WINGS - SPAR II - INSPECTION FOR FUEL TANK LEAKAGE
1. PLANNING INFORMATION A. SB EFFECTIVITY Aircraft affected: MODEL SN Embraer 170( ) and 175( ) All aircraft in operation that have reached 12,000 flight cycles. In-production effectivity: The subject presented in this bulletin does not affect any in-production aircraft. B. CONCURRENT REQUIREMENTS None C. REASON (1) HISTORY Two instances of fuel seepage at the Left-Hand (LH) wing and close to the Rib 10 area from two different aircraft, have been reported to Embraer, during a daily routine inspection. This seepage was caused by a crack at the LH wing spar II, in the fuel tank and close to the same Rib 10 area. Embraer has been informed that some other aircraft, in the field, with the same range of flight cycles have no evidence of fuel tank leakage or seepage. (2) OBJECTIVE To provide the instructions for doing a General Visual Inspection (GVI) for leakage on the Left-Hand (LH) and Right-Hand (RH) wings and a Detailed Inspection (DI) / Special Detailed Inspection (SDI) for cracks on spar II of the Left-Hand (LH) and Right-Hand (RH) wings. 

# SERVICE BULLETIN ALERT

ALERT DATE: 13/Feb/2012 REVISION No.: SB No.: 170-57-A053 PAGE: 1 of 20 Copyright © 2012 by Embraer S.A. All rights reserved.(3) EXPECTED BENEFITS The purpose this bulletin is aimed at detecting the possibility of fuel leakage and crack on spar II of the Left-Hand (LH) and Right-Hand (RH) wings. (4) REVISION HISTORY None. D. DESCRIPTION This Bulletin is divided into 5 PARTS, as follows:
PART I VISUAL INSPECTION FOR LEAKAGE ON THE LH AND RH WINGS Applicable to: Refer to 1.A. SB EFFECTIVITY PART I of this bulletin presents a General Visual Inspection (GVI) for leakage on the Left-Hand (LH) and Right-Hand (RH) wings.
PART II DETAILED INSPECTION FOR CRACKS ON SPAR II OF THE LH WING Applicable to: Refer to 1.A. SB EFFECTIVITY PART II of this bulletin presents a Detailed Inspection (DI) for cracks on spar II, spar cap third and the main box lower skin of the Left-Hand (LH) wing. To do this, it is necessary to open access panel 522AB.
PART III DETAILED INSPECTION FOR CRACKS ON SPAR II OF THE RH WING Applicable to: Refer to 1.A. SB EFFECTIVITY PART III of this bulletin presents a Detailed Inspection (DI) for cracks on spar II, spar cap third and the main box lower skin of the Right-Hand (RH) wing. To do this, it is necessary to open access panel 622AB.

PART IV SPECIAL DETAILED INSPECTION FOR CRACKS ON SPAR II OF THE LH WING Applicable to: Refer to 1.A. SB EFFECTIVITY PART IV of this bulletin presents a Special Detailed Inspection (SDI) for cracks on spar II of the Left-Hand (LH) wing using the Eddy Current inspection. 

# SERVICE BULLETIN ALERT

ALERT SB No.: 170-57-A053 PAGE: 2 DATE: 13/Feb/2012 REVISION No.: Copyright © 2012 by Embraer S.A. All rights reserved.To do this, it is necessary to defuel the aircraft fuel tanks.

PART V SPECIAL DETAILED INSPECTION FOR CRACKS ON SPAR II OF THE RH WING Applicable to: Refer to 1.A. SB EFFECTIVITY PART V of this bulletin presents a Special Detailed Inspection (SDI) for cracks on spar II of the Right-Hand (RH) wing using the Eddy Current inspection. To do this, it is necessary to defuel the aircraft fuel tanks. E. COMPLIANCE (1) Applicable to PART I (a) For aircraft that have reached between 12,000 and 13,925 flight cycles, the incorporation of PART I of this service bulletin is recommended within the next 150 Flight Cycle(s) or before the aircraft have reached 14,075 Flight Cycle(s), whichever occurs first. (b) For aircraft that have reached more than 13,925 flight cycles, the incorporation of PART I of this service bulletin is recommended within the next 75 Flight Cycle(s) or before the aircraft have reached 14,075 Flight Cycle(s), whichever occurs later. (c) If no sign of leakage is found, no immediate action is required. The inspection according to PART II and/or PART III is recommended within the next 450 Flight Cycle(s) and must be repeated every 450 Flight Cycle(s). If any sign of leakage is found, the repetitive inspection according to PART II and/or PART III is recommended every 50 Flight Cycle(s) until the accomplishment of PART IV and/or PART V. PART IV and/or PART V is recommended to be accomplished no later than 150 Flight Cycle(s). (2) Applicable to PART II and PART III (a) Incorporation of PART II and/or PART III of this service bulletin must be repeated 

# SERVICE BULLETIN ALERT

ALERT DATE: 13/Feb/2012 REVISION No.: SB No.: 170-57-A053 PAGE: 3 Copyright © 2012 by Embraer S.A. All rights reserved.every 450 Flight Cycle(s) after the accomplishment of PART I, if no sign of leakage is found. (b) Incorporation of PART II and/or PART III of this service bulletin is recommended immediately after the accomplishment of PART I, if any sign of leakage is found. This inspection must be repeated every 50 Flight Cycle(s) until the accomplishment of PART IV and/or PART V of this service bulletin, if no crack is detected. (3) Applicable to PART IV and V Incorporation of PART IV and/or PART V of this service bulletin is recommended within the next 150 Flight Cycle(s) after the accomplishment of PART I, if any sign of leakage is found. F. APPROVAL The technical aspects of this Service Bulletin are approved by: Embraer - Engineering Board. G. COMMUNICATIONS TO EMBRAER EMBRAER requests that any results found during these inspections be informed to your local EMBRAER representatives or offices. H. REFERENCES AMM 170/( ) Aircraft Maintenance Manual PART II - 06-44-00 - DIMENSIONS AND AREAS. AMM 170/( ) Aircraft Maintenance Manual PART II - 12-11-01 and 12-11-05 - SERVICING. AMM 170/( ) Aircraft Maintenance Manual PART II - 20-00-00 - STANDARD PRACTICES-AIRFRAME. AMM 170/( ) Aircraft Maintenance Manual PART II - 28-11-00 - FUEL. 

# SERVICE BULLETIN ALERT

ALERT SB No.: 170-57-A053 PAGE: 4 DATE: 13/Feb/2012 REVISION No.: Copyright © 2012 by Embraer S.A. All rights reserved.SRM 170/( ) Structural Repair Manual Part II - 51-21-07 - STANDARD PRACTICES AND STRUCTURES. SRM 170/( ) Structural Repair Manual Part II - 57-01-00 - WINGS. I. OTHER PUBLICATIONS AFFECTED None. 

# SERVICE BULLETIN ALERT

ALERT DATE: 13/Feb/2012 REVISION No.: SB No.: 170-57-A053 PAGE: 5 Copyright © 2012 by Embraer S.A. All rights reserved.2. MATERIAL INFORMATION A. MATERIAL - PRICE AND AVAILABILITY The necessary expendable or consumable parts given in the AMM Tasks referred to in this bulletin should be procured from the operator’s inventories or ordered as spares. B. TOOLING - PRICE AND AVAILABILITY (1) The tooling presented below, required to perform the Eddy Current inspection according to PART IV and PART V of this bulletin, should be procured directly from the manufacturer, as indicated in the associated Note.
ITEM PN DESCRIPTION SUPPLIER Phasec Model 3D Flaw Detector - Eddy Current Hocking 206P4F Pencil Probe, Shielded Hocking 12 Way / Microdot Coaxil Cable GE Inspection Technologies 29A029 Reference standard GE Inspection Technologies NOTE: Equivalent components for eddy current inspection may be used, provided they satisfy the sensitivity and resolution requirements prescribed by the procedure. (2) Whenever required, the necessary tooling presented in the AMM Tasks referred to in this bulletin, should be procured from the operator’s inventories or ordered as spares. 

# SERVICE BULLETIN ALERT

ALERT SB No.: 170-57-A053 PAGE: 6 DATE: 13/Feb/2012 REVISION No.: Copyright © 2012 by Embraer S.A. All rights reserved.3. ACCOMPLISHMENT INSTRUCTIONS NOTE: 1) For the purpose of this Service Bulletin, a General Visual Inspection (GVI) is: “A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of inspection is made from within touching distance, unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspectionarea. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked.” 2) For the purpose of this Service Bulletin, a Detailed Inspection (DI) is: “An intensive examination of a specific item, installation or assembly to detect damage, failure or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate access procedures may be required.” 3) For the purpose of this Service Bulletin, a Special Detailed Inspection (SDI) is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure or irregularity. The examination is likely to make extensive use of specialized Inspection Techniques and/or equipment. Intricate cleaning and substantial access or disassembly procedure may be required.” 4) Obey all of the WARNINGS and CAUTIONS included in the referenced manuals and procedures. 5) The Manuals and other documents are referred to by acronyms or using a simplified form. Refer to section 1.H. REFERENCES for a more complete definition. 6) This Service Bulletin effectivity is divided into 5 PARTS. The SB PARTS are featured to allow their independent accomplishment. The steps below outline the general accomplishment instructions. The detailed sequence is included in the respective figure, when necessary. A. Make sure that the aircraft is safe for maintenance. Refer to AMM TASK 20-00-00-910- 

# SERVICE BULLETIN ALERT

ALERT DATE: 13/Feb/2012 REVISION No.: SB No.: 170-57-A053 PAGE: 7 Copyright © 2012 by Embraer S.A. All rights reserved.801-A/200 - Aircraft Maintenance Safety Procedures - Standard Procedures. B. PART I - VISUAL INSPECTION FOR LEAKAGE ON THE LH AND RH WINGS (1) Perform a General Visual Inspection (GVI) for leakage in the Left-Hand (LH) and Right-Hand (RH) wings, close to the Rib 10 area. Refer to Figure 1

. – If no sign of leakage is found, no immediate action is required. The inspection according to PART II and/or PART III is recommended within the next 450 Flight Cycle(s) and must be repeated every 450 Flight Cycle(s). – If any sign of leakage is found, the inspection according to PART II and/or PART III is recommended immediately. This inspection must be repeated every 50 Flight Cycle(s) until the accomplishment of PART IV and/or PART V of this service bulletin, if no crack is detected. (2) Restore the aircraft to normal. (3) Enter the accomplishment of PART I of this bulletin in the applicable documents. C. PART II - DETAILED INSPECTION FOR CRACKS ON THE SPAR II OF THE LH WING (1) Remove and retain access panel 522AB. Refer to AMM TASK 06-44-00-800-801- A/100 - Wing Access Doors and Panels. (2) Perform a Detailed Inspection (DI) for cracks on spar II, spar capthird and main box lower skin of the Left-Hand (LH) wing, close to the Rib 10. Refer to Figure 2

. – If no crack is detected and no sign of leakage is found, repeat this Detailed Inspection (DI) every 450 Flight Cycle(s). – If no crack is detected and any sign of leakage is found, repeat this Detailed Inspection (DI) every 50 Flight Cycle(s), until the accomplishment of PART IV of this service bulletin. – If any crack is detected, contact Embraer for instructions to repair the damage. (3) Reinstall access panel 522AB. Refer to AMM TASK 06-44-00-800-801-A/100 - Wing Access Doors and Panels. (4) Restore the aircraft to normal. 

# SERVICE BULLETIN ALERT

ALERT SB No.: 170-57-A053 PAGE: 8 DATE: 13/Feb/2012 REVISION No.: Copyright © 2012 by Embraer S.A. All rights reserved.(5) Enter the accomplishment of PART II of this bulletin in the applicable documents. D. PART III - DETAILED INSPECTION FOR CRACKS ON THE SPAR II OF THE RH WING (1) Remove and retain access panel 622AB. Refer to AMM TASK 06-44-00-800-801- A/100 - Wing Access Doors and Panels. (2) Perform a Detailed Inspection (DI) for cracks on spar II, spar capthird and main box lower skin of the Right-Hand (RH) wing, close to the Rib 10. Refer to Figure 2

. – If no crack is detected and no sign of leakage is found, repeat this Detailed Inspection (DI) every 450 Flight Cycle(s). – If no crack is detected and any sign of leakage is found, repeat this Detailed Inspection (DI) every 50 Flight Cycle(s), until the accomplishment of PART IV of this service bulletin. – If any crack is detected, contact Embraer for instructions to repair the damage. (3) Reinstall access panel 622AB. Refer to AMM TASK 06-44-00-800-801-A/100 - Wing Access Doors and Panels. (4) Restore the aircraft to normal. (5) Enter the accomplishment of PART III of this bulletin in the applicable documents. E. PART IV - SPECIAL DETAILED INSPECTION FOR CRACKS ON THE SPAR II OF THE LH WING (1) Defuel the aircraft fuel tanks. Refer to AMM TASK 12-11-01-650-802-A/300 - Fuel Tank - Pressure Defueling. (2) Drain the remaining fuel. Refer to AMM TASK 12-11-05-680-801-A/300 - Fuel Tank - Water Draining. (3) Remove the fastener head sealing and the relevant sealant of the area to be inspect. Refer to SRM PART II 51-21-07/1 - SEALING REMOVAL. 

# SERVICE BULLETIN ALERT

ALERT DATE: 13/Feb/2012 REVISION No.: SB No.: 170-57-A053 PAGE: 9 Copyright © 2012 by Embraer S.A. All rights reserved.(4) Perform an Eddy-Current Inspection on the on spar II of the Left-Hand (LH) wing, close to the Rib 10 area, as per the instructions given in Figure 3 and Figure 4

. Observe the inspection results and proceed as follows: – If no crack is detected, repair the fuel tank sealing. Refer to SRM PART II 57-01-00/200-REPAIR 1P - Fuel Tank Sealing. – If any crack is detected, contact Embraer for instructions to repair the damage. (5) Do the defueled tank leak check. Refer to AMM TASK 28-11-00-790-802-A/500 - Wing Tank - Defueled Tank Leakage Check. (a) If leakage is detected, contact Embraer for further instructions. (6) Restore the aircraft to normal. (7) Enter the accomplishment of PART IV of this bulletin in the applicable documents. F. PART V - SPECIAL DETAILED INSPECTION FOR CRACKS ON THE SPAR II OF THE RH WING (1) Defuel the aircraft fuel tanks. Refer to AMM TASK 12-11-01-650-802-A/300 - Fuel Tank - Pressure Defueling. (2) Drain the remaining fuel. Refer to AMM TASK 12-11-05-680-801-A/300 - Fuel Tank - Water Draining. (3) Remove the fastener head sealing and the relevant sealant of the area to be inspect. Refer to SRM PART II 51-21-07/1 - SEALING REMOVAL. (4) Perform an Eddy-Current Inspection on the on spar II of the Right-Hand (RH) wing, close to the Rib 10 area, as per the instructions given in Figure 3 and Figure 4

. Observe the inspection results and proceed as follows: – If no crack is detected, repair the fuel tank sealing. Refer to SRM PART II 57-01-00/200-REPAIR 1P - Fuel Tank Sealing. – If any crack is detected, contact Embraer for instructions to repair the damage. 

# SERVICE BULLETIN ALERT

ALERT SB No.: 170-57-A053 PAGE: 10 DATE: 13/Feb/2012 REVISION No.: Copyright © 2012 by Embraer S.A. All rights reserved.(5) Do the defueled tank leak check. Refer to AMM TASK 28-11-00-790-802-A/500 - Wing Tank - Defueled Tank Leakage Check. (a) If leakage is detected, contact Embraer for further instructions. (6) Restore the aircraft to normal. (7) Enter the accomplishment of PART V of this bulletin in the applicable documents. NOTE: 1) Please inform us by e-mail fleet.monitoring@embraer.com.br of the aircraft manufacturer serial number and the SB incorporation date, specifying the SB Part(s) incorporated or whether the whole SB has been incorporated. This will enable Embraer to consider your aircraft configuration when providing future modifications. 2) To formally inform that the SB have been incorporated fleet-wide or that the SB will not be incorporated, so that Embraer can update the affected technical publications, use the “Service Bulletin Full-Fleet Incorporation Report” form, which is available on the Flyembraer portal (http://www.flyembraer.com). 3) Use the attached “Service Bulletin Evaluation” form to send us your comments regarding this SB. Your feedback will be much appreciated as an aid to help us improve the quality of the SBs. 

# SERVICE BULLETIN ALERT

ALERT DATE: 13/Feb/2012 REVISION No.: SB No.: 170-57-A053 PAGE: 11 Copyright © 2012 by Embraer S.A. All rights reserved.

### A TYPICAL ZONES

531 631 

### A B



### B SPAR II (REF.)

RIB 10 (REF.) AREA TO BE INSPECTEDEM170SB571326A.DGN 

# SERVICE BULLETIN ALERT

ALERT SB No.: 170-57-A053 PAGE: 12 DATE: 13/Feb/2012 REVISION No.: FIGURE 1 - VISUAL INSPECTION FOR LEAKAGE ON THE LH AND RH WINGS (SHEET 01 OF 01)

Copyright © 2012 by Embraer S.A. All rights reserved.ZONES 531 631 

### A 

### A TYPICAL SPAR II (REF.)

RIB 10 (REF.) 

### B



### B SPAR II (REF.) RIB 10 (REF.)

AREA TO BE INSPECTEDEM170SB571328A.DGN SPAR CAPTHIRD 

# SERVICE BULLETIN ALERT

ALERT DATE: 13/Feb/2012 REVISION No.: SB No.: 170-57-A053 PAGE: 13 FIGURE 2 - DETAILED INSPECTION FOR CRACKS ON SPAR II OF THE LH AND RH WINGS (SHEET 01 OF 01)

Copyright © 2012 by Embraer S.A. All rights reserved.ZONES 531 631 

### A



### A TYPICAL SPAR II (REF.)

RIB 10 (REF.) 

### B

SPAR II (REF.)

RIB 10 (REF.)



### B AREA TO BE INSPECTEDEM170SB571327A.DGN 

# SERVICE BULLETIN ALERT

ALERT SB No.: 170-57-A053 PAGE: 14 DATE: 13/Feb/2012 REVISION No.: FIGURE 3 - SPECIAL DETAILED INSPECTION FOR CRACKS ON SPAR II OF THE LH AND RH WINGS (SHEET 01 OF 01)

Copyright © 2012 by Embraer S.A. All rights reserved.NOTE: – Equivalent components for eddy current inspection may be used, provided they satisfy sensitivity and resolution requirements prescribed by the procedure. – The following calibration must be accomplished before any inspection, every time that the work is stopped for any reason, and before characterizing and sizing any defect signal. – The technician in charge of the accomplishment of this inspection must have at least a level - 2 qualification in Eddy-Current inspection, in accordance with MIL STD 410E of ATA specification 105, or other equivalent document that is approved by the operator’s local authority, demonstrated through a certificate issued by a certifying agency. 1. Calibrate the eddy-current equipment, according to the items below: (a) Visually verify if there is an obvious damage in the surface area that may affect the inspection (e.g. scratches, out-of-roundness, tooling marks). NOTE: Equipment standardization should be checked every haft hour during inspection and at the end of it. If anomalies are observed in the equipment operation or the equipment is out of its standardization, all parts tested after the last acceptable standardization should be reinspected, after the re-standardization has been accomplished. (b) Verify the Eddy Current Instrument and accessories (e.g. probe, probe cable, power cable and reference standard) for operation conditions, also check the Calibration Validity Date. (c) Connect the probe to the instrument. Power-on instrument and allow 5 minutes for warm-up or proceed according to the manufacturer’s instruction. (d) Adjust the frequency, gain, phase angle and other parameters as indicated below:
Probe: 206P4F Gain: 26.0/47.0 HP/LP: DC/100.0 Load uH: 22 Sweep: 0.2 s Phase: 161.6o Input Gain: High Drive: +8 dB Spot: 130/-30 XY Freq: 2 MHz Probe: Absolute Persist: 0.5 s Display: Spot (e) Position the probe on the reference standard in an area that does not have an artificial crack. Refer to Detail A. 

# SERVICE BULLETIN ALERT

ALERT DATE: 13/Feb/2012 REVISION No.: SB No.: 170-57-A053 PAGE: 15 FIGURE 4 - HIGH-FREQUENCY EDDY CURRENT INSPECTION (SHEET 01 OF 06)

Copyright © 2012 by Embraer S.A. All rights reserved.(f) Be sure that the probe is close as possible to 90 degrees to surface of the part. The probe must tightly fit but should not cause too much wear away of the probe coil. (g) Balance the instrument as shown in the manufacturer’s instructions. (h) Adjust the control of the phase rotation to obtain the sign lift-off in horizontal position. Refer to Detail B. (i) Slowly scan the probe above the reference standard adjustment: 1 The sensitivity through the gain controls of the instrument, permits to get the sign of the smallest artificial crack of 0.5 mm artificial crack depth (0.020 inch), at least 50% of amplitude of the scale. Refer to Detail C. 2 Controls the instruments as recommended per the manufacturer’s instruction. 2. Perform an eddy-current inspection of the surface as described below: NOTE: Before you scan an area of different geometry, calibrate the equipment. False indications can occur because of geometric variations, edge or hole margins, and presence of different materials near the scanning area. (a) Make sure that the surface in the inspection area is clean and free of conditions that could affect the test through false indication. (b) Place the pencil probe at the inspection area and press the Balance control button to set the signal dot to the display area. (c) Check the LIFT-OFF signal by moving the probe from fitting to air (away from the fitting area) and place it again at the same area. If the signal is similar to Detail B no other adjustment is necessary. (d) Be sure that the probe is as close as possible to 90 degrees to the surface of the part. (e) Balance the instrument as shown in the manufacturer’s instructions above surface at the inspection area. (f) Press the Balance button whenever the signal dot is out of the display area, but 

# SERVICE BULLETIN ALERT

ALERT SB No.: 170-57-A053 PAGE: 16 DATE: 13/Feb/2012 REVISION No.: FIGURE 4 - HIGH-FREQUENCY EDDY CURRENT INSPECTION (SHEET 02 OF 06)

Copyright © 2012 by Embraer S.A. All rights reserved.avoid changing other parameters such as gain, filters set and phase angle. (g) Scanning of an interest area should be made in two directions at least (longitudinal and transverse directions), with special attention to the edge effect. The scanning should be done the way the probe overlaps each step. 3. Evaluate the crack indications as described below: (a) All crack indication signal having an amplitude equal to or higher than simulations cracks of 0.2 mm of the reference standard must be considered a defect. (b) Take note of any location where the crack-like indication is found. (c) Repeat the inspection, paying particular attention to the areas where the indications have been noted. (d) Record all locations and responses to all crack indications. 

# SERVICE BULLETIN ALERT

ALERT DATE: 13/Feb/2012 REVISION No.: SB No.: 170-57-A053 PAGE: 17 FIGURE 4 - HIGH-FREQUENCY EDDY CURRENT INSPECTION (SHEET 03 OF 06)

Copyright © 2012 by Embraer S.A. All rights reserved.OK lift off lift off

ref ref

exec H F1 PROBE Absolute



### AEM170SB571329A.DGN 

# SERVICE BULLETIN ALERT

ALERT SB No.: 170-57-A053 PAGE: 18 DATE: 13/Feb/2012 REVISION No.: FIGURE 4 - HIGH-FREQUENCY EDDY CURRENT INSPECTION (SHEET 04 OF 06)

Copyright © 2012 by Embraer S.A. All rights reserved.OK lift off lift off

ref ref

exec H F1 PROBE Absolute LIFT−OFF

DOWN UP



### BEM170SB571330A.DGN 

# SERVICE BULLETIN ALERT

ALERT DATE: 13/Feb/2012 REVISION No.: SB No.: 170-57-A053 PAGE: 19 FIGURE 4 - HIGH-FREQUENCY EDDY CURRENT INSPECTION (SHEET 05 OF 06)

Copyright © 2012 by Embraer S.A. All rights reserved.50% FSH SIGNAL 0.5 mm DEEP EDM NOTCH 80% FSH SIGNAL 1.0 mm DEEP EDM NOTCH

20% FSH SIGNAL 0.2 mm DEEP EDM NOTCH

OK lift off lift off

ref ref

exec H F1 3 CORES



### CEM170SB571331A.DGN 

# SERVICE BULLETIN ALERT

ALERT SB No.: 170-57-A053 PAGE: 20 DATE: 13/Feb/2012 REVISION No.: FIGURE 4 - HIGH-FREQUENCY EDDY CURRENT INSPECTION (SHEET 06 OF 06)

Copyright © 2012 by Embraer S.A. All rights reserved.

### SERVICE BULLETIN EVALUATION

THE PURPOSE OF THIS FORM IS TO COLLECT DATA THAT WILL BE USED TO IMPROVE THE QUALITY OF OUR SERVICE BULLETINS AND UPDATE THE TECHNICAL PUBLICATIONS. PLEASE FILL IN FORM AND RETURN IT TO: EMBRAER - EMPRESA BRASILEIRA DE AERONÁUTICA S.A. EFTC - SERVICE BULLETIN ENGINEERING AV. BRIGADEIRO FARIA LIMA, 2170 SÃO JOSÉ DOS CAMPOS - SP - 12227-901 BRASIL Fax: + 55 12 3927-6600 (ext. 1624) e-mail: fleet.reliability@embraer.com.br S.B. Title: S.B.: (Number / Rev.) Operator:
SB Implementation Report Aircraft Serial Number or Registration Number: Incorporation Date: Aircraft Flight Hours: Aircraft Landings:

POST-ACCOMPLISHMENT EVALUATION: (Check applicable squares below) ESTIMATED MANPOWER: [ ] OK [ ] NOT OK (Explain Below) MATERIAL & KITS: [ ] OK [ ] NOT OK (Explain Below) ACCOMPLISHMENT INSTRUCTIONS: [ ] OK [ ] NOT OK (Explain Below) FIGURES: [ ] OK [ ] NOT OK (Explain Below) SB GENERAL EVALUATION: [ ] OK [ ] NOT OK (Explain Below) COMMENTS: (Bulletin quality/ Difficulties found at the time of incorporation/ Suggested improvements/ Other)

Organization: Fax: Phone:
E-mail: Address: Prepared by:(Name/Title) Date:

Copyright © 2012 by Embraer S.A. All rights reserved.