Airworthiness Directives; Piper Aircraft, Inc. Airplanes

Published date21 December 2018
Record Number2018-27577
CourtFederal Aviation Administration
Federal Register, Volume 83 Issue 245 (Friday, December 21, 2018)
[Federal Register Volume 83, Number 245 (Friday, December 21, 2018)]
                [Proposed Rules]
                [Pages 65592-65601]
                From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
                [FR Doc No: 2018-27577]
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                DEPARTMENT OF TRANSPORTATION
                Federal Aviation Administration
                14 CFR Part 39
                [Docket No. FAA-2018-1046; Product Identifier 2018-CE-049-AD]
                RIN 2120-AA64
                Airworthiness Directives; Piper Aircraft, Inc. Airplanes
                AGENCY: Federal Aviation Administration (FAA), DOT.
                ACTION: Notice of proposed rulemaking (NPRM).
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                SUMMARY: We propose to adopt a new airworthiness directive (AD) for
                certain Piper Aircraft, Inc. (Piper) Model PA-28-140, PA-28-150, PA-28-
                151, PA-28-160, PA-28-161, PA-28-180, PA-28-181, PA-28-235, PA-28R-180,
                PA-28R-200, PA-28R-201, PA-28R-201T, PA-28RT-201, PA-28RT-201T, PA-32-
                260, and PA-32-300 airplanes. This proposed AD was prompted by a report
                of a fatigue crack found in a visually inaccessible area of the lower
                main wing spar cap. This proposed AD would require calculating the
                factored service hours for each main wing spar to determine when an
                inspection is required, inspecting the lower main wing spar bolt holes
                for cracks, and replacing any cracked main wing spar. We are proposing
                this AD to address the unsafe condition on these products.
                DATES: We must receive comments on this proposed AD by February 4,
                2019.
                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 http://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.
                Examining the AD Docket
                 You may examine the AD docket on the internet at http://
                [[Page 65593]]
                www.regulations.gov by searching for and locating Docket No. FAA-2018-
                1046; 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, the regulatory evaluation, any comments received, and other
                information. The street address for Docket Operations (phone: 800-647-
                5527) is listed above. Comments will be available in the AD docket
                shortly after receipt.
                FOR FURTHER INFORMATION CONTACT: Dan McCully, Aerospace Engineer,
                Atlanta ACO Branch, FAA, 1701 Columbia Avenue, College Park, Georgia
                30337; phone: (404) 474-5548; fax: (404) 474-5605; email:
                william.mccully@faa.gov.
                SUPPLEMENTARY INFORMATION:
                Comments Invited
                 We invite 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-2018-1046;
                Product Identifier 2018-CE-049-AD'' at the beginning of your comments.
                We specifically invite comments on the overall regulatory, economic,
                environmental, and energy aspects of this NPRM. We will consider all
                comments received by the closing date and may amend this NPRM because
                of those comments.
                 We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
                will also post a report summarizing each substantive verbal contact we
                receive about this NPRM.
                Discussion
                 We received a report of a fatigue crack found in the lower main
                wing spar cap on a Piper Model PA-28R-201 airplane. An investigation
                revealed that repeated high-load operating conditions accelerated the
                fatigue crack growth in the lower main wing spar cap. In addition,
                because of the structural configuration of the wing assembly, the
                cracked area was inaccessible for a visual inspection. Model PA-28-140,
                PA-28-150, PA-28-151, PA-28-160, PA-28-161, PA-28-180, PA-28-181, PA-
                28-235, PA-28R-180, PA-28R-200, PA-28R-201T, PA-28RT-201, PA-28RT-201T,
                PA-32-260, and PA-32-300 airplanes have similar wing spar structures as
                the Model PA-28R-201.
                 Airplanes used in training and other high-load environments are
                typically operated for hire and have inspection programs that require
                100-hour inspections. We determined the number of 100-hour inspections
                an airplane has undergone is the best indicator of the airplane's usage
                history. Using the criteria in FAA Advisory Circular AC 23-13A,
                ``Fatigue, Fail-Safe, and Damage Tolerance Evaluation of Metallic
                Structure for Normal, Utility, Acrobatic, and Commuter Category
                Airplanes,'' which you can find at http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgAdvisoryCircular.nsf/MainFrame?OpenFrameset, we developed a factored service hours formula
                based on the number of 100-hour inspections completed on the airplane.
                A review of the airplane maintenance records to determine the
                airplane's usage and the application of the factored service hours
                formula will identify when an airplane meets the criteria for the
                proposed eddy current inspection of the lower main wing spar bolt
                holes.
                 Only an airplane with a main wing spar that has a factored service
                life of 5,000 hours, has had either main wing spar replaced with a
                serviceable main wing spar (more than zero hours TIS), or has airplane
                maintenance records that are missing or incomplete, must have the eddy
                current inspection.
                 This condition, if not addressed, could result in the wing
                separating from the fuselage in flight.
                Related Service Information
                 We reviewed Piper Aircraft Corporation Service Bulletin No. 886,
                dated June 8, 1988, and The New Piper Aircraft, Inc. Service Bulletin
                No. 978A, dated August 6, 1999. These service bulletins contain
                procedures for determining initial and repetitive inspection times
                based on the aircraft's usage and visually inspecting the wing lower
                spar caps and the upper wing skin adjacent to the fuselage and forward
                of each main spar for cracks. We also reviewed Piper Aircraft
                Corporation Service Letter No. 997, dated May 14, 1987. This service
                letter contains procedures for replacing airplane wings.
                FAA's Determination
                 We are proposing this AD because we 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 reviewing the airplane maintenance
                records to determine the number of 100-hour inspections completed on
                each installed main wing spar and using the number of 100-hour
                inspections to calculate the factored service hours for each main wing
                spar. This proposed AD would also require inspecting the lower main
                wing spar bolt holes for cracks once a main wing spar exceeds the
                specified factored service hours and replacing any main wing spar when
                a crack is indicated. This proposed AD would only apply when an
                airplane has either accumulated 5,000 or more hours time-in-service
                (TIS); has had either main wing spar replaced with a serviceable main
                wing spar (more than zero hours TIS); or has missing and/or incomplete
                maintenance records.
                Interim Action
                 We consider this proposed AD interim action. The inspection reports
                will provide us additional data for determining the cause of the
                cracking. After analyzing the data, we may take further rulemaking
                action.
                Costs of Compliance
                 We estimate that this proposed AD affects 19,696 airplanes of U.S.
                registry.
                 We estimate the following costs to comply with this proposed AD:
                 Estimated Costs
                ----------------------------------------------------------------------------------------------------------------
                 Cost per Cost on U.S.
                 Action Labor cost Parts cost product operators
                ----------------------------------------------------------------------------------------------------------------
                Review airplane maintenance 2 work-hours x $85 Not applicable............. $170 $3,348,320
                 records and calculate factored per hour = $170.
                 service hours.
                ----------------------------------------------------------------------------------------------------------------
                 We estimate the following costs to do the eddy current inspection.
                Because some airplanes are only used non-commercially and will not
                accumulate the specified factored service hours in the life of the
                airplane, we have no way of determining the number of airplanes that
                might need this inspection:
                [[Page 65594]]
                 On-Condition Costs
                ----------------------------------------------------------------------------------------------------------------
                 Action Labor cost Parts cost Cost per product
                ----------------------------------------------------------------------------------------------------------------
                Inspect the lower main wing spar 1.5 work-hours x $85 $20 $147.50 per wing spar.
                 and replace the attach nuts and per hour = $127.50
                 bolts. per wing spar.
                Report inspection results to the 1 work-hour x $85 = N/A $85.
                 FAA. $85.
                ----------------------------------------------------------------------------------------------------------------
                 We estimate the following costs to do any necessary replacements
                that would be required based on the results of the proposed inspection.
                We have no way of determining the number of aircraft that might need
                this replacement:
                 On-Condition Replacement Costs
                ----------------------------------------------------------------------------------------------------------------
                 Action Labor cost Parts cost Cost per product
                ----------------------------------------------------------------------------------------------------------------
                Replace main wing spar........... 32 work-hours x $85 per $5,540 $8,260 per wing spar.
                 hour = $2,720 per wing
                 spar.
                ----------------------------------------------------------------------------------------------------------------
                Paperwork Reduction Act
                 A federal agency may not conduct or sponsor, and a person is not
                required to respond to, nor shall a person be subject to a penalty for
                failure to comply with a collection of information subject to the
                requirements of the Paperwork Reduction Act unless that collection of
                information displays a currently valid OMB Control Number. The OMB
                Control Number for this information collection is 2120-0056. Public
                reporting for this collection of information is estimated to be
                approximately 1 hour per response, including the time for reviewing
                instructions, searching existing data sources, gathering and
                maintaining the data needed, completing and reviewing the collection of
                information. All responses to this collection of information are
                mandatory. Send comments regarding this burden estimate or any other
                aspect of this collection of information, including suggestions for
                reducing this burden to: Information Collection Clearance Officer,
                Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX
                76177-1524.
                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.
                 We are 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.
                 This AD is issued in accordance with authority delegated by the
                Executive Director, Aircraft Certification Service, as authorized by
                FAA Order 8000.51C. In accordance with that order, issuance of ADs is
                normally a function of the Compliance and Airworthiness Division, but
                during this transition period, the Executive Director has delegated the
                authority to issue ADs applicable to small airplanes, gliders,
                balloons, airships, domestic business jet transport airplanes, and
                associated appliances to the Director of the Policy and Innovation
                Division.
                Regulatory Findings
                 We 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) Is not a ``significant rule'' under the DOT Regulatory Policies
                and Procedures (44 FR 11034, February 26, 1979),
                 (3) Will not affect intrastate aviation in Alaska, and
                 (4) 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):
                Piper Aircraft, Inc.: Docket No. FAA-2018-1046; Product Identifier
                2018-CE-049-AD.
                (a) Comments Due Date
                 We must receive comments by February 4, 2019.
                (b) Affected ADs
                 None.
                (c) Applicability
                 This AD applies to Piper Aircraft, Inc. airplanes, certificated
                in any category, with a model and serial number shown in Table 1 to
                paragraph (c) of this AD, and that meet at least one of the criteria
                in paragraphs (c)(1), (2), or (3) of this AD.
                 (1) Has accumulated 5,000 or more hours time-in-service (TIS);
                or
                 (2) Has had either main wing spar replaced with a serviceable
                main wing spar (more than zero hours TIS); or
                 (3) Has missing and/or incomplete maintenance records.
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                (d) Subject
                 Joint Aircraft System Component (JASC)/Air Transport Association
                (ATA) of America Code 57, Wings.
                (e) Unsafe Condition
                 This AD was prompted by a report of a fatigue crack found in a
                visually inaccessible area of the lower main wing spar cap. We are
                issuing this AD to detect and correct fatigue cracks in the lower
                main wing spar cap bolt holes. The unsafe condition, if not
                addressed, could result in the wing separating from the fuselage in
                flight.
                (f) Compliance
                 Comply with this AD within the compliance times specified,
                unless already done.
                (g) Review Airplane Maintenance Records and Calculate Factored Service
                Hours for Each Main Wing Spar
                 (1) Within 30 days after the effective date of this AD, review
                the airplane maintenance records and determine the number of 100-
                hour inspections completed on the airplane since new and any record
                of wing spar replacement(s).
                 (i) If a main wing spar has been replaced with a new (zero hour
                TIS) main wing spar, count the number of 100-hour inspections from
                the time of installation of the new main wing spar.
                 (ii) If either main wing spar has been replaced with a
                serviceable main wing spar (more than zero hours TIS) or the
                airplane maintenance records are missing or incomplete, the factored
                service hours cannot be determined. Perform the eddy current
                inspection as specified in paragraph (h) of this AD.
                 (2) Before further flight after completing the action in
                paragraph (g)(1) of this AD, calculate the factored service hours
                for each main wing spar using the following formula: (N x 100) + [T-
                (N x 100)]/17 = Factored Service Hours, where N is the number of
                100-hour inspections and T is the total hours TIS of the airplane.
                Thereafter, after each annual inspection and 100-hour TIS
                inspection, recalculate the factored service hours for each main
                wing spar until the main wing spar has accumulated 5,000 or more
                factored service hours.
                 (3) An example of determining factored service hours for an
                airplane with no 100-hour inspections is as follows: The airplane
                maintenance records show that the airplane has a total of 12,100
                hours TIS, and only annual inspections have been done. Both main
                wing spars are original factory installed. In this case, N = 0 and T
                = 12,100. Use those values in the formula as follows:
                [[Page 65596]]
                (0 x 100) + [12,100-(0 x 100)]/17 = 711 factored service hours on
                each main wing spar.
                 (4) An example of determining factored service hours for an
                airplane with both 100-hour and annual inspections is as follows:
                The airplane was originally flown for personal use, then for
                training for a period of time, then returned to personal use. The
                airplane maintenance records show that the airplane has a total of
                5,600 hours TIS, and nineteen 100-hour inspections have been done.
                Both main wing spars are original factory installed. In this case, N
                = 19 and T = 5,600. Use those values in the formula as follows: (19
                x 100) + [5,600-(19 x 100)]/17 = (1,900 + 218) = 2,118 factored
                service hours on each main wing spar.
                (h) Eddy Current Inspect
                 Within the compliance time specified in paragraph (h)(1) or (2)
                of this AD, eddy current inspect the inner surface of each bolt hole
                on the lower main wing spar cap for cracks by using the procedure in
                appendix 1 of this AD.
                 (1) Within 100 hours TIS after complying with paragraph (g) of
                this AD or within 100 hours TIS after a main wing spar accumulates
                5,000 factored service hours, whichever occurs later; or
                 (2) For airplanes with an unknown number of factored service
                hours on a main wing spar, within the next 100 hours TIS after the
                effective date of this AD or within 60 days after the effective date
                of this AD, whichever occurs later.
                (i) Replace the Main Wing Spar
                 If a crack is found during an inspection required in paragraph
                (h) of this AD, before further flight, replace the main wing spar
                with a new (zero hours TIS) main wing spar or with a main wing spar
                that has been inspected as specified in appendix 1 of this AD and no
                cracks were found.
                (j) Report Inspection Results
                 Within 30 days after completing an inspection required in
                paragraph (h) of this AD, using Appendix 2, ``Inspection Results
                Form,'' of this AD, report the inspection results to the FAA at the
                Atlanta ACO Branch. Submit the report to the FAA using the contact
                information found in appendix 2 of this AD.
                (k) Special Flight Permit
                 A special flight permit may only be issued to operate the
                airplane to a location where the inspection requirement of paragraph
                (h) of this AD can be performed. This AD prohibits a special flight
                permit if the inspection reveals a crack in a main wing spar.
                (l) Paperwork Reduction Act Burden Statement
                 A federal agency may not conduct or sponsor, and a person is not
                required to respond to, nor shall a person be subject to a penalty
                for failure to comply with a collection of information subject to
                the requirements of the Paperwork Reduction Act unless that
                collection of information displays a currently valid OMB Control
                Number. The OMB Control Number for this information collection is
                2120-0056. Public reporting for this collection of information is
                estimated to be approximately 1 hour per response, including the
                time for reviewing instructions, searching existing data sources,
                gathering and maintaining the data needed, completing and reviewing
                the collection of information. All responses to this collection of
                information are mandatory. Send comments regarding this burden
                estimate or any other aspect of this collection of information,
                including suggestions for reducing this burden to: Information
                Collection Clearance Officer, Federal Aviation Administration, 10101
                Hillwood Parkway, Fort Worth, TX 76177-1524.
                (m) 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 (n) 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.
                (n) Related Information
                 For more information about this AD, contact Dan McCully,
                Aerospace Engineer, Atlanta ACO Branch, FAA, 1701 Columbia Avenue,
                College Park, Georgia 30337; phone: (404) 474-5548; fax: (404) 474-
                5605; email: william.mccully@faa.gov.
                BILLING CODE 4910-13-C
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                BILLING CODE 4910-13-P
                 Issued in Kansas City, Missouri, on December 7, 2018.
                Melvin J. Johnson,
                Aircraft Certification Service, Deputy Director, Policy and Innovation
                Division, AIR-601.
                [FR Doc. 2018-27577 Filed 12-20-18; 8:45 am]
                 BILLING CODE 4910-13-P
                

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