Airworthiness Directives; Airbus SAS Airplanes, 10772-10775 [2021-03568]
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10772
Federal Register / Vol. 86, No. 34 / Tuesday, February 23, 2021 / Rules and Regulations
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Will not affect intrastate aviation
in Alaska, and
(3) 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 Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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:
■
2021–04–07 Piper Aircraft, Inc.:
Amendment 39–21428; Docket No.
FAA–2020–0830; Project Identifier
2020–CE–002–AD.
(a) Effective Date
This airworthiness directive (AD) is
effective March 30, 2021.
(b) Affected ADs
None.
(c) Applicability
(c) This AD applies to the following Piper
Aircraft, Inc., airplanes, certificated in any
category:
(1) Model PA–46–350P (Malibu Mirage)
airplanes, serial numbers (S/Ns) 4622041,
4636041, 4636142, 4636143, 4636313,
4636341, and 4636379;
(2) Model PA–46–500TP (Malibu Meridian)
airplanes, S/Ns 4697141, 4697161, 4697086,
and 4697020; and
(3) Models PA–46–350P (Malibu Mirage),
PA–46R–350T (Malibu Matrix), and PA–46–
500TP (Malibu Meridian) airplanes, all serial
numbers, if the left wing has been replaced
with a serviceable (more than zero hours
time-in-service) wing.
(d) Subject
Joint Aircraft System Component (JASC)
3700, VACUUM SYSTEM.
(e) Unsafe Condition
This AD was prompted by nonconforming
stall warning heat control systems, utilizing
a left wing assembly without the proper stall
warning modification design. Without the
proper stall warning heat control
modification kit during flights into icing
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conditions with the landing gear down, ice
can form on the stall vane, which may result
in failure of the stall warning system. The
FAA is issuing this AD to identify and
correct nonconforming stall warning heat
control systems. The unsafe condition, if not
addressed, could result in the pilot being
unaware of an approaching stall situation.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Actions
(1) Within 100 hours time-in-service (TIS)
after the effective date of this AD or within
12 months after the effective date of this AD,
whichever occurs first, inspect the
configuration of stall warning heat control
system and, if required, install stall warning
heat control modification kit part number
(P/N) 8452–002 before further flight in
accordance with steps 2 and 3 of the
Instructions in Piper Aircraft, Inc., Service
Letter No. 1261, dated July 19, 2019.
(2) As of the effective date of this AD, do
not install a wing on any Model PA–46–350P
(Malibu Mirage), PA–46R–350T (Malibu
Matrix), or PA–46–500TP (Malibu Meridian)
airplane unless you have determined that the
wing has the correct stall warning heat
control system as required by paragraph
(g)(1) of this AD.
(h) Special Flight Permit
A special flight permit may be issued to
operate the airplane to a location where the
requirements of this AD can be accomplished
provided flight into known icing conditions
is prohibited.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Atlanta 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 (j)(1) of
this AD.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) 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 a Piper Aircraft, Inc.
Organization Designation Authorization
(ODA) that has been authorized by the
Manager, Atlanta ACO Branch 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.
(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. An AMOC is required
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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.
(j) Related Information
For more information about this AD,
contact John Lee, Aviation Safety Engineer,
Atlanta ACO Branch, FAA, 1701 Columbia
Avenue, College Park, GA 30337; phone:
(404) 474–5568; email: john.lee@faa.gov.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Piper Service Letter No. 1261, dated July
19, 2019.
(ii) [Reserved]
(3) For Piper Aircraft, Inc. service
information identified in this AD, contact
Piper Aircraft Inc., 2926 Piper Drive, Vero
Beach, FL 32960; phone: 772–299–2686;
email: customerservice@piper.com; website:
https://www.piper.com/.
(4) You may view this service information
at FAA, Airworthiness Products Section,
Operational Safety Branch, 901 Locust,
Kansas City, Missouri 64106. For information
on the availability of this material at the
FAA, call 816–329–4148.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
email: fedreg.legal@nara.gov, or go to:
https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
Issued on February 4, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–03499 Filed 2–22–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0969; Project
Identifier MCAI–2020–00853–T; Amendment
39–21393; AD 2021–02–10]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
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Federal Register / Vol. 86, No. 34 / Tuesday, February 23, 2021 / Rules and Regulations
ACTION:
Final rule.
The FAA is adopting a new
airworthiness directive (AD) for all
Airbus SAS Model A350–941 and –1041
airplanes. This AD was prompted by a
report that certain retaining rings could
cause damage to frame forks, brackets
and edge frames, and their surface
protection; subsequent investigation
showed that the depth of the frame fork
spotfacing on structural parts is
inadequate to accommodate the
retaining ring. This AD requires
repetitive inspections of certain areas of
each cargo door for damage and
corrective action. This AD also provides
an optional terminating modification, as
specified in a European Union Aviation
Safety Agency (EASA) AD, which is
incorporated by reference. The FAA is
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective March 30,
2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 30, 2021.
ADDRESSES: For material incorporated
by reference (IBR) in this AD, contact
the EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49
221 8999 000; email ADs@
easa.europa.eu; internet
www.easa.europa.eu. You may find this
IBR material on the EASA website at
https://ad.easa.europa.eu. You may
view this IBR material at the FAA,
Airworthiness Products Section,
Operational Safety 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 in the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
0969.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
10773
The FAA is issuing this AD to address
inadequate frame fork spotfacing depth
for the retaining rings, which could
reduce the structural integrity of the
airplane. See the MCAI for additional
background information.
and locating Docket No. FAA–2020–
0969; 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 final rule,
any comments received, and other
information. The address for Docket
Operations is U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Kathleen Arrigotti, Aerospace Engineer,
Large Aircraft Section, International
Validation Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3218; email
kathleen.arrigotti@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments
The FAA gave the public the
opportunity to participate in developing
this final rule. The FAA received no
comments on the NPRM or on the
determination of the cost to the public.
Conclusion
The FAA reviewed the relevant data
and determined that air safety and the
public interest require adopting this
final rule as proposed, except for minor
editorial changes. The FAA has
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Discussion
The EASA, which is the Technical
Agent for the Member States of the
European Union, has issued EASA AD
2020–0144, dated June 29, 2020 (EASA
AD 2020–0144) (also referred to as the
Mandatory Continuing Airworthiness
Information, or the MCAI), to correct an
unsafe condition for all Airbus SAS
Model A350–941 and –1041 airplanes.
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Airbus SAS Model A350–
941 and –1041 airplanes. The NPRM
published in the Federal Register on
October 26, 2020 (85 FR 67696). The
NPRM was prompted by a report that
certain retaining rings could cause
damage to frame forks, brackets and
edge frames, and their surface
protection; subsequent investigation
showed that the depth of the frame fork
spotfacing on structural parts is
inadequate to accommodate the
retaining ring. The NPRM proposed to
require repetitive inspections of certain
areas of each cargo door for damage and
corrective action. The NPRM also
proposed to provide an optional
terminating modification, as specified in
an EASA AD.
Related Service Information Under 1
CFR Part 51
EASA AD 2020–0144 describes
procedures for repetitive inspections of
the edge frames, brackets, frame forks,
and the access cover on the internal side
of each cargo door for damage
(including cracks and corrosion) and
corrective actions. Corrective actions
include repair or rework. EASA AD
2020–0144 also describes procedures for
an optional modification of each
affected cargo door, which terminates
the repetitive inspections. This material
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.
Costs of Compliance
The FAA estimates that this AD
affects 13 airplanes of U.S. registry. The
FAA estimates the following costs to
comply with this AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Labor cost
Parts cost
Cost per
product
Cost on U.S.
operators
24 work-hours × $85 per hour = $2,040 .....................................................................................
$0
$2,040
$26,520
ESTIMATED COSTS FOR OPTIONAL ACTIONS
Labor cost
Parts cost
9 work-hours × $85 per hour = $765 ................................................................................................................
Up to $8,570 .....
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21:28 Feb 22, 2021
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Cost per product
Up to $9,335.
10774
Federal Register / Vol. 86, No. 34 / Tuesday, February 23, 2021 / Rules and Regulations
The FAA has received no definitive
data on which to base the cost estimates
for the on-condition actions specified in
this AD.
According to the manufacturer, some
or all of the costs of this AD may be
covered under warranty, thereby
reducing the cost impact on affected
operators. The FAA does not control
warranty coverage for affected operators.
As a result, the FAA has included all
known costs in the cost estimate.
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.
The FAA is 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
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Will not affect intrastate aviation
in Alaska, and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
VerDate Sep<11>2014
21:28 Feb 22, 2021
Jkt 253001
the FAA amends 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:
■
2021–02–10 Airbus SAS: Amendment 39–
21393; Docket No. FAA–2020–0969;
Project Identifier MCAI–2020–00853–T.
(a) Effective Date
This airworthiness directive (AD) is
effective March 30, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus SAS Model
A350–941 and –1041 airplanes, certificated
in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 52, Doors.
(e) Reason
This AD was prompted by a report that
certain retaining rings could cause damage to
frame forks, brackets and edge frames, and
their surface protection; subsequent
investigation showed that the depth of the
frame fork spotfacing on structural parts is
inadequate to accommodate the retaining
ring. The FAA is issuing this AD to address
inadequate frame fork spotfacing depth for
the retaining rings, which could reduce the
structural integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, European Union Aviation
Safety Agency (EASA) AD 2020–0144, dated
June 29, 2020 (EASA AD 2020–0144).
(h) Exceptions to EASA AD 2020–0144
(1) Where EASA AD 2020–0144 refers to its
effective date, this AD requires using the
effective date of this AD.
(2) The ‘‘Remarks’’ section of EASA AD
2020–0144 does not apply to this AD.
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Large Aircraft
Section, International Validation Branch,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
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Fmt 4700
Sfmt 4700
found in 14 CFR 39.19. In accordance with
14 CFR 39.19, send your request to your
principal inspector or responsible Flight
Standards Office, as appropriate. If sending
information directly to the Large Aircraft
Section, International Validation Branch,
send it to the attention of the person
identified in paragraph (j) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the responsible
Flight Standards Office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, Large Aircraft Section,
International Validation Branch, FAA; or
EASA; or Airbus SAS’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(3) Required for Compliance (RC): Except
as required by paragraph (i)(2) of this AD, if
any service information contains procedures
or tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
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 procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(j) Related Information
For more information about this AD,
contact Kathleen Arrigotti, Aerospace
Engineer, Large Aircraft Section,
International Validation Branch, FAA, 2200
South 216th St., Des Moines, WA 98198;
telephone and fax 206–231–3218; email
kathleen.arrigotti@faa.gov.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) European Union Aviation Safety Agency
(EASA) AD 2020–0144, dated June 29, 2020.
(ii) [Reserved]
(3) For EASA AD 2020–0144, contact the
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221 8999
000; email ADs@easa.europa.eu; Internet
www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://
ad.easa.europa.eu.
(4) You may view this material at the FAA,
Airworthiness Products Section, Operational
Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195. This material may be found
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Federal Register / Vol. 86, No. 34 / Tuesday, February 23, 2021 / Rules and Regulations
in the AD docket on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2020–0969.
(5) You may view this material that is
incorporated by reference at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, email fedreg.legal@
nara.gov, or go to: https://www.archives.gov/
federal-register/cfr/ibr-locations.html.
Issued on January 12, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–03568 Filed 2–22–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0818; Project
Identifier MCAI–2020–00987–A; Amendment
39–21381; AD 2021–01–05]
RIN 2120–AA64
Airworthiness Directives; Pilatus
Aircraft Ltd. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Pilatus Aircraft Ltd. (Pilatus) Model PC–
24 airplanes. This 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
identifies the unsafe condition as
electrical harness installations on PC–24
airplanes that are not in compliance
with the approved design. This unsafe
condition could lead to wire chafing
and potential arcing or failure of wires
having the incorrect length, possibly
resulting in loss of system redundancy,
or generation of smoke and smell, or
loss of power plant fire protection
function. This AD requires modifying
the electrical harness installation. The
FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective March 30,
2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 30, 2021.
ADDRESSES: For service information
identified in this final rule, contact
Pilatus Aircraft Ltd., CH–6371, Stans,
Switzerland; phone: +41 848 24 7 365;
email: techsupport.ch@pilatusSUMMARY:
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21:28 Feb 22, 2021
Jkt 253001
aircraft.com; website: https://
www.pilatus-aircraft.com/. You may
view this service information at the
FAA, Airworthiness Products Section,
Operational Safety Branch, 901 Locust,
Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call 816–329–4148.
It is also available at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
0818.
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2020–0818; 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
final rule, the MCAI, any comments
received, and other information. The
address for Docket Operations is U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE, Washington, DC
20590.
FOR FURTHER INFORMATION CONTACT:
Doug Rudolph, Aviation Safety
Engineer, FAA, General Aviation &
Rotorcraft Section, International
Validation Branch, 901 Locust, Room
301, Kansas City, Missouri 64106;
phone: (816) 329–4059; fax: (816) 329–
4090; email: doug.rudolph@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain serial-numbered Pilatus
Model PC–24 airplanes. The NPRM
published in the Federal Register on
September 17, 2020 (85 FR 58002). The
NPRM was prompted by MCAI
originated by the European Union
Aviation Safety Agency (EASA), which
is the Technical Agent for the Member
States of the European Union. EASA has
issued EASA AD No. 2020–0158, dated
July 16, 2020 (referred to after this as
‘‘the MCAI’’), to address the unsafe
condition on these products. The MCAI
states:
During production, electrical harness
installations on some PC–24 aeroplanes were
found not to comply with the approved
design.
This condition, if not corrected, could lead
to wire chafing and potential arcing, or to
failure of wires having the incorrect length,
possibly resulting in loss of system
redundancy, or generation of smoke and
smell, or loss of power plant fire protection
function.
To address this potential unsafe condition,
Pilatus issued the [service bulletin] SB,
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10775
providing instructions to improve the
electrical harness installations in the nose
bay, cockpit, fuselage, wing fairing and rear
fuselage areas.
For the reason described above, this
[EASA] AD requires modification of the
electrical harness installations.
The incorrect length wires are too
short in length and do not have
appropriate slack, which could lead to
wires being pulled loose from the
terminals during flight or ground
operation. Generation of smell refers to
the smell from electrical arcing. You
may examine the MCAI in the AD
docket at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2020–0818.
In the NPRM, the FAA proposed to
require modifying the electrical harness
installation. The FAA is issuing this AD
to address the unsafe condition on these
products.
Discussion of Final Airworthiness
Directive
Comments
The FAA received no comments on
the NPRM or on the determination of
the costs.
Conclusion
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, it has notified the
FAA of the unsafe condition described
in the MCAI and service information
referenced above. The FAA reviewed
the relevant data and determined that
air safety and the public interest require
adopting this AD as proposed.
Accordingly, the FAA is issuing this AD
to address the unsafe condition on these
products. This AD is adopted as
proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Pilatus PC–24
Service Bulletin No. 91–001, dated
April 7, 2020. The service information
specifies procedures necessary to
improve the electrical harness
installation in the nose bay, cockpit,
avionics rack, fuselage, wing fairing,
and rear fuselage. 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.
Costs of Compliance
The FAA estimates that this AD will
affect 36 products of U.S. registry. The
FAA also estimates that it will take 20
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23FER1
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[Federal Register Volume 86, Number 34 (Tuesday, February 23, 2021)]
[Rules and Regulations]
[Pages 10772-10775]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-03568]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0969; Project Identifier MCAI-2020-00853-T;
Amendment 39-21393; AD 2021-02-10]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
[[Page 10773]]
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by
a report that certain retaining rings could cause damage to frame
forks, brackets and edge frames, and their surface protection;
subsequent investigation showed that the depth of the frame fork
spotfacing on structural parts is inadequate to accommodate the
retaining ring. This AD requires repetitive inspections of certain
areas of each cargo door for damage and corrective action. This AD also
provides an optional terminating modification, as specified in a
European Union Aviation Safety Agency (EASA) AD, which is incorporated
by reference. The FAA is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective March 30, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of March 30,
2021.
ADDRESSES: For material incorporated by reference (IBR) in this AD,
contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany;
telephone +49 221 8999 000; email [email protected]; internet
www.easa.europa.eu. You may find this IBR material on the EASA website
at https://ad.easa.europa.eu. You may view this IBR material at the
FAA, Airworthiness Products Section, Operational Safety 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 in
the AD docket on the internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2020-0969.
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-2020-
0969; 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 final rule, any comments received, and other information. The
address for Docket Operations is U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Kathleen Arrigotti, Aerospace
Engineer, Large Aircraft Section, International Validation Branch, FAA,
2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-
3218; email [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
The EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2020-0144, dated June 29, 2020 (EASA
AD 2020-0144) (also referred to as the Mandatory Continuing
Airworthiness Information, or the MCAI), to correct an unsafe condition
for all Airbus SAS Model A350-941 and -1041 airplanes.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to all Airbus SAS Model
A350-941 and -1041 airplanes. The NPRM published in the Federal
Register on October 26, 2020 (85 FR 67696). The NPRM was prompted by a
report that certain retaining rings could cause damage to frame forks,
brackets and edge frames, and their surface protection; subsequent
investigation showed that the depth of the frame fork spotfacing on
structural parts is inadequate to accommodate the retaining ring. The
NPRM proposed to require repetitive inspections of certain areas of
each cargo door for damage and corrective action. The NPRM also
proposed to provide an optional terminating modification, as specified
in an EASA AD.
The FAA is issuing this AD to address inadequate frame fork
spotfacing depth for the retaining rings, which could reduce the
structural integrity of the airplane. See the MCAI for additional
background information.
Comments
The FAA gave the public the opportunity to participate in
developing this final rule. The FAA received no comments on the NPRM or
on the determination of the cost to the public.
Conclusion
The FAA reviewed the relevant data and determined that air safety
and the public interest require adopting this final rule as proposed,
except for minor editorial changes. The FAA has determined that these
minor changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
EASA AD 2020-0144 describes procedures for repetitive inspections
of the edge frames, brackets, frame forks, and the access cover on the
internal side of each cargo door for damage (including cracks and
corrosion) and corrective actions. Corrective actions include repair or
rework. EASA AD 2020-0144 also describes procedures for an optional
modification of each affected cargo door, which terminates the
repetitive inspections. This material 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.
Costs of Compliance
The FAA estimates that this AD affects 13 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
24 work-hours x $85 per hour = $2,040........................ $0 $2,040 $26,520
----------------------------------------------------------------------------------------------------------------
Estimated Costs for Optional Actions
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Labor cost Parts cost Cost per product
------------------------------------------------------------------------
9 work-hours x $85 per hour Up to $8,570........ Up to $9,335.
= $765.
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[[Page 10774]]
The FAA has received no definitive data on which to base the cost
estimates for the on-condition actions specified in this AD.
According to the manufacturer, some or all of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected operators. The FAA does not control warranty coverage for
affected operators. As a result, the FAA has included all known costs
in the cost estimate.
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.
The FAA is 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
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2021-02-10 Airbus SAS: Amendment 39-21393; Docket No. FAA-2020-0969;
Project Identifier MCAI-2020-00853-T.
(a) Effective Date
This airworthiness directive (AD) is effective March 30, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus SAS Model A350-941 and -1041
airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 52, Doors.
(e) Reason
This AD was prompted by a report that certain retaining rings
could cause damage to frame forks, brackets and edge frames, and
their surface protection; subsequent investigation showed that the
depth of the frame fork spotfacing on structural parts is inadequate
to accommodate the retaining ring. The FAA is issuing this AD to
address inadequate frame fork spotfacing depth for the retaining
rings, which could reduce the structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, European Union Aviation Safety Agency (EASA) AD
2020-0144, dated June 29, 2020 (EASA AD 2020-0144).
(h) Exceptions to EASA AD 2020-0144
(1) Where EASA AD 2020-0144 refers to its effective date, this
AD requires using the effective date of this AD.
(2) The ``Remarks'' section of EASA AD 2020-0144 does not apply
to this AD.
(i) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Large Aircraft Section, International Validation 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 responsible Flight
Standards Office, as appropriate. If sending information directly to
the Large Aircraft Section, International Validation Branch, send it
to the attention of the person identified in paragraph (j) of this
AD. Information may be emailed to: [email protected].
Before using any approved AMOC, notify your appropriate principal
inspector, or lacking a principal inspector, the manager of the
responsible Flight Standards Office.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain instructions from a manufacturer, the instructions must be
accomplished using a method approved by the Manager, Large Aircraft
Section, International Validation Branch, FAA; or EASA; or Airbus
SAS's EASA Design Organization Approval (DOA). If approved by the
DOA, the approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraph (i)(2) of this AD, if any service information contains
procedures or tests that are identified as RC, those procedures and
tests must be done to comply with this AD; any procedures or tests
that are not identified as RC are recommended. Those procedures and
tests that are not identified 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 procedures and tests identified as RC can be done and the
airplane can be put back in an airworthy condition. Any
substitutions or changes to procedures or tests identified as RC
require approval of an AMOC.
(j) Related Information
For more information about this AD, contact Kathleen Arrigotti,
Aerospace Engineer, Large Aircraft Section, International Validation
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
and fax 206-231-3218; email [email protected].
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) European Union Aviation Safety Agency (EASA) AD 2020-0144,
dated June 29, 2020.
(ii) [Reserved]
(3) For EASA AD 2020-0144, contact the EASA, Konrad-Adenauer-
Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email
[email protected]; Internet www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://ad.easa.europa.eu.
(4) You may view this material at the FAA, Airworthiness
Products Section, Operational Safety Branch, 2200 South 216th St.,
Des Moines, WA. For information on the availability of this material
at the FAA, call 206-231-3195. This material may be found
[[Page 10775]]
in the AD docket on the internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2020-0969.
(5) You may view this material that is incorporated by reference
at the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, email
[email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on January 12, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-03568 Filed 2-22-21; 8:45 am]
BILLING CODE 4910-13-P
