[Federal Register Volume 89, Number 78 (Monday, April 22, 2024)]
[Rules and Regulations]
[Pages 29247-29252]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-08539]



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 Rules and Regulations
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  Federal Register / Vol. 89, No. 78 / Monday, April 22, 2024 / Rules 
and Regulations  

[[Page 29247]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2023-2143; Project Identifier MCAI-2023-00088-A; 
Amendment 39-22718; AD 2024-06-13]
RIN 2120-AA64


Airworthiness Directives; Diamond Aircraft Industries GmbH 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2022-21-15 
for certain Diamond Aircraft Industries GmbH (DAI) Model DA 42, DA 42 
NG, and DA 42 M-NG airplanes. AD 2022-21-15 required replacing the 
rudder T-yoke axle with an improved rudder T-yoke axle. Since the FAA 
issued AD 2022-21-15, the European Union Aviation Safety Agency (EASA) 
superseded its mandatory continuing airworthiness information (MCAI) to 
correct an unsafe condition on these products. This AD requires, for 
certain airplanes, inspecting the rudder steering bracket edge distance 
and depending on the inspection results, inspecting the T-yoke bolt 
hole for wear and play, and corrective action if necessary. For certain 
airplanes this AD requires replacing the rudder T-yoke bolt (axle) with 
a serviceable part, installing a new self-locking nut, and applying 
torque seal marks on the rudder T-yoke bolt head and self-locking nut. 
For all airplanes this AD requires repetitively inspecting the torque 
seal marks on the rudder T-yoke bolt head for proper alignment and the 
self-locking nut for proper installation and corrective action if 
necessary. This AD also prohibits the installation of affected parts. 
The FAA is issuing this AD to address the unsafe condition on these 
products.

DATES: This AD is effective May 28, 2024.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of May 28, 2024.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2023-2143; 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 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 service information contact Diamond Aircraft 
Industries GmbH, N.A. Otto-Stra[szlig]e 5, A-2700 Wiener Neustadt, 
Austria; phone: +43 2622 26700; email: diamondaircraft.com">airworthiness-austria@diamondaircraft.com; website: diamondaircraft.com.
     You may view this service information 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-2023-2143.

FOR FURTHER INFORMATION CONTACT: Penelope Trease, Aviation Safety 
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
phone: (303) 342-1094; email: [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2022-21-15, Amendment 39-22214 (87 FR 
67541, November 9, 2022) (AD 2022-21-15). AD 2022-21-15 applied to 
certain DAI Model DA 42, DA 42 NG, and DA 42 M-NG airplanes. AD 2022-
21-15 was prompted by MCAI originated by EASA, which is the Technical 
Agent for the Member States of the European Union. EASA issued EASA AD 
2019-0302, dated December 13, 2019 (EASA AD 2019-0302) to correct an 
unsafe condition on DAI Model DA 42, DA 42 NG, and DA 42 M-NG 
airplanes. EASA AD 2019-0302 described the unsafe condition as reports 
of a loose rudder T-yoke axle nut on DAI Model DA 42 airplanes and the 
need for new inspections for correct installation of the self-locking 
nut to the rudder T-yoke standard bolt LN 9037 (dimensions M6x90), and 
depending on findings, accomplishment of applicable corrective 
action(s) and replacement of the self-locking nut. EASA AD 2019-0302 
also provided an optional terminating action for the repetitive 
inspections. This condition, if not detected and corrected, could lead 
to vertical movement of the bolt, possibly resulting in reduced rudder 
control of the airplane.
    AD 2022-21-15 required replacing the rudder T-yoke axle with an 
improved rudder T-yoke bolt. The FAA issued AD 2022-21-15 to prevent 
movement of the T-yoke bolt.
    The NPRM published in the Federal Register on November 8, 2023 (88 
FR 77060). The NPRM was prompted by EASA AD 2023-0013, dated January 
18, 2023 (EASA AD 2023-0013) (also referred to as the MCAI) for all 
Model DA 42, DA 42 M, DA 42 NG, and DA 42 M-NG airplanes. EASA AD 2023-
0013 superseded EASA AD 2019-0302.
    The MCAI states that since EASA AD 2019-0302 was issued, DAI 
published revised service information to provide additional inspection 
and modification instructions. The MCAI requires a one-time inspection 
of the rudder steering bracket for insufficient edge distance or wear, 
replacement of rudder T-yoke standard bolt LN 9037 (dimensions M6x90) 
with rudder T-yoke bolt part number (P/N) D60-5320-00-32, repetitive 
inspections of rudder T-yoke bolt P/N D60-5320-00-32 for correct 
installation, corrective actions if necessary, and prohibits 
installation of rudder T-yoke standard bolt LN 9037 (dimensions M6x90). 
The affected and serviceable parts, identified as ``bolt'' in EASA AD 
2023-0013, were referred to as ``axle'' in EASA AD 2019-0302.
    This condition, if not detected and corrected, could lead to 
blockage or loss of rudder control. You may examine the MCAI in the AD 
docket at regulations.gov under Docket No. FAA-2023-2143.
    In the NPRM the FAA proposed to require, for certain airplanes, 
inspecting the rudder steering bracket edge distance and depending on 
the

[[Page 29248]]

inspection results, inspecting the T-yoke bolt hole for wear and play, 
and corrective action if necessary. For certain airplanes, the NPRM 
proposed to require replacing the rudder T-yoke bolt (axle) with a 
serviceable part and applying torque seal marks on the rudder T-yoke 
bolt head, and self-locking nut. For all airplanes, the NPRM proposed 
to require repetitively inspecting the torque seal marks on the rudder 
T-yoke bolt head for proper alignment and the self-locking nut for 
proper installation and corrective action if necessary. The NPRM also 
proposed to prohibit the installation of affected parts.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from three commenters. The commenters 
were two individuals and DAI. The individuals supported the NPRM 
without any changes. The following presents the comments received on 
the NPRM and the FAA's response to each comment.

Request To Extend the Compliance Time

    DAI requested that the compliance time in the proposed AD be 
changed from ``Within 200 hours time-in-service (TIS) or 9 months after 
the effective date of this AD, whichever occurs first'' to ``Within 200 
flight hours or 12 months after the effective date of this AD, 
whichever occurs first.'' DAI explained that the pilot and passenger 
seats need to be removed prior to the inspection of the rudder steering 
bracket and the installation of the improved T-yoke bolt and that the 
removal of these seats is already part of an airplane's annual 
inspection. DAI noted that extending the compliance time from 9 months 
to 12 months would allow operators to align the requirements specified 
in the proposed AD with an airplane's scheduled annual inspection. DAI 
mentioned that this would avoid unnecessary financial burden for 
operators. DAI also noted that the formation of wear in the hole in the 
rudder steering bracket is related to flight time and not a specific 
period of time. In addition, DAI emphasized that an unnecessary 
maintenance action that can be avoided also avoids possible maintenance 
errors.
    The FAA agrees with the commenter's request to extend the 
compliance time from 9 months to 12 months and revised paragraph (h)(1) 
of this AD to specify ``Within 200 hours time-in-service (TIS) or 12 
months after the effective date of this AD, whichever occurs first . . 
. .'' Extending the compliance time by 3 months will not adversely 
affect safety and will allow the inspection of the rudder steering 
bracket and the installation of the improved T-yoke bolt to be 
performed during the annual inspection. The FAA does not agree to 
change ``Within 200 hours time-in-service (TIS) . . . .'' to ``Within 
200 flight hours . . . .'' Although the MCAI compliance time specifies 
``flight hours'' this AD requires using ``hours TIS'' because ``TIS'' 
is defined in FAA regulations and is used with respect to maintenance 
records and ``flight hours'' is not defined in FAA regulations.

Request To Require Entire Work Instruction Instead of Specific Steps

    DAI requested that instead of referring to specific steps in the 
work instructions identified in paragraphs (h)(1) and (2) and paragraph 
(i) of the proposed AD that the entire work instruction be referred to. 
DAI stated that it is important to reference the entire document and 
include all of the steps instead of specific steps because there are 
additional steps that were not identified in paragraphs (h)(1) and (2) 
and paragraph (i) of the proposed AD that operators need to do in order 
to complete the required actions specified in the proposed AD. DAI 
provided the example that operators must do step 9, release rudder 
cable turnbuckles, of Diamond Aircraft Work Instruction WI-MSB 42-143 
and WI-MSB 42NG-086, Revision 3, dated November 15, 2022 (issued as one 
document) attached to Diamond Aircraft Mandatory Service Bulletin DAI 
MSB 42-143/1 and DAI MSB 42NG-086/1, dated January 25, 2022 (issued as 
one document) because it is important that the T-yoke bolt and self-
locking nut are tightened with released rudder cable tension.
    The FAA agrees to require additional steps from the applicable work 
instructions in paragraphs (h)(2) and (i) of this AD but does not agree 
to require compliance with the entire work instruction document. The 
requirements of this AD correspond with the requirements in EASA AD 
2023-0013. EASA AD 2023-0013 only requires the following specific steps 
from the work instructions: inspecting the edge distance and repair if 
required, inspecting the hole and repair if required, replacing an 
affected part with a serviceable part, and marking the head of the T-
yoke bolt and the self-locking nut.
    The FAA acknowledges that doing additional steps in the work 
instructions is necessary to complete the actions required by this AD, 
for example, removing the pilot and passenger seats prior to the 
inspection of the rudder steering bracket and the installation of the 
improved T-yoke bolt; however, to provide operators flexibility 
regarding how the required steps are accomplished, the FAA does not 
require that operators follow all of the steps in the work 
instructions. For example, 14 CFR part 135 operators could have their 
own maintenance program which includes instructions regarding pilot and 
passenger seat removal. Requiring seat removal in accordance with the 
work instructions would create an unnecessary burden on operators 
because they would have to submit an alternative method of compliance 
(AMOC) request to the FAA if they did not follow the process specified 
in the work instructions to remove the seats.
    Paragraph (h)(2) of this AD was revised to add steps 9 and 10 of 
Diamond Aircraft Work Instruction WI-MSB 42-143 and WI-MSB 42NG-086, 
Revision 3, dated November 15, 2022 (issued as one document) attached 
to Diamond Aircraft Mandatory Service Bulletin DAI MSB 42-143/1 and DAI 
MSB 42NG-086/1, dated January 25, 2022 (issued as one document), with 
the exception that instead of discarding a self-locking nut an operator 
is required to remove that part from service. Steps 9 and 10 of that 
work instruction specify releasing the rudder cable turnbuckles and 
removing and discarding the self-locking nut of the T-yoke bolt.
    Paragraph (i) of this AD was revised to add steps 6 through 9 of 
the Instructions, Section III, in Diamond Aircraft Work Instruction WI-
RSB 42-139 and WI-RSB 42NG-081, Revision 2, dated November 15, 2022 
(issued as one document) attached to Diamond Aircraft Recommended 
Service Bulletin DAI RSB 42-139 and DAI RSB 42NG-081, dated October 21, 
2019 (issued as one document), with the exception that instead of 
discarding a self-locking nut an operator is required to remove that 
part from service. Steps 6 through 9 of that work instruction are 
included in the ``Replacement of rudder T-yoke bolt'' instructions and 
specify procedures for accessing the rudder T-yoke bolt, which include 
disconnecting the nose landing gear (NLG) steering linkage at the 
steering cardan in the wheel well, releasing the rudder cable 
turnbuckles, removing the self-locking nut of the T-yoke bolt, 
discarding the nut, and removing the T-yoke bolt from the rudder 
steering bracket.

[[Page 29249]]

Request To Require Application of Torque Seal Marks for Group 1 Minus 
Group 2 Airplanes

    DAI requested that the requirement to apply torque seal marks be 
added in paragraph (h) of the proposed AD because that action should 
also be done on Group 1 minus Group 2 airplanes. DAI noted that the 
requirement to apply torque seal marks was only included in paragraph 
(i) of the proposed AD and was only applicable to Group 2 airplanes.
    The FAA agrees with the commenter's request but instead of revising 
paragraph (h) of this AD, the FAA revised paragraph (i) of this AD to 
change the header from ``Replacement'' to ``Replacement and Application 
of Torque Seal Marks,'' added paragraph (i)(1) that is applicable to 
Group 1 airplanes that are not also Group 2 airplanes, and moved the 
content of paragraph (i) of the proposed AD to paragraph (i)(2) of this 
AD.

Request To Have Operator Contact Only DAI for Post-Inspection 
Instructions

    DAI requested that paragraphs (h)(3) and (4) of the proposed AD be 
revised to require operators to contact only DAI for post-inspection 
instructions instead of contacting ``. . . the Manager, International 
Validation Branch, FAA; the European Union Aviation Safety Agency 
(EASA); or Diamond's EASA Design Organization Approval (DOA) . . . .'' 
DAI noted that depending on the extent of the inspection findings, in 
the case of a too large edge distance or a worn or enlarged hole on the 
rudder steering bracket, the rudder steering bracket could be repaired 
instead of being replaced. The commenter stated that the intention is 
to avoid the replacement of the rudder steering bracket if possible, 
but this has to be determined for each airplane by DAI experts.
    The FAA does not agree with the commenter's request. The FAA 
acknowledges that not all discrepancies will result in a rudder 
steering bracket having to be replaced and that some rudder steering 
brackets can be repaired. The FAA cannot delegate repair approval 
authority to a single outside entity; however, the current language in 
paragraphs (h)(3) and (4) of this AD provides operators the option to 
contact DAI's EASA DOA with the inspection findings for a determination 
regarding if the affected rudder steering bracket can be repaired or 
must be replaced. The FAA has not changed this AD regarding this issue.

Request To Clarify ``Proposed AD Requirements in This NPRM'' Section

    DAI requested clarification of the proposed requirement regarding 
repetitive inspections of the torque seal marks in the ``Proposed AD 
Requirements in this NPRM'' section of the NPRM. DAI stated that 
existing wording could be misinterpreted to mean the inspections would 
only apply to the torque seal marks on the T-yoke bolt head and 
clarification was needed to specify that the repetitive inspections are 
visual inspections of the torque seal marks for proper alignment on the 
T-yoke bolt head and the self-locking nut.
    The FAA acknowledges the commenter's request and agrees that the 
proposed wording clarifies the requirement in this AD regarding the 
repetitive inspections of the torque seal marks; however, the 
``Proposed AD Requirements in this NPRM'' section is not carried over 
to the final rule. The FAA has not changed this AD regarding this 
issue.

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, 
considered the comments 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 these products. Except for 
any changes described previously, 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 Diamond Aircraft Mandatory Service Bulletin DAI 
MSB 42-143/1 and DAI MSB 42NG-086/1, dated January 25, 2022 (issued as 
one document), published with DAI Work Instruction WI-MSB 42-143 and 
WI-MSB 42NG-086, Revision 3, dated November 15, 2022 (issued as one 
document) attached. The service bulletin specifies compliance with the 
work instruction, which contains procedures for inspecting the hole 
position and condition in the rudder steering bracket.
    The FAA also reviewed Diamond Aircraft Mandatory Service Bulletin 
DAI MSB 42-146 and DAI MSB 42NG-087, dated November 15, 2022 (issued as 
one document). The service bulletin specifies the serial numbers for 
affected airplanes defined as Group 2 airplanes in paragraph (g)(2) of 
this AD.
    In addition, the FAA reviewed Diamond Aircraft Recommended Service 
Bulletin DAI RSB 42-139 and DAI RSB 42NG-081, dated October 21, 2019 
(issued as one document), published with DAI Work Instruction WI-RSB 
42-139 and WI-RSB 42NG-081, Revision 2, dated November 15, 2022 (issued 
as one document) attached. The service bulletin specifies compliance 
with the work instruction, which contains procedures for replacement of 
the rudder T-yoke axle with an improved (additional retaining pin) 
rudder T-yoke axle.
    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 ADDRESSES.

Differences Between This AD and the MCAI

    The MCAI applies to DAI Model DA 42 M airplanes and this AD does 
not because those airplanes do not have an FAA type certificate.
    Paragraph (1) of the MCAI specifies a compliance time of within 200 
flight hours or 9 months after the effective date of the MCAI, 
whichever occurs first, for measuring the distance between the edge of 
the rudder steering bracket hole and rear edge of the rudder steering 
bracket but this AD requires doing that action within 200 hours TIS or 
12 months after the effective date of this AD, whichever occurs first. 
Extending the compliance time by three months will not adversely affect 
safety and will allow this action to be done during regularly scheduled 
maintenance. Although the MCAI compliance time specifies ``flight 
hours'' this AD requires using ``hours TIS.''
    Paragraph (3) of the MCAI specifies to contact the manufacturer for 
repair instructions and paragraph (7) of the MCAI specifies to contact 
the manufacturer for corrective actions if any discrepancy is found, 
but for both of those corrective actions, this AD requires contacting 
either the Manager, International Validation Branch, FAA; EASA; or 
Diamond's EASA DOA instead. If approved by the DOA, the approval must 
include the DOA-authorized signature.

Costs of Compliance

    The FAA estimates that this AD affects 205 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

[[Page 29250]]



                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                Action                          Labor cost           Parts cost             Cost per product                 Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection of rudder steering bracket   0.25 work-hour x $85 per               $0  $21.25............................  $4,356.25.
 edge distance.                          hour = $21.25.
Replacement of rudder t-yoke bolt P/N   0.50 work-hour x $85 per               82  $124.50...........................  $25,522.50.
 LN 9037 with P/N D60-5320-0032.         hour = $42.50.
Application of torque seal marks to     0.75 work-hour x $85 per               15  $78.75............................  $16,143.75.
 rudder T-yoke bolt and self-locking     hour = $63.75.
 nut.
Repetitive inspection of torque seal    0.25 work-hour x $85 per                0  $21.25, per inspection............  $4,356.25, per inspection.
 marks.                                  hour.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Inspection of rudder steering bracket hole for  0.50 work-hour x $85 per hour =               $0          $42.50
 wear and play, if edge distance is equal to     $42.50.
 or greater than 11 millimeters.
----------------------------------------------------------------------------------------------------------------

    Since the replacement or repair instructions could vary 
significantly from airplane to airplane if discrepancies are found 
during the inspections, the FAA has no data to determine the number of 
airplanes that would need follow-on actions or what the cost per 
airplane would be.

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 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 2022-21-15, Amendment 39-22214 (87 
FR 67541, November 9, 2022); and
0
b. Adding the following new airworthiness directive:

2024-06-13 Diamond Aircraft Industries GmbH: Amendment 39-22718; 
Docket No. FAA-2023-2143; Project Identifier MCAI-2023-00088-A.

(a) Effective Date

    This airworthiness directive (AD) is effective May 28, 2024.

(b) Affected ADs

    This AD replaces AD 2022-21-15, Amendment 39-22214 (87 FR 67541, 
November 9, 2022).

(c) Applicability

    This AD applies to Diamond Aircraft Industries GmbH (DAI) Model 
DA 42, DA 42 NG, and DA 42 M-NG airplanes, all serial numbers, 
certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC) Code 2700, Flight Control 
System.

(e) Unsafe Condition

    This AD was prompted by reports of a loose rudder T-yoke bolt 
nut, excessive wear of the hole, and insufficient hole edge margin 
at the rudder steering bracket. The FAA is issuing this AD to detect 
and correct vertical movement of the T-yoke bolt (axle). The unsafe 
condition, if not addressed, could lead to blockage or loss of 
rudder control and result in reduced control of the airplane.

(f) Compliance

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

(g) Definitions

    For the purposes of this AD, the following definitions apply.
    (1) Group 1 airplanes: Airplanes with serial numbers specified 
in Technical Details, section I.2, of Diamond Aircraft Mandatory

[[Page 29251]]

Service Bulletin DAI MSB 42-143/1 and DAI MSB 42NG-086/1, dated 
January 25, 2022 (issued as one document), published with DAI Work 
Instruction WI-MSB 42-143 and WI-MSB 42NG-086, Revision 3, dated 
November 15, 2022 (issued as one document) attached.
    (2) Group 2 airplanes: Airplanes with serial numbers specified 
in Technical Details, section I.2, of Diamond Aircraft Mandatory 
Service Bulletin DAI MSB 42-146 and DAI MSB 42NG-087, dated November 
15, 2022 (issued as one document).
    (3) Group 3 airplanes: Airplanes that are not in Group 1 or 
Group 2.
    (4) Depending on the serial number, a Group 1 airplane can also 
be a Group 2 airplane.

(h) Inspections and Corrective Actions

    For Group 1 and Group 2 airplanes: Do the inspection required by 
paragraph (h)(1) of this AD at the compliance time specified in 
paragraph (h)(1) of this AD and the applicable corrective actions 
specified in paragraphs (h)(2) through (4) of this AD at the 
applicable compliance times specified in paragraphs (h)(2) through 
(4) of this AD.
    (1) Within 200 hours time-in-service (TIS) or 12 months after 
the effective date of this AD, whichever occurs first, inspect the 
rudder steering bracket edge distance by measuring in accordance 
with step 6 of the Instructions, Section III, in Diamond Aircraft 
Work Instruction WI-MSB 42-143 and WI-MSB 42NG-086, Revision 3, 
dated November 15, 2022 (issued as one document) attached to Diamond 
Aircraft Mandatory Service Bulletin DAI MSB 42-143/1 and DAI MSB 
42NG-086/1, dated January 25, 2022 (issued as one document).
    (2) If, during the inspection required by paragraph (h)(1) of 
this AD, the measured distance is equal to or greater than 11 
millimeters (mm), before further flight, inspect the hole in the 
rudder steering bracket for wear and play in accordance with steps 9 
through 11 of the Instructions, Section III, in Diamond Aircraft 
Work Instruction WI-MSB 42-143 and WI-MSB 42NG-086, Revision 3, 
dated November 15, 2022 (issued as one document) attached to Diamond 
Aircraft Mandatory Service Bulletin DAI MSB 42-143/1 and DAI MSB 
42NG-086/1, dated January 25, 2022 (issued as one document). Where 
Diamond Aircraft Work Instruction WI-MSB 42-143 and WI-MSB 42NG-086, 
Revision 3, dated November 15, 2022 (issued as one document) 
attached to Diamond Aircraft Mandatory Service Bulletin DAI MSB 42-
143/1 and DAI MSB 42NG-086/1, dated January 25, 2022 (issued as one 
document) specifies to discard the self-locking nut this AD requires 
removing that part from service.
    (3) If, during the inspection required by paragraph (h)(1) of 
this AD, the measured distance is less than 11 mm, before further 
flight, contact the Manager, International Validation Branch, FAA; 
the European Union Aviation Safety Agency (EASA); or Diamond's EASA 
Design Organization Approval (DOA) for repair instructions, and 
within the compliance time specified therein, complete the repair. 
If approved by the DOA, the approval must include the DOA-authorized 
signature.
    (4) If, during the inspection required by paragraph (h)(2) of 
this AD, a worn or enlarged hole is found on the rudder steering 
bracket, or if the T-yoke bolt is found to have play, before further 
flight, contact the Manager, International Validation Branch, FAA; 
EASA; or Diamond's EASA DOA for instructions (repair or replacement 
of the rudder steering bracket), and within the compliance time 
specified therein, do the instructions. If approved by the DOA, the 
approval must include the DOA-authorized signature.

(i) Replacement and Application of Torque Seal Marks

    (1) For Group 1 airplanes that are not also Group 2 airplanes: 
Concurrently with the inspection required by paragraph (h)(1) of 
this AD, replace the rudder T-yoke bolt part number (P/N) LN 9037-
M6x90 with rudder T-yoke bolt P/N D60-5320-00-32, and apply torque 
seal marks on the rudder T-yoke bolt head and self-locking nut, in 
accordance with steps 13 through 15 of the Instructions, Section 
III, in Diamond Aircraft Work Instruction WI-MSB 42-143 and WI- MSB 
42NG-086, Revision 3, dated November 15, 2022 (issued as one 
document) attached to Diamond Aircraft Mandatory Service Bulletin 
DAI MSB 42-143/1 and DAI MSB 42NG-086/1, dated January 25, 2022 
(issued as one document).
    (2) For Group 2 airplanes: Concurrently with the inspection 
required by paragraph (h)(1) of this AD, replace the rudder T-yoke 
bolt part number (P/N) LN 9037-M6x90 with rudder T-yoke bolt P/N 
D60-5320-00-32, and apply torque seal marks on the rudder T-yoke 
bolt head and self-locking nut, in accordance with steps 6 through 
9, 14, 15, and 18 of the Instructions, Section III, in Diamond 
Aircraft Work Instruction WI-RSB 42-139 and WI-RSB 42NG-081, 
Revision 2, dated November 15, 2022 (issued as one document) 
attached to Diamond Aircraft Recommended Service Bulletin DAI RSB 
42-139 and DAI RSB 42NG-081, dated October 21, 2019 (issued as one 
document). Where Diamond Aircraft Work Instruction WI-RSB 42-139 and 
WI-RSB 42NG-081, Revision 2, dated November 15, 2022 (issued as one 
document) attached to Diamond Aircraft Recommended Service Bulletin 
DAI RSB 42-139 and DAI RSB 42NG-081, dated October 21, 2019 (issued 
as one document) specifies to discard the self-locking nut this AD 
requires removing that part from service.

(j) Repetitive Inspections

    (1) For Group 1 and Group 2 airplanes: Within 200 hours TIS 
after the inspection required by paragraph (h)(1) of this AD and, 
thereafter, at intervals not to exceed 200 hours TIS, inspect the 
torque seal marks on the T-yoke bolt head and self-locking nut for 
proper alignment.
    Note 1 to paragraph (j)(1): This can be accomplished using DAI 
Maintenance Manual (AMM) Temporary Revision (TR) AMM-TR-M[Auml]M-42-
1213/a, dated June 7, 2022 (DAI AMM TR AMM-TR-M[Auml]M-42-1213/a).
    (2) For Group 3 airplanes: Within 200 hours TIS after the 
effective date of this AD, and thereafter at intervals not to exceed 
200 hours TIS, inspect the torque seal marks on the T-yoke bolt head 
and self-locking nut for proper alignment.
    Note 2 to paragraph (j)(2): This can be accomplished using DAI 
AMM TR AMM-TR-M[Auml]M-42-1213/a.
    (3) For all airplanes: If, during any inspection required by 
paragraph (j)(1) or (j)(2) of this AD, it is found that the torque 
seal marks are not properly aligned, before further flight, contact 
the Manager, International Validation Branch, FAA; EASA; or 
Diamond's EASA DOA for approved repair instructions, and within the 
compliance time specified therein, accomplish those instructions 
accordingly. If approved by the DOA, the approval must include the 
DOA-authorized signature.

(k) Parts Installation Prohibition

    For all airplanes: As of the effective date of this AD, do not 
install on any airplane a rudder T-yoke bolt P/N LN 9037-M6x90.

(l) Credit for Previous Actions

    (1) You may take credit for the actions required by paragraphs 
(h)(1) and (2) of this AD if the actions were done before the 
effective date of this AD using any of the work instructions 
specified in paragraphs (l)(1)(i), (ii), or (iii) of this AD.
    (i) Diamond Aircraft Work Instruction WI-MSB 42-143 and WI-MSB 
42NG-086, Revision 0, dated December 23, 2021 (issued as one 
document) attached to Diamond Aircraft Mandatory Service Bulletin 
DAI MSB 42-143 and DAI MSB 42NG-086, dated December 23, 2021 (issued 
as one document).
    (ii) Diamond Aircraft Work Instruction WI-MSB 42-143 and WI-MSB 
42NG-086, Revision 1, dated January 25, 2022 (issued as one 
document) attached to Diamond Aircraft Mandatory Service Bulletin 
DAI MSB 42-143/1 and DAI MSB 42NG-086/1, dated January 25, 2022 
(issued as one document).
    (iii) Diamond Aircraft Work Instruction WI-MSB 42-143 and WI-MSB 
42NG-086, Revision 2, dated March 10, 2022 (issued as one document) 
attached to Diamond Aircraft Mandatory Service Bulletin DAI MSB 42-
143/1 and DAI MSB 42NG-086/1, dated January 25, 2022 (issued as one 
document).
    (2) You may take credit for the rudder T-yoke bolt replacement 
required by paragraph (i) of this AD if that action was done before 
the effective date of this AD using the Diamond Aircraft Work 
Instruction WI-RSB 42-139 and WI-RSB 42NG-081, Revision 1, dated 
October 24, 2019 (issued as one document) attached to Diamond 
Aircraft Recommended Service Bulletin DAI RSB 42-139 and DAI RSB 
42NG-081, dated October 21, 2019 (issued as one document).

(m) 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 International Validation Branch, send it to the 
attention of the person identified in paragraph (n)(2) of this AD or 
email to: 9-

[[Page 29252]]

[email protected]. 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 responsible Flight Standards Office.

(n) Additional Information

    (1) Refer to EASA AD 2023-0013, dated January 18, 2023, for 
related information. This EASA AD may be found in the AD docket at 
regulations.gov under Docket No. FAA-2023-2143.
    (2) For more information about this AD, contact Penelope Trease, 
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; phone: (303) 342-1094; email: 
[email protected].
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the address specified in 
paragraph (o)(3) of this AD.

(o) 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 the AD specifies otherwise.
    (i) Diamond Aircraft Mandatory Service Bulletin DAI MSB 42-143/1 
and DAI MSB 42NG-086/1, dated January 25, 2022 (issued as one 
document), published with DAI Work Instruction WI-MSB 42-143 and WI-
MSB 42NG-086, Revision 3, dated November 15, 2022 (issued as one 
document) attached.
    (ii) Diamond Aircraft Mandatory Service Bulletin DAI MSB 42-146 
and DAI MSB 42NG-087, dated November 15, 2022 (issued as one 
document).
    (iii) Diamond Aircraft Recommended Service Bulletin DAI RSB 42-
139 and DAI RSB 42NG-081, dated October 21, 2019 (issued as one 
document), published with DAI Work Instruction WI-RSB 42-139 and WI-
RSB 42NG-081, Revision 2, dated November 15, 2022 (issued as one 
document) attached.
    (3) For service information contact Diamond Aircraft Industries 
GmbH, N.A. Otto-Stra[szlig]e 5, A-2700 Wiener Neustadt, Austria; 
phone: +43 2622 26700; email: diamondaircraft.com">airworthiness-austria@diamondaircraft.com; website: diamondaircraft.com.
    (4) You may view this service information 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-2023-2143.
    (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 [email protected].

    Issued on March 22, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2024-08539 Filed 4-19-24; 8:45 am]
BILLING CODE 4910-13-P