81 FR 26106 - Airworthiness Directives; Piper Aircraft, Inc. Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 84 (May 2, 2016)

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.

[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]


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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; 
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.

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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