Airworthiness Directives; M7 Aerospace LLC Airplanes, 64993-64995 [2020-22225]

Download as PDF Federal Register / Vol. 85, No. 199 / Wednesday, October 14, 2020 / Proposed Rules Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. Issued on October 7, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–22665 Filed 10–13–20; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Examining the AD Docket Federal Aviation Administration You may examine the AD docket on the internet 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 NPRM, any comments received, and other information. The street address for Docket Operations is listed above. Comments will be available in the AD docket shortly after receipt. 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. 14 CFR Part 39 [Docket No. FAA–2020–0910; Project Identifier 2018–CE–044–AD] RIN 2120–AA64 Airworthiness Directives; M7 Aerospace LLC Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for M7 Aerospace LLC Model SA26–AT and SA26–T airplanes. This proposed AD was prompted by reports of the airplane power lever linkage detaching from the TPE331 engine propeller pitch control (PPC) shaft. This proposed AD would 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 proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by November 30, 2020. 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 https://www.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. For service information identified in this NPRM, contact Honeywell International Inc., 111 S 34th Street, SUMMARY: jbell on DSKJLSW7X2PROD with PRO_RULES 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. VerDate Sep<11>2014 17:18 Oct 13, 2020 Jkt 253001 SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2020–0910; Project Identifier 2018–CE–044–AD’’ at the beginning of your comments. The most helpful comments reference a specific portion of the proposal, 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 proposal 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 https:// www.regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this proposal. Confidential Business Information CBI is commercial or financial information that is both customarily and actually treated as private by its owner. PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 64993 Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this NPRM 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 NPRM, 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 NPRM. Submissions containing CBI should be sent to 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. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking. Discussion The FAA has received reports of the airplane power lever linkage detaching from the TPE331 engine PPC shaft. In flight operations, detachment may result in fuel flow to the engine remaining constant regardless of the power lever movement by the pilot. The orientation of the engine on certain M7 Aerospace LLC airplanes increases the vulnerability of detachment. The PPC lever is an airplane part and its detachment from the TPE331 has been the subject of previous ADs on other airplane type designs. This condition, if not addressed, could result in uncommanded change to the engine power settings with consequent loss of control. 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. 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 the ADDRESSES section. Other Related Service Information The FAA also reviewed paragraph j. of M7 Aerospace SA26 Series Maintenance Manual Temporary E:\FR\FM\14OCP1.SGM 14OCP1 64994 Federal Register / Vol. 85, No. 199 / Wednesday, October 14, 2020 / Proposed Rules 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. relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. FAA’s Determination The FAA is proposing this AD because the agency evaluated all the This proposed AD would require accomplishing the actions specified in the service information described previously. Costs of Compliance The FAA estimates that this proposed AD would affect 55 airplanes of U.S. registry. The FAA estimates the following costs to comply with this proposed AD: Proposed AD Requirements ESTIMATED COSTS Cost per product Labor cost Install secondary retention feature (safety wire). Inspect PPC lever ............................... 1 work-hour × $85 per hour = $85 .... $10 $95 1 work-hour × $85 per hour = $85 per inspection cycle. 19 work-hours × $85 per hour = $1,615. 0 85 1,000 2,615 Repair, replace, and/or rework PPC lever input shaft. The FAA estimates the following costs to do any adjustment that would Parts cost Cost on U.S. operators Action be required based on the results of the proposed inspection. The FAA has no $5,225. $4,675 per inspection cycle. $143,825. 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 × $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. jbell on DSKJLSW7X2PROD with PRO_RULES Regulatory Findings The FAA determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 VerDate Sep<11>2014 17:18 Oct 13, 2020 Jkt 253001 responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (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. M7 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (d) Subject Air Transport Association (ATA) of America Code 61, Propellers/propulsors. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 Aerospace LLC: Docket No. FAA–2020– 0910; Project Identifier 2018–CE–044– AD. (a) Comments Due Date The FAA must receive comments by November 30, 2020. (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. (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 E:\FR\FM\14OCP1.SGM 14OCP1 Federal Register / Vol. 85, No. 199 / Wednesday, October 14, 2020 / Proposed Rules 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. jbell on DSKJLSW7X2PROD with PRO_RULES (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 (1) For more information about this AD, contact Jonas Perez, Aerospace Engineer, Fort Worth ACO Branch, FAA, 10101 Hillwood Parkway, Fort Worth, Texas 76177–1524; VerDate Sep<11>2014 17:18 Oct 13, 2020 Jkt 253001 phone: 817–222–5145; fax: 817–222–5960; email: jonas.perez@faa.gov. (2) For Honeywell International Inc., service information identified in this AD, 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. (3) You may view this referenced 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. Issued on October 2, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–22225 Filed 10–13–20; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–0912; Product Identifier 2015–SW–071–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to supersede airworthiness directive (AD) 82–20–05 for Societe Nationale Industrielle Aerospatiale (now Airbus Helicopters) Model AS–350 and AS–355 series helicopters. AD 82–20–05 requires inspecting and establishing a life limit for the tail rotor (TR) drive shaft bearing (bearing). Since the FAA issued AD 82–20–05, inconsistencies have been identified between inspections and maintenance actions required by ADs and inspections and maintenance actions specified in the applicable maintenance manual. This proposed AD would require replacing certain part-numbered TR bearings with one part-numbered bearing and repetitively inspecting one partnumbered bearing. The actions of this proposed AD are intended to address an unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by November 30, 2020. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the SUMMARY: PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 64995 online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0912; 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 proposed AD, the European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD, any comments received, and other information. The street address for Docket Operations is listed above. Comments will be available in the AD docket shortly after receipt. For service information identified in this proposed rule, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone 972–641–0000 or 800–232–0323; fax 972–641–3775; or at https:// www.airbus.com/helicopters/services/ technical-support.html. You may view the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. FOR FURTHER INFORMATION CONTACT: David Hatfield, Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5116; email david.hatfield@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to participate in this rulemaking by submitting written comments, data, or views. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit only one time. Except for Confidential Business Information as described in the E:\FR\FM\14OCP1.SGM 14OCP1

Agencies

[Federal Register Volume 85, Number 199 (Wednesday, October 14, 2020)]
[Proposed Rules]
[Pages 64993-64995]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-22225]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0910; Project Identifier 2018-CE-044-AD]
RIN 2120-AA64


Airworthiness Directives; M7 Aerospace LLC Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for M7 Aerospace LLC Model SA26-AT and SA26-T airplanes. This proposed 
AD was prompted by reports of the airplane power lever linkage 
detaching from the TPE331 engine propeller pitch control (PPC) shaft. 
This proposed AD would 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 proposing this AD 
to address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by November 
30, 2020.

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 https://www.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.
    For service information identified in this NPRM, 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.

Examining the AD Docket

    You may examine the AD docket on the internet 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 NPRM, any comments received, and other information. The street 
address for Docket Operations is listed above. Comments will be 
available in the AD docket shortly after receipt.

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:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2020-0910; 
Project Identifier 2018-CE-044-AD'' at the beginning of your comments. 
The most helpful comments reference a specific portion of the proposal, 
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 proposal 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 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this proposal.

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 NPRM 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 NPRM, 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 NPRM. Submissions containing CBI should be sent to 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]. Any commentary that the FAA 
receives which is not specifically designated as CBI will be placed in 
the public docket for this rulemaking.

Discussion

    The FAA has received reports of the airplane power lever linkage 
detaching from the TPE331 engine PPC shaft. In flight operations, 
detachment may result in fuel flow to the engine remaining constant 
regardless of the power lever movement by the pilot. The orientation of 
the engine on certain M7 Aerospace LLC airplanes increases the 
vulnerability of detachment. The PPC lever is an airplane part and its 
detachment from the TPE331 has been the subject of previous ADs on 
other airplane type designs. This condition, if not addressed, could 
result in uncommanded change to the engine power settings with 
consequent loss of control.

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.
    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 the ADDRESSES section.

Other Related Service Information

    The FAA also reviewed paragraph j. of M7 Aerospace SA26 Series 
Maintenance Manual Temporary

[[Page 64994]]

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.

FAA's Determination

    The FAA is proposing this AD because the agency evaluated all the 
relevant information and determined the unsafe condition described 
previously is likely to exist or develop in other products of the same 
type design.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously.

Costs of Compliance

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

                                                 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 proposed 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 =                 $0              $85
                                                $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

    The FAA determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    (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 Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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 (AD):

M7 Aerospace LLC: Docket No. FAA-2020-0910; Project Identifier 2018-
CE-044-AD.

(a) Comments Due Date

    The FAA must receive comments by November 30, 2020.

(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

[[Page 64995]]

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.

(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

    (1) 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].
    (2) For Honeywell International Inc., 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.
    (3) You may view this referenced 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.

    Issued on October 2, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-22225 Filed 10-13-20; 8:45 am]
BILLING CODE 4910-13-P