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 004-25-84 now in your possession, 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 2012

S.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 OFFWING 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 field reports of the ramp/slide system’s aspirator 

becoming lodged against an extrusion “lip” of the off wing enclosure during 

the initial stages of the deployment sequence, tearing the aspirator blister, 

and potentially rendering the slide unusable. To address this issue, this 

Service Bulletin will outline instructions for the addition of an epoxy 

transition, adjacent to the enclosure extrusion in the area where the 

aspirator is stowed.

Due to manufacturing variation, some enclosures do not have this “lip” or it 

is of insignificant height. An epoxy transition is not necessary in these 

cases. 

C. Compliance

This service bulletin is covered by Airbus Service Bulletin A320-25-1649 

that has been rendered mandatory by EASA AD 2010-0210 and FAA AD 

2012-18-12.
S.B. A320 004-25-84

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ISSUE DATE: 05 Feb 2010

Revision No 4, 09 Nov 2012

SERVICE BULLETIN

D. Description

NOTE: Only those organizations authorized by the FAA or other 

airworthiness authorities are permitted to perform this modification.

Inspect the specified area of the enclosure. If an aluminum extrusion “lip” 

exists in this area that is equal to or greater than 0.0625 inches (1.6 mm) 

(above the inner surface of the enclosure), follow the instructions below for 

adding an epoxy transition in the area. If a “lip” does not exist, or it is less 

than 0.0625 inches (1.6 mm), reidentify the enclosure and return to service. 

Clean and sand specific area of enclosure. Prepare repair epoxy/putty per 

manufacturer’s instructions and apply to cleaned area of enclosure, forming 

a molded transition. Re-identify enclosure and return to service.

E. Approval

Certification, TSO-C69b 

(1). FAA Acknowledegment - This Service Bulletin contains modification 

information which has been submitted to the FAA under the TSOC69b authorization for the affected articles.

(2). The technical content of this document is approved under the 

authority of the DOA No. EASA.21J.031.

F. Labor Hours

It will take approximately 0.25 hour per system to accomplish the 

instructions outlined in this Service Bulletin not including cure time of the 

epoxy. 

G. Material - Cost and Availability 

Acetone Solvent (CH3COCH3) - Commercially Available

Sandpaper (Medium Grit) - Commercially Available

Fixmaster Underwater Repair 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

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ISSUE DATE: 05 Feb 2010

Revision No 4, 09 Nov 2012

SERVICE BULLETIN

I. Weight and Balance - None

J. Electrical Load Data - Not affected

K. References 

Engineering Change Notices (ECNs) MC17,839 and MC17,873. 

This Service Bulletin is subject to Aircraft Modification No. 150368 / K13014 

(classified minor) and is covered by aircraft Service Bulletin No. A320-25-

1649.

Under no circumstances shall the modified equipment, resulting from the 

application of this Service Bulletin, be installed on the aircraft type unless 

the corresponding modification, and if applicable, 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 Bulletins 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 area that is equal to or greater than 0.0625 inches 

(1.6 mm) (above the inner surface 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 service 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

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ISSUE DATE: 05 Feb 2010

Revision No 4, 09 Nov 2012

SERVICE BULLETIN

B. Lightly sand same area using medium-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 AND USAGE OF PRODUCT.

D. Cut approximately 1.0 In. (25.4 mm) section of repair epoxy/putty and knead 

to a consistent color per manufacturer’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 Company/Aerazur system part number stenciled 

on the underside of the enclosure assembly with black 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 Company/Aerazur enclosure part number stenciled on the inside of the enclosure assembly 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

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ISSUE DATE: 05 Feb 2010

Revision No 4, 09 Nov 2012

SERVICE BULLETIN

OFFWING RAMP/SLIDE ENCLOSURE

FIGURE 1

ENCLOSURE

A

A
S.B. A320 004-25-84

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ISSUE DATE: 05 Feb 2010

Revision No 4, 09 Nov 2012

SERVICE BULLETIN

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