Airworthiness Directives; Piper Aircraft, Inc. Airplanes, 72742-72748 [2016-24857]
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Proposed Rules
Federal Register
Vol. 81, No. 204
Friday, October 21, 2016
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.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9254; Directorate
Identifier 2015–CE–030–AD]
Examining the AD Docket
RIN 2120–AA64
Airworthiness Directives; Piper
Aircraft, Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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:
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SUMMARY:
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• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
You may examine the AD docket on
the Internet at https://
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: 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–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 https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
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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.
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Federal Register / Vol. 81, No. 204 / Friday, October 21, 2016 / Proposed Rules
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
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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
Action
Labor cost
Inspection of the oil cooler hose assembly ..............
Inspection of the clearance between the oil cooler
hose assembly and the front exhaust stacks.
Replacement of the oil cooler hose assembly ..........
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
Cost per
product
Parts cost
1 work-hour × $85 per
hour = $85.
.5 work-hour × $85 per
hour = $42.50.
1 work-hour × $85 per
hour = $85.
Not applicable ...
$85
Not applicable ..
$42.50
$430 .................
$515
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.
Cost on U.S. operators
$2,009,655.
$1,004,827.50 See note 1
to Cost of Compliance.
$12,176,145.
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
Action
Labor cost
Parts cost
Adjustment of the clearance between the oil cooler hose assembly and the front exhaust stacks.
1 work-hour × $85 per hour =
$85.
Not applicable .........................
Authority for This Rulemaking
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Cost per
product
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
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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.
$85
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 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.
List of Subjects in 14 CFR Part 39
(a) Comments Due Date
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The FAA must receive comments on this
AD action by December 5, 2016.
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Federal Register / Vol. 81, No. 204 / Friday, October 21, 2016 / Proposed Rules
This AD replaces AD 95–26–13,
Amendment 39–9472 (60 FR 67321,
December 29, 1995) (‘‘AD 95–26–13’’).
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 79, Engine Oil.
(c) Applicability
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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
(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.
(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.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
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
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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.
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
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(2) Certificated in any category.
(b) Affected ADs
Federal Register / Vol. 81, No. 204 / Friday, October 21, 2016 / Proposed Rules
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(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.
(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.
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.
(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,
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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.
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Federal Register / Vol. 81, No. 204 / Friday, October 21, 2016 / Proposed Rules
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(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
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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.
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(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: (404) 474–5606; email: gary.wechsler@
faa.gov.
BILLING CODE 4910–13–P
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Federal Register / Vol. 81, No. 204 / Friday, October 21, 2016 / Proposed Rules
72748
Federal Register / Vol. 81, No. 204 / Friday, October 21, 2016 / Proposed Rules
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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–7526; Directorate
Identifier 2014–NM–217–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Supplemental notice of
proposed rulemaking (SNPRM);
reopening of comment period.
AGENCY:
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Examining the AD Docket
We are revising an earlier
proposed airworthiness directive (AD)
for all Airbus Model A318, A319, A320,
and A321 series airplanes. This action
revises the notice of proposed
rulemaking (NPRM) by requiring an
additional action for sealant application
on some nuts and bolts on the National
Advisory Committee for Aeronautics
(NACA) duct assembly and adding a
grace period to the compliance time. We
are proposing this SNPRM to detect and
correct corroded circlips. Such
corrosion could lead to failure of the
circlips and consequent movement of
the FVP and result in a reduction of the
flame protector capability of the FVP
cartridge. Such a condition could result
in damage to the airplane in case of
lightning impact or fire on the ground.
Since the additional actions impose an
additional burden over those proposed
in the NPRM, we are reopening the
comment period to allow the public the
chance to comment on these proposed
changes.
DATES: The comment period for the
NPRM published in the Federal
Register on December 23, 2015 (80 FR
79742), is reopened.
We must receive comments on this
SNPRM 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
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
SUMMARY:
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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, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this SNPRM, contact Airbus,
Airworthiness Office—EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221.
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
7526; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1405;
fax 425–227–1149.
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–2015–7526; Directorate Identifier
2014–NM–217–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 based on those comments.
We will post all comments we
receive, without change, to https://
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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
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Airbus Model A318, A319,
A320, and A321 series airplanes. The
NPRM published in the Federal
Register on December 23, 2015 (80 FR
79742) (‘‘the NPRM’’). The NPRM was
prompted by the discovery of corroded
circlips in FVPs having a certain part
number. The NPRM proposed to require
an inspection to determine the part
number and serial number of the FVP,
and replacement if necessary.
Actions Since the NPRM Was Issued
Since we issued the NPRM, Airbus
has issued revised service information
to include an additional action to apply
sealant on nuts and bolts of the NACA
duct assembly. Airplanes on which the
installation in the original service
information was done would be
required to do this additional action. In
addition, we determined that a grace
period is needed so operators have
sufficient time to comply with the
requirements in this proposed AD.
In addition, the European Aviation
Safety Agency (EASA) superseded
EASA Airworthiness Directive 2014–
0234R1, dated December 11, 2014
(which was referred to in the NPRM),
and issued EASA Airworthiness
Directive 2016–0114, dated June 15,
2016; corrected June 23, 2016; which
retains the requirements of EASA AD
2014–0234R1 and includes an
additional action.
The EASA, which is the Technical
Agent for the Member States of the
European Union, has issued
Airworthiness Directive 2016–0114,
dated June 15, 2016; corrected June 23,
2016 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus
Model A318, A319, A320, and A321
series airplanes. The MCAI states:
On each aeroplane wing, a NACA duct
assembly is installed, including a Fuel Vent
Protector (FVP) which is used as flame
arrestor. This FVP is maintained in its NACA
duct assembly by a circlip (also known as Cclip). Following a wing water pressure test,
the FVP is removed and dried with heat.
During an inspection after this test, several
circlips were reported to be discoloured.
Investigation revealed that a batch of circlips
fitted on some FVP Part Number (P/N)
786073–1–0 have an increased risk of
E:\FR\FM\21OCP1.SGM
21OCP1
]]>Agencies
[Federal Register Volume 81, Number 204 (Friday, October 21, 2016)]
[Proposed Rules]
[Pages 72742-72748]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-24857]
========================================================================
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.
========================================================================
Federal Register / Vol. 81, No. 204 / Friday, October 21, 2016 /
Proposed Rules
[[Page 72742]]
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).
-----------------------------------------------------------------------
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 https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
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-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: 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-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 https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On 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.
[[Page 72743]]
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.
----------------------------------------------------------------------------------------------------------------
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.
[[Page 72744]]
(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
[[Page 72745]]
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.
[[Page 72746]]
(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: (404) 474-5606; email: gary.wechsler@faa.gov.
BILLING CODE 4910-13-P
[[Page 72747]]
[GRAPHIC] [TIFF OMITTED] TP21OC16.002
[[Page 72748]]
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
