Airworthiness Directives; Piper Aircraft, Inc. Airplanes, 74598-74601 [2020-25690]
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Federal Register / Vol. 85, No. 226 / Monday, November 23, 2020 / Rules and Regulations
and to ensure the Tamarack Active Camber
Surface (TACS) remains in a faired position
in the case of inadvertent power loss to the
ATLAS, which could lead to loss of control
of the airplane.
(f) Compliance
Unless already done, do the following
actions in paragraphs (g) and (h) of this AD.
(g) Modifications
Before further flight after the effective date
of this AD, do the following corrective
actions:
(1) Determine whether the serial number of
the TACS control unit (TCU) assembly is
listed in table 7.8. of Cranfield Aerospace
Solutions Limited (Cranfield) Service
Bulletin CAS/SB1480, Issue A, dated July
2019 (Cranfield CAS/SB1480, Issue A). If the
serial number of the TCU assembly is not
listed in table 7.8., replace the TCU assembly
with a TCU assembly that has a part number
listed in section 5 and a serial number listed
in table 7.8 of Cranfield CAS/SB1480, Issue
A.
(2) Determine whether centering strips
have been installed on the trailing edge of the
TACS by following step 7.4. of Cranfield
CAS/SB1480, Issue A. If the trailing edge of
the TCAS does not have centering strips,
install Cranfield modification CAeM/Cessna/
1475.
(h) Revision to the Maintenance Manual
Supplement
(1) Before further flight after the effective
date of this AD, revise the Airworthiness
Limitations section (ALS) and Instructions
for Continued Airworthiness for your
airplane by adding the updates in Tamarack
Aerospace Group Cessna 525, 525A & 525B
ATLAS Winglet Maintenance Manual
Supplement, Report Number: TAG–1100–
0101, Issue G, dated September 3, 2019.
(2) Thereafter, except as provided in
paragraph (i) of this AD, no alternative
inspection intervals may be approved for the
centering strips. Inserting a later issue of the
ALS with language identical to that
contained in Issue G for the centering strips
is acceptable for compliance with the
requirements of this paragraph.
(3) The airplane flight manual revision and
placard required by AD 2019–08–13, if
installed, may be removed after completing
the modifications required by paragraph (g)
of this AD.
(i) Alternative Methods of Compliance
(AMOCs)
The Manager, New York ACO Branch,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Program Manager, Continued
Operational Safety FAA, New York ACO
Branch, 1600 Stewart Avenue, Suite 410,
Westbury, New York 11590; telephone: (516)
287–7321; fax: (516) 794–5531; email: 9-avsnyaco-cos@faa.gov. Before using any
approved AMOC on any airplane to which
the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking
a PI, your local FSDO.
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(j) Related Information
Refer to European Union Aviation Safety
Agency (EASA) AD No. 2019–0086R1, dated
August 9, 2019, for related information. You
may examine the MCAI on the internet at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2020–0493.
(k) 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.
(i) Cranfield Aerospace Solutions Limited
Service Bulletin CAS/SB1480, Issue A, dated
July 2019.
(ii) Tamarack Aerospace Group Cessna 525,
525A, & 525B ATLAS Winglet Maintenance
Manual Supplement, Report Number: TAG–
1100–0101, Issue G, dated September 3,
2019.
(3) For Cranfield Aerospace Solutions
Limited and Tamarack Aerospace Group
service information identified in this AD,
contact Tamarack Aerospace Group, Inc.
2021 Industrial Drive, Sandpoint, Idaho
83864; telephone: (208) 255–4400; email:
support@tamarackaero.com; internet: https://
tamarackaero.com.
(4) 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.
(5) 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: fedreg.legal@nara.gov, or go to:
https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
Issued on November 13, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–25689 Filed 11–20–20; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–1059; Project
Identifier 2017–CE–035–AD; Amendment
39–21335; AD 2020–24–05]
RIN 2120–AA64
Airworthiness Directives; Piper
Aircraft, Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
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The FAA is adopting a new
airworthiness directive (AD) for certain
Piper Aircraft, Inc. (Piper) Models PA–
28–140, PA–28–150, PA–28–160, PA–
28–180, PA–28–235, PA–32–260, and
PA–32–300 airplanes. This AD was
prompted by reports of corrosion found
in an area of the main wing spar not
easily accessible for inspection. This AD
requires inspecting the left and right
main wing spars for corrosion, and, if
corrosion is found, taking all necessary
corrective actions. The FAA is issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective December
28, 2020.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 28, 2020.
ADDRESSES: For service information
identified in this final rule, contact
Piper Aircraft, Inc., 2926 Piper Drive,
Vero Beach, Florida 32960; telephone:
(772) 567–4361; internet: https://
www.piper.com. 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 on the internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2017–1059.
SUMMARY:
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–2017–
1059; 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: Dan
McCully, Aerospace Engineer, FAA,
Atlanta ACO Branch, 1701 Columbia
Avenue, College Park, Georgia 30337;
telephone: (404) 474–5548; fax: (404)
474–5606; email: william.mccully@
faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a supplemental
notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 by adding an
AD that would apply to certain serial-
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Federal Register / Vol. 85, No. 226 / Monday, November 23, 2020 / Rules and Regulations
numbered Piper Models PA–28–140,
PA–28–150, PA–28–160, PA–28–180,
PA–28–235, PA–32–260, and PA–32–
300 airplanes. The SNPRM published in
the Federal Register on August 4, 2020
(85 FR 47118). The FAA preceded the
SNPRM with a notice of proposed
rulemaking (NPRM) that published in
the Federal Register on November 7,
2017 (82 FR 51583).
The NPRM proposed to require
installing inspection access panels in
the lower wing skin near the left and the
right main wing spars (if not already
there), inspecting for corrosion, and
taking all necessary corrective actions if
corrosion is found. The NPRM was
prompted by reports of significant
corrosion found in an area of the main
wing spar not easily accessible for
inspection.
After the NPRM was issued, Piper
revised its service information to add a
minimum thickness dimension for the
top inboard wing skin and to include
procedures for reapplying corrosion
preventive compound if removed during
the inspection. Also, at the request of
some commenters, the FAA replaced the
proposal in the NPRM to install access
panels for the visual inspection with
optional access methods: The use of
existing access panels, installation of
access panels, accessing the area during
a concurrent inspection, or using a
borescope through existing holes or
openings. In the SNPRM, the FAA
proposed to inspect the left and right
main wing spar for corrosion, and, if
corrosion is found, take all necessary
corrective actions.
Corrosion of the main wing spar, if
not detected and corrected, could cause
the main wing spar to fail with
consequent loss of control of the
airplane. The FAA is issuing this AD to
address the unsafe condition on these
products.
Comments
The FAA received a comment from an
individual commenter. The commenter
supported the SNPRM without change.
Changes to the SNPRM
The FAA has removed the proposed
requirement in paragraph (g) of the
SNPRM to clean the inspection area in
accordance with the instructions in the
service information. Operators who
access the inspection area by a method
other than the inspection panels may
not have sufficient access to clean the
area as described in the service
information. The FAA has added
language to paragraph (h)(1) of the
SNPRM to clarify that if corrosion
exceeds the minimum allowable limit,
the structure must be repaired using a
method approved by the FAA office
specified in this AD.
Conclusion
The FAA reviewed the relevant data,
considered the comment received, and
determined that air safety requires
adopting the AD as proposed with the
clarification previously described.
Accordingly, the FAA is issuing this AD
to address the unsafe condition on these
products.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Piper Service
Bulletin No. 1304A, dated August 14,
2018 (Piper SB 1304A). The service
bulletin contains procedures for
installing an inspection access panel in
74599
the lower wing skin near the left and the
right main wing spars, if not already
there, inspecting for corrosion, and, if
corrosion is found, taking all necessary
corrective actions. The service bulletin
also contains procedures for applying
corrosion prevention and for verifying
that the top inboard wing skin thickness
meets or exceeds the minimum
thickness after corrosion is removed.
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.
Differences Between This AD and the
Service Information
Piper SB No. 1304A provides the
manufacturer’s procedures for installing
access panels on the lower skin of the
left wing and the right wing for easier
access to the left and right main wing
spar. This AD does not require installing
the access panels, but instead allows the
installation as an option to access the
inspection area.
In addition, Piper SB 1304A contains
actions labeled ‘‘Required for
Compliance’’ (RC), and the language in
the service bulletin and in paragraph
(j)(3) of this AD indicates that operators
must comply with all actions labeled RC
for compliance with this AD. However,
this AD does not require all of the steps
labeled as RC. Operators only need to
comply with the RC steps called out in
paragraphs (g) and (h) of this AD.
Costs of Compliance
The FAA estimates that this AD
affects 11,476 airplanes of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
ESTIMATED COSTS
Action
Main wing spar inspection.
Labor cost
Parts cost
Cost per product
2 work-hours × $85 per hour = $170
to inspect both wings.
Not Applicable ...............
$170 per inspection
cycle.
Cost on U.S. operators
$1,950,920 per inspection cycle.
OPTIONAL COSTS
Optional action
Labor cost
Parts cost
Install inspection access panel in the lower
wing skin near the left and the right main
wing spars.
6 work-hours × $85 per hour = $510 to install the inspection access panel on
both wings.
$220 for the kit that contains provisions
for installing inspections access panels
on both wings.
This AD does not require the
installation of the access panels for the
visual inspection; however, it allows the
installation of the panels, as one of four
options, to access the inspection area.
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On-Condition Costs
The extent of damage found during
the required inspection could vary
significantly from airplane to airplane.
The FAA has no way of determining
how much damage may be found on
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Cost per
product
$730
each airplane, the cost to repair
damaged parts on each airplane, or the
number of airplanes that may require
repair.
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Federal Register / Vol. 85, No. 226 / Monday, November 23, 2020 / Rules and Regulations
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.
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 to the extent that it justifies
making a regulatory distinction, 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.
Regulatory Findings
The Amendment
This AD will not have federalism
implications under Executive Order
Accordingly, under the authority
delegated to me by the Administrator,
(d) Subject
(f) Compliance
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 5711, Wing Spar.
Comply with this AD within the
compliance times specified, unless already
done.
(e) Unsafe Condition
(g) Inspect the Left and Right Main Wing
Spars for Corrosion
This AD was prompted by reports of
corrosion found in an area of the main wing
spar not easily accessible for inspection. The
FAA is issuing this AD to detect and correct
corrosion in the wing root area of the left and
the right main wing spars. Corrosion of the
main wing spar, if not detected and
corrected, could cause the main wing spar to
fail with consequent loss of control of the
airplane.
VerDate Sep<11>2014
17:19 Nov 20, 2020
Jkt 253001
Within the next 100 hours time-in-service
(TIS) after the effective date of this AD or
within the next 12 months after the effective
date of this AD, whichever occurs first, and
thereafter at intervals not to exceed 7 years,
inspect the forward and aft surfaces of the
left and right main wing spars between wing
station (WS) 24.24 and WS 49.25 for
corrosion as follows.
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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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
2020–24–05 Piper Aircraft, Inc.:
Amendment 39–21335; Docket No.
FAA–2017–1059; Project Identifier
2017–CE–035–AD.
(a) Effective Date
This airworthiness directive (AD) is
effective December 28, 2020.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the following Piper
Aircraft, Inc. model airplanes that are
certificated in any category:
(1) Gain visual access to the inspection
area by complying with either paragraph
(g)(1)(i), (ii), (iii), or (iv) of this AD.
Note 1 to paragraph (g)(1) of this AD: Step
1 and figure 1 in Part I Wing Spar Inspection
of Piper Aircraft, Inc. Service Bulletin No.
1304A, August 14, 2018 (Piper SB No.
1304A), contain instructions you may use for
identifying the inspection area and
determining if wing access panels have been
installed.
(i) Remove existing wing inspection access
panels and fairings.
(ii) Install Inspection Access Hole Kit part
number 765–106V, and then remove the wing
inspection access panels and fairings.
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Federal Register / Vol. 85, No. 226 / Monday, November 23, 2020 / Rules and Regulations
(iii) Access the inspection area during
concurrent maintenance such as a wing tank
removal, wing removal, or wing skin repair.
(iv) Use a lighted borescope capable of 10X
or higher power magnification display
through existing access points (e.g., wing root
fairing, landing gear panels, internal
lightening holes, or other access points
depending on model).
(2) Identify the wing spar configuration for
your airplane in accordance with table 1 and
figure 2 (sheets 1 and 2) in Part I Wing Spar
Inspection of Piper SB No. 1304A. Visually
inspect each spar component for evidence of
corrosion, including irregularities such as
blisters, flakes, chips, lumps, bulging skin,
and missing rivets.
Note 2 to paragraph (g)(2) of this AD: Paint
coatings may mask the initial stages of
corrosion, and faying surfaces, such as
riveted lap joints, may hide corrosion.
(h) Corrective Actions
(1) If any evidence of corrosion is found
during any inspection required by paragraph
(g) of this AD, before further flight, remove
the corrosion and determine whether the
thickness of the component meets or exceeds
the minimum thickness at all locations in
accordance with table 2 and step 5 in Part I
Wing Spar Inspection of Piper SB No. 1304A.
If the thickness of the component at any
location is less than the minimum thickness
specified in table 2 of Part I Wing Spar
Inspection of Piper SB No. 1304A, before
further flight, repair the structure in
accordance with a method approved by the
Manager, Atlanta ACO Branch, FAA. For a
repair method to be approved by the
Manager, Atlanta ACO Branch, as required by
this paragraph, the Manager’s approval letter
must specifically refer to this AD.
(2) If corrosion preventative compound
was removed as part of any inspection
required by paragraph (g) of this AD, before
further flight, apply corrosion preventative
compound by following step 1 in Part III
Return to Service of Piper SB No. 1304A.
(i) Credit for Actions Done Following
Previous Service Information
This paragraph provides credit for the
initial inspection and application of
corrosion preventative compound required
by paragraphs (g) and (h)(2) of this AD if you
performed the inspection before the effective
date of this AD using Piper Aircraft, Inc.
Service Bulletin No. 1304, dated August 23,
2017, and no evidence of corrosion was
found.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Atlanta ACO 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) of this
AD.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
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17:19 Nov 20, 2020
Jkt 253001
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) For service information that contains
steps that are labeled as required for
Compliance (RC), the following provisions
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. An AMOC is required
for any deviations to RC steps, including
substeps and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(k) Related Information
For more information about this AD,
contact Dan McCully, Aerospace Engineer,
FAA, Atlanta ACO Branch, 1701 Columbia
Avenue, College Park, Georgia 30337;
telephone: (404) 474–5548; fax: (404) 474–
5606; email: william.mccully@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.
(i) Piper Aircraft, Inc. Service Bulletin No.
1304A, August 14, 2018.
(ii) [Reserved]
(3) For Piper Aircraft, Inc. service
information identified in this AD, contact
Piper Aircraft, Inc., 2926 Piper Drive, Vero
Beach, Florida 32960; telephone: (772) 567–
4361; internet: https://www.piper.com.
(4) You may view this service information
at 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.
(5) 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: fedreg.legal@nara.gov, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on November 13, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–25690 Filed 11–20–20; 8:45 am]
BILLING CODE 4910–13–P
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74601
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0753; Project
Identifier 2019–CE–033–AD; Amendment
39–21331; AD 2020–24–01]
RIN 2120–AA64
Airworthiness Directives; Pilatus
Aircraft Ltd. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Pilatus Aircraft Ltd. Model PC–24
airplanes. This AD results from
mandatory continuing airworthiness
information (MCAI) originated by an
aviation authority of another country to
identify and correct an unsafe condition
on an aviation product. The MCAI
identifies the unsafe condition as
overheating of the electrical wiring
splices close to the right-hand pitotstatic connector on frame 10. The FAA
is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective December
28, 2020.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 28, 2020.
ADDRESSES: For service information
identified in this final rule, contact
Pilatus Aircraft Ltd., Customer
Technical Support (MCC), P.O. Box 992,
CH–6371 Stans, Switzerland; telephone:
+41 (0)41 619 67 74; fax: +41 (0)41 619
67 73; email: Techsupport@pilatusaircraft.com; internet: https://
www.pilatus-aircraft.com/en. 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–
0753.
SUMMARY:
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2020–0753; 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
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]]>Agencies
[Federal Register Volume 85, Number 226 (Monday, November 23, 2020)]
[Rules and Regulations]
[Pages 74598-74601]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-25690]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-1059; Project Identifier 2017-CE-035-AD; Amendment
39-21335; AD 2020-24-05]
RIN 2120-AA64
Airworthiness Directives; Piper Aircraft, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Piper Aircraft, Inc. (Piper) Models PA-28-140, PA-28-150, PA-
28-160, PA-28-180, PA-28-235, PA-32-260, and PA-32-300 airplanes. This
AD was prompted by reports of corrosion found in an area of the main
wing spar not easily accessible for inspection. This AD requires
inspecting the left and right main wing spars for corrosion, and, if
corrosion is found, taking all necessary corrective actions. The FAA is
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective December 28, 2020.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of December 28,
2020.
ADDRESSES: For service information identified in this final rule,
contact Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida
32960; telephone: (772) 567-4361; internet: https://www.piper.com. 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 on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
1059.
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-2017-
1059; 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: Dan McCully, Aerospace Engineer, FAA,
Atlanta ACO Branch, 1701 Columbia Avenue, College Park, Georgia 30337;
telephone: (404) 474-5548; fax: (404) 474-5606; email:
[email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a supplemental notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 by adding an AD that would apply to certain
serial-
[[Page 74599]]
numbered Piper Models PA-28-140, PA-28-150, PA-28-160, PA-28-180, PA-
28-235, PA-32-260, and PA-32-300 airplanes. The SNPRM published in the
Federal Register on August 4, 2020 (85 FR 47118). The FAA preceded the
SNPRM with a notice of proposed rulemaking (NPRM) that published in the
Federal Register on November 7, 2017 (82 FR 51583).
The NPRM proposed to require installing inspection access panels in
the lower wing skin near the left and the right main wing spars (if not
already there), inspecting for corrosion, and taking all necessary
corrective actions if corrosion is found. The NPRM was prompted by
reports of significant corrosion found in an area of the main wing spar
not easily accessible for inspection.
After the NPRM was issued, Piper revised its service information to
add a minimum thickness dimension for the top inboard wing skin and to
include procedures for reapplying corrosion preventive compound if
removed during the inspection. Also, at the request of some commenters,
the FAA replaced the proposal in the NPRM to install access panels for
the visual inspection with optional access methods: The use of existing
access panels, installation of access panels, accessing the area during
a concurrent inspection, or using a borescope through existing holes or
openings. In the SNPRM, the FAA proposed to inspect the left and right
main wing spar for corrosion, and, if corrosion is found, take all
necessary corrective actions.
Corrosion of the main wing spar, if not detected and corrected,
could cause the main wing spar to fail with consequent loss of control
of the airplane. The FAA is issuing this AD to address the unsafe
condition on these products.
Comments
The FAA received a comment from an individual commenter. The
commenter supported the SNPRM without change.
Changes to the SNPRM
The FAA has removed the proposed requirement in paragraph (g) of
the SNPRM to clean the inspection area in accordance with the
instructions in the service information. Operators who access the
inspection area by a method other than the inspection panels may not
have sufficient access to clean the area as described in the service
information. The FAA has added language to paragraph (h)(1) of the
SNPRM to clarify that if corrosion exceeds the minimum allowable limit,
the structure must be repaired using a method approved by the FAA
office specified in this AD.
Conclusion
The FAA reviewed the relevant data, considered the comment
received, and determined that air safety requires adopting the AD as
proposed with the clarification previously described. Accordingly, the
FAA is issuing this AD to address the unsafe condition on these
products.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Piper Service Bulletin No. 1304A, dated August 14,
2018 (Piper SB 1304A). The service bulletin contains procedures for
installing an inspection access panel in the lower wing skin near the
left and the right main wing spars, if not already there, inspecting
for corrosion, and, if corrosion is found, taking all necessary
corrective actions. The service bulletin also contains procedures for
applying corrosion prevention and for verifying that the top inboard
wing skin thickness meets or exceeds the minimum thickness after
corrosion is removed. 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.
Differences Between This AD and the Service Information
Piper SB No. 1304A provides the manufacturer's procedures for
installing access panels on the lower skin of the left wing and the
right wing for easier access to the left and right main wing spar. This
AD does not require installing the access panels, but instead allows
the installation as an option to access the inspection area.
In addition, Piper SB 1304A contains actions labeled ``Required for
Compliance'' (RC), and the language in the service bulletin and in
paragraph (j)(3) of this AD indicates that operators must comply with
all actions labeled RC for compliance with this AD. However, this AD
does not require all of the steps labeled as RC. Operators only need to
comply with the RC steps called out in paragraphs (g) and (h) of this
AD.
Costs of Compliance
The FAA estimates that this AD affects 11,476 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Main wing spar inspection....... 2 work-hours x $85 Not Applicable.... $170 per $1,950,920 per
per hour = $170 inspection cycle. inspection cycle.
to inspect both
wings.
----------------------------------------------------------------------------------------------------------------
Optional Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Optional action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Install inspection access panel in the 6 work-hours x $85 per hour = $220 for the kit that $730
lower wing skin near the left and the $510 to install the contains provisions for
right main wing spars. inspection access panel on installing inspections
both wings. access panels on both wings.
----------------------------------------------------------------------------------------------------------------
This AD does not require the installation of the access panels for
the visual inspection; however, it allows the installation of the
panels, as one of four options, to access the inspection area.
On-Condition Costs
The extent of damage found during the required inspection could
vary significantly from airplane to airplane. The FAA has no way of
determining how much damage may be found on each airplane, the cost to
repair damaged parts on each airplane, or the number of airplanes that
may require repair.
[[Page 74600]]
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 to the extent
that it justifies making a regulatory distinction, 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:
2020-24-05 Piper Aircraft, Inc.: Amendment 39-21335; Docket No. FAA-
2017-1059; Project Identifier 2017-CE-035-AD.
(a) Effective Date
This airworthiness directive (AD) is effective December 28,
2020.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the following Piper Aircraft, Inc. model
airplanes that are certificated in any category:
[GRAPHIC] [TIFF OMITTED] TR23NO20.002
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 5711, Wing Spar.
(e) Unsafe Condition
This AD was prompted by reports of corrosion found in an area of
the main wing spar not easily accessible for inspection. The FAA is
issuing this AD to detect and correct corrosion in the wing root
area of the left and the right main wing spars. Corrosion of the
main wing spar, if not detected and corrected, could cause the main
wing spar to fail with consequent loss of control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspect the Left and Right Main Wing Spars for Corrosion
Within the next 100 hours time-in-service (TIS) after the
effective date of this AD or within the next 12 months after the
effective date of this AD, whichever occurs first, and thereafter at
intervals not to exceed 7 years, inspect the forward and aft
surfaces of the left and right main wing spars between wing station
(WS) 24.24 and WS 49.25 for corrosion as follows.
(1) Gain visual access to the inspection area by complying with
either paragraph (g)(1)(i), (ii), (iii), or (iv) of this AD.
Note 1 to paragraph (g)(1) of this AD: Step 1 and figure 1 in
Part I Wing Spar Inspection of Piper Aircraft, Inc. Service Bulletin
No. 1304A, August 14, 2018 (Piper SB No. 1304A), contain
instructions you may use for identifying the inspection area and
determining if wing access panels have been installed.
(i) Remove existing wing inspection access panels and fairings.
(ii) Install Inspection Access Hole Kit part number 765-106V,
and then remove the wing inspection access panels and fairings.
[[Page 74601]]
(iii) Access the inspection area during concurrent maintenance
such as a wing tank removal, wing removal, or wing skin repair.
(iv) Use a lighted borescope capable of 10X or higher power
magnification display through existing access points (e.g., wing
root fairing, landing gear panels, internal lightening holes, or
other access points depending on model).
(2) Identify the wing spar configuration for your airplane in
accordance with table 1 and figure 2 (sheets 1 and 2) in Part I Wing
Spar Inspection of Piper SB No. 1304A. Visually inspect each spar
component for evidence of corrosion, including irregularities such
as blisters, flakes, chips, lumps, bulging skin, and missing rivets.
Note 2 to paragraph (g)(2) of this AD: Paint coatings may mask
the initial stages of corrosion, and faying surfaces, such as
riveted lap joints, may hide corrosion.
(h) Corrective Actions
(1) If any evidence of corrosion is found during any inspection
required by paragraph (g) of this AD, before further flight, remove
the corrosion and determine whether the thickness of the component
meets or exceeds the minimum thickness at all locations in
accordance with table 2 and step 5 in Part I Wing Spar Inspection of
Piper SB No. 1304A. If the thickness of the component at any
location is less than the minimum thickness specified in table 2 of
Part I Wing Spar Inspection of Piper SB No. 1304A, before further
flight, repair the structure in accordance with a method approved by
the Manager, Atlanta ACO Branch, FAA. For a repair method to be
approved by the Manager, Atlanta ACO Branch, as required by this
paragraph, the Manager's approval letter must specifically refer to
this AD.
(2) If corrosion preventative compound was removed as part of
any inspection required by paragraph (g) of this AD, before further
flight, apply corrosion preventative compound by following step 1 in
Part III Return to Service of Piper SB No. 1304A.
(i) Credit for Actions Done Following Previous Service Information
This paragraph provides credit for the initial inspection and
application of corrosion preventative compound required by
paragraphs (g) and (h)(2) of this AD if you performed the inspection
before the effective date of this AD using Piper Aircraft, Inc.
Service Bulletin No. 1304, dated August 23, 2017, and no evidence of
corrosion was found.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Atlanta ACO 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) 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.
(3) For service information that contains steps that are labeled
as required for Compliance (RC), the following provisions apply.
(i) The steps labeled as RC, including substeps under an RC step
and any figures identified in an RC step, must be done to comply
with the AD. An AMOC is required for any deviations to RC steps,
including substeps and identified figures.
(ii) Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection
program without obtaining approval of an AMOC, provided the RC
steps, including substeps and identified figures, can still be done
as specified, and the airplane can be put back in an airworthy
condition.
(k) Related Information
For more information about this AD, contact Dan McCully,
Aerospace Engineer, FAA, Atlanta ACO Branch, 1701 Columbia Avenue,
College Park, Georgia 30337; telephone: (404) 474-5548; fax: (404)
474-5606; 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.
(i) Piper Aircraft, Inc. Service Bulletin No. 1304A, August 14,
2018.
(ii) [Reserved]
(3) For Piper Aircraft, Inc. service information identified in
this AD, contact Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach,
Florida 32960; telephone: (772) 567-4361; internet: https://www.piper.com.
(4) You may view this service information at 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.
(5) 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 November 13, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2020-25690 Filed 11-20-20; 8:45 am]
BILLING CODE 4910-13-P
