Document ID: FAA-2022-0986-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus SAS Airplanes
Posted Date: 2022-08-02T04:00Z

[Federal Register Volume 87, Number 147 (Tuesday, August 2, 2022)]
[Proposed Rules]
[Pages 47144-47146]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-16451]

[[Page 47144]]

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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]
RIN 2120-AA64

Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2000-20-15, which applies to certain Airbus SAS Model A300 and A300-600 
series airplanes. AD 2000-20-15 requires 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 provides 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 
proposed AD would continue 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 proposed for incorporation by 
reference. This proposed AD would also remove airplanes from the 
applicability. The FAA is proposing this AD to address the unsafe 
condition on these products.

DATES: The FAA must receive comments on this proposed AD by September 
16, 2022.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to www.regulations.gov. 
Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For material that will be 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 material on the EASA website at 
https://ad.easa.europa.eu. 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 www.regulations.gov by searching for and locating Docket No. 
FAA-2022-0986.

Examining the AD Docket

    You may examine the AD docket at www.regulations.gov by searching 
for and locating 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 NPRM, the mandatory 
continuing airworthiness information (MCAI), any comments received, and 
other information. The street address for Docket Operations is listed 
above.

FOR FURTHER INFORMATION 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 
[email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2022-0986; Project Identifier 
MCAI-2021-01440-T'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may amend 
this proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
www.regulations.gov, including any personal information you provide. 
The agency will also post a report summarizing each substantive verbal 
contact received about this NPRM.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this NPRM contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this NPRM, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this NPRM. Submissions containing CBI should be sent to 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 [email protected]. Any 
commentary that the FAA receives which is not specifically designated 
as CBI will be placed in the public docket for this rulemaking.

Background

    The FAA issued AD 2000-20-15, Amendment 39-11926 (65 FR 60349, 
October 11, 2000) (AD 2000-20-15), for certain Airbus SAS Model A300 
and A300-600 series airplanes. AD 2000-20-15 requires 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 specifies 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.

Actions Since AD 2000-20-15 Was Issued

    Since the FAA issued AD 2000-20-15, the average flight time (AFT) 
of Model A300-600 airplanes has changed. It was determined that the 
existing inspection compliance times must be reduced.
    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued AD 2021-0288, dated December 21, 2021 (EASA 
AD 2021-0288) (also referred to as the MCAI), to correct an unsafe 
condition for all

[[Page 47145]]

Airbus SAS Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, B4-120, B4-
203, B4-220, C4-203, and F4-203 airplanes; and certain Airbus SAS Model 
A300 B4-603, B4-622, and B4-622R airplanes; Model A300 B4-605R series 
airplanes; Model C4-620 airplanes; and Model F4-605R airplanes. Model 
A300 B4-120, B4-220, C4-203, C4-620, and F4-203 airplanes are not 
certificated by the FAA and are not included on the U.S. type 
certificate data sheet; this proposed AD therefore does not include 
those airplanes in the applicability.
    This proposed 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 proposing 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. See the MCAI for additional background information.

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.

FAA's Determination

    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 the State of Design Authority, 
the FAA has been notified of the unsafe condition described in the MCAI 
referenced above. The FAA is issuing this NPRM after determining that 
the unsafe condition described previously is likely to exist or develop 
in other products of the same type design.

Proposed AD Requirements in This NPRM

    This proposed AD would retain all of the requirements of AD 2000-
20-15, but would reduce the compliance times and remove airplanes from 
the applicability. This proposed AD would require accomplishing the 
actions specified in EASA AD 2021-0288 described previously, except for 
any differences identified as exceptions in the regulatory text of this 
proposed AD.

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD 
process, the FAA developed a process to use some civil aviation 
authority (CAA) ADs as the primary source of information for compliance 
with requirements for corresponding FAA ADs. The FAA has been 
coordinating this process with manufacturers and CAAs. As a result, the 
FAA proposes to incorporate EASA AD 2021-0288 by reference in the FAA 
final rule. This proposed AD would, therefore, require compliance with 
EASA AD 2021-0288 in its entirety through that incorporation, except 
for any differences identified as exceptions in the regulatory text of 
this proposed AD. Using common terms that are the same as the heading 
of a particular section in EASA AD 2021-0288 does not mean that 
operators need comply only with that section. For example, where the AD 
requirement refers to ``all required actions and compliance times,'' 
compliance with this AD requirement is not limited to the section 
titled ``Required Action(s) and Compliance Time(s)'' in EASA AD 2021-
0288. Service information required by EASA AD 2021-0288 for compliance 
will be available at www.regulations.gov by searching for and locating 
Docket No. FAA-2022-0986 after the FAA final rule is published.

Costs of Compliance

    The FAA estimates that this proposed AD affects 67 airplanes of 
U.S. registry. The FAA estimates the following costs to comply with 
this proposed AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                              Cost per          Cost on U.S.
              Action                      Labor cost         Parts cost        product           operators
----------------------------------------------------------------------------------------------------------------
Inspection........................  6 work-hours x $85                 $0            $510  $34,170, per
                                     per hour = $510.                                       inspection cycle.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary repair 
that would be required 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
----------------------------------------------------------------------------------------------------------------
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

    The FAA determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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.

[[Page 47146]]

    For the reasons discussed above, I certify this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Would not affect intrastate aviation in Alaska, and
    (3) Would 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 Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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); and
0
b. Adding the following new AD:

Airbus SAS: Docket No. FAA-2022-0986; Project Identifier MCAI-2021-
01440-T.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by September 16, 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)(2) of 
this AD. Information may be emailed to: [email protected].
    (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) Related Information

    (1) For EASA AD 2021-0288, 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. 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 at 
www.regulations.gov by searching for and locating Docket No. FAA-
2022-0986.
    (2) 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 [email protected].

    Issued on July 27, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2022-16451 Filed 8-1-22; 8:45 am]
BILLING CODE 4910-13-P