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 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: 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: 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 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 https:// 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: https://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 https://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 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 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]

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

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 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: 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: 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 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 https://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: https://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

This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.