[Federal Register Volume 82, Number 160 (Monday, August 21, 2017)]
[Rules and Regulations]
[Pages 39523-39525]
[FR Doc No: 2017-17085]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0270; Product Identifier 2016-SW-032-AD; Amendment
39-18993; AD 2017-17-03]
RIN 2120-AA64

Airworthiness Directives; MD Helicopters, Inc., Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2014-16-01 for
MD Helicopters, Inc. (MDHI), Model MD900 helicopters. AD 2014-16-01
required an eddy current inspection of the main rotor upper hub
assembly (upper hub) for a crack. This AD requires additional
inspections and replacing the fillet seal. This AD was prompted by
three additional reports of upper hub cracks. The actions of this AD
are intended to prevent an unsafe condition on these products.

DATES: This AD is effective September 25, 2017.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of September
25, 2017.

ADDRESSES: For service information identified in this final rule,
contact MD Helicopters, Inc., Attn: Customer Support Division, 4555 E.
McDowell Rd., Mail Stop M615, Mesa, AZ 85215-9734; telephone 1-800-388-
3378; fax<PHONE_NUMBER>; or at http://www.mdhelicopters.com. You may
review the referenced service information at the FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321,
Fort Worth, TX 76177. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0270.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov in Docket No. FAA-2017-0270; or in person at the
Docket Management Facility between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD docket contains this AD, any
incorporated-by-reference information, the economic evaluation, any
comments received, and other information. The address for the Docket
Office (phone:<PHONE_NUMBER>) is Document Management Facility, 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: Eric Schrieber, Aviation Safety
Engineer, Los Angeles ACO Branch, Compliance and Airworthiness
Division, FAA, 3960 Paramount Blvd., Lakewood, California 90712;
telephone<PHONE_NUMBER>; email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to remove AD 2014-16-01, Amendment 39-17925 (79 FR 45322,
August 5, 2014) and add a new AD. AD 2014-16-01 applied to MDHI Model
MD900 helicopters, serial numbers 900-00008 through 900-00140, with an
upper hub part number (P/N) 900R2101006-105, -107, -109, or -111
installed. AD 2014-16-01 required eddy current inspecting the upper hub
and replacing it if there is a crack. The NPRM published in the Federal
Register on April 3, 2017 (82 FR 16138).
    The NPRM was prompted by reports of three additional cracks found
in the MD900 fleet. These cracks were not discovered by the one-time
eddy current inspection required by AD 2014-16-01, but were found
during regular maintenance of the upper hub. The NPRM proposed to
require for MDHI

MD900 helicopters with an upper hub, regardless of helicopter serial
number, repetitive visual inspections of the fillet seal and the areas
around the flexbeam boltholes for a crack and repetitive visual
inspections of the lead leg shims and bushings for corrosion around the
flexbeam boltholes. The NPRM also proposed repetitive ultrasonic eddy-
current inspections of the areas adjacent to the flexbeam boltholes for
a crack. If during any inspection there is corrosion or a crack, the
NPRM proposed replacing the upper hub before further flight. Finally,
after each inspection, the NPRM proposed installing a fillet seal to
the bushing and upper hub interface.

Comments

    We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM.

FAA's Determination

    We have reviewed the relevant information and determined that an
unsafe condition exists and is likely to exist or develop on other
helicopters of the same type design and that air safety and the public
interest require adopting the AD requirements as proposed.

Related Service Information Under 1 CFR Part 51

    MDHI has issued Service Bulletin SB900-125, dated February 19,
2016, which describes procedures for repetitive visual and eddy current
inspections of the upper hub upper and lower flexbeam bolthole areas
and for applying a fillet seal on the interface of the bushing and the
flex beam retention bolt hole.
    This service information 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.

Differences Between This AD and the Service Information

    The service information applies to upper hubs with 1,000 or more
hours TIS. This AD applies to all upper hubs regardless of hours TIS.
The service information applies to upper hub P/N 900R2101006-107 and -
109; this AD also applies to upper hub P/N 900R2101006-105 and -111.

Costs of Compliance

    We estimate that this AD affects 23 helicopters of U.S. Registry.
At an average labor rate of $85 per hour, we estimate that operators
may incur the following costs in order to comply with this AD.
    Inspecting the fillet seal around the flexbeam boltholes (100 hour
TIS inspection) requires about 1 work-hour, for a cost per helicopter
of $85 and a cost of $1,955 for the fleet, per inspection cycle.
Inspecting the flexbeam area and lead leg shims and bushings (annual
inspection) requires about 2 work-hours, for a cost per helicopter of
$170 and a cost of $3,910 for the fleet, per inspection cycle. Eddy
current inspecting (1,000 hour TIS inspection) the upper hub requires
about 2 work-hours, for a cost per helicopter of $170 and a cost of
$3,910 for the fleet.
    If required, replacing the upper hub requires about 11 work-hours,
and required parts would cost about $15,998, for a cost per helicopter
of $16,933. If required, replacing a missing or damaged fillet seal
requires about .5 work-hour, and required parts cost would be minimal,
for a cost per helicopter of $43.

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.
    We are 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

    We have determined that 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) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska to the extent
that a regulatory distinction is required, and
    (4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD)
2014-16-01, Amendment 39-17925 (79 FR 45322, August 5, 2014), and
adding the following new AD:

2017-17-03 MD Helicopters, Inc. (MDHI): Amendment 39-18993; Docket
No. FAA-2017-0270; Product Identifier 2016-SW-032-AD.

(a) Applicability

    This AD applies to Model MD900 helicopters with main rotor upper
hub assembly (upper hub) part number 900R2101006-105, -107, -109, or
-111 installed, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a cracked upper hub.
This condition could result in failure of the upper hub and
subsequent loss of control of the helicopter.

(c) Affected ADs

    This AD supersedes AD 2014-16-01, Amendment 39-17925 (79 FR
45322, August 5, 2014).

(d) Effective Date

    This AD becomes effective September 25, 2017.

(e) Compliance

    You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.

(f) Required Actions

    (1) Within 100 hours time-in-service (TIS), and thereafter at
intervals not to exceed 100 hours TIS:
    (i) Inspect the fillet seal around each flexbeam bolthole to
determine whether it adheres properly to the hub or bushing or is
missing. Indications of an improperly

adhered seal include lifting, bubbling, peeling away, drying out, or
cracking. If the fillet seal is not properly adhered or is missing,
before further flight, replace the fillet seal with sealant C232 or
equivalent by following the Accomplishment Instructions, paragraphs
2.D.(2) through 2.D.(5) and Figure 1, of MD Helicopters Service
Bulletin SB900-125, dated February 19, 2016 (SB900-125).
    (ii) Using a light and a 10X or higher power magnifying glass,
inspect the area outside of the fillet seal around each flexbeam
bolthole on the top of the upper hub assembly for a crack. If there
is a crack, before further flight, replace the upper hub assembly.
    (2) Within 12 months, and thereafter at intervals not to exceed
12 months:
    (i) Remove the paint and primer from the area around each
flexbeam bolthole on top of the upper hub. Remove the fillet seal
from the mating surface of each bushing and the top of the upper
hub.
    (ii) Using a light and a 10X or higher power magnifying glass,
inspect the area around each flexbeam bolthole for a crack. If there
is a crack, before further flight, replace the upper hub assembly.
    (iii) Inspect each lead leg shim and bushing for corrosion
around the flexbeam boltholes on the bottom of the upper hub in the
flexbeam pockets. If there is corrosion, before further flight:
    (A) Remove the lead leg shim from the flexbeam pocket and clean
the area adjacent to the flexbeam bolthole to remove any corrosion
within maximum repair damage limits. If the corrosion exceeds
maximum repair damage limits, replace the upper hub assembly.
    (B) Using a light and a 10X or higher power magnifying glass,
inspect the area around the flexbeam bolthole for a crack. If there
is a crack, before further flight, replace the upper hub assembly.
    (iv) Replace the fillet seal as described in paragraph (f)(1)(i)
of this AD.
    (3) Within 1,000 hours TIS, and thereafter at intervals not to
exceed 1,000 hours TIS:
    (i) Eddy current inspect the areas adjacent to each flexbeam
bolthole, top and bottom, for a crack. This eddy current inspection
must be performed by a Level II or higher technician with the
American Society for Nondestructive Testing ASNT-TC-1A, European
Committee for Standardization CEN EN 4179, Military Standard MIL-
STD-410, National Aerospace Standard NAS410, or equivalent
certification who has performed an eddy current inspection within
the last 12 months. If there is a crack, before further flight,
replace the upper hub assembly.
    (ii) Replace the fillet seal as described in paragraph (f)(1)(i)
of this AD.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles ACO Branch, FAA, may approve AMOCs
for this AD. Send your proposal to: Eric Schrieber, Aviation Safety
Engineer, Los Angeles ACO Branch, Compliance and Airworthiness
Division, FAA, 3960 Paramount Blvd., Lakewood, California 90712;
telephone<PHONE_NUMBER>; email<EMAIL_ADDRESS>    (2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office, before operating any aircraft
complying with this AD through an AMOC.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6220, Main Rotor
Head.

(i) 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 the AD specifies otherwise.
    (i) MD Helicopters Service Bulletin SB900-125, dated February
19, 2016.
    (ii) Reserved.
    (3) For MD Helicopters service information identified in this
AD, contact MD Helicopters, Inc., Attn: Customer Support Division,
4555 E. McDowell Rd., Mail Stop M615, Mesa, AZ 85215-9734; telephone
1-800-388-3378; fax<PHONE_NUMBER>; or at http://www.mdhelicopters.com.
    (4) You may view this service information at 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<PHONE_NUMBER>.
    (5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call<PHONE_NUMBER>, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on August 7, 2017.
Scott A. Horn,
Deputy Director for Regulatory Operations, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2017-17085 Filed 8-18-17; 8:45 am]
 BILLING CODE 4910-13-P


[Federal Register Volume 88, Number 67 (Friday, April 7, 2023)]
[Rules and Regulations]
[Pages 20738-20741]
[FR Doc No: 2023-07091]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-1473; Project Identifier MCAI-2022-00902-T;
Amendment 39-22363; AD 2023-04-16]
RIN 2120-AA64

Airworthiness Directives; Dassault Aviation Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2020-21-
20, which applied to certain Dassault Aviation Model FALCON 900EX
airplanes. AD 2020-21-20 required revising the existing maintenance or
inspection program, as applicable, to incorporate new or more
restrictive maintenance requirements and/or airworthiness limitations.
This AD was prompted by a determination that new or more restrictive
airworthiness limitations are necessary. This AD continues to require
the actions in AD 2020-21-20 and requires revising the existing
maintenance or inspection program, as applicable, to incorporate
additional new or more restrictive airworthiness limitations; as
specified in 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 May 12, 2023.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 12,
2023.
    The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
December 7, 2020 (85 FR 69144, November 2, 2020).

ADDRESSES:
    AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2022-1473; 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.
    Material Incorporated by Reference:
     For EASA material incorporated by reference in this AD,
contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone
+49 221 8999 000; email [email protected]; website easa.europa.eu. You
may find this material on the EASA website at ad.easa.europa.eu.
     You may view this material at the FAA, Airworthiness
Products Section, Operational Safety Branch, 2200 South 216th Street,
Des Moines, WA. For information on the availability of this material at
the FAA, call<PHONE_NUMBER>. It is also available in the AD docket at
regulations.gov under Docket No. FAA-2022-1473.

FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer,
Large Aircraft Section, International Validation Branch, FAA, 2200
South 216th Street, Des Moines, WA 98198; telephone<PHONE_NUMBER>; email
[email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2020-21-20, Amendment 39-21293 (85 FR
69144, November 2, 2020) (AD 2020-21-20). AD 2020-21-20 applied to
certain Dassault Aviation Model FALCON 900EX airplanes. AD 2020-21-20
required revising the existing maintenance or inspection program, as
applicable, to incorporate new or more restrictive maintenance
requirements and/or airworthiness limitations. The FAA issued AD 2020-
21-20 to address, among other things, fatigue cracking and damage in
principal structural elements; such fatigue cracking and damage could
result in reduced structural integrity of the airplane. AD 2020-21-20
specifies that accomplishing the actions required by paragraph (g) or
(i) of that AD terminates the requirements of paragraph (g)(1) of AD
2010-26-05, Amendment 39-16544 (75 FR 79952, December 21, 2010) for
Dassault Aviation Model FALCON 900EX airplanes, serial number (S/N) 97
and S/Ns 120 and higher. This AD therefore continues to allow that
terminating action.
    The NPRM published in the Federal Register on November 18, 2022 (87
FR 69214). The NPRM was prompted by AD 2022-0141, dated July 7, 2022,
issued by EASA (EASA AD 2022-0141) (referred to after this as the
MCAI). The MCAI states that new or more restrictive airworthiness
limitations have been developed.
    In the NPRM, the FAA proposed to continue to require the actions AD

2020-21-20. The NPRM also proposed to require revising the existing
maintenance or inspection program, as applicable, to incorporate
additional new or more restrictive airworthiness limitations, as
specified in EASA AD 2022-0141.
    The FAA is issuing this AD to address, among other things, fatigue
cracking and damage in principal structural elements. The unsafe
condition, if not addressed, could result in reduced structural
integrity of the airplane. You may examine the MCAI in the AD docket at
regulations.gov under Docket No. FAA-2022-1473.

Discussion of Final Airworthiness Directive

Comments

    The FAA received one comment from an anonymous commenter. The
following presents the comments received on the NPRM and the FAA's
response to each comment.

Request To Clarify Reason for Proposed AD

    The commenter requested more detail, and clarification of why the
FAA issued the proposed AD.
    The FAA agrees to clarify. EASA, which is the State of Design
Authority for the affected airplanes, issued the MCAI to address an
unsafe condition. The FAA reviewed the MCAI and concurred that an
unsafe condition is likely to exist or develop in the affected
airplanes. In order to require affected operators to accomplish the
proposed actions, the FAA must issue an airworthiness directive. The
FAA issued the proposed rule to provide interested parties the
opportunities to provide feedback, which the FAA considered before
issuing this AD. Once the AD is effective, operators must comply with
the required actions specified in this AD to ensure the identified
unsafe condition is addressed. The FAA did not change this AD as a
result of this comment.

Conclusion

    This product has been approved by the aviation authority of another
country and is approved for operation in the United States. Pursuant to
the FAA's bilateral agreement with this State of Design Authority, it
has notified the FAA of the unsafe condition described in the MCAI
referenced above. The FAA reviewed the relevant data, considered the
comment received, and determined that air safety requires adopting this
AD as proposed. Accordingly, the FAA is issuing this AD to address the
unsafe condition on this product. 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.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed EASA AD 2022-0141. This service information
specifies new or more restrictive airworthiness limitations for
airplane structures and safe life limits.
    This AD also requires EASA AD 2020-0117, dated May 20, 2020, which
the Director of the Federal Register approved for incorporation by
reference as of December 7, 2020 (85 FR 69144, November 2, 2020).
    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 191 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
    The FAA estimates the total cost per operator for the retained
actions from AD 2020-21-20 to be $7,650 (90 work-hours x $85 per work-
hour).
    The FAA has determined that revising the existing maintenance or
inspection program takes an average of 90 work-hours per operator,
although the agency recognizes that this number may vary from operator
to operator. Since operators incorporate maintenance or inspection
program changes for their affected fleet(s), the FAA has determined
that a per-operator estimate is more accurate than a per-airplane
estimate.
    The FAA estimates the total cost per operator for the new actions
to be $7,650 (90 work-hours x $85 per work-hour).

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, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive 2020-21-20, Amendment 39-21293 (85
FR 69144, November 2, 2020); and
0
b. Adding the following new airworthiness directive:

2023-04-16 Dassault Aviation: Amendment 39-22363; Docket No. FAA-
2022-1473; Project Identifier MCAI-2022-00902-T.

(a) Effective Date

    This airworthiness directive (AD) is effective May 12, 2023.

(b) Affected ADs

    (1) This AD replaces AD 2020-21-20, Amendment 39-21293 (85 FR
69144, November 2, 2020) (AD 2020-21-20).
    (2) This AD affects AD 2010-26-05, Amendment 39-16544 (75 FR
79952, December 21, 2010) (AD 2010-26-05).

(c) Applicability

    This AD applies to Dassault Aviation Model FALCON 900EX
airplanes, serial

number (S/N) 97 and S/Ns 120 and higher, certificated in any
category, with an original airworthiness certificate or original
export certificate of airworthiness issued on or before November 15,
2021.

(d) Subject

    Air Transport Association (ATA) of America Code: 05, Time
Limits/Maintenance Checks.

(e) Unsafe Condition

    This AD was prompted by a determination that new or more
restrictive airworthiness limitations are necessary. The FAA is
issuing this AD to address, among other things, fatigue cracking and
damage in principal structural elements. The unsafe condition, if
not addressed, could result in reduced structural integrity of the
airplane.

(f) Compliance

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

(g) Retained Revision of the Existing Maintenance or Inspection
Program, With a New Terminating Action

    This paragraph restates the requirements of paragraph (i) of AD
2020-21-20, with a new terminating action. For airplanes with an
original airworthiness certificate or original export certificate of
airworthiness issued on or before October 2, 2019: Except as
specified in paragraph (h) of this AD, comply with all required
actions and compliance times specified in, and in accordance with,
European Union Aviation Safety Agency (EASA) AD 2020-0117, dated May
20, 2020 (EASA AD 2020-0117). Accomplishing the revision of the
existing maintenance or inspection program required by paragraph (j)
of this AD terminates the requirements of this paragraph.

(h) Retained Exceptions to EASA AD 2020-0117 With No Changes

    This paragraph restates the exceptions specified in paragraph
(j) of AD 2020-21-20, with no changes.
    (1) The requirements specified in paragraphs (1) and (2) of EASA
AD 2020-0117 do not apply to this AD.
    (2) Paragraph (3) of EASA AD 2020-0117 specifies revising ``the
approved AMP'' within 12 months after its effective date, but this
AD requires revising the existing maintenance or inspection program,
as applicable, to incorporate the ``limitations, tasks and
associated thresholds and intervals'' specified in paragraph (3) of
EASA AD 2020-0117 within 90 days after December 7, 2020 (the
effective date of AD 2020-21-20).
    (3) The initial compliance time for doing the tasks specified in
paragraph (3) of EASA AD 2020-0117 is at the applicable ``associated
thresholds'' specified in paragraph (3) of EASA AD 2020-0117, or
within 90 days after December 7, 2020 (the effective date of AD
2020-21-20), whichever occurs later.
    (4) The provisions specified in paragraphs (4) and (5) of EASA
AD 2020-0117 do not apply to this AD.
    (5) The ``Remarks'' section of EASA AD 2020-0117 does not apply
to this AD.

(i) Retained Restrictions on Alternative Actions and Intervals, With a
New Exception

    This paragraph restates the requirements of paragraph (k) of AD
2020-21-20, with a new exception. Except as required by paragraph
(j) of this AD, after the maintenance or inspection program has been
revised as required by paragraph (g) of this AD, no alternative
actions (e.g., inspections) and intervals are allowed unless they
are approved as specified in the provisions of the ``Ref.
Publications'' section of EASA AD 2020-0117.

(j) New Revision of the Existing Maintenance or Inspection Program

    Except as specified in paragraph (k) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, EASA AD 2022-0141, dated July 7, 2022.
Accomplishing the revision of the existing maintenance or inspection
program required by this paragraph terminates the requirements of
paragraph (g) of this AD.

(k) Exceptions to EASA AD 2022-0141

    (1) The requirements specified in paragraphs (1) and (2) of EASA
AD 2022-0141 do not apply to this AD.
    (2) Paragraph (3) of EASA AD 2022-0141 specifies revising ``the
approved AMP'' within 12 months after its effective date, but this
AD requires revising the existing maintenance or inspection program,
as applicable, within 90 days after the effective date of this AD.
    (3) The initial compliance time for doing the tasks specified in
paragraph (3) of EASA 2022-0141 is at the applicable ``limitations''
and ``associated thresholds'' as incorporated by the requirements of
paragraph (3) of EASA AD 2022-0141, or within 90 days after the
effective date of this AD, whichever occurs later.
    (4) The provisions specified in paragraphs (4) and (5) of EASA
AD 2022-0141 do not apply to this AD.
    (5) The ``Remarks'' section of EASA AD 2022-0141 does not apply
to this AD.

(l) New Provisions for Alternative Actions and Intervals

    After the existing maintenance or inspection program has been
revised as required by paragraph (j) of this AD, no alternative
actions (e.g., inspections) and intervals are allowed unless they
are approved as specified in the provisions of the ``Ref.
Publications'' section of EASA AD 2022-0141.

(m) Terminating Action for Certain Actions in AD 2010-26-05

    Accomplishing the actions required by paragraph (g) or (j) of
this AD terminates the requirements of paragraph (g)(1) of AD 2010-
26-05, for Dassault Aviation Model FALCON 900EX airplanes, S/N 97
and S/Ns 120 and higher only.

(n) Additional AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
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 International
Validation Branch, send it to the attention of the person identified
in paragraph (o) 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, International
Validation Branch, FAA; or EASA; or Dassault Aviation's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.

(o) Additional Information

    For more information about this AD, contact Tom Rodriguez,
Aerospace Engineer, Large Aircraft Section, International Validation
Branch, FAA, 2200 South 216th Street, Des Moines, WA 98198;
telephone<PHONE_NUMBER>; email [email protected].

(p) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on
May 12, 2023.
    (i) European Union Aviation Safety Agency (EASA) AD 2022-0141,
dated July 7, 2022.
    (ii) [Reserved]
    (4) The following service information was approved for IBR on
December 7, 2020 (85 FR 69144, November 2, 2020).
    (i) European Union Aviation Safety Agency (EASA) AD 2020-0117,
dated May 20, 2020.
    (ii) [Reserved]
    (5) For EASA ADs 2020-0117 and 2022-0141, contact EASA, Konrad-
Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000;
email [email protected]; website easa.europa.eu. You may find these
EASA ADs on the EASA website at ad.easa.europa.eu.
    (6) You may view this material at the FAA, Airworthiness
Products Section, Operational Safety Branch, 2200 South 216th
Street, Des Moines, WA. For information on the availability of this
material at the FAA, call<PHONE_NUMBER>.
    (7) 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: www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on February 17, 2023.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2023-07091 Filed 4-6-23; 8:45 am]
BILLING CODE 4910-13-P