[Federal Register Volume 81, Number 204 (Friday, October 21, 2016)]
[Proposed Rules]
[Pages 72742-72748]
[FR Doc No: 2016-24857]

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Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.

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Federal Register / Vol. 81, No. 204 / Friday, October 21, 2016 /
Proposed Rules

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9254; Directorate Identifier 2015-CE-030-AD]
RIN 2120-AA64

Airworthiness Directives; Piper Aircraft, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 95-26-13,
which applies to certain Piper Aircraft, Inc. Models PA-28-140, PA-28-
150, PA-28-151, PA-28-161, PA-28-160, PA-28-180, PA-28-181, PA-28-235,
PA-28-236, PA-28R-180, PA-28R-200, PA-28R-201, PA-28S-160, PA-28S-180,
PA-32-260, PA-32-300, PA-32-301, PA-32-301T, PA-32R-300, PA-32R-301
(SP), PA-32R-301 (HP), PA-32R-301T, PA-32RT-300, PA-32RT-300T, and PA-
32S-300 airplanes equipped with oil cooler hose assemblies that do not
meet certain technical standard order (TSO) requirements. AD 95-26-13
requires inspections, replacement, and adjustment of the oil cooler
hose assemblies, as well as providing for a terminating action. Since
we issued AD 95-26-13, the FAA has received requests to clarify the
intent of AD 95-26-13. This proposed AD would maintain all of the
actions required by AD 95-26-13 and add language to clarify those
requirements. We are proposing this AD to prevent rupture or failure of
the oil cooler hose assemblies, which could result in engine stoppage
with consequent loss of control.

DATES: We must receive comments on this proposed AD by December 5,
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 http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

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-2016-
9254; 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:<PHONE_NUMBER>) 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:<PHONE_NUMBER>; fax: (404) 474-
5606; email<EMAIL_ADDRESS>
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-2016-9254;
Directorate Identifier 2015-CE-030-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 http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.

Discussion

    On December 19, 1995, we issued AD 95-26-13, Amendment 39-9472 (60
FR 67321, December 29, 1995) (``AD 95-26-13''), for certain Piper
Aircraft, Inc. Models PA-28-140, PA-28-150, PA-28-151, PA-28-161, PA-
28-160, PA-28-180, PA-28-181, PA-28-235, PA-28-236, PA-28R-180, PA-28R-
200, PA-28R-201, PA-28S-160, PA-28S-180, PA-32-260, PA-32-300, PA-32-
301, PA-32-301T, PA-32R-300, PA-32R-301 (SP), PA-32R-301 (HP), PA-32R-
301T, PA-32RT-300, PA-32RT-300T, and PA-32S-300 airplanes equipped with
oil cooler hose assemblies that do not meet TSO-C53a Type D
requirements. AD 95-26-13 requires repetitive inspections of the oil
cooler hose assemblies for deterioration; replacement of the hose
assemblies if damage is found; inspection for a minimum clearance
between the oil cooler assemblies and the front exhaust stacks,
depending on oil cooler location; and adjustment of the clearance if
minimum clearance is not found. AD 95-26-13 also provides the option of
installing TSO-C53a Type D oil cooler hose assemblies as a terminating
action for the repetitive inspections. AD 95-26-13 resulted from
numerous incidents/accidents caused by rupture or failure of the oil
cooler hose assemblies. We issued AD 95-26-13 to prevent rupture or
failure of the oil cooler hose assemblies, which could result in engine
stoppage with consequent loss of control.

Actions Since AD 95-26-13 Was Issued

    The FAA received several recent inquiries repeatedly asking for
clarification of the AD's applicability and compliance requirements.
For example, the AD did not apply to airplanes equipped with TSO-C53a
Type D specification oil cooler hoses, yet, callers repeatedly asked
whether the AD applied to airplanes with such hoses. It became apparent
that a rewrite of the AD was necessary to stem the mounting time
engineers were spending researching and responding to the inquiries.
The FAA believes that the proposed NPRM will provide the level of
clarification necessary to prevent similar inquiries in the future.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would retain all of the requirements of AD 95-26-
13 and add language to clarify those requirements.

Costs of Compliance

    We estimate that this proposed AD affects 23,643 airplanes of U.S.
registry.
    This proposed AD retains the same actions as AD 95-26-13 and the
proposed costs do not add any cost burden than that already in effect
by AD 95-26-13. The difference in the Costs of Compliance with the
proposed AD and AD 95-26-13 is that we use $85 an hour as a labor rate
in 2016 as opposed to $60 per hour in 1995.
    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
----------------------------------------------------------------------------------------------------------------
Inspection of the oil cooler     1 work-hour x $85   Not applicable.........             $85  $2,009,655.
 hose assembly.                   per hour = $85.
Inspection of the clearance      .5 work-hour x $85  Not applicable.........          $42.50  $1,004,827.50 See
 between the oil cooler hose      per hour = $42.50.                                           note 1 to Cost of
 assembly and the front exhaust                                                                Compliance.
 stacks.
Replacement of the oil cooler    1 work-hour x $85   $430...................            $515  $12,176,145.
 hose assembly.                   per hour = $85.
----------------------------------------------------------------------------------------------------------------

    Note to Costs of Compliance: The estimated cost of the inspection
of the clearance between the oil cooler hose assembly and the front
exhaust stacks is for all airplanes affected by this proposed AD;
however, the inspection applies only to airplanes with the oil cooler
mounted in a location other than at or aft of the rear of the engine.
We have no way of knowing how many affected airplanes have that
particular installation.
    We estimate the following costs to do any necessary adjustments
that would be required based on the results of the proposed inspection.
We have no way of determining the number of aircraft that might need
these adjustments:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per
                 Action                           Labor cost                  Parts cost              product
----------------------------------------------------------------------------------------------------------------
Adjustment of the clearance between the   1 work-hour x $85 per hour  Not applicable............             $85
 oil cooler hose assembly and the front    = $85.
 exhaust stacks.
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Authority for This Rulemaking

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

Regulatory Findings

    We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed
regulation:
    (1) Is not a ``significant regulatory action'' under Executive
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD)
95-26-13, Amendment 39-9472 (60 FR 67321, December 29, 1995), and
adding the following new AD:

Piper Aircraft, Inc.: Docket No. FAA-2016-9254; Directorate
Identifier 2015-CE-030-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by December 5,
2016.

(b) Affected ADs

    This AD replaces AD 95-26-13, Amendment 39-9472 (60 FR 67321,
December 29, 1995) (``AD 95-26-13'').

(c) Applicability

    This AD applies to Piper Aircraft, Inc. Models PA-28-140, PA-28-
150, PA-28-151, PA-28-161, PA-28-160, PA-28-180, PA-28-181, PA-28-
235, PA-28-236, PA-28R-180, PA-28R-200, PA-28R-201, PA-28S-160, PA-
28S-180, PA-32-260, PA-32-300, PA-32-301, PA-32-301T, PA-32R-300,
PA-32R-301 (SP), PA-32R-301 (HP), PA-32R-301T, PA-32RT-300, PA-32RT-
300T, and PA-32S-300 airplanes, all serial numbers, that are:
    (1) Equipped with oil cooler hose assemblies that do not meet
TSO-C53a, Type D requirements; and
    (2) Certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 79, Engine Oil.

(e) Unsafe Condition

    AD 95-26-13 was prompted by numerous incidents/accidents caused
by rupture or failure of the oil cooler hose assemblies. This AD
action was prompted by requests to clarify the intent of AD 95-26-
13. We are issuing this AD to prevent rupture or failure of the oil
cooler hose assemblies, which could result in engine stoppage with
consequent loss of control.

(f) Compliance

    Comply with this AD within the compliance times specified,
unless already done. You may review the flow chart found in appendix
1 to assist you in complying with the actions of this AD.

(g) Oil Cooler Mounted at or Aft of the Rear of the Engine

    For applicable airplanes with the oil cooler mounted at or aft
of the rear of the engine (See figure 1 to paragraphs (g) and (h)):
Within the next 100 hours time-in-service (TIS) after February 5,
1996 (the effective date retained from AD 95-26-13), and
repetitively thereafter at intervals not to exceed 100 hours TIS,
inspect the oil cooler hose assembly for oil soaked in the fire
sleeve of the oil hose assembly, a brownish or whitish color of the
fire sleeve of the oil hose assembly, and any evidence of
brittleness or deterioration of the fire sleeve of the oil hose
assembly as a result of heat or oil seepage.
[GRAPHIC] [TIFF OMITTED] TP21OC16.000

    (1) If any of the conditions described in paragraph (g) of this
AD are found on the oil cooler hose assembly during the inspection
required in paragraph (g) of this AD, before further flight, replace
the oil cooler hose assembly with TSO-C53a Type D oil cooler hose
assembly or TSO-C53a Type C oil cooler hose assembly that has been
inspected following paragraph (g) of this AD and found to be
airworthy.
    (2) Replacement of the oil cooler hose assembly with TSO-C53a
Type D oil cooler hose assembly is terminating action for this AD.

    Note 1 to paragraphs (g) and (h)(1) of this AD: Although not
required by this AD, the FAA recommends that an oil cooler assembly
flexibility test be done at 100-hour TIS intervals. Oil cooler hose
assembly flexibility may be determined by gently lifting each oil
cooler hose assembly in several places from the bottom of its
downward arc to the oil cooler. If the oil cooler hose assembly
moves slightly either from side-to-side or upward, with the hand at
the center of an even arc, then some flexibility remains. If the oil
cooler hose assembly appears hardened or inflexible, replacement is
recommended.

    Note 2 to paragraphs (g)(1), (h)(1)(i), and (i) of this AD: If
one of the oil cooler hose assemblies requires replacing, the FAA
recommends replacing both of the oil cooler hose assemblies to
simplify tracking the TIS of the assemblies.

(h) Oil Cooler Mounted in Location Other Than Aft of the Rear of the
Engine

    (1) For applicable airplanes with the oil cooler mounted in a
location other than at or aft of the rear of the engine (See figure
1 to paragraphs (g) and (h)): Within the next 100 hours TIS after
February 5, 1996 (the effective date retained from AD 95-26-13), and
repetitively thereafter at intervals not to exceed 100 hours TIS,
inspect the oil cooler hose assembly for oil soaked in the fire
sleeve of the oil hose assembly, a brownish or whitish color of the
fire sleeve of the oil hose

assembly, and any evidence of brittleness or deterioration of the
fire sleeve of the oil hose assembly as a result of heat or oil
seepage.
    (2) If any of the conditions described in paragraph (h)(1) of
this AD are found on the oil cooler hose assembly during the
inspection required in paragraph (h)(1) of this AD, before further
flight, replace the oil cooler hose assembly with TSO-C53a Type D
oil cooler hose assembly or TSO-C53a Type C oil cooler hose assembly
that has been inspected following paragraph (h)(1) of this AD and
found to be airworthy.
    (3) Within the next 100 hours TIS after February 5, 1996 (the
effective date retained from AD 95-26-13) and each time the oil
cooler hose assembly is replaced for any reason or inspected
following paragraph (h)(1) inspect to ensure the installation
conditions in paragraphs (h)(3)(i) through (iii) of this AD are met.
If the conditions listed in paragraphs (h)(3)(i) through (iii) of
this AD are not met, before further flight, make any necessary
adjustments. Please see figure 2 to paragraph (h) of this AD for
additional information.
    (i) The oil cooler hose assemblies pass underneath and behind
the electrical ground cable and in front of the lower of the two
engine mount.
    (ii) The oil cooler hose assemblies are secured to the engine
mount strut and a clearance of at least 2 inches exists between the
oil cooler hose assemblies and the exhaust stack.
    (iii) Oil cooler hose assemblies with a minimum outer diameter
of 0.75 inch are installed with a bend radius of at least 6.5
inches.
[GRAPHIC] [TIFF OMITTED] TP21OC16.001

    (3) Replacement of the oil cooler hose assembly with TSO-C53a
Type D oil cooler hose assembly and meeting the installation
conditions listed in paragraphs (h)(3)(i) through (iii) of this AD
terminate the requirements of this AD.

(i) Replacement of Oil Cooler Hose Assembly

    For all applicable airplanes installed with a TSO-C53a Type C
oil cooler hose assembly: When the oil cooler hose assembly
accumulates 8 years or 1,000 hours TIS, whichever occurs first,
replace the oil cooler hose assembly. If the oil cooler is mounted
in a location other than at or aft of the rear of the engine, before
further flight after replacement, you must do the actions required
in paragraph (h)(3) of this AD.
    (1) Replacement of the oil cooler hose assembly with TSO-C53a
Type D oil cooler hose assembly terminates the requirements of this
AD provided it meets the installation conditions listed in paragraph
(h)(3)(i) through (iii) of this AD.
    (2) You may at any time before 8 years or 1,000 hours TIS,
whichever occurs first, replace the oil cooler hose assembly with
TSO-C53a Type D oil cooler hose assembly to terminate the
requirements of this AD provided it meets the installation
conditions listed in paragraph (h)(3)(i) through (iii) of this AD.

(j) 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 paragraph (k) 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.
    (3) AMOCs approved for AD 95-26-13 (60 FR 67321, December 29,
1995) are approved as AMOCs for the corresponding provisions of this
AD.

(k) Related Information

    For more information about this AD, contact Gary Wechsler,
Aerospace Engineer, FAA, Atlanta Aircraft Certification Office, 1701
Columbia Avenue, College Park, Georgia 30337; telephone: (404) 474-
5575; fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>BILLING CODE 4910-13-P

[GRAPHIC] [TIFF OMITTED] TP21OC16.002

    Issued in Kansas City, Missouri, on October 7, 2016.
Pat Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-24857 Filed 10-20-16; 8:45 am]
 BILLING CODE 4910-13-C