Airworthiness Directives; Piper Aircraft, Inc. Airplanes, 74598-74601 [2020-25690]

Download as PDF 74598 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. VerDate Sep<11>2014 17:19 Nov 20, 2020 Jkt 253001 (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: PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 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- E:\FR\FM\23NOR1.SGM 23NOR1 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. VerDate Sep<11>2014 17:19 Nov 20, 2020 Jkt 253001 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 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 Cost per product $730 each airplane, the cost to repair damaged parts on each airplane, or the number of airplanes that may require repair. E:\FR\FM\23NOR1.SGM 23NOR1 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. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 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. E:\FR\FM\23NOR1.SGM 23NOR1 ER23NO20.002</GPH> 74600 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, VerDate Sep<11>2014 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: http:// 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 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 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 E:\FR\FM\23NOR1.SGM 23NOR1

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]


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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: http://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