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, 18033-18038 [2011-7569]

Download as PDF Federal Register / Vol. 76, No. 63 / Friday, April 1, 2011 / Rules and Regulations FAA AD Differences # 2 fire, the fire extinguishing capability would not be operational. * * * * Note 1: This AD differs from the MCAI and/or service information as follows: No Differences. * Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Actions (g) Within 8 days after the effective date of this AD: Visually inspect the extinguishing system line and the low pressure bleed line of the number 2 engine at frame 42 in the rear compartment to determine proper installation of the lines, in accordance with paragraph 2.B.(1) of the Accomplishment Instructions of Dassault Service Bulletin F50–519, dated February 18, 2011. (1) If the lines are properly installed, no further action is required by this paragraph. (2) If the lines are improperly installed, before further flight, do the actions specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD, in accordance with paragraph 2.B.(1) of the Accomplishment Instructions of Dassault Service Bulletin F50–519, dated February 18, 2011. (i) Inspect the improperly installed lines for deformation. (A) If no deformation is found on the improperly installed lines, before further flight, re-install the lines using the proper connections, in accordance with paragraph 2.B.(1) of the Accomplishment Instructions of Dassault Service Bulletin F50–519, dated February 18, 2011. (B) If any deformation is found on the improperly installed lines, before further flight, replace the lines in accordance with paragraph 2.B.(1) of the Accomplishment Instructions of Dassault Service Bulletin F50–519, dated February 18, 2011. (ii) Verify the correct connection of the lines in accordance with paragraph 2.B.(1) of the Accomplishment Instructions of Dassault Service Bulletin F50–519, dated February 18, 2011. jlentini on DSKJ8SOYB1PROD with RULES Reporting Requirement (h) Submit a report of the findings (both positive and negative) of the inspection required by paragraph (g) of this AD to Dassault Aviation, as specified in paragraph 2.B.(2) of the Accomplishment Instructions of Dassault Service Bulletin F50–519, dated February 18, 2011. Submit the report at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD. The report must include the information identified in Dassault Service Bulletin F50–519, dated February 18, 2011. Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120–0056. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 10 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 10 days after the effective date of this AD. VerDate Mar<15>2010 16:52 Mar 31, 2011 Jkt 223001 Other FAA AD Provisions (i) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): 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. 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 International Branch, send it to ATTN: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone 425–227–1137; fax 425–227– 1149. Information may be e-mailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of 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 (j) Refer to MCAI European Aviation Safety Agency Emergency Airworthiness Directive 2011–0025–E, dated February 18, 2011; and Dassault Service Bulletin F50–519, dated February 18, 2011; for related information. Material Incorporated by Reference (k) You must use Dassault Service Bulletin F50–519, dated February 18, 2011, to do the PO 00000 Frm 00033 Fmt 4700 Sfmt 4700 18033 actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey 07606; telephone 201–440–6700; Internet https:// www.dassaultfalcon.com. (3) You may review copies of the 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. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on March 21, 2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–7427 Filed 3–31–11; 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; Amendment 39–16635; AD 2011–06–10] 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: Final rule. AGENCY: We are superseding 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. That AD currently requires cleaning, inspecting, and 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 airplanes; and inserting a copy of the AD into the pilot’s operating handbook (POH) for certain airplanes. This new AD retains SUMMARY: E:\FR\FM\01APR1.SGM 01APR1 18034 Federal Register / Vol. 76, No. 63 / Friday, April 1, 2011 / Rules and Regulations the actions required by the previous AD (AD 99–15–04 R1), adds certain Model PA–46R–350T airplanes to the Applicability section, expands the applicability to include other T.I.T. systems, and incorporates new service information. This AD was prompted by the manufacturer revising related service information and adding an airplane model to the list of affected airplanes. We are issuing 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: This AD is effective May 6, 2011. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of May 6, 2011. ADDRESSES: 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: https://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 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 AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. 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: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 99–15–04 R1, Amendment 39–11747 (65 FR 33745, May 25, 2000). That AD applies to 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 T.I.T. gauge and associated probe. The NPRM published in the Federal Register on December 30, 2010 (75 FR 82329). That NPRM proposed to continue to require cleaning, inspecting, and calibrating the T.I.T. system on certain airplanes; replacing any T.I.T. system that fails the inspection and calibration test; repetitively replacing the T.I.T. probe on certain airplanes; and inserting a copy of the AD into the pilot’s operating handbook (POH). That NPRM also proposed to 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. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting the AD as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Costs of Compliance We estimate that this AD affects 898 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Cost per product Action Labor cost Parts cost Clean and inspect the T.I.T gauge and probe for certain Models PA–46– 310P and PA–46–350P airplanes. Calibrate the T.I.T. gauge for certain Models PA–46–310P and PA–46– 350P airplanes. Incorporate emergency procedures into POH. 1 work-hour × $85 per hour = $85 ...... Not applicable ................. $85 4 work-hours × $85 per hour = $340 .. Not applicable ................. 340 1 work-hour × $85 per hour = $85 ...... Not applicable ................. 85 The requirements of this 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 will be required based on the results of the inspection. We have no way of Cost on U.S. operators $85 × 780 affected airplanes = $66,300. 340 × 427 affected airplanes = $145,180. 85 × 898 affected airplanes = $76,330. determining the number of aircraft that might need these replacements: jlentini on DSKJ8SOYB1PROD with RULES ON-CONDITION COSTS Action Labor cost Parts cost Cost per product Replace probe ............................................. 1 work-hour × $85 per hour = $85 ................................................ $384 $469 VerDate Mar<15>2010 16:52 Mar 31, 2011 Jkt 223001 PO 00000 Frm 00034 Fmt 4700 Sfmt 4700 E:\FR\FM\01APR1.SGM 01APR1 18035 Federal Register / Vol. 76, No. 63 / Friday, April 1, 2011 / Rules and Regulations 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 AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under 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. § 39.13 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Affected ADs Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: (c) This AD applies to the following 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 that are: (1) Certificated in any category; and (2) equipped with a turbine inlet temperature (T.I.T.) system identified in table 3 of this AD. Relief from this AD is available only if the gauge and probe are replaced through STC and not if a second T.I.T. gauge was installed while retaining the Lewis or Transicoil T.I.T. gauge and probe. 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. [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: ■ 2011–06–10 Piper Aircraft, Inc. (Type Certificate Previously Held by The New Piper Aircraft, Inc.): Amendment 39– 16635; Docket No. FAA–2010–1295; Directorate Identifier 2010–CE–060–AD. Effective Date (a) This airworthiness directive (AD) is effective May 6, 2011. (b) This AD supersedes AD 99–15–04 R1, Amendment 39–11747. Applicability TABLE 1—GROUP 1 (AIRPLANES PREVIOUSLY AFFECTED BY AD 99–15–04 R1) Models Serial Numbers (S/N) PA–46–310P (Malibu) ......................................... PA–46–350P (Malibu Mirage) ............................ 46–8408001 through 46–8608067 and 4608001 through 4608140. 4622001 through 4622200 and 4636001 through 4636020. TABLE 2—GROUP 2 (AIRPLANES NOT PREVIOUSLY AFFECTED BY AD 99–15–04 R1) Models S/N PA–46–350P (Malibu Mirage) ............................................................................................................................... PA–46R–350T (Matrix) .......................................................................................................................................... 4636021 and subsequent. 4692001 and subsequent. TABLE 3—AFFECTED AIRPLANE MODELS AND CORRESPONDING AFFECTED TURBINE INLET TEMPERATURE (T.I.T.) SYSTEM Models S/N Indication system 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. 4636021 through 4636374 ......... PA–46–350P .......................................... 4636375 and subsequent .......... 481–389 or 481–392 or 686– 216 (preferred). 481–389 or 481–392 or 686– 216 (preferred). 686–216. PA–46R–350T ........................................ 4692001 and subsequent .......... Lewis T.I.T. analog indicators P/ N 471–008. Lewis T.I.T. digital indicators P/ N 548–811. Avidyne Entegra or other Electronic Flight Information System (EFIS) display. Avidyne Entegra or other EFIS display. jlentini on DSKJ8SOYB1PROD with RULES PA–46–350P .......................................... VerDate Mar<15>2010 16:52 Mar 31, 2011 Jkt 223001 PO 00000 Frm 00035 Fmt 4700 Sfmt 4700 E:\FR\FM\01APR1.SGM Probe P/N 686–216. 01APR1 18036 Federal Register / Vol. 76, No. 63 / Friday, April 1, 2011 / Rules and Regulations 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 T.I.T. 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 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. Compliance (f) For Group 1 airplanes: Comply with this AD within the compliance times specified, unless already done. TABLE 4—GROUP 1 AIRPLANES (AIRPLANES PREVIOUSLY AFFECTED BY AD 99–15–04 R1) Compliance Procedures (1) Clean and inspect the T.I.T. gauge and probe. Within the next 100 hours time-in-service (TIS) after August 31, 1999 (the effective date retained from AD 99–15–04). (2) Calibrate the T.I.T. system ........................... Within the next 100 hours TIS after August 31, 1999 (the effective date retained from AD 99–15–04). (3) If the T.I.T. probe fails the inspection required in paragraph (f)(1) of this AD and/or the T.I.T. 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 3 of this AD as long as it has been inspected, passed the inspection, and been 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. (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 3 of this AD after it has been inspected and properly calibrated. (6) Model PA–46–350P airplanes only: Replace the T.I.T. 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. jlentini on DSKJ8SOYB1PROD with RULES Actions Within the next 100 hours TIS after August 31, 1999 (the effective date retained from AD 99–15–04). Follow Piper Airplane Maintenance Manual PA–46–310P/PA–46–350P, Part Number 761 783, Chapter 77, section 77–20–00 A.(1)(d), dated July 1, 1998; and Piper Airplane Maintenance Manual PA–46–350P/ PA–46R–350T, Part Number 761 876, Chapter 77, section 77–20–00 1.C, page 1, dated August 28, 2007, and page 2, dated July 31, 2008, as applicable. Follow Piper Airplane Maintenance Manual PA–46–310P/PA–46–350P, Part Number 761 783, Chapter 77, section 77–20–00 A.(1)(g), dated July 1, 1998; and Piper Airplane Maintenance Manual PA–46–350P/ PA–46R–350T, Part Number 761 876, Chapter 77, section 77–20–00 1.F, page 2, dated July 31, 2008, and pages 3 and 4, dated August 28, 2007, 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, section 77–20–00 A.(1)(f), dated July 1, 1998; and Piper Airplane Maintenance Manual PA–46–350P/ PA–46R–350T, Part Number 761 876, Chapter 77, section 77–20–00 1.E., page 2, dated July 31, 2008, as applicable; or Piper Service Bulletin No. 995C, dated November 17, 2009 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 T.I.T. 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, section 77–20–00 A.(1)(f), dated July 1, 1998; or Piper Service Bulletin No. 995C, dated November 17, 2009. For serial numbers 4636001 through 4636020: Follow Piper Airplane Maintenance Manual PA–46–350P/PA–46R–350T, Part Number 761 876, Chapter 77, section 77–20–00 1.E., page 2, dated July 31, 2008; 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. VerDate Mar<15>2010 16:52 Mar 31, 2011 Jkt 223001 PO 00000 Frm 00036 Fmt 4700 Sfmt 4700 E:\FR\FM\01APR1.SGM 01APR1 18037 Federal Register / Vol. 76, No. 63 / Friday, April 1, 2011 / Rules and Regulations TABLE 5—GROUP 2 AIRPLANES (AIRPLANES NOT PREVIOUSLY AFFECTED BY AD 99–15–04 R1) Actions Compliance Procedures (1) Model PA–46–350P airplanes, S/Ns 4636021 through 4636374 only: Clean and inspect the T.I.T. gauge and probe. Within the next 100 hours TIS after the effective date of this AD. (2) Model PA–46–350P airplanes, S/Ns 4636021 through 4636374 only: If the T.I.T. probe fails the inspection required in paragraph (g)(1) of this AD, replace any failed parts with a serviceable part listed in table 3 of this AD as long as it has been inspected and has passed the inspection. (3) All Group 2 airplanes: Replace the T.I.T. probe with a new part number 686–216 probe. Before further flight after the cleaning and inspection required in paragraph (g)(1) of this AD. Follow Piper Airplane Maintenance Manual PA–46–350P/PA–46R–350T, Part Number 761 876, Chapter 77, section 77–20–00 1.C, page 1, dated August 28, 2007, and page 2, dated July 31, 2008. 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 3 of this AD after it has been inspected and properly calibrated. 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 Upon accumulating 250 hours TIS on the currently installed T.I.T. 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. Not applicable. 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. 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. Material Incorporated by Reference (j) You must use the service information contained in Table 6 of this AD to do the actions required by this AD, unless the AD specifies otherwise. Related Information (i) For more information about this AD, contact Darby Mirocha, Aerospace Engineer, TABLE 6—ALL MATERIAL INCORPORATED BY REFERENCE Revision Piper Service Bulletin No. 995C ................................................................................................. Piper Airplane Maintenance Manual PA–46–310P/PA–46–350P, Part Number 761 783, Chapter 77, ‘‘Engine Indicating,’’ Section 77–20–00, pages 1 through 4. Piper Airplane Maintenance Manual PA–46–350P/PA–46R–350T, Part Number 761 876, Chapter 77, ‘‘Engine Indicating,’’ Section 77–20–00, pages 1 through 4. jlentini on DSKJ8SOYB1PROD with RULES Document N/A .................... N/A ................... November 17, 2009. July 1, 1998. N/A ................... July 31, 2008. Section 77–20–00: pages 1, 3, and 4, dated August 28, 2007; page 2, dated July 31, 2008. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida 32960; telephone: (772) 567–4361; fax: (772) 978– 6573; Internet: https://www.piper.com/home/ pages/publications.cfm. (3) You may review copies of the 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. VerDate Mar<15>2010 16:52 Mar 31, 2011 Jkt 223001 (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at an NARA facility, call 202–741– 6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Appendix 1 to AD 2011–06–10—Model PA– 46–310P (Malibu); Emergency Procedures for the Pilot’s Operating Handbook (POH) (1) If the turbine inlet temperature indication fails or is suspected of failure PO 00000 Frm 00037 Fmt 4700 Sfmt 4700 Date 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. E:\FR\FM\01APR1.SGM 01APR1 18038 Federal Register / Vol. 76, No. 63 / Friday, April 1, 2011 / Rules and Regulations Appendix 2 to AD 2011–06–10—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 March 9, 2011. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–7569 Filed 3–31–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2011–0256; Directorate Identifier 2010–NM–114–AD; Amendment 39–16645; AD 2011–07–08] RIN 2120–AA64 Airworthiness Directives; Airbus Model A340–200 and –300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: SUMMARY: Two A340–300 aeroplanes experienced one single door opening of engine number (n°) 3 Thrust Reverser (TR) pivoting door during climb. These events were the result of a primary lock malfunction and incorrect engagement of the secondary lock. jlentini on DSKJ8SOYB1PROD with RULES * * * * * Deployment of one TR door in flight, particularly during the take-off or go around, could result in heavy buffet at low speed, or could significantly reduce take off performance [and increase pilot workload during takeoff or go around], which would constitute an unsafe condition. * * * VerDate Mar<15>2010 * * 18:13 Mar 31, 2011 Jkt 223001 This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective April 18, 2011. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of April 18, 2011. We must receive comments on this AD by May 16, 2011. ADDRESSES: You may send comments by any of the following methods: • 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, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; phone: 425– 227–1138; fax: 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2010–0044, dated March 17, 2010 [corrected March 25, 2010] (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Two A340–300 aeroplanes experienced one single door opening of engine number (n°) 3 Thrust Reverser (TR) pivoting door during climb. These events were the result of PO 00000 Frm 00038 Fmt 4700 Sfmt 4700 a primary lock malfunction and incorrect engagement of the secondary lock. While investigations on root cause of these events were conducted, preventive actions have been required by EASA AD 2008–0074, AD 2009–0063 [which corresponds to FAA AD 2009–21–05, Amendment 39–16042] and AD 2009–0133. The root cause has now been identified as being a combined failure of the thrust reverser pivoting door primary lock and actuator. Deployment of one TR door in flight, particularly during the take-off or go around, could result in heavy buffet at low speed, or could significantly reduce take off performance [and increase pilot workload during takeoff or go around], which would constitute an unsafe condition. Investigations have also identified that 10 TR pivoting doors of the 16 installed on each aeroplane may cause such effects. These are: —Outboard engines (n° 1 and 4): all 4 pivoting doors of each engine. —Inboard engines (n° 2 and 3): upper inboard pivoting door of each engine. In order to reinforce the thrust reverser locking mechanism, this AD requires installation of a new modified primary lock and a new modified actuator on the 10 critical thrust reverser pivoting doors. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued Mandatory Service Bulletin A340–78–4037, including Appendices 01 and 02, dated January 15, 2010; and Mandatory Service Bulletin A340–78–4038, Appendices 01 and 02, dated January 29, 2010. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. There are no products of this type currently registered in the United States. However, this rule is necessary to ensure that the described unsafe condition is addressed if any of these products are placed on the U.S. Register in the future. E:\FR\FM\01APR1.SGM 01APR1

Agencies

[Federal Register Volume 76, Number 63 (Friday, April 1, 2011)]
[Rules and Regulations]
[Pages 18033-18038]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-7569]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1295; Directorate Identifier 2010-CE-060-AD;
Amendment 39-16635; AD 2011-06-10]
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: Final rule.

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

SUMMARY: We are superseding 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. That AD
currently requires cleaning, inspecting, and 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 airplanes; and
inserting a copy of the AD into the pilot's operating handbook (POH)
for certain airplanes. This new AD retains

[[Page 18034]]

the actions required by the previous AD (AD 99-15-04 R1), adds certain
Model PA-46R-350T airplanes to the Applicability section, expands the
applicability to include other T.I.T. systems, and incorporates new
service information. This AD was prompted by the manufacturer revising
related service information and adding an airplane model to the list of
affected airplanes. We are issuing 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: This AD is effective May 6, 2011.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of May 6, 2011.

ADDRESSES: 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: https://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 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 AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (phone: 800-647-5527) is Document Management Facility,
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.

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:

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 99-15-04 R1, Amendment 39-11747 (65 FR 33745,
May 25, 2000). That AD applies to 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 T.I.T. gauge and associated probe. The NPRM published in the
Federal Register on December 30, 2010 (75 FR 82329). That NPRM proposed
to continue to require cleaning, inspecting, and calibrating the T.I.T.
system on certain airplanes; replacing any T.I.T. system that fails the
inspection and calibration test; repetitively replacing the T.I.T.
probe on certain airplanes; and inserting a copy of the AD into the
pilot's operating handbook (POH). That NPRM also proposed to 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.

Comments

We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.

Conclusion

We reviewed the relevant data and determined that air safety and
the public interest require adopting the AD as proposed except for
minor editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.

Costs of Compliance

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

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

The requirements of this 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 will be required based on the results of the 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.
----------------------------------------------------------------------------------------------------------------

[[Page 18035]]

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 AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under 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.

Adoption of the Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
99-15-04 R1, Amendment 39-11747 (65 FR 33745, May 25, 2000), and adding
the following new AD:

2011-06-10 Piper Aircraft, Inc. (Type Certificate Previously Held by
The New Piper Aircraft, Inc.): Amendment 39-16635; Docket No. FAA-
2010-1295; Directorate Identifier 2010-CE-060-AD.

Effective Date

(a) This airworthiness directive (AD) is effective May 6, 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-46-310P, PA-46-350P, and PA-46R-350T airplanes that are:
(1) Certificated in any category; and
(2) equipped with a turbine inlet temperature (T.I.T.) system
identified in table 3 of this AD. Relief from this AD is available
only if the gauge and probe are replaced through STC and not if a
second T.I.T. gauge was installed while retaining the Lewis or
Transicoil T.I.T. gauge and probe.

Table 1--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.
------------------------------------------------------------------------

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

Table 3--Affected Airplane Models and Corresponding Affected Turbine Inlet Temperature (T.I.T.) System
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------

[[Page 18036]]

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 T.I.T. 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 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.

Compliance

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

Table 4--Group 1 Airplanes (Airplanes Previously Affected by AD 99-15-04
R1)
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Clean and inspect the Within the next 100 Follow Piper
T.I.T. gauge and probe. hours time-in- Airplane
service (TIS) after Maintenance Manual
August 31, 1999 PA-46-310P/PA-46-
(the effective date 350P, Part Number
retained from AD 99- 761 783, Chapter
15-04). 77, section 77-20-
00 A.(1)(d), dated
July 1, 1998; and
Piper Airplane
Maintenance Manual
PA-46-350P/PA-46R-
350T, Part Number
761 876, Chapter
77, section 77-20-
00 1.C, page 1,
dated August 28,
2007, and page 2,
dated July 31,
2008, as
applicable.
(2) Calibrate the T.I.T. Within the next 100 Follow Piper
system. hours TIS after Airplane
August 31, 1999 Maintenance Manual
(the effective date PA-46-310P/PA-46-
retained from AD 99- 350P, Part Number
15-04). 761 783, Chapter
77, section 77-20-
00 A.(1)(g), dated
July 1, 1998; and
Piper Airplane
Maintenance Manual
PA-46-350P/PA-46R-
350T, Part Number
761 876, Chapter
77, section 77-20-
00 1.F, page 2,
dated July 31,
2008, and pages 3
and 4, dated August
28, 2007, as
applicable; or
Piper Service
Bulletin No. 995C,
dated November 17,
2009
(3) If the T.I.T. probe Before further Follow Piper
fails the inspection flight after the Airplane
required in paragraph cleaning and Maintenance Manual
(f)(1) of this AD and/or inspection required PA-46-310P/PA-46-
the T.I.T. system indicator in paragraph (f)(1) 350P, Part Number
cannot be calibrated as and the calibration 761 783, Chapter
required in paragraph required in 77, section 77-20-
(f)(2) of this AD, replace paragraph (f)(2) of 00 A.(1)(f), dated
any failed parts with a this AD. July 1, 1998; and
serviceable part listed in Piper Airplane
table 3 of this AD as long Maintenance Manual
as it has been inspected, PA-46-350P/PA-46R-
passed the inspection, and 350T, Part Number
been properly calibrated. 761 876, Chapter
77, section 77-20-
00 1.E., page 2,
dated July 31,
2008, as
applicable; or
Piper Service
Bulletin No. 995C,
dated November 17,
2009
(4) Incorporate the Within the next 100 Not applicable.
information from Appendix 1 hours TIS after
and Appendix 2, as August 31, 1999
applicable, of this AD into (the effective date
the Emergency Procedures retained from AD 99-
section of the pilot 15-04).
operating handbook (POH).
This may be done by
inserting a copy of this AD
into the POH.
(5) Only install a part As of July 28, 2000 Not applicable.
listed in table 3 of this (the effective date
AD after it has been of AD 99-15-04 R1).
inspected and properly
calibrated.
(6) Model PA-46-350P Upon accumulating For serial numbers
airplanes only: Replace the 250 hours TIS on 4622001 through
T.I.T. probe with a new the currently 4622200: Follow
part number 481-389, 481- installed T.I.T. Piper Airplane
392, or 686-216 probe probe or within the Maintenance Manual
(preferred). This action is next 100 hours TIS PA-46-310P/PA-46-
not required for Model PA- after August 31, 350P, Part Number
46-310P. 1999 (the effective 761 783, Chapter
date retained from 77, section 77-20-
AD 99-15-04), 00 A.(1)(f), dated
whichever occurs July 1, 1998; or
later, and Piper Service
thereafter at Bulletin No. 995C,
intervals not to dated November 17,
exceed 250 hours 2009.
TIS.
For serial numbers
4636001 through
4636020: Follow
Piper Airplane
Maintenance Manual
PA-46-350P/PA-46R-
350T, Part Number
761 876, Chapter
77, section 77-20-
00 1.E., page 2,
dated July 31,
2008; 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.

[[Page 18037]]

Table 5--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 T.I.T. this AD. PA-46-350P/PA-46R-
gauge and probe. 350T, Part Number
761 876, Chapter
77, section 77-20-
00 1.C, page 1,
dated August 28,
2007, and page 2,
dated July 31,
2008.
(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 T.I.T. probe fails the inspection required 2009.
inspection required in in paragraph (g)(1)
paragraph (g)(1) of this of this AD.
AD, replace any failed
parts with a serviceable
part listed in table 3 of
this AD as long as it has
been inspected and has
passed the inspection.
(3) All Group 2 airplanes: Upon accumulating Piper Service
Replace the T.I.T. probe 250 hours TIS on Bulletin No. 995C,
with a new part number 686- the currently dated November 17,
216 probe. installed T.I.T. 2009.
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 3 of this AD after
it has been inspected and
properly calibrated.
------------------------------------------------------------------------

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.

Material Incorporated by Reference

(j) You must use the service information contained in Table 6 of
this AD to do the actions required by this AD, unless the AD
specifies otherwise.

Table 6--All Material Incorporated by Reference
------------------------------------------------------------------------
Document Revision Date
------------------------------------------------------------------------
Piper Service Bulletin No. 995C N/A.................. November 17,
2009.
Piper Airplane Maintenance N/A.................. July 1, 1998.
Manual PA-46-310P/PA-46-350P,
Part Number 761 783, Chapter
77, ``Engine Indicating,''
Section 77-20-00, pages 1
through 4.
Piper Airplane Maintenance N/A.................. July 31, 2008.
Manual PA-46-350P/PA-46R-350T, Section 77-20-
Part Number 761 876, Chapter 00: pages 1, 3,
77, ``Engine Indicating,'' and 4, dated
Section 77-20-00, pages 1 August 28,
through 4. 2007; page 2,
dated July 31,
2008.
------------------------------------------------------------------------

(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact Piper
Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida 32960;
telephone: (772) 567-4361; fax: (772) 978-6573; Internet: https://www.piper.com/home/pages/publications.cfm.
(3) You may review copies of the 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.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at an NARA facility, call 202-741-6030, or go to https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

Appendix 1 to AD 2011-06-10--Model PA-46-310P (Malibu); 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.

[[Page 18038]]

Appendix 2 to AD 2011-06-10--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 March 9, 2011.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011-7569 Filed 3-31-11; 8:45 am]
BILLING CODE 4910-13-P

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