[Federal Register Volume 89, Number 102 (Friday, May 24, 2024)]
[Rules and Regulations]
[Pages 45754-45758]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-11420]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-1466; Project Identifier MCAI-2024-00205-R; 
Amendment 39-22752; AD 2024-07-51]
RIN 2120-AA64


Airworthiness Directives; Bell Textron Canada Limited Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Bell Textron Canada Limited Model 429 helicopters. The FAA 
previously sent this AD as an emergency AD to all known U.S. owners and 
operators of these helicopters. This AD was prompted by multiple 
reports of tail rotor (T/R) blade abrasion strip cracks. This AD 
requires repetitively inspecting and checking the T/R blade abrasion 
strip on certain T/R blades and, depending on results, replacing or 
marking the T/R blade. This AD also prohibits installing affected T/R 
blades on any helicopter. The FAA is issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective June 10, 2024. Emergency AD 2024-07-51, 
issued on March 29, 2024, which contained the requirements of this 
amendment, was effective with actual notice.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of June 10, 
2024.
    The FAA must receive comments on this AD by July 8, 2024.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to regulations.gov. Follow 
the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2024-1466; 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, any comments received, and other 
information. The street address for Docket Operations is listed above.
    Material Incorporated by Reference:
     For Bell material, contact Bell Textron Canada Limited, 
12,800 Rue de l'Avenir, Mirabel, Quebec J7J 1R4, Canada; phone 1-450-
437-2862 or 1-800-363-8023; fax 1-450-433-0272; email 
[email protected]; or at bellflight.com/support/contact-support.
     You may view this material at the FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, 
Fort Worth, TX 76177. For information on the availability of this 
material at the FAA, call (817) 222-5110. It is also available at 
regulations.gov under Docket No. FAA-2024-1466.

FOR FURTHER INFORMATION CONTACT: Dan McCully, Aviation Safety Engineer, 
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone (404) 
474-5548; email [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written data, views, or arguments 
about this final rule. Send your comments to an address listed under 
ADDRESSES. Include ``Docket No. FAA-2024-1466; Project Identifier MCAI-
2024-00205-R'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the final rule, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may

[[Page 45755]]

amend this final rule because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
regulations.gov, including any personal information you provide. The 
agency will also post a report summarizing each substantive verbal 
contact received about this final rule.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this AD contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this AD, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this AD. Submissions containing CBI should be sent to Dan 
McCully, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; phone (404) 474-5548; email 
[email protected]. Any commentary that the FAA receives that is 
not specifically designated as CBI will be placed in the public docket 
for this rulemaking.

Background

    The FAA issued Emergency AD 2024-07-51, dated March 29, 2024 (the 
emergency AD), to address an unsafe condition on Bell Textron Canada 
Limited Model 429 helicopters, serial number 57001 and subsequent, with 
a T/R blade part number (P/N) 429-016-101-105 having a serial number 
identified in Table 1 of Bell Alert Service Bulletin 429-24-63, dated 
March 21, 2024 (ASB 429-24-63) installed. The FAA sent the emergency AD 
to all known U.S. owners and operators of these helicopters. For 
affected T/R blades with an abrasion strip with any coating (such as a 
protective tape or protective coating), the emergency AD requires 
accomplishing actions in accordance with a method approved by the FAA, 
Transport Canada, or Bell Textron Canada Ltd.'s Design Approval 
Organization. For all other affected T/R blades, the emergency AD 
requires repetitively cleaning and inspecting, and repetitively 
checking the T/R blade abrasion strip and, depending on results, 
replacing, marking, or remarking the T/R blade. The emergency AD also 
prohibits installing affected T/R blades on any helicopter.
    The emergency AD was prompted by Transport Canada Emergency AD CF-
2024-11, dated March 22, 2024 (Transport Canada AD CF-2024-11), issued 
by Transport Canada, which is the aviation authority for Canada, to 
correct an unsafe condition on certain serial-numbered Bell Textron 
Canada Limited Model 429 helicopters. Transport Canada states that an 
investigation revealed a manufacturing defect in certain serial-
numbered T/R blades part number 429-016-101-105. Transport Canada 
further states that a critical step in the fabrication of the abrasion 
strip was missed, which could result in the presence of stress risers, 
leading to fatigue cracking. Accordingly, Transport Canada AD CF-2024-
11 requires inspecting the T/R blade abrasion strips and, depending on 
the results, replacing or marking the T/R blade. Thereafter, Transport 
Canada AD CF-2024-11 requires repetitively checking the T/R blade 
abrasion strips and, depending on the results, replacing the T/R blade. 
Lastly, Transport Canada AD CF-2024-11 requires repetitively inspecting 
the T/R blade abrasion strips and, depending on the results, replacing 
the T/R blade or reapplying the marking. The FAA is issuing this AD to 
address the unsafe condition on these products.
    You may examine Transport Canada AD CF-2024-11 in the AD docket at 
regulations.gov under Docket No. FAA-2024-1466.

Related Material Under 1 CFR Part 51

    The FAA reviewed ASB 429-24-63. For certain serial-numbered T/R 
blades P/N 429-016-101-105, this material specifies procedures for 
cleaning the T/R blade abrasion strip and, using a bright light, 
visually inspecting each side of the T/R blade abrasion strip for a 
chordwise crack. If there is a crack, this material specifies 
procedures for replacing the T/R blade. If there is not a crack, this 
material specifies procedures for marking the T/R blade with a paint 
marker. Following application of the marking, this material specifies 
procedures for visually checking each side of the T/R blade abrasion 
strip for a chordwise crack before each engine start and a longer-term 
repetitive visual inspection of the T/R blade abrasion strip for a 
chordwise crack and if necessary, reapplying the marking. If a crack is 
found as a result of any check or longer-term visual inspection, this 
material specifies procedures for replacing the T/R blade.
    This material is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section.

FAA's Determination

    These helicopters 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 the State of Design 
Authority, it has notified the FAA of the unsafe condition described in 
its emergency AD and the material described above. The FAA is issuing 
this AD after determining that the unsafe condition described 
previously is likely to exist or develop on other products of the same 
type design.

AD Requirements

    This AD requires accomplishing the actions specified in Transport 
Canada AD CF-2024-11, except as discussed under ``Differences Between 
this AD and the Transport Canada Emergency AD.''
    This AD requires a check that the owner/operator (pilot) holding at 
least a private pilot certificate may perform and must enter compliance 
with the applicable paragraph of the AD into the helicopter maintenance 
records in accordance with 14 CFR 43.9(a) and 91.417(a)(2)(v). The 
pilot may perform this check because it only involves using a 
flashlight and visually checking affected T/R blade abrasion strips for 
a crack. This action could be performed equally well by a pilot or a 
mechanic. This is an exception to the FAA's standard maintenance 
regulations.

Differences Between This AD and the Transport Canada Emergency AD

    Regarding the initial inspection for a chordwise crack, this AD 
distinguishes requirements if there is or is not any coating (such as a 
protective tape or protective coating) over the T/R blade abrasion 
strip, whereas Transport Canada AD CF-2024-11 does not. This AD 
requires reporting certain information if any T/R blade abrasion strip 
has a crack, whereas Transport Canada AD CF-2024-11 does not. Transport 
Canada AD CF-2024-11 allows the installation of an affected T/R blade 
so long as it passes the inspection and is marked as required within, 
whereas this AD prohibits installing an affected T/R blade on any 
helicopter.

[[Page 45756]]

Interim Action

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

Justification for Immediate Adoption and Determination of the Effective 
Date

    Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 
U.S.C. 551 et seq.) authorizes agencies to dispense with notice and 
comment procedures for rules when the agency, for ``good cause,'' finds 
that those procedures are ``impracticable, unnecessary, or contrary to 
the public interest.'' Under this section, an agency, upon finding good 
cause, may issue a final rule without providing notice and seeking 
comment prior to issuance. Further, section 553(d) of the APA 
authorizes agencies to make rules effective in less than thirty days, 
upon a finding of good cause.
    An unsafe condition exists that required the immediate adoption of 
Emergency AD 2024-07-51, issued on March 29, 2024, to all known U.S. 
owners and operators of these helicopters. The FAA found that the risk 
to the flying public justified waiving notice and comment prior to 
adoption of this rule because the affected components are part of an 
assembly that is critical to the control of a helicopter. Multiple T/R 
abrasion strip cracks have been reported, and investigation revealed 
that a manufacturing defect exists in some of the abrasion strips, 
which may lead to fatigue cracking and catastrophic T/R blade failure, 
which in turn can cause the destruction of the T/R gearbox and loss of 
directional control. At this time, the growth rate of the fatigue 
cracking has not been determined. For these reasons, the initial 
actions required by this AD must be accomplished within three days or 
prior to the second flight after the effective date of this AD, 
whichever occurs first. Thereafter, other actions required by this AD 
must be accomplished before the second and each subsequent flight. 
These conditions still exist, therefore, notice and opportunity for 
prior public comment are impracticable and contrary to the public 
interest pursuant to 5 U.S.C. 553(b)(3)(B).
    In addition, the FAA finds that good cause exists pursuant to 5 
U.S.C. 553(d) for making this amendment effective in less than 30 days, 
for the same reasons the FAA found good cause to forego notice and 
comment.

Regulatory Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not 
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt 
a rule without prior notice and comment. Because the FAA has determined 
that it has good cause to adopt this rule without prior notice and 
comment, RFA analysis is not required.

Costs of Compliance

    The FAA estimates that this AD affects 145 helicopters of U.S. 
Registry. Labor rates are estimated at $85 per work-hour. Based on 
these numbers, the FAA estimates the following costs to comply with 
this AD.
    Actions required for a T/R blade abrasion strip with any coating 
could vary. The FAA has no data to determine the costs to accomplish 
these actions or the number of helicopters that may be affected by this 
requirement.
    Cleaning and inspecting a T/R blade abrasion strip takes 
approximately 0.5 work-hour for an estimated cost of up to $170 per 
helicopter (there are up to 4 affected T/R blades per helicopter) and 
$24,650 for the U.S. fleet, per inspection cycle. Checking a T/R blade 
abrasion strip takes approximately 0.25 work-hour for an estimated cost 
of up to $85 per helicopter and $12,325 for the U.S. fleet, per check 
cycle. Marking a T/R blade takes approximately 0.25 work-hour with a 
nominal parts cost for an estimated cost of up to $85 per helicopter 
and $12,325 for the U.S. fleet for the initial application and per 
reapplication.
    If required, replacing a T/R blade takes approximately 6 work-hours 
and parts cost approximately $53,802 for an estimated cost of $54,312 
per T/R blade. Reporting information takes approximately 1 work-hour 
for an estimated cost of $85 per T/R blade.

Paperwork Reduction Act

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

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    The FAA is issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: General requirements. 
Under that section, Congress charges the FAA with promoting safe flight 
of civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds necessary 
for safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national Government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866, and
    (2) Will not affect intrastate aviation in Alaska.

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.

[[Page 45757]]

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2024-07-51 Bell Textron Canada Limited: Amendment 39-22752; Docket 
No. FAA-2024-1466; Project Identifier MCAI-2024-00205-R.

(a) Effective Date

    The FAA issued Emergency Airworthiness Directive (AD) 2024-07-51 
on March 29, 2024, directly to affected owners and operators. As a 
result of such actual notice, the emergency AD was effective for 
those owners and operators on the date it was provided. This AD 
contains the same requirements as the emergency AD and, for those 
who did not receive actual notice, is effective on June 10, 2024.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bell Textron Canada Limited Model 429 
helicopters, serial number 57001 and subsequent, certificated in any 
category, with a tail rotor (T/R) blade part number 429-016-101-105 
having a serial number identified in Table 1 of Bell Alert Service 
Bulletin 429-24-63, dated March 21, 2024 (ASB 429-24-63), installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code: 6410, Tail Rotor 
Blades.

(e) Unsafe Condition

    This AD was prompted by multiple reports of T/R blade abrasion 
strip cracks. The FAA is issuing this AD to detect a cracked T/R 
blade abrasion strip. The unsafe condition, if not addressed, could 
result in severe imbalance, T/R blade failure, loss of the T/R 
gearbox, loss of directional control, and subsequent loss of control 
of the helicopter.

(f) Compliance

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

(g) Required Actions

    (1) For each T/R blade identified in paragraph (c) of this AD, 
within three days or prior to the second flight after the effective 
date of this AD, whichever occurs first, accomplish the actions 
required by paragraph (g)(1)(i) or (ii) of this AD, as applicable.
    (i) If there is any coating (such as a protective tape or 
protective coating) over the T/R blade abrasion strip, accomplish 
further actions in accordance with a method approved by the 
International Validation Branch, FAA; or Transport Canada; or Bell 
Textron Canada Ltd.'s Design Approval Organization (DAO). If 
approved by the DAO, the approval must include the DAO-authorized 
signature.
    (ii) If there is no coating over the T/R blade abrasion strip, 
clean the abrasion strip by following the Accomplishment 
Instructions, part I, paragraph 3, of ASB 429-24-63. Using a 
flashlight, visually inspect both sides of the T/R blade abrasion 
strip for a chordwise crack in the area shown in Figure 1 of ASB 
429-24-63. Figure 2 of ASB 429-24-63 shows an example of a T/R blade 
abrasion strip crack.
    (A) As a result of the actions required by paragraph (g)(1)(ii) 
of this AD, if there is any chordwise crack, before further flight, 
remove the T/R blade from service and replace it with an airworthy 
T/R blade.
    (B) As a result of the actions required by paragraph (g)(1)(ii) 
of this AD, if there is not a crack, before further flight, mark an 
``X'' on the T/R blade with a paint marker as shown in Figure 1 of 
ASB 429-24-63, except do not use the color blue, orange, red, or 
green. The letter ``X'' must have a minimum height of 3 inches.
    (2) For each T/R blade marked with an ``X,'' accomplish the 
actions required by paragraph (g)(2)(i) and (ii) of this AD.
    (i) Before the second flight after accomplishing the actions 
required by paragraph (g)(1)(ii)(B) of this AD, and thereafter 
before each subsequent flight, using a flashlight, visually check 
both sides of each abrasion strip for a chordwise crack. A chordwise 
crack runs from the direction of the leading edge to the trailing 
edge. A chordwise crack may be a straight or hairline crack. The 
owner/operator (pilot) holding at least a private pilot certificate 
may perform this check and must enter compliance with this paragraph 
of the AD into the helicopter maintenance records in accordance with 
14 CFR 43.9(a) and 91.417(a)(2)(v). The record must be maintained as 
required by 14 CFR 91.417, 121.380, or 135.439.
    (ii) As a result of the actions required by paragraph (g)(2)(i) 
of this AD, if there is any chordwise crack, before further flight, 
remove the T/R blade from service and replace it with an airworthy 
T/R blade.
    (3) For each T/R blade marked with an ``X,'' within 25 hours 
time-in-service after accomplishing the actions required by 
paragraph (g)(1)(ii)(B) of this AD and thereafter within intervals 
not to exceed 25 hours time-in-service, clean each abrasion strip by 
following the Accomplishment Instructions, part III, paragraph 2, of 
ASB 429-24-63. Using a flashlight, visually inspect each side of the 
T/R blade abrasion strip for a chordwise crack in the area shown in 
Figure 1 of ASB 429-24-63. Figure 2 of ASB 429-24-63 shows an 
example of a T/R blade abrasion strip crack. The actions required by 
this paragraph do not terminate the actions required by paragraph 
(g)(2)(i) of this AD.
    (i) As a result of the actions required by the introductory text 
of paragraph (g)(3) of this AD, if there is any chordwise crack, 
before further flight, remove the T/R blade from service and replace 
it with an airworthy T/R blade.
    (ii) As a result of the actions required by the introductory 
text of paragraph (g)(3) of this AD, if there is not a crack and the 
``X'' marking is deteriorated or not clearly visible, before further 
flight, reapply the ``X'' marking on the T/R blade with a paint 
marker as shown in Figure 1 of ASB 429-24-63, except do not use the 
color blue, orange, red, or green. The letter ``X'' must have a 
minimum height of 3 inches.
    (4) If there is any chordwise crack as a result of any action 
required by paragraph (g)(1)(ii), (g)(2)(i), or (g)(3) of this AD, 
within 7 days after completing the action, report the information in 
Appendix 1 to this AD by email to [email protected].
    (5) As of the effective date of this AD, do not install a T/R 
blade that is identified in paragraph (c) of this AD on any 
helicopter.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, International Validation Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Validation Branch, send 
it to the attention of the person identified in paragraph (i) of 
this AD or email to: [email protected]. If mailing 
information, also submit information by email.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(i) Additional Information

    For more information about this AD, contact Dan McCully, 
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; phone (404) 474-5548; email 
[email protected].

(j) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference of the material listed in this paragraph 
under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this material as applicable to do the actions 
required by this AD, unless this AD specifies otherwise.
    (i) Bell Alert Service Bulletin 429-24-63, dated March 21, 2024.
    (ii) [Reserved]
    (3) For Bell material, contact Bell Textron Canada Limited, 
12,800 Rue de l'Avenir, Mirabel, Quebec J7J 1R4, Canada; phone 1-
450-437-2862 or 1-800-363-8023; fax 1-450-433-0272; email 
[email protected]; or at bellflight.com/support/contact-support.
    (4) You may view this material at the FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-
321, Fort Worth, TX 76177. For information on the availability of 
this material at the FAA, call (817) 222-5110.
    (5) You may view this material at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].

Appendix 1 to AD 2024-07-51

    Report the following information for each cracked tail rotor 
blade abrasion strip by email to: [email protected].
    In the subject line of the email, include the text ``AD 2024-07-
51''.
    (1) Date of inspection or check that revealed a chordwise crack:

[[Page 45758]]

    (2) Total hours time-in-service on the tail rotor blade(s) with 
a cracked abrasion strip:
    (3) Date of previous inspection or check and total hours time-
in-service on the tail rotor blade(s) at the date of previous 
inspection or check:
    (4) Helicopter serial number:
    (5) Helicopter N-number:
    (6) Tail rotor blade serial number(s):
    (7) Indicate if each chordwise crack is on one or both sides of 
the tail rotor blade. Provide the following information for each 
chordwise crack: Measurement of the location of each chordwise crack 
as measured from the tail rotor blade tip and measurement of the 
length of each chordwise crack as measured from the tail rotor blade 
leading edge.
    (8) Describe in detail any information and findings, including 
any previous maintenance or modification of the cracked area, and, 
if possible, provide photos.

    Issued on May 20, 2024.
James D. Foltz,
Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2024-11420 Filed 5-21-24; 11:15 am]
BILLING CODE 4910-13-P