# Piper Service Bulletin 1262: Revision B - Rights: © Piper. Filed by the FAA in regulations.gov docket FAA-2015-4213; AD 2016-01-01 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Piper Service Bulletin 1262](https://openairdocs.org/service-documents/piper/sb-1262.md) - Title as filed: Piper Service Bulletin No. 1262B - Pages: 8 - PDF: https://openairdocs.org/files/sha256/bf/a8/bfa83a080738663a26029736898e5ebc7e9adee7ca245254f09dd2353ee33962 - Page: https://openairdocs.org/service-documents/piper/sb-1262/file/bfa83a080738 ## Text This text is OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 (OCR) Piper SERVICE NO. 1262B Piper Aircraft, Inc. BULLETIN 2926 Piper Drive Vero Beach, Florida, U.S.A. 32960 PIPER CONSIDERS COMPLIANCE MANDATORY Date: April 23, 2015 (S) Service Bulletin (SB) 1262B supersedes SB 1262A in its entirety. Aircraft that have previously complied with SB 1262A or SB 1262 are already in compliance with SB 1262B. SUBJECT: WING INSPECTION REASON FOR REVISION: SB 1262B provides additional clarification for identifying the presence of sealant at specific locations on the upper wing skin. MODELS AFFECTED: SERIAL NUMBERS AFFECTED: PA-46-500TP Meridian 4697001 thru 4697528 COMPLIANCE TIME: To coincide with the next regularly scheduled maintenance event, but not to exceed the next 100 hours time in service, or the next 12 calendar months, whichever occurs 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 bulletin provides instructions for inspecting and sealing, or resealing if necessary, the upper wing surface. This service bulletin also provides instructions for inspecting the wing stringers for water intrusion. Both left and right outboard wing sections are joined to the center wing section by a structural splice. This splice is then covered by a sheet metal wing skin, forming butt joints with adjacent wing skins at Wing Station (WS) 107.50 and WS 116.00. The inspection is intended to determine if there has been any water intrusion into the stringers. • SAFETY INTENT: The safety intent of this service bulletin is to minimize the possibility of water entering the stringers common to the upper wing skin. Left uncorrected, multiple freeze/thaw cycles of water at this location could compromise the bond between the stringer flanges and the inner surface of the wing skin, which could reduce the structural integrity of the wing. ATA: 5317 (OVER) ### Page 2 (OCR) SERVICE BULLETIN NO. 1262B PAGE 2 of 8 CONFIGURATION DESCRIPTION: Incorporating this service bulletin will insure that the upper wing surfaces of affected aircraft are properly sealed at WS 107.50 and WS 116.00. INSTRUCTIONS: Some steps in these instructions are identified as "required for compliance" (RC). If this service bulletin is mandated by an airworthiness directive (AD), the steps identified as RC must be done to comply with the AD. Steps not identified as RC are recommended and may be deviated from, done as a part of other actions, or done with accepted methods different from those given in this SB, if the RC steps can be done and the airplane can be put back in a serviceable condition. NOTE: The following instructions apply to both left and right wings. Part I. Inspection NOTE: The affected area is painted with polyurethane enamel, which, when cured, exhibits a durable hard surface. At locations where this paint is applied over a more flexible substrate such as sealer, fine hairline cracks can appear in the paint. These cracks do not extend into the sealer or to the airframe structure underneath, and are therefore not a cause for concern. RC - Examine the top surface of the wing, at the two fore and aft running butt joints located along WS 107.5 and WS 116.00. See Figure 1 and Figure 2, Views A - A and B - B. NOTE: No sealant should be applied to the aft 3.8 inches of the wing skin, as identified in Figure 1 with note "Apply no sealant to this area." If a continuous, concave fillet bead of sealant can be seen extending the full length of both joints as shown in View B - B, from the deice boot (or the wing leading edge, if no deice boot is installed) to the location 3.8 inches forward of the trailing edge of the wing skin, as identified in Figure 1 as "Inspection Area,' no rework is required. Proceed to Part III, Documentation of Compliance. If any portion of the joints identified in Figure 1 as "Inspection Area" does not have a continuous, concave fillet bead of sealant as shown in View A - A, rework is required. Proceed to Part II, Rework. ### Page 3 (OCR) SERVICE BULLETIN NO. 1262B PAGE 3 of 8 - WING LEADING EDGE See NOTE A OUTBD See NOTE B INSPECTION AREA > See NOTE A A (Fig. 2) 1(702) - See NOTE B 3.8 i in APPLY NO SEALANT TO THIS AREA WING FLAP TRAILING EDGE WS WS OF WING SKIN 116.00 107.50 NOTE A: Sealant bead not present. This area requires rework per Part Il. NOTE B: Sealant bead is present. No rework required in this area. LOOKING DOWN AND FORWARD (OBLIQUE) ON UPPER WING SURFACE LEFT SIDE (RIGHT SIDE IS OPPOSITE) Figure 1 Wing Inspection Area ### Page 4 (OCR) SERVICE BULLETIN NO. 1262B PAGE 4 of 8 UPPER WING SKIN UPPER WING SKIN SEALANT • UPPER WING SKIN UPPER WING SKIN UP UP • SPLICE • SPLICE VIEW A-A VIEW B-B SEALANT ABSENT SEALANT PRESENT REWORK REQUIRED NO REWORK REQUIRED Figure 2 Indentification of Sealant on Upper Wing Skin Part II. Rework For the locations requiring rework at the joints located along WS 107.50 and WS 116.00, proceed with the following sealing instructions. 1. RC - Inspect stringers for water intrusion a. Remove access panels on lower surface of wing, as needed to gain access to the end caps of the three stringers shown in Figure 3. Remove sealant from end cap. b. Drill a hole large enough to accomplish this inspection, not to exceed 0.375 inches in diameter, centered on the outboard end cap of each of the three stringers shown in Figure 3 C. Using a borescope or other suitable tool, examine the interior of each stringer, and verify that the cavity is dry. NOTE: Due to wing dihedral, any moisture will tend to collect at the inboard end of the stringer. If any moisture is discovered, or if there is any evidence that moisture was present at any time prior to this inspection, proceed with the corrective action described in Steps 1) through 5) below for each affected stringer. • If there is no evidence that moisture was ever present, skip Steps 1) through 5) below, and proceed to Step d. WARNING: THE VAPORS EMITTED FROM THE SOLVENTS AND CORROSION PREVENTATIVE COMPOUNDS USED IN THE STEPS THAT FOLLOW ARE FLAMMABLE. EXTINGUISH OPEN FLAMES, AVOID SPARKS, AND USE IN A WELL-VENTILATED AREA. STANDARD SHOP VACUUMS MAY BE USED TO EVACUATE WATER FROM A STRINGER CAVITY, BUT MUST NOT BE USED ON FLAMMABLE LIQUIDS, AS THE ELECTRIC MOTOR PROVIDES AN IGNITION SOURCE. 1) Obtain a suitable length of flexible tubing, with an outside diameter smaller than the diameter of the hole drilled in Part II, Step 1.b, and a length of at least four (4) feet. NOTE: Overall length of each stringer is 32.55 inches. NOTE: Each stringer cavity has a volume of 15 tablespoons (approximately one cup). 2) Insert tubing through inspection hole until it reaches the far (inboard) end of the stringer. Use suction to evacuate as much water as possible. ### Page 5 (OCR) SERVICE BULLETIN NO. 1262B PAGE 5 of 8 STRINGERS TINED FWD OPENING, ACCESS PANEL WS WING LEADING EDGE MAIN WING SPAR WS 116.00 BOTTOM SURFACE DRILL INSPECTION HOLES OF UPPER WING SKIN INTO STRINGER END CAPS (NO LARGER THAN 0.375 IN.) DETAIL C TINBD FWD SEE DETAIL C RIGHT WING VIEW LOOKING UP LOOKING UP AT LOWER WING SURFACE RIGHT SIDE (LEFT SIDE IS OPPOSITE) Figure 3 Wing Inspection Area - Detail ### Page 6 (OCR) SERVICE BULLETIN NO. 1262B PAGE 6 of 8 3) Flood the stringer cavity with alcohol that conforms to one of the following specifications: Isopropyl alcohol per ASTM D770 or TT-1-735 Methanol per SAE AMS3004 or O-M-232 Denatured alcohol per SAE AMS3002 Flood the stringer cavity to a level which, at a minimum, covers the area where moisture was present. Use flexible tubing and suction to evacuate as much solvent as possible. Repeat this flushing process at least three (3) times. Re-examine interior of stringer and inspect for corrosion. If present, classify the level of corrosion damage using guidelines found in Airworthiness Circular AC 43-4a, "Corrosion Control for Aircraft," Ch. 6, Sec. 4, Para. 640. Light corrosion, which is characterized by discoloration or pitting to a depth of approximately 0.001 (1/1000) inch maximum, is acceptable. Any corrosion beyond this limit will Flood the stringer cavity a final time with a corrosion preventative compound such as LPS Procyon, Ardrox (Dinitrol) AV8, or other MIL-PRF-16173 Class I or II, Grade 1 or 4 compliant corrosion preventive compound (procure locally, or order Piper part number (P/N) 89500-800). Fill the stringer cavity to a level which, at a minimum, covers the area where moisture was present. Use flexible tubing and suction to evacuate as much liquid as possible. Allow a minimum of 24 hours drying time before proceeding to Step d, below. d. Locally clean the outer surface around the three inspection holes with solvent mixture*, and reseal using one of the following methods. Any method may be used as long as it provides adequate resealing, and selection depends on availability of materials. NOTE: Method 2) or 3) may be required for holes larger than 0.250 inch in diameter, to achieve proper sealing. 1) Reseal the holes closed with B2 sealant**, covering a diameter at least three times the diameter of the hole, and at least one hole diameter thick. 2) Fabricate a circular patch from 2024 aluminum, with diameter three (3) times the diameter of the hole, any thickness from 0.016 to 0.032 inches, inclusive. Clean patch with solvent mixture* and allow to dry. Center metal patch over hole, bond in place with B2 sealant** and completely overcoat with B2 sealant**. 3) Locally procure aluminum wool conforming to MIL-A-4864 or A-A-1043. Impregnate an appropriate amount of aluminum wool with B2 sealant**. Lay mixture over the hole, covering a diameter at least three times the diameter of the hole, and at least one hole diameter thick. Knead sealant/wool mixture to ensure thorough wet out and to remove entrapped air. e. Reinstall access panels that were removed in Step 1.a. 2. RC - Seal Wing Skin Butt Joints a. Using solvent mixture", thoroughly clean the butt joints on the top surface of the wing that are shown in Figure 1, and allow to dry. NOTE: The procedure described below will not alter the appearance of the wing when finished. At the operator's discretion, a fillet seal may be applied at the these butt joints, in a manner that matches the existing fillet seals, instead of following Steps 2.b. and 2.c. If desired, this visible fillet seal may be painted after curing with a polyurethane enamel such as Imron paint or equivalent, b. Using a piping bag or a syringe, force A2 sealant** into the butt joints on the top surface of the wing, located along WS 107.50 and WS 116.00, in the areas identified in Figure 1. c. Using a clean cloth dampened with solvent mixture*, wipe surface clean of all visible traces of A2 sealant** ### Page 7 (OCR) SERVICE BULLETIN NO. 1262B PAGE 7 of 8 Solvent mixture shall consist of either one of the two mixture options: 50% Isopropyl Alcohol 50% Methyl Ethyl Ketone or 50% Isopropyl Alcohol 50% Acetone Solvent components shall conform to the following specifications: ASTM D329 Standard Specification for Acetone ASTM D740 Standard Specification for Methyl Ethyl Ketone ASTM D770 or TT-I-735 Standard Specification for Isopropyl Alcohol Sealant shall conform to AMS-S-8802, Type 1, Class A2 or B2 as applicable. Examples of commercially available products are shown in Table 1. Mix sealant according to manufacturer's instructions. TABLE 1 AMS-S-8802, TYPE 1, CLASS A2 & B2 SEALANTS SEALANT MANUFACTURER PART NUMBER MANUFACTURER B2 SEALANT A2 SEALANT PPG PR-1440-B2 PR-1440-A2 ЗМ AC-236 B-2 AC-236 A-2 AC-350 B-2 AC-350 A-2 FLAMEMASTER CS-3204 B-2 CS-3204 A-2 ROYAL ADHESIVES WS-8020 B-2 WS-8020 A-2 AND SEALANTS WS-8020RC B-2 WS-8020RC A-2 Part III. Documentation of Compliance Make a logbook entry documenting compliance with this service bulletin. ### Page 8 (OCR) SERVICE BULLETIN NO. 1262B PAGE 8 of 8 MATERIAL REQUIRED: See Instructions, Part Il AVAILABILITY OF PARTS: Procure materials locally. EFFECTIVITY DATE: This service bulletin is effective upon receipt. SUMMARY: Applicable factory participation is limited to new aircraft in warranty at the time of compliance. Factory participation will remain in effect for a period of time not to exceed 180 days from the date of this service bulletin. Please contact your Factory Authorized Piper Service Facility to make arrangements for compliance with this service bulletin in accordance with the compliance time indicated. NOTE: Please notify the factory of any address/ownership corrections. Changes should include aircraft model, serial number, and current owner's name and address. Corrections and/or changes should be directed to: PIPER AIRCRAFT, INC. Attn.: Customer Service 2926 Piper Drive Vero Beach, FL 32960 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.