Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes, 66175-66178 [2018-27899]
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Federal Register / Vol. 83, No. 246 / Wednesday, December 26, 2018 / Proposed Rules
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 airworthiness
directive (AD):
■
The Boeing Company: Docket No. FAA–
2018–1011; Product Identifier 2018–
NM–131–AD.
(a) Comments Due Date
We must receive comments by February
11, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing
Company Model 767–200, –300, –300F, and
–400ER series airplanes, certificated in any
category.
(d) Subject
Air Transport Association (ATA) of
America Code 25, Equipment/Furnishings.
(e) Unsafe Condition
This AD was prompted by reports of
uncommanded movements of the Captain’s
and First Officer’s seats. We are issuing this
AD to address uncommanded movement of
the Captain’s and First Officer’s seats. An
uncommanded seat movement during a
critical part of a flight, such as take-off or
landing, could cause a flight control
obstruction or unintended flight control
input, which could result in the loss of the
ability to control the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Seat Identification and On-Condition
Actions
Within 36 months after the effective date
of this AD, do an inspection to determine the
part number, and serial number as
applicable, of the Captain’s and First
Officer’s seats, and do all applicable oncondition actions, in accordance with the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 767–25–
0539, Revision 1, dated July 17, 2018.
(h) Detailed Inspection and Repetitive
Checks of Horizontal Movement System and
On-Condition Actions
Except as specified in paragraph (i) of this
AD: At the applicable times specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Special Attention Service Bulletin 767–25–
0549, Revision 1, dated August 10, 2018
(‘‘BSASB 767–25–0549, Revision 1’’), do all
applicable actions identified as ‘‘RC’’
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(required for compliance) in, and in
accordance with, the Accomplishment
Instructions of BSASB 767–25–0549,
Revision 1.
(i) Exceptions to Service Information
Specifications
For purposes of determining compliance
with the requirements of this AD: Where
BSASB 767–25–0549, Revision 1, uses the
phrase ‘‘the original issue date of this service
bulletin,’’ this AD requires using ‘‘the
effective date of this AD.’’
(j) Optional Terminating Action for
Repetitive Checks
(1) For Group 1, Configuration 2 and 4
airplanes identified in BSASB 767–25–0549,
Revision 1: Installation of a serviceable
Captain’s seat, as specified in, and in
accordance with, the Accomplishment
Instructions of BSASB 767–25–0549,
Revision 1, terminates the repetitive checks
of the Captain’s seat as required by paragraph
(h) of this AD for that airplane only.
(2) For Group 1, Configuration 3 and 4
airplanes: Installation of a serviceable First
Officer’s seat BSASB 767–25–0549, Revision
1, as specified in, and in accordance with,
the Accomplishment Instructions of BSASB
767–25–0549, Revision 1, terminates the
repetitive checks of the First Officer’s seat as
required by paragraph (h) of this AD for that
airplane only.
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle ACO Branch,
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
certification office, send it to the attention of
the person identified in paragraph (l)(1) of
this AD. Information may be emailed to: 9ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle ACO
Branch, FAA, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) For service information that contains
steps that are labeled as Required for
Compliance (RC), the provisions of
paragraphs (k)(4)(i) and (k)(4)(ii) of this AD
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
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66175
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(l) Related Information
(1) For more information about this AD,
contact Brandon Lucero, Aerospace Engineer,
Cabin Safety and Environmental Systems
Section, FAA, Seattle ACO Branch, 2200
South 216th St., Des Moines, WA 98198;
phone and fax: 206–231–3569; email:
Brandon.Lucero@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet https://
www.myboeingfleet.com. You may view this
referenced service information at the FAA,
Transport Standards Branch, 2200 South
216th St., Des Moines, WA. For information
on the availability of this material at the
FAA, call 206–231–3195.
Issued in Des Moines, Washington, on
December 13, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–27882 Filed 12–21–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–1058; Product
Identifier 2018–CE–051–AD]
RIN 2120–AA64
Airworthiness Directives; Pilatus
Aircraft 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 Pilatus
Aircraft Ltd. Model PC–6, PC–6/350,
PC–6/350–H1, PC–6/350–H2, PC–6/A,
PC–6/A–H1, PC–6/A–H2, PC–6/B–H2,
PC–6/B1–H2, PC–6/B2–H2, PC–6/B2–
H4, PC–6/C–H2, PC–6/C1–H2, PC–6–
H1, and PC–6–H2 airplanes. This
proposed AD results from mandatory
continuing airworthiness information
(MCAI) originated by an aviation
authority of another country to identify
SUMMARY:
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Federal Register / Vol. 83, No. 246 / Wednesday, December 26, 2018 / Proposed Rules
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and correct an unsafe condition on an
aviation product. The MCAI describes
the unsafe condition as sheared or
missing rivets on the horizontal
stabilizer hinge bracket assemblies. 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 February 11, 2019.
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 PILATUS
Aircraft Ltd., Customer Technical
Support (MCC), P.O. Box 992, CH–6371
Stans, Switzerland; phone: +41 (0)41
619 67 74; fax: +41 (0)41 619 67 73;
email: techsupport@pilatusaircraft.com; internet: https://
www.pilatus-aircraft.com. You may
review this referenced service
information at the FAA, Policy and
Innovation Division, 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–2018–
1058; or in person at Docket Operations
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
Docket Operations (telephone (800)
647–5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Standards Branch,
901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4059; fax: (816) 329–4090; email:
doug.rudolph@faa.gov.
SUPPLEMENTARY INFORMATION:
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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–2018–1058; Product Identifier
2018–CE–051–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 European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued AD No. 2018–
0217, dated October 10, 2018 (referred
to after this as ‘‘the MCAI’’), to correct
an unsafe condition for the specified
products. The MCAI states:
During a routine inspection, the rivets of
the hinge bracket assemblies on a Pilatus PC–
6 were found to be sheared or missing.
Investigation results identified that this was
most likely due to application of too much
force to the ends of the horizontal stabilizer
during ground handling.
This condition, if not detected and
corrected, could lead to failure of the primary
horizontal stabilizer load path and
consequent separation of the horizontal
stabilizer, possibly resulting in loss of control
of the aeroplane.
To address this potential unsafe condition,
Pilatus Aircraft Ltd issued the SB [service
bulletin] to provide applicable inspection
instructions.
For the reasons described above, this
[EASA] AD requires a one-time inspection of
the affected parts and the horizontal
stabilizer front spar attachment area and,
depending on findings, accomplishment of
applicable corrective action(s). This [EASA]
AD also requires, before installation,
inspection of, and, depending on findings,
corrective action(s) on, affected parts held as
spare.
The amount of force to the ends of the
horizontal stabilizer cannot be
quantified; however, fleet experience
shows that repetitive pushing or pulling
on the horizontal stabilizer to move the
airplane on the ground can overload the
rivets. Although a root cause could not
be determined, due to the severity of
separation of a horizontal stabilizer,
EASA determined that the corrective
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Fmt 4702
Sfmt 4702
actions should be required for other
airplanes of the same type design.
Pilatus Aircraft Ltd. had previously
considered the small size of the original
‘‘DO NOT PUSH’’ markings and the
significant chance of the markings being
over-sprayed during a respray. As a
result, Pilatus Aircraft Ltd. issued a
service bulletin to specify replacing the
smaller markings with new, larger
placards. The FAA proposes to require
these placards in the NPRM.
You may examine the MCAI on the
internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2018–1058.
Related Service Information Under 1
CFR Part 51
Pilatus Aircraft Ltd. has issued PC–6
Service Bulletin No. 55–004, dated July
2, 2018. The service information
contains procedures for inspecting the
left-hand and right-hand horizontal
stabilizer hinge bracket assemblies and,
if any discrepancies are found, repairing
or replacing any damaged rivets and
screws. Pilatus Aircraft Ltd. has also
issued PC–6 Service Bulletin No. 55–
002, Revision. No. 1, dated February 18,
2016. This service information contains
procedures for inspecting and repairing
the horizontal stabilizer attachment
hardware and installing four ‘‘DO NOT
PUSH’’ placards. This 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.
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.
We have reviewed the MCAI and, in
general, agree with the substance. The
MCAI AD does not require installing
‘‘DO NOT PUSH’’ placards. We have
added that requirement to this proposed
AD.
Costs of Compliance
We estimate that this proposed AD
would affect 30 products of U.S.
registry. We also estimate that it would
take about 9 work-hours per product to
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Federal Register / Vol. 83, No. 246 / Wednesday, December 26, 2018 / Proposed Rules
comply with the inspection and placard
requirements of this proposed AD. The
average labor rate is $85 per work-hour.
Required parts would cost about $200
per product.
Based on these figures, we estimate
the cost of the proposed inspection and
placard requirements on U.S. operators
to be $28,950, or $965 per product.
In addition, we estimate the following
to do any necessary follow-on actions:
Each rivet replacement would take 2
work-hours, fastener replacement would
take 3 work-hours, one hinge bracket
assembly replacement would take 9
work-hours, and two hinge bracket
assembly replacements would take 15
work-hours. The total estimated cost of
parts would be $10,000. We have no
way of determining the number of
products that may need replacement.
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.
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.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to small airplanes, gliders,
balloons, airships, domestic business jet
transport airplanes, and associated
appliances to the Director of the Policy
and Innovation Division.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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
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17:37 Dec 21, 2018
Jkt 247001
List of Subjects in 14 CFR Part 39
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 airworthiness
directive (AD):
■
Pilatus Aircraft Ltd.: Docket No. FAA–2018–
1058; Product Identifier 2018–CE–051–
AD.
(a) Comments Due Date
We must receive comments by February
11, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Pilatus Aircraft Ltd.
Model PC–6, PC–6/350, PC–6/350–H1, PC–6/
350–H2, PC–6/A, PC–6/A–H1, PC–6/A–H2,
PC–6/B–H2, PC–6/B1–H2, PC–6/B2–H2, PC–
6/B2–H4, PC–6/C–H2, PC–6/C1–H2, PC–6–
H1, PC–6–H2 airplanes, all serial numbers,
certificated in any category.
Note 1 to paragraph (c): These airplanes
may also be identified as Fairchild Republic
Company airplanes, Fairchild Industries
airplanes, Fairchild Heli Porter airplanes, or
Fairchild-Hiller Corporation airplanes.
(d) Subject
Air Transport Association of America
(ATA) Code 55: Stabilizers.
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66177
(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 sheared or
missing rivets on the horizontal stabilizer
hinge bracket assemblies. We are issuing this
AD to prevent failure of the primary
horizontal stabilizer load path, which could
lead to separation of the horizontal stabilizer
and result in loss of control of the airplane.
(f) Actions and Compliance
Unless already done, do the following
actions in paragraphs (f)(1) and (2).
(1) Within the next 100 hours time-inservice after the effective date of this AD or
within the next 12 months after the effective
date of this AD, whichever occurs first:
(i) Inspect the left-hand and the right-hand
horizontal stabilizer hinge bracket assemblies
for cracks, loose screws and rivets, sheared
rivets, missing rivets, and looseness of the
electrical bonding strap, and inspect the top
and bottom screws at each hinge bracket.
Repair or replace any parts with
discrepancies before further flight. You must
do the actions required by this paragraph by
following sections C through G of the
Accomplishment Instructions—Part 1—On
Aircraft in Pilatus Aircraft Ltd. PC–6 Service
Bulletin No. 55–004, dated July 2, 2018.
(ii) Install four ‘‘DO NOT PUSH’’ placards,
part number 110.71.06.847 or 110.71.06.848,
on the horizontal stabilizer by following
section G of the Accomplishment
Instructions—Aircraft in Pilatus Aircraft Ltd.
PC–6 Service Bulletin No. 55–002, Revision.
No. 1, dated February 18, 2016.
(2) After the effective date of this AD, do
not install a horizontal stabilizer on any
airplane unless it has been inspected as
specified in paragraph (f)(1)(i) of this AD and
found to be free of discrepancies or all
discrepancies have been repaired or replaced.
(g) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Small Airplane
Standards Branch, 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: Doug Rudolph,
Aerospace Engineer, FAA, Small Airplane
Standards Branch, 901 Locust, Room 301,
Kansas City, Missouri 64106; telephone:
(816) 329–4059; fax: (816) 329–4090; email:
doug.rudolph@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.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
instead be accomplished using a method
approved by the Manager, Small Airplane
Standards Branch, FAA, or the European
Aviation Safety Agency (EASA).
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(h) Related Information
Refer to MCAI European Aviation Safety
Agency AD No. 2018–0217, dated October
10, 2018, for related information. You may
examine the MCAI on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2018–1058. For
service information related to this AD,
contact PILATUS Aircraft Ltd., Customer
Technical Support (MCC), P.O. Box 992, CH–
6371 Stans, Switzerland; phone: +41 (0)41
619 67 74; fax: +41 (0)41 619 67 73; email:
techsupport@pilatus-aircraft.com; internet:
https://www.pilatus-aircraft.com. You may
review this referenced service information at
the FAA, Policy and Innovation Division, 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
December 17, 2018.
Melvin J. Johnson,
Aircraft Certification Service, Deputy
Director, Policy and Innovation Division,
AIR–601.
[FR Doc. 2018–27899 Filed 12–21–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–1012; Product
Identifier 2018–NM–132–AD]
RIN 2120–AA64
Examining the AD Docket
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all The
Boeing Company Model 777 airplanes.
This proposed AD was prompted by
reports of uncommanded movements of
the Captain’s and First Officer’s seats.
This proposed AD would require an
identification of the part number, and if
applicable the serial number, of the
Captain’s and First Officer’s seats, and
do applicable on-condition actions for
affected seats. This proposed AD would
also require a one-time detailed
inspection and repetitive checks of the
horizontal movement system of the
Captain’s and First Officer’s seats and
applicable on-condition actions. This
proposed AD would also provide an
optional terminating action for the
repetitive checks of the horizontal
movement system. We are proposing
this AD to address the unsafe condition
on these products.
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SUMMARY:
VerDate Sep<11>2014
17:37 Dec 21, 2018
We must receive comments on
this proposed AD by February 11, 2019.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster
Blvd., MC 110–SK57, Seal Beach, CA
90740–5600; telephone 562–797–1717;
internet https://
www.myboeingfleet.com. You may view
this service information at the FAA,
Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2018–
1012.
DATES:
Jkt 247001
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
1012; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this NPRM, the
regulatory evaluation, any comments
received, and other information. The
street address for Docket Operations
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Brandon Lucero, Aerospace Engineer,
Cabin Safety and Environmental
Systems Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–
231–3569; email: Brandon.Lucero@
faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
PO 00000
Frm 00016
Fmt 4702
Sfmt 4702
section. Include ‘‘Docket No. FAA–
2018–1012; Product Identifier 2018–
NM–132–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this NPRM. We will consider
all comments received by the closing
date and may amend this NPRM
because of those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We have received reports indicating
that there have been uncommanded
movements of the Captain’s and First
Officer’s seats. A Model 747 operator
reported that during a takeoff, the First
Officer’s seat unlocked from its seat
tracks and moved aft. The First Officer
was unable to control the airplane and
the Captain took over the controls to
avoid a rejected takeoff. The unlocking
of the seat from the seat tracks was
caused by actuator damage, which was
a result of incorrect adjustment of the
seat’s manual release lever cable, which
allowed the clutch mechanism to only
partially engage. Captain’s and First
Officer’s seats having the same part
numbers are installed on both Model
747 and Model 777 airplanes. We are
considering additional rulemaking to
address the unsafe condition for Model
747 airplanes.
In addition, a Model 777 operator
reported that the Captain’s seat could
not be locked in position after an
adjustment to the horizontal seat
position in flight. The seat became
unlocked from the track and moved
freely forward and aft. Control was
given to the First Officer for approach
and landing. The results of an
inspection revealed that the horizontal
actuator output shaft had broken. When
a horizontal actuator output shaft
breaks, the pilot cannot prevent seat
movement in a forward and aft direction
and cannot lock the seat in position. A
broken horizontal actuator output shaft
is the result of high loads, that exceed
the design limits, caused by a stalled
motor that can occur due to high
mechanical resistance to motion during
powered operation of the seat. Foreign
object debris (FOD) in the seat tracks is
another condition that can result in a
stalled motor and cause the horizontal
actuator output shaft to break.
An uncommanded seat movement
during a critical part of a flight, such as
takeoff or landing, could cause a flight
E:\FR\FM\26DEP1.SGM
26DEP1
Agencies
[Federal Register Volume 83, Number 246 (Wednesday, December 26, 2018)]
[Proposed Rules]
[Pages 66175-66178]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-27899]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-1058; Product Identifier 2018-CE-051-AD]
RIN 2120-AA64
Airworthiness Directives; Pilatus Aircraft 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
Pilatus Aircraft Ltd. Model PC-6, PC-6/350, PC-6/350-H1, PC-6/350-H2,
PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/
B2-H4, PC-6/C-H2, PC-6/C1-H2, PC-6-H1, and PC-6-H2 airplanes. This
proposed AD results from mandatory continuing airworthiness information
(MCAI) originated by an aviation authority of another country to
identify
[[Page 66176]]
and correct an unsafe condition on an aviation product. The MCAI
describes the unsafe condition as sheared or missing rivets on the
horizontal stabilizer hinge bracket assemblies. 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 February 11,
2019.
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
PILATUS Aircraft Ltd., Customer Technical Support (MCC), P.O. Box 992,
CH-6371 Stans, Switzerland; phone: +41 (0)41 619 67 74; fax: +41 (0)41
619 67 73; email: aircraft.com">techsupport@pilatus-aircraft.com; internet: https://
www.pilatus-aircraft.com. You may review this referenced service
information at the FAA, Policy and Innovation Division, 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-2018-
1058; or in person at Docket Operations 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 Docket Operations (telephone
(800) 647-5527) is in the ADDRESSES section. Comments will be available
in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA,
Small Airplane Standards Branch, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-4090; email:
doug.rudolph@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-2018-1058;
Product Identifier 2018-CE-051-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 European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued AD
No. 2018-0217, dated October 10, 2018 (referred to after this as ``the
MCAI''), to correct an unsafe condition for the specified products. The
MCAI states:
During a routine inspection, the rivets of the hinge bracket
assemblies on a Pilatus PC-6 were found to be sheared or missing.
Investigation results identified that this was most likely due to
application of too much force to the ends of the horizontal
stabilizer during ground handling.
This condition, if not detected and corrected, could lead to
failure of the primary horizontal stabilizer load path and
consequent separation of the horizontal stabilizer, possibly
resulting in loss of control of the aeroplane.
To address this potential unsafe condition, Pilatus Aircraft Ltd
issued the SB [service bulletin] to provide applicable inspection
instructions.
For the reasons described above, this [EASA] AD requires a one-
time inspection of the affected parts and the horizontal stabilizer
front spar attachment area and, depending on findings,
accomplishment of applicable corrective action(s). This [EASA] AD
also requires, before installation, inspection of, and, depending on
findings, corrective action(s) on, affected parts held as spare.
The amount of force to the ends of the horizontal stabilizer cannot
be quantified; however, fleet experience shows that repetitive pushing
or pulling on the horizontal stabilizer to move the airplane on the
ground can overload the rivets. Although a root cause could not be
determined, due to the severity of separation of a horizontal
stabilizer, EASA determined that the corrective actions should be
required for other airplanes of the same type design.
Pilatus Aircraft Ltd. had previously considered the small size of
the original ``DO NOT PUSH'' markings and the significant chance of the
markings being over-sprayed during a respray. As a result, Pilatus
Aircraft Ltd. issued a service bulletin to specify replacing the
smaller markings with new, larger placards. The FAA proposes to require
these placards in the NPRM.
You may examine the MCAI on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
1058.
Related Service Information Under 1 CFR Part 51
Pilatus Aircraft Ltd. has issued PC-6 Service Bulletin No. 55-004,
dated July 2, 2018. The service information contains procedures for
inspecting the left-hand and right-hand horizontal stabilizer hinge
bracket assemblies and, if any discrepancies are found, repairing or
replacing any damaged rivets and screws. Pilatus Aircraft Ltd. has also
issued PC-6 Service Bulletin No. 55-002, Revision. No. 1, dated
February 18, 2016. This service information contains procedures for
inspecting and repairing the horizontal stabilizer attachment hardware
and installing four ``DO NOT PUSH'' placards. This 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.
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.
We have reviewed the MCAI and, in general, agree with the
substance. The MCAI AD does not require installing ``DO NOT PUSH''
placards. We have added that requirement to this proposed AD.
Costs of Compliance
We estimate that this proposed AD would affect 30 products of U.S.
registry. We also estimate that it would take about 9 work-hours per
product to
[[Page 66177]]
comply with the inspection and placard requirements of this proposed
AD. The average labor rate is $85 per work-hour. Required parts would
cost about $200 per product.
Based on these figures, we estimate the cost of the proposed
inspection and placard requirements on U.S. operators to be $28,950, or
$965 per product.
In addition, we estimate the following to do any necessary follow-
on actions: Each rivet replacement would take 2 work-hours, fastener
replacement would take 3 work-hours, one hinge bracket assembly
replacement would take 9 work-hours, and two hinge bracket assembly
replacements would take 15 work-hours. The total estimated cost of
parts would be $10,000. We have no way of determining the number of
products that may need replacement.
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.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to small airplanes, gliders,
balloons, airships, domestic business jet transport airplanes, and
associated appliances to the Director of the Policy and Innovation
Division.
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 airworthiness
directive (AD):
Pilatus Aircraft Ltd.: Docket No. FAA-2018-1058; Product Identifier
2018-CE-051-AD.
(a) Comments Due Date
We must receive comments by February 11, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Pilatus Aircraft Ltd. Model PC-6, PC-6/350,
PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2,
PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, PC-6/C1-H2, PC-6-H1,
PC-6-H2 airplanes, all serial numbers, certificated in any category.
Note 1 to paragraph (c): These airplanes may also be identified
as Fairchild Republic Company airplanes, Fairchild Industries
airplanes, Fairchild Heli Porter airplanes, or Fairchild-Hiller
Corporation airplanes.
(d) Subject
Air Transport Association of America (ATA) Code 55: Stabilizers.
(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 sheared or
missing rivets on the horizontal stabilizer hinge bracket
assemblies. We are issuing this AD to prevent failure of the primary
horizontal stabilizer load path, which could lead to separation of
the horizontal stabilizer and result in loss of control of the
airplane.
(f) Actions and Compliance
Unless already done, do the following actions in paragraphs
(f)(1) and (2).
(1) Within the next 100 hours time-in-service after the
effective date of this AD or within the next 12 months after the
effective date of this AD, whichever occurs first:
(i) Inspect the left-hand and the right-hand horizontal
stabilizer hinge bracket assemblies for cracks, loose screws and
rivets, sheared rivets, missing rivets, and looseness of the
electrical bonding strap, and inspect the top and bottom screws at
each hinge bracket. Repair or replace any parts with discrepancies
before further flight. You must do the actions required by this
paragraph by following sections C through G of the Accomplishment
Instructions--Part 1--On Aircraft in Pilatus Aircraft Ltd. PC-6
Service Bulletin No. 55-004, dated July 2, 2018.
(ii) Install four ``DO NOT PUSH'' placards, part number
110.71.06.847 or 110.71.06.848, on the horizontal stabilizer by
following section G of the Accomplishment Instructions--Aircraft in
Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 55-002, Revision.
No. 1, dated February 18, 2016.
(2) After the effective date of this AD, do not install a
horizontal stabilizer on any airplane unless it has been inspected
as specified in paragraph (f)(1)(i) of this AD and found to be free
of discrepancies or all discrepancies have been repaired or
replaced.
(g) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Small Airplane Standards Branch, 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: Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas
City, Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-
4090; email: doug.rudolph@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.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must
instead be accomplished using a method approved by the Manager,
Small Airplane Standards Branch, FAA, or the European Aviation
Safety Agency (EASA).
[[Page 66178]]
(h) Related Information
Refer to MCAI European Aviation Safety Agency AD No. 2018-0217,
dated October 10, 2018, for related information. You may examine the
MCAI on the internet at https://www.regulations.gov by searching for
and locating Docket No. FAA-2018-1058. For service information
related to this AD, contact PILATUS Aircraft Ltd., Customer
Technical Support (MCC), P.O. Box 992, CH-6371 Stans, Switzerland;
phone: +41 (0)41 619 67 74; fax: +41 (0)41 619 67 73; email:
aircraft.com">techsupport@pilatus-aircraft.com; internet: https://www.pilatus-
aircraft.com. You may review this referenced service information at
the FAA, Policy and Innovation Division, 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 December 17, 2018.
Melvin J. Johnson,
Aircraft Certification Service, Deputy Director, Policy and Innovation
Division, AIR-601.
[FR Doc. 2018-27899 Filed 12-21-18; 8:45 am]
BILLING CODE 4910-13-P