[Federal Register Volume 87, Number 117 (Friday, June 17, 2022)]
[Rules and Regulations]
[Pages 36387-36390]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-13016]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-0380; Project Identifier MCAI-2021-01178-T; 
Amendment 39-22076; AD 2022-12-04]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus SAS Model A330-200 series airplanes, Model A330-200 
Freighter series airplanes, and Model A330-300 series airplanes. This 
AD was prompted by a determination that certain service information 
specified in AD 2018-20-19 contained instructions that could be 
misleading, resulting in a necessary inspection not being accomplished 
on certain airplanes. This AD requires a rototest for certain modified 
airplanes for any crack around the right-side upper and lower bulk door 
support or door latch fitting holes at certain bulk cargo door frames, 
or repetitive inspections for any crack at certain fittings, and on-
condition actions, 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 22, 2022.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of July 22, 
2022.

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 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 https://www.regulations.gov by searching for and locating 
Docket No. FAA-2022-0380.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2022-0380; 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.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
Large Aircraft Section, FAA, International Validation Branch, 2200 
South 216th St., Des Moines, WA 98198; phone 206-231-3229; email 
[email protected].

SUPPLEMENTARY INFORMATION:

Background

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2021-0233, dated October 27, 2021 
(EASA AD

[[Page 36388]]

2021-0233) (also referred to as the MCAI), to correct an unsafe 
condition for certain Airbus SAS Model A330-200 series airplanes, Model 
A330-200 Freighter series airplanes, and Model A330-300 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 certain Airbus SAS 
Model A330-200 series airplanes, Model A330-200 Freighter series 
airplanes, and Model A330-300 series airplanes. The NPRM published in 
the Federal Register on March 28, 2022 (87 FR 17198). The NPRM was 
prompted by a determination that tartaric sulfuric anodizing (TSA)/
chromic acid anodizing (CAA) surface treatment in the door fitting 
attachment holes leads to a detrimental effect on fatigue behavior; and 
that certain service information specified in AD 2018-20-19, Amendment 
39-19453 (83 FR 52126, October 16, 2018) (AD 2018-20-19) contains 
instructions that could be misleading, resulting in a necessary 
inspection not being accomplished on certain airplanes. The potentially 
misleading instructions are for an optional action, and apply only to 
model A330-200, A330-200 Freighter, and A330-300 airplanes. The NPRM 
proposed to require a rototest for certain modified airplanes for any 
crack around the right-side upper and lower bulk door support or door 
latch fitting holes at certain bulk cargo door frames, or repetitive 
inspections for any crack at certain fittings, and on-condition 
actions, as specified in EASA AD 2021-0233.
    The FAA is issuing this AD to address possible fatigue cracks in 
the bulk cargo door frames, caused by TSA/CAA surface treatment in 
frame (FR) 67 and FR69 cargo door frame attachment holes. See the MCAI 
for additional background information.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from the Air Line Pilots Association, 
International (ALPA) who supported the NPRM without change.

Conclusion

    The FAA reviewed the relevant data, considered the comment 
received, and determined that air safety requires adopting this AD as 
proposed. 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. Accordingly, the FAA is issuing this AD to 
address the unsafe condition on these products.

Related Service Information Under 1 CFR Part 51

    EASA AD 2021-0233 specifies procedures for a rototest for any crack 
around the holes at the upper and lower door support fittings of frame 
FR67 and FR69 right hand side and the holes at door latch fitting of 
FR69 right hand side; or repetitive detailed inspections of the frame 
around the fittings, or high frequency eddy current (HFEC) and 
ultrasonic inspections of the upper door supper fitting holes and 
rototests of the lower door fitting holes of the door latch fittings at 
FR69 for any crack; and on-condition actions. On-condition actions 
include installing new (never installed on an airplane) bushes to the 
latch fittings of FR69 and repair, and a rototest of the support 
fittings and the frame holes at FR67.
    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 109 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
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Up to 15 work-hours x $85 per hour               $0  Up to $1,275.................  Up to $138,975.
 = $1,275.
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    The FAA estimates the following costs to do any necessary on-
condition action that would be required based on the results of any 
required or optional actions. The FAA has no way of determining the 
number of aircraft that might need this on-condition action:

                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
3 work-hours x $85 per hour = $255....          $1,915           $2,170
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    The FAA has received no definitive data on which to base the cost 
estimates for the repairs 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.

[[Page 36389]]

    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.

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:

2022-12-04 Airbus SAS: Amendment 39-22076; Docket No. FAA-2022-0380; 
Project Identifier MCAI-2021-01178-T.

(a) Effective Date

    This airworthiness directive (AD) is effective July 22, 2022.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus SAS airplanes identified in 
paragraphs (c)(1) through (3) of this AD, certificated in any 
category, as identified in European Union Aviation Safety Agency 
(EASA) AD 2021-0233, dated October 27, 2021 (EASA AD 2021-0233).
    (1) Model A330-201, -202, -203, -223, and -243 airplanes.
    (2) Model A330-223F and -243F airplanes.
    (3) Model A330-301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a determination that tartaric sulfuric 
anodizing (TSA)/chromic acid anodizing (CAA) surface treatment in 
the door fitting attachment holes leads to a detrimental effect on 
fatigue behavior; and that certain service information specified in 
AD 2018-20-19 contains instructions that could be misleading, 
resulting in a necessary inspection not being accomplished on 
certain airplanes. The FAA is issuing this AD to address possible 
fatigue cracks in the bulk cargo door frames, caused by TSA/CAA 
surface treatment in frame (FR) 67 and FR69 cargo door frame 
attachment holes. Cracks in the bulk cargo door frames can cause the 
in-flight loss of a bulk cargo door, damage to the airplane, and 
subsequent reduced control 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, EASA AD 2021-0233.

(h) Exceptions to EASA AD 2021-0233

    (1) Where EASA AD 2021-0233 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) The ``Remarks'' section of EASA AD 2021-0233 does not apply 
to this AD.
    (3) Where paragraph (4) of EASA AD 2021-0233 specifies to 
``accomplish those instructions accordingly'' if discrepancies are 
detected, for this AD a discrepancy is any cracking, and if any 
cracking is detected, the cracking must be repaired before further 
flight 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.
    (4) Where paragraph (4) of EASA AD 2021-0233 specifies to 
``contact Airbus for approved repair instructions,'' for this AD use 
``accomplish corrective actions in accordance with the instructions 
of the SB and contact the Manager, Large Aircraft Section, 
International Validation Branch, FAA; or EASA; or Airbus SAS's EASA 
DOA for approved repair instructions. If approved by the DOA, the 
approval must include the DOA-authorized signature''
    (5) Although the service information referenced in EASA AD 2021-
0233 specifies to do a check of the aircraft records for 
accomplishment of certain service information, and specifies that 
action as ``RC,'' (required for compliance), this AD does not 
include that requirement.
    (6) Where the Applicability section of EASA AD 2021-0233 refers 
to ``defects,'' for this AD ``defects'' are cracks.

(i) No Reporting Requirement

    Although the service information referenced in EASA AD 2021-0233 
specifies to submit certain information to the manufacturer, this AD 
does not include that requirement.

(j) Additional 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: [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(s) (h)(3) and (4), (i), and (j)(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.

(k) Related Information

    For more information about this AD, contact Vladimir Ulyanov, 
Aerospace Engineer, Large Aircraft Section, FAA, International 
Validation Branch, 2200 South 216th St., Des Moines, WA 98198; phone 
206-231-3229; email [email protected].

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference 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 2021-0233, 
dated October 27, 2021.
    (ii) [Reserved]
    (3) For EASA AD 2021-0233, 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

[[Page 36390]]

availability of this material at the FAA, call 206-231-3195.
    (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 June 3, 2022.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2022-13016 Filed 6-16-22; 8:45 am]
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