Airworthiness Directives; Airbus SAS Airplanes

[Federal Register Volume 86, Number 106 (Friday, June 4, 2021)]
[Rules and Regulations]
[Pages 29944-29946]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-11726]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0028; Project Identifier MCAI-2020-01516-T; 
Amendment 39-21533; AD 2021-09-19]
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 adopting a new airworthiness directive (AD) for all 
Airbus SAS Model A319-171N airplanes, Model A320-271N, -272N, and -273N 
airplanes, and Model A321-271N, -272N, -271NX, and -272NX airplanes. 
This AD was prompted by a report indicating that during a full scale 
fatigue test of the forward engine mounts, premature wear was 
identified on the forward engine mount shackle assemblies; in addition, 
during bearing replacement, the bearing lock washer was found broken. 
This AD requires replacing any forward engine mount shackle assemblies 
having a certain part number with a serviceable part, and re-
identifying the engine mount, or replacing any forward engine mount 
assemblies having a certain part number, 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 July 9, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of July 9, 
2021.

ADDRESSES: For 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 IBR material on the EASA website 
at https://ad.easa.europa.eu. You may view this service information 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 on the internet at https://www.regulations.gov by searching 
for and locating Docket No. FAA-2021-0028.

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-2021-
0028; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, any comments received, and other information. The 
address for Docket Operations is U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
Large Aircraft Section, International Validation Branch, FAA, 2200 
South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3223; 
email [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2020-0250, dated November 11, 2020 
(EASA AD 2020-0250) (also referred to as the Mandatory Continuing 
Airworthiness Information, or the MCAI), to correct an unsafe condition 
for all Airbus SAS Model A319-171N airplanes, Model A320-271N, -272N, 
and -273N airplanes, and Model A321-271N, -272N, -271NX, and -272NX 
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 
A319-171N airplanes, Model A320-271N, -272N, and -273N airplanes, and 
Model A321-271N, -272N, -271NX, and -272NX airplanes. The NPRM 
published in the Federal Register on February 24, 2021 (86 FR 11156). 
The NPRM was prompted by a report indicating that during a full scale 
fatigue test of the forward engine mounts, premature wear was 
identified on the forward engine mount shackle assemblies; in addition, 
during bearing replacement, the bearing lock washer was found broken. 
The NPRM proposed to require replacing any forward engine mount shackle 
assemblies having a certain part number with a serviceable part, and 
re-identifying the engine mount, or replacing any forward engine mount 
assemblies having a certain part number, as specified in EASA AD 2020-
0250.
    The FAA is issuing this AD to address premature wear and broken 
bearing lock washers at the forward engine mounts, which could lead to 
overload of the forward engine mount beams and engine mount failure, 
with consequent in-flight engine detachment, and possibly result in 
reduced controllability of the airplane. See the MCAI for additional 
background information.

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule. The FAA has considered the comment 
received. The Air Line Pilots Association, International (ALPA) 
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

[[Page 29945]]

    <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 2020-0250 describes procedures for replacing any forward 
engine mount shackle assemblies having part number D7121513500xxx 
(`xxx' can be any numerical value) with a serviceable part, and re-
identifying the engine mount, or replacing any forward engine mount 
assemblies having part number D7121506500xxx (`xxx' can be any 
numerical value) and fitted with an affected engine mount shackle 
assembly. 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 70 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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             Labor cost                            Parts cost                          Cost per product                    Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
5 work-hours x $85 per hour = $425.  Up to $75,360........................  Up to $75,785........................  Up to $5,304,950.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some or all of the costs of this AD 
may be covered under warranty, thereby reducing the cost impact on 
affected operators. The FAA does not control warranty coverage for 
affected operators. As a result, the FAA has included all known costs 
in the cost estimate.

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:

2021-09-19 Airbus SAS: Amendment 39-21533; Docket No. FAA-2021-0028; 
Project Identifier MCAI-2020-01516-T.

(a) Effective Date

    This airworthiness directive (AD) is effective July 9, 2021.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus SAS Model A319-171N airplanes, 
Model A320-271N, -272N, and -273N airplanes, and Model A321-271N, -
272N, -271NX, and -272NX airplanes, certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Powerplant.

(e) Reason

    This AD was prompted by a report indicating that during a full 
scale fatigue test of the forward engine mounts, premature wear was 
identified on the forward engine mount shackle assemblies; in 
addition, during bearing replacement, the bearing lock washer was 
found broken. The FAA is issuing this AD to address premature wear 
and broken bearing lock washers at the forward engine mounts, which 
could lead to overload of the forward engine mount beams and engine 
mount failure, with consequent in-flight engine detachment, and 
possibly result in reduced controllability of the airplane.

(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 
2020-0250, dated November 11, 2020 (EASA AD 2020-0250).

(h) Exceptions to EASA AD 2020-0250

    (1) Where EASA AD 2020-0250 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) The ``Remarks'' section of EASA AD 2020-0250 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.

[[Page 29946]]

    (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 Sanjay Ralhan, 
Aerospace Engineer, Large Aircraft Section, International Validation 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3223; email [email protected].

(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 2020-0250, 
dated November 11, 2020.
    (ii) [Reserved]
    (3) For EASA AD 2020-0250, 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) 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-2021-0028.
    (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 April 23, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-11726 Filed 6-3-21; 8:45 am]
BILLING CODE 4910-13-P

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