1 [Federal Register Volume 78, Number 251 (Tuesday
Contents
1. 150 PA I8AS 150 PA 18A Restricted PA 18A 135 Restricted and PA 18A 150 Restricted 18 1 through 18 8309025 18900 through 1809032 and 1809034 through 1809040 Piper Aircraft Inc PA 19 Army L 18C and PA 19S 19 1 19 2 and 19 3 Piper Aircraft Inc PA 20 PA 20S PA 20 115 PA 20S 115 PA 20 135 and PA 20S 135 20 1 through 20 1121 Piper Aircraft Inc d Subject PA 22 PA 22 108 PA 22 135 PA 22S 135 PA 22 150 PA 22S 150 PA 22 160 and PA 22S 160 22 1 through 22 9848 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 We are revising AD 99 01 05 Amendment 39 10972 63 FR 72132 December 31 1998 because of reports that paragraph c had been misinterpreted and caused confusion This AD removes the language in paragraph c of AD 99 01 05 which caused the confusion 2 This AD clarifies 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 otherwi2. Costs of Compliance We estimate that this AD affects 22 000 airplanes of U S registry We estimate the following costs to comply with this AD However the only difference in the costs presented below and the costs associated with AD 99 01 05 is the change in the labor rate from 65 per hour to 85 per hour Estimated Costs Action Labor cost Parts cost Cost per Cost on U S product operators Inspection of 8 work hours x 85 per hour Not 680 per 14 960 000 the wing lift 680 per inspection cycle applicable inspection cycle per inspection struts and wing cycle lift strut forks Installation 1 work hour x 85 85 30 115 2 530 000 placard We estimate the following costs to do any necessary replacements that will be required based on the results of the inspection We have no way of determining the number of aircraft that might need these replacements On Condition Costs Action Labor cost per Parts cost per Cost per product wing lift strut wing lift strut per wing lift strut Replacement of the wing lift strut 4 work hours x 85 440 780 and or wing lift strut forks per hour 340 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 thi
3. Certificate STC SA4635NM dated February 1 1991 16 iv Jensen 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 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 99 01 05 R1 Procedures and Requirements for Ultrasonic Inspection of Piper Wing Lift Struts Equipment Requirements 1 A portable ultrasonic thickness gauge or
4. Federal Register Volume 78 Number 251 Tuesday December 31 2013 Rules and Regulations Pages 79599 79600 From the Federal Register Online via the Government Printing Office www gpo gov FR Doc No 2013 30859 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Docket No FAA 2013 0023 Directorate Identifier 96 CE 072 AD Amendment 39 17688 AD 99 01 05 R1 RIN 2120 AA64 Airworthiness Directives Various Aircraft Equipped With Wing Lift Struts AGENCY Federal Aviation Administration FAA DOT ACTION Final rule correction SUMMARY The FAA is correcting an airworthiness directive AD that published in the Federal Register That AD applies to certain aircraft equipped with wing lift struts The list of affected airplanes in the Applicability section is incorrect Several Piper Aircraft Inc Model PA 18 airplanes were inadvertently omitted from the final rule however those models were included in the notice of proposed rulemaking This document corrects that error In all other respects the original document remains the same DATES This final rule is effective January 14 2014 ADDRESSES You may examine the AD docket on the Internet at http www regulations gov by searching for and locating it in Docket No FAA 2013 00023 or in person at the Docket Management Facility between 9 a m and 5 p m Monday through Friday except Federal holidays The AD docket contains this AD the regulatory ev
5. 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 bef
6. 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 layer The thickness gate level s
7. aircraft log book 19 4 Pencil Marks Flexible Ruler Bottom View of Forward Lift Strut Bottom View of Rear Lift Strut Figure 1 Issued in Kansas City Missouri on November 22 2013 Earl Lawrence Manager Small Airplane Directorate Aircraft Certification Service 20
8. for Non destructive Testing or the Military Standard for Nondestructive Testing Personnel Qualification and Certification MIL STD 410E which can be found on the Internet at http aerospacedefense thomasnet com Asset MIL STD 410 pdf i If no corrosion is found on any wing lift strut during the inspection required in paragraph i 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 12 wing lift strut at intervals not to exceed 24 calendar months following the procedures in paragraph i 1 or i 2 of this AD including all subparagraphs ii If corrosion is found on any wing lift strut during the inspection required in paragraph 1 2 of this AD or during any repetitive inspection required in paragraph i 2 1 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 j 1 j 2 or G 3 of this AD Do the replacement following the procedures specified in those paragraphs as applicable j Wing Lift Strut Replacement Options Before further flight after the removal requir
9. in paragraph 1 of this AD including all subparagraphs m Wing Lift Strut Fork Replacement Options Before further flight after the removal required in paragraph k of this AD replace the wing lift strut forks following one of the options in paragraph m 1 m 2 m 3 or m 4 of this AD including all subparagraphs or inspect the wing lift strut forks following paragraph 1 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 1 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 j 2 of this AD Installing one of the
10. 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 0 of this AD for approving such actions as an alternative method of compliance AMOC h Remove Wing Lift Struts At whichever of the compliance times specified in paragraphs h 1 or h 2 of this AD that 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 1 1 i 2 Q 1 G 2 or G 3 of this AD including all subparagraphs 1 Within 1 calendar month after February 8 1999 the effective date retained from AD 99 01 05 Amendment 39 10972 63 FR 72132 December 31 1998 or 2 Within 24 calendar months after the last inspection done in accordance with AD 93 10 06 Amendment 39 8586 58 FR 29965 May 25 1993 which was superseded by AD 99 01 05 Amendment 39 10972 63 FR 72132 December 31 1998 whichever occurs later i Inspect Wing Lift Struts Before further flight after the removal required in paragraph h of this AD inspect each wing lift strut following paragraph i 1 or 1 2 of this AD including all subparagraphs or do the wing lift strut replacement followin
11. of the Amendment Accordingly under the authority delegated to me by the Administrator the FAA amends 14 CFR part 39 as follows PART 39 AIRWORTHINESS DIRECTIVES 1 The authority citation for part 39 continues to read as follows Authority 49 U S C 106 g 40113 44701 39 13 Amended 2 The FAA amends 39 13 by removing Airworthiness Directive AD 99 01 05 Amendment 39 10972 63 FR 72132 December 31 1998 and adding the following new AD AIRWORTHINESS DIRECTIVE FAA Aviation Safety www faa gov aircraft safety alerts www gpoaccess gov fr advanced html CORRECTION Federal Register Volume 78 Number 251 Tuesday December 31 2013 Pages 79599 79600 99 01 05 R1 Various Aircraft Amendment 39 17688 Docket No FAA 2013 0023 Directorate Identifier 96 CE 072 AD a Effective Date This AD is effective January 14 2014 b Affected ADs This AD revises AD 99 01 05 Amendment 39 10972 63 FR 72132 December 31 1998 which superseded AD 93 10 06 Amendment 39 8586 58 FR 29965 May 25 1993 AD 99 26 19 Amendment 39 11479 64 FR 72524 December 28 1999 also relates to the subject of this AD c Applicability This AD applies to the following airplanes identified in table 1 of paragraph c of this AD that are 1 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 por
12. 4 474 5551 fax 404 474 5606 email gregory noles faa gov 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 q 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 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
13. 7 5527 is Document Management Facility U S Department of Transportation Docket Operations M 30 West Building Ground Floor Room W12 140 1200 New Jersey Avenue SE Washington DC 20590 FOR FURTHER INFORMATION CONTACT For Piper Aircraft Inc airplanes contact Gregory Keith Noles Aerospace Engineer FAA Atlanta Aircraft Certification Office 1701 Columbia Avenue College Park Georgia 30337 phone 404 474 5551 fax 404 474 5606 email gregory noles faa gov For FS 2000 Corp FS 2001 Corp FS 2002 Corporation and FS 2003 Corporation airplanes contact Jeff Morfitt Aerospace Engineer FAA Seattle Aircraft Certification Office 1601 Lind Avenue SW Renton Washington 98057 phone 425 917 6405 fax 245 917 6590 email jeff morfitt faa gov For 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 SUPPLEMENTARY INFORMATION Discussion We issued a notice of proposed rulemaking NPRM to amend 14 CFR part 39 to revise AD 99 01 05 Amendment 39 10972 63 FR 72132 December 31 1998 AD 99 01 05 AD 99 01 05 applied to the specified products The NPRM published in the Federal Register on January 16 2013 78 FR 3356 The NPRM proposed to retain all requirements of AD 99 01 05 and clarify our intent of required actio
14. All Piper Aircraft Inc E 2 and F 2 All Piper Aircraft Inc J3C 40 J3C 50 J3C S50S Army L 4 L 4B L 4H All and L 4J J3C 65 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 Inc J4 J4A J4A S and J4E Army L 4E 4 401 through 4 1649 Piper Aircraft Inc PA 11 and PA 11S 11 1 through 11 1678 Piper Aircraft Inc PA 15 15 1 through 15 388 Piper Aircraft Inc PA 16 and PA 16S 16 1 through 16 736 Piper Aircraft Inc PA 17 17 1 through 17 215 Piper Aircraft Inc 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 I8AS 135 PA 18 150 PA 18A 150 PA 18S 150 PA I8AS 150 PA 18A Restricted PA 18A 135 Restricted and PA 18A 150 Restricted 18 1 through 18 8309025 18900 through 1809032 and 1809034 through 1809040 Piper Aircraft Inc PA 19 Army L 18C and PA 19S 19 1 19 2 and 19 3 Piper Aircraft Inc PA 20 PA 20S PA 20 115 PA 20S 115 PA 20 135 and PA 20S 135 20 1 through 20 1121 Piper Aircraft Inc ok CK ok OK x PA 22 PA 22 108 PA 22 135 PA 22S 135 PA 22 150 PA 22S 150 PA 22 160 and PA 22
15. S 160 Issued in Kansas City Missouri on December 18 2013 Earl Lawrence Manager Small Airplane Directorate Aircraft Certification Service 22 1 through 22 9848 Federal Register Volume 78 Number 237 Tuesday December 10 2013 Rules and Regulations Pages 73997 74004 From the Federal Register Online via the Government Printing Office www gpo gov FR Doc No 2013 29396 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Docket No FAA 2013 0023 Directorate Identifier 96 CE 072 AD Amendment 39 17688 AD 99 01 05 R1 RIN 2120 AA64 Airworthiness Directives Various Aircraft Equipped with Wing Lift Struts AGENCY Federal Aviation Administration FAA DOT ACTION Final rule SUMMARY We are revising Airworthiness Directive AD 99 01 05 for certain aircraft equipped with wing lift struts AD 99 01 05 required repetitively inspecting the wing lift struts for corrosion repetitively inspecting the wing lift strut forks for cracks replacing any corroded wing lift strut replacing any cracked wing lift strut fork and repetitively replacing the wing lift strut forks at a specified time for certain airplanes AD 99 01 05 also required incorporating a NO STEP placard on the wing lift strut Since we issued AD 99 01 05 we were informed that paragraph c had been misinterpreted and caused confusion This AD clarifies the intent of the language in paragraph c of AD 99 01 05 and retains a
16. aluation any comments received and other information The address for the Docket Office phone 800 647 5527 is Document Management Facility U S Department of Transportation Docket Operations M 30 West Building Ground Floor Room W12 140 1200 New Jersey Avenue SE Washington DC 20590 FOR FURTHER INFORMATION CONTACT For Piper Aircraft Inc airplanes contact Gregory Keith Noles Aerospace Engineer FAA Atlanta Aircraft Certification Office 1701 Columbia Avenue College Park Georgia 30337 phone 404 474 5551 fax 404 474 5606 email gregory noles faa gov For FS 2000 Corp FS 2001 Corp FS 2002 Corporation and FS 2003 Corporation airplanes contact Jeff Morfitt Aerospace Engineer FAA Seattle Aircraft Certification Office 1601 Lind Avenue SW Renton Washington 98057 phone 425 917 6405 fax 245 917 6590 email jeff morfitt faa gov For 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 SUPPLEMENTARY INFORMATION Airworthiness Directive 99 01 05 R1 Amendment 39 17688 78 FR 73997 December 10 2013 will require repetitively inspecting the wing lift struts for corrosion repetitively inspecting the wing lift strut forks for cracks replacing any corroded wing lift strut replacing any cracked wing lift s
17. ed in paragraph h of this AD replace the wing lift struts following one of the options in paragraph j 1 G 2 or j 3 of this AD including all subparagraphs or inspect each wing lift strut following paragraph 1 1 or i 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 1i 1 or 4 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 1 1 or i 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 i 1 and i 2 of this AD and the wing lift strut fork removal inspection and replacement requirement in paragraphs k and 1 of this AD including all subparagraphs for
18. f 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 Enable the thickness gate and
19. 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 prevention steps are then taken to protect these item
20. g one of the options in paragraph j 1 Q 2 or G 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 i 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 i 1 or 4 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 i 1 of this AD or during any repetitive inspection required in paragraph 1 1 G of this AD before further flight replace the affected wing lift strut with one of the replacement options specified in paragraph j 1 j 2 or G 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
21. graphs 1 or m of this AD including all subparagraphs D Inspect and Replace Wing Lift Strut Forks Before further flight after the removal required in paragraph k of this AD inspect the wing lift strut forks following paragraph 1 of this AD including all subparagraphs or do the wing lift strut 13 fork replacement following one of the options in paragraph m 1 m 2 m 3 or m 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 specified in paragraph 1 2 or 1 3 of this AD is reached provided no cracks are found 1 If cracks are found during any inspection required in paragraph 1 of this AD or during any repetitive inspection required in paragraph 1 2 or 1 3 of this AD before further flight replace the affected wing lift strut fork with one of the replacement options specified in paragraph m 1 m 2 m 3 or m 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 i
22. hould 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 18 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 Inspection Procedure 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 drawing
23. irplane o 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 p 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 Amendment 39 8586 58 FR 29965 May 25 1993 and AD 99 01 05 Amendment 39 10972 63 FR 72132 December 31 1998 are approved as AMOCs for this AD p 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 40
24. ll other requirements of AD 99 01 05 We are issuing this AD to correct the unsafe condition on these products DATES This AD is effective January 14 2014 The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of February 8 1999 63 FR 72132 December 31 1998 ADDRESSES For 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 supplemental type certificate 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 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 Examining the AD Docket You may examine the AD docket on the Internet at http www regulations gov by searching for and locating it in Docket No FAA 2013 00023 or in person at the Docket Management Facility between 9 a m and 5 p m Monday through Friday except Federal holidays The AD docket contains this AD the regulatory evaluation any comments received and other information The address for the Docket Office phone 800 64
25. n done in accordance paragraph j 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 i 1 or 1 2 of this AD including all subparagraphs n Install Placard 1 Within 1 calendar month after February 8 1999 the effective date retained from AD 99 01 05 Amendment 39 10972 63 FR 72132 December 31 1998 or within 24 calendar months after the last inspection required by AD 93 10 06 Amendment 39 8586 58 FR 29965 May 25 1993 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 the actions in one of the following paragraphs n 1 or n 1 i1 of this AD 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 15 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 The NO STEP markings required by paragraph n 1 or n 1 Gi of this AD must remain in place for the life of the a
26. nitial inspection required in paragraph 1 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 m 1 m 2 m 3 or m 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 1 of this AD including all subparagraphs 3 If no cracks are found during the initial inspection required in paragraph 1 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 m 1 m 2 m 3 or m 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
27. ns if the seal on a sealed wing lift strut is ever improperly broken Comments We gave the public the opportunity to participate in developing this AD The following presents the comments received on the proposal and the FAA s response to each comment Request to Combine This AD with Another AD Len J Buckel stated that AD 99 26 19 Amendment 39 11470 64 FR 72524 December 28 1999 AD 99 26 19 and AD 99 01 05 should be combined into one AD The commenter stated that since AD 99 01 05 is being revised it should also be revised to include Piper Aircraft Inc Piper Model J 2 airplanes which are covered separately in AD 99 26 19 so that all affected Piper airplanes would be covered in one AD We do not agree with the commenter AD 99 01 05 is being revised only to clarify language about how to maintain a sealed wing lift strut assembly if the seal is ever improperly broken This revision does not require any additional actions for the owners operators The same confusing and misleading language that prompted this revision is also included in AD 99 26 19 which will also be revised In order to avoid any further confusion we believe that it is in the best interest of the owners operators to maintain two separate ADs We have not changed the final rule AD action based on this comment Request to Further Clarify Paragraph g Jamison Peters of Airframes Alaska stated that stronger and clearer language should be added to this AD that
28. ore 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 the
29. p 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 A2BE010FB 1CA61A285256CC100 8213D6 OpenDocument amp 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 rg faa gov Regulatory_and_Guidance_Library rgstc nsf 0 873CC69D42C87CF585256CC1008 213DC OpenDocument amp Highlight sal586nm 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 B05 1 D04CCCOBED7E85256CC10 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 which can be found on the Internet at http rgl faa gov Regulatory_and_Guidance_Library rgstc nsf 0 E726AA A283 1BD20085256CC200 OE3DB7 OpenDocument amp Highlight sa4635nm This installation may have already bee
30. ph b 1 i paragraph 1 1 paragraph b 1 i B and b 1 iv paragraph 1 2 paragraph b 1 i C and b 1 iv paragraph 1 3 paragraph b 1 i1 A and b 1 iv paragraph 1 4 paragraph b 1 iii b 2 b 1 iv paragraph m 1 paragraph b 3 through b 3 ii paragraph m 2 paragraph b 4 through b 4 vi paragraph m 3 thru m 3 vi paragraph b 5 through b 5 ii paragraph m 4 Paragraph c Removed paragraph d paragraph n 1 paragraph d 1 paragraph n 1 i paragraph d 2 paragraph n 1 i1 N A paragraph n 2 g Compliance Unless already done compliance with AD 99 01 05 Amendment 39 10972 63 FR 72132 11 December 31 1998 do the following actions within the compliance times specified in paragraphs h through n 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
31. s 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 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 17 Instrument Setup 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 compatible with the transducer 4 I
32. s rulemaking under the authority described in Subtitle VII Part A Subpart III section 44701 General requirements Under that section Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices methods and procedures the Administrator finds necessary for safety in air commerce This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132 This AD will not have a substantial direct effect on the States on the relationship between the national government and the States or on the distribution of power and responsibilities among the various levels of government For the reasons discussed above I certify that this AD 1 Is not a significant regulatory action under Executive Order 12866 2 Is not a significant rule under 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 Adoption
33. se unsealing a sealed strut This AD retains all the actions required in AD 99 01 05 and this AD does not require any actions over that already required by AD 99 01 05 This AD does not add any additional burden to the owners operators of the affected airplanes 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 10 f Paragraph Designation Changes to AD 99 01 05 R1 Since AD 99 01 05 Amendment 39 10972 63 FR 72132 December 31 1998 was issued the AD format has been revised and certain paragraphs have been rearranged As a result the corresponding paragraph identifiers have changed in this AD as listed in the following table Table 2 to Paragraph f of This AD Revised Paragraph Identifiers Requirement in AD 99 01 05 Corresponding requirement in AD 99 01 05 R1 paragraph a paragraph h paragraph a 1 paragraph i 1 paragraph a 1 i paragraph i 1 i paragraph a 1 1i paragraph i 1 ii paragraph a 2 paragraph i 2 paragraph a 2 i paragraph i 2 i paragraph a 2 1i paragraph i 2 i1 paragraph a 3 paragraph j 1 paragraph a 4 paragraph j 2 paragraph a 5 paragraph j 3 paragraph b paragraph k paragraph b 1 paragraph 1 paragra
34. se new sealed wing lift strut assemblies terminates the repetitive inspection requirements in paragraphs 1 1 and i 2 of this AD and the wing lift strut fork removal inspection and replacement requirements in paragraphs k and 1 of this AD including all subparagraphs for that wing lift strut assembly 14 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 1 1 or 1 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 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 am
35. specifies allowing a sealed wing lift strut to be temporarily unsealed in order to perform proper maintenance actions The commenter stated that the proposed language in Note 1 to paragraph g seems somewhat ambiguous using the word never in regards to the seal of a strut being never broken but then saying that nor did we intend to preclude proper maintenance action that may temporarily unseal a sealed strut We agree with the commenter that the proposed language could be interpreted as ambiguous or conflicting We have revised Note 2 to paragraph g to further clarify that properly unsealing and resealing a sealed wing lift strut for maintenance as long as all regulations and issues are considered is still considered a terminating action for the repetitive inspection requirements of this AD Conclusion We reviewed the relevant data considered the comments received and determined that air safety and the public interest require adopting this AD with the change described previously and minor editorial changes We have determined that these minor changes e Are consistent with the intent that was proposed in the NPRM 78 FR 3356 January 16 2013 for correcting the unsafe condition and e Do not add any additional burden upon the public than was already proposed in the NPRM 78 FR 3356 January 16 2013 We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD
36. 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 which can be found on the Internet at http rgl faa gov Regulatory_and_Guidance_Library rgstc nsf 0 E726AAA283 1BD20085256CC200 OE3DB7 OpenDocument amp Highlight sa4635nm Repetitively thereafter inspect the newly installed wing lift struts at intervals not to exceed 60 calendar months following the procedures in paragraph 1 1 or 4 2 of this AD including all subparagraphs k Remove Wing Lift Strut Forks For all affected airplane models except for Models 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 Amendment 39 10972 63 FR 72132 December 31 1998 or within 500 hours TIS after the last inspection done in accordance with AD 93 10 06 Amendment 39 8586 58 FR 29965 May 25 1993 which was superseded by AD 99 01 05 whichever occurs later remove the wing lift strut forks unless already replaced in accordance with paragraph j 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 para
37. tion of each wing and 2 certificated in any category Table 1 to Paragraph c of This AD Applicability Type certificate holder Aircraft model Serial numbers FS 2000 Corp L 14 All FS 2001 Corp J5A Army L 4F JSA 80 JSB Army L 4G All J5C AE 1 and HE 1 FS 2002 Corporation PA 14 14 1 through 14 523 FS 2003 Corporation PA 12 and PA 12S 12 1 through 12 4036 LAVIA ARGENTINA PA 25 PA 25 235 and PA 25 260 25 1 through 25 S A LAVIASA 8156024 Piper Aircraft Inc TG 8 Army TG 8 Navy XLNP 1 All Piper Aircraft Inc E 2 and F 2 All Piper Aircraft Inc J3C 40 J3C 50 J3C 50S Army L 4 L 4B L 4H and L 4J J3C 65 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 All Piper Aircraft Inc Piper Aircraft Inc J4 J4A J4A S and J4E Army L 4E PA 11 and PA 11S 4 401 through 4 1649 11 1 through 11 1678 Piper Aircraft Inc PA 15 15 1 through 15 388 Piper Aircraft Inc PA 16 and PA 16S 16 1 through 16 736 Piper Aircraft Inc PA 17 17 1 through 17 215 Piper Aircraft Inc 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 I8AS 135 PA 18 150 PA 18A 150 PA 18S
38. trut fork repetitively replacing the wing lift strut forks at a specified time for certain airplanes and incorporating a NO STEP placard on the wing lift strut As published table 1 of paragraph c in the Applicability section is incorrect Several Piper Aircraft Inc Model PA 18 airplanes were inadvertently omitted from the final rule however those models were included in the notice of proposed rulemaking that was published in the Federal Register on January 16 2013 78 FR 3356 No other part of the preamble or regulatory information has been changed therefore only the changed portion of the final rule is being published in the Federal Register The effective date of this AD remains January 14 2013 Correction of Regulatory Text 39 13 Corrected In the Federal Register of December 10 2013 on page 73999 in Table 1 to Paragraph c of this AD Applicability paragraph c of AD 99 01 05 R1 Amendment 39 17688 is corrected as follows ok cK Ok ok Table 1 to Paragraph c of This AD Applicability Type certificate holder Aircraft model Serial numbers FS 2000 Corp L 14 All FS 2001 Corp J5A Army L 4F JSA 80 JSB Army L 4G All J5C AE 1 and HE 1 FS 2002 Corporation PA 14 14 1 through 14 523 FS 2003 Corporation PA 12 and PA 12S 12 1 through 12 4036 LAVIA ARGENTINA PA 25 PA 25 235 and PA 25 260 25 1 through 25 S A LAVIASA 8156024 Piper Aircraft Inc TG 8 Army TG 8 Navy XLNP 1
Download Pdf Manuals
Related Search