Airworthiness Directives; Airbus SAS Airplanes

[Federal Register Volume 85, Number 229 (Friday, November 27, 2020)]
[Rules and Regulations]
[Pages 75838-75840]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-26046]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0788; Product Identifier 2020-NM-091-AD; Amendment 
39-21327; AD 2020-23-11]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Airbus SAS Model A300 series airplanes; and Airbus SAS Model A300 B4-
600, B4-600R, and F4-600R series airplanes, and Airbus SAS Model A300 
C4-605R Variant F airplanes (collectively called Model A300-600 series 
airplanes). This AD was prompted by reports of cracking at a certain 
hole location on the left-hand (LH) side of a certain frame (FR). This 
AD requires repetitive inspections for discrepancies of certain areas 
in and around the fuselage, as specified in two European Union Aviation 
Safety Agency (EASA) ADs, which are incorporated by reference. The FAA 
is issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective January 4, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 4, 
2021.

ADDRESSES: For material incorporated by reference (IBR) in this AD, 
contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; 
telephone +49 221 8999 000; email [email protected]; internet 
www.easa.europa.eu. You may find this IBR material on the EASA website 
at https://ad.easa.europa.eu. You may view this IBR material at the 
FAA, Airworthiness Products Section, Operational Safety Branch, 2200 
South 216th St., Des Moines, WA. For information on the availability of 
this material at the FAA, call 206-231-3195. It is also available in 
the AD docket on the internet at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2020-0788.

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-
0788; 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:

Discussion

    The EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2020-0110R1, dated May 27, 2020; and 
EASA AD 2020-0111R2, dated June 16, 2020 (``EASA AD 2020-0110R1'' and 
``EASA AD 2020-0111R2'') (also

[[Page 75839]]

referred to as ``the Mandatory Continuing Airworthiness Information,'' 
or ``the MCAI''); to correct an unsafe condition for all Airbus SAS 
Model A300 series airplanes and Airbus SAS Model A300-600 series 
airplanes.
    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to all Airbus SAS Model 
A300 series airplanes and Airbus SAS Model A300-600 series airplanes. 
The NPRM published in the Federal Register on September 1, 2020 (85 FR 
54286). The NPRM was prompted by reports of cracking at hole location 
#10 on the LH side of FR4. The NPRM proposed to require repetitive 
inspections for discrepancies of certain areas in and around the 
fuselage, as specified in two EASA ADs.
    The FAA is issuing this AD to address fatigue cracking, which could 
result in reduced structural integrity of the fuselage. See the MCAI 
for additional background information.

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule. The FAA has considered the comment 
received. FedEx indicated its support for the NPRM.

Conclusion

    The FAA reviewed the relevant data, considered the comment 
received, and determined that air safety and the public interest 
require adopting this final rule as proposed, except for minor 
editorial changes. The FAA has determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
    <bullet> 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 2020-0110R1 describes procedures for repetitive special 
detailed inspections for discrepancies (i.e., cracking) of the fuselage 
internal structure at certain frames, windshield frame lower section 
and closing panel, fuselage skin lap joint, and center wing bottom skin 
internal angle; and applicable corrective actions (repairing 
discrepancies).
    EASA AD 2020-0111R2 describes procedures for repetitive special 
detailed inspections for discrepancies of the outer wing bottom skin 
internal joint plate, outer wing bottom skin, fuselage internal 
structure at certain frames, and windshield frame lower section and 
closing panel; and applicable corrective actions (repairing 
discrepancies).
    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 118 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
90 work-hours x $85 per hour = $7,650........................              $0           $7,650         $902,700
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data that would enable the 
agency to provide cost estimates for the on-condition actions specified 
in this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    The FAA is issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: General requirements. 
Under that section, Congress charges the FAA with promoting safe flight 
of civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds necessary 
for safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Will not affect intrastate aviation in Alaska, and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2020-23-11 Airbus SAS: Amendment 39-21327; Docket No. FAA-2020-0788; 
Product Identifier 2020-NM-091-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective January 4, 2021.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus SAS airplanes identified in 
paragraphs (c)(1) and (2) of this AD, certificated in any category.
    (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; 
Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R and F4-
622R airplanes; and Model A300 C4-605R Variant F airplanes.

[[Page 75840]]

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage; 
57, Wings.

(e) Reason

    This AD was prompted by reports of cracking at hole location #10 
on the left-hand side of frame 4. The FAA is issuing this AD to 
address fatigue cracking, which could result in reduced structural 
integrity of the fuselage.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Requirements

    (1) For airplanes identified in paragraph (c)(1) of this AD: 
Except as specified in paragraphs (h)(1) and (3) of this AD, comply 
with all required actions and compliance times specified in, and in 
accordance with, European Union Aviation Safety Agency (EASA) AD 
2020-0110R1, dated May 27, 2020 (``EASA AD 2020-0110R1'').
    (2) For airplanes identified in paragraph (c)(2) of this AD: 
Except as specified in paragraphs (h)(2) and (3) of this AD, comply 
with all required actions and compliance times specified in, and in 
accordance with, EASA AD 2020-0111R2, dated June 16, 2020 (``EASA AD 
2020-0111R2'').

(h) Exceptions to EASA AD 2020-0110R1 and EASA AD 2020-0111R2

    (1) Where EASA AD 2020-0110R1 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) Where paragraph (4) of EASA AD 2020-0111R2 refers to June 3, 
2020 (``the effective date of this [EASA] AD at original issue''), 
this AD requires using the effective date of this AD.
    (3) The ``Remarks'' section of EASA AD 2020-0110R1 and EASA AD 
2020-0111R2 does not apply to this AD.

(i) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Large Aircraft Section, International Validation Branch, FAA, has 
the authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or 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 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.

(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 2020-0110R1, 
dated May 27, 2020.
    (ii) European Union Aviation Safety Agency (EASA) AD 2020-
0111R2, dated June 16, 2020.
    (3) For EASA AD 2020-0110R1 and EASA AD 2020-0111R2, contact the 
EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 
221 8999 000; email [email protected]; Internet www.easa.europa.eu. 
You may find this EASA AD on the EASA website at https://ad.easa.europa.eu.
    (4) You may view this material at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 2200 South 216th St., 
Des Moines, WA. For information on the availability of this material 
at the FAA, call 206-231-3195. This material may be found in the AD 
docket on the internet at https://www.regulations.gov by searching 
for and locating Docket No. FAA-2020-0788.
    (5) You may view this material that is incorporated by reference 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at NARA, email 
[email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on November 4, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-26046 Filed 11-25-20; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T01:54:58.762706+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

af1fae87139c15d2b644310538b4a400116ff0bd52c268622beffd93a4513ba4

Text SHA-256

788c71087cc9e66cec4848642f75af398e17821e71bb334bc16124f291e3b00c