81 FR 26106 - Airworthiness Directives; Piper Aircraft, Inc. Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 84 (May 2, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 84 (May 2, 2016)
| Page Range | 26106-26109 | |
| FR Document | 2016-09238 |
[Federal Register Volume 81, Number 84 (Monday, May 2, 2016)] [Rules and Regulations] [Pages 26106-26109] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-09238] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2014-0338; Directorate Identifier 2014-CE-010-AD; Amendment 39-18495; AD 2016-08-18] RIN 2120-AA64 Airworthiness Directives; Piper Aircraft, Inc. Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. Model PA-31-350 airplanes. This AD was prompted by a report of an engine fire caused by a leak in the fuel pump inlet hose. This AD requires 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. We are issuing this AD to correct the unsafe condition on these products. DATES: This AD is effective June 6, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 6, 2016. ADDRESSES: For service information identified in this final rule, 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. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-0338. Examining the AD Docket You may examine the AD docket on the Internet at http://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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800-647- 5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: 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: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Piper Aircraft, Inc. Model PA-31-350 airplanes. The SNPRM published in the Federal Register on January 26, 2016 (81 FR 4214). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that 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. The NPRM was prompted by a report of an engine fire on a Piper Aircraft, Inc. (Piper) Model PA-31-350 airplane. Investigation revealed that the fire was caused by a leak in the fuel pump inlet hose that resulted from repeated contact with an adjacent turbocharger support assembly caused by inadequate clearance between the two assemblies. The SNPRM proposed to require the same actions as proposed in the NPRM using revised service information issued by the manufacturer to clarify which engines are part of the airplane applicability and to revise the instructions for accomplishing the proposed actions. This condition, if not corrected, could result in damage to the fuel inlet hose assembly, which could cause the fuel pump inlet hose to fail and leak fuel in the engine compartment. This condition could also cause damage to the turbocharger support assembly, which could require the turbocharger support assembly to be repaired or replaced. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the SNPRM (81 FR 4214, January 26, 2016) or on the determination of the cost to the public. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the SNPRM (81 FR 4214, January 26, 2016) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the SNPRM (81 FR 4214, January 26, 2016). 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 [[Page 26107]] available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. --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. Differences Between This AD and the Service Information There are differences between the compliance times for the corrective actions in this AD and those in the related service information. We based the compliance times in this 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 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 AD. Costs of Compliance We estimate that this AD affects 773 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on Action Labor cost Parts cost Cost per U.S. product operators ---------------------------------------------------------------------------------------------------------------- Inspect for proper clearance between the .5 work-hour x $85 per hour = N/A $42.50 $32,852.50 fuel hose assembly and the turbocharger $85. support assembly. Inspect the fuel hose assembly for evidence .5 work-hour x $85 per hour = N/A 42.50 32,852.50 of leaking, cracking, chafing, and any $42.50. other sign of damage. Inspect the turbocharger support assembly .5 work-hour x $85 per hour = N/A 42.50 32,852.50 for evidence of chafing and any other sign $42.50. of damage. Engine run-up/leak check................... 1 work-hour x $85 = $85 (.5 N/A 85 65,705 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 5.5 work-hours x N/A $467.50 assembly for proper clearance $85 per hour = between the fuel hose $467.50. assembly and the turbocharger support assembly. Replace Piper fuel pump inlet 1 work-hour x 1,068 1,153 hose assembly, part number $85 per hour = 39995-34 (2 per airplane). $85. Replace Lycoming turbocharger 24 work-hours x 12,874 14,914 support assembly, part number $85 per hour = LW-18302 (2 per airplane). $2,040. ------------------------------------------------------------------------ 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 This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. [[Page 26108]] Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2016-08-18 Piper Aircraft, Inc.: Amendment 39-18495; Docket No. FAA- 2014-0338; Directorate Identifier 2014-CE-010-AD. (a) Effective Date This AD is effective June 6, 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 Engine name number (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. 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 June 6, 2016 (the effective date of this AD) or within the next 6 months after June 6, 2016 (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 June 6, 2016 (the effective date of this AD) or within the next 6 months after June 6, 2016 (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 June 6, 2016 (the effective date of this AD) or within the next 6 months after June 6, 2016 (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 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: [email protected]. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015. (ii) Reserved. [[Page 26109]] (3) For Piper Aircraft, Inc. 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. (4) You may view this service information at 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Kansas City, Missouri, on April 14, 2016. Robert P. Busto, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-09238 Filed 4-29-16; 8:45 am] BILLING CODE 4910-13-P
![26106 Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations
(2) The subject of this AD is addressed in Piper Aircraft, Inc. Model PA–31–350 airplanes. The SNPRM published in the
European Aviation Safety Agency (EASA) AD airplanes. This AD was prompted by a Federal Register on January 26, 2016
No. 2015–0033–E, dated February 24, 2015. report of an engine fire caused by a leak (81 FR 4214). We preceded the SNPRM
You may view the EASA AD on the Internet in the fuel pump inlet hose. This AD with a notice of proposed rulemaking
at http://www.regulations.gov in Docket No.
FAA–2015–3970.
requires inspecting the fuel hose (NPRM) that published in the Federal
assembly and the turbocharger support Register on June 3, 2014 (79 FR 31888).
(j) Subject assembly for proper clearance between The NPRM proposed to require
Joint Aircraft Service Component (JASC) them, inspecting each assembly for any inspecting the fuel hose assembly and
Code: 5302: Rotorcraft Tailboom. sign of damage, and making any the turbocharger support assembly for
(k) Material Incorporated by Reference necessary repairs or replacements. We proper clearance between them,
are issuing this AD to correct the unsafe inspecting each assembly for any sign of
(1) The Director of the Federal Register
approved the incorporation by reference of
condition on these products. damage, and making any necessary
the service information listed in this DATES: This AD is effective June 6, 2016. repairs or replacements. The NPRM was
paragraph under 5 U.S.C. 552(a) and 1 CFR The Director of the Federal Register prompted by a report of an engine fire
part 51. approved the incorporation by reference on a Piper Aircraft, Inc. (Piper) Model
(2) You must use this service information of a certain publication listed in this AD PA–31–350 airplane. Investigation
as applicable to do the actions required by as of June 6, 2016. revealed that the fire was caused by a
this AD, unless the AD specifies otherwise. leak in the fuel pump inlet hose that
ADDRESSES: For service information
(i) Airbus Helicopters Emergency Alert resulted from repeated contact with an
Service Bulletin No. 05A017, Revision 2, identified in this final rule, contact
Piper Aircraft, Inc., 2926 Piper Drive, adjacent turbocharger support assembly
dated February 20, 2015.
(ii) Reserved. Vero Beach, Florida 32960; telephone: caused by inadequate clearance between
(3) For Airbus Helicopters service (772) 567–4361; fax: (772) 978–6573; the two assemblies. The SNPRM
information identified in this final rule, Internet: www.piper.com/home/pages/ proposed to require the same actions as
contact Airbus Helicopters, Inc., 2701 N. Publications.cfm. You may view this proposed in the NPRM using revised
Forum Drive, Grand Prairie, TX 75052; referenced service information at the service information issued by the
telephone (972) 641–0000 or (800) 232–0323; FAA, Small Airplane Directorate, 901 manufacturer to clarify which engines
fax (972) 641–3775; or at http:// are part of the airplane applicability and
Locust, Kansas City, Missouri 64106.
www.airbushelicopters.com/techpub. to revise the instructions for
(4) You may view this service information For information on the availability of
this material at the FAA, call (816) 329– accomplishing the proposed actions.
at FAA, Office of the Regional Counsel,
4148. It is also available on the internet This condition, if not corrected, could
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177. For at http://www.regulations.gov by result in damage to the fuel inlet hose
information on the availability of this searching for and locating Docket No. assembly, which could cause the fuel
material at the FAA, call (817) 222–5110. FAA–2014–0338. pump inlet hose to fail and leak fuel in
(5) You may view this service information the engine compartment. This condition
that is incorporated by reference at the Examining the AD Docket could also cause damage to the
National Archives and Records You may examine the AD docket on turbocharger support assembly, which
Administration (NARA). For information on the Internet at http:// could require the turbocharger support
the availability of this material at NARA, call assembly to be repaired or replaced.
(202) 741–6030, or go to: http://
www.regulations.gov by searching for
www.archives.gov/federal-register/cfr/ibr- and locating Docket No. FAA–2014– Comments
locations.html. 0338; or in person at the Docket
Management Facility between 9 a.m. We gave the public the opportunity to
Issued in Fort Worth, Texas, on April 15, participate in developing this AD. We
2016.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket received no comments on the SNPRM
Scott A. Horn, (81 FR 4214, January 26, 2016) or on the
contains this AD, the regulatory
Acting Manager, Rotorcraft Directorate, evaluation, any comments received, and determination of the cost to the public.
Aircraft Certification Service.
other information. The address for the Conclusion
[FR Doc. 2016–09235 Filed 4–29–16; 8:45 am]
Docket Office (phone: 800–647–5527) is
BILLING CODE 4910–13–P We reviewed the relevant data and
Document Management Facility, U.S.
determined that air safety and the
Department of Transportation, Docket
public interest require adopting this AD
Operations, M–30, West Building
DEPARTMENT OF TRANSPORTATION as proposed except for minor editorial
Ground Floor, Room W12–140, 1200
changes. We have determined that these
Federal Aviation Administration New Jersey Avenue SE., Washington,
minor changes:
DC 20590. • Are consistent with the intent that
14 CFR Part 39 FOR FURTHER INFORMATION CONTACT: Gary was proposed in the SNPRM (81 FR
Wechsler, Aerospace Engineer, FAA, 4214, January 26, 2016) for correcting
[Docket No. FAA–2014–0338; Directorate Atlanta Aircraft Certification Office,
Identifier 2014–CE–010–AD; Amendment the unsafe condition; and
39–18495; AD 2016–08–18]
1701 Columbia Avenue, College Park, • Do not add any additional burden
Georgia 30337; telephone: (404) 474– upon the public than was already
RIN 2120–AA64 5575; fax: (404) 474–5606; email: proposed in the SNPRM (81 FR 4214,
gary.wechsler@faa.gov. January 26, 2016).
Airworthiness Directives; Piper SUPPLEMENTARY INFORMATION:
mstockstill on DSK3G9T082PROD with RULES
Aircraft, Inc. Airplanes Related Service Information Under 1
Discussion CFR Part 51
AGENCY: Federal Aviation
Administration (FAA), DOT. We issued a supplemental notice of We reviewed Piper Aircraft, Inc.
ACTION: Final rule. proposed rulemaking (SNPRM) to Service Bulletin No. 1257A, dated
amend 14 CFR part 39 by adding an AD August 4, 2015. The service information
SUMMARY: We are adopting a new that would apply to certain Piper describes procedures for the following.
airworthiness directive (AD) for certain Aircraft, Inc. Model PA–31–350 This service information is reasonably
VerDate Sep<11>2014 17:39 Apr 29, 2016 Jkt 238001 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 E:\FR\FM\02MYR1.SGM 02MYR1](https://thefederalregister.org/doc/81_FR_26190/page/1.svg)
![26108 Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations
Adoption of the Amendment § 39.13 [Amended] (b) Affected ADs
Accordingly, under the authority None.
■ 2. The FAA amends § 39.13 by adding
delegated to me by the Administrator, the following new airworthiness (c) Applicability
the FAA amends 14 CFR part 39 as directive (AD):
follows: This AD applies to Piper Aircraft, Inc.
2016–08–18 Piper Aircraft, Inc.: Model PA–31–350 airplanes, serial numbers
PART 39—AIRWORTHINESS Amendment 39–18495; Docket No. 31–5001 through 31–5004, 31–7305005
DIRECTIVES FAA–2014–0338; Directorate Identifier through 31–8452024, and 31–8253001
2014–CE–010–AD. through 31–8553002, certificated in any
■ 1. The authority citation for part 39 category, that are equipped with the
continues to read as follows: (a) Effective Date following engines and fuel pump hose
Authority: 49 U.S.C. 106(g), 40113, 44701. This AD is effective June 6, 2016. assemblies:
TABLE 1 TO PARAGRAPH (C) OF THIS AD—APPLICABLE ENGINES AND FUEL PUMP HOSE ASSEMBLIES
Engine Manufacturer’s hose name Manufacturer’s part number (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 Injector Lycoming LW–12877–6S142 ........... Exit fuel hose from engine fuel pump.
TIO540–J2BD (right wing) .... Hose, Fuel pump to Injector Lycoming LW–12877–6S142 ........... Exit fuel hose from engine fuel pump.
LTIO–540–J2BD (left wing) .. Hose Assembly—Fuel .......... Piper 39995–034 ............................. Inlet fuel hose to engine fuel pump.
(d) Subject within the next 6 months after June 6, 2016 section of Piper Aircraft, Inc. Service Bulletin
Joint Aircraft System Component (JASC)/ (the effective date of this AD), whichever No. 1257A, dated August 4, 2015.
Air Transport Association (ATA) of America occurs first, visually inspect the inlet and (2) If any leaks found during the engine
Code 73: Engine Fuel and Control. exit fuel hose assemblies listed in table 1 to run-up required in paragraph (j)(1) of this AD
paragraph (c) of this AD for evidence of emanate from any fuel line component
(e) Unsafe Condition leaking, cracking, chafing, and any other sign adjusted, repaired, or replaced during any
This AD was prompted by a report of an of damage. Do the inspection following the actions required in paragraphs (g)(1) through
engine fire caused by a leak in the fuel pump INSTRUCTIONS section of Piper Aircraft, (i)(2) of this AD, before further flight, take all
inlet hose. We are issuing this AD to correct Inc. Service Bulletin No. 1257A, dated necessary corrective actions following the
the unsafe condition on these products. August 4, 2015. INSTRUCTIONS section of Piper Aircraft,
(2) Before further flight after the inspection Inc. Service Bulletin No. 1257A, dated
(f) Compliance required in paragraph (h)(1) of this AD, if any August 4, 2015.
Comply with this AD within the evidence of leaking, cracking, chafing, or any (k) Alternative Methods of Compliance
compliance times specified in paragraphs other sign of damage is found in any inlet or (AMOCs)
(g)(1) through (j)(2) of this AD, unless already exit fuel host assembly listed in table 1 to
done. paragraph (c) of this AD, replace the fuel (1) The Manager, Atlanta Aircraft
hose assembly with a serviceable part. Do the Certification Office (ACO), FAA, has the
(g) Ensure Proper Clearance Between the authority to approve AMOCs for this AD, if
replacement following the INSTRUCTIONS
Fuel Hose Assembly and the Turbocharger requested using the procedures found in 14
section of Piper Aircraft, Inc. Service Bulletin
Support Assembly CFR 39.19. In accordance with 14 CFR 39.19,
No. 1257A, dated August 4, 2015.
(1) Within the next 60 hours time-in- send your request to your principal inspector
service (TIS) after June 6, 2016 (the effective (i) Visually Inspect the Turbocharger or local Flight Standards District Office, as
Support Assembly and Replace if Necessary appropriate. If sending information directly
date of this AD) or within the next 6 months
to the manager of the ACO, send it to the
after June 6, 2016 (the effective date of this (1) Within the next 60 hours TIS after June
attention of the person identified in the
AD), whichever occurs first, inspect to 6, 2016 (the effective date of this AD) or
Related Information section of this AD.
determine the clearance between the inlet within the next 6 months after June 6, 2016
(2) Before using any approved AMOC,
and exit fuel hose assemblies listed in table (the effective date of this AD), whichever notify your appropriate principal inspector,
1 to paragraph (c) of this AD, and each occurs first, visually inspect each or lacking a principal inspector, the manager
turbocharger support assembly, Lycoming P/ turbocharger support assembly, Lycoming P/ of the local flight standards district office/
N LW–18302. There should be a minimum N LW–18302, for evidence of chafing and any certificate holding district office.
3⁄16-inch clearance. Do the inspection other signs of damage. Do the inspection
following the INSTRUCTIONS section of following the INSTRUCTIONS section of (l) Related Information
Piper Aircraft, Inc. Service Bulletin No. Piper Aircraft, Inc. Service Bulletin No. For more information about this AD,
1257A, dated August 4, 2015. 1257A, dated August 4, 2015. contact Gary Wechsler, Aerospace Engineer,
(2) Before further flight after the inspection (2) Before further flight after the inspection FAA, Atlanta ACO, 1701 Columbia Avenue,
required in paragraph (g)(1) of this AD, if the required in paragraph (i)(1) of this AD, if any College Park, Georgia 30337; telephone: (404)
measured clearance is less than 3⁄16-inch, evidence of chafing or any other sign of 474–5575; fax: (404) 474–5606; email:
make all necessary adjustments to make the damage is found on any turbocharger support gary.wechsler@faa.gov.
clearance a minimum of 3⁄16-inch between assembly, replace Lycoming P/N LW–18302
the inlet and exit fuel hose assemblies listed with a serviceable part. Do the replacement (m) Material Incorporated by Reference
in table 1 to paragraph (c) of this AD and following the INSTRUCTIONS section of (1) The Director of the Federal Register
each turbocharger support assembly, Piper Aircraft, Inc. Service Bulletin No. approved the incorporation by reference
Lycoming P/N LW–18302, following the 1257A, dated August 4, 2015. (IBR) of the service information listed in this
mstockstill on DSK3G9T082PROD with RULES
INSTRUCTIONS section of Piper Aircraft, paragraph under 5 U.S.C. 552(a) and 1 CFR
(j) Engine Run-Up part 51.
Inc. Service Bulletin No. 1257A, dated
August 4, 2015. (1) If any fuel line component was adjusted (2) You must use this service information
or replaced during any actions required in as applicable to do the actions required by
(h) Visually Inspect the Fuel Hose Assembly paragraphs (g)(1) through (i)(2) of this AD, this AD, unless the AD specifies otherwise.
and Replace if Necessary before further flight, perform an engine run- (i) Piper Aircraft, Inc. Service Bulletin No.
(1) Within the next 60 hours TIS after June up on the ground to check for leaks. Do the 1257A, dated August 4, 2015.
6, 2016 (the effective date of this AD) or engine run-up following the INSTRUCTIONS (ii) Reserved.
VerDate Sep<11>2014 17:39 Apr 29, 2016 Jkt 238001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\02MYR1.SGM 02MYR1](https://thefederalregister.org/doc/81_FR_26190/page/3.svg)
![Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 26109
(3) For Piper Aircraft, Inc. service of certain publications listed in this AD NPRM also proposed to provide a
information identified in this AD, contact as of June 6, 2016. modification of the pivot bulkhead,
Piper Aircraft, Inc., 926 Piper Drive, Vero which would terminate the repetitive
ADDRESSES: For service information
Beach, Florida 32960; telephone: (772) 567– inspections. We are issuing this AD to
4361; fax: (772) 978–6573; Internet: identified in this final rule, contact
www.piper.com/home/pages/ Boeing Commercial Airplanes, detect and correct fatigue cracking of the
Publications.cfm. Attention: Data & Services Management, outer flanges of the left and right side
(4) You may view this service information P.O. Box 3707, MC 2H–65, Seattle, WA forward outer chords of the pivot
at FAA, Small Airplane Directorate, 901 98124–2207; telephone: 206–544–5000, bulkhead, which could result in a
Locust, Kansas City, Missouri 64106. For extension 1; fax: 206–766–5680; severed forward outer chord and
information on the availability of this Internet: https:// consequent loss of horizontal stabilizer
material at the FAA, call (816) 329–4148. www.myboeingfleet.com. You may view control.
(5) You may view this service information
that is incorporated by reference at the
this referenced service information at Comments
National Archives and Records the FAA, Transport Airplane
We gave the public the opportunity to
Administration (NARA). For information on Directorate, 1601 Lind Avenue SW.,
participate in developing this AD. The
the availability of this material at NARA, call Renton, WA. For information on the
following presents the comments
202–741–6030, or go to: http:// availability of this material at the FAA,
received on the NPRM and the FAA’s
www.archives.gov/federal-register/cfr/ibr- call 425–227–1221. It is also available
locations.html. response to each comment.
on the Internet at http://
Issued in Kansas City, Missouri, on April www.regulations.gov by searching for Request To Exclude Certain
14, 2016. and locating Docket No. FAA–2015– Requirements From the NPRM
Robert P. Busto, 1428. American Airlines (AA) requested
Acting Manager, Small Airplane Directorate, Examining the AD Docket that we revise the NPRM to exclude
Aircraft Certification Service. doing the work in accordance with
[FR Doc. 2016–09238 Filed 4–29–16; 8:45 am]
You may examine the AD docket on paragraph 3.B.4., of the Work
the Internet at http:// Instructions of Boeing Alert Service
BILLING CODE 4910–13–P
www.regulations.gov by searching for Bulletin 777–53A0075, dated January
and locating Docket No. FAA–2015– 14, 2015, which specifies ‘‘Put the
DEPARTMENT OF TRANSPORTATION 1428; or in person at the Docket airplane back into a serviceable
Management Facility between 9 a.m. condition.’’ AA stated that doing this
Federal Aviation Administration and 5 p.m., Monday through Friday, action does not affect the condition that
except Federal holidays. The AD docket the AD seeks to address. AA added that
14 CFR Part 39 contains this AD, the regulatory most operators will accomplish these
evaluation, any comments received, and modifications as part of a maintenance
[Docket No. FAA–2015–1428; Directorate
other information. The address for the visit, and returning the airplane to a
Identifier 2015–NM–026–AD; Amendment
39–18499; AD 2016–09–01] Docket Office (phone: 800–647–5527) is serviceable condition will not be
Docket Management Facility, U.S. possible in the context of the statement,
RIN 2120–AA64 Department of Transportation, Docket but rather will occur at a point in time
Operations, M–30, West Building well after the work is completed.
Airworthiness Directives; The Boeing Ground Floor, Room W12–140, 1200
Company Airplanes We agree that putting the airplane
New Jersey Avenue SE., Washington, back into a serviceable condition is not
AGENCY: Federal Aviation DC 20590. directly related to addressing the unsafe
Administration (FAA), DOT. FOR FURTHER INFORMATION CONTACT: condition identified in this AD.
ACTION: Final rule. Narinder Luthra, Aerospace Engineer, However, we do not agree to specifically
Airframe Branch, ANM–120S, FAA, exclude paragraph 3.B.4., of the Work
SUMMARY: We are adopting a new Seattle Aircraft Certification Office Instructions of Boeing Alert Service
airworthiness directive (AD) for certain (ACO), 1601 Lind Avenue SW., Renton, Bulletin 777–53A0075, dated January
The Boeing Company Model 777–200 WA 98057–3356; phone: 425–917–6513; 14, 2015, from this final rule because it
and –300 series airplanes. This AD was fax: 425–917–6590; email: is not required for compliance with the
prompted by reports of fatigue cracking narinder.luthra@faa.gov. AD actions.
of a certain chord of the pivot bulkhead. SUPPLEMENTARY INFORMATION: The FAA worked in conjunction with
This AD requires repetitive inspections industry, under the Airworthiness
for cracking of the left side and right Discussion Directives Implementation Aviation
side forward outer chords of the pivot We issued a notice of proposed Rulemaking Committee (AD ARC), to
bulkhead, and related investigative and rulemaking (NPRM) to amend 14 CFR enhance the AD system. One
corrective actions if necessary. This AD part 39 by adding an AD that would enhancement is a new process for
also provides a modification of the pivot apply to certain The Boeing Company annotating which steps in the service
bulkhead, which would terminate the Model 777–200 and –300 series information are ‘‘required for
repetitive inspections. We are issuing airplanes. The NPRM published in the compliance’’ (RC) with an AD.
this AD to detect and correct fatigue Federal Register on June 15, 2015 (80 Differentiating these steps from other
cracking of the outer flanges of the left FR 34103) (‘‘the NPRM’’). The NPRM tasks in the service information is
and right side forward outer chords of was prompted by reports of fatigue expected to improve an owner’s/
mstockstill on DSK3G9T082PROD with RULES
the pivot bulkhead, which could result cracking of a certain chord of the pivot operator’s understanding of AD
in a severed forward outer chord and bulkhead. The NPRM proposed to requirements and help provide
consequent loss of horizontal stabilizer require repetitive inspections for consistent judgment in AD compliance.
control. cracking of the left side and right side In response to the AD Implementation
DATES: This AD is effective June 6, 2016. forward outer chords of the pivot ARC, the FAA released AC 20–176A,
The Director of the Federal Register bulkhead, and related investigative and dated June 16, 2014 (http://rgl.faa.gov/
approved the incorporation by reference corrective actions if necessary. The Regulatory_and_Guidance_Library/rg
VerDate Sep<11>2014 17:39 Apr 29, 2016 Jkt 238001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 E:\FR\FM\02MYR1.SGM 02MYR1](https://thefederalregister.org/doc/81_FR_26190/page/4.svg)
Document Created: 2016-04-30 13:35:18
Document Modified: 2016-04-30 13:35:18
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective June 6, 2016. | |
| 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: [email protected] | |
| FR Citation | 81 FR 26106 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR