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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 air-
    planes, all serial numbers, certificated in any category.

(d) SUBJECT

    Air Transport Association (ATA) of America Code 61, Propellers/propul-
    sors.

(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 al-
    ready 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, in-
    spect 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 inspec-
    tions 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 accord-
    ance  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.

(i) SECONDARY RETENTION FEATURE (SAFETY WIRE)

    Before further flight  after completing the actions required  by para-
    graph (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 Mainte-
nance Manual Temporary Revision 4-02, dated July 22, 2020, contains infor-
mation 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 in-
    spector, 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: jonas.perez@faa.gov.

(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 Honey-
    well International Inc.,  111 S 34th Street,  Phoenix, Arizona  85034-
    2802;   phone:  855-808-6500;   email:  AeroTechSupport@honeywell.com;
    internet: https://aerospace.honeywell.com/en/services/maintenance-and-
    monitoring.

(5) You may view this service information at FAA, FAA, Airworthiness Prod-
    ucts 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 refer-
    ence at the National Archives and Records Administration  (NARA).  For
    information on the availability  of  this  material  at  NARA,  email:
    fedreg.legal@nara.gov,  or  go  to:  https://www.archives.gov/federal-
    register/cfr/ibr-locations.html.

Issued on December 28, 2020.  Lance T. Gant,  Director,  Compliance & Air-
worthiness Division, Aircraft Certification Service.

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: jonas.perez@faa.gov.
PREAMBLE 

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:
AeroTechSupport@honeywell.com; 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:
jonas.perez@faa.gov.

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:

Estimated Costs

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

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

Action
Labor cost
Parts cost
Cost per 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

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]

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