AIRWORTHINESS DIRECTIVE
Contents
1. Enable the thickness gate and adjust the gate so that it starts at the first backwall echo and ends at the second backwall echo Measuring between the first and second backwall echoes will produce a measurement of the steel thickness that is not affected by the paint layer on the strut If instability of the gate trigger occurs adjust the gain gate level and or damping to stabilize the thickness reading 9 Check the digital display reading and if it does not agree with the known thickness of the thinnest thickness follow your instrument s calibration recommendations to produce the correct thickness reading When a single element transducer is used this will usually involve adjusting the fine delay setting 10 Place the transducer on the thickest step of shim using couplant Adjust the thickness gate width so that the gate is triggered by the second backwall reflection of the thick section If the digital display does not agree with the thickest thickness follow your instruments calibration recommendations to produce the correct thickness reading A slight adjustment in the velocity may be necessary to get both the thinnest and the thickest reading correct Document the changed velocity value 11 Place couplant on an area of the lift strut which is thought to be free of corrosion and ring the transducer to surface Minor adjustments to the signal and gate settings may be required to account for coupling improvements resulting from the paint la2. 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 11 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 4 of this AD or if any 9 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 1 1 i 2 or i 3 of this AD Do the replacement following the procedures specified
3. color of the airplane n Alternative Methods of Compliance AMOCs 1 The Manager Atlanta ACO FAA has the authority to approve AMOCs for this AD related to Piper Aircraft Inc airplanes the Manager Seattle ACO FAA has the authority to approve AMOCs for this AD related to FS 2000 Corp FS 2001 Corp FS 2002 Corporation and FS 2003 Corporation airplanes and the Manager Standards Office FAA has the authority to approve AMOCs for this AD related to LAVIA ARGENTINA S A LAVIASA airplanes 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 ACO send it to the attention of the appropriate person identified in paragraph o 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 AMOCs approved for AD 93 10 06 AD 99 01 05 and AD 99 01 05 R1 are approved as AMOCs for this AD o Related Information 1 For more information about this AD related to Piper Aircraft Inc airplanes contact Gregory Keith Noles Aerospace Engineer FAA Atlanta ACO 1701 Columbia Avenue College Park Georgia 30337 phone 404 474 5551 fax 404 474 5606 email gregory noles faa gov
4. 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 j Remove Wing Lift Strut Forks 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 1 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 1 of this AD including all subparagraphs 2 For all airplanes new to this AD not previously affecte
5. 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 1 1 1 2 1 3 or 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 1 1 1 2 3 or 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 neve
6. 2 For more information about this AD related to FS 2000 Corp FS 2001 Corp FS 2002 Corporation and FS 2003 Corporation airplanes contact Jeff Morfitt Aerospace Engineer FAA Seattle ACO 1601 Lind Avenue SW Renton Washington 98057 phone 425 917 6405 fax 245 917 6590 email jeff morfitt faa gov 3 For more information about this AD related to LAVIA ARGENTINA S A LAVIASA airplanes contact S M Nagarajan Aerospace Engineer FAA Small Airplane Directorate 901 Locust Room 301 Kansas City Missouri 64106 telephone 816 329 4145 fax 816 329 4090 email sarjapur nagarajan faa gov p Material Incorporated by Reference 1 The Director of the Federal Register approved the incorporation by reference IBR 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 13 3 The following service information was approved for IBR on February 8 1999 63 FR 72132 December 31 1998 i Piper Aircraft Corporation Mandatory Service Bulletin No 528D dated October 19 1990 ii Piper Aircraft Corporation Mandatory Service Bulletin No 910A dated October 10 1989 iii 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 iv Je
7. AIRWORTHINESS DIRECTIVE FAA Aviation Safety www faa gov aircraft safety alerts www gpoaccess gov fr advanced html 2015 08 04 Various Aircraft Amendment 39 18140 Docket No FAA 2014 1083 Directorate Identifier 2014 CE 036 AD a Effective Date This AD is effective June 3 2015 b Affected ADs This AD supersedes AD 99 01 05 R1 Amendment 39 17688 78 FR 73997 December 10 2013 corrected 78 FR 79599 December 31 2013 AD 99 01 05 R1 AD 99 26 19 R1 Amendment 39 17681 78 FR 76040 December 16 2013 also relates to the subject of this AD c Applicability This AD applies to the following airplanes identified in Table 1 and Table 2 to paragraph c of this AD that are equipped with wing lift struts including airplanes commonly known as a Clipped Wing Cub which modify the airplane primarily by removing approximately 40 inches of the inboard portion of each wing and are certificated in any category 1 Based on optional engine installations some airplanes may have been re identified or registered with another model that is not listed in the type certificate data sheet TCDS For instance Piper Model J3C 65 airplanes are type certificated on Type Certificate Data Sheet TCDS A 691 but may also have been re identified or registered as a Model J3C 115 J3F 50 J3C 75 J3C 75D J3C 75S J3L 75 J3C 85 J3C 85S J3C 90 J3F 90 J3F 90S J3C 100 or J3 LAJ airplane 2 The airplane model number on the affected airp
8. D except for the addition of certain model airplanes to the applicability paragraph c of this AD 3 We are issuing this AD to detect and correct corrosion and cracking on the front and rear wing lift struts and forks which could cause the wing lift strut to fail This failure could result in the wing separating from the airplane f Compliance 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 alternat
9. Internet at http rg faa gov Regulatory_and_Guidance_Library rgstc nsf 0 2E708575849845B285256CC10082 13CA OpenDocument amp Highlight sa1583nm ii For Model PA 14 airplanes STC SA1584NM which can be found on the Internet at http rg faa gov Regulatory_and_Guidance_Library rgstc nsf 0 39872B8 1447 1737685256CC10082 13D0 OpenDocument amp Highlight sa1584nm iii For Models PA 16 and PA 16S airplanes STC SA1590NM which can be found on the Internet at http rg faa gov Regulatory_and_Guidance_Library rgstc nsf 0 B28C4162E30D941F85256CC1008 213F6 OpenDocument amp 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 I8AS 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 A2BE010FB1CA61A285256CC100 8213D6 OpenDocument amp Highlight sal585nm 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 873CC69D42C87CF585256CC 1008 213DC OpenDocument amp Highlight sal586nm and vi For Model PA 22 airplanes STC SA1587NM
10. and PA 16S 16 1 through 16 Inc 736 Piper Aircraft PA 17 17 1 through 17 Inc 215 Piper Aircraft PA 18 PA 18S PA 18 105 Special PA 18S 105 18 1 through 18 Inc Special PA 18A PA 18 125 Army L 21A PA 18S 8309025 18900 125 PA 18AS 125 PA 18 135 Army L 21B PA through 1809032 18A 135 PA 18S 135 PA 18AS 135 PA 18 150 and 1809034 PA 18A 150 PA 18S 150 PA 18AS 150 PA 18A through 1809040 Restricted PA 18A 135 Restricted and PA 18A 150 Restricted Piper Aircraft PA 19 Army L 18C and PA 19S 18 1 through 18 Inc 7632 and 19 1 19 2 and 19 3 Piper Aircraft PA 20 PA 20S PA 20 115 PA 20S 115 PA 20 20 1 through 20 Inc 135 and PA 20S 135 1121 Piper Aircraft PA 22 PA 22 108 PA 22 135 PA 22S 135 PA 22 150 22 1 through 22 Inc PA 22S 150 PA 22 160 and PA 22S 160 9848 Table 2 to Paragraph c of This AD Airplanes New to This AD Type certificate holder Piper Aircraft Inc Aircraft Serial Nos model J 3 October 15 1939 1100 through 1200 and 1999 and up that were manufactured before Piper Aircraft J3C 65 All Inc Army L 4A Piper Aircraft J3P 2325 2327 2339 2340 2342 2344 2345 2347 2349 2351 2355 Inc and up that were manufactured before January 10 1942 Piper Aircraft J4B 4 400 and up that were manufactured before Dec
11. before proceeding further 6 If the A trace is unsteady or the thickness reading is clearly wrong adjust the signal gain and or gate setting to obtain reasonable and steady readings If any instrument setting is adjusted repeat steps 13 and 14 of the INSTRUMENT SETUP section before proceeding further 7 In areas where obstructions are present take a data point as close to the correct area as possible NOTE The strut wall contains a fabrication bead at approximately 40 of the strut chord The bead may interfere with accurate measurements in that specific location 8 A measurement of 0 024 inch or less shall require replacement of the strut prior to further flight 9 If at any time during testing an area is encountered where a valid thickness measurement cannot be obtained due to a loss of signal strength or quality the area shall be considered suspect These areas may have a remaining wall thickness of less than 0 020 inch which is below the range of this setup or they may have small areas of localized corrosion or pitting present The latter case will result in a reduction in signal strength due to the sound being scattered from the rough surface and may result in a signal that includes echoes from the pits as well as the backwall The suspect area s shall be tested with a Maule Fabric Tester as specified in Piper MSB No 528D dated October 19 1990 or Piper MSB No 910A dated October 10 1989 10 Record the lift strut inspection in
12. ble with the transducer 4 If a removable delay line is used remove it and place a drop of couplant between the transducer face and the delay line to assure good transmission of ultrasonic energy Reassemble the delay line transducer and continue 5 Program a velocity of 0 231 inch microsecond into the ultrasonic unit unless an alternative instrument calibration procedure is used to set the sound velocity 6 Obtain a step wedge or steel shims per item 3 of the EQUIPMENT REQUIREMENTS Place the probe on the thickest sample using couplant Rotate the transducer slightly back and forth to ring the transducer to the sample Adjust the delay and range settings to arrive at an A trace signal display with the first backwall echo from the steel near the left side of the screen and the second backwall echo near the right of the screen Note that when a single element transducer is used the initial pulse and the delay line steel interface will be off of the screen to the left Adjust the gain to place the amplitude of the first backwall signal at approximately 80 screen height on the A trace 7 Ring the transducer on the thinnest step or shim using couplant Select positive half wave rectified negative half wave rectified or filtered signal display to obtain the cleanest signal Adjust the pulse voltage pulse width and damping to obtain the best signal resolution These settings can vary from one transducer to another and are also user dependent 8
13. d 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 1 of this AD including all subparagraphs k Inspect and Replace Wing Lift Strut Forks 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 10 including all subparagraphs or do the wing lift strut fork replacement following one of the options in paragraph 1 1 D 2 3 or 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 rg faa gov Regulatory_and_Guidance_Library rgAdvisoryCircular nsf 0 99c827db9baac8 1b86 256b4500596c4e FILE Chapter 2005 pdf Repetitively thereafter inspect at intervals not to exceed 500 hours TIS until the replacement time requirement
14. ember 11 1942 Inc Piper Aircraft J4F 4 828 and up Inc d Subject Joint Aircraft System Component JASC Air Transport Association ATA of America Code 57 Wings e Unsafe Condition 1 The subject of this AD was originally prompted by reports of corrosion damage found on the wing lift struts AD 99 01 05 R1 is being superseded to include certain Piper Aircraft Inc Models J 3 J3C 65 Army L4A J3P J4B and J4F airplanes that were inadvertently omitted from the applicability paragraph c of AD 99 01 05 64 FR 72524 December 28 1999 99 01 05 and subsequently AD 99 01 05 R1 Note 2 to paragraph e of this AD There is a serial number overlap between the Piper PA 18 series airplanes and the Piper Model PA 19 Army L 18C airplanes listed in AD 99 01 05 R1 Serial numbers 18 1 through 18 7632 listed for the PA 18 series airplanes are also now listed under Model PA 19 Army L 18C and Model PA 19S 2 AD 99 01 05 R1 was issued to clarify the FAA s intention that if a sealed wing lift strut assembly is installed as a replacement part the repetitive inspection requirement is terminated only if the seal is never improperly broken If the seal is improperly broken then that wing lift strut becomes subject to continued repetitive inspections We did not intend to promote drilling holes into or otherwise unsealing a sealed strut This AD retains all the actions required in AD 99 01 05 R1 There are no new requirements in this A
15. ements 1 A portable ultrasonic thickness gauge or flaw detector with echo to echo digital thickness readout capable of reading to 0 001 inch and an A trace waveform display will be needed to do this inspection 2 An ultrasonic probe with the following specifications will be needed to accomplish this inspection 10 MHz or higher 0 283 inch or smaller diameter dual element or delay line transducer designed for thickness gauging The transducer and ultrasonic system shall be capable of accurately measuring the thickness of AISI 4340 steel down to 0 020 inch An accuracy of 0 002 inch throughout a 0 020 inch to 0 050 inch thickness range while calibrating shall be the criteria for acceptance 3 Either a precision machined step wedge made of 4340 steel or similar steel with equivalent sound velocity or at least three shim samples of same material will be needed to accomplish this inspection One thickness of the step wedge or shim shall be less than or equal to 0 020 inch one shall be greater than or equal to 0 050 inch and at least one other step or shim shall be between these two values 4 Glycerin light oil or similar non water based ultrasonic couplants are recommended in the setup and inspection procedures Water based couplants containing appropriate corrosion inhibitors may be utilized provided they are removed from both the reference standards and the test item after the inspection procedure is completed and adequate corrosion prev
16. ention steps are then taken to protect these items e NOTE Couplant is defined as a substance used between the face of the transducer and test surface to improve transmission of ultrasonic energy across the transducer strut interface e NOTE If surface roughness due to paint loss or corrosion is present the surface should be sanded or polished smooth before testing to assure a consistent and smooth surface for making contact with the transducer Care shall be taken to remove a minimal amount of 14 structural material Paint repairs may be necessary after the inspection to prevent further corrosion damage from occurring Removal of surface irregularities will enhance the accuracy of the inspection technique 1 Set up the ultrasonic equipment for thickness measurements as specified in the instrument s user s manual Because of the variety of equipment available to perform ultrasonic thickness measurements some modification to this general setup procedure may be necessary However the tolerance requirement of step 13 and the record keeping requirement of step 14 must be satisfied 2 If battery power will be employed check to see that the battery has been properly charged The testing will take approximately two hours Screen brightness and contrast should be set to match environmental conditions 3 Verify that the instrument is set for the type of transducer being used i e single or dual element and that the frequency setting is compati
17. in those paragraphs as applicable i Wing Lift Strut Replacement Options 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 1 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
18. ing a complete grid make two rows of marks spaced every 1 4 inch across the width of the strut One row of marks should be about 11 inches from the lower end of the strut and the second row should be several inches away where the strut starts to narrow Lay the flexible ruler between respective tick marks of the two rows and use tape or a rubber band to keep the ruler in place See Figure 1 3 Apply a generous amount of couplant inside each of the square areas or along the edge of the ruler Re application of couplant may be necessary 4 Place the transducer inside the first square area of the drawn grid or at the first 1 4 inch mark on the ruler and ring the transducer to the strut When using a dual element transducer be very careful to record the thickness value with the axis of the transducer elements perpendicular to any curvature in the strut If this is not done loss of signal or inaccurate readings can result 5 Take readings inside each square on the grid or at 1 4 inch increments along the ruler and record the results When taking a thickness reading rotate the transducer slightly back and forth and experiment with the angle of contact to produce the lowest thickness reading possible Pay close attention to the A scan display to assure that the thickness gate is triggering off of maximized backwall echoes NOTE A reading shall not exceed 041 inch If a reading exceeds 041 inch repeat steps 13 and 14 of the INSTRUMENT SETUP section
19. ive method of compliance AMOC g Remove Wing Lift Struts 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 1 2 or 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 1 2 or G 3 of this AD including all subparagraphs h Inspect Wing Lift Struts For all airplanes listed in this AD Befo
20. lane or its registry may or may not contain the dash e g J3 and J 3 This AD applies to both variations Note 1 to paragraph c of this AD There is a serial number overlap between the Piper PA 18 series airplanes and the Piper Model PA 19 Army L 18C airplanes listed in AD 99 01 05 R1 Serial numbers 18 1 through 18 7632 listed for the PA 18 series airplanes are also now listed under Model PA 19 Army L 18C and Model PA 19S Table 1 to Paragraph c of This AD Airplanes Previously Affected by AD 99 01 05 R1 Type certificate Aircraft model Serial Nos holder FS 2000 Corp L 14 All FS 2001 Corp J5A Army L 4F JSA 80 JSB Army L 4G JSC AE 1 All and HE 1 FS 2002 PA 14 14 1 through 14 Corporation 523 FS 2003 PA 12 and PA 12S 12 1 through 12 Corporation 4036 LAVIA PA 25 PA 25 235 and PA 25 260 25 1 through 25 ARGENTINA 8156024 S A LAVIASA Piper Aircraft TG 8 Army TG 8 Navy XLNP 1 All Inc Piper Aircraft E 2 and F 2 All Inc Piper Aircraft J3C 40 J3C 50 J3C 50S J3C 65 Army L 4 L 4B L 4H All Inc L 4J Navy NE 1 and NE 2 J3C 65S J3F 50 J3F 50S J3F 60 J3F 60S J3F 65 Army L 4D J3F 65S J3L J3L S J3L 65 Army L 4C and J3L 65S Piper Aircraft J4 J4A J4A S and J4E Army L 4E 4 401 through 4 Inc 1649 Piper Aircraft PA 11 and PA 11S 11 1 through 11 Inc 1678 Piper Aircraft PA 15 15 1 through 15 Inc 388 Piper Aircraft PA 16
21. 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 12 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
22. lled 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 11 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
23. nsen Aircraft Installation Instructions for Modified Lift Strut Fittings which incorporates pages 1 and 5 Original Issue dated July 15 1983 pages 2 4 and 6 Revision No 1 dated March 30 1984 and pages a and 3 Revision No 2 dated April 20 1984 4 For Piper Aircraft Inc service information identified in this AD contact Piper Aircraft Inc Customer Services 2926 Piper Drive Vero Beach Florida 32960 telephone 772 567 4361 Internet www piper com Copies of the instructions to the F Atlee Dodge STC and information about the Jensen Aircraft STCs may be obtained from F Atlee Dodge Aircraft Services LLC 6672 Wes Way Anchorage Alaska 99518 0409 Internet www fadodge com 5 You may review copies of the referenced service information at the FAA Small Airplane Directorate 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 http www regulations gov by searching for and locating Docket No FAA 2014 1083 6 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 call 202 741 6030 or go to http www archives gov federal register cfr ibr locations html Appendix to AD 2015 08 04 Procedures and Requirements for Ultrasonic Inspection of Piper Wing Lift Struts Equipment Requir
24. r 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 1 1 1 2 DG or 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 D Wing Lift Strut Fork Replacement Options 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 1 1 2 1 3 or 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 insta
25. re 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 1 2 or 4 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 1 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 11 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 of this AD before further flight replace the affected wing lift strut with one of the replacement options specified in paragraph 1 1 i 2 or 1 3 of this AD Do the replacement following the procedures specified in those paragraphs as applicable 2
26. the aircraft log book 16 Bottom View of Rear Lift Strut Figure 1 Issued in Kansas City Missouri on April 8 2015 Earl Lawrence Manager Small Airplane Directorate Aircraft Certification Service 17
27. which can be found on the Internet at http rgl faa gov Regulatory_and_Guidance_Library rgstc nsf 0 B05 1 DO4 CCCOBED7E85256CC10 08213E0 OpenDocument amp Highlight sal587nm 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 m Install Placard 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 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
28. yer The thickness gate level should be set just high enough so as not to be triggered by irrelevant signal noise An area on the upper surface of the lift strut above the inspection area would be a good location to complete this step and should produce a thickness reading between 0 034 inch and 0 041 inch 12 Repeat steps 8 9 10 and 11 until both thick and thin shim measurements are within tolerance and the lift strut measurement is reasonable and steady 15 13 Verify that the thickness value shown in the digital display is within 0 002 inch of the correct value for each of the three or more steps of the setup wedge or shims Make no further adjustments to the instrument settings 14 Record the ultrasonic versus actual thickness of all wedge steps or steel shims available as a record of setup 1 Clean the lower 18 inches of the wing lift struts using a cleaner that will remove all dirt and grease Dirt and grease will adversely affect the accuracy of the inspection technique Light sanding or polishing may also be required to reduce surface roughness as noted in the EQUIPMENT REQUIREMENTS section 2 Using a flexible ruler draw a 1 4 inch grid on the surface of the first 11 inches from the lower end of the strut as shown in Piper MSB No 528D dated October 19 1990 or Piper MSB No 910A dated October 10 1989 as applicable This can be done using a soft 2 pencil and should be done on both faces of the strut As an alternative to draw
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