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