Airworthiness Directives; Mitsubishi Heavy Industries, Ltd. Airplanes, 4217-4220 [2016-01381]
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Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Proposed Rules
4217
TABLE 1 TO PARAGRAPH (C) OF THIS AD—APPLICABLE ENGINES AND FUEL PUMP HOSE ASSEMBLIES—Continued
Engine
Manufacturer’s hose name
Manufacturer’s part No. (P/N)
Hose description
LTIO–540–J2BD (left wing) ...........
Hose Assembly—Fuel ..................
Piper 39995–034 ..........................
Inlet fuel hose to engine fuel
pump.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 73: Engine Fuel and Control.
(e) Unsafe Condition
This AD was prompted by a report of an
engine fire caused by a leak in the fuel pump
inlet hose. We are issuing this AD to correct
the unsafe condition on these products.
(f) Compliance
Comply with this AD within the
compliance times specified in paragraphs
(g)(1) through (j)(2) of this AD, unless already
done.
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(g) Ensure Proper Clearance Between the
Fuel Hose Assembly and the Turbocharger
Support Assembly
(1) Within the next 60 hours time-inservice (TIS) after the effective date of this
AD or within the next 6 months after the
effective date of this AD, whichever occurs
first, inspect to determine the clearance
between the inlet and exit fuel hose
assemblies listed in table 1 to paragraph (c)
of this AD, and each turbocharger support
assembly, Lycoming P/N LW–18302. There
should be a minimum 3⁄16-inch clearance. Do
the inspection following the INSTRUCTIONS
section of Piper Aircraft, Inc. Service Bulletin
No. 1257A, dated August 4, 2015.
(2) Before further flight after the inspection
required in paragraph (g)(1) of this AD, if the
measured clearance is less than 3⁄16-inch,
make all necessary adjustments to make the
clearance a minimum of 3⁄16-inch between
the inlet and exit fuel hose assemblies listed
in table 1 to paragraph (c) of this AD and
each turbocharger support assembly,
Lycoming P/N LW–18302, following the
INSTRUCTIONS section of Piper Aircraft,
Inc. Service Bulletin No. 1257A, dated
August 4, 2015.
(h) Visually Inspect the Fuel Hose Assembly
and Replace if Necessary
(1) Within the next 60 hours TIS after the
effective date of this AD or within the next
6 months after the effective date of this AD,
whichever occurs first, visually inspect the
inlet and exit fuel hose assemblies listed in
table 1 to paragraph (c) of this AD for
evidence of leaking, cracking, chafing, and
any other sign of damage. Do the inspection
following the INSTRUCTIONS section of
Piper Aircraft, Inc. Service Bulletin No.
1257A, dated August 4, 2015.
(2) Before further flight after the inspection
required in paragraph (h)(1) of this AD, if any
evidence of leaking, cracking, chafing, or any
other sign of damage is found in any inlet or
exit fuel host assembly listed in table 1 to
paragraph (c) of this AD, replace the fuel
hose assembly with a serviceable part. Do the
replacement following the INSTRUCTIONS
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section of Piper Aircraft, Inc. Service Bulletin
No. 1257A, dated August 4, 2015.
(i) Visually Inspect the Turbocharger
Support Assembly and Replace if Necessary
(1) Within the next 60 hours TIS after the
effective date of this AD or within the next
6 months after the effective date of this AD,
whichever occurs first, visually inspect each
turbocharger support assembly, Lycoming P/
N LW–18302, for evidence of chafing and any
other signs of damage. Do the inspection
following the INSTRUCTIONS section of
Piper Aircraft, Inc. Service Bulletin No.
1257A, dated August 4, 2015.
(2) Before further flight after the inspection
required in paragraph (i)(1) of this AD, if any
evidence of chafing or any other sign of
damage is found on any turbocharger support
assembly, replace Lycoming
P/N LW–18302 with a serviceable part. Do
the replacement following the
INSTRUCTIONS section of Piper Aircraft,
Inc. Service Bulletin No. 1257A, dated
August 4, 2015.
FAA, Atlanta ACO, 1701 Columbia Avenue,
College Park, Georgia 30337; telephone: (404)
474–5575; fax: (404) 474–5606; email:
gary.wechsler@faa.gov.
(2) For service information identified in
this AD, contact Piper Aircraft, Inc., 926
Piper Drive, Vero Beach, Florida 32960;
telephone: (772) 567–4361; fax: (772) 978–
6573; Internet: www.piper.com/home/pages/
Publications.cfm. You may review copies of
the referenced service information at the
FAA, Small Airplane Directorate, 901 Locust,
Kansas City, Missouri 64106. For information
on the availability of this material at the
FAA, call (816) 329–4148.
Issued in Kansas City, Missouri, on January
16, 2016.
Melvin Johnson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2016–01380 Filed 1–25–16; 8:45 am]
BILLING CODE 4910–13–P
(j) Engine Run-Up
(1) If any fuel line component was adjusted
or replaced during any actions required in
paragraphs (g)(1) through (i)(2) of this AD,
before further flight, perform an engine runup on the ground to check for leaks. Do the
engine run-up following the INSTRUCTIONS
section of Piper Aircraft, Inc. Service Bulletin
No. 1257A, dated August 4, 2015.
(2) If any leaks found during the engine
run-up required in paragraph (j)(1) of this AD
emanate from any fuel line component
adjusted, repaired, or replaced during any
actions required in paragraphs (g)(1) through
(i)(2) of this AD, before further flight, take all
necessary corrective actions following the
INSTRUCTIONS section of Piper Aircraft,
Inc. Service Bulletin No. 1257A, dated
August 4, 2015.
DEPARTMENT OF TRANSPORTATION
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Atlanta Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
SUMMARY:
(l) Related Information
(1) For more information about this AD,
contact Gary Wechsler, Aerospace Engineer,
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–1363; Directorate
Identifier 2015–CE–040–AD]
RIN 2120–AA64
Airworthiness Directives; Mitsubishi
Heavy Industries, Ltd. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Mitsubishi Heavy Industries, Ltd.
Models MU–2B–30, MU–2B–35, MU–
2B–36, MU–2B–36A, and MU–2B–60
airplanes. This proposed AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as reports of cracks found in
the attach fittings of the main landing
gear oleo strut. We are issuing this
proposed AD to require actions to
address the unsafe condition on these
products.
DATES: We must receive comments on
this proposed AD by March 11, 2016.
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Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Proposed Rules
You may send comments 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: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590,
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Mitsubishi
Heavy Industries America, Inc., c/o
Turbine Aircraft Services, Inc., 4550
Jimmy Doolittle Drive, Addison, Texas
75001; telephone: (972) 248–3108, ext.
209; fax: (972) 248–3321; Internet:
https://mu-2aircraft.com. You may
review this referenced service
information at the FAA, Small Airplane
Directorate, 901 Locust, Kansas City,
Missouri 64106. For information on the
availability of this material at the FAA,
call (816) 329–4148.
ADDRESSES:
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–
1363; 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:
Andrew McAnaul, Aerospace Engineer,
FAA, ASW–143 (c/o San Antonio
MIDO), 10100 Reunion Place, Suite 650,
San Antonio, Texas 78216; phone: (210)
308–3365; fax: (210) 308–3370; email:
andrew.mcanaul@faa.gov.
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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–2016–1363; Directorate Identifier
2015–CE–040–AD’’ at the beginning of
your comments. We specifically invite
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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://
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
The Japan Civil Aviation Bureau
(JCAB), which is the aviation authority
for Japan, has issued AD No. TCD–
8595–2015, dated July 1, 2015 (referred
to after this as ‘‘the MCAI’’), to correct
an unsafe condition for certain
Mitsubishi Heavy Industries, Ltd. (MHI)
Models MU–2B–30, MU–2B–35, and
MU–2B–36 airplanes. You may examine
the MCAI on the Internet at https://
www.regulations.gov by searching for
and locating it in Docket No. FAA–
2016–1363.
We have received reports of seven
failures of the main landing gear oleo
strut attach fitting on certain MHI
Models MU–2B–30, MU–2B–35, MU–
2B–36, MU–2B–36A, and MU–2B–60
airplanes. Investigation revealed that the
failures resulted from improper
lubrication and/or hard landings, which
caused cracks to develop in the main
landing gear oleo strut attach fitting.
Japan is the State of Design for MHI
Models MU–2B–30, MU–2B–35, and
MU–2B–36, which the MCAI AD
applies to, and the United States is the
State of Design for MHI Models MU–
2B–36A and MU–2B–60 airplanes.
Related Service Information Under
1 CFR Part 51
Mitsubishi Heavy Industries, Ltd. has
issued MU–2 Service Bulletin No. 243,
dated June 30, 2015, and MU–2 Service
Bulletin No. 105/32–017, dated
September 29, 2015. These service
bulletins describe procedures for
visually inspecting the lugs of the oleo
attach fittings on both sides for cracks,
and if any visible cracks are found,
replacing with a new fitting. Mitsubishi
Heavy Industries, Ltd. has also issued
MU–2 Service News JCAB T.C.: No. 171,
FAA T.C.: No. 124/32–011, dated April
27, 2012, and MU–2 Service News JCAB
T.C.: No. 176, FAA T.C.: No. 128/32–
013, dated July 18, 2013. This service
information specifies doing repetitive
ultrasound inspections of the main
landing gear oleo upper attach fittings
for cracks and ensuring proper
lubrication of the main landing gear
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Sfmt 4702
oleo fitting. All the related service
information is reasonably available
because the interested parties have
access to it through their normal course
of business or by the means identified
in the ADDRESSES section of this NPRM.
FAA’s Determination and Requirements
of the Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with this State of
Design Authority, they have notified us
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between This Proposed AD
and the MCAI
We have determined that the
repetitive visual inspections specified in
the MCAI are not adequate for detecting
cracks in the main landing gear oleo
strut attach fitting. Repetitive ultrasonic
inspections of the main landing gear
oleo strut attach fitting have been added
into the maintenance requirement
manual for these airplanes, which is not
considered mandatory in the FAA’s
airworthiness regulatory system.
Therefore, we are proposing to
incorporate that requirement through
the rulemaking process.
Costs of Compliance
We estimate that this proposed AD
will affect 95 products of U.S. registry.
We also estimate that it would take
about 5 work-hours per product to
comply with the visual inspection
requirement of this proposed AD. The
average labor rate is $85 per work-hour.
Based on these figures, we estimate
the cost of the visual inspection
requirements of this proposed AD on
U.S. operators to be $40,375, or $425 per
product.
We also estimate that it would take
about 3 work-hours per product to
comply with the ultrasound inspection
requirements of this proposed AD. The
average labor rate is $85 per work-hour.
Based on these figures, we estimate
the cost of the ultrasound inspection
requirements of this proposed AD on
U.S. operators to be $24,225, or $255 per
product.
Owner/operators have the option to
do an ultrasound inspection in lieu of
the required visual inspection.
In addition, we estimate that any
necessary follow-on actions would take
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Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Proposed Rules
about 24 work-hours and require parts
costing $5,220, for a cost of $7,260 per
product to replace the left-hand main
landing gear oleo strut. We have no way
of determining the number of products
that may need this action.
In addition, we also estimate that any
necessary follow-on actions would take
about 45 work-hours and require parts
costing $5,220, for a cost of $9,045 per
product to replace the right-hand main
landing gear oleo strut. We have no way
of determining the number of products
that may need this action.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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 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 this 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.
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Jkt 238001
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 adding
the following new AD:
■
Mitsubishi Heavy Industries, Ltd.: Docket
No. FAA–2016–1363; Directorate
Identifier 2015–CE–040–AD.
(a) Comments Due Date
We must receive comments by March 11,
2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Mitsubishi Heavy
Industries, Ltd. Models MU–2B–30, MU–2B–
35, MU–2B–36 airplanes, serial numbers 502
through 696, except 652 and 661, and Models
MU–2B–36A and MU–2B–60 airplanes, serial
numbers 661SA, and 697SA through 1569SA,
certificated in any category.
(d) Subject
Air Transport Association of America
(ATA) Code 32: Landing Gear.
(e) Reason
This AD was prompted by mandatory
continuing airworthiness information (MCAI)
originated by an aviation authority of another
country to identify and correct an unsafe
condition on an aviation product. The MCAI
describes the unsafe condition as reports of
cracks found in the fittings of the main
landing gear oleo strut. We are issuing this
proposed AD to prevent failure of the main
landing gear oleo strut attach fitting, which
could cause the landing gear to fail and result
in loss of control.
(f) Actions and Compliance
Unless already done, do the following
actions:
(1) Within the next 100 hours time-inservice (TIS) after the effective date of this
AD or within the next 6 months after the
effective date of this AD, whichever occurs
first, do a visual inspection of the main
landing gear oleo upper attach fittings for
cracks. Do the inspection following the
INSTRUCTIONS section in Mitsubishi Heavy
Industries, Ltd. MU–2 Service Bulletin No.
243, dated June 30, 2015, and the
INSTRUCTIONS section in Mitsubishi Heavy
PO 00000
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Fmt 4702
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4219
Industries, Ltd. MU–2 Service Bulletin No.
105/32–017, dated September 29, 2015, as
applicable.
(2) Before further flight after the inspection
required in paragraph (f)(1) of this AD, if no
signs of cracks are found, lubricate the pin
assembly attached to the main landing gear
oleo attach fitting as specified in Mitsubishi
Heavy Industries, Ltd. MU–2 Service News
JCAB T.C.: No. 171, FAA T.C.: No. 124/32–
011, dated April 27, 2012.
(3) Within the next 100 hours TIS after
doing the initial visual inspection required in
paragraph (f)(1) of this AD or within the next
12 months after doing the initial visual
inspection required in paragraph (f)(1) of this
AD, whichever occurs first, do an ultrasound
inspection of the main landing gear oleo
upper attach fittings for cracks as specified in
Mitsubishi Heavy Industries, Ltd. MU–2
Service News JCAB T.C.: No. 176, FAA T.C.:
No. 128/32–013, dated July 18, 2013. This
ultrasound inspection may also be done in
place of the visual inspection required in
paragraph (f)(1) of this AD if done within the
next 100 hours TIS after the effective date of
this AD or within the next 6 months after the
effective date of this AD, whichever occurs
first. Repetitively thereafter inspect every 600
hours TIS or 36 months, whichever occurs
first, and any time a hard landing or
overweight landing occurs.
(4) Before further flight after any inspection
required in paragraph (f)(3) of this AD, if no
signs of cracks are found, lubricate the pin
assembly attached to the main landing gear
oleo attach fitting as specified in Mitsubishi
Heavy Industries, Ltd. MU–2 Service News
JCAB T.C.: No. 171, FAA T.C.: No. 124/32–
011, dated April 27, 2012, and Mitsubishi
Heavy Industries, Ltd. MU–2 Service News
JCAB T.C.: No. 176, FAA T.C.: No. 128/32–
013, dated July 18, 2013.
(5) Before further flight after any inspection
required in paragraph (f)(1) and (f)(3) of this
AD where cracks are found, replace the main
landing gear oleo upper attach fittings
following the INSTRUCTIONS section in
Mitsubishi Heavy Industries, Ltd. MU–2
Service Bulletin No. 243, dated June 30,
2015, and the INSTRUCTIONS sections in
Mitsubishi Heavy Industries, Ltd. MU–2
Service Bulletin No. 105/32–017, dated
September 29, 2015, as applicable. After
replacement, continue with the repetitive
ultrasound inspection requirements of
paragraph (f)(3) of this AD.
(g) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Andrew McAnaul, Aerospace
Engineer, FAA, ASW–143 (c/o San Antonio
MIDO), 10100 Reunion Place, Suite 650, San
Antonio, Texas 78216; phone: (210) 308–
3365; fax: (210) 308–3370; email:
andrew.mcanaul@faa.gov. Before using any
approved AMOC on any airplane to which
the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking
a PI, your local FSDO.
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(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(h) Related Information
Refer to MCAI Japan Civil Aviation Bureau
(JCAB) AD No. TCD–8585–2015, dated July 1,
2015, for related information. You may
examine the MCAI on the Internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2016–1363. For
service information related to this AD,
contact Mitsubishi Heavy Industries
America, Inc., c/o Turbine Aircraft Services,
Inc., 4550 Jimmy Doolittle Drive, Addison,
Texas 75001; telephone: (972) 248–3108, ext.
209; fax: (972) 248–3321; Internet: https://mu2aircraft.com. You may review this
referenced service information at the FAA,
Small Airplane Directorate, 901 Locust,
Kansas City, Missouri 64106. For information
on the availability of this material at the
FAA, call (816) 329–4148.
Issued in Kansas City, Missouri, on January
16, 2016.
Melvin Johnson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2016–01381 Filed 1–25–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
FOR FURTHER INFORMATION CONTACT:
[Docket No. FAA–2015–4133; Airspace
Docket No. 15–ANM–27]
Steve Haga, Federal Aviation
Administration, Operations Support
Group, Western Service Center, 1601
Lind Avenue SW., Renton, WA 98057;
telephone (425) 203–4563.
Proposed Revocation of Class D
Airspace; Vancouver, WA
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
This action proposes to
remove Class D airspace at Pearson
Field, Vancouver, WA. FAA Joint Order
7400.2K states that non-towered airports
requiring a surface area will be
designated Class E. Class E surface area
airspace was established on December
10, 2015. The FAA is proposing this
action due to the lack of an operating air
traffic control tower at Pearson Field
Airport, Vancouver, WA.
DATES: Comments must be received on
or before March 11, 2016.
ADDRESSES: Send comments on this
proposal to the U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
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SUMMARY:
VerDate Sep<11>2014
17:48 Jan 25, 2016
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590;
telephone (202) 366–9826. You must
identify FAA Docket No. FAA–2015–
4133; Airspace Docket No. 15–ANM–27,
at the beginning of your comments. You
may also submit comments through the
Internet at https://www.regulations.gov.
You may review the public docket
containing the proposal, any comments
received, and any final disposition in
person in the Dockets Office between
9:00 a.m. and 5:00 p.m., Monday
through Friday, except Federal holidays.
The Docket Office (telephone 1–800–
647–5527), is on the ground floor of the
building at the above address.
FAA Order 7400.9Z, Airspace
Designations and Reporting Points, and
subsequent amendments can be viewed
online at https://www.faa.gov/air_traffic/
publications/. For further information,
you can contact the Airspace Policy
Group, Federal Aviation
Administration, 800 Independence
Avenue SW., Washington, DC 29591;
telephone: 202–267–8783. The Order is
also available for inspection at the
National Archives and Records
Administration (NARA). For
information on the availability of FAA
Order 7400.9Z at NARA, call 202–741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federalregulations/ibr_locations.html.
FAA Order 7400.9, Airspace
Designations and Reporting Points, is
published yearly and effective on
September 15.
Jkt 238001
SUPPLEMENTARY INFORMATION:
Authority for This Rulemaking
The FAA’s authority to issue rules
regarding aviation safety is found in
Title 49 of the United States Code.
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. This rulemaking is
promulgated under the authority
described in Subtitle VII, Part, A,
Subpart I, Section 40103. Under that
section, the FAA is charged with
prescribing regulations to assign the use
of airspace necessary to ensure the
safety of aircraft and the efficient use of
airspace. This regulation is within the
scope of that authority as it would
remove Class D airspace at Pearson
Field Airport, Vancouver, WA.
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Comments Invited
Interested parties are invited to
participate in this proposed rulemaking
by submitting such written data, views,
or arguments, as they may desire.
Comments that provide the factual basis
supporting the views and suggestions
presented are particularly helpful in
developing reasoned regulatory
decisions on the proposal. Comments
are specifically invited on the overall
regulatory, aeronautical, economic,
environmental, and energy-related
aspects of the proposal.
Communications should identify both
docket numbers and be submitted in
triplicate to the address listed above.
Commenters wishing the FAA to
acknowledge receipt of their comments
on this notice must submit with those
comments a self-addressed, stamped
postcard on which the following
statement is made: ‘‘Comments to
Docket No. FAA–2015–4133; Airspace
Docket No. 15–ANM–27.’’ The postcard
will be date/time stamped and returned
to the commenter.
Availability of NPRMs
An electronic copy of this document
may be downloaded through the
Internet at https://www.regulations.gov.
Recently published rulemaking
documents can also be accessed through
the FAA’s Web page at https://www.faa.
gov/airports_airtraffic/air_traffic/
publications/airspace_amendments/.
You may review the public docket
containing the proposal, any comments
received, and any final disposition in
person in the Dockets Office (see the
ADDRESSES section for the address and
phone number) between 9:00 a.m. and
5:00 p.m., Monday through Friday,
except federal holidays. An informal
docket may also be examined during
normal business hours at the Northwest
Mountain Regional Office of the Federal
Aviation Administration, Air Traffic
Organization, Western Service Center,
Operations Support Group, 1601 Lind
Avenue SW., Renton, WA 98057.
Persons interested in being placed on
a mailing list for future NPRMs should
contact the FAA’s Office of Rulemaking,
(202) 267–9677, for a copy of Advisory
Circular No. 11–2A, Notice of Proposed
Rulemaking Distribution System, which
describes the application procedure.
Availability and Summary of
Documents Proposed for Incorporation
by Reference
This document would amend FAA
Order 7400.9Z, Airspace Designations
and Reporting Points, dated August 6,
2015, and effective September 15, 2015.
FAA Order 7400.9Z is publicly available
E:\FR\FM\26JAP1.SGM
26JAP1
]]>Agencies
[Federal Register Volume 81, Number 16 (Tuesday, January 26, 2016)]
[Proposed Rules]
[Pages 4217-4220]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-01381]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-1363; Directorate Identifier 2015-CE-040-AD]
RIN 2120-AA64
Airworthiness Directives; Mitsubishi Heavy Industries, Ltd.
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Mitsubishi Heavy Industries, Ltd. Models MU-2B-30, MU-2B-35,
MU-2B-36, MU-2B-36A, and MU-2B-60 airplanes. This proposed AD results
from mandatory continuing airworthiness information (MCAI) originated
by an aviation authority of another country to identify and correct an
unsafe condition on an aviation product. The MCAI describes the unsafe
condition as reports of cracks found in the attach fittings of the main
landing gear oleo strut. We are issuing this proposed AD to require
actions to address the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by March 11, 2016.
[[Page 4218]]
ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Mitsubishi Heavy Industries America, Inc., c/o Turbine Aircraft
Services, Inc., 4550 Jimmy Doolittle Drive, Addison, Texas 75001;
telephone: (972) 248-3108, ext. 209; fax: (972) 248-3321; Internet:
https://mu-2aircraft.com. You may review this referenced service
information at the FAA, Small Airplane Directorate, 901 Locust, Kansas
City, Missouri 64106. For information on the availability of this
material at the FAA, call (816) 329-4148.
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-
1363; 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: Andrew McAnaul, Aerospace Engineer,
FAA, ASW-143 (c/o San Antonio MIDO), 10100 Reunion Place, Suite 650,
San Antonio, Texas 78216; phone: (210) 308-3365; fax: (210) 308-3370;
email: andrew.mcanaul@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-2016-1363;
Directorate Identifier 2015-CE-040-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://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
The Japan Civil Aviation Bureau (JCAB), which is the aviation
authority for Japan, has issued AD No. TCD-8595-2015, dated July 1,
2015 (referred to after this as ``the MCAI''), to correct an unsafe
condition for certain Mitsubishi Heavy Industries, Ltd. (MHI) Models
MU-2B-30, MU-2B-35, and MU-2B-36 airplanes. You may examine the MCAI on
the Internet at https://www.regulations.gov by searching for and
locating it in Docket No. FAA-2016-1363.
We have received reports of seven failures of the main landing gear
oleo strut attach fitting on certain MHI Models MU-2B-30, MU-2B-35, MU-
2B-36, MU-2B-36A, and MU-2B-60 airplanes. Investigation revealed that
the failures resulted from improper lubrication and/or hard landings,
which caused cracks to develop in the main landing gear oleo strut
attach fitting.
Japan is the State of Design for MHI Models MU-2B-30, MU-2B-35, and
MU-2B-36, which the MCAI AD applies to, and the United States is the
State of Design for MHI Models MU-2B-36A and MU-2B-60 airplanes.
Related Service Information Under 1 CFR Part 51
Mitsubishi Heavy Industries, Ltd. has issued MU-2 Service Bulletin
No. 243, dated June 30, 2015, and MU-2 Service Bulletin No. 105/32-017,
dated September 29, 2015. These service bulletins describe procedures
for visually inspecting the lugs of the oleo attach fittings on both
sides for cracks, and if any visible cracks are found, replacing with a
new fitting. Mitsubishi Heavy Industries, Ltd. has also issued MU-2
Service News JCAB T.C.: No. 171, FAA T.C.: No. 124/32-011, dated April
27, 2012, and MU-2 Service News JCAB T.C.: No. 176, FAA T.C.: No. 128/
32-013, dated July 18, 2013. This service information specifies doing
repetitive ultrasound inspections of the main landing gear oleo upper
attach fittings for cracks and ensuring proper lubrication of the main
landing gear oleo fitting. All the related service information is
reasonably available because the interested parties have access to it
through their normal course of business or by the means identified in
the ADDRESSES section of this NPRM.
FAA's Determination and Requirements of the Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with this State of Design Authority, they
have notified us of the unsafe condition described in the MCAI and
service information referenced above. We are proposing this AD because
we evaluated all information and determined the unsafe condition exists
and is likely to exist or develop on other products of the same type
design.
Differences Between This Proposed AD and the MCAI
We have determined that the repetitive visual inspections specified
in the MCAI are not adequate for detecting cracks in the main landing
gear oleo strut attach fitting. Repetitive ultrasonic inspections of
the main landing gear oleo strut attach fitting have been added into
the maintenance requirement manual for these airplanes, which is not
considered mandatory in the FAA's airworthiness regulatory system.
Therefore, we are proposing to incorporate that requirement through the
rulemaking process.
Costs of Compliance
We estimate that this proposed AD will affect 95 products of U.S.
registry. We also estimate that it would take about 5 work-hours per
product to comply with the visual inspection requirement of this
proposed AD. The average labor rate is $85 per work-hour.
Based on these figures, we estimate the cost of the visual
inspection requirements of this proposed AD on U.S. operators to be
$40,375, or $425 per product.
We also estimate that it would take about 3 work-hours per product
to comply with the ultrasound inspection requirements of this proposed
AD. The average labor rate is $85 per work-hour.
Based on these figures, we estimate the cost of the ultrasound
inspection requirements of this proposed AD on U.S. operators to be
$24,225, or $255 per product.
Owner/operators have the option to do an ultrasound inspection in
lieu of the required visual inspection.
In addition, we estimate that any necessary follow-on actions would
take
[[Page 4219]]
about 24 work-hours and require parts costing $5,220, for a cost of
$7,260 per product to replace the left-hand main landing gear oleo
strut. We have no way of determining the number of products that may
need this action.
In addition, we also estimate that any necessary follow-on actions
would take about 45 work-hours and require parts costing $5,220, for a
cost of $9,045 per product to replace the right-hand main landing gear
oleo strut. We have no way of determining the number of products that
may need this action.
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 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 this 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 adding the following new AD:
Mitsubishi Heavy Industries, Ltd.: Docket No. FAA-2016-1363;
Directorate Identifier 2015-CE-040-AD.
(a) Comments Due Date
We must receive comments by March 11, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Mitsubishi Heavy Industries, Ltd. Models MU-
2B-30, MU-2B-35, MU-2B-36 airplanes, serial numbers 502 through 696,
except 652 and 661, and Models MU-2B-36A and MU-2B-60 airplanes,
serial numbers 661SA, and 697SA through 1569SA, certificated in any
category.
(d) Subject
Air Transport Association of America (ATA) Code 32: Landing
Gear.
(e) Reason
This AD was prompted by mandatory continuing airworthiness
information (MCAI) originated by an aviation authority of another
country to identify and correct an unsafe condition on an aviation
product. The MCAI describes the unsafe condition as reports of
cracks found in the fittings of the main landing gear oleo strut. We
are issuing this proposed AD to prevent failure of the main landing
gear oleo strut attach fitting, which could cause the landing gear
to fail and result in loss of control.
(f) Actions and Compliance
Unless already done, do the following actions:
(1) Within the next 100 hours time-in-service (TIS) after the
effective date of this AD or within the next 6 months after the
effective date of this AD, whichever occurs first, do a visual
inspection of the main landing gear oleo upper attach fittings for
cracks. Do the inspection following the INSTRUCTIONS section in
Mitsubishi Heavy Industries, Ltd. MU-2 Service Bulletin No. 243,
dated June 30, 2015, and the INSTRUCTIONS section in Mitsubishi
Heavy Industries, Ltd. MU-2 Service Bulletin No. 105/32-017, dated
September 29, 2015, as applicable.
(2) Before further flight after the inspection required in
paragraph (f)(1) of this AD, if no signs of cracks are found,
lubricate the pin assembly attached to the main landing gear oleo
attach fitting as specified in Mitsubishi Heavy Industries, Ltd. MU-
2 Service News JCAB T.C.: No. 171, FAA T.C.: No. 124/32-011, dated
April 27, 2012.
(3) Within the next 100 hours TIS after doing the initial visual
inspection required in paragraph (f)(1) of this AD or within the
next 12 months after doing the initial visual inspection required in
paragraph (f)(1) of this AD, whichever occurs first, do an
ultrasound inspection of the main landing gear oleo upper attach
fittings for cracks as specified in Mitsubishi Heavy Industries,
Ltd. MU-2 Service News JCAB T.C.: No. 176, FAA T.C.: No. 128/32-013,
dated July 18, 2013. This ultrasound inspection may also be done in
place of the visual inspection required in paragraph (f)(1) of this
AD if done within the next 100 hours TIS after the effective date of
this AD or within the next 6 months after the effective date of this
AD, whichever occurs first. Repetitively thereafter inspect every
600 hours TIS or 36 months, whichever occurs first, and any time a
hard landing or overweight landing occurs.
(4) Before further flight after any inspection required in
paragraph (f)(3) of this AD, if no signs of cracks are found,
lubricate the pin assembly attached to the main landing gear oleo
attach fitting as specified in Mitsubishi Heavy Industries, Ltd. MU-
2 Service News JCAB T.C.: No. 171, FAA T.C.: No. 124/32-011, dated
April 27, 2012, and Mitsubishi Heavy Industries, Ltd. MU-2 Service
News JCAB T.C.: No. 176, FAA T.C.: No. 128/32-013, dated July 18,
2013.
(5) Before further flight after any inspection required in
paragraph (f)(1) and (f)(3) of this AD where cracks are found,
replace the main landing gear oleo upper attach fittings following
the INSTRUCTIONS section in Mitsubishi Heavy Industries, Ltd. MU-2
Service Bulletin No. 243, dated June 30, 2015, and the INSTRUCTIONS
sections in Mitsubishi Heavy Industries, Ltd. MU-2 Service Bulletin
No. 105/32-017, dated September 29, 2015, as applicable. After
replacement, continue with the repetitive ultrasound inspection
requirements of paragraph (f)(3) of this AD.
(g) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Office, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. Send
information to ATTN: Andrew McAnaul, Aerospace Engineer, FAA, ASW-
143 (c/o San Antonio MIDO), 10100 Reunion Place, Suite 650, San
Antonio, Texas 78216; phone: (210) 308-3365; fax: (210) 308-3370;
email: andrew.mcanaul@faa.gov. Before using any approved AMOC on any
airplane to which the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
[[Page 4220]]
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(h) Related Information
Refer to MCAI Japan Civil Aviation Bureau (JCAB) AD No. TCD-
8585-2015, dated July 1, 2015, for related information. You may
examine the MCAI on the Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2016-1363. For service
information related to this AD, contact Mitsubishi Heavy Industries
America, Inc., c/o Turbine Aircraft Services, Inc., 4550 Jimmy
Doolittle Drive, Addison, Texas 75001; telephone: (972) 248-3108,
ext. 209; fax: (972) 248-3321; Internet: https://mu-2aircraft.com.
You may review this referenced service information at the FAA, Small
Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For
information on the availability of this material at the FAA, call
(816) 329-4148.
Issued in Kansas City, Missouri, on January 16, 2016.
Melvin Johnson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-01381 Filed 1-25-16; 8:45 am]
BILLING CODE 4910-13-P
