Rule2022-24310
Airworthiness Directives; Airbus SAS Airplanes
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
November 9, 2022
Effective
December 14, 2022
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is superseding Airworthiness Directive (AD) 2000-20- 15, which applied to certain Airbus SAS Model A300 and A300-600 series airplanes. AD 2000-20-15 required a high frequency eddy current (HFEC) inspection to detect cracking of the rear fittings of fuselage frame FR40 at stringer 27, and repetitive inspections or repair, as applicable. In lieu of accomplishing the repetitive inspections, AD 2000-20-15 provided a modification that would allow the inspection to be deferred for a certain period of time. This AD was prompted by cracking of the rear fittings of fuselage frame FR40 at stringer 27, and a determination that reduced compliance times are necessary. This AD removes airplanes from the applicability, and continues to require the actions in AD 2000-20-15, but at reduced compliance times, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 87 Issue 216 (Wednesday, November 9, 2022)</title>
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[Federal Register Volume 87, Number 216 (Wednesday, November 9, 2022)]
[Rules and Regulations]
[Pages 67545-67547]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2022-24310]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2022-0986; Project Identifier MCAI-2021-01440-T;
Amendment 39-22201; AD 2022-21-02]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2000-20-
15, which applied to certain Airbus SAS Model A300 and A300-600 series
airplanes. AD 2000-20-15 required a high frequency eddy current (HFEC)
inspection to detect cracking of the rear fittings of fuselage frame
FR40 at stringer 27, and repetitive inspections or repair, as
applicable. In lieu of accomplishing the repetitive inspections, AD
2000-20-15 provided a modification that would allow the inspection to
be deferred for a certain period of time. This AD was prompted by
cracking of the rear fittings of fuselage frame FR40 at stringer 27,
and a determination that reduced compliance times are necessary. This
AD removes airplanes from the applicability, and continues to require
the actions in AD 2000-20-15, but at reduced compliance times, as
specified in a European Union Aviation Safety Agency (EASA) AD, which
is incorporated by reference. The FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective December 14, 2022.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of December 14,
2022.
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2022-0986; 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.
Material Incorporated by Reference:
<bullet> For material incorporated by reference in this AD, contact
EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221
8999 000; email <a href="/cdn-cgi/l/email-protection#b3f2f7c0f3d6d2c0d29dd6c6c1dcc3d29dd6c6"><span class="__cf_email__" data-cfemail="7534310635101406145b1000071a05145b1000">[email protected]</span></a>; website easa.europa.eu. You may
find this IBR material on the EASA website at ad.easa.europa.eu.
<bullet> 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. It is also available in the AD docket at
<a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2022-0986.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, Large
[[Page 67546]]
Aircraft Section, FAA, International Validation Branch, 2200 South
216th St., Des Moines, WA 98198; telephone and fax 206-231-3225; email
<a href="/cdn-cgi/l/email-protection#4c282d22623e232825222d0c2a2d2d622b233a"><span class="__cf_email__" data-cfemail="f7939699d98598939e9996b7919696d9909881">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2000-20-15, Amendment 39-11926 (65 FR
60349, October 11, 2000) (AD 2000-20-15). AD 2000-20-15 applied to
certain Airbus SAS Model A300 and A300-600 series airplanes. AD 2000-
20-15 required a HFEC inspection to detect cracking of the rear
fittings of fuselage frame FR40 at stringer 27, and repetitive
inspections or repair, as applicable. In lieu of accomplishing the
repetitive inspections, AD 2000-20-15 provides a modification that
would allow the inspection to be deferred for a certain period of time.
The FAA issued AD 2000-20-15 to address fatigue cracking of the rear
fittings of fuselage frame FR40 at stringer 27, which could result in
reduced structural integrity of the airplane.
The NPRM published in the Federal Register on August 2, 2022 (87 FR
47144). The NPRM was prompted by EASA AD 2021-0288, dated December 21,
2021, issued by the European Union Aviation Safety Agency (referred to
after this as the MCAI). The MCAI states that cracking of the rear
fittings of fuselage frame FR40 at stringer 27 was found, and a
determination made that reduced compliance times are necessary.
You may examine the MCAI in the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2022-0986.
In the NPRM, the FAA proposed to continue to require the actions in
AD 2000-20-15, but at reduced compliance times, as specified in EASA AD
2021-0288, dated December 21, 2021. The NPRM also proposed to remove
airplanes from the applicability, as specified in EASA AD 2021-0288.
The FAA is issuing this AD to address the unsafe condition on these
products.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from the Air Line Pilots Association,
International (ALPA), and FedEx Express, who supported the NPRM without
change.
Conclusion
This product has been approved by the aviation authority of another
country and is approved for operation in the United States. Pursuant to
the FAA's bilateral agreement with this State of Design Authority, it
has notified the FAA of the unsafe condition described in the MCAI
referenced above. The FAA reviewed the relevant data, considered the
comment[s] received, and determined that air safety requires adopting
this AD as proposed. Accordingly, the FAA is issuing this AD to address
the unsafe condition on this product. Except for minor editorial
changes, this AD is adopted as proposed in the NPRM. None of the
changes will increase the economic burden on any operator.
Related Service Information Under 1 CFR Part 51
EASA AD 2021-0288 specifies procedures for repetitive inspections
of the rear fittings of fuselage frame FR40 at stringer 27 for
cracking, and repair of any cracking. 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 67 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
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Cost per
Action Labor cost Parts cost product Cost on U.S. operators
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Inspection.................... 6 work-hours x $85 per $0 $510 $34,170, per inspection
hour = $510. cycle.
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The FAA estimates the following costs to do any necessary repair
based on the results of any required inspection. The FAA has no way of
determining the number of aircraft that might need this repair:
Estimated Costs of On-Condition Actions
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Cost per
Labor cost Parts cost product
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31 work-hours x $85 per hour = $2,635. $132 $2,767
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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 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
[[Page 67547]]
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by:
0
a. Removing Airworthiness Directive AD 2000-20-15, Amendment 39-11926
(65 FR 60349, October 11, 2000) (AD 2000-20-15); and
0
b. Adding the following new airworthiness directive:
2022-21-02 Airbus SAS: Amendment 39-22201; Docket No. FAA-2022-0986;
Project Identifier MCAI-2021-01440-T.
(a) Effective Date
This airworthiness directive (AD) is effective December 14,
2022.
(b) Affected ADs
This AD replaces AD 2000-20-15, Amendment 39-11926 (65 FR 60349,
October 11, 2000) (AD 2000-20-15).
(c) Applicability
This AD applies to Airbus SAS airplanes identified in paragraphs
(c)(1) through (4) of this AD, certificated in any category, as
specified in European Union Aviation Safety Agency (EASA) AD 2021-
0288, dated December 21, 2021 (EASA AD 2021-0288).
(1) Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203
airplanes.
(2) Model A300 B4-603 and B4-622 airplanes.
(3) Model A300 B4-605R and B4-622R airplanes.
(4) Model A300 F4-605R airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by cracking of the rear fittings of
fuselage frame FR40 at stringer 27, and a determination that reduced
compliance times are necessary. The FAA is issuing this AD to
address fatigue cracking of the rear fittings of fuselage frame FR40
at stringer 27, which could result in reduced structural integrity
of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraphs (h) and (i) of this AD: Comply
with all required actions and compliance times specified in, and in
accordance with, EASA AD 2021-0288.
(h) Exceptions to EASA AD 2021-0288
(1) Where paragraph (1) of EASA AD 2021-0288 specifies, for
certain conditions, using the compliance time and repetitive
intervals ``in the applicable SB,'' and where ``the applicable SB''
specifies that the ``1st inspection will be done within [a specified
number of flight cycles] after receipt of the Service Bulletin,''
this AD requires compliance within the specified number of flight
cycles after the effective date of this AD.
(2) Where EASA AD 2021-0288 refers to its effective date, this
AD requires using the effective date of this AD.
(3) The ``Remarks'' section of EASA AD 2021-0288 does not apply
to this AD.
(i) No Reporting Requirement
Although the service information referenced in EASA AD 2021-0288
specifies to submit certain information to the manufacturer, this AD
does not include that requirement.
(j) Additional 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: <a href="/cdn-cgi/l/email-protection#fac3d7bbaca9d7bbb3a8d7cdc9cad7bbb7b5b9ba9c9b9bd49d958c"><span class="__cf_email__" data-cfemail="96afbbd7c0c5bbd7dfc4bba1a5a6bbd7dbd9d5d6f0f7f7b8f1f9e0">[email protected]</span></a>.
(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.
(k) Additional Information
For more information about this AD, contact Dan Rodina,
Aerospace Engineer, Large Aircraft Section, FAA, International
Validation Branch, 2200 South 216th St., Des Moines, WA 98198;
telephone and fax 206-231-3225; email <a href="/cdn-cgi/l/email-protection#c7a3a6a9e9b5a8a3aea9a687a1a6a6e9a0a8b1"><span class="__cf_email__" data-cfemail="5c383d32722e333835323d1c3a3d3d723b332a">[email protected]</span></a>.
(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.
(3) The following service information was approved for IBR on
December 14, 2022.
(i) European Union Aviation Safety Agency (EASA) AD 2021-0288,
dated December 21, 2021.
(ii) [Reserved]
(4) For EASA AD 2021-0288, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49 221 8999 000; email
<a href="/cdn-cgi/l/email-protection#58191c2b183d392b39763d2d2a372839763d2d"><span class="__cf_email__" data-cfemail="9bdadfe8dbfefae8fab5feeee9f4ebfab5feee">[email protected]</span></a>; website easa.europa.eu. You may find this EASA
AD on the EASA website at ad.easa.europa.eu.
(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.
(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
<a href="/cdn-cgi/l/email-protection#1e786c3077706d6e7b7d6a7771705e707f6c7f30797168"><span class="__cf_email__" data-cfemail="b8deca96d1d6cbc8dddbccd1d7d6f8d6d9cad996dfd7ce">[email protected]</span></a>, or go to: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">www.archives.gov/federal-register/cfr/ibr-locations.html</a>.
Issued on September 28, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2022-24310 Filed 11-8-22; 8:45 am]
BILLING CODE 4910-13-P
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