Notification of a Proposal to issue an Airworthiness Directive

for FSH is inappropriate for the affected aeroplanes operated under EU regulations. Based on this determination, EASA has decided not to adopt the FAA AD. For the reasons described above, this AD requires repetitive calculations of AAU and EFSH, as defined in this AD and, depending on the results, an EC inspection of the main wing spar caps for cracks and, depending on findings, replacement of the affected main wing spar. This AD also requires reporting the inspection results to EASA, the FAA and Piper. Appendix 2 of this AD includes a flowchart to assist operators to determine which action is required and when, and also provides some examples of calculation. This AD is considered to be an interim action and further AD action may follow. Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: Review of Maintenance Records and Calculation(s): (1) Within 30 days after the effective date of this AD, and, thereafter, during each 100-hours or annual inspection, as applicable, review the aeroplane maintenance records for completeness and determine whether a wing or wing spar has been replaced with a wing or wing spar that had more than zero hours’ TIS at the time of installation. (2) If, as result of any review as required by paragraph (1) of this AD, it is determined that a wing spar has accumulated or exceeded 5 000 hours’ TIS, within 30 days after the effective date of this AD, or after that review, whichever occurs later, calculate the AAU, as defined in this AD. (3) If the result of the calculation as required by paragraph (2) of this AD is 100 (TIS/year) or more, before next flight, calculate the EFSH by using the formula specified in Figure 1 of this AD. EASA PAD No.: 21-041 TE.CAP.00112-009 © European Union Aviation Safety Agency. All rights reserved. ISO9001 Certified. Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. An agency of the European Union Page 4 of 7 Figure 1 – EFSH Calculation EFSH = (TIS - 100 x Years) + (100 x Years) / 15 Inspection: (4) If, as a result of the calculation as required by paragraph (3) of this AD, the EFSH are determined to be 5 000 or more, within 100 hours after accumulating 5 000 EFSH, or within 100 hours after the effective date of this AD, whichever occurs later, accomplish an EC inspection of the inner surface of the two lower outboard bolt holes on the lower main wing spar cap for cracks. If the wing is installed, use steps 1 to 3 (inclusive) of the instructions of the SB or, if the wing is not installed, use step 3 of the instructions of the SB. (5) If, as result of the first review as required by paragraph (1) of this AD, maintenance records are found to be incomplete (i.e. unknown whether a wing spar has been installed with more than zero hours’ TIS), or spar/aeroplane TIS or FH are unknown, within 100 hours after the effective date of this AD, accomplish an EC inspection of the inner surface of the two lower outboard bolt holes on the lower main wing spar cap for cracks. If the wing is installed, use steps 1 to 3 (inclusive) of the instructions of the SB or, if the wing is not installed, use step 3 of the instructions of the SB. Wing Spar Replacement: (6) If, during the EC inspection as required by paragraph (4) or (5) of this AD, as applicable, any crack is detected that exceeds the acceptance criteria of the SB, before next flight, replace the main wing spar with a new (zero TIS) main wing spar, or with a serviceable (more than zero TIS) main wing spar that, before installation, has passed an EC inspection (no cracks detected) in accordance with steps 1 to 3 (inclusive) of the instructions of the SB. Replacement of a main wing spar can be accomplished in accordance with the instructions of Piper Service Letter (SL) 997. Bolt Replacement: (7) Before next flight after the EC inspection as required by paragraph (4) or (5) of this AD, as applicable, or during the main wing spar replacement as required by paragraph (6) of this AD, as applicable, install new bolts in accordance with step 6 of the instructions of the SB. Reporting: (8) Within 30 days after the EC inspection as required by paragraph (4) or (5) of this AD, as applicable, report the inspection results to EASA, the FAA and to Piper Aircraft. This can be accomplished by using Appendix 1 (Inspection Results Form) of this AD and the contact information found on that Form. Ref. Publications: Piper SB 1345 dated 27 March 2020. Piper SL 997 dated 14 May 1987. EASA PAD No.: 21-041 TE.CAP.00112-009 © European Union Aviation Safety Agency. All rights reserved. ISO9001 Certified. Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. An agency of the European Union Page 5 of 7 Remarks: 1. This Proposed AD will be closed for consultation on 07 April 2021. 2. Enquiries regarding this PAD should be referred to the EASA Safety Information Section, Certification Directorate. E-mail: ADs@easa.europa.eu. 3. Information about any failures, malfunctions, defects or other occurrences, which may be similar to the unsafe condition addressed by this PAD, and which may occur, or have occurred on a product, part or appliance not affected by this PAD, can be reported to the EU aviation safety reporting system. This may include reporting on the same or similar components, other than those covered by the design to which this PAD applies, if the same unsafe condition can exist or may develop on an aircraft with those components installed. Such components may be installed under an FAA Parts Manufacturer Approval (PMA), Supplemental Type Certificate (STC) or other modification. 4. For any question concerning the technical content of the requirements in this PAD, please contact: Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida 32960, United States of America; Telephone: +1 772-299-2141; E-mail: CustomerService@piper.com; Website: https://www.piper.com/contact-us/ or https://www.piper.com/technical-publications. EASA PAD No.: 21-041 TE.CAP.00112-009 © European Union Aviation Safety Agency. All rights reserved. ISO9001 Certified. Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. An agency of the European Union Page 6 of 7 Appendix 1 Inspection Results Form E-mail completed from to: 9-ASO-ATLCOS-Reporting@faa.gov and customer.service@piper.com and ads@easa.auropa.eu SUBJECT LINE: Docket No. FAA-2018-1046 Or mail to: Federal Aviation Administration Atlanta ACO Brach, AIR-7A1 1701 Columbia Avenue College Park, GA 30337 and Piper Certification Office 2926 Piper Drive Vero Beach, FL 32960 Include Photos, if applicable Aircraft Model: PA- Serial Number: Aircraft Total TIS: or FH: Registration: EASA FSH – LH Wing: RH Wing: (if both wings are factory installed original, these numbers should be the same) Inspection Results LH Wings Spar FWD: Accepted ꙱ Rejected ꙱ RH Wings Spar FWD: Accepted ꙱ Rejected ꙱ LH Wing Spar AFT: Accepted ꙱ Rejected ꙱ RH Wing Spar AFT: Accepted ꙱ Rejected ꙱ Inspector Comments (observed damage, condition of hole, etc.) Inspector Information: Name (print): Signature: Certificate No.: Date: EASA PAD No.: 21-041 TE.CAP.00112-009 © European Union Aviation Safety Agency. All rights reserved. ISO9001 Certified. Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. An agency of the European Union Page 7 of 7 Appendix 2 – Flowchart / Examples of Calculation Example 1: For an a/c with 8 years in service and 700 hours TIS (TIS=700), the results would be: 1. Paragraph (2): TIS/years = 700/8 = 87,5 <100 → no action required. Example 2: For an a/c with 8 years in service and 3 000 hours TIS Hours (TIS=3 000), the results would be: 1. Paragraph (2): TIS/years = 3 000/8 = 375 >100 → go to paragraph (3); 2. Paragraph (3): EFSH = (3 000-100x8) + (100x8)/15= 2 253 < 5 000 → no further action Example 3: For an a/c with 8 years in service and 6 000 hours TIS (TIS = 6 000), the results would be: 1. Paragraph (2): TIS/Age = 6 000/8 = 750 >100 → go to paragraph (3); 2. Paragraph (3): EFSH = (6 000-100x8)+(100x8)/15 = 5 253 → go to paragraph (4). Example of calendar years: For an aeroplane that was manufactured in 1989, 1990 is the first calendar year to be counted, and the full year before calculation would be the last, so (at this time, in 2021) the number would be 31. No further action If TIS/years ≥ 100 Calculate EFSH [see Figure 1 of this AD] Calculate AAU: TIS/years. If TIS/years < 100 EC Inspection If EFSH < 5000 If EFSH ≥ 5000 Paragraph (2) Paragraph (3) If TIS unknown TIS ≥ 5000 hrs If TIS < 5000hrs Paragraph (4) or (5)