Document ID: FAA-2020-0914-0006
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus SAS Airplanes
Posted Date: 2021-03-17T04:00Z

[Federal Register Volume 86, Number 50 (Wednesday, March 17, 2021)]
[Rules and Regulations]
[Pages 14528-14531]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-05534]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0914; Product Identifier 2020-NM-058-AD; Amendment 
39-21463; AD 2021-05-20]
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) 2018-16-
02, which applied to all Airbus SAS Model A318-111 and -112 airplanes; 
Model A319-111, -112, -113, -114, and -115 airplanes; Model A320-211, -
212, -214, and -216 airplanes; and Model A321-111, -112, -211, -212, 
and -213 airplanes. AD 2018-16-02 required modifying and re-identifying 
the 3-lug aft engine mount assemblies. This AD continues to require 
modifying and re-identifying the 3-lug aft engine mount assemblies, and 
also requires modifying and re-identifying the 4-lug aft engine mount 
assemblies; as specified in a European Union Aviation Safety Agency 
(EASA) AD, which is incorporated by reference. This AD was prompted by 
a report of a production quality deficiency on the inner retainer 
installed on link assemblies of the aft engine mount, which could 
result in failure of the retainer. The FAA is issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective April 21, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of April 21, 
2021.

ADDRESSES: For material incorporated by reference (IBR) in this AD, 
contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; 
phone: +49 221 8999 000; email: ADs@easa.europa.eu; 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-2020-0914.

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-
0914; 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; phone and fax: 206-231-3223; 
email: sanjay.ralhan@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    The EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2020-0085, dated April 6, 2020 (EASA 
AD 2020-0085) (also referred to as the

[[Page 14529]]

Mandatory Continuing Airworthiness Information, or the MCAI), to 
correct an unsafe condition for all Airbus SAS Model A318-111 and -112 
airplanes; Model A319-111, -112, -113, -114, and -115 airplanes; Model 
A320-211, -212, -214, -215, and -216 airplanes; and Model A321-111, -
112, -211, -212, and -213 airplanes. Model A320-215 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 2018-16-02, Amendment 39-19342 (83 FR 
39326, August 9, 2018) (AD 2018-16-02). AD 2018-16-02 applied to all 
Airbus SAS Model A318-111 and -112 airplanes, Model A319-111, -112, -
113, -114, and -115 airplanes, Model A320-211, -212, -214, and -216 
airplanes, and Model A321-111, -112, -211, -212, and -213 airplanes. 
The NPRM published in the Federal Register on October 14, 2020 (85 FR 
64984). The NPRM was prompted by a report of a production quality 
deficiency on the inner retainer installed on link assemblies of the 
aft engine mount, which could result in failure of the retainer. The 
NPRM proposed to continue to require modifying and re-identifying the 
3-lug aft engine mount assemblies, as specified in an EASA AD. The NPRM 
also proposed to require modifying and re-identifying the 4-lug aft 
engine mount assemblies, as specified in an EASA AD.
    The FAA is issuing this AD to address non-conforming retainers of 
the aft engine mount. This condition could result in loss of the 
locking feature of the nuts of the inner and outer pins; loss of the 
pins will result in the aft mount engine link no longer being secured 
to the aft engine mount, possibly resulting in damage to 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 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) expressed 
support for the NPRM.

Request for Consistency in Used Terms

    Delta Air Lines (DAL) requested that, for consistency, the FAA 
remove the parenthesis around the terms 3-lug and 4-lug under the 
Actions Since AD 2018-16-02 Was Issued heading in the NPRM. No further 
justification was provided.
    The FAA agrees that the change would have provided consistency in 
terminology. However, that portion of the NPRM is not restated in this 
final rule; therefore, no change has been made to this final rule in 
this regard.

Request To Remove Duplicate Wording

    DAL requested that the FAA revise the NPRM to remove duplicate 
wording ``procedures for'' under the Related IBR Material Under 1 CFR 
part 51 heading. DAL pointed out that the duplicate wording is a 
typographical error.
    The FAA agrees for the reasons provided and has updated this final 
rule accordingly.

Request To Clarify Whether Model CFM56-5B and -5C Engines are Affected

    United Airlines (UAL) requested that the FAA clarify whether the 
NPRM affects airplanes equipped with CFM International, S.A. Model 
CFM56-5B and -5C engines that are fitted with a turbine rear frame 
(TRF) with a 4-lug configuration.
    The FAA agrees to clarify. EASA AD 2020-0085 defines a 4-lug engine 
as a ``CFM56-5A1, CFM56-5A3, CFM56-5A4, CFM56-5A4/F, CFM56-5A5 or 
CFM56-5A5/F engines, fitted with a turbine rear frame (TRF) having a P/
N [part number] as identified in Appendix 1 of [EASA AD 2020-0085].'' 
The FAA has not received any information regarding Model CFM56-5B and -
5C engines that would cause the FAA to determine that those engine 
models are subject to the identified unsafe condition; therefore, those 
engines are not included in the applicability of this AD. However, 
should the FAA receive information that the Model CFM56-5B and -5C 
engines are subject to the identified unsafe condition, the FAA may 
consider additional rulemaking at that time. This final rule has not 
been changed in this regard.

Request To Extend Compliance Time for Parked Airplanes

    DAL requested that the FAA extend the compliance time specified in 
the NPRM for airplanes that are parked due to the ongoing COVID-19 
pandemic. DAL pointed out that many operators have had to park 
airplanes, and that there is uncertainty regarding any return to 
service schedule. DAL mentioned that parked aircraft/engines are not 
operating and, therefore, do not accrue time/cycles. DAL then specified 
the belief that any deadline for modification and re-identification 
should be extended by adding the duration of parking.
    The FAA disagrees with the request. DAL indicated concern related 
to the retained requirements of the AD 2018-16-02. The unsafe condition 
is the result of a production deficiency that can cause pitting 
corrosion, which is not directly related to the accumulation of flight 
cycles or flight hours. Corrosion growth is normally related to 
calendar time and it is unknown if pitting corrosion is arrested while 
the airplane is in long term storage/parking and therefore the FAA does 
not agree with the request to provide a compliance time extension for 
parked airplanes. However, under the provisions of paragraph (k)(1) of 
this AD, the FAA may approve requests for adjustments to the compliance 
time if data are submitted to substantiate that such an adjustment 
would provide an acceptable level of safety. This AD has not been 
changed in this regard.

Request To Clarify Use of ``Production Quality Deficiency''

    DAL requested that the FAA revise paragraph (h)(5) of the NPRM to 
better define the production quality deficiency that prompted the NPRM. 
DAL pointed out that the NPRM does not define the production quality 
deficiency, and does not refer to any other document for a definition.
    The FAA partially agrees. During in-service inspections, several 
aft engine mount inner retainers, fitted on airplanes equipped with 
Model CFM56-5A/5B engines, were found broken. Investigation identified 
that the main cause of crack initiation was the vibration dynamic 
effect that affects the retainers, and that the ``dull'' surface finish 
pitting is an aggravating factor when compared with the ``bright'' 
surface finishing. The ``dull'' surface finish pitting is the 
production quality deficiency. The FAA has not revised paragraph (h)(5) 
of this AD, but has instead added paragraph (g) of this AD to include 
the definition of the production quality deficiency. Subsequent 
paragraphs have been redesignated have accordingly.

Request To Correct Reference to AD 2018-16-02

    DAL requested that the FAA revise paragraph (h)(7) of the proposed 
AD to correct the reference to AD 2018-16-02.
    The FAA agrees for the reasons provided and has updated paragraph 
(i)(7) of this AD (paragraph (h)(7) of the proposed AD) accordingly.

[[Page 14530]]

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 with the changes described previously 
and 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.
    The FAA also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this final 
rule.

Related Service Information Under 1 CFR Part 51

    EASA AD 2020-0085 describes procedures for modifying and re-
identifying the aft engine mount retainer 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 119 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      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2018-16-02...  20 work-hours x $85 per           $3,152          $4,852        $577,388
                                         hour = $1,700.
New actions...........................  16 work-hours x $85 per            4,362           5,722         680,918
                                         hour = $1,360.
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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
    (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 2018-16-02, Amendment 39-19342 (83 
FR 39326, August 9, 2018), and
0
b. Adding the following new airworthiness directive:

2021-05-20 Airbus SAS: Amendment 39-21463; Docket No. FAA-2020-0914; 
Product Identifier 2020-NM-058-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective April 21, 2021.

(b) Affected ADs

    (1) This AD replaces AD 2018-16-02, Amendment 39-19342 (83 FR 
39326, August 9, 2018) (AD 2018-16-02).
    (2) This AD affects AD 2016-14-09, Amendment 39-18590 (81 FR 
44989, July 12, 2016) (AD 2016-14-09).
    (3) This AD affects AD 2017-04-10, Amendment 39-18805 (82 FR 
11791, February 27, 2017) (AD 2017-04-10).

(c) Applicability

    This AD applies to all the Airbus SAS airplanes identified in 
paragraphs (c)(1) through (4) of this AD, certificated in any 
category.
    (1) Model A318-111 and -112 airplanes.
    (2) Model A319-111, -112, -113, -114, and -115 airplanes.
    (3) Model A320-211, -212, -214, and -216 airplanes.
    (4) Model A321-111, -112, -211, -212, and -213 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of a production quality 
deficiency on the inner retainer installed on link assemblies of the 
aft engine mount, which could result in failure of the retainer. The 
FAA is issuing this AD to address non-conforming retainers of the 
aft engine mount. This condition could result in loss of the locking 
feature of the nuts of the inner and outer pins; loss of the pins 
will result in the aft mount engine link no longer being secured to 
the aft engine mount, possibly resulting in damage to the airplane.

(f) Compliance

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

(g) Definition

    For the purposes of this AD, the production quality deficiency 
is defined as a ``dull'' finish, which is caused by surface finish 
pitting, and is an aggravating factor to crack initiation from 
vibration dynamic effect when compared with the ``bright'' surface 
finish.

(h) Requirements

    Except as specified in paragraph (i) of this AD: Comply with all 
required actions and compliance times specified in, and in 
accordance with, paragraphs (3) through (6), (8), (9), (11), and 
(12) of European Union Aviation Safety Agency (EASA) AD 2020-0085, 
dated April 6, 2020 (EASA AD 2020-0085).

[[Page 14531]]

(i) Exceptions to EASA AD 2020-0085

    (1) Where EASA AD 2020-0085 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) Where EASA AD 2020-0085 refers to August 16, 2017 (the 
effective date of EASA AD 2017-0138, dated August 2, 2017), this AD 
requires using September 13, 2018 (the effective date of AD 2018-16-
02).
    (3) Where EASA AD 2020-0085 refers to December 15, 2017 (the 
issue date of EASA AD 2017-0251), this AD requires using September 
13, 2018 (the effective date of AD 2018-16-02).
    (4) The ``Remarks'' section of EASA AD 2020-0085 does not apply 
to this AD.
    (5) Where paragraph (8) of EASA AD 2020-0085 specifies ``do not 
operate any airplane having installed a, and do not install on any 
airplane a `dull' finish aft engine mount inner retainer,'' for this 
AD, do not operate any airplane having installed any inner retainers 
affected by the production quality deficiency (as defined in 
paragraph (g) of this AD), and do not install on any airplane a 
`dull' finish aft engine mount inner retainer.
    (6) Where paragraph (9.3) of EASA AD 2020-0085 refers to January 
27, 2016 (the effective date of EASA AD 2016-0010, dated January 13, 
2016), this AD requires using April 3, 2017 (the effective date of 
AD 2017-04-10).
    (7) Where paragraph (12) of EASA AD 2020-0085 specifies a 
compliance time of ``before next flight after December 15, 2017,'' 
for this AD, that compliance time is ``within 30 days after 
September 13, 2018'' (the effective date of AD 2018-16-02.)

(j) Terminating Action for AD 2016-14-09 and AD 2017-04-10

    (1) Modification of an airplane as required by paragraph (h) of 
this AD (i.e., accomplishing the modification required by paragraph 
(3) of EASA AD 2020-0085, the replacement specified in paragraph (4) 
of EASA AD 2020-0085, or the modification specified in paragraph (5) 
of EASA AD 2020-0085), constitutes terminating action for the 
repetitive detailed inspections required by paragraph (l) of AD 
2016-14-09 for that airplane.
    (2) Modification of an airplane as required by paragraph (h) of 
this AD (i.e., accomplishing the modification required by paragraph 
(3) of EASA AD 2020-0085, the replacement specified in paragraph (4) 
of EASA AD 2020-0085, or the modification specified in paragraph (5) 
of EASA AD 2020-0085), is a method of compliance with the 
requirements of paragraph (g) of AD 2017-04-10 for that airplane.

(k) 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 (l) of this 
AD. Information may be emailed to: 9-AVS-AIR-730-AMOC@faa.gov.
    (i) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the responsible Flight Standards Office.
    (ii) AMOCs approved previously for AD 2018-16-02 are approved as 
AMOCs for the corresponding provisions of EASA AD 2020-0085 that are 
required by paragraph (g) of this AD.
    (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 (k)(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.

(l) 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; phone and 
fax: 206-231-3223; email: sanjay.ralhan@faa.gov.

(m) 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 2020-0085, 
dated April 6, 2020.
    (ii) [Reserved]
    (3) For EASA AD 2020-0085, contact the EASA, Konrad-Adenauer-
Ufer 3, 50668 Cologne, Germany; phone: +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-2020-0914.
    (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 March 1, 2021.
Ross Landes,
Deputy Director for Regulatory Operations, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2021-05534 Filed 3-16-21; 8:45 am]
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