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

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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

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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

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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

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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 inspection

area. 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

INSPECTED

EM170SB571326A.DGN

SERVICE BULLETIN

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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

INSPECTED

EM170SB571328A.DGN

SPAR

CAPTHIRD

SERVICE BULLETIN

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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

INSPECTED

EM170SB571327A.DGN

SERVICE BULLETIN

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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

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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

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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

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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

A

EM170SB571329A.DGN

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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

B

EM170SB571330A.DGN

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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

CORES 3

C

EM170SB571331A.DGN

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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:

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