Piper Aircraft, Inc. 

2926 Piper Drive 

SERVICE NO. 12628 

BULLETIN 

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 I 

SB 1262A or SB 1262 are already in compliance with SB 12628. 

SUBJECT: 

REASON FOR REVISION: 

MODELS AFFECTED: 

PA-46-500TP Meridian 

COMPLIANCE TIME: 

APPROVAL: 

PURPOSE: 

·SAFETY INTENT: 

WING INSPECTION 

SB 1262B provides additional clarification for identifying I 

the presence of sealant at specific locations on the upper 

wing skin. 

SERIAL NUMBERS AFFECTED: 

4697001 thru 4697528 

To coincide with the next regularly scheduled maintenance event, but not to exceed I 

the next 100 hours time in service, or the next 12 calendar months, whichever 

occurs first. 

The engineering aspects of this service document have been shown to comply 

with the applicable Federal Aviation Regulations and are FAA approved. 

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. 

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) 
SERVICE BULLETIN N0.12628 

CONFIGURATION 

DESCRIPTION: 

INSTRUCTIONS: 

PAGE2of8 

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. 

NOTE: 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 107.51 

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 Ill, 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. 
SERVICE BULLETIN N0.1262B PAGE 3 of 8 

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OUTBD 

~----.. ~~--~W-IN•G~LE-A•D~I~N•G•E•D~G·E~._ .. ._._._ .. ~._ --

- r . - . \-

INSPECTION 

AREA 

See NOTE A 

WING FLAP 

NOTE A: Sealant bead not present. This area requires rework per Part 11. 

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 

" 

TRAILING EDGE 

OFWINGSKIN 
SERVICE BULLETIN NO. 12628 PAGE4of8 

t 

UP 

UPPER WING SKIN 

VIEW A-A 

SEALANT ABSENT 

REWORK REQUIRED 

Figure 2 

UPPER WING SKIN 

t 

UP 

UPPER WING SKIN 

VIEW 8-8 

SEALANT PRESENT 

NO REWORK REQUIRED 

lndentifrcation 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. AC- 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. 
SERVICE BULLETIN N0. 1262B 

J INBO 

FWD 

WING 

LEADING 

EDGE 

BOTTOM SURFACE 

OF UPPER WING SKIN 

SEE 

DETAIL 

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DETAIL C 

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STRINGERS 

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RIGHT WING 

VIEW LOOKING UP 

LOOKING UP AT LOWER WING SURFACE 

RIGHT SIDE (LEFT SIDE IS OPPOSITE) 

Figure 3 

Wing Inspection Area - Detail 

PAGE 5 of 8 

OPENING. 

ACCESS PANEL 

MAIN WING SPAR 

DRILL INSPECTION HOLES 

INTO STRINGER END CAPS 

(NO LARGER THAN 0.375 IN.) 

JINBD 

FWD 
SERVICE BULLETIN N0.12628 PAGE6of8 

3) Flood the stringer cavity with alcohol that conforms to one of the following specifications: 

Isopropyl alcohol per ASTM 0770 or TT+ 735 

Methanol per SAE AMS3004 or 0-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. 

4) 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 (1/1 000) inch maximum, is acceptable. Any corrosion beyond this limit will 

require corrective action. 

5) 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 82 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 82 sealant•• and completely overcoat with 

82 sealant••. 

3) Locally procure aluminum wool conforming to MIL-A-4864 or A·A-1043. Impregnate an appropriate 

amount of aluminum wool with 82 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 sealanVwool 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 faints 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.lf desired, this visible fillet 

seal may be painted after curing with a polyurethane enamel such as lmron paint or equivalent, 

to match adjacent wing color .. 

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•• 

prior to curing, to provide an aesthetically acceptable result. 
SERVICE BULLETIN N0. 1262B 

Solvent mixture shall consist of either one of the two mixture options: 

50% Isopropyl Alcohol 

or 

50% Methyl Ethyl Ketone 

50% Isopropyl Alcohol 

50% Acetone 

Solvent components shall conform to the following specifications: 

ASTM 0329 Standard Specification for Acetone 

ASTM 0740 Standard Specification for Methyl Ethyl Ketone 

ASTM 0770 orTT-1-735 Standard Specification for Isopropyl Alcohol 

Sealant shall conform to AMS-S-8802, Type 1, Class A2 or 82 as applicable. 

PAGE7of8 

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 A2SEALANT 

PPG PR-1440-82 PR-144Q-A2 

3M AC-236 8-2 AC-236 A-2 

AC-350 B-2 AC-350 A-2 

FLAME MASTER CS-3204 B-2 CS-3204 A-2 

ROYAL ADHESIVES WS-8020 8-2 WS-8020 A-2 

AND SEALANTS WS-8020RC 8-2 WS-8020RC A-2 

Part Ill. Documentation of Compliance 

Make a logbook entry documenting compliance with this service bulletin. 
SERVICE BULLETIN N0.1262B PAGE 8 of 8 

MATERIAL REQUIRED: See Instructions. Part II 

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