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Rule2021-25532

Airworthiness Directives; Airbus Canada Limited Partnership (Type Certificate Previously Held by C Series Aircraft Limited Partnership (CSALP); Bombardier, Inc.) Airplanes

Primary source

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Published

November 24, 2021

Effective

December 29, 2021

Issuing agencies

Transportation DepartmentFederal Aviation Administration

Abstract

The FAA is adopting a new airworthiness directive (AD) for all Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500-1A11 airplanes. This AD was prompted by a report of cracking in certain components on left and right sides of the aft wing-to-body fairing (WTBF) structure near the tie-rod attachment at a certain fuselage station; this cracking likely resulted from excessive tie-rod preload. This AD requires inspecting the aft WTBF structure for any cracking or damage, adjusting the load on the two tie-rods at a certain fuselage station, and repair if necessary, as specified in two Transport Canada Civil Aviation (TCCA) ADs, which are incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.

Full Text

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<title>Federal Register, Volume 86 Issue 224 (Wednesday, November 24, 2021)</title>
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[Federal Register Volume 86, Number 224 (Wednesday, November 24, 2021)]
[Rules and Regulations]
[Pages 66940-66945]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2021-25532]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0201; Project Identifier MCAI-2020-01346-T;
Amendment 39-21790; AD 2021-22-17]
RIN 2120-AA64

Airworthiness Directives; Airbus Canada Limited Partnership (Type
Certificate Previously Held by C Series Aircraft Limited Partnership
(CSALP); Bombardier, Inc.) 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 all
Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500-1A11
airplanes. This AD was prompted by a report of cracking in certain
components on left and right sides of the aft wing-to-body fairing
(WTBF) structure near the tie-rod attachment at a certain fuselage
station; this cracking likely resulted from excessive tie-rod preload.
This AD requires inspecting the aft WTBF structure for any cracking or
damage, adjusting the load on the two tie-rods at a certain fuselage
station, and repair if necessary, as specified in two Transport Canada
Civil Aviation (TCCA) ADs, which are incorporated by reference. The FAA
is issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective December 29, 2021.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of December 29,
2021.

ADDRESSES: For TCCA material incorporated by reference (IBR) in this
AD, contact the TCCA, Transport Canada National Aircraft Certification,
159 Cleopatra Drive, Nepean, Ontario K1A 0N5, Canada; telephone 888-
663-3639; email <a href="/cdn-cgi/l/email-protection#edaca9c0aea3ad998ec38a8ec38e8c">[email&#160;protected]</a>; internet <a href="https://tc.canada.ca/en/aviation">https://tc.canada.ca/en/aviation</a>. You

[[Page 66941]]

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 <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching for and locating Docket No. FAA-2021-
0201.

Examining the AD Docket

You may examine the AD docket at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by
searching for and locating Docket No. FAA-2021-0201; 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
two TCCA ADs, 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: Antariksh Shetty, Aerospace Engineer,
Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7300; fax 516-
794-5531; email <a href="/cdn-cgi/l/email-protection#cef7e3afb8bde3a0b7afada1e3ada1bd8ea8afafe0a9a1b8">[email&#160;protected]</a>.

SUPPLEMENTARY INFORMATION:

Background

The TCCA, which is the aviation authority for Canada, has issued
TCCA AD CF-2020-32, dated September 25, 2020 (TCCA AD CF-2020-32), to
correct an unsafe condition for all Airbus Canada Limited Partnership
Model BD-500-1A10 and BD-500-1A11 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 Canada
Limited Partnership Model BD-500-1A10 and BD-500-1A11 airplanes. The
NPRM published in the Federal Register on April 1, 2021 (86 FR 17087).
The NPRM was prompted by a report of cracking in certain components on
left and right sides of the aft WTBF structure near the tie-rod
attachment at a certain fuselage station; this cracking likely resulted
from excessive tie-rod preload. The NPRM proposed to require inspecting
the aft WTBF structure for any cracking or damage, adjusting the load
on the two tie-rods at a certain fuselage station, and repair if
necessary, as specified in TCCA AD CF-2020-32.
Since the NPRM was issued, the TCCA has issued TCCA AD CF-2020-
32R1, dated April 23, 2021 (TCCA AD CF-2020-32R1), which provides
extended compliance times for airplanes on which a certain WTBF
reinforcement modification has been accomplished. The applicability of
TCCA AD CF-2020-32R1 is the same as in TCCA AD CF-2020-32; therefore,
there is no change to the applicability of this AD. In addition, TCCA
AD CF-2020-32R1 does not add any new requirements; the change to the
compliance time is relieving. Operators can address the unsafe
condition identified in this AD by accomplishing the actions specified
in either TCCA AD CF-2020-32 or TCCA AD CF-2020-32R1.
The FAA is issuing this AD to address such cracking, which could
lead to loss of aft WTBF integrity and result in damage due to parts
departing the airplane, loss of the radio altimeter, and effects on
airplane stability and performance. See TCCA ADs CF-2020-32 and CF-
2020-32R1 for additional background information.

Discussion of Final Airworthiness Directive

Comments

The FAA received comments from two commenters, including Airbus
Canada Limited Partnership (Airbus Canada) and Delta Air Lines (DAL).
Additionally, on July 20, 2021, the FAA, Airbus Canada, and DAL had a
meeting to clarify some of DAL's comments. A record of that meeting can
be found in the docket for this final rule. The following presents the
comments received on the NPRM and the FAA's response to each comment.

Request for Clarification of ``approved'' as Used in ``later-approved
revision''

Airbus Canada requested clarification on the use of ``approved'' in
``later-approved revision'' stated in paragraph (h)(5) of the proposed
AD. Airbus Canada pointed out that the referenced document is not an
approved document and is not listed on the TCCA or FAA type certificate
data sheet as an approved publication. Airbus Canada stated that it
found that the phrase seemed to imply authority involvement in
approving that document, but TCCA's involvement, per Canadian
regulations, is to find whether implementation of that document is
appropriate and sufficient to rectify an unsafe condition.
DAL stated that including ``approved'' in the phrase ``or later
approved revisions'' changes the definition of ``applicable [aircraft
maintenance publication] AMP [data module] DM'' as provided in the TCCA
AD CF-2020-32. DAL stated that the aircraft maintenance publication is
an FAA-accepted document, not an FAA-approved document. DAL requested
that if the FAA retains ``or later approved revision,'' that the FAA
then provide its approval of Issue 006 of the document in the final
rue. DAL also stated that if Airbus Canada revises the document,
operators are not generally aware of corresponding changes to data
modules, and operators would not be able to use the later revision
without FAA approval and would not be able to do the inspection.
The FAA agrees to clarify. The FAA does not have jurisdiction over
TCCA regulatory requirements. However, U.S. operators must follow FAA
requirements and regulations for compliance with FAA ADs. For the
purposes of this AD, Airbus Canada Limited Partnership AMP DM BD500-A-
J53-82-55-04AAA-720A-A (Aft fairing strut, Wing To Body Fairing
(WTBF)--Install procedure) Issue 006, dated June 26, 2020, is the
approved version specified in TCCA AD CF-2020-32 and TCCA AD CF-2020-
32R1. Operators must have approval to use later revisions of referenced
documents. If the phrase ``or later revision'' is not modified,
operators could comply with a document containing changes that have not
been reviewed and approved by TCCA, the FAA, or the design approval
organization (DAO) for Airbus Canada to mitigate the unsafe condition.
The FAA has revised paragraph (h)(6) of this AD to specify that later
revisions must be approved by the Manager, New York ACO Branch, FAA; or
TCCA; or Airbus Canada's TCCA Design Approval Organization (DAO). If
approved by the DAO, the approval must include the DAO-authorized
signature.

Request To Incorporate Revised TCCA AD Into Final Rule

DAL stated that TCCA has released a Revision 01 to the TCCA AD CF-
2020-32, which specifies revised compliance times and references
revised service information that contains information for airplanes
delivered with a new configuration. DAL requested that the proposed AD
be revised to incorporate the later revision instead of the original
TCCA AD CF-2020-32.
The FAA agrees to reference the later revision as an optional
method of compliance. TCCA has issued TCCA AD CF-2020-32R1, which
extends the repetitive inspection intervals for airplanes on which the
modification to strengthen the support structure of the aft WTBF has
been accomplished. The FAA has revised paragraphs (g), and (h)(1)
through (7) of this AD to reference TCCA AD CF-2020-32R1 and has

[[Page 66942]]

added and re-designated lower level paragraphs in paragraph (h) of this
AD.

Request To Revise Cost Estimate

DAL requested that the FAA revise the cost estimate to increase the
number of airplanes estimated to be affected by the AD requirements.
DAL pointed out that the applicability statement in paragraph (c) of
the proposed AD identified all Model BD-500-1A10 and BD-500-1A11
airplanes as being affected by the proposed requirements. DAL stated
that it has 48 of these airplanes and is aware of another operator
taking delivery of these airplanes, which is more than the 11 airplanes
estimated in the Cost of Compliance section of the NPRM.
The FAA agrees to revise the Cost of Compliance section to increase
the number of airplanes estimated to be affected by the requirements of
this AD. As of September 15, 2021, the database that was used to
provide the estimate for the NPRM shows 54 U.S.-registered airplanes
that could be affected by this AD, which supports DAL's request. The
FAA has revised the cost estimate accordingly.

Request To Revise AD To Accommodate Operator Produced Part With
Improved Design

DAL requested an exception be added to paragraph (h) of the AD to
allow DAL to use Airbus Canada service information for inspection
instructions. DAL stated that, given that many of their airplanes have
had longeron repairs or replacements after delivery with components
designed and made under an owner-operator produced parts (OOPP)
process, it would not be able to comply with the inspections due to a
statement in the service information that excludes use of the service
information on airplanes that do not have systems and parts that were
installed at delivery or as changed by a service bulletin. DAL stated
that until Airbus Canada develops a WTBF configuration that does not
crack, it concurs with the inspection requirement and wants to be able
to use the inspection instructions to comply with the proposed AD.
The FAA disagrees. If an operator or owner is unable to comply with
requirements due to an airplane configuration that does not conform to
the configurations addressed by service information, operators or
owners must request an alternative method of compliance (AMOC) as
specified in paragraph (i)(1) of this AD. AMOC requests should include
sufficient data to show that the proposed alternate solution is
complete and addresses the unsafe condition. The FAA also does not
consider it appropriate to include various provisions or exceptions in
an AD applicable only to a single operator's unique circumstances. The
FAA has not changed this AD in this regard.

Request To Provide Alternative Repair Instructions for Non-Standard
Configurations

DAL stated that it has installed longerons that it designed and
manufactured under its OOPP program, and is concerned about not being
able to acquire repair instructions as instructed in the event that
those certain longerons are found to be cracked. DAL has stated that
Airbus Canada would not be able to provide support for OOPP. DAL
pointed out that paragraph (i)(2) of the proposed AD states that for
any requirement to obtain instructions from a manufacturer, that it
should use a method approved by the Manager, New York ACO Branch, FAA;
or TCCA; or Airbus Canada's TCCA Design Approval Organization (DAO).
DAL proposed that the proposed AD be revised to add an exception that
states that replacement of damaged structural elements would be
acceptable in lieu of a repair.
The FAA disagrees with the request. Paragraph (i)(2) provides for
receiving instructions from the Manager, New York ACO Branch, FAA, or
TCCA in lieu of instructions from Airbus Canada's DAO if the DAO cannot
provide repair instructions. Also, paragraph (i)(1) of this AD provides
procedures to request an AMOC to the methods required to be used in
this AD. AMOCs are issued after an AD has been issued and sufficient
data has been provided to show that the proposed alternate solution is
complete and addresses the unsafe condition. The FAA also does not
consider it appropriate to include various provisions or exceptions in
an AD applicable only to a single operator's unique circumstances. The
FAA has not changed this AD in this regard.

Request To Revise Inspection Report Requirement

DAL noted that paragraph (h)(6) of the proposed AD specified
reporting requirements. DAL perceived reporting requirements as a tool
to be used mostly to support efforts to understand statistical
probabilities of failure. DAL then considered that reporting findings
in situations where the airplane configuration deviates from the
configuration that the manufacturer is analyzing is possibly disruptive
to prediction models, and suggested revising the AD to exempt operators
from reporting in cases where the affected parts have been previously
repaired or replaced, particularly if it is a non-conforming
configuration.
The FAA does not agree to add an exemption for airplanes on which
an affected part has been repaired or replaced, even if it is not in a
configuration that conforms to a manufacturer's configuration. Reasons
to have a reporting requirement can extend beyond statistical analysis
for fatigue or aging of a part, and information from non-conforming
configurations can be beneficial in determining a corrective action.
The FAA has not changed this AD regarding this issue.
DAL also requested that the compliance time for reporting
inspection results be extended from 30 days to 180 days after the
inspection. DAL considered the 30 days to be too onerous considering
how long heavy maintenance visits take and that an inspection could be
conducted at the start of the visit, but the paper records might not be
received until 60 days after the inspection. DAL noted that an extended
time window will allow findings to be batched together for a group
report and preclude undue compliance issues related to late reporting.
The FAA disagrees with the request. TCCA specified 30 days and that
aligns with the FAA's standardized compliance time for inspection
reports. The FAA and Airbus Canada concur with TCCA's decision. The
manufacturer uses the reports to analyze the findings and to develop
new service information that incorporates those findings. However, once
this AD is published, any person may request approval of an AMOC under
the provisions of paragraph (i)(1) of this AD. The FAA has not changed
this AD regarding this issue.

Request To Remove Exception for No Flights With Cracking

DAL requested that the proposed exception in paragraph (h)(2) of
the proposed AD be removed. DAL explained that both TCCA ADs CF-2020-32
and CF-2020-32R1 state to repair cracks or damage by using certain
service information, and that the steps state that the damage is to be
reported to and dispositioned by Airbus Canada, but no mention of any
fly-on allowance for documented crack or damage findings.
The FAA disagrees with the request. In both TCCA ADs CF-2020-32 and
CF-2020-32R1, there is no phrase that specifically states that the
repair is to be done before further flight. Therefore, operators might
inadvertently determine that the compliance times specified in

[[Page 66943]]

both TCCA ADs CF-2020-32 and CF-2020-32R1 are for both accomplishing
the inspections and repairs. The FAA found it necessary to clarify that
it does not intend to allow flight with known cracking. The FAA has not
changed this AD regarding this issue.

Request To Revise Description of Root Cause

DAL requested that the Discussion section of the NPRM be updated to
reflect new information on the number of aft WTBF configurations. DAL
pointed out that the Discussion section stated that ``the cracking
reportedly begins earlier on airplanes with the latest of the two aft
WTBF configurations.'' DAL acknowledged that the statement may have
been true at the time of drafting, but added that the FAA should be
informed that there is a third WTBF configuration which includes
additional structure.
The FAA concurs with the request, however the content of the
Discussion section of the NPRM is not repeated in this AD.

Conclusion

The FAA reviewed the relevant data, considered the comments
received, and determined that air safety requires adopting this AD as
proposed. Except for minor editorial changes, and any other changes
described previously, 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

TCCA ADs CF-2020-32 and CF-2020-32R1 specify procedures for doing
repetitive detailed visual inspections of the aft WTBF structure for
any cracking or damage (including, but not limited to, cracking),
adjusting the load on the two tie-rods at fuselage station (FS) 973,
reporting inspection results, and repairing any cracked or damaged WTBF
structure. These documents are unique because TCCA AD CF-2020-32R1
includes revised compliance times for certain airplanes. 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.

Interim Action

The FAA considers that this AD is an interim action. If final
action is later identified, the FAA might consider further rulemaking
then.

Costs of Compliance

The FAA estimates that this AD affects 54 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:

Estimated Costs for Required Actions *
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
9 work-hours x $85 per hour = $765........................... $0 $765 $41,310
----------------------------------------------------------------------------------------------------------------
* Table does not include estimated costs for reporting.

The FAA estimates that it would take about 1 work-hour per product
to comply with the reporting requirement in this AD. The average labor
rate is $85 per hour. Based on these figures, the FAA estimates the
cost of reporting on U.S. operators to be $4,590, or $85 per product.
The FAA has received no definitive data on which to base the cost
estimates for the on-condition repairs specified in this AD.

Paperwork Reduction Act

A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a currently valid OMB Control Number. The OMB
Control Number for this information collection is 2120-0056. Public
reporting for this collection of information is estimated to take
approximately 1 hour per response, including the time for reviewing
instructions, searching existing data sources, gathering and
maintaining the data needed, and completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Send comments regarding this burden estimate
or any other aspect of this collection of information, including
suggestions for reducing this burden, to: Information Collection
Clearance Officer, Federal Aviation Administration, 10101 Hillwood
Parkway, Fort Worth, TX 76177-1524.

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.

The Amendment

Accordingly, under the authority delegated to me by the
Administrator,

[[Page 66944]]

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:

2021-22-17 Airbus Canada Limited Partnership (Type Certificate
Previously Held by C Series Aircraft Limited Partnership (CSALP);
Bombardier, Inc.): Amendment 39-21790; Docket No. FAA-2021-0201;
Project Identifier MCAI-2020-01346-T.

(a) Effective Date

This airworthiness directive (AD) is effective December 29,
2021.

(b) Affected ADs

None.

This AD applies to all Airbus Canada Limited Partnership (type
certificate previously held by C Series Aircraft Limited Partnership
(CSALP); Bombardier, Inc.) Model BD-500-1A10 and BD-500-1A11
airplanes, certificated in any category.

(d) Subject

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

(e) Reason

This AD was prompted by a report of cracking in the longeron,
frame, and tie-rod on left and right sides of the aft wing-to-body
fairing (WTBF) structure near the tie-rod attachment at fuselage
station (FS) 973; this cracking likely resulted from excessive tie-
rod preload. The FAA is issuing this AD to address such cracking,
which could lead to loss of aft WTBF integrity and result in damage
due to parts departing the airplane, loss of the radio altimeter,
and effects on airplane stability and performance.

(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, Transport Canada Civil Aviation (TCCA) AD CF-2020-
32, dated September 25, 2020 (TCCA AD CF-2020-32); or TCCA AD CF-
2020-32R1, dated April 23, 2021 (TCCA AD CF-2020-32R1).

(h) Exceptions to TCCA AD CF-2020-32 and TCCA AD CF-2020-32R1

(1) Where TCCA AD CF-2020-32 and TCCA AD CF-2020-32R1 refer to
its effective date, this AD requires using the effective date of
this AD.
(2) Where TCCA AD CF-2020-32R1 refers to the effective date of
TCCA AD CF-2020-32 (October 9, 2020), this AD requires using the
effective date of this AD.
(3) Where paragraphs B. and E. of TCCA AD CF-2020-32 and Part II
and V of TCCA AD CF-2020-32R1 specify to repair ``any cracks or
damage'' at certain compliance times or intervals, this AD requires
repairing any cracks or damage before further flight.
(4) Where TCCA AD CF-2020-32 and TCCA AD CF-2020-32R1 refer to
hours air time, this AD requires using flight hours.
(5) Where table 1 of TCCA AD CF-2020-32 specifies a compliance
time ``for new aeroplanes with an aeroplane date of manufacture, as
identified on the identification plate of the aeroplane, dated on or
after the effective date of this AD'' and table 1 of TCCA AD CF-
2020-32R1 specifies a compliance time ``for new aeroplanes with an
aeroplane date of manufacture, as identified on the identification
plate of the aeroplane, dated on or after the effective date of AD
CF-2020-32 (9 October 2020),'' for this AD use ``for airplanes with
a date of manufacture, as identified on the identification plate of
the airplane, dated on or after the effective date of this AD.''
(6) Where TCCA AD CF-2020-32 and TCCA AD CF-2020-32R1 define the
``applicable [aircraft maintenance publication] AMP [data module]
DM,'' replace the text ``Airbus Canada Limited Partnership AMP DM
BD500-A-J53-82-55-04AAA-720A-A (Aft fairing strut, Wing To Body
Fairing (WTBF)--Install procedure) Issue 006, dated 26 June 2020, or
later revisions,'' with the ``Airbus Canada Limited Partnership AMP
DM BD500-A-J53-82-55-04AAA-720A-A (Aft fairing strut, Wing To Body
Fairing (WTBF)--Install procedure) Issue 006, dated 26 June 2020; or
later revisions approved by the Manager, New York ACO Branch, FAA,
or TCCA, or Airbus Canada's TCCA Design Approval Organization (DAO).
If approved by the DAO, the approval must include the DAO-authorized
signature.''
(7) Paragraph D. of TCCA AD CF-2020-32 and Part IV of TCCA AD
CF-2020-32R1 specify to report inspection results to Airbus Canada
Limited Partnership within a certain compliance time. For this AD,
report inspection results at the applicable time specified in
paragraph (h)(7)(i) or (ii) of this AD.
(i) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(ii) If the inspection was done before the effective date of
this AD: Submit the report within 30 days after the effective date
of this AD.

(i) Additional AD Provisions

The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York ACO 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 manager of the certification
office, send it to ATTN: Program Manager, Continuing Operational
Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 516-228-7300; tax 516-794-5531. 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, New York ACO
Branch, FAA; or TCCA; or Airbus Canada's TCCA Design Approval
Organization (DAO). If approved by the DAO, the approval must
include the DAO-authorized signature.
(3) Paperwork Reduction Act Burden Statement: A federal agency
may not conduct or sponsor, and a person is not required to respond
to, nor shall a person be subject to a penalty for failure to comply
with a collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 1
hour per response, including the time for reviewing instructions,
searching existing data sources, gathering and maintaining the data
needed, and completing and reviewing the collection of information.
All responses to this collection of information are mandatory as
required by this AD. Send comments regarding this burden estimate or
any other aspect of this collection of information, including
suggestions for reducing this burden to Information Collection
Clearance Officer, Federal Aviation Administration, 10101 Hillwood
Parkway, Fort Worth, TX 76177-1524.

(j) Related Information

For more information about this AD, contact Antariksh Shetty,
Aerospace Engineer, Airframe and Propulsion Section, FAA, New York
ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
telephone 516-228-7300; fax 516-794-5531; email <a href="/cdn-cgi/l/email-protection#41786c2037326c2f3820222e6c222e32012720206f262e37">[email&#160;protected]</a>.

(k) 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) Transport Canada Civil Aviation (TCCA) AD CF-2020-32, dated
September 25, 2020 (TCCA AD CF-2020-32).
(ii) Transport Canada Civil Aviation (TCCA) AD CF-2020-32R1,
dated April 23, 2021 (TCCA AD CF-2020-32R1).
(3) For TCCA AD CF-2020-32 and TCCA AD CF-2020-32R1, contact
Transport Canada National Aircraft Certification, 159 Cleopatra
Drive, Nepean, Ontario K1A 0N5,

[[Page 66945]]

Canada; telephone 888-663-3639; email <a href="/cdn-cgi/l/email-protection#4001046d030e0034236e27236e2321">[email&#160;protected]</a>; internet
<a href="https://tc.canada.ca/en/aviation">https://tc.canada.ca/en/aviation</a>.
(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.
(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
<a href="/cdn-cgi/l/email-protection#5533277b3c3b26253036213c3a3b153b3427347b323a23">[email&#160;protected]</a>, or go to: <a href="https://www.archives.gov/federal-register/cfr/ibr-locations.html">https://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

Issued on October 19, 2021.
Ross Landes,
Deputy Director for Regulatory Operations, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021-25532 Filed 11-23-21; 8:45 am]
BILLING CODE 4910-13-P

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This is legal information, not legal advice. Laws vary by jurisdiction and change frequently. Always verify current law with official sources and consult a licensed attorney in your jurisdiction for advice on your specific situation.