AD 2015-08-04

Unless already done (compliance with AD 99-01-05 R1 and AD 93-10-06, Amendment 39-8586 (58 FR 29965, May 25, 1993) “AD 93-010-06”), do the following actions within the compliance times specified in paragraphs (g) through (m) of this AD, including all subparagraphs. Properly unsealing and resealing a sealed wing lift strut is still considered a terminating action for the repetitive inspection requirements of this AD as long as all appropriate regulations and issues are considered, such as static strength, fatigue, material effects, immediate and long-term (internal and external) corrosion protection, resealing methods, etc. Current FAA regulations in 14 CFR 43.13(b) specify that maintenance performed will result in the part's condition to be at least equal to its original or properly altered condition. Any maintenance actions that unseal a sealed wing lift strut should be coordinated with the Atlanta Aircraft Certification Office (ACO) through the local airworthiness authority (e.g., Flight Standards District Office). There are provisions in paragraph (n) of this AD for approving such actions as an alternative method of compliance (AMOC).

(1) For all airplanes previously affected by AD 99-01-05 R1: Within 1 calendar month after February 8, 1999 (the effective date retained from AD 99-01-05), or within 24 calendar months after the last inspection done in accordance with AD 93-10-06 (which was superseded by AD 99-01-05), whichever occurs later, remove the wing lift struts following Piper Aircraft Corporation Mandatory Service Bulletin (Piper MSB) No. 528D, dated October 19, 1990, or Piper MSB No. 910A, dated October 10, 1989, as applicable. Before further flight after the removal, do the actions in one of the following paragraphs (h)(1), (h)(2), (i)(1), (i)(2), or (i)(3) of this AD, including all subparagraphs.

(2) For all airplanes new to this AD (not previously affected by AD 99-01-05 R1): Within 1 calendar month after the effective date of this AD or within 24 calendar months after the last inspection done in accordance with AD 93-10-06 (which was superseded by AD 99-01-05), whichever occurs later, remove the wing lift struts following Piper Aircraft Corporation Mandatory Service Bulletin (Piper MSB) No. 528D, dated October 19, 1990, or Piper MSB No. 910A, dated October 10, 1989, as applicable. Before further flight after the removal, do the actions in one of the following paragraphs (h)(1), (h)(2), (i)(1), (i)(2), or (i)(3) of this AD, including all subparagraphs.

For all airplanes listed in this AD: Before further flight after the removal required in paragraph (g) of this AD, inspect each wing lift strut following paragraph (h)(1) or (h)(2) of this AD, including all subparagraphs, or do the wing lift strut replacement following one of the options in paragraph (i)(1), (i)(2), or (i)(3) of this AD.

(1) Inspect each wing lift strut for corrosion and perceptible dents following Piper MSB No. 528D, dated October 19, 1990, or Piper MSB No. 910A, dated October 10, 1989, as applicable.

(i) If no corrosion is visible and no perceptible dents are found on any wing lift strut during the inspection required in paragraph (h)(1) of this AD, before further flight, apply corrosion inhibitor to each wing lift strut following Piper MSB No. 528D, dated October 19, 1990, or Piper MSB No. 910A, dated October 10, 1989, as applicable. Repetitively thereafter inspect each wing lift strut at intervals not to exceed 24 calendar months following the procedures in paragraph (h)(1) or (h)(2) of this AD, including all subparagraphs.

(ii) If corrosion or perceptible dents are found on any wing lift strut during the inspection required in paragraph (h)(1) of this AD or during any repetitive inspection required in paragraph (h)(1)(i) of this AD, before further flight, replace the affected wing lift strut with one of the replacement options specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD. Do the replacement following the procedures specified in those paragraphs, as applicable.

(2) Inspect each wing lift strut for corrosion following the procedures in the Appendix to this AD. This inspection must be done by a Level 2 or Level 3 inspector certified using the guidelines established by the American Society for Non-destructive Testing or the “Military Standard for Nondestructive Testing Personnel Qualification and Certification” (MIL-STD-410E).

(i) If no corrosion is found on any wing lift strut during the inspection required in paragraph (h)(2) of this AD and all requirements in the Appendix to this AD are met, before further flight, apply corrosion inhibitor to each wing lift strut following Piper MSB No. 528D, dated October 19, 1990, or Piper MSB No. 910A, dated October 10, 1989, as applicable. Repetitively thereafter inspect each wing lift strut at intervals not to exceed 24 calendar months following the procedures in paragraph (h)(1) or (h)(2) of this AD, including all subparagraphs.

(ii) If corrosion is found on any wing lift strut during the inspection required in paragraph (h)(2) of this AD or during any repetitive inspection required in paragraph (h)(2)(i) of this AD, or if any requirement in the Appendix of this AD is not met, before further flight after any inspection in which corrosion is found or the Appendix requirements are not met, replace the affected wing lift strut with one of the replacement options specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD. Do the replacement following the procedures specified in those paragraphs, as applicable.

Before further flight after the removal required in paragraph (g) of this AD, replace the wing lift struts following one of the options in paragraph (i)(1), (i)(2), or (i)(3) of this AD, including all subparagraphs, or inspect each wing lift strut following paragraph (h)(1) or (h)(2) of this AD.

(1) Install original equipment manufacturer (OEM) part number wing lift struts (or FAA-approved equivalent part numbers) that have been inspected following the procedures in either paragraph (h)(1) or (h)(2) of this AD, including all subparagraphs, and are found to be airworthy. Do the installations following Piper MSB No. 528D, dated October 19, 1990, or Piper MSB No. 910A, dated October 10, 1989, as applicable. Repetitively thereafter inspect the newly installed wing lift struts at intervals not to exceed 24 calendar months following the procedures in either paragraph (h)(1) or (h)(2) of this AD, including all subparagraphs.

(2) Install new sealed wing lift strut assemblies (or FAA-approved equivalent part numbers) (these sealed wing lift strut assemblies also include the wing lift strut forks) following Piper MSB No. 528D, dated October 19, 1990, and Piper MSB No. 910A, dated October 10, 1989, as applicable. Installing one of these new sealed wing lift strut assemblies terminates the repetitive inspection requirements in paragraphs (h)(1) and (h)(2) of this AD, and the wing lift strut fork removal, inspection, and replacement requirement in paragraphs (j) and (k) of this AD, including all subparagraphs, for that wing lift strut assembly.

(3) Install F. Atlee Dodge wing lift strut assemblies following F. Atlee Dodge Aircraft Services, Inc. Installation Instructions No. 3233-I for Modified Piper Wing Lift Struts Supplemental Type Certificate (STC) SA4635NM, dated February 1, 1991. Repetitively thereafter inspect the newly installed wing lift struts at intervals not to exceed 60 calendar months following the procedures in paragraph (h)(1) or (h)(2) of this AD, including all subparagraphs.

(1) For all airplanes previously affected by AD 99-01-05 R1, except for Model PA-25, PA-25-235, and PA-25-260 airplanes: Within the next 100 hours time-in-service (TIS) after February 8, 1999 (the effective date retained from AD 99-01-05) or within 500 hours TIS after the last inspection done in accordance with AD 93-10-06 (which was superseded by AD 99-01-05), whichever occurs later, remove the wing lift strut forks (unless already replaced in accordance with paragraph (i)(2) of this AD). Do the removal following Piper MSB No. 528D, dated October 19, 1990, or Piper MSB No. 910A, dated October 10, 1989, as applicable. Before further flight after the removal, do the actions in one of the following paragraphs (k) or (l) of this AD, including all subparagraphs.

(2) For all airplanes new to this AD (not previously affected by AD 99-01-05 R1): Within the next 100 hours TIS after the effective date of this AD or within 500 hours TIS after the last inspection done in accordance with AD 93-10-06 (which was superseded by AD 99-01-05), whichever occurs later, remove the wing lift strut forks (unless already replaced in accordance with paragraph (i)(2) of this AD). Do the removal following Piper MSB No. 528D, dated October 19, 1990, or Piper MSB No. 910A, dated October 10, 1989, as applicable. Before further flight after the removal, do the actions in one of the following paragraphs (k) or (l) of this AD, including all subparagraphs.

For all airplanes affected by this AD: Before further flight after the removal required in paragraph (j) of this AD, inspect the wing lift strut forks following paragraph (k) of this AD, including all subparagraphs, or do the wing lift strut fork replacement following one of the options in paragraph (l)(1), (l)(2), (l)(3), or (l)(4) of this AD, including all subparagraphs. Inspect the wing lift strut forks for cracks using magnetic particle procedures, such as those contained in FAA Advisory Circular (AC) 43.13-1B, Chapter 5, which can be found on the Internet http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgAdvisoryCircular.nsf/0/99c827db9baac81b86256b4500596c4e/$FILE/Chapter%2005.pdf. Repetitively thereafter inspect at intervals not to exceed 500 hours TIS until the replacement time requirement specified in paragraph (k)(2) or (k)(3) of this AD is reached provided no cracks are found.

(1) If cracks are found during any inspection required in paragraph (k) of this AD or during any repetitive inspection required in paragraph (k)(2) or (k)(3) of this AD, before further flight, replace the affected wing lift strut fork with one of the replacement options specified in paragraph (l)(1), (l)(2), (l)(3), or (l)(4) of this AD, including all subparagraphs. Do the replacement following the procedures specified in those paragraphs, as applicable.

(2) If no cracks are found during the initial inspection required in paragraph (k) of this AD and the airplane is currently equipped with floats or has been equipped with floats at any time during the previous 2,000 hours TIS since the wing lift strut forks were installed, at or before accumulating 1,000 hours TIS on the wing lift strut forks, replace the wing lift strut forks with one of the replacement options specified in paragraph (l)(1), (l)(2), (l)(3), or (l)(4) of this AD, including all subparagraphs. Do the replacement following the procedures specified in those paragraphs, as applicable. Repetitively thereafter inspect the newly installed wing lift strut forks at intervals not to exceed 500 hours TIS following the procedures specified in paragraph (k) of this AD, including all subparagraphs.

(3) If no cracks are found during the initial inspection required in paragraph (k) of this AD and the airplane has never been equipped with floats during the previous 2,000 hours TIS since the wing lift strut forks were installed, at or before accumulating 2,000 hours TIS on the wing lift strut forks, replace the wing lift strut forks with one of the replacement options specified in paragraph (l)(1), (l)(2), (l)(3), or (l)(4) of this AD, including all subparagraphs. Do the replacement following the procedures specified in those paragraphs, as applicable. Repetitively thereafter inspect the newly installed wing lift strut forks at intervals not to exceed 500 hours TIS following the procedures specified in paragraph (k) of this AD, including all subparagraphs.

Before further flight after the removal required in paragraph (j) of this AD, replace the wing lift strut forks following one of the options in paragraph (l)(1), (l)(2), (l)(3), or (l)(4) of this AD, including all subparagraphs, or inspect the wing lift strut forks following paragraph (k) of this AD, including all subparagraphs.

(1) Install new OEM part number wing lift strut forks of the same part numbers of the existing part (or FAA-approved equivalent part numbers) that were manufactured with rolled threads. Wing lift strut forks manufactured with machine (cut) threads are not to be used. Do the installations following Piper MSB No. 528D, dated October 19, 1990, or Piper MSB No. 910A, dated October 10, 1989, as applicable. Repetitively thereafter inspect and replace the newly installed wing lift strut forks at intervals not to exceed 500 hours TIS following the procedures specified in paragraph (k) of this AD, including all subparagraphs.

(2) Install new sealed wing lift strut assemblies (or FAA-approved equivalent part numbers) (these sealed wing lift strut assemblies also include the wing lift strut forks) following Piper MSB No. 528D, dated October 19, 1990, and Piper MSB No. 910A, dated October 10, 1989, as applicable. This installation may have already been done through the option specified in paragraph (i)(2) of this AD. Installing one of these new sealed wing lift strut assemblies terminates the repetitive inspection requirements in paragraphs (h)(1) and (h)(2) of this AD, and the wing lift strut fork removal, inspection, and replacement requirements in paragraphs (j) and (k) of this AD, including all subparagraphs, for that wing lift strut assembly.

(3) For the airplanes specified below, install Jensen Aircraft wing lift strut fork assemblies specified below in the applicable STC following Jensen Aircraft Installation Instructions for Modified Lift Strut Fitting. Installing one of these wing lift strut fork assemblies terminates the repetitive inspection requirement of this AD only for that wing lift strut fork. Repetitively inspect each wing lift strut as specified in paragraph (h)(1) or (h)(2) of this AD, including all subparagraphs.

(i) For Models PA-12 and PA-12S airplanes: STC SA1583NM, which can be found on the Internet at http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/2E708575849845B285256CC1008213CA?OpenDocument&Highlight=sa1583nm;

(ii) For Model PA-14 airplanes: STC SA1584NM, which can be found on the Internet at http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/39872B814471737685256CC1008213D0?OpenDocument&Highlight=sa1584nm;

(iii) For Models PA-16 and PA-16S airplanes: STC SA1590NM, which can be found on the Internet at http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/B28C4162E30D941F85256CC1008213F6?OpenDocument&Highlight=sa1590nm;

(iv) For Models PA-18, PA-18S, PA-18 “105” (Special), PA-18S “105” (Special), PA-18A, PA-18 “125” (Army L-21A), PA-18S “125”, PA-18AS “125”, PA-18 “135” (Army L-21B), PA-18A “135”, PA-18S “135”, PA-18AS “135”, PA-18 “150”, PA-18A “150”, PA-18S “150”, PA-18AS “150”, PA-18A (Restricted), PA-18A “135” (Restricted), and PA-18A “150” (Restricted) airplanes: STC SA1585NM, which can be found on the Internet at http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/A2BE010FB1CA61A285256CC1008213D6?OpenDocument&Highlight=sa1585nm;

(v) For Models PA-20, PA-20S, PA-20 “115”, PA-20S “115”, PA-20 “135”, and PA-20S “135” airplanes: STC SA1586NM, which can be found on the Internet at http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/873CC69D42C87CF585256CC1008213DC?OpenDocument&Highlight=sa1586nm; and

(vi) For Model PA-22 airplanes: STC SA1587NM, which can be found on the Internet at http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/B051D04CCC0BED7E85256CC1008213E0?OpenDocument&Highlight=sa1587nm.

(4) Install F. Atlee Dodge wing lift strut assemblies following F. Atlee Dodge Installation Instructions No. 3233-I for Modified Piper Wing Lift Struts (STC SA4635NM), dated February 1, 1991. This installation may have already been done in accordance paragraph (i)(3) of this AD. Installing these wing lift strut assemblies terminates the repetitive inspection requirements of this AD for the wing lift strut fork only. Repetitively inspect the wing lift struts as specified in paragraph (h)(1) or (h)(2) of this AD, including all subparagraphs.

(1) For all airplanes previously affected by AD 99-01-05 R1, except for Models PA-25, PA-25-235, and PA-25-260 airplanes: Within 1 calendar month after February 8, 1999 (the effective date retained from AD 99-01-05), or within 24 calendar months after the last inspection required by AD 93-10-06 (which was superseded by AD 99-01-05), whichever occurs later, and before further flight after any replacement of a wing lift strut assembly required by this AD, do one of the following actions in paragraph (m)(1)(i) or (m)(1)(ii) of this AD. The “NO STEP” markings required by paragraph (m)(1)(i) or (m)(1)(ii) of this AD must remain in place for the life of the airplane.

(i) Install “NO STEP” decal, Piper (P/N) 80944-02, on each wing lift strut approximately 6 inches from the bottom of the wing lift strut in a way that the letters can be read when entering and exiting the airplane; or

(ii) Paint the words “NO STEP” approximately 6 inches from the bottom of the wing lift strut in a way that the letters can be read when entering and exiting the airplane. Use a minimum of 1-inch letters using a color that contrasts with the color of the airplane.

(2) For all airplanes new to this AD (not previously affected by AD 99-01-05 R1): Within 1 calendar month after the effective date of this AD or within 24 calendar months after the last inspection required by AD 93-10-06 (which was superseded by AD 99-01-05), whichever occurs later, and before further flight after any replacement of a wing lift strut assembly required by this AD, do one of the following actions in paragraph (m)(2)(i) or (m)(2)(ii) of this AD. The “NO STEP” markings required by paragraph (m)(2)(i) or (m)(2)(ii) of this AD must remain in place for the life of the airplane.

(i) Install “NO STEP” decal, Piper (P/N) 80944-02, on each wing lift strut approximately 6 inches from the bottom of the wing lift strut in a way that the letters can be read when entering and exiting the airplane; or

(ii) Paint the words “NO STEP” approximately 6 inches from the bottom of the wing lift strut in a way that the letters can be read when entering and exiting the airplane. Use a minimum of 1-inch letters using a color that contrasts with the color of the airplane.