Airworthiness Directives; Piper Aircraft, Inc. Airplanes, 4214-4217 [2016-01380]

Download as PDF 4214 Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Proposed Rules participation in and compliance with USDA programs; and to improve current regulations to help USDA agencies advance the USDA mission. USDA is particularly interested in public comments that speak to areas in which we can reduce costs and reporting burdens on the public, through technological advances or other modernization efforts, and comments on regulatory flexibility. III. Regulatory Flexibility mstockstill on DSK4VPTVN1PROD with PROPOSALS IV. Existing USDA Regulations In addition to retrospective review actions and other regulatory reforms identified in USDA’s 2015 Fall Regulatory Agenda, we welcome comments from the public on any of USDA’s existing regulations and ways to improve them to help USDA agencies advance the mission of the Department consistent with the Executive Order. USDA notes that this RFI is issued solely for information and programplanning purposes. While responses to this RFI do not bind USDA to any further actions, all submissions will be reviewed by the appropriate program 17:48 Jan 25, 2016 Dated: January 7, 2016. Thomas J. Vilsack, Secretary. [FR Doc. 2016–00693 Filed 1–25–16; 8:45 am] BILLING CODE 3410–90–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration USDA is also seeking public input on measures that can be taken to reduce burdens and increase flexibility and freedom of choice for the public. Regulatory flexibility includes a variety of regulatory techniques that can help avoid unnecessary costs on regulated entities and avoid negative impacts. Regulatory flexibility techniques could include: • Pilot projects, which can be used to test regulatory approaches; • Safe harbors, which are streamlined modes of regulatory compliance and can serve to reduce compliance costs; • Sunset provisions, which terminate a rule after a certain date; • Trigger provisions, which specify one or more threshold indicators that the rule is designed to address; • Phase-ins, which allow the rule to be phased-in for different groups at different times; • Streamlined requirements, which provide exemptions or other streamlined requirements if a particular entity (for example, a small business) may otherwise experience disproportionate burden from a rule; • State flexibilities, which provide greater flexibility to States or other regulatory partners, for example, giving them freedom to implement alternative regulatory approaches; and • Exceptions, which allow exceptions to part of the rule, or the entire rule in cases where there is a potential or suspected unintended consequence. VerDate Sep<11>2014 office, and made publicly available on https://www.regulations.gov. Jkt 238001 14 CFR Part 39 [Docket No. FAA–2014–0338; Directorate Identifier 2014–CE–010–AD] RIN 2120–AA64 Airworthiness Directives; Piper Aircraft, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. AGENCY: We are revising an earlier proposed airworthiness directive (AD) for certain Piper Aircraft, Inc. Model PA–31–350 airplanes. The NPRM proposed to require inspecting the fuel hose assembly and the turbocharger support assembly for proper clearance between them, inspecting each assembly for any sign of damage, and making any necessary repairs or replacements. The NPRM was prompted by a report of an engine fire caused by a leak in the fuel pump inlet hose. This action revises the NPRM by requiring the use of revised procedures in a new service bulletin. We are proposing this supplemental NPRM (SNPRM) to correct the unsafe condition on these products. Since these actions impose an additional burden over that proposed in the NPRM, we are reopening the comment period to allow the public the chance to comment on these proposed changes. DATES: We must receive comments on this SNPRM by March 11, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, 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, SUMMARY: PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 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 Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida 32960; telephone: (772) 567–4361; fax: (772) 978–6573; Internet: www.piper.com/home/pages/ Publications.cfm. You may view this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, 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 by searching for and locating Docket No. FAA–2014– 0338; 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: Gary Wechsler, Aerospace Engineer, FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park, Georgia 30337; telephone: (404) 474– 5575; fax: (404) 474–5606; email: gary.wechsler@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–2014–0338; Directorate Identifier 2014–CE–010–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. E:\FR\FM\26JAP1.SGM 26JAP1 Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Proposed Rules Discussion We issued an NPRM to amend 14 CFR part 39 by adding an AD that would apply to certain Piper Aircraft, Inc. Model PA–31–350 airplanes. The NPRM published in the Federal Register on June 3, 2014 (79 FR 31888). The NPRM proposed to require inspecting the fuel hose assembly and the turbocharger support assembly for proper clearance between them, inspecting each assembly for any sign of damage, and making any necessary repairs or replacements. Actions Since Previous NPRM Was Issued Since we issued the NPRM (79 FR 31888, June 3, 2014), Piper Aircraft, Inc. has revised the related service information to clarify which engines are part of the airplane applicability and to revise the accomplishment instructions for inspecting for proper clearance between the fuel hose assembly and the turbocharger support assembly, inspecting the fuel hose assembly and the turbocharger support assembly for any signs of damage, and taking all necessary corrective actions. mstockstill on DSK4VPTVN1PROD with PROPOSALS Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM (79 FR 31888, June 3, 2014) and the FAA’s response to the comment. Request To Change the Applicability of the AD Joe Miller of Werbelow’s Air Ventures, Inc., requested that the Applicability section of the AD be changed so that it applies only to Piper Aircraft, Inc. Model PA–31–350 airplanes with TIO–540–J2B engine configurations. The commenter stated that Model PA–31–350 airplanes configured with TIO–540–J2B engines have fuel pumps orientated such that their inlet fuel hose assemblies can adversely contact a nearby turbocharger support assembly. The commenter also stated that the other type certificated engine configurations of applicable Model PA– 31–350 airplanes have engine fuel pumps orientated such that their inlet fuel hose assemblies cannot adversely contact the nearby turbocharger support assembly. The commenter requested that the AD exclude Model PA–31–350 airplanes that have the fuel pump installed on a Lycoming (L)TIO–540–J2BD engine. We partially agree with the commenter. We agree that there is more than one orientation for the engine fuel pump in the applicable Model PA–31– 350 airplanes with (L)TIO–540 series engines because this is shown in the Lycoming parts catalog for the TIO, LTIO–540–J2B, and –J2BD engines, which were type certificated on the Model PA–31–350 airplane. We disagree with the commenter’s request to change the actions of the AD so that they apply only to the inlet hose assembly for the engine fuel pump of the TIO–540–J2B engine configuration of applicable Model PA–31–350 airplanes. We reviewed the Lycoming parts catalog for the TIO, LTIO–540–J2B, and –J2BD engines and applicable Model PA–31–350 airplanes with (L)TIO–540–J2BD engines and found that the TIO and LTIO–540–J2B and –J2BD engines each have a fuel pump with one fuel hose assembly (either and inlet or exit) that can be incorrectly installed so that it is in contact with the nearby turbocharger support assembly. Related Service Information Under 1 CFR Part 51 We reviewed Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015. The service information describes procedures for the following. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this SNPRM. —Inspecting for a minimum 3/16-inch clearance between the fuel hose assembly and the turbocharger support assembly and making any necessary adjustments. —Inspecting the fuel hose assembly for any signs of damage and, if necessary, replacing with a serviceable part. —Inspecting the turbocharger support assembly for any signs of damage and, if necessary, repairing or replacing with a serviceable part. —Performing an engine run-up to check for any leaks. FAA’s Determination We are proposing this SNPRM because we evaluated all the relevant 4215 information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Certain changes described above expand the scope of the NPRM (79 FR 31888, June 3, 2014). As a result, we have determined that it is necessary to reopen the comment period to provide additional opportunity for the public to comment on this SNPRM. Proposed Requirements of This SNPRM This SNPRM would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between this Proposed AD and the Service Information.’’ Differences Between This SNPRM and the Service Information There are differences between the compliance times for the corrective actions in this proposed AD and those in the related service information. We based the compliance times in this proposed AD on risk analysis and cost impact to operators. There has only been one event of the reported incident in the operational history of Piper Model PA–31–350 airplanes. Cost was also a strong consideration due to the age of the fleet and the number of airplanes still in service. The one-time inspection required in this proposed AD is very inexpensive and requires minimal time to accomplish. It is expected that almost all airplanes in service can be cleared with a single inspection, and no additional actions or costs would be incurred by the vast majority of the fleet. We determined that a single inspection with any necessary corrective actions is an adequate terminating action for the unsafe condition. The risk related to future maintenance on the fuel line would be mitigated by the related service information and awareness from this proposed AD. Costs of Compliance We estimate that this proposed AD affects 773 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Inspect for proper clearance between the fuel hose assembly and the turbocharger support assembly. .5 work-hour × $85 per hour = $85. VerDate Sep<11>2014 17:48 Jan 25, 2016 Jkt 238001 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 Parts cost E:\FR\FM\26JAP1.SGM N/A 26JAP1 Cost per product $42.50 Cost on U.S. operators $32,852.50 4216 Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Proposed Rules ESTIMATED COSTS—Continued Action Labor cost Inspect the fuel hose assembly for evidence of leaking, cracking, chafing, and any other sign of damage. Inspect the turbocharger support assembly for evidence of chafing and any other sign of damage. Engine run-up/leak check ........................................................ .5 work-hour × $85 per hour = $42.50. .5 work-hour × $85 per hour = $42.50. 1 work-hour × $85 = $85 (.5 work hour per engine). We estimate the following costs to do any necessary follow-on actions that Cost per product Parts cost will be required based on the results of the inspection. We have no way of Cost on U.S. operators N/A 42.50 32,852.50 N/A 42.50 32,852.50 N/A 85.00 65,705.00 determining the number of airplanes that might need these corrective actions. ON-CONDITION COSTS Action Labor cost Adjust routing of fuel hose assembly for proper clearance between the fuel hose assembly and the turbocharger support assembly. Replace Piper fuel pump inlet hose assembly, part number 39995–34 (2 per airplane). Replace Lycoming turbocharger support assembly, part number LW– 18302 (2 per airplane). 5.5 work-hours × $85 per hour = $467.50. 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. mstockstill on DSK4VPTVN1PROD with PROPOSALS Regulatory Findings We 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 Parts cost N/A 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: $467.50 $1,068 1,153.00 12,874 24 work-hours × $85 per hour = $2,040. the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this 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. Cost per product 14,914.00 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 adding the following new airworthiness directive (AD): ■ Piper Aircraft, Inc.: FAA–2014–0338; Directorate Identifier 2014–CE–010–AD. (a) Comments Due Date We must receive comments by March 11, 2016. (b) Affected ADs None. (c) Applicability This AD applies to Piper Aircraft, Inc. Model PA–31–350 airplanes, serial numbers 31–5001 through 31–5004, 31–7305005 through 31–8452024, and 31–8253001 through 31–8553002, certificated in any category, that are equipped with the following engines and fuel pump hose assemblies: TABLE 1 TO PARAGRAPH (C) OF THIS AD—APPLICABLE ENGINES AND FUEL PUMP HOSE ASSEMBLIES Engine Manufacturer’s hose name Manufacturer’s part No. (P/N) Hose description TIO–540–J2B (right wing) .............. Hose Assembly—Fuel .................. Piper 39995–034 .......................... LTIO–540–J2B (left wing) .............. Hose, Fuel pump to Injector ......... Lycoming LW–12877–6S142 ....... TIO540–J2BD (right wing) ............. Hose, Fuel pump to Injector ......... Lycoming LW–12877–6S142 ....... Inlet fuel hose to engine fuel pump. Exit fuel hose from engine fuel pump. Exit fuel hose from engine fuel pump. VerDate Sep<11>2014 17:48 Jan 25, 2016 Jkt 238001 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 E:\FR\FM\26JAP1.SGM 26JAP1 Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Proposed Rules 4217 TABLE 1 TO PARAGRAPH (C) OF THIS AD—APPLICABLE ENGINES AND FUEL PUMP HOSE ASSEMBLIES—Continued Engine Manufacturer’s hose name Manufacturer’s part No. (P/N) Hose description LTIO–540–J2BD (left wing) ........... Hose Assembly—Fuel .................. Piper 39995–034 .......................... Inlet fuel hose to engine fuel pump. (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 73: Engine Fuel and Control. (e) Unsafe Condition This AD was prompted by a report of an engine fire caused by a leak in the fuel pump inlet hose. We are issuing this AD to correct the unsafe condition on these products. (f) Compliance Comply with this AD within the compliance times specified in paragraphs (g)(1) through (j)(2) of this AD, unless already done. mstockstill on DSK4VPTVN1PROD with PROPOSALS (g) Ensure Proper Clearance Between the Fuel Hose Assembly and the Turbocharger Support Assembly (1) Within the next 60 hours time-inservice (TIS) after the effective date of this AD or within the next 6 months after the effective date of this AD, whichever occurs first, inspect to determine the clearance between the inlet and exit fuel hose assemblies listed in table 1 to paragraph (c) of this AD, and each turbocharger support assembly, Lycoming P/N LW–18302. There should be a minimum 3⁄16-inch clearance. Do the inspection following the INSTRUCTIONS section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015. (2) Before further flight after the inspection required in paragraph (g)(1) of this AD, if the measured clearance is less than 3⁄16-inch, make all necessary adjustments to make the clearance a minimum of 3⁄16-inch between the inlet and exit fuel hose assemblies listed in table 1 to paragraph (c) of this AD and each turbocharger support assembly, Lycoming P/N LW–18302, following the INSTRUCTIONS section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015. (h) Visually Inspect the Fuel Hose Assembly and Replace if Necessary (1) Within the next 60 hours TIS after the effective date of this AD or within the next 6 months after the effective date of this AD, whichever occurs first, visually inspect the inlet and exit fuel hose assemblies listed in table 1 to paragraph (c) of this AD for evidence of leaking, cracking, chafing, and any other sign of damage. Do the inspection following the INSTRUCTIONS section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015. (2) Before further flight after the inspection required in paragraph (h)(1) of this AD, if any evidence of leaking, cracking, chafing, or any other sign of damage is found in any inlet or exit fuel host assembly listed in table 1 to paragraph (c) of this AD, replace the fuel hose assembly with a serviceable part. Do the replacement following the INSTRUCTIONS VerDate Sep<11>2014 17:48 Jan 25, 2016 Jkt 238001 section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015. (i) Visually Inspect the Turbocharger Support Assembly and Replace if Necessary (1) Within the next 60 hours TIS after the effective date of this AD or within the next 6 months after the effective date of this AD, whichever occurs first, visually inspect each turbocharger support assembly, Lycoming P/ N LW–18302, for evidence of chafing and any other signs of damage. Do the inspection following the INSTRUCTIONS section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015. (2) Before further flight after the inspection required in paragraph (i)(1) of this AD, if any evidence of chafing or any other sign of damage is found on any turbocharger support assembly, replace Lycoming P/N LW–18302 with a serviceable part. Do the replacement following the INSTRUCTIONS section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015. FAA, Atlanta ACO, 1701 Columbia Avenue, College Park, Georgia 30337; telephone: (404) 474–5575; fax: (404) 474–5606; email: gary.wechsler@faa.gov. (2) For service information identified in this AD, contact Piper Aircraft, Inc., 926 Piper Drive, Vero Beach, Florida 32960; telephone: (772) 567–4361; fax: (772) 978– 6573; Internet: www.piper.com/home/pages/ Publications.cfm. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. Issued in Kansas City, Missouri, on January 16, 2016. Melvin Johnson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–01380 Filed 1–25–16; 8:45 am] BILLING CODE 4910–13–P (j) Engine Run-Up (1) If any fuel line component was adjusted or replaced during any actions required in paragraphs (g)(1) through (i)(2) of this AD, before further flight, perform an engine runup on the ground to check for leaks. Do the engine run-up following the INSTRUCTIONS section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015. (2) If any leaks found during the engine run-up required in paragraph (j)(1) of this AD emanate from any fuel line component adjusted, repaired, or replaced during any actions required in paragraphs (g)(1) through (i)(2) of this AD, before further flight, take all necessary corrective actions following the INSTRUCTIONS section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015. DEPARTMENT OF TRANSPORTATION (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Atlanta Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. 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 appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. SUMMARY: (l) Related Information (1) For more information about this AD, contact Gary Wechsler, Aerospace Engineer, PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–1363; Directorate Identifier 2015–CE–040–AD] RIN 2120–AA64 Airworthiness Directives; Mitsubishi Heavy Industries, Ltd. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Mitsubishi Heavy Industries, Ltd. Models MU–2B–30, MU–2B–35, MU– 2B–36, MU–2B–36A, and MU–2B–60 airplanes. This proposed 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 reports of cracks found in the attach fittings of the main landing gear oleo strut. We are issuing this proposed AD to require actions to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by March 11, 2016. E:\FR\FM\26JAP1.SGM 26JAP1

Agencies

[Federal Register Volume 81, Number 16 (Tuesday, January 26, 2016)]
[Proposed Rules]
[Pages 4214-4217]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-01380]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0338; Directorate Identifier 2014-CE-010-AD]
RIN 2120-AA64


Airworthiness Directives; Piper Aircraft, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

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

SUMMARY: We are revising an earlier proposed airworthiness directive 
(AD) for certain Piper Aircraft, Inc. Model PA-31-350 airplanes. The 
NPRM proposed to require inspecting the fuel hose assembly and the 
turbocharger support assembly for proper clearance between them, 
inspecting each assembly for any sign of damage, and making any 
necessary repairs or replacements. The NPRM was prompted by a report of 
an engine fire caused by a leak in the fuel pump inlet hose. This 
action revises the NPRM by requiring the use of revised procedures in a 
new service bulletin. We are proposing this supplemental NPRM (SNPRM) 
to correct the unsafe condition on these products. Since these actions 
impose an additional burden over that proposed in the NPRM, we are 
reopening the comment period to allow the public the chance to comment 
on these proposed changes.

DATES: We must receive comments on this SNPRM by March 11, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, 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 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida 32960; 
telephone: (772) 567-4361; fax: (772) 978-6573; Internet: 
www.piper.com/home/pages/Publications.cfm. You may view this referenced 
service information at the FAA, Small Airplane Directorate, 901 Locust, 
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 by searching for and locating Docket No. FAA-2014-
0338; 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: Gary Wechsler, Aerospace Engineer, 
FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, 
College Park, Georgia 30337; telephone: (404) 474-5575; fax: (404) 474-
5606; email: gary.wechsler@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-2014-0338; 
Directorate Identifier 2014-CE-010-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.

[[Page 4215]]

Discussion

    We issued an NPRM to amend 14 CFR part 39 by adding an AD that 
would apply to certain Piper Aircraft, Inc. Model PA-31-350 airplanes. 
The NPRM published in the Federal Register on June 3, 2014 (79 FR 
31888). The NPRM proposed to require inspecting the fuel hose assembly 
and the turbocharger support assembly for proper clearance between 
them, inspecting each assembly for any sign of damage, and making any 
necessary repairs or replacements.

Actions Since Previous NPRM Was Issued

    Since we issued the NPRM (79 FR 31888, June 3, 2014), Piper 
Aircraft, Inc. has revised the related service information to clarify 
which engines are part of the airplane applicability and to revise the 
accomplishment instructions for inspecting for proper clearance between 
the fuel hose assembly and the turbocharger support assembly, 
inspecting the fuel hose assembly and the turbocharger support assembly 
for any signs of damage, and taking all necessary corrective actions.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the NPRM (79 FR 
31888, June 3, 2014) and the FAA's response to the comment.

Request To Change the Applicability of the AD

    Joe Miller of Werbelow's Air Ventures, Inc., requested that the 
Applicability section of the AD be changed so that it applies only to 
Piper Aircraft, Inc. Model PA-31-350 airplanes with TIO-540-J2B engine 
configurations.
    The commenter stated that Model PA-31-350 airplanes configured with 
TIO-540-J2B engines have fuel pumps orientated such that their inlet 
fuel hose assemblies can adversely contact a nearby turbocharger 
support assembly. The commenter also stated that the other type 
certificated engine configurations of applicable Model PA-31-350 
airplanes have engine fuel pumps orientated such that their inlet fuel 
hose assemblies cannot adversely contact the nearby turbocharger 
support assembly.
    The commenter requested that the AD exclude Model PA-31-350 
airplanes that have the fuel pump installed on a Lycoming (L)TIO-540-
J2BD engine.
    We partially agree with the commenter. We agree that there is more 
than one orientation for the engine fuel pump in the applicable Model 
PA-31-350 airplanes with (L)TIO-540 series engines because this is 
shown in the Lycoming parts catalog for the TIO, LTIO-540-J2B, and -
J2BD engines, which were type certificated on the Model PA-31-350 
airplane.
    We disagree with the commenter's request to change the actions of 
the AD so that they apply only to the inlet hose assembly for the 
engine fuel pump of the TIO-540-J2B engine configuration of applicable 
Model PA-31-350 airplanes. We reviewed the Lycoming parts catalog for 
the TIO, LTIO-540-J2B, and -J2BD engines and applicable Model PA-31-350 
airplanes with (L)TIO-540-J2BD engines and found that the TIO and LTIO-
540-J2B and -J2BD engines each have a fuel pump with one fuel hose 
assembly (either and inlet or exit) that can be incorrectly installed 
so that it is in contact with the nearby turbocharger support assembly.

Related Service Information Under 1 CFR Part 51

    We reviewed Piper Aircraft, Inc. Service Bulletin No. 1257A, dated 
August 4, 2015. The service information describes procedures for the 
following. This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section of this 
SNPRM.

--Inspecting for a minimum 3/16-inch clearance between the fuel hose 
assembly and the turbocharger support assembly and making any necessary 
adjustments.
--Inspecting the fuel hose assembly for any signs of damage and, if 
necessary, replacing with a serviceable part.
--Inspecting the turbocharger support assembly for any signs of damage 
and, if necessary, repairing or replacing with a serviceable part.
--Performing an engine run-up to check for any leaks.

FAA's Determination

    We are proposing this SNPRM 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. 
Certain changes described above expand the scope of the NPRM (79 FR 
31888, June 3, 2014). As a result, we have determined that it is 
necessary to reopen the comment period to provide additional 
opportunity for the public to comment on this SNPRM.

Proposed Requirements of This SNPRM

    This SNPRM would require accomplishing the actions specified in the 
service information described previously, except as discussed under 
``Differences Between this Proposed AD and the Service Information.''

Differences Between This SNPRM and the Service Information

    There are differences between the compliance times for the 
corrective actions in this proposed AD and those in the related service 
information.
    We based the compliance times in this proposed AD on risk analysis 
and cost impact to operators. There has only been one event of the 
reported incident in the operational history of Piper Model PA-31-350 
airplanes. Cost was also a strong consideration due to the age of the 
fleet and the number of airplanes still in service.
    The one-time inspection required in this proposed AD is very 
inexpensive and requires minimal time to accomplish. It is expected 
that almost all airplanes in service can be cleared with a single 
inspection, and no additional actions or costs would be incurred by the 
vast majority of the fleet.
    We determined that a single inspection with any necessary 
corrective actions is an adequate terminating action for the unsafe 
condition. The risk related to future maintenance on the fuel line 
would be mitigated by the related service information and awareness 
from this proposed AD.

Costs of Compliance

    We estimate that this proposed AD affects 773 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
----------------------------------------------------------------------------------------------------------------
Inspect for proper clearance between    .5 work-hour x $85 per               N/A          $42.50      $32,852.50
 the fuel hose assembly and the          hour = $85.
 turbocharger support assembly.

[[Page 4216]]

 
Inspect the fuel hose assembly for      .5 work-hour x $85 per               N/A           42.50       32,852.50
 evidence of leaking, cracking,          hour = $42.50.
 chafing, and any other sign of damage.
Inspect the turbocharger support        .5 work-hour x $85 per               N/A           42.50       32,852.50
 assembly for evidence of chafing and    hour = $42.50.
 any other sign of damage.
Engine run-up/leak check..............  1 work-hour x $85 = $85              N/A           85.00       65,705.00
                                         (.5 work hour per
                                         engine).
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary follow-on 
actions that will be required based on the results of the inspection. 
We have no way of determining the number of airplanes that might need 
these corrective actions.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Adjust routing of fuel hose assembly for        5.5 work-hours x $85 per hour =              N/A         $467.50
 proper clearance between the fuel hose          $467.50.
 assembly and the turbocharger support
 assembly.
Replace Piper fuel pump inlet hose assembly,    1 work-hour x $85 per hour = $85          $1,068        1,153.00
 part number 39995-34 (2 per airplane).
Replace Lycoming turbocharger support           24 work-hours x $85 per hour =            12,874       14,914.00
 assembly, part number LW-18302 (2 per           $2,040.
 airplane).
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation Programs'' 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this 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 this 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

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 adding the following new airworthiness 
directive (AD):

Piper Aircraft, Inc.: FAA-2014-0338; Directorate Identifier 2014-CE-
010-AD.

(a) Comments Due Date

    We must receive comments by March 11, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Piper Aircraft, Inc. Model PA-31-350 
airplanes, serial numbers 31-5001 through 31-5004, 31-7305005 
through 31-8452024, and 31-8253001 through 31-8553002, certificated 
in any category, that are equipped with the following engines and 
fuel pump hose assemblies:

              Table 1 to Paragraph (c) of This AD--Applicable Engines and Fuel Pump Hose Assemblies
----------------------------------------------------------------------------------------------------------------
                                         Manufacturer's hose    Manufacturer's part No.
                Engine                           name                    (P/N)               Hose description
----------------------------------------------------------------------------------------------------------------
TIO-540-J2B (right wing).............  Hose Assembly--Fuel....  Piper 39995-034........  Inlet fuel hose to
                                                                                          engine fuel pump.
LTIO-540-J2B (left wing).............  Hose, Fuel pump to       Lycoming LW-12877-6S142  Exit fuel hose from
                                        Injector.                                         engine fuel pump.
TIO540-J2BD (right wing).............  Hose, Fuel pump to       Lycoming LW-12877-6S142  Exit fuel hose from
                                        Injector.                                         engine fuel pump.

[[Page 4217]]

 
LTIO-540-J2BD (left wing)............  Hose Assembly--Fuel....  Piper 39995-034........  Inlet fuel hose to
                                                                                          engine fuel pump.
----------------------------------------------------------------------------------------------------------------

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 73: Engine Fuel and Control.

(e) Unsafe Condition

    This AD was prompted by a report of an engine fire caused by a 
leak in the fuel pump inlet hose. We are issuing this AD to correct 
the unsafe condition on these products.

(f) Compliance

    Comply with this AD within the compliance times specified in 
paragraphs (g)(1) through (j)(2) of this AD, unless already done.

(g) Ensure Proper Clearance Between the Fuel Hose Assembly and the 
Turbocharger Support Assembly

    (1) Within the next 60 hours time-in-service (TIS) after the 
effective date of this AD or within the next 6 months after the 
effective date of this AD, whichever occurs first, inspect to 
determine the clearance between the inlet and exit fuel hose 
assemblies listed in table 1 to paragraph (c) of this AD, and each 
turbocharger support assembly, Lycoming P/N LW-18302. There should 
be a minimum \3/16\-inch clearance. Do the inspection following the 
INSTRUCTIONS section of Piper Aircraft, Inc. Service Bulletin No. 
1257A, dated August 4, 2015.
    (2) Before further flight after the inspection required in 
paragraph (g)(1) of this AD, if the measured clearance is less than 
\3/16\-inch, make all necessary adjustments to make the clearance a 
minimum of \3/16\-inch between the inlet and exit fuel hose 
assemblies listed in table 1 to paragraph (c) of this AD and each 
turbocharger support assembly, Lycoming P/N LW-18302, following the 
INSTRUCTIONS section of Piper Aircraft, Inc. Service Bulletin No. 
1257A, dated August 4, 2015.

(h) Visually Inspect the Fuel Hose Assembly and Replace if Necessary

    (1) Within the next 60 hours TIS after the effective date of 
this AD or within the next 6 months after the effective date of this 
AD, whichever occurs first, visually inspect the inlet and exit fuel 
hose assemblies listed in table 1 to paragraph (c) of this AD for 
evidence of leaking, cracking, chafing, and any other sign of 
damage. Do the inspection following the INSTRUCTIONS section of 
Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 
2015.
    (2) Before further flight after the inspection required in 
paragraph (h)(1) of this AD, if any evidence of leaking, cracking, 
chafing, or any other sign of damage is found in any inlet or exit 
fuel host assembly listed in table 1 to paragraph (c) of this AD, 
replace the fuel hose assembly with a serviceable part. Do the 
replacement following the INSTRUCTIONS section of Piper Aircraft, 
Inc. Service Bulletin No. 1257A, dated August 4, 2015.

(i) Visually Inspect the Turbocharger Support Assembly and Replace if 
Necessary

    (1) Within the next 60 hours TIS after the effective date of 
this AD or within the next 6 months after the effective date of this 
AD, whichever occurs first, visually inspect each turbocharger 
support assembly, Lycoming P/N LW-18302, for evidence of chafing and 
any other signs of damage. Do the inspection following the 
INSTRUCTIONS section of Piper Aircraft, Inc. Service Bulletin No. 
1257A, dated August 4, 2015.
    (2) Before further flight after the inspection required in 
paragraph (i)(1) of this AD, if any evidence of chafing or any other 
sign of damage is found on any turbocharger support assembly, 
replace Lycoming P/N LW-18302 with a serviceable part. Do the 
replacement following the INSTRUCTIONS section of Piper Aircraft, 
Inc. Service Bulletin No. 1257A, dated August 4, 2015.

(j) Engine Run-Up

    (1) If any fuel line component was adjusted or replaced during 
any actions required in paragraphs (g)(1) through (i)(2) of this AD, 
before further flight, perform an engine run-up on the ground to 
check for leaks. Do the engine run-up following the INSTRUCTIONS 
section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated 
August 4, 2015.
    (2) If any leaks found during the engine run-up required in 
paragraph (j)(1) of this AD emanate from any fuel line component 
adjusted, repaired, or replaced during any actions required in 
paragraphs (g)(1) through (i)(2) of this AD, before further flight, 
take all necessary corrective actions following the INSTRUCTIONS 
section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated 
August 4, 2015.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Atlanta Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. 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 appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(l) Related Information

    (1) For more information about this AD, contact Gary Wechsler, 
Aerospace Engineer, FAA, Atlanta ACO, 1701 Columbia Avenue, College 
Park, Georgia 30337; telephone: (404) 474-5575; fax: (404) 474-5606; 
email: gary.wechsler@faa.gov.
    (2) For service information identified in this AD, contact Piper 
Aircraft, Inc., 926 Piper Drive, Vero Beach, Florida 32960; 
telephone: (772) 567-4361; fax: (772) 978-6573; Internet: 
www.piper.com/home/pages/Publications.cfm. You may review copies of 
the referenced service information at the FAA, Small Airplane 
Directorate, 901 Locust, Kansas City, Missouri 64106. For 
information on the availability of this material at the FAA, call 
(816) 329-4148.

    Issued in Kansas City, Missouri, on January 16, 2016.
Melvin Johnson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-01380 Filed 1-25-16; 8:45 am]
 BILLING CODE 4910-13-P
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