Engenharia PAGE 1 Airbus A320-214 Tail: PR-AVR MSN: 4941 FH: 6006,00 FC: 4002,00 Our Reference: MS/ST-0026-2013/00 Subject: SEVERAL DAMAGES ON THE UPR FUSELAGE SKIN Damage Location: Two damages lacated btw FR 21/22 and STGR 05/06 And Two damages located btw FR 21/23 and btw STRG 24/26 Next Flight Schedule: 10/Jul/2013 – 6AM Local Time MSN 5193 POST MOD 35812K10500 PAGE 1 Background Information: During Daily Check several damages were constated: DAMAGE 1: Abrasion plus Scratches area on the following position: At FR 21 common to STGR 06. DAMAGE 2: Abrasion plus Scratches area on the following position: Btw FR 21/22 and btw STGR 06/07. NOTE: The reason for this request is that the aircraft is POST MOD 35812K10500, resulting in a damage without predicted repair by SRM. NOTE: This allowable damage data is not applicable after Modification 35812K10500 for area defined between FR21 and FR24, and between STGR5 and STGR11 LH/RH (Refer. A320 SRM 53-11-11-101, paragraph 4.A.). DAMAGE 3: Dent on the Skin Fuselage btw FR 21/23 and btw STRG 25/26 DAMAGE 4: Dent on the Skin Fuselage common to Frame 23 and btw STRG 24/25. Engenharia

Damages location on the Upper Shell DAMAGE LOCATION PAGE 2 DAMAGE 1: Abrasion plus Scratches on the Skin fuselage at FR 21 common to STGR 06. DAMAGE 2: Abrasion plus Scratches on the Skin fuselage btw FR 21/22 and btw STGR 06/07. Damages location on the Upper Shell Airbus A320-214 Tail: PR-AVR MSN: 4941 STRG 6 A LAP JOINT FR 20 FR 21 Engenharia

ORIGINAL FASTENERS AFFECTED DAMAGE LOCATION PAGE 3 DAMAGE 1 DAMAGE 2 SKIN UPPER SHELL DOF STRG 6 ORIGINAL FASTENERS AFFECTED ASNA2051DEJ040** (2EA) LAP JOINT DET. A FR 21 Engenharia

MAPPING GRID 10X10mm (DAMAGE 1) DIMENSIONS OF DAMAGE PAGE 4 DAMAGE 1: The reworked area with Dimensions: Original Thickness max. = 2,0mm Remaning Thickness = 1,9mm Removed material = 0.1mm (Y) Original Thickness min. = 1,2mm Remaning Thickness min. = 1,1mm Lenght = 70mm Widht = 62mm (as per Blending/Rework Dimensions Y> = 40T). The affected area was reworked by Blend-out as per A320 SRM 51-73-00, paragraph 5. The affected area by scracth was inspected (DVI) and is free the marks and scratches. The Fasteners on affected area was removed as per A320 SRM 51-42-11. ROTATING PROBE TESTING Performed in the affected hole as per NTM 51-10-01-250-801-A-01 (Procedure A) PB 6 and NO DISCRAPANCY FOUND. EDDY CURRENT (HFEC Inspection) Performed around the holes as per NTM 51-10-08-250-802-A-01 (Procedure A) PB 6 and NO CRACK FOUND. Performed MEASUREMENT OF REMAINING STRUCTURE THICKNESS on skin fuselage as per NTM 51-10-04-270-802-A-01.   1 2 3 4 5 6 A 1,2 2,0 B 1,1 1,9 C D E F G MAPPING GRID 10X10mm (DAMAGE 1) Engenharia

MAPPING GRID 10X10mm (DAMAGE 2) DIMENSIONS OF DAMAGE PAGE 5 DAMAGE 2: The reworked area with Dimensions: Original Thickness min. = 1,2mm Remaning Thickness min. = 1,1mm Removed material = 0.1mm (Y) Lenght = 50mm Widht = 33mm (as per Blending/Rework Dimensions Y> = 40T). The affected area was reworked by Blend-out as per A320 SRM 51-73-00, paragraph 5. The affected area by scracth was inspected (DVI) and is free the marks and scratches. ROTATING PROBE TESTING Performed in the affected hole as per NTM 51-10-01-250-801-A-01 (Procedure A) PB 6 and NO DISCRAPANCY FOUND. EDDY CURRENT (HFEC Inspection) Performed around the holes as per NTM 51-10-08-250-802-A-01 (Procedure A) PB 6 and NO CRACK FOUND. Performed MEASUREMENT OF REMAINING STRUCTURE THICKNESS on skin fuselage as per NTM 51-10-04-270-802-A-01.   1 2 3 4 5 6 A 1,2 1,1 B C D MAPPING GRID 10X10mm (DAMAGE 2) Engenharia

Engenharia REPAIR PROPOSAL PAGE 6 CURRENT SITUATION: NOTE: The reason for this request is that the aircraft is POST MOD 35812K10500, resulting in a damage without predicted repair by SRM. CURRENT SITUATION: Performed Blend-out on the affected area with material removed: For Original thickness = 2.0mm _Remaining thickness= 1,9mm (Depth of Rework as Percentage of Nominal Material Thickness = 5,0%) For Original thickness = 1,2mm _Remaining thickness= 1,1mm (Depth of Rework as Percentage of Nominal Material Thickness = 8,3%) Removed the two Original fasteners ASNA2051DEJ040** (2 EA). Performed ROTATING PROBE TESTING in the affected hole as per NTM 51-10-01-250-801-A-01 (Procedure A) PB 6 and NO DISCRAPANCY FOUND. Performed EDDY CURRENT (HFEC Inspection) around the holes as per NTM 51-10-08-250-802-A-01 (Procedure A) PB 6 and NO CRACK FOUND. Performed MEASUREMENT OF REMAINING STRUCTURE THICKNESS on skin fuselage as per NTM 51-10-04-270-802-A-01. REPAIR PROPOSAL (DAMAGE 1 AND DAMAGE 2): Perform surface protection of the repair area I.A.W. A320 SRM 51-21-11 and SRM 51-23-11. Perform wet assembly of the fasteners repair I.A.W. A320 SRM 51-24-00. Perform installation of 2 new fasteners HL11VF6-3 (2EA) + HL70-6 as per A320 SRM 51-42-00 Perform restored surface protection in accordance with A320 SRM 51-75-12. NOTE: This propose was based on the RDAS AIRTAC Ref. 70577657/033/2013 and 70577895/033/2013 and 70577895/033/2013 and 70579490/003/2013 of a same damage in the same location that occurred recently in the aircraft MSN 3509, 5193, 4942 and 4941. Engenharia

Damages location on the Rear Side Shell DAMAGE LOCATION PAGE 7 DAMAGE 3: Dent on the Skin Fuselage btw FR 21/23 and btw STRG 25/26 DAMAGE 4: Dent on the Skin Fuselage common to Frame 23 and btw STRG 24/25. Airbus A320-214 Tail: PR-AVR MSN: 4941 Damages location on the Rear Side Shell Engenharia

Dented area location on the Rear Side Shell DAMAGE LOCATION PAGE 8 DOF Dented area location on the Rear Side Shell DAMAGE 4 STRG 24 STRG 25 A DAMAGE 3 FR 23 Engenharia

Two Fasteners affected DIMENSIONS OF DAMAGE PAGE 9 DAMAGE 4: A = 0mm B = 0mm L = 100mm W = 50mm D = 2,80mm T= 1,40mm DAMAGE 4 NOTE: The Dented area is common to Skin and Frame and two fasteners affected. Two Fasteners affected DAMAGE 3: A = 7mm B = 10mm L = 60mm W = 60mm D = 1,0mm T= 1,40mm DAMAGE 3 DET. A View from outside Engenharia

Engenharia DAMAGE REPORT DAMAGE 4 DAMAGE 3 PAGE 10 View from inside STRG 25 DAMAGE 4 DAMAGE 3 Performed HFEC on the affected surface of the Frame in accordance with NTM 51-10-08-250-802-A-01 (Procedure A) PB 6 and NO CRACK FOUND. Performed DV inspection on the affected fasteners and NO DISCRAPANCY FOUND. Engenharia

Engenharia DAMAGE REPORT PAGE 11 CURRENT SITUATION: The Dented area caused by impact was inspected (DVI) and adjacent structural no discrepancy found. DAMAGE 3: The Dented area with Dimensions: A = 7mm, B = 10mm, L = 60mm, W = 60mm, D = 1,0mm (Measured from outside) and original Thickness = 1,4mm was assessed as per A320 SRM 53-11-11-101, Paragraph 4.C (Dents out of “nearness/form” Criterion), Diagram 103 and classified as Repair Category “C” Diamond <1> and <3> and must be applied the permanent repair within 3000FC. DAMAGE 4: The Dented area with Dimensions: A = 0mm, B = 0mm, L = 100mm, W = 50mm, D = 2,80mm (Measured from outside) and original Thickness = 1,4mm was assessed as per A320 SRM 53-11-11-101, Paragraph 4.C (Dents out of “nearness/form” Criterion), Diagram 103 and classified as Repair Category “C” Diamond <1> and <3> and must be applied the permanent repair within 3000FC. NOTE: The Dented area is common to Skin and Frame and two fasteners affected. Performed HFEC (internally and externally) on the Skin affected surface in accordance with NTM 51-10-08-250-802-A-01 (Procedure A) PB 6 and NO CRACK FOUND. Performed HFEC on the affected surface of the Frame in accordance with NTM 51-10-08-250-802-A-01 (Procedure A) PB 6 and NO CRACK FOUND. Engenharia

Engenharia REPAIR PROPOSAL PAGE 12 REPAIR PROPOSAL (DAMAGE 3 AND DAMAGE 4): Perform surface protection of the repair area I.A.W. A320 SRM 51-21-11 and SRM 51-23-11. Perform restored surface protection in accordance with A320 SRM 51-75-12. Could the AIB consider the already performed repair as a temporary repair until next C check, that will occur in no more than 6000 FC or 24 months? NOTE: A response within 4 hours is required one time it is an AOG situation. If the temporary repair is considered acceptable, could the AIB provide us the RDAS Number in advanced? Our New Reference for issue the RDAS: MS/ST-0026-2013/00. Engenharia

Engenharia CLARIFICATION PAGE 13 Our new Reference: MS/ST-0026-2013/01 Your reference: 70579891/005 In response to message ref. 70579891/005: AIRBUS request: 1. Please could AVA confirm the Aircraft type & MSN in question? It is noted on the damage report it quotes A320 while within the applied actions it refers to SRM A318. 2. Damages 3 & 4 are shown in relation to AOA Sensor. Has the SRM 53-00-11 been consulted ( Aerodynamic Requirements for Allowable Damage Angle of Attack Probes ) ONE answer: 1. The AVA confirms the serial (MSN: 4941) and type of aircraft (A320-214) and made ​​the necessary corrections regarding current actions on page 11. 2. For 3 damage & 4 were checked the definition of areas (Angle of Attack Sensors - Definition of Areas) according to Figure 106 and this out area of the Angle of Attack sensor center (450mm > 250 = R9) and were checked defining characteristic parameters Damage and Repair and Aerodynamic Requirements and are within the Requirements for allowable damages and repairs (D= 2,8mm > 2,5 (contact Airbus) and d = 450mm > 250mm (Double repair)). NOTE: External Doubler is permited for damaged area. If the temporary repair is considered acceptable, could the AIB provide us the RDAS Number in advanced? Our New Reference for issue the RDAS: MS/ST-0026-2013/01. Engenharia

Engenharia REPAIR FEEDBACK PAGE 14 Our new Reference: MS/ST-0026-2013/01 and MS/ST-0026-2013/02 Your reference: 70579891/005, 70579891/008 and 70579891/011 In response to message ref. 70579891/008 and 70579891/011: AIRBUS request: Additional HFEC inspection (NTM 51-10-08) of STGR25 close to both damages. Replacement of the two fasteners in dent damage 4 if damaged. ONE answer: Performed HFEC on the affected surface, cleat FR23 and STRG25 in accordance with NTM 51-10-08-250-802-A-01 PB 6 and NO CRACK FOUND. Removed two (2EA) fasteners on affected area as per A320 SRM 51-42-11. Enlarged the holes to their final diameter (3/16”) as per A320 SRM 51-44-12. Performed the countersink the fastener holes Chapter 51−44−11. Perform a detailed visual inspection (DVI) on the internal and external surface and on the cleat frame and NO DISCREPANCY FOUND. Performed rototest inspection in holes as per A320 NTM 51-10-01 and NO CRACK FOUND. Perform surface protection in c´sink and holes I.A.W. A320 SRM 51-21-11 and SRM 51-23-11. Performed wet assembly of the fasteners I.A.W. A320 SRM 51-24-00. Performed installation of the fasteners I.A.W. A320 SRM 51-42-00. Performed restored surface protection in accordance with SRM 51-75-12. NOTE: Could the AIB provide us a Permanent Repair Design from Airbus, to be accomplished within 3000FC? If the temporary repair is considered acceptable, could the AIB provide us the RDAS Number in advanced? Our New Reference for issue the RDAS: MS/ST-0026-2013/02. Engenharia