-350T (Matrix)--
Emergency Procedures for the Pilot's Operating Handbook (POH)

    (1) If the turbine inlet temperature indication fails or is 
suspected of failure during takeoff, climb, descent or landing, set 
power per the POH Section 5 Power Setting Table and then lean to the 
approximate POH Power Setting Table fuel flow plus 4 GPH.
    (2) If the turbine inlet temperature indication fails or is 
suspected of failure after cruise power has been set, maintain the 
power setting and increase indicated fuel flow by 1 GPH. Continually 
monitor engine cylinder head and oil temperatures to avoid exceeding 
temperature limits.

    Issued in Kansas City, Missouri on December 22, 2010.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010-32959 Filed 12-29-10; 8:45 am]
BILLING CODE 4910-13-P