S.B. A320 004-25-84, Rev. 4 **HIGHLIGHTS SERVICE BULLETIN**  **REVISION NOTICE** Air Cruisers Company 1747 State Route 34 Wall Township, NJ 07727-3935 USA CAGE CODE 70167 Aerazur 61 Rue Pierre CURIE 78370 PLAISIR FRANCE CAGE CODE F6101

Revision No. 4 of Service Bulletin A320 004-25-84 is issued to add FAA AD 2012- 18-12 to Compliance Paragraph 1.C. Compliance paragraph 1.C. and Approval paragraph 1.E.2. have been updated per Airbus instructions.
Please discard S.B. A320 00 4-25-84 now in your posse ssion, and replace with the attached revised Service Bulletin A320 004-25-84, Revision 4, dated 09 Nov 2012.

Revision Date Original Issue 05 Feb 2010 1 09 Apr 2010 2 11 Feb 2011 3 28 Oct 2011 4 09 Nov 2012S.B. A320 004-25-84 Page 1 of 6 ISSUE DATE: 05 Feb 2010 Revision No 4, 09 Nov 2012 

# SERVICE BULLETIN Air Cruisers Company 1747 State Route 34 Wall Township, NJ 07727-3935 USA CAGE CODE 70167 Aerazur 61 Rue Pierre CURIE 78370 PLAISIR FRANCE CAGE CODE F6101

**EQUIPMENT FURNISHINGS - EMERGENCY EQUIPMENT**  **A319/A320 OFFWIN G RAMP/SLIDE EVACUATION SYSTEMS**  **ENCLOSURE MODIFICATION**
1. Planning Information A. Effectivity Offwing Ramp/Slide Systems P/Ns D31865-109, -110, -209, -210 Enclosures P/Ns D36179-107, -108, -207, -208 B. Reason There have been sporadic fi eld reports of the ramp/slide system’s aspirator becoming lodged against an extrusion “lip” of the off wing encl osure during the initial stages of the deployment sequence, tearing the aspirator blister, and potentially ren dering the slide unusable. Toaddress this issue, this Service Bulletin will outl ine instructions for t he addition of an epoxy transition, adjacent to the enclos ure extrusion in the area where the aspirator is stowed. Due to manufacturing variation, some enc losures do not have this “lip” or it is of insignificant hei ght. An epoxy transition is not necessary in these cases. C. Compliance This service bulletin is covered byAirbus Service Bulletin A320-25-1649 that has been r endered mandatory by EASAAD 2010-0210 and FAA AD 2012-18-12.S.B. A320 004-25-84 Page 2 of 6 ISSUE DATE: 05 Feb 2010 Revision No 4, 09 Nov 2012 

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D. Description
**NOTE :**  Only those organizations aut horized by the FAA or other airworthiness authorities are permitt ed to perform this modification. Inspect the specified area of the enclos ure. If an aluminum extrusion “lip” exists in this area that is equal to or greater than 0.062 5 inches (1.6 mm) (above the inner surface ofthe enclosure), follow th e instructions below for adding an epoxy transition in t he area. If a “lip” does notexist, or it is less than 0.0625 inches (1.6 mm), reidentify the enclosure and return to service. Clean and sand specific area of enclosu re. Prepare repair epoxy/putty per manufacturer’s instructions and applyto cleaned area of enclosure, forming a molded transition. Re -identify enclosure and return to service. E. Approval Certification, TSO-C69b (1). FAA Acknowledegment - This Servic e Bulletin contains modification information which has been subm itted to the FAA under the TSOC69b authorization for the affected articles. (2). The technical c ontent of this documentis approved under the authority of the DOA No. EASA.21J.031. F. Labor Hours It will take approxim ately 0.25 hour per system to accomplish the instructions outlined in this Service Bu lletin not including cure time of the epoxy. G. Material - Cost and Availability Acetone Solvent (CH 3 COCH 3 ) - Commercially Available Sandpaper (Medium Grit) - Commercially Available Fixmaster Underwater R epair Epoxy (Item No. 82093) or Loctite Repair Putty Multi-Purpose (Item No. 431348) - Commercially Available, or contact your Zodiac Services Representative. H. Tooling No specific tooling is necessary for the accomplishment of this Service Bulletin.S.B. A320 004-25-84 Page 3 of 6 ISSUE DATE: 05 Feb 2010 Revision No 4, 09 Nov 2012 

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I. Weight and Balance - None J. Electrical Load Data - Not affected K. References Engineering Change No tices (ECNs) MC17, 839 and MC17,873. This Service Bulletin is subject toAircraft Modification No. 150368 / K13014 (classified minor) and is covered by aircraft Service Bulletin No. A320-25- 1649.
Under no circumstances s hall the modified equipment, resulting from the application of this Serv ice Bulletin, be installed on the aircraft type unless the corresponding modification, and if appl icable, its aircraft Service Bulletin are approved. L. Other Publications Affected Component Maintenance Manual 25-60- 58 will require a revision to incorporate this Service Bulletin. M. Interchangeability of Parts Refer to Airbus S.B. Ref. 25-1649. N. Family Tree Charts of Modification Relationships - None Air Cruisers Company Service Bull etins 004-25-42 (“Enclosure Door Modification”) and 004-25-48 (“Improved Lacing Cover and Aspirator”) must be incorporated prior to performing the modification and re-identification instructions contained herein.
2. Accomplishment Instructions **NOTE** : System is considered unpacked as part of regularly scheduled maintenance. **NOTE** : Inspect the specified area of the enclosure. If an aluminum extrusion “lip” exits in this areathat is equal to or greater than 0.0625 inches (1.6 mm) (above the inner surfac e of the enclosure). follow the instructions below for adding an epoxy transition in this area. If a “lip” does not exist, or it is less than 0.0625 inches(1.6 mm), reidentify the enclosure and return to serv ice per the instructions below. A. Thoroughly clean area of enclosure where transition will be added (see Figures 1 and 2) using a clean cloth dampened in acetone solvent.S.B. A320 004-25-84 Page 4 of 6 ISSUE DATE: 05 Feb 2010 Revision No 4, 09 Nov 2012 

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B. Lightly sand same area using medi um-grit sandpaper to roughen the surface. C. Re-clean area to remove sanding residue using a clean cloth dampened in acetone solvent.
**CAUTION:** FOLLOW EPOXY MANUFACTURER’S INSTRUCTIONS REGARDING SAFETY A ND USAGE OF PRODUCT. D. Cut approximately 1.0 In . (25.4 mm) section of re pair epoxy/putty and knead to a consistent color per ma nufacturer’s instructions. E. Form a transition by molding epoxy/putty to geometry shown in Figure 2, Section A-A. Use of a non- stick spatula, dampened with water, will aid in the formation of the transition. F. Obliterate the Air Cruisers Com pany/Aerazur system part number stenciled on the underside of the enclo sure assembly with blac k indelible ink. Mark the appropriate new system part number per Table 1 and add “Modified/inspected per S.B. A320 004-25- 84” adjacent to the dash number. G. Obliterate the Air Cruisers Comp any/Aerazur enclosure part number stenciled on the inside of the enclosure asse mbly with black indelible ink. Mark the appropriate new enclosure part number per Table 1 and add “Modified/inspected per S.B. A320 004-25- 84” adjacent to the dash number.

OLD SYSTEM OLD ENCLOSURE CMM FOLDING PROCEDURE NEW SYSTEM NEW ENCLOSURE

D31865-109 D36179-107 25-60-58 P-11907 D31865-309 D36179-307

D31865-110 D36179-108 25-60-58 P-11907 D31865-310 D36179-308

D31865-209 D36179-207 25-60-58 P-11907 D31865-311 D36179-407

D31865-210 D36179-208 25-60-58 P-11907 D31865-312 D36179-408

**TABLE 1**S.B. A320 004-25-84 Page 5 of 6 ISSUE DATE: 05 Feb 2010 Revision No 4, 09 Nov 2012 

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**OFFWING RAMP/SLIDE ENCLOSURE FIGURE 1**  **ENCLOSURE A** 
**A**S.B. A320 004-25-84 Page 6 of 6 ISSUE DATE: 05 Feb 2010 Revision No 4, 09 Nov 2012 

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**TRANSITION AREA FIGURE 2**  **0.75 In. (19.1 mm)** 

**4.0-4.25 In. (101.6-107.9 mm)**  **1.00-1.25 In. (25.4-31.8 mm)**  **INSIDE EDGE OF ENCLOSURE**  **TOP SURFACE**
**LIP TRANSITION** 

**VIEW A-A**

**TOP SURFACE**
**LIP**

**TRANSITION DOOR SEAL** 

**SECTION A-A A** 

**A DOOR SEAL** 

**IF “H” IS LESS THAN 0.0625 IN. (1.6 MM) ONLY IDENTIFY**  **THE ENCLOSURE. IF “H” IS EQUAL TO OR**  **GREATER THAN 0.0625 IN. (1.6MM) ADD EPOXY**  **TRANSITION AND REIDENTIFY THE**  **ENCLOSURE. H**