Airworthiness Directives; Airbus SAS Airplanes, 17198-17201 [2022-06392]
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17198
Proposed Rules
Federal Register
Vol. 87, No. 59
Monday, March 28, 2022
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2022–0380; Project
Identifier MCAI–2021–01178–T]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt 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
proposed 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 proposed AD
would 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 a European
Union Aviation Safety Agency (EASA)
AD, which is proposed for incorporation
by reference. 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 May 12, 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
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
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SUMMARY:
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• 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: Deliver to Mail
address above 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 ADs@easa.europa.eu;
internet www.easa.europa.eu. You may
find this material on the EASA website
at https://ad.easa.europa.eu.
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
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:
Vladimir Ulyanov, Aerospace Engineer,
Large Aircraft Section, FAA,
International Validation Branch, 2200
South 216th St., Des Moines, WA 98198;
telephone and fax 206–231–3229; email
vladimir.ulyanov@faa.gov.
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–2022–0380; Project Identifier
MCAI–2021–01178–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 https://
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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 Vladimir Ulyanov,
Aerospace Engineer, Large Aircraft
Section, FAA, International Validation
Branch, 2200 South 216th St., Des
Moines, WA 98198; telephone and fax
206–231–3229; email vladimir.ulyanov@
faa.gov. Any commentary that the FAA
receives which is not specifically
designated as CBI will be placed in the
public docket for this rulemaking.
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
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.
This proposed 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, 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
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misleading instructions are for an
optional action, and apply only to
model A330–200, A330–200 Freighter,
and A330–300 airplanes, therefore this
AD does not propose to supersede AD
2018–20–19. The FAA is proposing this
AD to address possible fatigue cracks in
the bulk cargo door frames, caused by
TSA/CAA surface treatment in frame
(FR) 67 and FR 69 bulk 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. See the MCAI for
additional background information.
AD 2018–20–19 superseded AD 2017–
16–07, Amendment 39–18984 (82 FR
41874, September 5, 2017) (AD 2017–
16–07), and applies to certain Airbus
SAS Model A330–200 series airplanes,
Model A330–200 Freighter series
airplanes, Model A330–300 series
airplanes, Model A340–200 series
airplanes, and Model A340–300 series
airplanes. AD 2018–20–19 was
prompted by a determination that only
airplanes having manufacturer serial
numbers (MSNs) 0400 through 1779
inclusive are affected by TSA/CAA
surface treatment in the door fitting
attachment holes, and that airplanes
having MSNs 0001 through 0399
inclusive were excluded from AD 2017–
16–07. AD 2018–20–19 requires new
inspections of certain attachment holes
for residual surface treatment and
cracking, and corrective action if
necessary; and provides an optional
terminating action for the inspections.
Since AD 2018–20–09 was issued, it
was determined that the service bulletin
used for the optional modification on
certain airplanes, Airbus Service
Bulletin A330–53–3275, dated
September 8, 2017, contained
instructions that could be misleading.
As a result, the special detailed
inspection (rototest inspection) that was
intended to be accomplished prior to
accomplishing the optional
modification may not have been
accomplished on all airplanes. This
proposed AD would therefore require a
rototest for any crack around the holes
at the holes of the upper and lower door
support fittings of FR67 and FR69 on
the right hand side and the holes at door
latch fittings of FR69 on the right hand
side, or repetitive detailed inspections
for cracks 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, and
on-condition actions.
These proposed actions would be
required for Airbus SAS Model A330–
200 series airplanes, Model A330–200
Freighter series airplanes, and Model
A330–300 series airplanes, MSN 1
through 1779 inclusive, on which
Airbus Service Bulletin A330–53–3275
was embodied, except those airplanes
on which during the embodiment of that
service bulletin the rototest inspection
was accomplished with no defect
detected or any defects corrected, as
applicable, as specified in Airbus
Service Bulletin A330–53–3275.
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 (FR)67
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
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. Oncondition 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.
FAA’s Determination
These products have been approved
by the aviation authority of another
country and are approved for operation
in the United States. Pursuant to the
FAA’s bilateral agreement with the State
of Design Authority, it has notified the
FAA of the unsafe condition described
in the MCAI referenced above. The FAA
is issuing this NPRM after determining
17199
that the unsafe condition described
previously is likely to exist or develop
in other products of these same type
designs.
Proposed AD Requirements in this
NPRM
This proposed AD would require
accomplishing the actions specified in
EASA AD 2021–0233 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 2021–0233 by
reference in the FAA final rule. This
proposed AD would, therefore, require
compliance with EASA AD 2021–0233
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 2021–0233 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 2021–0233.
Service information required by EASA
AD 2021–0233 for compliance will be
available at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2022–0380 after the FAA final
rule is published.
Costs of Compliance
The FAA estimates that this proposed
AD would affect 109 airplanes of U.S.
registry. The FAA estimates the
following costs to comply with this
proposed AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Labor cost
Parts cost
Cost per product
Cost on U.S.
operators
Up to 15 work-hours × $85 per hour = $1,275 ...........
$0
Up to $1,275 ...............................................................
Up to $138,975.
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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
Labor cost
Parts cost
Cost per
product
3 work-hours × $85 per hour = $255 ......................................................................................................................
$1,915
$2,340
The FAA has received no definitive
data on which to base the cost estimates
for the repairs specified in this proposed
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.
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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.
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.
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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
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
Airbus SAS: Docket No. FAA–2022–0380;
Project Identifier MCAI–2021–01178–T.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by May 12,
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 FR 69 cargo door frame attachment
holes. Cracks in the bulk cargo door frames
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Requirements
1. The authority citation for part 39
continues to read as follows:
■
§ 39.13
can cause the in-flight loss of a bulk cargo
door, damage to the airplane, and subsequent
reduced control of the airplane.
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
crack, 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.
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(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)(2) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. 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 paragraphs (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.
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(k) Related Information
(1) For EASA AD 2021–0233, contact
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +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. 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
https://www.regulations.gov by searching for
and locating Docket No. FAA–2022–0380.
(2) 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; telephone
and fax 206–231–3229; email
vladimir.ulyanov@faa.gov.
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Issued on March 22, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2022–06392 Filed 3–25–22; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2022–0294; Project
Identifier MCAI–2021–00550–R]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters Deutschland GmbH (AHD)
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for all
Airbus Helicopters Deutschland GmbH
(AHD) Model MBB–BK117 A–1, MBB–
BK117 A–3, MBB–BK117 A–4, MBB–
BK117 B–1, MBB–BK117 B–2, MBB–
BK117 C–1, MBB–BK117 C–2, and
MBB–BK117 D–2 helicopters. This
proposed AD was prompted by the
FAA’s determination that aging of the
elastomeric material of certain tension
torsion straps (TT-Straps), during the
period since manufacturing date up to
first flight on a helicopter, may affect its
structural characteristics. This proposed
AD would require the replacement of
certain TT-Straps, implementation of
storage life limits for TT-Straps, a
prohibition on installing certain TTStraps and conditions for installation of
certain other TT-Straps, as specified in
a European Union Aviation Safety
Agency (EASA) AD, which is proposed
for incorporation by reference (IBR). 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 May 12, 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
https://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: Deliver to Mail
address above between 9 a.m. and 5
SUMMARY:
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17201
p.m., Monday through Friday, except
Federal holidays.
For EASA material that is proposed
for IBR in this AD, contact 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 the EASA material on the EASA
website at https://ad.easa.europa.eu.
You may view this material at the FAA,
Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy., Room 6N–321, Fort Worth, TX
76177. For information on the
availability of this material at the FAA,
call (817) 222–5110. The EASA material
is also available at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2022–
0294.
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2022–0294; 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 EASA AD, any comments
received, and other information. The
street address for Docket Operations is
listed above.
FOR FURTHER INFORMATION CONTACT:
Kristi Bradley, Program Manager, COS
Program Management Section,
Operational Safety Branch, Compliance
& Airworthiness Division, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
phone: (817) 222–5110; email:
kristin.bradley@faa.gov.
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–2022–0294; Project Identifier
MCAI–2021–00550–R’’ 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 https://
www.regulations.gov, including any
personal information you provide. The
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Agencies
[Federal Register Volume 87, Number 59 (Monday, March 28, 2022)]
[Proposed Rules]
[Pages 17198-17201]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-06392]
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Proposed Rules
Federal Register
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This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 87, No. 59 / Monday, March 28, 2022 /
Proposed Rules
[[Page 17198]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2022-0380; Project Identifier MCAI-2021-01178-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 adopt 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
proposed 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 proposed AD would 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 a
European Union Aviation Safety Agency (EASA) AD, which is proposed for
incorporation by reference. 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 May 12,
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 https://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: Deliver to Mail address above 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.
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 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: Vladimir Ulyanov, Aerospace Engineer,
Large Aircraft Section, FAA, International Validation Branch, 2200
South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3229;
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-2022-0380; Project Identifier
MCAI-2021-01178-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
https://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
Vladimir Ulyanov, Aerospace Engineer, Large Aircraft Section, FAA,
International Validation Branch, 2200 South 216th St., Des Moines, WA
98198; telephone and fax 206-231-3229; 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
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 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.
This proposed 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, 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
[[Page 17199]]
misleading instructions are for an optional action, and apply only to
model A330-200, A330-200 Freighter, and A330-300 airplanes, therefore
this AD does not propose to supersede AD 2018-20-19. The FAA is
proposing this AD to address possible fatigue cracks in the bulk cargo
door frames, caused by TSA/CAA surface treatment in frame (FR) 67 and
FR 69 bulk 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. See
the MCAI for additional background information.
AD 2018-20-19 superseded AD 2017-16-07, Amendment 39-18984 (82 FR
41874, September 5, 2017) (AD 2017-16-07), and applies to certain
Airbus SAS Model A330-200 series airplanes, Model A330-200 Freighter
series airplanes, Model A330-300 series airplanes, Model A340-200
series airplanes, and Model A340-300 series airplanes. AD 2018-20-19
was prompted by a determination that only airplanes having manufacturer
serial numbers (MSNs) 0400 through 1779 inclusive are affected by TSA/
CAA surface treatment in the door fitting attachment holes, and that
airplanes having MSNs 0001 through 0399 inclusive were excluded from AD
2017-16-07. AD 2018-20-19 requires new inspections of certain
attachment holes for residual surface treatment and cracking, and
corrective action if necessary; and provides an optional terminating
action for the inspections. Since AD 2018-20-09 was issued, it was
determined that the service bulletin used for the optional modification
on certain airplanes, Airbus Service Bulletin A330-53-3275, dated
September 8, 2017, contained instructions that could be misleading. As
a result, the special detailed inspection (rototest inspection) that
was intended to be accomplished prior to accomplishing the optional
modification may not have been accomplished on all airplanes. This
proposed AD would therefore require a rototest for any crack around the
holes at the holes of the upper and lower door support fittings of FR67
and FR69 on the right hand side and the holes at door latch fittings of
FR69 on the right hand side, or repetitive detailed inspections for
cracks 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, and on-condition actions.
These proposed actions would be required for Airbus SAS Model A330-
200 series airplanes, Model A330-200 Freighter series airplanes, and
Model A330-300 series airplanes, MSN 1 through 1779 inclusive, on which
Airbus Service Bulletin A330-53-3275 was embodied, except those
airplanes on which during the embodiment of that service bulletin the
rototest inspection was accomplished with no defect detected or any
defects corrected, as applicable, as specified in Airbus Service
Bulletin A330-53-3275.
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
(FR)67 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 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.
FAA's Determination
These products have been approved by the aviation authority of
another country and are approved for operation in the United States.
Pursuant to the FAA's bilateral agreement with the State of Design
Authority, it has notified the FAA 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 these same type designs.
Proposed AD Requirements in this NPRM
This proposed AD would require accomplishing the actions specified
in EASA AD 2021-0233 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 2021-0233 by reference in the FAA
final rule. This proposed AD would, therefore, require compliance with
EASA AD 2021-0233 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 2021-0233 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-
0233. Service information required by EASA AD 2021-0233 for compliance
will be available at https://www.regulations.gov by searching for and
locating Docket No. FAA-2022-0380 after the FAA final rule is
published.
Costs of Compliance
The FAA estimates that this proposed AD would affect 109 airplanes
of U.S. registry. The FAA estimates the following costs to comply with
this proposed 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
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Cost per
Labor cost Parts cost product
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3 work-hours x $85 per hour = $255.... $1,915 $2,340
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The FAA has received no definitive data on which to base the cost
estimates for the repairs specified in this proposed 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
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.
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
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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]
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2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
Airbus SAS: Docket No. FAA-2022-0380; Project Identifier MCAI-2021-
01178-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by May 12, 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 FR 69 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 crack, 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.
[[Page 17201]]
(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)(2) 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
paragraphs (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
(1) 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. 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 https://www.regulations.gov by searching for and locating Docket No. FAA-
2022-0380.
(2) 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; telephone and fax 206-231-3229; email
[email protected].
Issued on March 22, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2022-06392 Filed 3-25-22; 8:45 am]
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