ENGINEERING ORDER N° IM-A319/A320-53/1493 - Apsyswebapp.ifrskeyes.com/GED/AMSFSKUPRD/(1493)...

ENGINEERING ORDER N° IM-A319/A320-53/1493

Engineering Management Pudahuel, Santiago, Chile

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Form 145-38 Rev 0

PART LIST

ITEM QTY PART NUMBER DESCRIPTION REMARKS

KIT 531287A01R02

2 31 ASNA2049DXJ4019 RIVET

3 4 ASNA2001V3-4 SCREW

4 6 NAS1169-10 WASHER

5 2 NAS1102E3-6 SCREW

CONSUMABLE PART LIST


1 AR Primer Epoxy Paint-- Corrosion Inhibiting Structure

Material No. 04DAB2

2 AR Coating-- Flexible Structure Material No. 04QAB2

3 AR Polysulfide Sealant-General Purpose Brushable

Material No. 06AAA1

4 AR Polysulfide Sealant-Low Density Multi-Purpose Interior

Material No. 06ACC1

5 AR Non Aqueous Cleaner-General Material No. 08BAA9

6 AR Surface Pretreatment-Light Alloys Chemical Conversion

Material No. 10ABC1

7 AR Textile-Lint Free Cotton Material No. 14SBA1

For the specification of materials (Material No.) given in this E.O., refer to Airbus Consumable Materials List Manual (CML).

TOOL LIST


NO REQUIRED



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Form 145-38 Rev 0

REVISION RECORD

N° REVISION ITEM DESCRIPTION DATE

0

ALL

ORIGINAL RELEASE

January 20, 2015 (LG)



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Form 145-38 Rev 0

Effective date of AD: December, 19-2014

Repetitive interval (whichever occurs first) : 12.000FC / 24.000FH

Table 2 - Applicability This E.O. is applicable to:



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Form 145-38 Rev 0

Table 3 – Specific Sky fleet Applicability This E.O. is applicable to following Sky aircrafts:

CC-ADO 0447 CC-ABV 1400 CC-ABW 1523 CC-AHC 2119 CC-AFY 2129 CC-AIY 2214 CC-AJF 2249 CC-AFZ 2251 CC-AFX 2283 CC-AIB 2378 CC-AIC 2380 CC-AID 2436 CC-AHD 2460 CC-AHE 2548 CC-AJG 3331 CC-AMP 3171

Terminating Action Modification of an airplane in accordance with the instructions of Airbus SB A320-53-1281 constitutes terminating action for the repetitive inspections as required by this E.O. for that airplane.



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WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00. NOTE: The accomplishment instructions of this E.O. refer to procedures included in AIRBUS documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the AIRBUS document must be used. NOTE: The access and close-up instructions, not comprising return to service tests, in this E.O. do not constitute or affect the technical intent of the E.O. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical intent of the E.O. is met within the set parameters. NOTE: The purpose of flow charts is to supplement the information given in the Procedure and Compliance paragraphs and not to serve as the primary source for tasks or compliance times given in this E.O.



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Form 145-38 Rev 0

TASK DESCRIPTION MEC LICENSE

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Task 531287-832-801-001 - Inspection of external fuselage skin panel at FR34.

Subtask 531287-910-001-001 - Standard Practices

For the specification of materials (Mat. No.) given in this E.O., refer to Consumable Materials List (CML). If the length of any fastener specified in this Service Bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. For the identification of Zones, refer to AMM 06-20-00, Page Block 001. To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-001. Remove and install fasteners in accordance with SRM 51-42-00. Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00. If alternative and substitute fasteners have to be used, you must make sure that the associated nut/collar are compatible in accordance with SRM 51-40-00 "Mating Part" column. Apply sealant in accordance with SRM 51-24-00. Renew the protective finish in accordance with SRM 51-75-12. For electrical bonding, refer to ESPM 20-51-20 and AMM Task 20-28-00-912-001.



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Subtask 531287-941-001-001- Job Set-up

The following items shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear). - Engine shut down, thrust reversers closed and locked. - Aircraft in clean configuration. - Parking brake applied. - Aircraft electrical network de-energized. - Hydraulic systems depressurized. - Access to the cockpit and cabin is available. - All circuit breakers are in closed position. - All controls in NORM, AUTO or OFF position.

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A. Make sure that the aircraft is electrically grounded. Refer to AMM 12-34-24-869-

002.

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B. Put an access platform in position at zone 190 and zone 825.

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C. Open the FWD cargo compartment door 825AR; refer to AMM Task 52-30-00-

860-001.

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D. Remove the access panel 191BB; refer to AMM Task 53-35-13-000-002.

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E. Remove the Cargo-Compartment floor panel(s) at Frame 34 to get access to the

fuselage, refer to AMM Task 53-22-14-000-001.

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Subtask 531287-010-001-001 - Remove the Belly Fairing Panel at FR34 for access.

CAUTION: DO NOT USE A METAL SCRAPER TO REMOVE THE UNWANTED MATERIAL. A METAL SCRAPER CAN CAUSE DAMAGE TO THE SURFACE OF THE COMPONENT

A. Remove the belly fairing panel Item (1) at Frame 34 In accordance with SRM 51-

42-00. Refer to Fig. A-FCAAA. If necessary, use a non-metallic spatula to remove the sealant and clean the areas with: Non Aqueous Cleaner-General 08BAA9 Textile-Lint Free Cotton 14SBA1 Get access to the work area. Refer to Fig. A-FCAAA Sheet 01. Remove: 1 Skin panel Item (1) Retain 31 Rivet Item (2) Discard 4 Screw Item (3) Discard 6 Washer Item (4) Discard 2 Screw Item (5) Discard

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Subtask 531287-832-001-001 - Do a Detailed Inspection of the External Fuselage Skin Panel at FR34, between STGR 43 LH and RH Sides.

A. Do a detailed inspection of the external fuselage skin panel at Frame 34 between

Stringer 43 LH and RH sides. Check if there are chafing marks on fuselage skin panel at inspection area. Refer to Fig. A-FFAAA and Fig. A-FBAAA. Chafing marks are found? YES NO If no chafing marks are found go to SUBTASK 531287-410-001 001. If chafing marks are found, before further flights, rework the Fuselage Skin Panel per SUBTASK 531287-833-003 001 and do a Special Detailed Inspection of External Fuselage Skin Panel for crack per SUBTASK 531287-832-002 001.

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Subtask 531287-833-003-001 - Rework the Fuselage Skin Panel (Depending on Inspection result)

A. Rework damage of the fuselage skin panel in accordance with SRM 53-21-11.

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Subtask 531287-832-002-001 - Do a Special Detailed Inspection of External Fuselage Skin Panel for crack. (Only if rework was done)

A. Do a special detailed inspection for crack as per NTM 51-10-08. Refer to Fig. A-

FFAAA and Fig. A-FBAAA. Check if there is crack on fuselage skin panel at rework location. CRACK WAS FOUND? YES NO

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a) If crack is found:

<1> Do the measurement of crack length as per NTM 51-10-08, and remaining thickness as per NTM 51-10-04. <2> Contact Engineering Department for further instruction.

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b) If no crack is found:

<1> Do the measurement of remaining thickness as per NTM 51-10-04.

Is the remaining thickness out of SRM 53-21-11 limits?

YES NO

If the remaining thickness is out of SRM 53-21-11 limits contact Engineering Department for further instruction.

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c) If the remaining thickness is within of SRM 53-21-11:

[1] Re-protect the reworked area in accordance with SRM 51-75-12.

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[2] Renew the protective finish of the fuselage per SRM 51-75-12.

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[3] Do SUBTASK 531287-410-001 001 Install the Belly Fairing Panel at FR34, removed for access.

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Subtask 531287-410-001-001 - Install the Belly Fairing Panel at FR34 removed for access

A. Install the belly fairing panel Item (1) at Frame 34 in accordance with SRM 51-42-00 and 51-43-00. Refer to Fig. A-FCAAA. Install the following: 1 Skin panel Item (1) Retained at removal 4 Screw ASNA2001V3-4 Item 3 6 Washer NAS1169-10 Item 4 2 Screw NAS1102E3-6 Item 5 31 Rivet ASNA2049DXJ4019 Item 2

NOTE: Wet Install the Countersunk Rivets Item 2 with Polysulfide Sealant- General Purpose Brushable, Material N° 06AAA1.

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B. Apply a bead of sealant around the mating surface of the parts installed and to

the interface with the structure in accordance with SRM 51-24-00. Use a Polysulfide Sealant-Low Density Multi-Purpose Interior, Material N° 06ACC1

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C. Renew the protective finish in accordance with SRM 51-75-12. Use Surface

Pretreatment-Light Alloys Chemical Conversion, Material N° 10ABC1

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B. Restore the paint scheme in accordance with SRM 51-75-12. Use Primer Epoxy

Paint- - Corrosion Inhibiting Structure, Material N° 04DAB2 and Coating-- Flexible Structure, Material N° 04QAB2.

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C. Apply special protection in accordance with SRM 51-23-12.

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Subtask 531287-942-001-001 - Close-up

A. Make sure that the work areas are clean and clear of tools and other items of

equipment.

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B. Install the Cargo-Compartment floor panel(s) removed for access, refer to AMM

Task 53-22-14-400-001.

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C. Install the access panel 191BB; refer to AMM Task 53-35-13-400-002.

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D. Close the FWD cargo compartment door 825; refer to AMM Task 52-30-00-860-

002.

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E. Remove the access platform(s).

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F. Restore the systems and the aircraft to normal operating condition.

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G. Fill the Inspection Report and send to Engineering Department.

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Deviation Record Sheet Paragraph Observation Action Authorized by Performed by



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DISCREPANCY FOUND PARAGRAPH CORRECTIVE ACTION DETAIL MEC LICENSE

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ENGINEERING ORDER N° IM-A319/A320-53/1493 - Apsyswebapp.ifrskeyes.com/GED/AMSFSKUPRD/(1493)...

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Transcript of ENGINEERING ORDER N° IM-A319/A320-53/1493 - Apsyswebapp.ifrskeyes.com/GED/AMSFSKUPRD/(1493)...