[Federal Register Volume 89, Number 204 (Tuesday, October 22, 2024)]
[Rules and Regulations]
[Pages 84277-84280]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-24368]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-1480; Project Identifier MCAI-2023-00930-A; 
Amendment 39-22851; AD 2024-19-09]
RIN 2120-AA64


Airworthiness Directives; DAHER (Type Certificate Previously Held 
by SOCATA) Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2016-08-08 
for all SOCATA (type certificate now held by DAHER) Model MS 880B, MS 
885, MS 892A-150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS 894E, 
Rallye 100S, Rallye 150ST, Rallye 150T, Rallye 235C, and Rallye 235E 
airplanes. AD 2016-08-08 required doing repetitive detailed visual 
inspections of the intersection between the axle radius and the nose 
landing gear (NLG) fork area for chafing; doing repetitive dye 
penetrant inspections on the NLG wheel axle for cracks, distortion, and 
nicks or wear; doing corrective actions if necessary; and replacing the 
NLG wheel axle attachment screws with new screws. This AD is prompted 
by the introduction of a new inspection method and a new design for the 
affected NLG wheel axle that provides terminating action for the 
repetitive inspections, as specified in updated service information 
published by the manufacturer. This AD requires preparing, inspecting, 
replacing, reconditioning the NLG wheel axle, and prohibiting affected 
parts. The FAA is issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective November 26, 2024.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 26, 
2024.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2024-1480; 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:
    <bullet> For Daher Aerospace material identified in this AD, 
contact Daher Aerospace, Customer Support, Airplane Division, 65921 
Tarbes Cedex 9, France; phone: 33 (0)5 62.41.73.00; email: 
<a href="/cdn-cgi/l/email-protection#f682949b95978493b6ca97d69e849390cb" http: daher.com">daher.com</a>">tbmcare@daher.com</a>; website: daher.com.
    <bullet> You may view this material at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 901 Locust, Kansas City, 
MO 64106. For information on the availability of this material at the 
FAA, call (817) 222-5110. It is also available at regulations.gov under 
Docket No. FAA-2024-1480.

FOR FURTHER INFORMATION CONTACT: Fred Guerin, Aviation Safety Engineer, 
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (206) 
231-2346; email: <a href="/cdn-cgi/l/email-protection#e583978081cb829080978c8ba5838484cb828a93"><span class="__cf_email__" data-cfemail="23455146470d445646514a4d634542420d444c55">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2016-08-08, Amendment 39-18484 (81 FR 
21711, April 13, 2016) (AD 2016-08-08). AD 2016-08-08 applied to SOCATA 
(type certificate now held by DAHER) Model MS 880B, MS 885, MS 892A-
150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS 894E, Rallye 100S, 
Rallye 150ST, Rallye 150T, Rallye 235C, and Rallye 235E airplanes.
    AD 2016-08-08 was prompted by MCAI originated by European Union 
Aviation Safety Agency (EASA), which is the Technical Agent for the 
Member States of the European Union. EASA issued AD 2015-0203, dated 
October 7, 2015 (EASA AD 2015-0203) to correct an unsafe condition 
identified as fatigue failure of the NLG wheel axle. EASA AD 2015-0203 
was prompted by an NLG wheel axle failure that occurred in service. The 
investigation revealed that this failure was due to fatigue caused by 
premature wear. EASA AD 2015-0203 required retaining the requirements 
of Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) France 
AD 91-163(A)R2, dated March 30, 1994, which was superseded, but 
required those actions to be accomplished within reduced intervals.
    AD 2016-08-08 required doing repetitive detailed visual inspections 
of the intersection between the axle radius and the NLG fork area for 
chafing; doing repetitive dye penetrant inspections on the NLG wheel 
axle for cracks, distortion, and nicks or wear; corrective actions if 
necessary; and replacing the NLG wheel axle attachment screws with new 
screws. The FAA issued AD 2016-08-08 to address chafing and cracking of 
the NLG wheel axle, which could lead to failure of the NLG with 
consequent damage to the airplane and/or injury to occupants.
    Since the FAA issued AD 2016-08-08, EASA superseded EASA AD 2015-
0203 and issued EASA AD 2023-0080, dated April 17, 2023 (EASA AD 2023-
0080) (also referred to as the MCAI) to correct an unsafe condition for 
all DAHER AEROSPACE Model MS 880 B, MS 880 B-D, MS 881, MS 883, MS 884, 
MS 885, MS 886, MS 887, MS 890 A, MS 890 B, MS 892 A.150, MS 892 B.150, 
MS 892 E.150, MS 892 E-D.150, MS 893 A, MS 893 B, MS 893 E, MS 893 E-D, 
MS 894 A, MS 894 E, RALLYE 100 S, RALLYE 100 S-D, RALLYE 100 ST, RALLYE 
100 ST-D, RALLYE 110 ST, RALLYE 150 ST, RALLYE 150 ST-D, RALLYE 150 T, 
RALLYE 150 T-D, RALLYE 150 SV, RALLYE 150 SVS, RALLYE 180 T, RALLYE 180 
TS, RALLYE 180 T-D, RALLYE 235 A, RALLYE 235 F, RALLYE 235 E, and 
RALLYE 235 E-D airplanes.
    The MCAI states that it retains the requirements of EASA AD 2015-
0203 but introduces a new inspection method and a new design of the NLG 
wheel axle as a terminating action for the repetitive detailed 
inspections. You may examine the MCAI in the AD docket at 
regulations.gov under Docket No. FAA-2024-1480.
    The NPRM published in the Federal Register on June 4, 2024 (89 FR 
47879). In the NPRM, the FAA proposed to

[[Page 84278]]

retain none of the requirements of AD 2016-08-08. The NPRM proposed to 
require repetitively inspecting the NLG wheel axle and, if chafing, 
cracking, or damage was found, installing the newly designed NLG wheel 
axle and attachment screws, which would terminate the actions specified 
in the proposed AD. The NPRM also proposed a magnetic particle 
inspection after a visual inspection if no damage was found, or when 
installing an airworthy part that was previously in service. The NPRM 
also proposed to require repetitively replacing the NLG wheel axle 
attachment screws.

Discussion of Final Airworthiness Directive

Comments

    The FAA received no comments on the NPRM or on the determination of 
the costs.

Change Since NPRM Was Published

    The NPRM proposed to require repetitively replacing the NLG wheel 
axle attachment screws every 2,000 hours time-in-service (TIS). The FAA 
re-evaluated this requirement and determined that clarification of the 
intent of this requirement is needed. The FAA revised paragraph (i) of 
this AD to clarify that any screw found to be distorted, scratched, 
nicked, or worn during any repetitive inspection required by paragraph 
(h)(1) of this AD must be replaced before further flight. If no screw 
is found to be distorted, scratched, nicked, or worn during any 
repetitive inspection required by paragraph (h)(1) of this AD, all of 
the NLG wheel axle attachment screws must be replaced initially before 
exceeding 2,000 hours TIS total on the airplane; before exceeding 2,000 
hours TIS since the last time the attachment screws were replaced; or 
within 50 hours TIS after the effective date of this AD, whichever 
occurs later, and repetitively thereafter at intervals not to exceed 
2,000 hours TIS after the last replacement.

Conclusion

    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 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 and 
determined that air safety requires adopting this AD as proposed. 
Accordingly, the FAA is issuing this AD to address the unsafe condition 
on these products. Except for the change described previously, this AD 
is adopted as proposed in the NPRM. This change will not increase the 
economic burden on any operator.

Material Incorporated by Reference Under 1 CFR Part 51

    The FAA reviewed Daher Service Bulletin SB 150, Revision 4, dated 
January 2023. This material specifies procedures for preparing, 
inspecting, replacing, and reconditioning the NLG wheel axle. This 
material also specifies procedures for replacing the NLG wheel axle 
attachment screws.
    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.

Differences Between This AD and the MCAI

    The applicability of the MCAI includes DAHER AEROSPACE Model MS 
886, MS 887, MS 890 A, MS 890 B, MS 892 B.150, MS 892 E-D.150, MS 893 
B, MS 893 E-D, RALLYE 100 S-D, RALLYE 100 ST, RALLYE 100 ST-D, RALLYE 
110 ST, RALLYE 150 ST-D, RALLYE 150 T-D, RALLYE 150 SV, RALLYE 150 SVS, 
RALLYE 180 T, RALLYE 180 TS, RALLYE 180 T-D, RALLYE 235 A, RALLYE 235 
F, and RALLYE 235 E-D airplanes and the applicability of this AD does 
not because these models do not have an FAA type certificate.

Costs of Compliance

    The FAA estimates that this AD affects 32 airplanes of U.S. 
registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Magnetic particle inspection....  1 work-hour x $85   $100..............  $185..............  $5,920.
                                   per hour = $85.
Inspection of the NLG wheel       2 work-hours x $85  $100..............  $270 (per           $8,640.
 bearing and axle surface and      per hour = $170                         inspection cycle).
 attachment screws.                (per inspection
                                   cycle).
NLG wheel axle attachment screw   1 work-hour x $85   $50 (per cycle)...  $135 (per cycle)..  $4,320 (per
 replacement.                      per hour = $85                                              cycle).
                                   (per cycle).
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary action 
that would be required based on the results of the inspections. The 
agency has no way of determining the number of airplanes that might 
need this action:

                                               On-condition costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Installation of a nose gear wheel axle         2 work-hours x $85 per hour =            $1,000           $1,170
 (including NLG wheel spacer) and attachment    $170.
 screw replacement.
----------------------------------------------------------------------------------------------------------------

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.

[[Page 84279]]

    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 has 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) 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 2016-08-08, Amendment 39-18484 (81 
FR 21711, April 13, 2016); and
0
b. Adding the following new airworthiness directive:

2024-19-09 DAHER (Type Certificate previously held by SOCATA): 
Amendment 39-22851; Docket No. FAA-2024-1480; Project Identifier 
MCAI-2023-00930-A.

(a) Effective Date

    This airworthiness directive (AD) is effective November 26, 
2024.

 (b) Affected ADs

    This AD replaces AD 2016-08-08, Amendment 39-18484 (81 FR 21711, 
April 13, 2016).

 (c) Applicability

    This AD applies to DAHER (type certificate previously held by 
SOCATA) Model MS 880B, MS 885, MS 892A-150, MS 892E-150, MS 893A, MS 
893E, MS 894A, MS 894E, Rallye 100S, Rallye 150ST, Rallye 150T, 
Rallye 235C, and Rallye 235E airplanes, all serial numbers, 
certificated in any category.

 (d) Subject

    Joint Aircraft System Component (JASC) Code 3220, Nose/Tail 
Landing Gear.

 (e) Unsafe Condition

    This AD was prompted by a report of a nose landing gear (NLG) 
wheel axle failure in service. The FAA is issuing this AD to address 
chafing and cracking of the NLG wheel axle. The unsafe condition, if 
not addressed, could lead to failure of the NLG with consequent 
damage to the airplane and injury to occupants.

 (f) Compliance

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

 (g) Definitions

    For the purpose of this AD the following definitions apply:
    (1) Group 1 Airplanes: Airplanes having any affected parts 
installed as of the effective date of this AD.
    (2) Group 2 Airplanes: Airplanes that do not have any affected 
parts installed as of the effective date of this AD.
    (3) Affected Parts: NLG wheel axles having part number (P/N) 
8954200270 and NLG wheel spacer having P/N 8954200260.
    (4) Serviceable Parts: NLG wheel axles having P/N AV-RAL-001-01 
and NLG wheel spacer having P/N AV-RAL-002-01.
    (5) New Part: Any part that has zero hours time-in-service 
(TIS).

 (h) Inspections and Axle Replacement For Group 1 Airplanes

    (1) Within 200 hours TIS after the effective date of this AD, 
and thereafter at intervals not to exceed 200 hours TIS, perform a 
detailed visual inspection for chafing and cracking between the NLG 
wheel bearing and axle surface in accordance with paragraphs B.1 and 
B.2 of Daher Service Bulletin SB 150, Revision 4, dated January 2023 
(Daher SB 150, Revision 4).
    (2) If any chafing or cracking is found during any inspection 
required by paragraph (h)(1) of this AD, before further flight, 
replace the NLG wheel axle with one of the following:
    (i) An NLG wheel axle that is found to be free of chafing and 
cracking per the inspection required by paragraph (h)(1) of this AD 
and free of damage per the inspection required by paragraph (h)(3) 
of this AD.
    (ii) Serviceable parts, as defined in this AD, in accordance 
with paragraphs C.2 through C.4 of Daher SB 150, Revision 4. This 
part installation makes the airplane a Group 2 airplane and 
terminates the inspection requirements in this AD.
    (3) If no chafing or cracking is found during any inspection 
required by paragraph (h)(1) of this AD, before further flight, do a 
magnetic particle inspection of the NLG wheel axle for damage 
(distortion, nicks, wear, and cracking).
    (4) If any damage is found during any magnetic particle 
inspection required by paragraph (h)(3) of this AD, before further 
flight, replace the NLG wheel axle with one of the following:
    (i) An NLG wheel axle that is found to be free of chafing and 
cracking per the inspection required by paragraph (h)(1) of this AD 
and free of damage per the inspection required by paragraph (h)(3) 
of this AD.
    (ii) Serviceable parts, as defined in this AD, in accordance 
with paragraphs C.2 through C.4 of Daher SB 150, Revision 4. This 
part installation makes the airplane a Group 2 airplane and 
terminates the inspection requirements in this AD.

 (i) NLG Wheel Axle Attachment Screw Replacement For Group 1 and Group 
2 Airplanes

    Replace the NLG wheel axle attachment screws in accordance with 
paragraph C.2 of Daher SB 150, Revision 4, as follows:
    (1) If no screw is found to be distorted, scratched, nicked, or 
worn during any repetitive inspection required by paragraph (h)(1) 
of this AD, replace all of the NLG wheel axle attachment screws as 
follows:
    (i) Initially before exceeding 2,000 hours TIS total on the 
airplane; before exceeding 2,000 hours TIS since the last time the 
attachment screws were replaced; or within 50 hours TIS after the 
effective date of this AD, whichever occurs later; and
    (ii) Repetitively thereafter at intervals not to exceed 2,000 
hours TIS after the last replacement.
    (2) If any screw is found to be distorted, scratched, nicked, or 
worn during any repetitive inspection required by paragraph (h)(1) 
of this AD, replace that screw before further flight.

 (j) Installation Prohibition For Group 1 and Group 2 Airplanes

    As of the effective date of this AD, do not install an affected 
NLG wheel axle, as defined in this AD, on any airplane, unless the 
criteria in paragraphs (j)(1) and (2) of this AD are met:
    (1) The affected NLG wheel axle is found to be free of chafing 
and cracking per the inspection required by paragraph (h)(1) of this 
AD and free of damage per the inspection required by paragraph 
(h)(3) of this AD.
    (2) The NLG wheel axle attachment screws are replaced with new 
screws.

 (k) Credit for Previous Actions

    You may take credit for the initial actions required by 
paragraphs (h) and (i) of this AD if you performed those actions 
before the effective date of this AD using SOCATA SB

[[Page 84280]]

150, Revision 2; or Daher-SOCATA SB 150, Revision 3.

 (l) 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 local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Validation Branch, mail 
it to the address identified in paragraph (m)(1) of this AD or email 
to: <a href="/cdn-cgi/l/email-protection#52131f1d11123433337c353d24"><span class="__cf_email__" data-cfemail="21606c6e62614740400f464e57">[email protected]</span></a>. If mailing information, also submit information by 
email. Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local Flight Standards Office.

 (m) Additional Information

    (1) For more information about this AD, contact Fred Guerin, 
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; phone: (206) 231-2346; email: 
<a href="/cdn-cgi/l/email-protection#7f190d1a1b51180a1a0d16113f191e1e51181009"><span class="__cf_email__" data-cfemail="066074636228617363746f684660676728616970">[email protected]</span></a>.
    (2) Material identified in this AD that is not incorporated by 
reference is available at the address specified in paragraph (n)(3) 
of this AD.

 (n) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the material listed in this 
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this material as applicable to do the actions 
required by this AD, unless the AD specifies otherwise.
    (i) Daher Service Bulletin SB 150, Revision 4, dated January 
2023.
    (ii) [Reserved]
    (3) For Daher Aerospace material identified in this AD, contact 
Daher Aerospace, Customer Support, Airplane Division, 65921 Tarbes 
Cedex 9, France; phone: 33 (0)5 62.41.73.00; email: 
<a href="/cdn-cgi/l/email-protection#1b6f7976787a697e5b277a3b73697e7d26" http: daher.com">daher.com</a>">tbmcare@daher.com</a>; website: daher.com.
    (4) You may view this material at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 901 Locust, Kansas 
City, MO 64106. For information on the availability of this material 
at the FAA, call (817) 222-5110.
    (5) You may view this material at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email <a href="/cdn-cgi/l/email-protection#b1d7c39fd8dfc2c1d4d2c5d8dedff1dfd0c3d09fd6dec7"><span class="__cf_email__" data-cfemail="0e687c2067607d7e6b6d7a6761604e606f7c6f20696178">[email protected]</span></a>.

    Issued on October 10, 2024.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2024-24368 Filed 10-21-24; 8:45 am]
BILLING CODE 4910-13-P


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