Airworthiness Directives; Airbus SAS Airplanes, 31097-31100 [2021-12172]
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Federal Register / Vol. 86, No. 111 / Friday, June 11, 2021 / Rules and Regulations
(5) Model A340–541 airplanes.
(6) Model A340–642 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 25, Equipment/furnishings.
(e) Reason
This AD was prompted by reports that, for
certain lower deck mobile crew rest (LDMCR)
units, the connection of a certain halon outlet
tube to the outlet of a certain fire
extinguisher bottle may be incorrect. The
FAA is issuing this AD to address this
condition, which, in case of a fire inside the
LDMCR, could lead to disconnection of the
tube, possibly resulting in reduced
concentration of fire suppressing agent at any
location inside the LDMCR.
(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 2020–0255.
(h) Exceptions to EASA AD 2020–0255
(1) Where EASA AD 2020–0255 refers to its
effective date, this AD requires using the
effective date of this AD.
(2) The ‘‘Remarks’’ section of EASA AD
2020–0255 does not apply to this AD.
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(i) No Reporting Requirement
Although the service information
referenced in EASA AD 2020–0255 specifies
to submit certain information to the
manufacturer, this AD does not include that
requirement.
(j) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Large Aircraft
Section, International Validation Branch,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. In accordance with
14 CFR 39.19, send your request to your
principal inspector or responsible Flight
Standards Office, as appropriate. If sending
information directly to the Large Aircraft
Section, International Validation Branch,
send it to the attention of the person
identified in paragraph (k) of this AD.
Information may be emailed to: 9–AVS–AIR–
730–AMOC@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the responsible
Flight Standards Office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, Large Aircraft Section,
International Validation Branch, FAA; or
EASA; or Airbus SAS’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
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(3) Required for Compliance (RC): Except
as required by paragraph (j)(2) of this AD, if
any service information contains procedures
or tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(k) Related Information
For more information about this AD,
contact Vladimir Ulyanov, Aerospace
Engineer, Large Aircraft Section,
International Validation Branch, FAA, 2200
South 216th St., Des Moines, WA 98198;
telephone and fax 206–231–3229; email
vladimir.ulyanov@faa.gov.
(l) 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 2020–0255, dated November 13,
2020.
(ii) [Reserved]
(3) For EASA AD 2020–0255, contact
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221 8999
000; email ADs@easa.europa.eu; internet
www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://
ad.easa.europa.eu.
(4) You may view this material at the FAA,
Airworthiness Products Section, Operational
Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195. 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–2021–0140.
(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 May 20, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–12175 Filed 6–10–21; 8:45 am]
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31097
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–1113; Project
Identifier MCAI–2020–00893–T; Amendment
39–21580; AD 2021–11–18]
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) 2019–03–
10, which applied to all Airbus SAS
Model A300 series airplanes; and Model
A300 B4–600, B4–600R, and F4–600R
series airplanes, and Model A300 C4–
605R Variant F airplanes (collectively
called Model A300–600 series
airplanes). AD 2019–03–10 required
repetitive detailed visual inspections of
the main landing gear (MLG) leg
components and replacement of the
MLG leg if cracked components are
found. This AD continues to require the
actions required by AD 2019–03–10. For
certain airplanes, this AD also requires
modification of the MLG hinge arm by
installing improved MLG hinge arm/
barrel pins; an out-of-roundness check
of removed pins; repetitive inspections
of any affected pins and the associated
connecting rod bushes, and replacement
of the MLG leg if cracked components
are found; and installation of an
improved spacer; as specified in a
European Union Aviation Safety Agency
(EASA) AD, which is incorporated by
reference. This AD was prompted by
reports of cracks in MLG leg
components and a determination that
additional actions (including
inspections, modifications, and checks)
are needed to address the unsafe
condition. The FAA is issuing this AD
to address the unsafe condition on these
products.
DATES: This AD is effective July 16,
2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 16, 2021.
ADDRESSES: For EASA material
incorporated by reference (IBR) in this
AD, contact 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
SUMMARY:
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IBR material on the EASA website at
https://ad.easa.europa.eu.
For Safran material that will be IBR in
this AD, contact Safran Landing
Systems, One Carbon Way, Walton, KY
41094; telephone 859–525–8583; fax
859–485–8827; internet https://
www.safran-landing-systems.com.
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–
1113.
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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–
1113; 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: Dan
Rodina, Aerospace Engineer, Large
Aircraft Section, International
Validation Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3225; email
dan.rodina@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
EASA, which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2020–0145,
dated July 1, 2020 (EASA AD 2020–
0145) (also referred to as the Mandatory
Continuing Airworthiness Information,
or the MCAI), to correct an unsafe
condition for all Airbus SAS Model
A300 series airplanes; Model A300–600
series airplanes; and Model A300F4–
608ST airplanes. EASA AD 2020–0145
supersedes EASA AD 2018–0170, dated
August 6, 2018 (which corresponds to
FAA AD 2019–03–10, Amendment 39–
19562 (84 FR 5595, February 22, 2019)
(AD 2019–03–10)). Model A300F4–
608ST airplanes are not certificated 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.
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
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part 39 to supersede AD 2019–03–10.
AD 2019–03–10 applied to all Airbus
SAS Model A300 and A300–600 series
airplanes. The NPRM published in the
Federal Register on December 8, 2020
(85 FR 78971). The NPRM was
prompted by reports of cracks in MLG
leg components, and a determination
that additional actions (including
inspections, modifications, and out-ofroundness checks) are needed to
address the unsafe condition. The
NPRM proposed to continue to require
the actions required by AD 2019–03–10.
For certain airplanes, this AD also
requires modification of the MLG hinge
arm by installing improved MLG hinge
arm/barrel pins; an out-of-roundness
check of removed pins; repetitive
inspections of any affected pins and the
associated connecting rod bushes, and
replacement of the MLG leg if cracked
components are found; and installation
of an improved spacer; as specified in
an EASA AD.
The FAA is issuing this AD to address
cracking of certain components in the
MLG leg, which could result in an MLG
collapse, and consequent damage to the
airplane and injury to the airplane
occupants. 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.
Support for the NPRM
The Air Line Pilots Association,
International (ALPA) and an anonymous
commenter indicated support for the
NPRM.
Request To Clarify Inspection
Threshold for Certain Airplanes
United Parcel Service (UPS Airlines)
asked that the proposed AD be revised
to add a statement to clarify that the
general visual inspection (GVI) for
Group 2 airplanes begins within 30
months after the effective date of the
FAA AD. UPS Airlines stated that it has
been accomplishing Airbus Service
Bulletin A300–32–6120 at gear
overhaul, which replaces the old hinge
arm barrel pin with a new hinge arm
barrel pin, prior to release of Airbus
Service Bulletin A300–32–6121. UPS
Airlines further pointed out that Airbus
Service Bulletin A300–32–6121 was
released after Airbus Service Bulletin
A300–32–6120 (pin replacement), and
added installation of a new spacer
during gear overhaul. UPS Airlines
added that EASA AD 2020–0145 does
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not have clear instructions for the initial
inspection start date for airplanes with
modifications accomplished using
Airbus Service Bulletin A300–32–6120
that have not accomplished Airbus
Service Bulletin A300–32–6121.
Further, UPS Airlines asserted that this
request is in line with the 30-month pin
replacement threshold for airplanes
equipped with the older pin. Airplanes
with the newer pins installed in the past
three years without the spacer
installation, UPS Airlines also asserted,
are less prone to any safety or
operational concerns than those with
the older pins.
The FAA does not agree with the
commenter’s request. In developing an
appropriate compliance time for this
AD, the FAA considered the urgency
associated with the subject unsafe
condition as well as the
recommendations of the manufacturer.
The compliance time for the initial GVI
for Group 2 airplanes is ‘‘Within 30
months after pin replacement,’’ as
specified in EASA AD 2020–0145.
Airbus Service Bulletin A300–32–6120,
which provides instructions for pin
replacement, was issued September 24,
2019. Therefore, the earliest possible
compliance time for the inspection
would be 30 months from September 24,
2019. The FAA has not changed this AD
in this regard.
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 as proposed, except for minor
editorial changes. The FAA has
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
EASA AD 2020–0145 describes
procedures for repetitive detailed visual
inspections of the MLG leg components
and replacement of the MLG leg if
cracked components are found. EASA
AD 2020–0145 also describes
procedures, for certain airplanes, for
modification of the MLG hinge arm by
installing improved pins, which would
terminate the repetitive detailed
inspections required by AD 2019–03–
10; an out-of-roundness check of
removed pins; repetitive inspections of
affected pins and the associated
connecting rod bushes for cracking, and
replacement of the MLG leg if cracked
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components are found; and installation
of an improved spacer, which would
terminate the repetitive pin and rod
bushes inspections. EASA AD 2020–
0145 also describes procedures for
reporting results of the out-of-roundness
check to Safran.
Safran Landing Systems has issued
Safran Service Bulletin 470–32–840,
dated December 3, 2019. This service
information describes procedures for
inspecting the hinge arm pins of the
MLG barrel to detect local out-ofroundness.
This material is reasonably available
because the interested parties have
access to it through their normal course
31099
of business or by the means identified
in the ADDRESSES section.
Costs of Compliance
The FAA estimates that this AD
affects 128 airplanes of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS *
Action
Labor cost
Parts cost
Retained actions from
AD 2019–03–10.
New modifications .........
New inspection ..............
New out-of-roundness
check.
1 work-hour × $85 per hour = $85, per inspection cycle.
180 work-hours × $85 per hour = $15,300 ........
1 work-hour × $85 per hour = $85 .....................
4 work-hours × $85 per hour = $340 .................
$0
17,993
0
0
Cost per product
Cost on U.S. operators
$85, per inspection
cycle.
33,293 ..........................
85 .................................
340 ...............................
$10,880, per inspection
cycle.
4,261,504.
10,880.
43,520.
* Table does not include estimated costs for reporting.
The FAA estimates that it would take
about 1 work-hour per product to
comply with the reporting requirement
in this AD. The average labor rate is $85
per hour. Based on these figures, the
FAA estimates the cost of reporting the
inspection results on U.S. operators to
be $85, or $85 per product.
ESTIMATED COSTS OF ON-CONDITION ACTIONS
Labor cost
Parts cost
Cost per product
20 work-hours × $85 per hour = $1,700 per MLG ...............................................
$3,400,000 per MLG .............................
$3,401,700 per MLG.
Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork
Reduction Act unless that collection of
information displays a current valid
OMB control number. The control
number for the collection of information
required by this AD is 2120–0056. The
paperwork cost associated with this AD
has been detailed in the Costs of
Compliance section of this document
and includes time for reviewing
instructions, as well as completing and
reviewing the collection of information.
Therefore, all reporting associated with
this AD is mandatory. Comments
concerning the accuracy of this burden
and suggestions for reducing the burden
should be directed to the Information
Collection Clearance Officer, Federal
Aviation Administration, 10101
Hillwood Parkway, Fort Worth, TX
76177–1524.
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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
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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.
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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,
■
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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:
a. Removing Airworthiness Directive
(AD) 2019–03–10, Amendment 39–
19562 (84 FR 5595, February 22, 2019);
and
■ b. Adding the following new AD:
■
■
2021–11–18 Airbus SAS: Amendment 39–
21580; Docket No. FAA–2020–1113;
Project Identifier MCAI–2020–00893–T.
(a) Effective Date
This airworthiness directive (AD) is
effective July 16, 2021.
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(b) Affected ADs
This AD replaces AD 2019–03–10,
Amendment 39–19562 (84 FR 5595, February
22, 2019) (AD 2019–03–10).
(ii) If the inspection was done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
(c) Applicability
This AD applies to all Airbus SAS
airplanes, certificated in any category,
identified in paragraphs (c)(1) through (5) of
this AD.
(1) Model A300 B2–1A, B2–1C, B2K–3C,
B2–203, B4–2C, B4–103, and B4–203
airplanes.
(2) Model A300 B4–601, B4–603, B4–620,
and B4–622 airplanes.
(3) Model A300 B4–605R and B4–622R
airplanes.
(4) Model A300 F4–605R and F4–622R
airplanes.
(5) Model A300 C4–605R Variant F
airplanes.
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Large Aircraft
Section, International Validation Branch,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. In accordance with
14 CFR 39.19, send your request to your
principal inspector or responsible Flight
Standards Office, as appropriate. If sending
information directly to the Large Aircraft
Section, International Validation Branch,
send it to the attention of the person
identified in paragraph (j) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the responsible
Flight Standards Office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, Large Aircraft Section,
International Validation Branch, FAA; or
EASA; or Airbus SAS’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(3) Required for Compliance (RC): Except
as required by paragraph (i)(2) of this AD, if
any service information referenced in EASA
AD 2020–0145 that contains RC procedures
or tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(4) Paperwork Reduction Act Burden
Statement: A federal agency may not conduct
or sponsor, and a person is not required to
respond to, nor shall a person be subject to
a penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork Reduction
Act unless that collection of information
displays a current valid OMB Control
Number. The OMB Control Number for this
information collection is 2120–0056. Public
reporting for this collection of information is
estimated to be approximately 1 hour per
response, including the time for reviewing
instructions, searching existing data sources,
gathering and maintaining the data needed,
and completing and reviewing the collection
of information. All responses to this
collection of information are mandatory as
required by this AD. Send comments
regarding this burden estimate or any other
(d) Subject
Air Transport Association (ATA) of
America Code 32, Landing Gear.
(e) Reason
This AD was prompted by reports of cracks
in main landing gear (MLG) leg components,
and a determination that additional actions
(including inspections, modifications, and
out-of-roundness checks) are needed to
address the unsafe condition. The FAA is
issuing this AD to address cracking of certain
components in the MLG leg, which could
result in an MLG collapse, and consequent
damage to the airplane and injury to the
airplane occupants.
(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 2020–0145, dated
July 1, 2020 (EASA AD 2020–0145).
(h) Exceptions to EASA AD 2020–0145
(1) Where EASA AD 2020–0145 refers to its
effective date, this AD requires using the
effective date of this AD.
(2) Where EASA AD 2020–0145 refers to
the effective date of EASA AD 2018–0170,
this AD requires using March 29, 2019 (the
effective date of AD 2019–03–10).
(3) The ‘‘Remarks’’ section of EASA AD
2020–0145 does not apply to this AD.
(4) Paragraph (3) of EASA AD 2020–0145
specifies to ‘‘send all removed pins for an
out-of-roundness check.’’ For this AD, do an
inspection of each pin for out-of-roundness,
in accordance with Safran Service Bulletin
470–32–840, dated December 3, 2019.
(5) Paragraph (3) of EASA AD 2020–0145
specifies to report inspection results to
Safran within a certain compliance time. For
this AD, report inspection results at the
applicable time specified in paragraph
(h)(5)(i) or (ii) of this AD.
(i) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the inspection.
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aspect of this collection of information,
including suggestions for reducing this
burden to Information Collection Clearance
Officer, Federal Aviation Administration,
10101 Hillwood Parkway, Fort Worth, TX
76177–1524.
(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; telephone and
fax 206–231–3225; email dan.rodina@
faa.gov.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) European Union Aviation Safety Agency
(EASA) AD 2020–0145, dated July 1, 2020.
(ii) Safran Service Bulletin 470–32–840,
dated December 3, 2019.
(3) For EASA AD 2020–0145, contact
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221 8999
000; email ADs@easa.europa.eu; internet
www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://
ad.easa.europa.eu.
(4) For Safran service information, contact
Safran Landing Systems, One Carbon Way,
Walton, KY 41094; telephone 859–525–8583;
fax 859–485–8827; internet https://
www.safran-landing-systems.com.
(5) 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–2020–1113.
(6) 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 May 20, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–12172 Filed 6–10–21; 8:45 am]
BILLING CODE 4910–13–P
E:\FR\FM\11JNR1.SGM
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]]>Agencies
[Federal Register Volume 86, Number 111 (Friday, June 11, 2021)]
[Rules and Regulations]
[Pages 31097-31100]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-12172]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-1113; Project Identifier MCAI-2020-00893-T;
Amendment 39-21580; AD 2021-11-18]
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) 2019-03-
10, which applied to all Airbus SAS Model A300 series airplanes; and
Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model
A300 C4-605R Variant F airplanes (collectively called Model A300-600
series airplanes). AD 2019-03-10 required repetitive detailed visual
inspections of the main landing gear (MLG) leg components and
replacement of the MLG leg if cracked components are found. This AD
continues to require the actions required by AD 2019-03-10. For certain
airplanes, this AD also requires modification of the MLG hinge arm by
installing improved MLG hinge arm/barrel pins; an out-of-roundness
check of removed pins; repetitive inspections of any affected pins and
the associated connecting rod bushes, and replacement of the MLG leg if
cracked components are found; and installation of an improved spacer;
as specified in a European Union Aviation Safety Agency (EASA) AD,
which is incorporated by reference. This AD was prompted by reports of
cracks in MLG leg components and a determination that additional
actions (including inspections, modifications, and checks) are needed
to address the unsafe condition. The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective July 16, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of July 16,
2021.
ADDRESSES: For EASA material incorporated by reference (IBR) in this
AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany;
telephone +49 221 8999 000; email [email protected]; internet
www.easa.europa.eu. You may find this
[[Page 31098]]
IBR material on the EASA website at https://ad.easa.europa.eu.
For Safran material that will be IBR in this AD, contact Safran
Landing Systems, One Carbon Way, Walton, KY 41094; telephone 859-525-
8583; fax 859-485-8827; internet https://www.safran-landing-systems.com.
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-2020-1113.
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-
1113; 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: Dan Rodina, Aerospace Engineer, Large
Aircraft Section, International Validation Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax 206-231-3225; email
[email protected].
SUPPLEMENTARY INFORMATION:
Background
EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2020-0145, dated July 1, 2020 (EASA
AD 2020-0145) (also referred to as the Mandatory Continuing
Airworthiness Information, or the MCAI), to correct an unsafe condition
for all Airbus SAS Model A300 series airplanes; Model A300-600 series
airplanes; and Model A300F4-608ST airplanes. EASA AD 2020-0145
supersedes EASA AD 2018-0170, dated August 6, 2018 (which corresponds
to FAA AD 2019-03-10, Amendment 39-19562 (84 FR 5595, February 22,
2019) (AD 2019-03-10)). Model A300F4-608ST airplanes are not
certificated 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.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2019-03-10. AD 2019-03-10 applied to all
Airbus SAS Model A300 and A300-600 series airplanes. The NPRM published
in the Federal Register on December 8, 2020 (85 FR 78971). The NPRM was
prompted by reports of cracks in MLG leg components, and a
determination that additional actions (including inspections,
modifications, and out-of-roundness checks) are needed to address the
unsafe condition. The NPRM proposed to continue to require the actions
required by AD 2019-03-10. For certain airplanes, this AD also requires
modification of the MLG hinge arm by installing improved MLG hinge arm/
barrel pins; an out-of-roundness check of removed pins; repetitive
inspections of any affected pins and the associated connecting rod
bushes, and replacement of the MLG leg if cracked components are found;
and installation of an improved spacer; as specified in an EASA AD.
The FAA is issuing this AD to address cracking of certain
components in the MLG leg, which could result in an MLG collapse, and
consequent damage to the airplane and injury to the airplane occupants.
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.
Support for the NPRM
The Air Line Pilots Association, International (ALPA) and an
anonymous commenter indicated support for the NPRM.
Request To Clarify Inspection Threshold for Certain Airplanes
United Parcel Service (UPS Airlines) asked that the proposed AD be
revised to add a statement to clarify that the general visual
inspection (GVI) for Group 2 airplanes begins within 30 months after
the effective date of the FAA AD. UPS Airlines stated that it has been
accomplishing Airbus Service Bulletin A300-32-6120 at gear overhaul,
which replaces the old hinge arm barrel pin with a new hinge arm barrel
pin, prior to release of Airbus Service Bulletin A300-32-6121. UPS
Airlines further pointed out that Airbus Service Bulletin A300-32-6121
was released after Airbus Service Bulletin A300-32-6120 (pin
replacement), and added installation of a new spacer during gear
overhaul. UPS Airlines added that EASA AD 2020-0145 does not have clear
instructions for the initial inspection start date for airplanes with
modifications accomplished using Airbus Service Bulletin A300-32-6120
that have not accomplished Airbus Service Bulletin A300-32-6121.
Further, UPS Airlines asserted that this request is in line with the
30-month pin replacement threshold for airplanes equipped with the
older pin. Airplanes with the newer pins installed in the past three
years without the spacer installation, UPS Airlines also asserted, are
less prone to any safety or operational concerns than those with the
older pins.
The FAA does not agree with the commenter's request. In developing
an appropriate compliance time for this AD, the FAA considered the
urgency associated with the subject unsafe condition as well as the
recommendations of the manufacturer. The compliance time for the
initial GVI for Group 2 airplanes is ``Within 30 months after pin
replacement,'' as specified in EASA AD 2020-0145. Airbus Service
Bulletin A300-32-6120, which provides instructions for pin replacement,
was issued September 24, 2019. Therefore, the earliest possible
compliance time for the inspection would be 30 months from September
24, 2019. The FAA has not changed this AD in this regard.
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 as proposed, except for minor
editorial changes. The FAA has determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
EASA AD 2020-0145 describes procedures for repetitive detailed
visual inspections of the MLG leg components and replacement of the MLG
leg if cracked components are found. EASA AD 2020-0145 also describes
procedures, for certain airplanes, for modification of the MLG hinge
arm by installing improved pins, which would terminate the repetitive
detailed inspections required by AD 2019-03-10; an out-of-roundness
check of removed pins; repetitive inspections of affected pins and the
associated connecting rod bushes for cracking, and replacement of the
MLG leg if cracked
[[Page 31099]]
components are found; and installation of an improved spacer, which
would terminate the repetitive pin and rod bushes inspections. EASA AD
2020-0145 also describes procedures for reporting results of the out-
of-roundness check to Safran.
Safran Landing Systems has issued Safran Service Bulletin 470-32-
840, dated December 3, 2019. This service information describes
procedures for inspecting the hinge arm pins of the MLG barrel to
detect local out-of-roundness.
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 128 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 2019- 1 work-hour x $85 per $0 $85, per $10,880, per
03-10. hour = $85, per inspection cycle. inspection cycle.
inspection cycle.
New modifications.............. 180 work-hours x $85 17,993 33,293............ 4,261,504.
per hour = $15,300.
New inspection................. 1 work-hour x $85 per 0 85................ 10,880.
hour = $85.
New out-of-roundness check..... 4 work-hours x $85 per 0 340............... 43,520.
hour = $340.
----------------------------------------------------------------------------------------------------------------
* Table does not include estimated costs for reporting.
The FAA estimates that it would take about 1 work-hour per product
to comply with the reporting requirement in this AD. The average labor
rate is $85 per hour. Based on these figures, the FAA estimates the
cost of reporting the inspection results on U.S. operators to be $85,
or $85 per product.
Estimated Costs of On-Condition Actions
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
20 work-hours x $85 per hour = $1,700 per $3,400,000 per MLG.......... $3,401,700 per MLG.
MLG.
----------------------------------------------------------------------------------------------------------------
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the
Information Collection Clearance Officer, Federal Aviation
Administration, 10101 Hillwood Parkway, Fort Worth, TX 76177-1524.
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:
0
a. Removing Airworthiness Directive (AD) 2019-03-10, Amendment 39-19562
(84 FR 5595, February 22, 2019); and
0
b. Adding the following new AD:
2021-11-18 Airbus SAS: Amendment 39-21580; Docket No. FAA-2020-1113;
Project Identifier MCAI-2020-00893-T.
(a) Effective Date
This airworthiness directive (AD) is effective July 16, 2021.
[[Page 31100]]
(b) Affected ADs
This AD replaces AD 2019-03-10, Amendment 39-19562 (84 FR 5595,
February 22, 2019) (AD 2019-03-10).
(c) Applicability
This AD applies to all Airbus SAS airplanes, certificated in any
category, identified in paragraphs (c)(1) through (5) of this AD.
(1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and
B4-203 airplanes.
(2) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
(3) Model A300 B4-605R and B4-622R airplanes.
(4) Model A300 F4-605R and F4-622R airplanes.
(5) Model A300 C4-605R Variant F airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
Gear.
(e) Reason
This AD was prompted by reports of cracks in main landing gear
(MLG) leg components, and a determination that additional actions
(including inspections, modifications, and out-of-roundness checks)
are needed to address the unsafe condition. The FAA is issuing this
AD to address cracking of certain components in the MLG leg, which
could result in an MLG collapse, and consequent damage to the
airplane and injury to the airplane occupants.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, European Union Aviation Safety Agency (EASA) AD
2020-0145, dated July 1, 2020 (EASA AD 2020-0145).
(h) Exceptions to EASA AD 2020-0145
(1) Where EASA AD 2020-0145 refers to its effective date, this
AD requires using the effective date of this AD.
(2) Where EASA AD 2020-0145 refers to the effective date of EASA
AD 2018-0170, this AD requires using March 29, 2019 (the effective
date of AD 2019-03-10).
(3) The ``Remarks'' section of EASA AD 2020-0145 does not apply
to this AD.
(4) Paragraph (3) of EASA AD 2020-0145 specifies to ``send all
removed pins for an out-of-roundness check.'' For this AD, do an
inspection of each pin for out-of-roundness, in accordance with
Safran Service Bulletin 470-32-840, dated December 3, 2019.
(5) Paragraph (3) of EASA AD 2020-0145 specifies to report
inspection results to Safran within a certain compliance time. For
this AD, report inspection results at the applicable time specified
in paragraph (h)(5)(i) or (ii) of this AD.
(i) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(ii) If the inspection was done before the effective date of
this AD: Submit the report within 30 days after the effective date
of this AD.
(i) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Large Aircraft Section, International Validation Branch, FAA, has
the authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or responsible Flight
Standards Office, as appropriate. If sending information directly to
the Large Aircraft Section, International Validation Branch, send it
to the attention of the person identified in paragraph (j) of this
AD. Information may be emailed to: [email protected].
Before using any approved AMOC, notify your appropriate principal
inspector, or lacking a principal inspector, the manager of the
responsible Flight Standards Office.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain instructions from a manufacturer, the instructions must be
accomplished using a method approved by the Manager, Large Aircraft
Section, International Validation Branch, FAA; or EASA; or Airbus
SAS's EASA Design Organization Approval (DOA). If approved by the
DOA, the approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraph (i)(2) of this AD, if any service information referenced
in EASA AD 2020-0145 that contains RC procedures or tests that are
identified as RC, those procedures and tests must be done to comply
with this AD; any procedures or tests that are not identified as RC
are recommended. Those procedures and tests that are not identified
as RC may be deviated from using accepted methods in accordance with
the operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.
(4) Paperwork Reduction Act Burden Statement: A federal agency
may not conduct or sponsor, and a person is not required to respond
to, nor shall a person be subject to a penalty for failure to comply
with a collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 1
hour per response, including the time for reviewing instructions,
searching existing data sources, gathering and maintaining the data
needed, and completing and reviewing the collection of information.
All responses to this collection of information are mandatory as
required by this AD. Send comments regarding this burden estimate or
any other aspect of this collection of information, including
suggestions for reducing this burden to Information Collection
Clearance Officer, Federal Aviation Administration, 10101 Hillwood
Parkway, Fort Worth, TX 76177-1524.
(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; telephone
and fax 206-231-3225; email [email protected].
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) European Union Aviation Safety Agency (EASA) AD 2020-0145,
dated July 1, 2020.
(ii) Safran Service Bulletin 470-32-840, dated December 3, 2019.
(3) For EASA AD 2020-0145, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49 221 8999 000; email
[email protected]; internet www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://ad.easa.europa.eu.
(4) For Safran service information, contact Safran Landing
Systems, One Carbon Way, Walton, KY 41094; telephone 859-525-8583;
fax 859-485-8827; internet https://www.safran-landing-systems.com.
(5) 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-2020-1113.
(6) 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 May 20, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-12172 Filed 6-10-21; 8:45 am]
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