Airworthiness Directives; Piper Aircraft, Inc. Airplanes, 31892-31899 [2017-14375]
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Issued in Washington, DC, on June 30,
2017.
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Acting Assistant Secretary Energy Efficiency
and Renewable Energy.
[FR Doc. 2017–14472 Filed 7–10–17; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9254; Directorate
Identifier 2015–CE–030–AD; Amendment
39–18948; AD 2017–14–04]
RIN 2120–AA64
Airworthiness Directives; Piper
Aircraft, Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (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 certain technical standard order
(TSO) requirements. AD 95–26–13
required inspections, replacement, and
adjustment of the oil cooler hose
assemblies, as well as providing for a
terminating action. This AD retains all
of the requirements of AD 95–26–13 and
adds language to clarify those
requirements. This AD was prompted by
several inquiries asking for clarification
of the AD’s applicability and
compliance requirements. We are
issuing this AD to correct the unsafe
condition on these products.
DATES: This AD is effective August 15,
2017.
SUMMARY:
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 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,
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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:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 95–26–13,
Amendment 39–9472 (60 FR 67321,
December 29, 1995) (‘‘AD 95–26–13’’).
AD 95–26–13 applied 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 technical
standard order C53a (TSO–C53a) Type
D requirements. The NPRM published
in the Federal Register on October 21,
2016 (81 FR 72742). The NPRM was
prompted by several inquiries asking for
clarification of the AD’s applicability
and compliance requirements. The
NPRM proposed to retain all of the
requirements of AD 95–26–13 and add
language to clarify those requirements.
We are issuing this AD to correct the
unsafe condition on these products.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Request the Unsafe Condition Be
Addressed by Department of Commerce
G. Fenton requested this unsafe
condition be addressed through the
Department of Commerce instead of the
Federal Aviation Administration
because the NPRM applied to airplanes
used for commercial purposes.
We disagree with this comment
because the Federal Aviation
Administration is charged by Congress
to provide for the safe and efficient use
of national airspace by commercial and
private airplane operators.
We have not changed the AD based on
this comment.
Request To Change Labor Rate in Cost
of Compliance
G. Fenton requested we change the
labor rate in the Cost of Compliance
section to $72.50 per hour instead of
$85 per hour. He thought the increased
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cost from $60 per hour from the 1995
AD to $85 per hour for this AD is
unnecessary. He thought we should
adjust the cost of the labor rate to a
value between the two.
We disagree with this comment. The
rate of $85 per hour is provided by the
FAA Office of Aviation Policy and Plans
for us to use when estimating the labor
costs of complying with AD
requirements.
We have not changed the AD based on
this comment.
Request We Compile Changes From the
Previous AD Into One Location
Jonathan Hartley requested we put all
of the changes to this AD from AD 95–
26–13 in a conspicuous location to
reduce confusion and workload
associated with compliance.
We partially agree with this comment.
We agree there are instances where
compliance confusion and workload
could exist with the wording in the
NPRM. However, we disagree with
compiling the changes into one location
because of formatting constraints in the
AD structure.
We have made language changes to
the regulatory text in the AD to clarify
the compliance confusion and to reduce
workload.
Request We Include an Outline for
Maintaining Other Types of Oil Cooler
Hoses
Jonathan Hartley requested we
include in this AD an outline
maintaining specific requirements for
other types of oil cooler hoses.
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We disagree with this comment. The
unsafe condition addressed by this AD
applies only to Type C and Type D oil
cooler hoses. The requirements for
maintaining other types of oil cooler
hoses are not required to comply with
the actions of this AD.
We have not changed the AD based on
this comment.
hose assembly being terminating action
for the AD.
We agree with this comment. The
installation of the Type D oil cooler
hose assembly terminates the
requirement for the installation
inspection.
We have changed the language in the
AD to address the contradiction.
Request We Include Additional
Information Describing the Types of
Hoses
Conclusion
George Ballard requested we include
in the AD information explaining what
constitutes a Type C and Type D hose
assembly. He doesn’t think the TSO
adequately explains the difference
between the Type C and Type D hose
assemblies.
We disagree with this comment. The
differences between the Type C and
Type D hoses are provided in great
detail in TSO–C53a and its referenced
documents. This AD does not require
that level of detail to comply with the
inspections or corrective actions
specified in the AD.
We have not changed the AD based on
this comment.
Request We Clarify Terminating Action
for Installation of Type D Hose
Assemblies
Greg Dodson stated the requirement to
inspect the oil cooler hose assembly
installation for an oil cooler mounted in
a location other than at or aft of the rear
of the engine any time the oil cooler
hose assembly is replaced conflicts with
the installation of a Type D oil cooler
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Costs of Compliance
We estimate that this AD affects
23,643 airplanes of U.S. registry.
This AD retains the same actions as
AD 95–26–13 and the 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 this 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 AD:
ESTIMATED COSTS
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.
1 work-hour × $85 per hour = $85 ......
Not applicable
$85
.5 work-hour × $85 per hour = 42.50 ..
Not applicable
$42.50
1 work-hour × $85 per hour = $85 ......
$430 ................
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Note: 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 AD; however,
the inspection applies only to airplanes with
the oil cooler mounted in a location other
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Parts cost
Cost per
product
Action
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
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$515
Cost on U.S.
operators
$2,009,655.
$1,004,827.50 See note 1 to
Cost of Compliance.
$12,176,145.
be required based on the results of the
inspection. We have no way of
determining the number of aircraft that
might need these adjustments:
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Federal Register / Vol. 82, No. 131 / Tuesday, July 11, 2017 / Rules and Regulations
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
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.
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Regulatory Findings
We have determined that 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,
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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.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
[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:
■
2017–14–04 Piper Aircraft, Inc.:
Amendment 39–18948; Docket No.
FAA–2016–9254; Directorate Identifier
2015–CE–030–AD.
(a) Effective Date
This AD is effective August 15, 2017.
(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,
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$85
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 one or more oil cooler
hose assemblies that do not meet technical
standard order C53a (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
PART 39—AIRWORTHINESS
DIRECTIVES
§ 39.13
Cost per
product
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) Inspection Procedures for an Oil Cooler
Mounted AT or AFT of the Rear of the
Engine
For any oil cooler hose assemblies that do
not meet TSO–C53a, Type D requirements:
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 fire sleeve
of each oil cooler hose assembly for soaked
oil, a brownish or whitish color, and any
evidence of brittleness or deterioration as a
result of heat or oil seepage. See figure 1 to
paragraphs (g) and (h) of this AD for
additional information.
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(h) Inspection Procedures for an Oil Cooler
Mounted in a Location Other Than AT or
AFT of the Rear of the Engine
(1) For any oil cooler hose assemblies that
do not meet TSO–C53a, Type D
requirements: Within the next 100 hours TIS
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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 fire sleeve of each oil cooler
hose assembly for soaked oil, a brownish or
whitish color, and any evidence of brittleness
or deterioration as a result of heat or oil
seepage. See figure 1 to paragraphs (g) and (h)
of this AD for additional information.
(2) For any oil cooler hose assemblies that
do not meet TSO–C53a, Type D
requirements: 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 assemblies to
ensure the installation conditions in
paragraphs (h)(2)(i) through (iii) of this AD
are met. See figure 1 to paragraphs (g) and
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(h) of this AD for additional information. If
the conditions listed in paragraphs (h)(2)(i)
through (iii) of this AD are not met, before
further flight, make any necessary
adjustments. See figure 2 to paragraph (h)(2)
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 mounts.
(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.
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Note 1 to paragraphs (g) and (h)(1) of this
AD: Although not required by this AD, the
FAA recommends that an oil cooler hose
assembly flexibility test be done at 100-hour
TIS intervals by gently lifting each oil cooler
hose assembly in several places along its
bottom surface, ideally at the center of an arc.
If the oil cooler hose assembly moves
slightly, either from side-to-side or upward,
then some flexibility remains. If the oil cooler
hose assembly appears hardened or
inflexible, replacement is recommended.
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(i) Corrective Actions
(1) If any of the conditions described in
paragraph (g) or (h)(1) of this AD are found
on an oil cooler hose assembly during the
inspection required in paragraph (g) or (h)(1)
of this AD, as applicable, before further
flight, replace the oil cooler hose assembly
with a serviceable new or used TSO–C53a
Type D oil cooler hose assembly or TSO–
C53a Type C oil cooler hose assembly. If a
used TSO–C53a Type C oil cooler hose
assembly is installed, it must have
documented hours TIS.
Note 2 to paragraphs (i)(1) and (j) of this
AD: If only one of the two oil cooler hose
assemblies requires replacement, the FAA
recommends replacing both of the oil cooler
hose assemblies to simplify tracking the
hours TIS of the assemblies.
(2) If a newly installed oil cooler hose
assembly is a TSO–C53a Type C oil cooler
hose assembly and it is mounted in a location
other than at or aft of the rear of the engine,
then replacement of the oil cooler hose
assembly must meet the conditions listed in
paragraphs (h)(2)(i) through (iii) of this AD.
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(3) If compliance with paragraphs (i)(1) and
(i)(2) of this AD results in both oil cooler
hose assemblies of an airplane meeting TSO–
C53a Type D requirements, then the
requirements of this AD are terminated for
the airplane.
(j) Life Limit of TSO–C53a Type C Oil Cooler
Hose Assemblies
(1) When a TSO–C53a Type C oil cooler
hose assembly accumulates 8 years or 1,000
hours TIS, whichever occurs first, replace the
oil cooler hose assembly with a serviceable
new or used TSO–C53a Type D oil cooler
hose assembly or TSO–C53a Type C oil
cooler hose assembly. If a used TSO–C53a
Type C oil cooler hose assembly is installed,
it must have documented hours TIS. If the
newly installed oil cooler is a TSO–C53a
Type C oil cooler hose assembly and it is
mounted in a location other than at or aft of
the rear of the engine the installation must
meet the conditions listed in paragraphs
(h)(2)(i) through (iii) of this AD.
(2) You may at any time before a TSO–
C53a Type C oil cooler hose assembly
exceeds the life limit in paragraph (j)(1) of
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this AD, replace a TSO–C53a Type C oil
cooler hose assembly with a TSO–C53a Type
D oil cooler hose assembly.
(3) If compliance with paragraphs (j)(1) or
(j)(2) of this AD results in both oil cooler hose
assemblies of an airplane meeting TSO–C53a
Type D requirements, then the requirements
of this AD are terminated for the airplane.
(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
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.
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(3) AMOCs approved for AD 95–26–13 (60
FR 67321, December 29, 1995) are not
approved as AMOCs for the corresponding
provisions of this AD.
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(l) Related Information
For more information about this AD,
contact Gary Wechsler, Aerospace Engineer,
FAA, Atlanta Aircraft Certification Office,
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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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Appendix 1 to AD 201 7-14-04
(
Start
)
AD paragraph references
are noted with ()
PA-28 & PA-32
airplanes of (c) equipped with one or more
oil cooler hose that are not TSO-CS3a, Type D
compliant per (c)(l)
No
End
Yes
Inspect each non-
Yes
, - - - - - - - - - . 1 compliant hose per (c)(l) ~---<
for condition within 100
hrs TIS per (g)
Good
Oil Cooler
Mounted at or Aft of
the rear of the Engine
per Figure 1?
No
Inspect each non>---.! compliant hose per (c)(l) ~------,
for condition within 100
hrs TIS per (h)(1)
Bad
Bad
Good
Inspection
good or bad?
No
Will
the hose
reach 8 yrs TIS or
accumulate 1000 TIS
before the next
100 hrs
TIS?
Yes
Replace hose with
Type Cor TypeD
hose per (i)(l)
Type C
TypeD
Two
Yes
TypeD hoses
in airplane
Terminate AD
Yes
Two
No
Type D hoses > - - - - - - - - - - - - - - - - "
in airplane
End
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No
Federal Register / Vol. 82, No. 131 / Tuesday, July 11, 2017 / Rules and Regulations
Issued in Kansas City, Missouri, on June
29, 2017.
Pat Mullen,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2017–14375 Filed 7–10–17; 8:45 am]
BILLING CODE 4910–13–C
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0060; Directorate
Identifier 2016–SW–090–AD; Amendment
39–18949; AD 2017–14–05]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Airbus
Helicopters Model SA330J helicopters.
This AD requires replacing certain
hydraulic pumps and is prompted by
reports of broken screws that attach the
cover of the hydraulic pump. The
actions of this AD are intended to
prevent an unsafe condition on these
products.
SUMMARY:
This AD becomes effective July
26, 2017.
We must receive comments on this
AD by September 11, 2017.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
DATES:
mstockstill on DSK30JT082PROD with RULES
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–2017–
0060; or in person at the Docket
Operations Office between 9 a.m. and 5
p.m., Monday through Friday, except
VerDate Sep<11>2014
16:47 Jul 10, 2017
Jkt 241001
Federal holidays. The AD docket
contains this AD, the European Aviation
Safety Agency (EASA) AD, the
economic evaluation, any comments
received, and other information. The
street address for the Docket Operations
Office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
For service information identified in
this final rule, contact Airbus
Helicopters, 2701 N. Forum Drive,
Grand Prairie, TX 75052; telephone
(972) 641–0000 or (800) 232–0323; fax
(972) 641–3775; or at https://
www.airbushelicopters.com/techpub/
FO/scripts/myFO_login.php. You may
review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy, Room 6N–321,
Fort Worth, TX 76177.
FOR FURTHER INFORMATION CONTACT: Matt
Fuller, Senior Aviation Safety Engineer,
Safety Management Group, Rotorcraft
Directorate, FAA, 10101 Hillwood
Pkwy, Fort Worth, TX 76177; telephone
(817) 222–5110; email matthew.fuller@
faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments prior to it becoming effective.
However, we invite you to participate in
this rulemaking by submitting written
comments, data, or views. We also
invite comments relating to the
economic, environmental, energy, or
federalism impacts that resulted from
adopting this AD. The most helpful
comments reference a specific portion of
the AD, explain the reason for any
recommended change, and include
supporting data. To ensure the docket
does not contain duplicate comments,
commenters should send only one copy
of written comments, or if comments are
filed electronically, commenters should
submit them only one time. We will file
in the docket all comments that we
receive, as well as a report summarizing
each substantive public contact with
FAA personnel concerning this
rulemaking during the comment period.
We will consider all the comments we
receive and may conduct additional
rulemaking based on those comments.
Discussion
EASA, which is the Technical Agent
for the Member States of the European
Union, has issued EASA Emergency AD
No. 2016–264–E, dated December 22,
PO 00000
Frm 00013
Fmt 4700
Sfmt 4700
31899
2016, to correct an unsafe condition for
Airbus Helicopters Model SA330J
helicopters. EASA advises of reports of
broken screws that attach the cover of
the hydraulic pump. A subsequent
investigation identified a batch of
screws delivered between July 1, 2015,
and November 1, 2016, that have
intrinsic embrittlement and reduced
mechanical properties. Hydrogen was
introduced into this batch of screws
during production, causing the screws
to become brittle and lack sufficient
strength. These screws were installed in
a batch of hydraulic pumps, part
number (P/N) FR65WEO2005–175A,
identified by certain serial numbers,
EASA advises.
This condition, if not detected and
corrected, could lead to the failure of a
cover bolt and loss of fluid from the
hydraulic pump, resulting in loss of the
hydraulic system and subsequent loss of
helicopter control. As a result, EASA
AD No. 2016–264–E requires replacing
the hydraulic pumps.
FAA’s Determination
These helicopters have been approved
by the aviation authority of France and
are approved for operation in the United
States. Pursuant to our bilateral
agreement with France, EASA, its
technical representative, has notified us
of the unsafe condition described in the
EASA AD. We are issuing this AD
because we evaluated all information
provided by EASA and determined the
unsafe condition exists and is likely to
exist or develop on other helicopters of
these same type designs.
Related Service Information
We reviewed Airbus Helicopters
Emergency Alert Service Bulletin No.
SA330–29.12, Revision 0, dated
December 22, 2016 (Airbus EASB), for
Model SA330J helicopters and military
model SA330L, SA330Jm, SA330S1,
and SA330Sm helicopters. The Airbus
EASB specifies removing Nexter
Mechanics hydraulic pumps P/N
FR65WEO2005–175A with certain serial
numbers. If both the right-hand (RH)
and left-hand (LH) hydraulic pumps
have an affected P/N and serial number,
the Airbus EASB specifies replacing the
RH hydraulic pump before further flight
and the LH hydraulic pump within 110
flying hours or 6 months. If only one
hydraulic pump has an affected P/N and
serial number, the Airbus EASB
specifies replacing it within 110 flying
hours or 6 months. The Airbus EASB
also specifies that, for 6 months after
receipt of the Airbus EASB, before
installing an affected hydraulic pump it
must be ‘‘returned to conformity’’ by
complying with Nexter Mechanics Alert
E:\FR\FM\11JYR1.SGM
11JYR1
Agencies
[Federal Register Volume 82, Number 131 (Tuesday, July 11, 2017)]
[Rules and Regulations]
[Pages 31892-31899]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-14375]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9254; Directorate Identifier 2015-CE-030-AD;
Amendment 39-18948; AD 2017-14-04]
RIN 2120-AA64
Airworthiness Directives; Piper Aircraft, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (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 certain
technical standard order (TSO) requirements. AD 95-26-13 required
inspections, replacement, and adjustment of the oil cooler hose
assemblies, as well as providing for a terminating action. This AD
retains all of the requirements of AD 95-26-13 and adds language to
clarify those requirements. This AD was prompted by several inquiries
asking for clarification of the AD's applicability and compliance
requirements. We are issuing this AD to correct the unsafe condition on
these products.
DATES: This AD is effective August 15, 2017.
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 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: gary.wechsler@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 95-26-13, Amendment 39-9472 (60 FR 67321,
December 29, 1995) (``AD 95-26-13''). AD 95-26-13 applied 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 technical standard
order C53a (TSO-C53a) Type D requirements. The NPRM published in the
Federal Register on October 21, 2016 (81 FR 72742). The NPRM was
prompted by several inquiries asking for clarification of the AD's
applicability and compliance requirements. The NPRM proposed to retain
all of the requirements of AD 95-26-13 and add language to clarify
those requirements. We are issuing this AD to correct the unsafe
condition on these products.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Request the Unsafe Condition Be Addressed by Department of Commerce
G. Fenton requested this unsafe condition be addressed through the
Department of Commerce instead of the Federal Aviation Administration
because the NPRM applied to airplanes used for commercial purposes.
We disagree with this comment because the Federal Aviation
Administration is charged by Congress to provide for the safe and
efficient use of national airspace by commercial and private airplane
operators.
We have not changed the AD based on this comment.
Request To Change Labor Rate in Cost of Compliance
G. Fenton requested we change the labor rate in the Cost of
Compliance section to $72.50 per hour instead of $85 per hour. He
thought the increased
[[Page 31893]]
cost from $60 per hour from the 1995 AD to $85 per hour for this AD is
unnecessary. He thought we should adjust the cost of the labor rate to
a value between the two.
We disagree with this comment. The rate of $85 per hour is provided
by the FAA Office of Aviation Policy and Plans for us to use when
estimating the labor costs of complying with AD requirements.
We have not changed the AD based on this comment.
Request We Compile Changes From the Previous AD Into One Location
Jonathan Hartley requested we put all of the changes to this AD
from AD 95-26-13 in a conspicuous location to reduce confusion and
workload associated with compliance.
We partially agree with this comment. We agree there are instances
where compliance confusion and workload could exist with the wording in
the NPRM. However, we disagree with compiling the changes into one
location because of formatting constraints in the AD structure.
We have made language changes to the regulatory text in the AD to
clarify the compliance confusion and to reduce workload.
Request We Include an Outline for Maintaining Other Types of Oil Cooler
Hoses
Jonathan Hartley requested we include in this AD an outline
maintaining specific requirements for other types of oil cooler hoses.
We disagree with this comment. The unsafe condition addressed by
this AD applies only to Type C and Type D oil cooler hoses. The
requirements for maintaining other types of oil cooler hoses are not
required to comply with the actions of this AD.
We have not changed the AD based on this comment.
Request We Include Additional Information Describing the Types of Hoses
George Ballard requested we include in the AD information
explaining what constitutes a Type C and Type D hose assembly. He
doesn't think the TSO adequately explains the difference between the
Type C and Type D hose assemblies.
We disagree with this comment. The differences between the Type C
and Type D hoses are provided in great detail in TSO-C53a and its
referenced documents. This AD does not require that level of detail to
comply with the inspections or corrective actions specified in the AD.
We have not changed the AD based on this comment.
Request We Clarify Terminating Action for Installation of Type D Hose
Assemblies
Greg Dodson stated the requirement to inspect the oil cooler hose
assembly installation for an oil cooler mounted in a location other
than at or aft of the rear of the engine any time the oil cooler hose
assembly is replaced conflicts with the installation of a Type D oil
cooler hose assembly being terminating action for the AD.
We agree with this comment. The installation of the Type D oil
cooler hose assembly terminates the requirement for the installation
inspection.
We have changed the language in the AD to address the
contradiction.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 23,643 airplanes of U.S. registry.
This AD retains the same actions as AD 95-26-13 and the 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 this 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 AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Inspection of the oil cooler hose 1 work-hour x $85 per Not applicable...... $85 $2,009,655.
assembly. 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 hose 1 work-hour x $85 per $430................ $515 $12,176,145.
assembly. hour = $85.
----------------------------------------------------------------------------------------------------------------
Note: 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 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 inspection. We have
no way of determining the number of aircraft that might need these
adjustments:
[[Page 31894]]
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 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.
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 removing Airworthiness Directive (AD)
95-26-13, Amendment 39-9472 (60 FR 67321, December 29, 1995), and
adding the following new AD:
2017-14-04 Piper Aircraft, Inc.: Amendment 39-18948; Docket No. FAA-
2016-9254; Directorate Identifier 2015-CE-030-AD.
(a) Effective Date
This AD is effective August 15, 2017.
(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 one or more oil cooler hose assemblies that do
not meet technical standard order C53a (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) Inspection Procedures for an Oil Cooler Mounted AT or AFT of the
Rear of the Engine
For any oil cooler hose assemblies that do not meet TSO-C53a,
Type D requirements: 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 fire sleeve of each oil cooler hose assembly
for soaked oil, a brownish or whitish color, and any evidence of
brittleness or deterioration as a result of heat or oil seepage. See
figure 1 to paragraphs (g) and (h) of this AD for additional
information.
[[Page 31895]]
[GRAPHIC] [TIFF OMITTED] TR11JY17.016
Note 1 to paragraphs (g) and (h)(1) of this AD: Although not
required by this AD, the FAA recommends that an oil cooler hose
assembly flexibility test be done at 100-hour TIS intervals by
gently lifting each oil cooler hose assembly in several places along
its bottom surface, ideally at the center of an arc. If the oil
cooler hose assembly moves slightly, either from side-to-side or
upward, then some flexibility remains. If the oil cooler hose
assembly appears hardened or inflexible, replacement is recommended.
(h) Inspection Procedures for an Oil Cooler Mounted in a Location Other
Than AT or AFT of the Rear of the Engine
(1) For any oil cooler hose assemblies that do not meet TSO-
C53a, Type D requirements: 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 fire sleeve of each oil cooler hose assembly for soaked
oil, a brownish or whitish color, and any evidence of brittleness or
deterioration as a result of heat or oil seepage. See figure 1 to
paragraphs (g) and (h) of this AD for additional information.
(2) For any oil cooler hose assemblies that do not meet TSO-
C53a, Type D requirements: 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 assemblies to ensure the installation
conditions in paragraphs (h)(2)(i) through (iii) of this AD are met.
See figure 1 to paragraphs (g) and (h) of this AD for additional
information. If the conditions listed in paragraphs (h)(2)(i)
through (iii) of this AD are not met, before further flight, make
any necessary adjustments. See figure 2 to paragraph (h)(2) 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 mounts.
(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.
[[Page 31896]]
[GRAPHIC] [TIFF OMITTED] TR11JY17.001
(i) Corrective Actions
(1) If any of the conditions described in paragraph (g) or
(h)(1) of this AD are found on an oil cooler hose assembly during
the inspection required in paragraph (g) or (h)(1) of this AD, as
applicable, before further flight, replace the oil cooler hose
assembly with a serviceable new or used TSO-C53a Type D oil cooler
hose assembly or TSO-C53a Type C oil cooler hose assembly. If a used
TSO-C53a Type C oil cooler hose assembly is installed, it must have
documented hours TIS.
Note 2 to paragraphs (i)(1) and (j) of this AD: If only one of
the two oil cooler hose assemblies requires replacement, the FAA
recommends replacing both of the oil cooler hose assemblies to
simplify tracking the hours TIS of the assemblies.
(2) If a newly installed oil cooler hose assembly is a TSO-C53a
Type C oil cooler hose assembly and it is mounted in a location
other than at or aft of the rear of the engine, then replacement of
the oil cooler hose assembly must meet the conditions listed in
paragraphs (h)(2)(i) through (iii) of this AD.
(3) If compliance with paragraphs (i)(1) and (i)(2) of this AD
results in both oil cooler hose assemblies of an airplane meeting
TSO-C53a Type D requirements, then the requirements of this AD are
terminated for the airplane.
(j) Life Limit of TSO-C53a Type C Oil Cooler Hose Assemblies
(1) When a TSO-C53a Type C oil cooler hose assembly accumulates
8 years or 1,000 hours TIS, whichever occurs first, replace the oil
cooler hose assembly with a serviceable new or used TSO-C53a Type D
oil cooler hose assembly or TSO-C53a Type C oil cooler hose
assembly. If a used TSO-C53a Type C oil cooler hose assembly is
installed, it must have documented hours TIS. If the newly installed
oil cooler is a TSO-C53a Type C oil cooler hose assembly and it is
mounted in a location other than at or aft of the rear of the engine
the installation must meet the conditions listed in paragraphs
(h)(2)(i) through (iii) of this AD.
(2) You may at any time before a TSO-C53a Type C oil cooler hose
assembly exceeds the life limit in paragraph (j)(1) of this AD,
replace a TSO-C53a Type C oil cooler hose assembly with a TSO-C53a
Type D oil cooler hose assembly.
(3) If compliance with paragraphs (j)(1) or (j)(2) of this AD
results in both oil cooler hose assemblies of an airplane meeting
TSO-C53a Type D requirements, then the requirements of this AD are
terminated for the airplane.
(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 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.
[[Page 31897]]
(3) AMOCs approved for AD 95-26-13 (60 FR 67321, December 29,
1995) are not approved as AMOCs for the corresponding provisions of
this AD.
(l) 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 31898]]
[GRAPHIC] [TIFF OMITTED] TR11JY17.018
[[Page 31899]]
Issued in Kansas City, Missouri, on June 29, 2017.
Pat Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-14375 Filed 7-10-17; 8:45 am]
BILLING CODE 4910-13-C