Airworthiness Directives; M7 Aerospace LLC Airplanes

[Federal Register Volume 86, Number 13 (Friday, January 22, 2021)]
[Rules and Regulations]
[Pages 6559-6561]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-01332]



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                                                Federal Register
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Federal Register / Vol. 86, No. 13 / Friday, January 22, 2021 / Rules 
and Regulations

[[Page 6559]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0910; Project Identifier 2018-CE-044-AD; Amendment 
39-21378; AD 2021-01-02]
RIN 2120-AA64


Airworthiness Directives; M7 Aerospace LLC Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for M7 
Aerospace LLC Models SA26-AT and SA26-T airplanes. This AD was prompted 
by reports of the airplane power lever linkage detaching from the 
TPE331 engine propeller pitch control (PPC) shaft. This AD requires 
repetitively inspecting the PPC for proper torque and making any 
necessary corrections until the replacement of the PPC assembly and the 
installation of a secondary retention feature (safety wire) are done. 
The FAA is issuing this AD to address the unsafe condition on these 
products.

DATES: This AD is effective February 26, 2021.
    The Director of the Federal Register approved the incorporation by 
reference (IBR) of a certain publication listed in this AD as of May 5, 
2017 (82 FR 15982, March 31, 2017).

ADDRESSES: For service information identified in this final rule, 
contact Honeywell International Inc., 111 S 34th Street, Phoenix, 
Arizona 85034-2802; phone: 855-808-6500; email: 
[email protected]; internet: https://aerospace.honeywell.com/en/services/maintenance-and-monitoring. You may 
view this service information at the FAA, Airworthiness Products 
Section, Operational Safety Branch, 901 Locust, Kansas City, Missouri 
64106. For information on the availability of this material at the FAA, 
call 816-329-4148. It is also available at https://www.regulations.gov 
by searching for and locating Docket No. FAA-2020-0910.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2020-0910; 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 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.

FOR FURTHER INFORMATION CONTACT: Jonas Perez, Aerospace Engineer, Fort 
Worth ACO Branch, FAA, 10101 Hillwood Parkway, Fort Worth, Texas 76177-
1524; phone: 817-222-5145; fax: 817-222-5960; email: 
[email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to M7 Aerospace LLC Models 
SA26-AT and SA26-T airplanes. The NPRM published in the Federal 
Register on October 14, 2020 (85 FR 64993). The NPRM was prompted by 
reports of the airplane power lever linkage detaching from the TPE331 
engine PPC shaft. In the NPRM, the FAA proposed to require repetitively 
inspecting the PPC for proper torque and making any necessary 
corrections until the replacement of the PPC assembly and the 
installation of a secondary retention feature (safety wire) are done. 
The FAA is issuing this AD to prevent uncommanded change to the engine 
power settings with consequent loss of control.

Discussion of Final Airworthiness Directive

Comments

    The FAA received no comments on the NPRM or on the determination of 
the costs.

Conclusion

    The FAA reviewed the relevant data 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. This AD is 
adopted as proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Honeywell International Inc. Service Bulletin 
TPE331-72-2190, dated December 21, 2011, which contains procedures for 
replacing or reworking the propeller pitch control assembly, 
incorporating a threaded hole in the splined end of the shouldered 
shaft, and reassembling the propeller pitch control assembly. Honeywell 
International Inc. Service Bulletin TPE331-72-2190, dated December 21, 
2011, was previously approved for IBR on May 5, 2017 (82 FR 15982, 
March 31, 2017). 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.

Other Related Service Information

    The FAA also reviewed paragraph j. of M7 Aerospace SA26 Series 
Maintenance Manual Temporary Revision 4-02, dated July 22, 2020, which 
contains information related to the installation of the secondary 
retention feature (safety wire) on the airplane PPC lever and the PPC 
assembly.

Costs of Compliance

    The FAA estimates that this AD affects 55 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

[[Page 6560]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                              Cost per          Cost on U.S.
              Action                      Labor cost         Parts cost        product           operators
----------------------------------------------------------------------------------------------------------------
Install secondary retention         1 work-hour x $85 per             $10             $95  $5,225.
 feature (safety wire).              hour = $85.
Inspect PPC lever.................  1 work-hour x $85 per               0              85  $4,675 per inspection
                                     hour = $85 per                                         cycle.
                                     inspection cycle.
Repair, replace, and/or rework PPC  19 work-hours x $85             1,000           2,615  $143,825.
 lever input shaft.                  per hour = $1,615.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any adjustment that 
would be required based on the results of the inspection. The FAA has 
no way of determining the number of aircraft that might need the 
adjustment:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Correct attachment of the PPC lever...........  1 work-hour x $85 per hour = $85              $0             $85
----------------------------------------------------------------------------------------------------------------

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,
    (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 adding the following new airworthiness 
directive:

2021-01-02 M7 Aerospace LLC: Amendment 39-21378; Docket No. FAA-
2020-0910; Project Identifier 2018-CE-044-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective February 26, 
2021.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to M7 Aerospace LLC Model SA26-AT and SA26-T 
airplanes, all serial numbers, certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 61, Propellers/
propulsors.

(e) Unsafe Condition

    This AD was prompted by reports of the airplane power lever 
linkage detaching from the TPE331 engine propeller pitch control 
(PPC) shaft. The FAA is issuing this AD to address detachment of the 
power lever linkage to the TPE331 engine PPC shaft, which could 
result in uncommanded change to the engine power settings with 
consequent loss of control.

(f) Compliance

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

(g) PPC Lever Inspection

    (1) Within 100 hours time-in-service (TIS) after the effective 
date of this AD and thereafter at intervals not to exceed 100 hours 
TIS, inspect the security of the PPC lever by pulling the PPC lever 
upward by hand to ensure it does not detach from the PPC input 
shaft. If the PPC lever detaches during any inspection, before 
further flight, comply with paragraphs (h) and (i) of this AD.
    (2) The replacement/re-identification required by paragraph (h) 
of this AD and the installation of the secondary retention feature 
(safety wire) required by paragraph (i) of this AD terminate the 
repetitive inspections of the PPC lever attachment required by 
paragraph (g)(1) of this AD.

(h) Replace and Inspect the PPC Assembly

    Within 600 hours TIS after the effective date of this AD or 
within 12 months after the effective date of this AD, whichever 
occurs first, unless required before further flight by paragraph 
(g)(1) of this AD, do the actions in either paragraph (h)(1) or (2) 
of this AD in accordance with the Accomplishment Instructions in 
Honeywell International Inc. Service Bulletin TPE331-72-2190, dated 
December 21, 2011, except you are not required to report information 
to the manufacturer.
    (1) Replace the PPC assembly with the applicable new design PPC 
assembly.
    (2) Inspect the splined end of the shouldered shaft for the 
presence and condition of a threaded hole and, before further 
flight, repair or replace the cam assembly or rework the PPC 
assembly, as necessary, and re-identify the shouldered shaft.

[[Page 6561]]

(i) Secondary Retention Feature (Safety Wire)

    Before further flight after completing the actions required by 
paragraph (h) of this AD, install the secondary retention feature 
(safety wire) on the airplane PPC lever and the PPC assembly.

    Note 1 to paragraph (i): Paragraph j. of M7 Aerospace SA26 
Series Maintenance Manual Temporary Revision 4-02, dated July 22, 
2020, contains information related to installation of the secondary 
retention feature (safety wire).

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Section, Small Airplane 
Standards 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 (k)(1) of this AD.
    (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.

(k) Related Information

    For more information about this AD, contact Jonas Perez, 
Aerospace Engineer, Fort Worth ACO Branch, FAA, 10101 Hillwood 
Parkway, Fort Worth, Texas 76177-1524; phone: 817-222-5145; fax: 
817-222-5960; email: [email protected].

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference 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.
    (3) The following service information was approved for IBR on 
May 5, 2017 (82 FR 15982, March 31, 2017).
    (i) Honeywell International Inc. Service Bulletin TPE331-72-
2190, dated December 21, 2011.
    (ii) [Reserved]
    (4) For Honeywell service information identified in this AD, 
contact Honeywell International Inc., 111 S 34th Street, Phoenix, 
Arizona 85034-2802; phone: 855-808-6500; email: 
[email protected]; internet: https://aerospace.honeywell.com/en/services/maintenance-and-monitoring.
    (5) You may view this service information at FAA, FAA, 
Airworthiness Products Section, Operational Safety Branch, 901 
Locust, Kansas City, Missouri 64106. For information on the 
availability of this material at the FAA, call 816-329-4148.
    (6) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on December 28, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-01332 Filed 1-21-21; 8:45 am]
BILLING CODE 4910-13-P

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