Airworthiness Directives; Cirrus Design Corporation Airplanes, 96863-96866 [2024-28552]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 89, Number 235 (Friday, December 6, 2024)]
[Rules and Regulations]
[Pages 96863-96866]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-28552]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-2546; Project Identifier AD-2024-00574-A; 
Amendment 39-22902; AD 2024-24-11]
RIN 2120-AA64


Airworthiness Directives; Cirrus Design Corporation Airplanes

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 Cirrus Design Corporation (Cirrus) Model SR20, SR22, and SR22T 
airplanes. This AD was prompted by a report of failure of the upper 
power lever. This AD requires repetitively inspecting (visual) the 
upper power lever for any crack(s) and depending on the results of any 
visual inspection, either inspecting (fluorescent penetrant) or 
replacing the upper power lever. This AD also requires reporting all 
inspection results to the FAA. The FAA is issuing this AD to address 
the unsafe condition on these products.

DATES: This AD is effective December 23, 2024.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 23, 
2024.
    The FAA must receive comments on this AD by January 21, 2025.

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-2024-2546; 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 Cirrus material identified in this AD, contact Cirrus 
Design Corporation, 4515 Taylor Circle, Duluth, MN 55811; phone: (218) 
788-3000; fax: (218) 788-3525; email: cirrusaircraft.com">fieldservice@cirrusaircraft.com; 
website: cirrusaircraft.com.
     You may view this material at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 901 Locust, Kansas City, 
MO 64106. For information on the availability of this material at the 
FAA, call (817) 222-5110. It is also available at regulations.gov under 
Docket No. FAA-2024-2546.

FOR FURTHER INFORMATION CONTACT: Gregory Koenig, Aviation Safety 
Engineer, FAA, 1801 S Airport Road, Wichita, KS 67209; phone: (847) 
294-7127; 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 
the ADDRESSES section. Include ``Docket No. FAA-2024-2546; Project 
Identifier AD-2024-00574-A'' 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 
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

[[Page 96864]]

confidential under the FOIA, and they will not be placed in the public 
docket of this AD. Submissions containing CBI should be sent to Gregory 
Koenig, Aviation Safety Engineer, FAA, 1801 S Airport Road, Wichita, KS 
67209. 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 is issuing this AD to correct an unsafe condition on 
certain Cirrus Model SR20, SR22, and SR22T airplanes. The FAA received 
a report that a Cirrus Model SR20 airplane was involved in an incident 
where the upper power lever failed while advancing to full throttle in 
preparation for takeoff. The flight was successfully aborted by cutting 
fuel to the airplane. After the incident, an additional 26 upper power 
levers have been reported to have cracks. The available data indicates 
that the probability of visual inspection methods to detect cracks in 
the upper power levers are inadequate, and therefore a fluorescent 
penetrant inspection (FPI) is also necessary if cracks are not detected 
during the visual inspection. These cracks have only been discovered on 
upper power levers that include a takeoff/go-around switch. This 
condition, if not addressed, could result in loss of engine thrust 
control and reduced control of the airplane. The FAA is issuing this AD 
to address the unsafe condition on these products.

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 design.

Material Incorporated by Reference Under 1 CFR Part 51

    The FAA reviewed Cirrus SR2X Service Bulletin SB2X-76-05, dated 
October 29, 2024 (Cirrus SB2X-76-05). This material specifies 
procedures for inspecting the upper power lever and replacement of the 
upper power lever if cracks are found. 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 accomplishing the actions specified in the 
material described previously, except as discussed under ``Differences 
Between this AD and the Referenced Material.'' This AD also requires 
sending all inspection results to the FAA.

Differences Between This AD and the Referenced Material

    The effectivity in Cirrus SB2X-76-05 specifies certain airplane 
serial numbers through 9749, but this AD is applicable to Model SR20, 
SR22, and SR22T airplanes, certificated in any category, that are 
equipped with upper power lever part number (P/N) 19181-001, 19181-002, 
or 46505-001.
    Cirrus SB2X-76-05 specifies that the compliance time is within 10 
flight hours for airplanes with 2,000 flight hours or more, but this AD 
has a compliance time of before an upper power lever accumulates 1,200 
hours time-in-service (TIS), within 10 hours TIS on the upper power 
lever after the effective date of this AD, or within 15 days after the 
effective date of this AD, whichever occurs later. This compliance time 
was developed based on data received from the 27 reported incidents, 
which indicated that an incident occurred as low as 2,948 hours TIS and 
that this unsafe condition could occur on airplanes with 1,200 hours 
TIS accumulated on the upper power lever. Based on this incident data, 
coupled with the fact that a large number of airplanes are either 
approaching or over 1,200 hours TIS and the propagation rate for this 
unsafe condition is unknown, the FAA's risk assessment was that the 
accumulation of 2,000 flight hours or more would not adequately 
mitigate the unsafe condition.
    Cirrus SB2X-76-05 includes an action to revise the aircraft 
maintenance manual (AMM) by including a temporary revision that 
specifies repetitive inspections every 2,000 hours TIS, but this AD 
does not require this AMM revision. Instead, this AD requires 
repetitive inspections at intervals not to exceed 110 hours TIS. While 
Cirrus specifies a repetitive inspection every 2,000 hours TIS, the FAA 
is requiring a repetitive inspection at a frequency that considers the 
potential development and propagation of these cracks beyond 1,200 
hours TIS.
    Cirrus SB2X-76-05 does not specify reporting inspection results and 
this AD requires reporting inspection results to the FAA.
    Cirrus SB2X-76-05 specifies to return cracked (damaged) upper power 
levers to Cirrus, but this AD does not require this action. This AD, 
instead, requires removing any cracked (damaged) upper power lever from 
service.
    Replacing the upper power lever with P/N 19181-001, 19181-002, or 
46505-001 does not terminate the requirements of this AD. The 
inspection would be required before any affected upper power lever 
accumulates 1,200 hours TIS.

Interim Action

    The FAA considers this AD to be an interim action. The manufacturer 
is currently developing a terminating action that will address the 
unsafe condition identified in this AD. Once the modification is 
developed, approved, and available, the FAA might consider additional 
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 cracking in the upper power lever leads to failure of the upper 
power lever, which could result in loss of engine thrust control and 
reduced control of the airplane. The FAA's initial analysis based on 
crack data from the reported incidents shows that this condition could 
occur on airplanes with 1,200 hours TIS accumulated on the upper power 
lever. Since a large percentage of the Cirrus Model SR20, SR22, and 
SR22T airplanes have exceeded or are approaching 1,200 hours TIS and 
because the propagation rate for this unsafe condition is unknown, an 
inspection of the upper power lever is required within 10 hours TIS or 
15 days after the effective date of this AD, whichever occurs later, 
for airplanes before accumulating 1,200 hours TIS to detect cracks in 
the upper power lever. These compliance times are shorter than the time 
necessary for the public to comment and for publication of the final 
rule. Accordingly, notice and opportunity for prior public comment are 
unnecessary, pursuant to 5 U.S.C. 553(b).
    In addition, for the foregoing reason(s), the FAA finds that good 
cause

[[Page 96865]]

exists pursuant to 5 U.S.C. 553(d) for making this amendment effective 
in less than 30 days.

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 6,811 airplanes of U.S. 
registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
            Action                Labor cost      Parts cost      Cost per product       Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Perform visual inspection....  2 work-hours x             $0  $170 per inspection.....  $1,157,870 per
                                $85 per hour =                                           inspection.
                                $170 per
                                inspection.
Report inspection results....  1 work-hour x               0  $85 per inspection......  $578,935 per inspection.
                                $85 per hour =
                                $85 per
                                inspection.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Perform FPI...................................  2 work-hours x $85 per hour =                 $0            $170
                                                 $170 per inspection.
Replace upper power lever.....................  1 work-hour x $85 per hour = $85              50             135
----------------------------------------------------------------------------------------------------------------

    The FAA has included all known costs in its cost estimate. 
According to the manufacturer, however, some of the costs of this AD 
may be covered under warranty, thereby reducing the cost impact on 
affected operators.

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:

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 adding the following new airworthiness 
directive:

2024-24-11 Cirrus Design Corporation: Amendment 39-22902; Docket No. 
FAA-2024-2546; Project Identifier AD-2024-00574-A.

(a) Effective Date

    This airworthiness directive (AD) is effective December 23, 
2024.

(b) Affected ADs

    None.

[[Page 96866]]

(c) Applicability

    This AD applies to Cirrus Design Corporation Model SR20, SR22, 
and SR22T airplanes, certificated in any category, that are equipped 
with upper power lever part number (P/N) 19181-001, 19181-002, or 
46505-001.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7603, Power Lever.

(e) Unsafe Condition

    This AD was prompted by a report of failure of the upper power 
lever. The FAA is issuing this AD to detect and address cracks in 
the upper power lever. The unsafe condition, if not addressed, could 
result in loss of engine thrust control and reduced control of the 
airplane.

(f) Compliance

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

(g) Required Actions

    (1) Initially, at whichever time occurs latest in paragraphs 
(g)(1)(i) through (iii) of this AD and thereafter at intervals not 
to exceed 110 hours time-in-service (TIS), visually inspect the 
upper power lever in accordance with paragraphs A. through F. of the 
Accomplishment Instructions in Cirrus SR2X Service Bulletin SB2X-76-
05, dated October 29, 2024 (Cirrus SB2X-76-05).
    (i) Before any upper power lever identified in paragraph (c) of 
this AD accumulates 1,200 hours TIS,
    Note 1 to paragraph (g)(1)(i): These parts are not serialized. 
If by checking the logbook, you cannot determine how many hours the 
upper power lever has since installation, then you may use the hours 
TIS of the airplane.
    (ii) Within 10 hours TIS on the upper power lever after the 
effective date of this AD; or
    (iii) Within 15 days after the effective date of this AD.
    (2) If any crack(s) are found during any inspection required by 
paragraph (g)(1) of this AD, before further flight, replace the 
upper power lever with a new (zero hours TIS) upper power lever and 
do the actions in accordance with paragraphs L. through N. of the 
Accomplishment Instructions in Cirrus SB2X-76-05, as applicable.
    (3) If no crack(s) are found during any inspection required by 
(g)(1) of this AD, before further flight, perform a fluorescent 
penetrant inspection in accordance with paragraphs G. through J. of 
the Accomplishment Instructions in Cirrus SB2X-76-05.
    (i) If any crack(s) are found during any inspection required by 
paragraph (g)(3) of this AD, before further flight, replace the 
upper power lever with a new (zero hours TIS) upper power lever and 
do the actions in accordance with paragraphs L. through N. of the 
Accomplishment Instructions in Cirrus SB2X-76-05, as applicable.
    (ii) If no crack(s) are found during any inspection required by 
paragraph (g)(3) of this AD, reinstall the existing upper power 
lever and do the actions in accordance with paragraphs L. through N. 
of the Accomplishment Instructions in Cirrus SB2X-76-05, as 
applicable.
    (4) Cirrus SB2X-76-05 specifies to return cracked (damaged) 
upper power levers to Cirrus, this AD does not require that action 
but requires removing any cracked (damaged) upper power lever from 
service.

(h) Reporting Requirement

    Within 5 days after the inspections required by paragraphs 
(g)(1) and (3) of this AD or within 5 days after the effective date 
of this AD, whichever occurs later, report all inspection results to 
the FAA at the address specified in paragraph (j) of this AD. The 
report must include the airplane registration and serial number, 
results of each inspection, the airplane's hours TIS, and any 
additional operator/mechanic comments.

(i) Alternative Methods of Compliance (AMOCs)

    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 Central Certification Branch, send it 
to the attention of the person identified in paragraph (j) of this 
AD. Information may be emailed to: [email protected]. 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) Additional Information

    For more information about this AD, contact Gregory Koenig, 
Aviation Safety Engineer, FAA, 1801 S Airport Road, Wichita, KS 
67209; phone: (847) 294-7127; email: [email protected].

(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) Cirrus SR2X Service Bulletin SB2X-76-05, dated October 29, 
2024.
    (ii) [Reserved]
    (3) For Cirrus material identified in this AD, contact Cirrus 
Design Corporation, 4515 Taylor Circle, Duluth, MN 55811; phone: 
(218) 788-3000; fax: (218) 788-3525; email: 
cirrusaircraft.com">fieldservice@cirrusaircraft.com; website: cirrusaircraft.com.
    (4) You may view this material at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 901 Locust, Kansas 
City, MO 64106. For information on the availability of this material 
at the FAA, call (817) 222-5110.
    (5) You may view this material at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].

    Issued on November 27, 2024.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2024-28552 Filed 12-3-24; 11:15 am]
BILLING CODE 4910-13-P