Airworthiness Directives; Diamond Aircraft Industries GmbH Airplanes, 29247-29252 [2024-08539]
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29247
Rules and Regulations
Federal Register
Vol. 89, No. 78
Monday, April 22, 2024
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents.
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
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superseded its mandatory continuing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 Tyoke 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.
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SUMMARY:
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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+e 5, A–2700 Wiener
Neustadt, Austria; phone: +43 2622
26700; email: 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: penelope.trease@
faa.gov.
SUPPLEMENTARY INFORMATION:
DATES:
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
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NG, and DA 42 M–NG airplanes. EASA
AD 2019–0302 described the unsafe
condition as reports of a loose rudder Tyoke 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 selflocking 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 onetime 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
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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 selflocking 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.
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-inservice (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.
Discussion of Final Airworthiness
Directive
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,
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.
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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
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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 selflocking 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 Tyoke 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.
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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.
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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.
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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 Tyoke 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
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29249
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 DOAauthorized 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:
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ESTIMATED COSTS
Labor cost
Inspection of rudder steering bracket
edge distance.
Replacement of rudder t-yoke bolt P/N
LN 9037 with P/N D60–5320–0032.
Application of torque seal marks to rudder T-yoke bolt and self-locking nut.
Repetitive inspection of torque seal
marks.
0.25 work-hour × $85 per hour = $21.25
$0
$21.25 ....................
$4,356.25.
0.50 work-hour × $85 per hour = $42.50
82
$124.50 ..................
$25,522.50.
0.75 work-hour × $85 per hour = $63.75
15
$78.75 ....................
$16,143.75.
0.25 work-hour × $85 per hour ..............
0
$21.25, per inspection.
$4,356.25, per inspection.
The FAA estimates the following
costs to do any necessary on-condition
action that would be required based on
Parts cost
Cost on U.S.
operators
Action
the results of any required actions. The
FAA has no way of determining the
Cost per product
number of aircraft that might need this
on-condition action:
ON-CONDITION COSTS
Action
Labor cost
Inspection of rudder steering bracket hole for wear
and play, if edge distance is equal to or greater
than 11 millimeters.
0.50 work-hour × $85 per hour = $42.50 .....................
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
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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.
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
Regulatory Findings
§ 39.13
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
■
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[Amended]
2. The FAA amends § 39.13 by:
■ a. Removing Airworthiness Directive
2022–21–15, Amendment 39–22214 (87
FR 67541, November 9, 2022); and
■ b. Adding the following new
airworthiness directive:
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Cost per
product
Parts cost
$0
$42.50
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
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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 selflocking 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 DOAauthorized signature.
VerDate Sep<11>2014
16:51 Apr 19, 2024
Jkt 262001
(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)
¨ M–42–1213/a, dated June 7,
AMM–TR–MA
¨ M–42–
2022 (DAI AMM TR AMM–TR–MA
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
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
29251
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–
¨ M–42–1213/a.
TR–MA
(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 DOAauthorized 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 Tyoke 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-
E:\FR\FM\22APR1.SGM
22APR1
29252
Federal Register / Vol. 89, No. 78 / Monday, April 22, 2024 / Rules and Regulations
AVS-AIR-730-AMOC@faa.gov. 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.
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
(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: penelope.trease@faa.gov.
(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.
lotter on DSK11XQN23PROD with RULES1
(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+e 5, A–2700 Wiener Neustadt,
Austria; phone: +43 2622 26700; email:
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 fr.inspection@nara.gov.
16:51 Apr 19, 2024
Jkt 262001
Federal Aviation Administration
14 CFR Parts 61, 63, and 65
[Docket No. FAA–2022–1463; Amdt. No. 65–
64A]
RIN 2120–AL74
Airman Certification Standards and
Practical Test Standards for Airmen;
Incorporation by Reference
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; correction.
AGENCY:
(o) Material Incorporated by Reference
VerDate Sep<11>2014
DEPARTMENT OF TRANSPORTATION
On April 1, 2024, the Federal
Aviation Administration (FAA)
published a final rule in the Federal
Register to incorporate certain Airman
Certification Standards and Practical
Test Standards by reference into the
certification requirements for pilots,
flight instructors, flight engineers,
aircraft dispatchers, and parachute
riggers. In that final rule, the FAA
incorrectly set forth certain regulatory
text which, if not corrected, would
remove certain content from the Code of
Federal Regulations the FAA did not
intend to remove. This correction
remedies the error.
DATES: Effective on May 31, 2024.
ADDRESSES: For information on where to
obtain copies of rulemaking documents
and other information related to this
final rule, see ‘‘How to Obtain
Additional Information’’ in the
SUPPLEMENTARY INFORMATION section of
this document.
FOR FURTHER INFORMATION CONTACT:
James Ciccone, Training and
Certification Group, AFS–810, Federal
Aviation Administration, 800
Independence Avenue SW, Washington,
DC 20591; telephone (202) 267–1100;
email ACSPTSinquiries@faa.gov.
SUPPLEMENTARY INFORMATION: On April
1, 2024, the Federal Aviation
Administration (FAA) published the
final rule, Airman Certification
Standards and Practical Test Standards
for Airmen; Incorporation by
Reference.1 That final rule adopted
several amendments to parts 61, 63, and
65 of Title 14 of the Code of Federal
SUMMARY:
1 89
PO 00000
FR 22482 FR Doc 2024–06644.
Frm 00006
Fmt 4700
Sfmt 9990
Regulations (14 CFR) by incorporating
by reference (IBR) the Airman
Certification Standards (ACS) and
Practical Test Standards (PTS). The ACS
and PTS 2 serve as the testing standards
for airman certificates and rating
practical tests. Among other things, the
final rule revised § 65.119(a) to require
compliance with the respective PTS for
parachute riggers. However, the FAA
inadvertently set forth only the
revisions to the introductory text of
paragraph (a) and did not address the
undesignated paragraph at the end of
paragraph (a). The FAA is correcting
this error by setting forth the entirety of
paragraph (a) and designating the
currently-undesignated paragraph at the
end of paragraph (a) as paragraph (a)(3).
Correction
Effective May 31, 2024, in rule
document 2024–06644 at 89 FR 22482
in the issue of April 1, 2024, on page
22520, in the third column, in
amendatory instruction 16, paragraph a
is corrected to read as follows:
■
§ 65.119
[Corrected]
*
*
*
*
*
(a) Present evidence satisfactory to the
Administrator that the applicant has
had at least 3 years of experience as a
parachute rigger and has satisfactorily
packed at least 100 parachutes of each
of two types in common use, in
accordance with the manufacturer’s
instructions—
(1) While a certificated and
appropriately rated senior parachute
rigger; or
(2) While under the supervision of a
certificated and appropriately rated
parachute rigger or a person holding
appropriate military ratings.
(3) An applicant may combine
experience specified in paragraphs (a)(1)
and (2) of this section to meet the
requirements of this paragraph (a).
*
*
*
*
*
Issued under authority provided by 49
U.S.C. 106(f), 40113, 44701, 44702, and
44703 in Washington, DC.
Brandon Roberts,
Executive Director, Office of Rulemaking.
[FR Doc. 2024–08631 Filed 4–19–24; 8:45 am]
BILLING CODE 4910–13–M
2 ACS and PTS refers to both the singular
Standard and the plural Standards throughout the
document.
E:\FR\FM\22APR1.SGM
22APR1
]]>Agencies
[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]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
========================================================================
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
