Airworthiness Directives; Airbus SAS Airplanes, 9429-9432 [2022-03633]
Download as PDF
<![CDATA[
Federal Register / Vol. 87, No. 35 / Tuesday, February 22, 2022 / Rules and Regulations
9429
ESTIMATED COSTS *
Action
Spoiler assembly replacement.
Parts cost
Cost per
spoiler assembly
$44,039 .............................
$49,989 .............................
Labor cost
70 work-hours × $85 per
hour = $5,950.
Cost on U.S.
operators
$399,912
* Each airplane contains two spoiler assemblies.
Authority: 49 U.S.C. 106(g), 40113, 44701.
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,
and
(2) Will not affect intrastate aviation
in Alaska.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
lotter on DSK11XQN23PROD with RULES1
Adoption of the Amendment
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
2022–05–01 Learjet, Inc.: Amendment 39–
21952; Docket No. FAA–2022–0144;
Project Identifier AD–2022–00042–T.
(a) Effective Date
This airworthiness directive (AD) is
effective March 9, 2022.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Learjet, Inc., Model 35,
35A (C–21A), 36, 36A, 55, 55B, 55C, and 60
airplanes, certificated in any category, with
any spoiler assembly that meets any of the
criteria identified in paragraph (c)(1) or (2) of
this AD.
(1) The spoiler assembly’s life limit was
extended by Restored Aircraft Sales and
Service, LLC.
(2) The maintenance records related to the
life limit for the spoiler assembly are missing
or incomplete.
(d) Subject
Air Transport Association (ATA) of
America Code 5755, Spoilers.
(e) Unsafe Condition
This AD was prompted by a report
indicating that a repair station performed a
life extension program on spoiler assemblies
that had reached or were close to reaching
their life limit. The FAA is issuing this AD
to prevent use of a spoiler assembly beyond
its FAA-approved life limit, which could
lead to undetected cracking and consequent
failure or separation of the spoiler assembly,
resulting in a reduction or complete loss of
control of the airplane.
Jkt 256001
Issued on February 16, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2022–03805 Filed 2–17–22; 11:15 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
(h) Parts Installation Prohibition
16:05 Feb 18, 2022
(l) Material Incorporated by Reference
None.
Comply with this AD within the
compliance times specified, unless already
done.
PART 39—AIRWORTHINESS
DIRECTIVES
VerDate Sep<11>2014
(k) Related Information
For more information about this AD,
contact Tara Shawn, Aerospace Engineer,
Airframe and Services Section, FAA, Wichita
ACO Branch, 1801 Airport Road, Room 100,
Wichita, KS 67209; phone: 316–946–4141;
email: Tara.Shawn@faa.gov.
Federal Aviation Administration
(g) Spoiler Assembly Removal
1. The authority citation for part 39
continues to read as follows:
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Wichita 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 responsible Flight
Standards 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 (k) of this
AD.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the responsible Flight Standards Office.
(f) Compliance
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
■
(i) Special Flight Permit
Special flight permits, as described in 14
CFR 21.197 and 21.199, may be issued to
operate the airplane to a location where the
requirements of this AD can be
accomplished, but concurrence by the
Manager, Wichita ACO Branch, FAA, is
required before issuance of the special flight
permit.
For each spoiler assembly identified in
paragraph (c) of this AD: Remove the spoiler
assembly from service before further flight.
As of the effective date of this AD, no
person may install, on any airplane, a spoiler
assembly identified in paragraph (c) of this
AD.
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
[Docket No. FAA–2021–1006; Project
Identifier MCAI–2021–00700–T; Amendment
39–21940; AD 2022–03–22]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
E:\FR\FM\22FER1.SGM
22FER1
9430
ACTION:
Federal Register / Vol. 87, No. 35 / Tuesday, February 22, 2022 / Rules and Regulations
Final rule.
The FAA is superseding
Airworthiness Directive (AD) 2019–26–
01, which applied to certain Airbus SAS
Model A350–941 and –1041 airplanes.
AD 2019–26–01 required repetitive
detailed inspections, and applicable
corrective actions, and provided an
optional modification that terminated
the inspections. Since the FAA issued
AD 2019–26–01, a determination was
made that a related production
modification was not properly installed
on certain airplanes. This AD retains the
requirements of AD 2019–26–01, and,
for certain airplanes, adds a one-time
detailed inspection of the modification
for proper installation, and applicable
corrective actions if necessary, 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 29,
2022.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 29, 2022.
ADDRESSES: For the material
incorporated by reference (IBR) in this
AD, contact the EASA, KonradAdenauer-Ufer 3, 50668 Cologne,
Germany; telephone +49 221 8999 000;
email ADs@easa.europa.eu; internet
www.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–2021–
1006.
lotter on DSK11XQN23PROD with RULES1
SUMMARY:
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–1006; 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 mandatory continuing
airworthiness information (MCAI), any
comments received, and other
information. The address for Docket
Operations is U.S. Department of
Transportation, Docket Operations, M–
VerDate Sep<11>2014
16:05 Feb 18, 2022
Jkt 256001
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3225; email
dan.rodina@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
EASA, which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2021–0141,
dated June 15, 2021 (EASA AD 2021–
0141) (also referred to as the MCAI), to
correct an unsafe condition for certain
Airbus SAS Model A350–941 and –1041
airplanes.
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2019–26–01,
Amendment 39–21023 (85 FR 4199,
January 24, 2020) (AD 2019–26–01). AD
2019–26–01 applied to certain Airbus
SAS Model A350–941 and –1041
airplanes. The NPRM published in the
Federal Register on November 18, 2021
(86 FR 64416). The NPRM was
prompted by reports of sealant bead
damage caused by rotation of the
attachment fitting bearing assembly of a
trimmable horizontal stabilizer (THS)
and a determination that a related
production modification was not
properly installed on certain airplanes.
The NPRM proposed to retain the
requirements of AD 2019–26–01, and,
for certain airplanes, proposed to add a
one-time detailed inspection of the
modification for proper installation, and
applicable corrective actions if
necessary, as specified in EASA AD
2021–0141.
The FAA is issuing this AD to address
possible water ingress due to sealant
bead damage, which could result in
corrosion damage in the aluminum
corner fitting. This condition, if not
addressed, could lead to detachment
and loss of the THS, possibly resulting
in loss of control of the airplane and
injury to persons on the ground. See the
MCAI for additional background
information.
Discussion of Final Airworthiness
Directive
Comments
The FAA received a comment from
the Air Line Pilots Association,
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
International (ALPA), who supported
the NPRM without change.
Conclusion
The FAA reviewed the relevant data,
considered the comment received, and
determined that air safety requires
adopting this AD as proposed. Except
for minor editorial changes, this AD is
adopted as proposed in the NPRM.
None of the changes will increase the
economic burden on any operator.
Accordingly, the FAA is issuing this AD
to address the unsafe condition on these
products.
Related Service Information Under 1
CFR Part 51
EASA AD 2021–0141 describes
procedures for repetitive detailed
inspections for damage of the fillet
sealant and corrosion on aluminum in
the lower and upper corner fittings and
bearing assembly attachment interface at
frame (FR) 102, left-hand and right-hand
sides, and an optional modification
(application of new corrosion protection
in the THS upper and lower attachment
fitting bearing assembly) that would
eliminate the need for the repetitive
inspections. EASA AD 2021–0141 also
describes procedures for a one-time
detailed inspection of the modification
of the lower and upper corner fittings
and bearing assembly attachment
interface at FR 102, left-hand and righthand sides (Airbus production
modification 113102) for discrepancies
(including missing sealant bead, cracks
in the sealant bead, and corrosion on the
affected bearing zone) and corrective
actions (including, but not limited to, a
check for grease, a check for cracks in
the sealant bead, applying sealant,
torqueing the bearing nut, inspecting for
corrosion on the affected bearing zone,
applying corrosion preventative
compound and actions to address
missing grease and corrosion). 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 15 airplanes of U.S. registry. The
FAA estimates the following costs to
comply with this AD:
E:\FR\FM\22FER1.SGM
22FER1
Federal Register / Vol. 87, No. 35 / Tuesday, February 22, 2022 / Rules and Regulations
9431
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Labor cost
Retained actions from AD 2019-26-01 ...........
New actions ....................................................
30 work-hours × $85 per hour = $2,550 ........
32 work-hours × $85 per hour = $2,720 ........
The FAA has received no definitive
data that enables the agency to provide
Cost per
product
Parts cost
$0
0
$2,550
2,720
Cost on U.S.
operators
$38,250
40,800
cost estimates for the corrective actions
(including repair) specified in this AD.
ESTIMATED COSTS OF OPTIONAL ACTIONS
Labor cost
Parts cost
Cost per
product
34 work-hours × $85 per hour = $2,890 .................................................................................................................
$0
$2,890
Authority for This Rulemaking
List of Subjects in 14 CFR Part 39
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.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
lotter on DSK11XQN23PROD with RULES1
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.
VerDate Sep<11>2014
16:05 Feb 18, 2022
Jkt 256001
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:
■ a. Removing Airworthiness Directive
(AD) 2019–26–01, Amendment 39–
21023 (85 FR 4199, January 24, 2020);
and
■ b. Adding the following new AD:
■
2022–03–22 Airbus SAS: Amendment 39–
21940; Docket No. FAA–2021–1006;
Project Identifier MCAI–2021–00700–T.
(a) Effective Date
This airworthiness directive (AD) is
effective March 29, 2022.
(b) Affected ADs
This AD replaces AD 2019–26–01,
Amendment 39–21023 (85 FR 4199, January
24, 2020) (AD 2019–26–01).
(c) Applicability
This AD applies to Airbus SAS Model
A350–941 and –1041 airplanes, certificated
in any category, as identified in European
Union Aviation Safety Agency (EASA) AD
2021–0141, dated June 15, 2021 (EASA AD
2021–0141).
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
(e) Reason
This AD was prompted by reports of
sealant bead damage caused by rotation of
the attachment fitting bearing assembly of a
trimmable horizontal stabilizer (THS) and a
determination that a related production
modification was not properly installed on
certain airplanes. The FAA is issuing this AD
to address possible water ingress due to
sealant bead damage, which could result in
corrosion damage in the aluminum corner
fitting. This condition, if not addressed,
could lead to detachment and loss of the
THS, possibly resulting in loss of control of
the airplane and injury to persons on the
ground.
(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, EASA AD 2021–0141.
(h) Exceptions to EASA AD 2021–0141
(1) Where EASA AD 2021–0141 refers to
February 21, 2018 (the effective date of EASA
AD 2018–0037), this AD requires using
February 28, 2020 (the effective date of FAA
AD 2019–26–01).
(2) Where EASA AD 2021–0141 refers to its
effective date, this AD requires using the
effective date of this AD.
(3) The ‘‘Remarks’’ section of EASA AD
2021–0141 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
E:\FR\FM\22FER1.SGM
22FER1
9432
Federal Register / Vol. 87, No. 35 / Tuesday, February 22, 2022 / Rules and Regulations
identified in paragraph (j) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov.
(i) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the responsible Flight Standards Office.
(ii) AMOCs approved previously for AD
2019–26–01 are approved as AMOCs for the
corresponding provisions of EASA AD 2021–
0141 that are required by paragraph (g) of this
AD.
(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): For any
service information referenced in EASA AD
2021–0141 that contains RC procedures and
tests: Except as required by paragraph (i)(2)
of this AD, RC 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.
lotter on DSK11XQN23PROD with RULES1
(j) Related Information
For more information about this AD,
contact Dan Rodina, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone and fax 206–
231–3225; email dan.rodina@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 2021–0141, dated June 15, 2021.
(ii) [Reserved]
(3) For EASA AD 2021–0141, contact
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.
(5) You may view this material that is
incorporated by reference at the National
VerDate Sep<11>2014
16:05 Feb 18, 2022
Jkt 256001
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, email
fr.inspection@nara.gov, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on January 28, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2022–03633 Filed 2–18–22; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2022–0101; Project
Identifier AD–2021–01456–E; Amendment
39–21949; AD 2022–04–07]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company Turbofan Engines
Examining the AD Docket
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
General Electric Company (GE) GEnx–
1B64, –1B64/P1, –1B64/P2, –1B67,
–1B67/P1, –1B67/P2, –1B70, –1B70/75/
P1, –1B70/75/P2, –1B70/P1, –1B70/P2,
–1B70C/P1, –1B70C/P2, –1B74/75/P1,
–1B74/75/P2, –1B76/P2, –1B76A/P2,
GEnx–2B67, –2B67B, and –2B67/P
model turbofan engines. This AD was
prompted by an in-flight shutdown
(IFSD) of an engine and subsequent
investigation by the manufacturer that
revealed an improperly torqued fuel
metering unit (FMU) bypass valve (BPV)
plug. This AD requires a shim check
inspection of the FMU BPV plug and,
depending on the results of the
inspection, replacement of the FMU.
The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective March 9,
2022.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of March 9, 2022.
The FAA must receive comments on
this AD by April 8, 2022.
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.
SUMMARY:
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
• 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 final rule, contact General Electric
Company, 1 Neumann Way, Cincinnati,
OH 45215; phone: (513) 552–3272;
email: aviation.fleetsupport@ae.ge.com;
website: https://www.ge.com. You may
view this service information at the
FAA, Airworthiness Products Section,
Operational Safety Branch, 1200 District
Avenue, Burlington, MA 01803. For
information on the availability of this
material at the FAA, call (817) 222–
5110. It is also available at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2022–
0101.
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2022–0101; 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 street address for
the Docket Operations is listed above.
FOR FURTHER INFORMATION CONTACT:
Alexei Marqueen, Aviation Safety
Engineer, ECO Branch, FAA, 1200
District Avenue, Burlington, MA 01803;
phone: (781) 238–7178; email:
Alexei.T.Marqueen@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
On July 20, 2021, a Boeing model
747–8F airplane, powered by GEnx–
2B67/P model turbofan engines, flying
from Hong Kong to Dubai, experienced
N1 overspeed and fire warnings that
resulted in an IFSD and air turnback
(ATB) to Hong Kong. After landing, the
engine reignited and emergency crews
extinguished the fire. The investigation
led by the National Transportation
Safety Board found several fuel system
leaks including at the FMU supply
pressure (P1) BPV pressure port with a
loose FMU BPV plug safety cabled in
place. Because a safety cable was in
place, the investigation concluded that
the FMU BPV plug might not have been
torqued properly during production or
during an engine shop visit. During the
investigation, GE discovered that
another operator, operating a Boeing
E:\FR\FM\22FER1.SGM
22FER1
]]>Agencies
[Federal Register Volume 87, Number 35 (Tuesday, February 22, 2022)]
[Rules and Regulations]
[Pages 9429-9432]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-03633]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-1006; Project Identifier MCAI-2021-00700-T;
Amendment 39-21940; AD 2022-03-22]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
[[Page 9430]]
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2019-26-
01, which applied to certain Airbus SAS Model A350-941 and -1041
airplanes. AD 2019-26-01 required repetitive detailed inspections, and
applicable corrective actions, and provided an optional modification
that terminated the inspections. Since the FAA issued AD 2019-26-01, a
determination was made that a related production modification was not
properly installed on certain airplanes. This AD retains the
requirements of AD 2019-26-01, and, for certain airplanes, adds a one-
time detailed inspection of the modification for proper installation,
and applicable corrective actions if necessary, 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 29, 2022.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of March 29,
2022.
ADDRESSES: For the 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 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-2021-1006.
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-1006; 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
mandatory continuing airworthiness information (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: Dan Rodina, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax 206-231-3225; email
[email protected].
SUPPLEMENTARY INFORMATION:
Background
EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2021-0141, dated June 15, 2021 (EASA
AD 2021-0141) (also referred to as the MCAI), to correct an unsafe
condition for certain Airbus SAS Model A350-941 and -1041 airplanes.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2019-26-01, Amendment 39-21023 (85 FR 4199,
January 24, 2020) (AD 2019-26-01). AD 2019-26-01 applied to certain
Airbus SAS Model A350-941 and -1041 airplanes. The NPRM published in
the Federal Register on November 18, 2021 (86 FR 64416). The NPRM was
prompted by reports of sealant bead damage caused by rotation of the
attachment fitting bearing assembly of a trimmable horizontal
stabilizer (THS) and a determination that a related production
modification was not properly installed on certain airplanes. The NPRM
proposed to retain the requirements of AD 2019-26-01, and, for certain
airplanes, proposed to add a one-time detailed inspection of the
modification for proper installation, and applicable corrective actions
if necessary, as specified in EASA AD 2021-0141.
The FAA is issuing this AD to address possible water ingress due to
sealant bead damage, which could result in corrosion damage in the
aluminum corner fitting. This condition, if not addressed, could lead
to detachment and loss of the THS, possibly resulting in loss of
control of the airplane and injury to persons on the ground. See the
MCAI for additional background information.
Discussion of Final Airworthiness Directive
Comments
The FAA received a comment from the Air Line Pilots Association,
International (ALPA), who supported the NPRM without change.
Conclusion
The FAA reviewed the relevant data, considered the comment
received, and determined that air safety requires adopting this AD as
proposed. Except for minor editorial changes, this AD is adopted as
proposed in the NPRM. None of the changes will increase the economic
burden on any operator. Accordingly, the FAA is issuing this AD to
address the unsafe condition on these products.
Related Service Information Under 1 CFR Part 51
EASA AD 2021-0141 describes procedures for repetitive detailed
inspections for damage of the fillet sealant and corrosion on aluminum
in the lower and upper corner fittings and bearing assembly attachment
interface at frame (FR) 102, left-hand and right-hand sides, and an
optional modification (application of new corrosion protection in the
THS upper and lower attachment fitting bearing assembly) that would
eliminate the need for the repetitive inspections. EASA AD 2021-0141
also describes procedures for a one-time detailed inspection of the
modification of the lower and upper corner fittings and bearing
assembly attachment interface at FR 102, left-hand and right-hand sides
(Airbus production modification 113102) for discrepancies (including
missing sealant bead, cracks in the sealant bead, and corrosion on the
affected bearing zone) and corrective actions (including, but not
limited to, a check for grease, a check for cracks in the sealant bead,
applying sealant, torqueing the bearing nut, inspecting for corrosion
on the affected bearing zone, applying corrosion preventative compound
and actions to address missing grease and corrosion). 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 15 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
[[Page 9431]]
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 30 work-hours x $85 per $0 $2,550 $38,250
2019[dash]26[dash]01. hour = $2,550.
New actions........................... 32 work-hours x $85 per 0 2,720 40,800
hour = $2,720.
----------------------------------------------------------------------------------------------------------------
The FAA has received no definitive data that enables the agency to
provide cost estimates for the corrective actions (including repair)
specified in this AD.
Estimated Costs of Optional Actions
------------------------------------------------------------------------
Cost per
Labor cost Parts cost product
------------------------------------------------------------------------
34 work-hours x $85 per hour = $2,890. $0 $2,890
------------------------------------------------------------------------
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.
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:
0
a. Removing Airworthiness Directive (AD) 2019-26-01, Amendment 39-21023
(85 FR 4199, January 24, 2020); and
0
b. Adding the following new AD:
2022-03-22 Airbus SAS: Amendment 39-21940; Docket No. FAA-2021-1006;
Project Identifier MCAI-2021-00700-T.
(a) Effective Date
This airworthiness directive (AD) is effective March 29, 2022.
(b) Affected ADs
This AD replaces AD 2019-26-01, Amendment 39-21023 (85 FR 4199,
January 24, 2020) (AD 2019-26-01).
(c) Applicability
This AD applies to Airbus SAS Model A350-941 and -1041
airplanes, certificated in any category, as identified in European
Union Aviation Safety Agency (EASA) AD 2021-0141, dated June 15,
2021 (EASA AD 2021-0141).
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of sealant bead damage caused by
rotation of the attachment fitting bearing assembly of a trimmable
horizontal stabilizer (THS) and a determination that a related
production modification was not properly installed on certain
airplanes. The FAA is issuing this AD to address possible water
ingress due to sealant bead damage, which could result in corrosion
damage in the aluminum corner fitting. This condition, if not
addressed, could lead to detachment and loss of the THS, possibly
resulting in loss of control of the airplane and injury to persons
on the ground.
(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, EASA AD 2021-0141.
(h) Exceptions to EASA AD 2021-0141
(1) Where EASA AD 2021-0141 refers to February 21, 2018 (the
effective date of EASA AD 2018-0037), this AD requires using
February 28, 2020 (the effective date of FAA AD 2019-26-01).
(2) Where EASA AD 2021-0141 refers to its effective date, this
AD requires using the effective date of this AD.
(3) The ``Remarks'' section of EASA AD 2021-0141 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
[[Page 9432]]
identified in paragraph (j) of this AD. Information may be emailed
to: [email protected].
(i) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the responsible Flight Standards Office.
(ii) AMOCs approved previously for AD 2019-26-01 are approved as
AMOCs for the corresponding provisions of EASA AD 2021-0141 that are
required by paragraph (g) of this AD.
(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): For any service information
referenced in EASA AD 2021-0141 that contains RC procedures and
tests: Except as required by paragraph (i)(2) of this AD, RC
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 Dan Rodina,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
and fax 206-231-3225; 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 2021-0141,
dated June 15, 2021.
(ii) [Reserved]
(3) For EASA AD 2021-0141, contact 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.
(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 28, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2022-03633 Filed 2-18-22; 8:45 am]
BILLING CODE 4910-13-P
