SERVICE LETTER NO. 1095A

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Piper Aircraft, Inc. 2926 Piper Drive Vero Beach, FL, U.S.A. 32960 Date: September 24, 2020 (S) (M) (OVER) SERVICE LETTER NO. 1095A ATA/JASC: 5100 Service Letter (SL) 1095A supersedes SL 1095 in its entirety. Aircraft that were previously made compliant with SL 1095 are in compliance with SL 1095A. SUBJECT: CLASSIFICATION AND DISPOSITION OF DENTS CAUSED BY HAIL DAMAGE REASON FOR REVISION: SL 1095A improves clarity, updates dent classification and disposition, and adds multiple models. Other changes update the document to the current Piper format. MODELS AFFECTED: SERIAL NUMBERS AFFECTED: PA-28-140/150/160 Cherokee All PA-28-180 Cherokee All PA-28-235 Cherokee Pathfinder All PA-28-236 Dakota All PA-28-151 Warrior All PA-28-161 Cadet All PA-28-161 Warrior II/III All PA-28-180 Archer All PA-28-181 Archer II/III All PA-28-201T Turbo Dakota All PA-28R-180 Arrow All PA-28R-200 Arrow/II All PA-28R-201 Arrow/III All PA-28R-201T Turbo Arrow III All PA-28RT-201 Arrow IV All PA-28RT-201T Turbo Arrow IV All PA-32-260/-300 Cherokee Six All PA-32R-300 Lance All PA-32RT-300/-300T Lance II/Turbo Lance II All PA-32R-301 Saratoga SP/II HP All PA-32R-301T Turbo Saratoga SP All PA-32-301 Saratoga All PA-32-301T Turbo Saratoga All PA-32R-301T Saratoga II TC All PA-32-301FT Piper 6X All PA-32-301XTC Piper 6XT All SERVICE LETTER NO. 1095A PAGE 2 of 5 PA-34-200 Seneca All PA-34-200T Seneca II All PA-34-220T Seneca III All PA-34-220T Seneca IV All PA-34-220T Seneca V All PA-44-180 Seminole All PA-44-180T Turbo Seminole All COMPLIANCE TIME: On condition; then, a repetitive inspection every 250 hours, or annually, whichever comes first APPROVAL: The engineering aspects of this service document have been shown to comply with the applicable Federal Aviation Regulations and are FAA approved. PURPOSE: This service letter provides guidelines for classifying dents to the aircraft surfaces as a result of hail, and establishes corrective action based on the severity of the damage. NOTE: Piper Aircraft makes no representation as to the aesthetic quality resulting from compliance with this service letter. INSTRUCTIONS: WARNING: ANY CRACKS DISCOVERED IN THE AIRCRAFT STRUCTURE MUST BE REPAIRED PRIOR TO THE NEXT FLIGHT. AN AIRPLANE WITH CRACKS IN ITS STRUCTURE DOES NOT MEET ITS TYPE DESIGN AND NO LONGER POSSESSES ITS REQUIRED TYPE DESIGN STRENGTH. 1. Inspection of Dents a. Determine the locations where dents are present. • Metal skin of the fuselage, wings or empennage • Control surfaces • Composite component b. Measure the maximum depth and circumscribable diameter of the dents from the aircraft exterior. For depth measurements on curved surfaces, measure the maximum depth of the dent from the general contour. The dent diameter is measured to the point where the skin material rejoins the general contour. See Figure 1. c. Measure the distance from the circumscribable diameter (defined in Step b) to the nearest fastener. Note the diameter of the fastener. d. Visually inspect the dent area for cracks, abrasions, creases, or abrupt changes in contour within an area encompassing two times the circumscribable diameter. Use a 10X magnifier or an equivalent inspection method. e. Visually inspect adjacent interior structural components for deformation. SERVICE LETTER NO. 1095A PAGE 3 of 5 Figure 1 Dent Profile Definitions Part Dent Maximum Dent Diameter A A Section A-A Dent Depth Max. Dent Dia. Section A-A (Overlapping Dents) Dent Depth Max. Dent Dia. 2. Classification of Dents NOTE: Dents classified as minor or major require an additional inspection of the inner surface of the dent, using criteria defined in Step 1.d. a. Negligible – Must meet all of the following dent limitations: 1) Dents only in the metal skin of the fuselage, wings and empennage (not applicable to control surfaces and substructure such as spars, frames and stringers). 2) Refer to Table 1 to assess the allowable depth of dents for the nominal thickness of the dented material. Dents must have a circumscribable diameter no greater than two (2.0) inches. NOTE: Refer to “Skin Materials and Thickness” figures, in Chapter 51 of the applicable Piper Airplane Maintenance Manual (AMM), or Section IV of the applicable Service Manual or AMM, for the thickness of the structure where a given dent is located. 3) Dents are a minimum distance of two times (2X) the nearest fastener’s diameter from that fastener, when measured from a dent’s circumscribable diameter to the nearest fastener. 4) There are no cracks, abrasions or creases within an area encompassing 2X the dent’s circumscribable diameter. 5) There are no deformations of the interior structure adjacent to the dents. b. Minor – Must meet all of the dent limitations provided under Negligible, except for item 3; the dents may be less than 2X the nearest fastener’s diameter from that fastener. c. Major – Exceed any or all of dent limitations 2, 4 and/or 5, provided under Negligible. d. Composite Components e. Control Surfaces – Do not meet negligible dent limitation 1. SERVICE LETTER NO. 1095A PAGE 4 of 5 3. Disposition of Dents NOTE: For repair guidance (where applicable), see Federal Aviation Administration Advisory Circular AC 43.13-1B. This free document is available for download from the FAA, at https://www.faa.gov/ regulations_policies/advisory_circulars/. a. Negligible – Acceptable as is. Cosmetic repair is not required. b. Minor – The affected parts must be replaced, or they may be repaired as follows: For each fastener that is within a distance of 2X the applicable fastener’s diameter from the edge of any dent, install one matching (same size and type) fastener adjacent to the applicable fastener. New fasteners shall be installed in accordance with the following limitations: • a minimum of 2X the fastener diameter from the edge of the dent • a minimum of 3X the fastener diameter from existing fasteners