Airworthiness Directives; Airbus SAS Airplanes, 59406-59409 [2020-20826]
Download as PDF
<![CDATA[
59406
Federal Register / Vol. 85, No. 184 / Tuesday, September 22, 2020 / Rules and Regulations
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 helicopters 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
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):
■
VerDate Sep<11>2014
16:32 Sep 21, 2020
Jkt 250001
2020–19–11 Leonardo S.p.a.: Amendment
39–21254; Docket No. FAA–2020–0411;
Product Identifier 2018–SW–061–AD.
(a) Applicability
This AD applies to Leonardo S.p.a. Model
A119 and AW119 MKII helicopters,
certificated in any category, with 90-degree
tail rotor gearbox (TGB) part number (P/N)
109–0440–06–101 or 109–0440–06–105
having serial number 167, 169 through 172
inclusive, 215 through 225 inclusive, 227,
230, 232, 233, AW268, K3, K16, M47, or L29,
installed.
(b) Unsafe Condition
This AD defines the unsafe condition as
corrosion on the internal surface of the 90degree TGB output shaft. This condition
could result in failure of the 90-degree TGB
output shaft and reduced control of the
helicopter.
(c) Effective Date
This AD becomes effective October 27,
2020.
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
(1) Within 25 hours time-in-service (TIS) or
3 months, whichever occurs first, and
thereafter at intervals not to exceed 100 hours
TIS or 6 months, whichever occurs first,
borescope inspect the entire internal surface
of the 90-degree TGB output shaft for
corrosion. Refer to Figure 3 of Leonardo
Helicopters Alert Service Bulletin No. 119–
090, dated July 23, 2018, for a depiction of
the entry point for the borescope. If there is
corrosion, before further flight, remove from
service the TGB.
(2) After the effective date of this AD, do
not install on any helicopter any 90-degree
TGB P/N 109–0440–06–101 or 109–0440–06–
105 that has serial number 167, 169 through
172 inclusive, 215 through 225 inclusive,
227, 230, 232, 233, AW268, K3, K16, M47, or
L29, unless the actions required by paragraph
(e)(1) of this AD have been done.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Rotorcraft Standards
Branch, FAA, may approve AMOCs for this
AD. Send your proposal to: Rao Edupuganti,
Aviation Safety Engineer, Regulations and
Policy Section, Rotorcraft Standards Branch,
FAA, 10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone 817–222–5110; email 9ASW-FTW-AMOC-Requests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, the FAA suggests
that you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office, before
operating any aircraft complying with this
AD through an AMOC.
(g) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency (now
PO 00000
Frm 00030
Fmt 4700
Sfmt 4700
European Union Aviation Safety Agency)
(EASA) AD No. 2018–0156, dated July 24,
2018. You may view the EASA AD on the
internet at https://www.regulations.gov in
Docket No. FAA–2020–0411.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 62 Tail Rotor Gearbox.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference 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) Leonardo Helicopters Alert Service
Bulletin No. 119–090, dated July 23, 2018.
(ii) [Reserved]
(3) For service information identified in
this AD, contact Leonardo S.p.a. Helicopters,
Emanuele Bufano, Head of Airworthiness,
Viale G. Agusta 520, 21017 C. Costa di
Samarate (Va) Italy; telephone +39–0331–
225074; fax +39–0331–229046; or at https://
www.leonardocompany.com/en/home.
(4) You may view this service information
at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177. For
information on the availability of this
material at the FAA, call 817–222–5110.
(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/ibrlocations.html.
Issued on September 9, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–20750 Filed 9–21–20; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0328; Product
Identifier 2020–NM–030–AD; Amendment
39–21244; AD 2020–19–03]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus SAS Model A318 series
airplanes; Model A319–111, –112, –113,
SUMMARY:
E:\FR\FM\22SER1.SGM
22SER1
Federal Register / Vol. 85, No. 184 / Tuesday, September 22, 2020 / Rules and Regulations
–114, –115, –131, –132, and –133
airplanes; Model A320–211, –212, –214,
–216, –231, –232, and –233 airplanes;
and Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
This AD was prompted by reports of
crack findings in and around the
fastener holes of the central and lateral
window frame upper junction; those
cracks were found on fastener holes
outside of the inspection area specified
in a certain airworthiness limitation
item (ALI) task. This AD requires
repetitive inspections of the upper
junction fastener holes at the lateral
window frame for cracking; and for
certain airplanes, repetitive inspections
of the spotface around the fastener holes
for cracking; and 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.
This AD is effective October 27,
2020.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of October 27, 2020.
DATES:
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 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–
0328.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
0328; 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.
VerDate Sep<11>2014
16:32 Sep 21, 2020
Jkt 250001
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
Large Aircraft Section, International
Validation Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3223; email
sanjay.ralhan@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
The EASA, which is the Technical
Agent for the Member States of the
European Union, has issued EASA AD
2020–0019, dated February 5, 2020
(‘‘EASA AD 2020–0019’’) (also referred
to as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus SAS Model A318–
111, –112, –121, and –122 airplanes;
Model A319–111, –112, –113, –114,
–115, –131, –132, and –133 airplanes;
Model A320–211, –212, –214, –215,
–216, –231, –232, and –233 airplanes;
and Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
Model A320–215 airplanes are not
certificated by the FAA and are not
included on the U.S. type certificate
data sheet; therefore, this AD does not
include those airplanes in the
applicability.
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Airbus SAS Model
A318–111, –112, –121, and –122
airplanes; Model A319–111, –112, –113,
–114, –115, –131, –132, and –133
airplanes; Model A320–211, –212, –214,
–215, –216, –231, –232, and –233
airplanes; and Model A321–111, –112,
–131, –211, –212, –213, –231, and –232
airplanes. The NPRM published in the
Federal Register on April 10, 2020 (85
FR 20213). The NPRM was prompted by
reports of crack findings in and around
the fastener holes of the central and
lateral window frame upper junction;
those cracks were found on fastener
holes outside of the inspection area
specified in a certain ALI task. The
NPRM proposed to require repetitive
inspections of the upper junction
fastener holes at the lateral window
frame for cracking; and for certain
airplanes, repetitive inspections of the
spotface around the fastener holes for
cracking; and corrective actions if
necessary; as specified in an EASA AD.
The FAA is issuing this AD to address
such cracking, which could result in
reduced structural integrity of the
airplane. See the MCAI for additional
background information.
Comments
The FAA gave the public the
opportunity to participate in developing
PO 00000
Frm 00031
Fmt 4700
Sfmt 4700
59407
this final rule. The following presents
the comment received on the NPRM and
the FAA’s response to each comment.
Request To Clarify Impact on
Operator’s Maintenance Program
Delta Air Lines, Inc. (DAL) asked that
the FAA include a statement that the
proposed AD affects and is related to
AD 2019–23–01, Amendment 39–19794
(84 FR 66579, December 5, 2019) (‘‘AD
2019–23–01’’), and could impact an
operator’s maintenance program. DAL
stated that the procedures specified in
Airbus Service Bulletins A320–53–1448
and A320–53–1449, both dated August
5, 2019 (referred to in EASA AD 2020–
0019), cancel and replace Airworthiness
Limitation Item (ALI) Task 531125,
dated October 11, 2019, which is
required in Airworthiness Limitations
Section (ALS) part 2, revision 7. DAL
added that FAA Global Alternative
Method of Compliance (AMOC) AIR–
676–20–138, dated April 4, 2020,
approved ALS part 2, revision 8, which
removes ALI Task 531125. DAL noted
that, for operators that have
incorporated revision 8 prior to issuance
of the proposed AD, there would be a
potential gap in tracking, and that
adding the requested statement would
bring awareness to the relationship
between the specified service
information, MCAI, affected ADs and
ALI task.
The FAA acknowledges the
commenter’s concern, and provides the
following clarification: AD 2019–23–01
does not mandate incorporation of ALS
part 2, revision 08, in the operator’s
maintenance or inspection program. In
addition, ALI Task 531125 was removed
from ALS part 2, revision 8, for specific
model airplanes with specific
configurations. The FAA has no way to
ascertain the impact on an individual
operator’s maintenance program and
customize the AD requirements in
accordance with DAL’s maintenance or
inspection program. However, under the
provisions of paragraph (i) of this AD,
the FAA will consider requests for
approval of an AMOC if an operator’s
maintenance program is adversely
affected by the requirements of this AD,
if sufficient data are submitted to
substantiate that fact and that show the
method used adequately addresses the
unsafe condition identified in this AD.
The FAA has not changed this AD
regarding this issue.
Conclusion
The FAA reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting this
final rule as proposed, except for minor
E:\FR\FM\22SER1.SGM
22SER1
59408
Federal Register / Vol. 85, No. 184 / Tuesday, September 22, 2020 / Rules and Regulations
Related IBR Material Under 1 CFR Part
51
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.
EASA AD 2020–0019 describes
procedures for repetitive inspections of
the upper junction fastener holes at the
lateral window frame for cracking,
repetitive inspections of the spotface
around the fastener holes for cracking,
and corrective actions. Corrective
actions include repair. 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 938 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
4 work-hours × $85 per hour = $340 ..........................................................................................
$0
$340
$318,920
The FAA has received no definitive
data that will enable the FAA to provide
cost estimates for the on-condition
actions specified in this AD.
Authority for This Rulemaking
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.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of crack
findings in and around the fastener holes of
the central and lateral window frame upper
junction; those cracks were found on fastener
holes outside of the inspection area specified
in a certain airworthiness limitation item
(ALI) task. The FAA is issuing this AD to
address such cracking, which could result in
reduced structural integrity of the airplane.
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.
■
2020–19–03 Airbus SAS: Amendment 39–
21244; Docket No. FAA–2020–0328;
Product Identifier 2020–NM–030–AD.
(1) Where EASA AD 2020–0019 refers to its
effective date, this AD requires using the
effective date of this AD.
(2) The ‘‘Remarks’’ section of EASA AD
2020–0019 does not apply to this AD.
Regulatory Findings
(a) Effective Date
This AD is effective October 27, 2020.
(i) Other FAA AD Provisions
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
VerDate Sep<11>2014
16:32 Sep 21, 2020
Jkt 250001
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
(f) Compliance
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):
■
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus SAS
airplanes specified in paragraphs (c)(1)
through (4) of this AD, certificated in any
category, as identified in European Union
Aviation Safety Agency (EASA) AD 2020–
0019, dated February 5, 2020 (‘‘EASA AD
2020–0019’’).
(1) Model A318–111, –112, –121, and –122
airplanes.
(2) Model A319–111, –112, –113, –114,
–115, –131, –132, and –133 airplanes.
(3) Model A320–211, –212, –214, –216,
–231, –232, and –233 airplanes.
(4) Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
PO 00000
Frm 00032
Fmt 4700
Sfmt 4700
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 2020–0019.
(h) Exceptions to EASA AD 2020–0019
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 local Flight Standards
District 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 local flight
E:\FR\FM\22SER1.SGM
22SER1
Federal Register / Vol. 85, No. 184 / Tuesday, September 22, 2020 / Rules and Regulations
standards district office/certificate holding
district 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): For any
service information referenced in EASA AD
2020–0019 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.
Issued on September 1, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
(j) Related Information
For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
Large Aircraft Section, International
Validation Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198; telephone and
fax 206–231–3223; email sanjay.ralhan@
faa.gov.
SUMMARY:
(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 2020–0019, dated February 5,
2020.
(ii) [Reserved]
(3) For information about EASA AD 2020–
0019, contact the EASA, Konrad-AdenauerUfer 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
in the AD docket on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2020–0328.
(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.
VerDate Sep<11>2014
16:32 Sep 21, 2020
Jkt 250001
[FR Doc. 2020–20826 Filed 9–21–20; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0460; Product
Identifier 2018–SW–078–AD; Amendment
39–21252; AD 2020–19–09]
RIN 2120–AA64
Airworthiness Directives; Leonardo
S.p.A. Helicopters
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all
Leonardo S.p.A. Model AW169
helicopters and certain Leonardo S.p.A
Model AW189 helicopters. This AD was
prompted by a report of a broken
extrusion rubber window seal. This AD
requires installation of a reinforcement
around the rubber filler wedge where
the extrusion rubber window seal meets
the door’s emergency exit handle. The
FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective October 27,
2020.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of October 27, 2020.
ADDRESSES: For service information
identified in this final rule, contact
Leonardo S.p.A. Helicopters, Emanuele
Bufano, Head of Airworthiness, Viale G.
Agusta 520, 21017 C. Costa di Samarate
(Va) Italy; telephone +39–0331–225074;
fax +39–0331–229046; or at https://
www.leonardocompany.com/en/home.
You may view this service information
at the FAA, Office of the Regional
Counsel, Southwest Region, 10101
Hillwood Pkwy., Room 6N–321, Fort
Worth, TX 76177. For information on
the availability of this material at the
FAA, call 817–222–5110.
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–
0460; or in person at Docket Operations
PO 00000
Frm 00033
Fmt 4700
Sfmt 4700
59409
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
Docket Operations is listed above.
FOR FURTHER INFORMATION CONTACT:
Kristi Bradley, Aviation Safety Engineer,
International Validation Branch,
General Aviation & Rotorcraft Unit,
FAA, 10101 Hillwood Pkwy., Fort
Worth, TX 76177; telephone 817–222–
5110; email kristin.bradley@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Leonardo S.p.A. Model
AW169 helicopters and certain
Leonardo S.p.A. Model AW189
helicopters. The NPRM published in the
Federal Register on June 3, 2020 (85 FR
34139). The NPRM was prompted by a
report of a broken extrusion rubber
window seal, part number (P/N)
A417AF001WB. The NPRM proposed to
require installation of a reinforcement
around the rubber filler wedge where
the extrusion rubber window seal meets
the door’s emergency exit handle. The
FAA is issuing this AD to address
broken extrusion rubber window seals,
which could result in an excessive load
required to release the emergency exit
window, possibly resulting in delayed
evacuation of helicopter occupants
during an emergency.
The European Aviation Safety Agency
(now European Union Aviation Safety
Agency) (EASA), which is the Technical
Agent for the Member States of the
European Union, issued EASA AD
2018–0197, dated September 5, 2018
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for all Leonardo S.p.A. Model
AW169 helicopters and certain
Leonardo S.p.A. Model AW189
helicopters. EASA advises of a broken
extrusion rubber window seal, P/N
A417AF001WB. According to EASA, an
investigation determined that the
damage to the rubber filler wedge of the
rubber window seal could have been
caused by the excessive tension of the
string applied during the installation of
an affected emergency exit handle.
EASA advises that this condition, if not
corrected, could result in an excessive
load to release the emergency exit
window, possibly resulting in delayed
evacuation of helicopter occupants
during an emergency. EASA states that,
due to design similarities, the same
unsafe condition could exist or develop
E:\FR\FM\22SER1.SGM
22SER1
]]>Agencies
[Federal Register Volume 85, Number 184 (Tuesday, September 22, 2020)]
[Rules and Regulations]
[Pages 59406-59409]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-20826]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0328; Product Identifier 2020-NM-030-AD; Amendment
39-21244; AD 2020-19-03]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, -
113,
[[Page 59407]]
-114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214,
-216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -
211, -212, -213, -231, and -232 airplanes. This AD was prompted by
reports of crack findings in and around the fastener holes of the
central and lateral window frame upper junction; those cracks were
found on fastener holes outside of the inspection area specified in a
certain airworthiness limitation item (ALI) task. This AD requires
repetitive inspections of the upper junction fastener holes at the
lateral window frame for cracking; and for certain airplanes,
repetitive inspections of the spotface around the fastener holes for
cracking; and 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 October 27, 2020.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of October 27,
2020.
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 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-2020-0328.
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-
0328; 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: Sanjay Ralhan, Aerospace Engineer,
Large Aircraft Section, International Validation Branch, FAA, 2200
South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3223;
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 2020-0019, dated February 5, 2020
(``EASA AD 2020-0019'') (also referred to as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition for certain Airbus SAS Model A318-111, -112, -121, and -122
airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes; Model A320-211, -212, -214, -215, -216, -231, -232, and -233
airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and
-232 airplanes. Model A320-215 airplanes are not certificated by the
FAA and are not included on the U.S. type certificate data sheet;
therefore, this AD does not include those airplanes in the
applicability.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain Airbus SAS
Model A318-111, -112, -121, and -122 airplanes; Model A319-111, -112, -
113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212,
-214, -215, -216, -231, -232, and -233 airplanes; and Model A321-111, -
112, -131, -211, -212, -213, -231, and -232 airplanes. The NPRM
published in the Federal Register on April 10, 2020 (85 FR 20213). The
NPRM was prompted by reports of crack findings in and around the
fastener holes of the central and lateral window frame upper junction;
those cracks were found on fastener holes outside of the inspection
area specified in a certain ALI task. The NPRM proposed to require
repetitive inspections of the upper junction fastener holes at the
lateral window frame for cracking; and for certain airplanes,
repetitive inspections of the spotface around the fastener holes for
cracking; and corrective actions if necessary; as specified in an EASA
AD. The FAA is issuing this AD to address such cracking, which could
result in reduced 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 following presents the comment received
on the NPRM and the FAA's response to each comment.
Request To Clarify Impact on Operator's Maintenance Program
Delta Air Lines, Inc. (DAL) asked that the FAA include a statement
that the proposed AD affects and is related to AD 2019-23-01, Amendment
39-19794 (84 FR 66579, December 5, 2019) (``AD 2019-23-01''), and could
impact an operator's maintenance program. DAL stated that the
procedures specified in Airbus Service Bulletins A320-53-1448 and A320-
53-1449, both dated August 5, 2019 (referred to in EASA AD 2020-0019),
cancel and replace Airworthiness Limitation Item (ALI) Task 531125,
dated October 11, 2019, which is required in Airworthiness Limitations
Section (ALS) part 2, revision 7. DAL added that FAA Global Alternative
Method of Compliance (AMOC) AIR-676-20-138, dated April 4, 2020,
approved ALS part 2, revision 8, which removes ALI Task 531125. DAL
noted that, for operators that have incorporated revision 8 prior to
issuance of the proposed AD, there would be a potential gap in
tracking, and that adding the requested statement would bring awareness
to the relationship between the specified service information, MCAI,
affected ADs and ALI task.
The FAA acknowledges the commenter's concern, and provides the
following clarification: AD 2019-23-01 does not mandate incorporation
of ALS part 2, revision 08, in the operator's maintenance or inspection
program. In addition, ALI Task 531125 was removed from ALS part 2,
revision 8, for specific model airplanes with specific configurations.
The FAA has no way to ascertain the impact on an individual operator's
maintenance program and customize the AD requirements in accordance
with DAL's maintenance or inspection program. However, under the
provisions of paragraph (i) of this AD, the FAA will consider requests
for approval of an AMOC if an operator's maintenance program is
adversely affected by the requirements of this AD, if sufficient data
are submitted to substantiate that fact and that show the method used
adequately addresses the unsafe condition identified in this AD. The
FAA has not changed this AD regarding this issue.
Conclusion
The FAA reviewed the relevant data, considered the comment
received, and determined that air safety and the public interest
require adopting this final rule as proposed, except for minor
[[Page 59408]]
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 IBR Material Under 1 CFR Part 51
EASA AD 2020-0019 describes procedures for repetitive inspections
of the upper junction fastener holes at the lateral window frame for
cracking, repetitive inspections of the spotface around the fastener
holes for cracking, and corrective actions. Corrective actions include
repair. 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 938 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
----------------------------------------------------------------------------------------------------------------
4 work-hours x $85 per hour = $340........................... $0 $340 $318,920
----------------------------------------------------------------------------------------------------------------
The FAA has received no definitive data that will enable the FAA to
provide cost estimates for the on-condition actions specified in this
AD.
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 (AD):
2020-19-03 Airbus SAS: Amendment 39-21244; Docket No. FAA-2020-0328;
Product Identifier 2020-NM-030-AD.
(a) Effective Date
This AD is effective October 27, 2020.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus SAS airplanes specified in
paragraphs (c)(1) through (4) of this AD, certificated in any
category, as identified in European Union Aviation Safety Agency
(EASA) AD 2020-0019, dated February 5, 2020 (``EASA AD 2020-0019'').
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(3) Model A320-211, -212, -214, -216, -231, -232, and -233
airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of crack findings in and around
the fastener holes of the central and lateral window frame upper
junction; those cracks were found on fastener holes outside of the
inspection area specified in a certain airworthiness limitation item
(ALI) task. The FAA is issuing this AD to address such cracking,
which could result in reduced 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, EASA AD 2020-0019.
(h) Exceptions to EASA AD 2020-0019
(1) Where EASA AD 2020-0019 refers to its effective date, this
AD requires using the effective date of this AD.
(2) The ``Remarks'' section of EASA AD 2020-0019 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 local Flight
Standards District 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 local flight
[[Page 59409]]
standards district office/certificate holding district 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): For any service information
referenced in EASA AD 2020-0019 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 Sanjay Ralhan,
Aerospace Engineer, Large Aircraft Section, International Validation
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
and fax 206-231-3223; 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 2020-0019,
dated February 5, 2020.
(ii) [Reserved]
(3) For information about EASA AD 2020-0019, 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 in the AD
docket on the internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2020-0328.
(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 September 1, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020-20826 Filed 9-21-20; 8:45 am]
BILLING CODE 4910-13-P
