Rule2024-18580
Airworthiness Directives; Bell Textron Inc. (Type Certificate Previously Held by Bell Helicopter Textron, Inc.), Helicopters
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
August 20, 2024
Effective
September 4, 2024
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is superseding Airworthiness Directive (AD) 2000-18- 09, which applied to certain Bell Helicopter Textron, Inc. (now Bell Textron Inc.), Model 412, 412CF, and 412EP helicopters. AD 2000-18-09 required repetitively inspecting the upper left-hand cap angle (cap angle) and adjacent structure for a crack and, depending on the results, replacing any cracked cap angle and repairing any crack in the adjacent structure. This AD was prompted by a report of a fatigue crack in a tail boom attachment cap angle. This AD retains the requirements of AD 2000-18-09, expands the applicability by adding models and an additional part-numbered cap angle, reduces the inspection intervals, and requires using updated procedures. This AD also updates the reporting requirement. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 89 Issue 161 (Tuesday, August 20, 2024)</title>
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[Federal Register Volume 89, Number 161 (Tuesday, August 20, 2024)]
[Rules and Regulations]
[Pages 67263-67267]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2024-18580]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-2010; Project Identifier AD-2024-00366-R;
Amendment 39-22807; AD 2024-16-01]
RIN 2120-AA64
Airworthiness Directives; Bell Textron Inc. (Type Certificate
Previously Held by Bell Helicopter Textron, Inc.), Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2000-18-
09, which applied to certain Bell Helicopter Textron, Inc. (now Bell
Textron Inc.), Model 412, 412CF, and 412EP helicopters. AD 2000-18-09
required repetitively inspecting the upper left-hand cap angle (cap
angle) and adjacent structure for a crack and, depending on the
results, replacing any cracked cap angle and repairing any crack in the
adjacent structure. This AD was prompted by a report of a fatigue crack
in a tail boom attachment cap angle. This AD retains the requirements
of AD 2000-18-09, expands the applicability by adding models and an
additional part-numbered cap angle, reduces the inspection intervals,
and requires using updated procedures. This AD also updates the
reporting requirement. The FAA is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective September 4, 2024.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of September 4,
2024.
The FAA must receive comments on this AD by October 4, 2024.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://regulations.gov">regulations.gov</a>. Follow
the instructions for submitting comments.
<bullet> Fax: 202-493--2251.
<bullet> 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.
<bullet> 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 <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2024-2010; 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.
[[Page 67264]]
Material Incorporated by Reference:
<bullet> For Bell material identified in this AD, contact Bell
Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; phone: (450) 437-
2862 or (800) 363-8023; fax: (450) 433-0272; email:
<a href="/cdn-cgi/l/email-protection#eb9b99848f9e889f989e9b9b84999fab898e87878d87828c839fc5888486"><span class="__cf_email__" data-cfemail="18686a777c6d7b6c6b6d6868776a6c587a7d74747e74717f706c367b7775">[email protected]</span></a>; website: <a href="http://bellflight.com/support/contact-support">bellflight.com/support/contact-support</a>.
<bullet> 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.
FOR FURTHER INFORMATION CONTACT: Hung Nguyen, Aviation Safety Engineer,
FAA, 1801 S Airport Road, Wichita, KS 67209; phone: (562) 627-5362;
email: <a href="/cdn-cgi/l/email-protection#452d302b226b336b2b22303c202b052324246b222a33"><span class="__cf_email__" data-cfemail="79110c171e570f57171e0c001c17391f1818571e160f">[email protected]</span></a>.
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
the ADDRESSES section. Include ``Docket No. FAA-2024-2010; Project
Identifier AD-2024-00366-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 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
<a href="http://regulations.gov">regulations.gov</a>, 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 Hung
Nguyen, Aviation Safety Engineer, FAA, 1801 S Airport Road, Wichita, KS
67209; phone: (562) 627-5362; email: <a href="/cdn-cgi/l/email-protection#80e8f5eee7aef6aeeee7f5f9e5eec0e6e1e1aee7eff6"><span class="__cf_email__" data-cfemail="69011c070e471f47070e1c100c07290f0808470e061f">[email protected]</span></a>. Any
commentary that the FAA receives which is not specifically designated
as CBI will be placed in the public docket for this rulemaking.
Background
The FAA issued AD 2000-18-09, Amendment 39-11894 (65 FR 55175,
September 13, 2000) (AD 2000-18-09), for Bell Helicopter Textron, Inc.
(now Bell Textron Inc.), Model 412, 412CF, and 412EF helicopters with
cap angle part number (P/N) 212-030-191-001, installed. AD 2000-18-09
was prompted by a report of a fatigue crack in a tail boom attachment
cap angle. AD 2000-18-09 required repetitively inspecting certain part-
numbered cap angles for a crack and, depending on the results,
replacing a cracked cap angle with an airworthy cap angle and repairing
any cracked adjacent structure. AD 2000-18-09 also required reporting
any crack to the FAA. The FAA issued AD 2000-18-09 to prevent failure
of a cap angle, loss of the tail boom, and subsequent loss control of
the helicopter.
Actions Since Issuance of AD 2000-18-09
Since the FAA issued AD 2000-18-09, Bell Textron Inc., has received
additional reports of occurrences of fractured cap angles, which were
found during routine inspections and during the repetitive 100 hours
time-in-service (TIS) inspection required by AD 2000-18-09. Further
investigation revealed the 100 hours TIS interval is not adequate to
detect cracks before fracture of a cap angle could occur. Accordingly,
Bell Textron Inc., issued updated material to reduce the inspection
interval to 25 flight hours for certain helicopters and 50 flight hours
for certain other helicopters to detect cracks and prevent failures of
the cap angle. The updated material also specifies inspecting for and
removing any sealant before inspecting the cap angle area.
Additionally, due to the similarity to Model 412, 412CF, and 412EP
helicopters, the FAA determined that Bell Textron Inc., Model 212,
205A, 205A-1, and 205B helicopters are also affected by the same unsafe
condition.
Furthermore, since AD 2000-18-09 was issued, the FAA has revised
its writing practices to comply with updated formats and policy. As a
result, paragraph identifiers have changed and the reporting
requirement that was required by AD 2000-18-09 has been revised in this
AD. This AD also incorporates updated procedures by reference and
removes the information in Note 1 of AD 2000-18-09 as that information
is understood.
Lastly, since the FAA issued AD 2000-18-09, Bell Helicopter
Textron, Inc., changed its name to Bell Textron Inc.; this AD reflects
that change.
FAA's Determination
The FAA is issuing this AD because the agency determined the unsafe
condition described previously is likely to exist or develop in other
products of the same type designs.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed Bell Alert Service Bulletin (ASB) 205-24-122 for
Model 205A and 205A-1 helicopters, Bell ASB 205B-24-77 for Model 205B
helicopters, Bell ASB 212-24-169 for Model 212 helicopters, Bell ASB
412-24-197 for Model 412 and 412EP helicopters, and Bell ASB 412CF-24-
77 for Model 412CF helicopters, all dated April 22, 2024. This material
specifies procedures for inspecting for and removing any sealant,
inspecting the cap angle area with a 10X magnifying glass and bright
light for a crack and if a crack is found, this material specifies
replacing the cap angle or contacting Bell for further instructions.
This material also specifies touching up any primer that may have been
damaged during the sealant removal.
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.
AD Requirements
This AD requires visually inspecting for sealant around the edge of
the fitting and depending on the results, removing any sealant. This AD
also requires, using a 10X or higher power magnifying glass and
flashlight, inspecting the cap angle and adjacent structure for a
crack. Depending on these results, this AD requires removing an
affected cap angle from service and installing an airworthy cap angle,
repairing an affected adjacent structure, and reporting certain
information to the FAA.
Differences Between This AD and the Referenced Material
If there is a crack in the cap angle and the helicopter is at a
location where the cap angle cannot be replaced, the referenced
material specifies contacting
[[Page 67265]]
the manufacturer, whereas this AD does not include that action.
If there is a crack in the adjacent structure to the cap angle,
this AD requires repairing the adjacent structure in accordance with a
method approved by the FAA, whereas the referenced material does not
address this condition.
If there is a crack, this AD requires reporting certain
information, whereas the referenced material does not.
Interim Action
The FAA considers this AD to be an interim action. The manufacturer
is currently investigating the root cause of the unsafe condition
identified in this AD. If final action is later identified, the FAA
might consider further rulemaking.
Justification for Immediate Adoption and Determination of the Effective
Date
Section 553(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 requires the immediate adoption of
this AD without providing an opportunity for public comments prior to
adoption. The FAA has found that the risk to the flying public
justifies forgoing 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. In addition, cracking could
lead to instantaneous failure before detection. As the FAA has no
information pertaining to the extent of cracking of the affected
components that may currently exist in helicopters or how quickly the
condition may propagate to failure, for certain helicopters the initial
instance of the actions required by this AD must be accomplished within
25 hours TIS, and thereafter within intervals not to exceed 25 hours
TIS. Based on the average flight-hour utilization rate of these
helicopters, the compliance time for the initial instance of the
required actions is a period of up to 1 month. Accordingly, notice and
opportunity for prior public comment are impracticable and contrary to
the public interest pursuant to 5 U.S.C. 553(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 forgo 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 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 157 helicopters of U.S.
registry. Labor costs are estimated at $85 per work-hour. Based on
these numbers, the FAA estimates the following costs to comply with
this AD.
Visually inspecting for the presence of sealant takes a minimal
amount of time for a nominal cost. If required, removing sealant will
take approximately 0.5 work-hour for an estimated cost of $43 per
helicopter.
Inspecting the cap angle and adjacent structure will take
approximately 0.5 work-hour for an estimated cost of $43 per helicopter
and $6,751 for the U.S. fleet, per inspection cycle.
If required, replacing an affected cap angle will take
approximately 400 work-hours and parts will cost up to approximately
$1,171 for an estimated cost of $35,171 per replacement.
If required, repairing an adjacent structure will take
approximately 16 work-hours for an estimated cost of $1,360 per
helicopter. The FAA has no data to determine the parts costs to
accomplish this repair.
If required, reporting inspection results will take approximately 1
work-hour for an estimated cost of $85 per report.
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 a 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 above, 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:
[[Page 67266]]
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 2000-18-09, Amendment 39-11894 (65
FR 55175, September 13, 2000); and
0
b. Adding the following new airworthiness directive:
2024-16-01 Bell Textron Inc. (Type Certificate previously held by
Bell Helicopter Textron, Inc.): Amendment 39-22807; Docket No. FAA-
2024-2010; Project Identifier AD-2024-00366-R.
(a) Effective Date
This airworthiness directive (AD) is effective September 4,
2024.
(b) Affected ADs
This AD replaces AD 2000-18-09, Amendment 39-11894 (65 FR 55175,
September 13, 2000).
(c) Applicability
This AD applies to Bell Textron Inc. (type certificate
previously held by Bell Helicopter Textron, Inc.), Model 205A, 205A-
1, 205B, 212, 412, 412CF, and 412EP helicopters, certificated in any
category, identified in paragraphs (c)(1) and (2) of this AD.
(1) Model 205A, 205A-1, and 205B helicopters, with an upper
left-hand cap angle (cap angle) part number (P/N) 205-030-207-005
installed.
(2) Model 212, 412, 412CF, and 412EP helicopters, with a cap
angle P/N 212-030-191-001 installed.
(d) Subject
Joint Aircraft System Component (JASC) Code: 5300, Fuselage
structure.
(e) Unsafe Condition
This AD was prompted by reports of a fatigue crack in a tail
boom attachment cap angle. The FAA is issuing this AD to prevent
failure of a cap angle. The unsafe condition, if not addressed,
could result in failure of the fuselage and bulkhead, and subsequent
separation of the tail boom and loss control of the helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) For Model 205A, 205A-1, 205B, 212, 412CF, and 412
helicopters identified in paragraph (c) of this AD; and for Model
412EP helicopters identified in paragraph (c)(2) of this AD with
serial numbers 36087 through 36693 inclusive, within 25 hours time-
in-service (TIS) after the effective date of this AD, and thereafter
at intervals not to exceed 25 hours TIS; and for Model 412EP
helicopters identified in paragraph (c)(2) of this AD with serial
numbers 36694 through 36999 inclusive and 37002 through 37999
inclusive, within 50 hour TIS after the effective date of this AD,
and thereafter at intervals not to exceed 50 hours TIS, accomplish
the actions required by paragraphs (g)(1)(i) and (ii) of this AD.
(i) Visually inspect for the presence of sealant around the
forward edge of the left-hand tail boom cap angle fitting in the
``Inspection Area'' depicted in Figure 1., of Bell Alert Service
Bulletin (ASB) 205-24-122, Bell ASB 205B-24-77, Bell ASB 212-24-169,
Bell ASB 412-24-197, or Bell ASB 412CF-24-77, all dated April 22,
2024, as applicable to your model helicopter. If there is any
sealant, before further flight, remove any sealant by following the
Accomplishment Instructions, paragraph 2., of Bell ASB 205-24-122,
Bell ASB 205B-24-77, Bell ASB 212-24-169, Bell ASB 412-24-197, or
Bell ASB 412CF-24-77, all dated April 22, 2024, as applicable to
your model helicopter.
(ii) Using a 10X or higher power magnifying glass and
flashlight, visually inspect the cap angle and adjacent structure
for a crack in the ``Inspection Area'' depicted in Figure 1., of
Bell ASB 205-24-122, Bell ASB 205B-24-77, Bell ASB 212-24-169, Bell
ASB 412-24-197, or Bell ASB 412CF-24-77, all dated April 22, 2024,
as applicable to your model helicopter.
(A) If there is any crack in the cap angle, before further
flight, remove the cap angle from service and install an airworthy
cap angle.
(B) If there is any crack in the adjacent structure, before
further flight, repair the structure in accordance with a method
approved by the Manager, Central Certification Branch, FAA. For a
repair method to be approved by the Manager, Central Certification
Branch, FAA; as required by this paragraph, the Manager's approval
letter must specifically refer to this AD.
(2) If there is a crack as a result of any instance of an
inspection required by paragraph (g)(1)(ii) of this AD, within 10
days after completing the inspection, report the information in
Appendix 1 to this AD by email to <a href="/cdn-cgi/l/email-protection#feb18e9b8c9f8a9791909f92ad9f989b8a87be989f9fd0999188"><span class="__cf_email__" data-cfemail="5916293c2b382d30363738350a383f3c2d20193f3838773e362f">[email protected]</span></a>.
(h) Special Flight Permit
Special flight permits may be issued in accordance with 14 CFR
21.197 and 21.199 to operate the helicopter to a location where the
actions required by this AD can be performed, provided after
takeoff, the flight is straight and level until landing, and avoids
areas of known turbulence and provided no passengers are onboard.
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Central Certification 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 certification office, send it to the
attention of the person identified in paragraph (j) of this AD.
Information may be emailed to: <a href="/cdn-cgi/l/email-protection#94d5d9dbd7d4f2f5f5baf3fbe2"><span class="__cf_email__" data-cfemail="22636f6d61624443430c454d54">[email protected]</span></a>.
(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.
(j) Related Information
For more information about this AD, contact Hung Nguyen,
Aviation Safety Engineer, FAA, 1801 S Airport Road, Wichita, KS
67209; phone: (562) 627-5362; email: <a href="/cdn-cgi/l/email-protection#89e1fce7eea7ffa7e7eefcf0ece7c9efe8e8a7eee6ff"><span class="__cf_email__" data-cfemail="bad2cfd4dd94cc94d4ddcfc3dfd4fadcdbdb94ddd5cc">[email protected]</span></a>.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the material listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this material as applicable to do the actions
required by this AD, unless the AD specifies otherwise.
(i) Bell Alert Service Bulletin (ASB) 205-24-122, dated April
22, 2024.
(ii) Bell ASB 205B-24-77, dated April 22, 2024.
(iii) Bell ASB 212-24-169, dated April 22, 2024.
(iv) Bell ASB 412-24-197, dated April 22, 2024.
(v) Bell ASB 412CF-24-77, dated April 22, 2024.
(3) For Bell material identified in this AD, contact Bell
Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; phone: (450) 437-
2862 or (800) 363-8023; fax: (450) 433-0272; email:
<a href="/cdn-cgi/l/email-protection#4030322f24352334333530302f32340022252c2c262c292728346e232f2d"><span class="__cf_email__" data-cfemail="1464667b70617760676164647b6660547671787872787d737c603a777b79">[email protected]</span></a>; website: <a href="http://bellflight.com/support/contact-support">bellflight.com/support/contact-support</a>.
(4) You may view this material at the FAA, Office of Regional
Counsel, Southwest Region, 10101 Hillwood Pkwy., 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 <a href="http://www.archives.gov/federal-register/cfr/ibr-locations">www.archives.gov/federal-register/cfr/ibr-locations</a> or email <a href="/cdn-cgi/l/email-protection#ee889cc087809d9e8b8d9a878180ae808f9c8fc0898198"><span class="__cf_email__" data-cfemail="761004581f1805061315021f1918361817041758111900">[email protected]</span></a>.
Appendix 1 to AD 2024-16-01
Report the following information for each crack by email to:
<a href="/cdn-cgi/l/email-protection#eaa59a8f988b9e8385848b86b98b8c8f9e93aa8c8b8bc48d859c"><span class="__cf_email__" data-cfemail="145b64716675607d7b7a757847757271606d547275753a737b62">[email protected]</span></a>.
In the subject line of the email, include the text ``AD 2024-16-
01''.
(1) Date of inspection that revealed a crack in the cap angle or
in the adjacent structure.
(2) Helicopter Model:
(3) Date of previous inspection of the cap angle and adjacent
structure:
(4) Helicopter serial number:
(5) Total hours time-in-service accumulated since new on the
airframe:
(6) Helicopter N-number:
(7) Cap angle(s) part number:
(8) Describe in detail any information and findings, including
any previous maintenance or modification of the cracked area, any
cracks in the surrounding areas such as the fitting or web, and, if
possible, provide photos.
[[Page 67267]]
Issued on August 1, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2024-18580 Filed 8-15-24; 11:15 am]
BILLING CODE 4910-13-P
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This is legal information, not legal advice. Laws vary by jurisdiction and change frequently. Always verify current law with official sources and consult a licensed attorney in your jurisdiction for advice on your specific situation.