Airworthiness Directives; Airbus SAS Airplanes, 71240-71244 [2020-24642]
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Federal Register / Vol. 85, No. 217 / Monday, November 9, 2020 / Rules and Regulations
19026 (82 FR 43160, September 14,
2017), and
■ b. Adding the following new AD:
2020–22–11 Airbus SAS: Amendment 39–
21307; Docket No. FAA–2020–0464;
Product Identifier 2020–NM–040–AD.
(a) Effective Date
This AD is effective December 14, 2020.
(b) Affected ADs
This AD replaces AD 2017–18–17,
Amendment 39–19026 (82 FR 43160,
September 14, 2017) (‘‘AD 2017–18–17’’).
(c) Applicability
This AD applies to all Airbus SAS Model
A300 B4–603, A300 B4–620, A300 B4–622,
A300 B4–605R, A300 B4–622R, A300 F4–
605R, A300 F4–622R, and A300 C4–605R
Variant F airplanes, certificated in any
category.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report
indicating that the material used to
manufacture the upper frame feet was
changed and negatively affected the fatigue
life of the frame feet, and a determination
that more work is required for certain
airplanes that were previously modified. The
FAA is issuing this AD to address cracking
of the center section of the fuselage, which
could result in a ruptured frame foot and
reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(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 2020–0051, dated
March 11, 2020 (‘‘EASA AD 2020–0051’’).
(h) Exceptions to EASA AD 2020–0051
(1) Where EASA AD 2020–0051 refers to its
effective date, this AD requires using the
effective date of this AD.
(2) The ‘‘Remarks’’ section of EASA AD
2020–0051 does not apply to this AD.
(3) For airplanes on which the
modification specified in Airbus Service
Bulletin A300–53–6178 has been done:
Where paragraph (4) of EASA AD 2020–0051
specifies to do certain actions ‘‘no later than
6 months (estimated by projection of airplane
usage) prior to exceeding 24,500 flight cycles
or 42,700 flight hours, whichever occurs first,
after Airbus Service Bulletin A300–53–6178
embodiment (at any revision),’’ this AD
requires doing those actions prior to
exceeding 24,100 total flight cycles or 42,000
total flight hours, whichever occurs first after
doing the modification.
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
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(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
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
2020–0051 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,
Large Aircraft Section, International
Validation Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198; phone 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 2020–0051, dated March 11,
2020.
(ii) [Reserved]
(3) For EASA AD 2020–0051, contact the
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; phone: +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.
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(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–2020–0464.
(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 October 19, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–24641 Filed 11–6–20; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0451; Product
Identifier 2020–NM–036–AD; Amendment
39–21302; AD 2020–22–06]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 99–01–19
and AD 2004–25–02, which applied to
certain Airbus SAS Model A320 series
airplanes. AD 99–01–19 and AD 2004–
25–02 required repetitive inspections to
detect fatigue cracking in certain areas
of the fuselage, and corrective action if
necessary. AD 2004–25–02 also
provided an optional terminating action
for the repetitive inspections. This AD
continues to require, for certain
airplanes, repetitive inspections of the
fastener holes for any cracking, and
repair if necessary, and provides an
optional terminating action for the
fastener hole inspections. This AD also
revises the applicability to include
additional airplanes and requires, for all
airplanes, inspections of the emergency
exit door structure for any cracking and
repair if necessary; as specified in a
European Union Aviation Safety Agency
(EASA) AD, which is incorporated by
reference. This AD was prompted by a
report that during full scale tests to
support the Model A320 structure
extended service goal (ESG) exercise,
SUMMARY:
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Federal Register / Vol. 85, No. 217 / Monday, November 9, 2020 / Rules and Regulations
several cracks were found on both sides
of the overwing emergency exit door
cut-outs at fuselage section 15. The FAA
is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective December
14, 2020.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 14, 2020.
The Director of the Federal Register
also approved the incorporation by
reference of a certain other publication
listed in this AD as of February 10, 2005
(70 FR 1184, January 6, 2005).
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of February 12, 1999 (64 FR
1114, January 8, 1999).
ADDRESSES: For EASA AD 2020–
0040R1, which is incorporated by
reference (IBR), 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.
For Airbus service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
EIAS, Rond-Point Emile Dewoitine No:
2, 31700 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airwortheas@airbus.com; internet https://
www.airbus.com. You may view EASA
AD 2020–0040R1 and the Airbus service
information identified in this AD 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–
0451.
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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–
0451; 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.
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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
2020–0040R1, dated June 16, 2020
(‘‘EASA AD 2020–0040R1’’) (also
referred to as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus SAS Model A319–
111, –112, –113, –114, –115, –131, –132,
and –133 airplanes; and Model A320–
211, –212, –214, –215, –216, –231, –232,
and –233 airplanes. Model A320–215
airplanes are not certified by the FAA
and are not included on the U.S. type
certificate data sheet; this AD therefore
does not include those airplanes in the
applicability. EASA AD 2020–0040R1
superseded French AD 2002–259(B),
dated May 15, 2002 (which
corresponded to FAA AD 2004–25–02,
Amendment 39–13889 (70 FR 1184,
January 6, 2005) (‘‘AD 2004–25–02’’)).
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 99–01–19,
Amendment 39–10987 (64 FR 1114,
January 8, 1999) (‘‘AD 99–01–19’’); and
AD 2004–25–02. AD 99–01–19 and AD
2004–25–02 applied to certain Airbus
SAS Model A320 series airplanes. The
NPRM published in the Federal
Register on June 4, 2020 (85 FR 34371).
The NPRM was prompted by a report
that during full scale tests to support the
Model A320 structure ESG exercise,
several cracks were found on both sides
of the overwing emergency exit door
cut-outs at fuselage section 15. The
NPRM proposed to continue to require,
for certain airplanes, repetitive
inspections of the fastener holes for any
cracking, and repair if necessary, and
would provide an optional terminating
action for the fastener hole inspections.
The NPRM also proposed to revise the
applicability to include additional
airplanes and requires, for all airplanes,
inspections of the emergency exit door
structure for any cracking and repair if
necessary, as specified in EASA AD
2020–0040R1.
The FAA is issuing this AD to address
fatigue cracking of the fuselage, which
could result in reduced structural
integrity of the airplane. See the MCAI
for additional background information.
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Comments
The FAA gave the public the
opportunity to participate in developing
this final rule. The following presents
the comments received on the NPRM
and the FAA’s response to each
comment.
Request To Use the Latest EASA AD
American Airlines (AAL) and United
Airlines (UAL) requested that the NPRM
specify EASA AD 2020–0040R1, which
is the latest EASA AD, and it revises the
applicability to exclude airplanes that
have embodied certain modifications in
production, and that those airplanes are,
therefore, not applicable to the NPRM.
AAL stated that FAA AD 2004–25–02
and EASA AD 2020–0040R1 contain a
difference in the applicability. AAL
stated that FAA AD 2004–25–02 applies
to Airbus Model A320 airplanes without
modification 21346 embodied in
production. AAL also stated that EASA
AD 2020–0040R1 applies to all Airbus
Model A319 and A320 airplanes, except
for those with modification 160001
embodied in production, or Airbus
Service Bulletin A320–57–1193
embodied in service, or Model A319
airplanes that have had modification
28238, 28162, and 28342 embodied in
production. AAL commented that some
of its Model A319 airplanes have had
modification 160001 embodied in
production, but would still be required
to accomplish the actions specified in
paragraph (k) of the NPRM.
The FAA agrees with the comment.
The FAA has revised all applicable
sections in this final rule to specify
EASA AD 2020–0040R1, dated June 16,
2020, which clarifies the conditions and
applicability for certain airplanes as of
the effective date of this final rule. For
clarification, airplane models that have
embodied certain modifications or
service information in production,
paragraph (k) of this AD does not apply.
The FAA has also determined that no
additional work is required for airplanes
on which the actions specified in EASA
AD 2020–0040, dated February 28,
2020, have already been done.
Changes Since the NPRM Was Issued
The FAA inadvertently omitted
paragraph (l)(4) from the proposed AD,
and has added it to this AD to clarify
that, ‘‘The ‘‘Remarks’’ section of EASA
AD 2020–0040R1 does not apply to this
AD.’’
Conclusion
The FAA reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this
final rule with the change described
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Federal Register / Vol. 85, No. 217 / Monday, November 9, 2020 / Rules and Regulations
previously and 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.
The FAA also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this final rule.
Related IBR Material Under 1 CFR Part
51
EASA AD 2020–0040R1 describes,
among other actions, procedures for
This AD also requires Airbus Service
Bulletin A320–53–1032, Revision 01,
dated January 15, 1998, which the
Director of the Federal Register
approved for incorporation by reference
as of February 12, 1999 (64 FR 1114,
January 8, 1999).
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.
inspections of the emergency exit door
structure for any cracking and repair, if
necessary.
Airbus has issued Service Bulletin
A320–53–1031, Revision 02, dated
December 5, 2001. This service
information describes procedures for
repetitive rotating probe inspections of
the fasteners holes and repair if
necessary.
This AD also requires Airbus Service
Bulletin A320–53–1032, Revision 02,
dated December 5, 2001, which the
Director of the Federal Register
approved for incorporation by reference
as of February 10, 2005 (70 FR 1184,
January 6, 2005).
Costs of Compliance
The FAA estimates that this AD
affects 800 airplanes of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Labor cost
Retained actions from
AD 2004–25–02.
New actions ..................
Up to 19 work-hours × $85 per hour = Up to
$1,615.
Up to 23 work-hours × $85 per hour = Up to
$1,955.
The FAA estimates the following
costs to do any necessary on-condition
actions that would be required based on
Cost per
product
Parts cost
the results of any required actions. The
FAA has no way of determining the
Cost on U.S.
operators
$0
Up to $1,615 ........
Up to $1,292,000.
0
Up to $1,955 ........
Up to $1,564,000.
number of aircraft that might need these
on-condition actions:
ESTIMATED COSTS OF ON-CONDITION ACTIONS: MODIFICATION, REPAIR OF FASTENER HOLES, AND REPAIR OF CRACKS IN
THE EMERGENCY EXIT DOOR STRUCTURE THAT ARE WITHIN LIMITS
Cost per
product
Labor cost
Parts cost
Up to 66 work-hours × $85 per hour = Up to $5,610 ..................................................................
Up to $85,000 .............
Up to $90,610.
ESTIMATED COSTS FOR OPTIONAL ACTIONS
Labor cost
Parts cost
Cost per
product
1 work-hour × $85 per hour = $85 ..........................................................................................................................
$4,219
$4,304
The FAA has received no definitive
data that would enable the agency to
provide cost estimates for certain other
repairs specified in this AD.
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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
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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
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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.
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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:
a. Removing Airworthiness Directive
(AD) 99–01–19, Amendment 39–10987
(64 FR 1114, January 8, 1999); and AD
2004–25–02, Amendment 39–13889 (70
FR 1184, January 6, 2005); and
■ b. Adding the following new AD:
■
■
2020–22–06 Airbus SAS: Amendment 39–
21302; Docket No. FAA–2020–0451; Product
Identifier 2020–NM–036–AD.
(a) Effective Date
This AD is effective December 14, 2020.
(b) Affected ADs
This AD replaces AD 99–01–19,
Amendment 39–10987 (64 FR 1114, January
8, 1999) (‘‘AD 99–01–19’’); and AD 2004–25–
02, Amendment 39–13889 (70 FR 1184,
January 6, 2005) (‘‘AD 2004–25–02’’).
(c) Applicability
This AD applies to Airbus SAS Model
A319–111, –112, –113, –114, –115, –131,
–132, and –133 airplanes; and Model A320–
211, –212, –214, –216, –231, –232, and –233
airplanes, certificated in any category, as
identified in European Union Aviation Safety
Agency (EASA) AD 2020–0040R1, dated June
16, 2020 (‘‘EASA AD 2020–0040R1’’).
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report that,
during full scale tests to support the Model
A320 structure extended service goal (ESG)
exercise, several cracks were found on both
sides of the overwing emergency exit door
cut-outs at fuselage section 15. The FAA is
issuing this AD to address fatigue cracking of
the fuselage, which could result in reduced
structural integrity of the airplane.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Initial Inspections, With No
Changes
For Airbus SAS Model A320–111, –211,
–212, and –231 series airplanes on which
Airbus Modification 21346 has not been
done: This paragraph restates the
requirements of paragraph (f) of AD 2004–
25–02, with no changes. At the applicable
time specified in paragraph (g)(1) or (2) of
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this AD: Do a detailed inspection to find
cracking on the outboard flanges around the
fastener holes of frames 38 through 41,
between stringers 12 and 21, using Airbus
Service Bulletin A320–53–1032, Revision 02,
dated December 5, 2001.
(1) For airplanes on which the inspection
specified in Airbus Service Bulletin A320–
53–1032, Revision 01, dated January 15,
1998; or Airbus Service Bulletin A320–53–
1032, Revision 02, dated December 5, 2001;
has been done as of February 10, 2005 (the
effective date of AD 2004–25–02): Do the
next inspection within 4,900 flight cycles
after accomplishment of the last inspection,
or within 1,100 flight cycles after February
10, 2005, whichever is later.
(2) For airplanes on which no inspection
specified in Airbus Service Bulletin A320–
53–1032, Revision 01, dated January 15,
1998; or Airbus Service Bulletin A320–53–
1032, Revision 02, dated December 5, 2001;
has been done as of February 10, 2005 (the
effective date of AD 2004–25–02): Do the
inspection at the earlier of the times specified
in paragraphs (g)(2)(i) and (ii) of this AD.
(i) Before the accumulation of 30,000 total
flight cycles.
(ii) Before the accumulation of 24,800 total
flight cycles, or within 3,500 flight cycles
after February 10, 2005 (the effective date of
AD 2004–25–02), whichever is later.
(h) Retained Repetitive Inspections if No
Cracking is Found, With No Changes
This paragraph restates the requirements of
paragraph (g) of AD 2004–25–02, with no
changes. If no crack is found during the
inspection required by paragraph (g)(1) or (2)
of this AD: Repeat the inspection thereafter
at intervals not to exceed 4,900 flight cycles.
(i) Retained Corrective Actions With New
Repetitive Inspections and Compliance
Language
This paragraph restates the requirements of
paragraph (h) of AD 2004–25–02, with new
repetitive inspections and compliance
language. If any crack is found during any
inspection required by paragraph (g) of this
AD, before further flight, repair using Airbus
Service Bulletin A320–53–1032, Revision 01,
dated January 15, 1998; or Airbus Service
Bulletin A320–53–1032, Revision 02, dated
December 5, 2001. Accomplishment of a
repair using the service bulletin before the
effective date of this AD ends the repetitive
inspection requirements for the area repaired.
As of the effective date of this AD, the repair
does not constitute terminating action for the
repetitive inspection. Thereafter, repeat the
inspection at intervals not to exceed 4,900
flight cycles. If any crack is found during any
inspection required by this AD, and the
service bulletin specifies to contact Airbus
for appropriate action: Before further flight,
repair 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).
(j) Retained Optional Terminating Action
With Changes to the Service Information
Compliance Language
This paragraph restates the optional
terminating action specified in paragraphs (i)
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and (j) of AD 2004–25–02, with changes to
the service information compliance language.
Accomplishment of Airbus Modification
21346 using Airbus Service Bulletin A320–
53–1031, Revision 02, dated December 5,
2001, constitutes terminating action for the
repetitive inspection requirements of
paragraphs (h) and (i) this AD.
(k) New Requirements
Except as specified in paragraph (l) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, EASA AD 2020–0040R1.
(l) Exceptions to EASA AD 2020–0040R1
(1) Where EASA AD 2020–0040R1 refers to
its effective date, this AD requires using the
effective date of this AD.
(2) Where EASA AD 2020–0040R1 refers to
‘‘13 March 2020 [the effective date of the
original issue of this AD],’’ this AD requires
using the effective date of this AD.
(3) Where EASA AD 2020–0040R1 requires
the accomplishment of repetitive inspections
and corrective actions as specified in
paragraphs (1) and (2) of the EASA AD, those
actions are not required by this AD as
specified in the EASA AD. Those actions are
required by paragraphs (g), (h), and (i) of this
AD.
(4) The ‘‘Remarks’’ section of EASA AD
2020–0040R1 does not apply to this AD.
(m) Credit for Previous Actions
This paragraph provides credit for the
optional terminating action specified in
paragraph (j) of this AD, if Airbus
Modification 21346 was performed before the
effective date of this AD using Airbus Service
Bulletin A320–53–1031, dated December 9,
1994.
(n) 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 (o)(1) 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
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 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
E:\FR\FM\09NOR1.SGM
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71244
Federal Register / Vol. 85, No. 217 / Monday, November 9, 2020 / Rules and Regulations
2020–0040R1 that contains RC procedures
and tests: Except as required by paragraph
(n)(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.
in the AD docket on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2020–0451.
(8) 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.
Products Section, Operational Safety
Branch, 901 Locust, Kansas City, MO
64106. For information on the
availability of this material at the FAA,
call 816–329–4148. It is also available
on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
0719.
Issued on October 15, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
(o) Related Information
(1) 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.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (p)(6) and (7) of this AD.
BILLING CODE 4910–13–P
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–
0719; 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:
Doug Rudolph, Aerospace Engineer,
FAA, General Aviation & Rotorcraft
Section, International Validation
Branch, 901 Locust, Room 301, Kansas
City, Missouri 64106; telephone: (816)
329–4059; fax: (816) 329–4090; email:
doug.rudolph@faa.gov.
SUPPLEMENTARY INFORMATION:
(p) 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.
(3) The following service information was
approved for IBR on December 14, 2020.
(i) European Union Aviation Safety Agency
(EASA) AD 2020–0040R1, dated June 16,
2020.
(ii) Airbus Service Bulletin A320–53–1031,
Revision 02, dated December 5, 2001.
(4) The following service information was
approved for IBR on February 10, 2005 (70
FR 1184, January 6, 2005).
(i) Airbus Service Bulletin A320–53–1032,
Revision 02, dated December 5, 2001.
(ii) [Reserved]
(5) The following service information was
also approved for IBR on February 12, 1999
(64 FR 1114, January 8, 1999).
(i) Airbus Service Bulletin A320–53–1032,
Revision 01, dated January 15, 1998.
(ii) [Reserved]
(6) For EASA AD 2020–0040R1, 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. For Airbus material,
contact Airbus SAS, Airworthiness Office—
EIAS, Rond-Point Emile Dewoitine No: 2,
31700 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com; internet
https://www.airbus.com.
(7) 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
VerDate Sep<11>2014
15:57 Nov 06, 2020
Jkt 253001
[FR Doc. 2020–24642 Filed 11–6–20; 8:45 am]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0719; Project
Identifier 2019–CE–041–AD; Amendment
39–21313; AD 2020–22–17]
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
movement of the aft fuel pipe within the
coupling, which can cause damage to
the O-rings and lead to a fuel leak, fuel
fire or explosion, and consequent loss of
control of the airplane. This AD requires
replacing and prohibits installing
affected parts. The FAA is issuing this
AD to address the unsafe condition on
these products.
DATES: This AD is effective December
14, 2020.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 14, 2020.
ADDRESSES: For service information
identified in this final rule, contact
Pilatus Aircraft Ltd., Customer Support
General Aviation, CH–6371 Stans,
Switzerland, telephone: +41 848 24 7
365, techsupport.ch@pilatusaircraft.com, https://www.pilatusaircraft.com. You may view this service
information at the FAA, Airworthiness
SUMMARY:
PO 00000
Frm 00022
Fmt 4700
Sfmt 4700
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to Pilatus Model PC–24 airplanes
with a certain part-numbered flexible
saddle clamp installed between frame
34 and 36. The NPRM published in the
Federal Register on July 30, 2020 (85 FR
45810). The NPRM proposed to require
actions to correct the unsafe condition
on the specified products and 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 issued AD No. 2019–0240,
dated September 25, 2019 (referred to
after this as ‘‘the MCAI’’), which states:
An occurrence was reported where, during
maintenance, when system pressure was
applied to a motive-flow fuel pipe, the aft
fuel pipe was found to move to the end stop
within the coupling. When system pressure
was released, the aft fuel pipe returned to its
point of origin. This movement can cause
damage to the O-rings.
This condition, if not corrected, could lead
to a fuel leak and consequently a fuel
contamination of the rear fuselage, which, in
combination with an ignition source in this
E:\FR\FM\09NOR1.SGM
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]]>Agencies
[Federal Register Volume 85, Number 217 (Monday, November 9, 2020)]
[Rules and Regulations]
[Pages 71240-71244]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-24642]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0451; Product Identifier 2020-NM-036-AD; Amendment
39-21302; AD 2020-22-06]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 99-01-19
and AD 2004-25-02, which applied to certain Airbus SAS Model A320
series airplanes. AD 99-01-19 and AD 2004-25-02 required repetitive
inspections to detect fatigue cracking in certain areas of the
fuselage, and corrective action if necessary. AD 2004-25-02 also
provided an optional terminating action for the repetitive inspections.
This AD continues to require, for certain airplanes, repetitive
inspections of the fastener holes for any cracking, and repair if
necessary, and provides an optional terminating action for the fastener
hole inspections. This AD also revises the applicability to include
additional airplanes and requires, for all airplanes, inspections of
the emergency exit door structure for any cracking and repair if
necessary; as specified in a European Union Aviation Safety Agency
(EASA) AD, which is incorporated by reference. This AD was prompted by
a report that during full scale tests to support the Model A320
structure extended service goal (ESG) exercise,
[[Page 71241]]
several cracks were found on both sides of the overwing emergency exit
door cut-outs at fuselage section 15. The FAA is issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective December 14, 2020.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of December 14,
2020.
The Director of the Federal Register also approved the
incorporation by reference of a certain other publication listed in
this AD as of February 10, 2005 (70 FR 1184, January 6, 2005).
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
February 12, 1999 (64 FR 1114, January 8, 1999).
ADDRESSES: For EASA AD 2020-0040R1, which is incorporated by reference
(IBR), 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. For Airbus service information identified
in this final rule, contact Airbus SAS, Airworthiness Office--EIAS,
Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email
[email protected]; internet https://www.airbus.com. You
may view EASA AD 2020-0040R1 and the Airbus service information
identified in this AD 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-2020-0451.
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-
0451; 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 2020-0040R1, dated June 16, 2020
(``EASA AD 2020-0040R1'') (also referred to as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition for certain Airbus SAS Model A319-111, -112, -113, -114, -
115, -131, -132, and -133 airplanes; and Model A320-211, -212, -214, -
215, -216, -231, -232, and -233 airplanes. Model A320-215 airplanes are
not certified by the FAA and are not included on the U.S. type
certificate data sheet; this AD therefore does not include those
airplanes in the applicability. EASA AD 2020-0040R1 superseded French
AD 2002-259(B), dated May 15, 2002 (which corresponded to FAA AD 2004-
25-02, Amendment 39-13889 (70 FR 1184, January 6, 2005) (``AD 2004-25-
02'')).
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 99-01-19, Amendment 39-10987 (64 FR 1114,
January 8, 1999) (``AD 99-01-19''); and AD 2004-25-02. AD 99-01-19 and
AD 2004-25-02 applied to certain Airbus SAS Model A320 series
airplanes. The NPRM published in the Federal Register on June 4, 2020
(85 FR 34371). The NPRM was prompted by a report that during full scale
tests to support the Model A320 structure ESG exercise, several cracks
were found on both sides of the overwing emergency exit door cut-outs
at fuselage section 15. The NPRM proposed to continue to require, for
certain airplanes, repetitive inspections of the fastener holes for any
cracking, and repair if necessary, and would provide an optional
terminating action for the fastener hole inspections. The NPRM also
proposed to revise the applicability to include additional airplanes
and requires, for all airplanes, inspections of the emergency exit door
structure for any cracking and repair if necessary, as specified in
EASA AD 2020-0040R1.
The FAA is issuing this AD to address fatigue cracking of the
fuselage, 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 comments
received on the NPRM and the FAA's response to each comment.
Request To Use the Latest EASA AD
American Airlines (AAL) and United Airlines (UAL) requested that
the NPRM specify EASA AD 2020-0040R1, which is the latest EASA AD, and
it revises the applicability to exclude airplanes that have embodied
certain modifications in production, and that those airplanes are,
therefore, not applicable to the NPRM.
AAL stated that FAA AD 2004-25-02 and EASA AD 2020-0040R1 contain a
difference in the applicability. AAL stated that FAA AD 2004-25-02
applies to Airbus Model A320 airplanes without modification 21346
embodied in production. AAL also stated that EASA AD 2020-0040R1
applies to all Airbus Model A319 and A320 airplanes, except for those
with modification 160001 embodied in production, or Airbus Service
Bulletin A320-57-1193 embodied in service, or Model A319 airplanes that
have had modification 28238, 28162, and 28342 embodied in production.
AAL commented that some of its Model A319 airplanes have had
modification 160001 embodied in production, but would still be required
to accomplish the actions specified in paragraph (k) of the NPRM.
The FAA agrees with the comment. The FAA has revised all applicable
sections in this final rule to specify EASA AD 2020-0040R1, dated June
16, 2020, which clarifies the conditions and applicability for certain
airplanes as of the effective date of this final rule. For
clarification, airplane models that have embodied certain modifications
or service information in production, paragraph (k) of this AD does not
apply. The FAA has also determined that no additional work is required
for airplanes on which the actions specified in EASA AD 2020-0040,
dated February 28, 2020, have already been done.
Changes Since the NPRM Was Issued
The FAA inadvertently omitted paragraph (l)(4) from the proposed
AD, and has added it to this AD to clarify that, ``The ``Remarks''
section of EASA AD 2020-0040R1 does not apply to this AD.''
Conclusion
The FAA reviewed the relevant data, considered the comments
received, and determined that air safety and the public interest
require adopting this final rule with the change described
[[Page 71242]]
previously and 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.
The FAA also determined that these changes will not increase the
economic burden on any operator or increase the scope of this final
rule.
Related IBR Material Under 1 CFR Part 51
EASA AD 2020-0040R1 describes, among other actions, procedures for
inspections of the emergency exit door structure for any cracking and
repair, if necessary.
Airbus has issued Service Bulletin A320-53-1031, Revision 02, dated
December 5, 2001. This service information describes procedures for
repetitive rotating probe inspections of the fasteners holes and repair
if necessary.
This AD also requires Airbus Service Bulletin A320-53-1032,
Revision 02, dated December 5, 2001, which the Director of the Federal
Register approved for incorporation by reference as of February 10,
2005 (70 FR 1184, January 6, 2005).
This AD also requires Airbus Service Bulletin A320-53-1032,
Revision 01, dated January 15, 1998, which the Director of the Federal
Register approved for incorporation by reference as of February 12,
1999 (64 FR 1114, January 8, 1999).
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 800 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2004- Up to 19 work-hours x $0 Up to $1,615.... Up to
25-02. $85 per hour = Up to $1,292,000.
$1,615.
New actions.................. Up to 23 work-hours x 0 Up to $1,955.... Up to
$85 per hour = Up to $1,564,000.
$1,955.
----------------------------------------------------------------------------------------------------------------
The FAA estimates the following costs to do any necessary on-
condition actions that would be required based on the results of any
required actions. The FAA has no way of determining the number of
aircraft that might need these on-condition actions:
Estimated Costs of On-Condition Actions: Modification, Repair of
Fastener Holes, and Repair of Cracks in the Emergency Exit Door
Structure That are Within Limits
------------------------------------------------------------------------
Labor cost Parts cost Cost per product
------------------------------------------------------------------------
Up to 66 work-hours x $85 per Up to $85,000..... Up to $90,610.
hour = Up to $5,610.
------------------------------------------------------------------------
Estimated Costs for Optional Actions
------------------------------------------------------------------------
Cost per
Labor cost Parts cost product
------------------------------------------------------------------------
1 work-hour x $85 per hour = $85...... $4,219 $4,304
------------------------------------------------------------------------
The FAA has received no definitive data that would enable the
agency to provide cost estimates for certain other repairs 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.
[[Page 71243]]
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:
0
a. Removing Airworthiness Directive (AD) 99-01-19, Amendment 39-10987
(64 FR 1114, January 8, 1999); and AD 2004-25-02, Amendment 39-13889
(70 FR 1184, January 6, 2005); and
0
b. Adding the following new AD:
2020-22-06 Airbus SAS: Amendment 39-21302; Docket No. FAA-2020-0451;
Product Identifier 2020-NM-036-AD.
(a) Effective Date
This AD is effective December 14, 2020.
(b) Affected ADs
This AD replaces AD 99-01-19, Amendment 39-10987 (64 FR 1114,
January 8, 1999) (``AD 99-01-19''); and AD 2004-25-02, Amendment 39-
13889 (70 FR 1184, January 6, 2005) (``AD 2004-25-02'').
(c) Applicability
This AD applies to Airbus SAS Model A319-111, -112, -113, -114,
-115, -131, -132, and -133 airplanes; and Model A320-211, -212, -
214, -216, -231, -232, and -233 airplanes, certificated in any
category, as identified in European Union Aviation Safety Agency
(EASA) AD 2020-0040R1, dated June 16, 2020 (``EASA AD 2020-
0040R1'').
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report that, during full scale tests
to support the Model A320 structure extended service goal (ESG)
exercise, several cracks were found on both sides of the overwing
emergency exit door cut-outs at fuselage section 15. The FAA is
issuing this AD to address fatigue cracking of the fuselage, 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) Retained Initial Inspections, With No Changes
For Airbus SAS Model A320-111, -211, -212, and -231 series
airplanes on which Airbus Modification 21346 has not been done: This
paragraph restates the requirements of paragraph (f) of AD 2004-25-
02, with no changes. At the applicable time specified in paragraph
(g)(1) or (2) of this AD: Do a detailed inspection to find cracking
on the outboard flanges around the fastener holes of frames 38
through 41, between stringers 12 and 21, using Airbus Service
Bulletin A320-53-1032, Revision 02, dated December 5, 2001.
(1) For airplanes on which the inspection specified in Airbus
Service Bulletin A320-53-1032, Revision 01, dated January 15, 1998;
or Airbus Service Bulletin A320-53-1032, Revision 02, dated December
5, 2001; has been done as of February 10, 2005 (the effective date
of AD 2004-25-02): Do the next inspection within 4,900 flight cycles
after accomplishment of the last inspection, or within 1,100 flight
cycles after February 10, 2005, whichever is later.
(2) For airplanes on which no inspection specified in Airbus
Service Bulletin A320-53-1032, Revision 01, dated January 15, 1998;
or Airbus Service Bulletin A320-53-1032, Revision 02, dated December
5, 2001; has been done as of February 10, 2005 (the effective date
of AD 2004-25-02): Do the inspection at the earlier of the times
specified in paragraphs (g)(2)(i) and (ii) of this AD.
(i) Before the accumulation of 30,000 total flight cycles.
(ii) Before the accumulation of 24,800 total flight cycles, or
within 3,500 flight cycles after February 10, 2005 (the effective
date of AD 2004-25-02), whichever is later.
(h) Retained Repetitive Inspections if No Cracking is Found, With No
Changes
This paragraph restates the requirements of paragraph (g) of AD
2004-25-02, with no changes. If no crack is found during the
inspection required by paragraph (g)(1) or (2) of this AD: Repeat
the inspection thereafter at intervals not to exceed 4,900 flight
cycles.
(i) Retained Corrective Actions With New Repetitive Inspections and
Compliance Language
This paragraph restates the requirements of paragraph (h) of AD
2004-25-02, with new repetitive inspections and compliance language.
If any crack is found during any inspection required by paragraph
(g) of this AD, before further flight, repair using Airbus Service
Bulletin A320-53-1032, Revision 01, dated January 15, 1998; or
Airbus Service Bulletin A320-53-1032, Revision 02, dated December 5,
2001. Accomplishment of a repair using the service bulletin before
the effective date of this AD ends the repetitive inspection
requirements for the area repaired. As of the effective date of this
AD, the repair does not constitute terminating action for the
repetitive inspection. Thereafter, repeat the inspection at
intervals not to exceed 4,900 flight cycles. If any crack is found
during any inspection required by this AD, and the service bulletin
specifies to contact Airbus for appropriate action: Before further
flight, repair 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).
(j) Retained Optional Terminating Action With Changes to the Service
Information Compliance Language
This paragraph restates the optional terminating action
specified in paragraphs (i) and (j) of AD 2004-25-02, with changes
to the service information compliance language. Accomplishment of
Airbus Modification 21346 using Airbus Service Bulletin A320-53-
1031, Revision 02, dated December 5, 2001, constitutes terminating
action for the repetitive inspection requirements of paragraphs (h)
and (i) this AD.
(k) New Requirements
Except as specified in paragraph (l) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, EASA AD 2020-0040R1.
(l) Exceptions to EASA AD 2020-0040R1
(1) Where EASA AD 2020-0040R1 refers to its effective date, this
AD requires using the effective date of this AD.
(2) Where EASA AD 2020-0040R1 refers to ``13 March 2020 [the
effective date of the original issue of this AD],'' this AD requires
using the effective date of this AD.
(3) Where EASA AD 2020-0040R1 requires the accomplishment of
repetitive inspections and corrective actions as specified in
paragraphs (1) and (2) of the EASA AD, those actions are not
required by this AD as specified in the EASA AD. Those actions are
required by paragraphs (g), (h), and (i) of this AD.
(4) The ``Remarks'' section of EASA AD 2020-0040R1 does not
apply to this AD.
(m) Credit for Previous Actions
This paragraph provides credit for the optional terminating
action specified in paragraph (j) of this AD, if Airbus Modification
21346 was performed before the effective date of this AD using
Airbus Service Bulletin A320-53-1031, dated December 9, 1994.
(n) 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 (o)(1) 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 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 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
[[Page 71244]]
2020-0040R1 that contains RC procedures and tests: Except as
required by paragraph (n)(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.
(o) Related Information
(1) 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].
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (p)(6) and (7) of this AD.
(p) 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.
(3) The following service information was approved for IBR on
December 14, 2020.
(i) European Union Aviation Safety Agency (EASA) AD 2020-0040R1,
dated June 16, 2020.
(ii) Airbus Service Bulletin A320-53-1031, Revision 02, dated
December 5, 2001.
(4) The following service information was approved for IBR on
February 10, 2005 (70 FR 1184, January 6, 2005).
(i) Airbus Service Bulletin A320-53-1032, Revision 02, dated
December 5, 2001.
(ii) [Reserved]
(5) The following service information was also approved for IBR
on February 12, 1999 (64 FR 1114, January 8, 1999).
(i) Airbus Service Bulletin A320-53-1032, Revision 01, dated
January 15, 1998.
(ii) [Reserved]
(6) For EASA AD 2020-0040R1, 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. For Airbus
material, contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point
Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5
61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; internet https://www.airbus.com.
(7) 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-2020-0451.
(8) 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 October 15, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2020-24642 Filed 11-6-20; 8:45 am]
BILLING CODE 4910-13-P
