# ~EMBRAER ALERT 

# SERVICE BULLETIN In connection with the use of this document, Embraer does not provide any exp ress or i mpl ied wa rran ties and e xpre ssly disclaims any warran t y of merch antabi lit y or fitness for a p articular purpose . FLIGHT CONTROLS - INSPECTION OF THE RUDDER TRIM TAB ACTUATOR 1. PLANN I NG I NFORMATION A . SB EFFECTIVITY A i rcraft affected : MODEL EMB-110- BANDEIRANTE Affected component: SN All ai r craft in operation equipped with the affected Part Number. Rudder Trim Tab Actuator Pa rt Numbers 110P2-506-10-09 -36 , 1 10P2-506- 10-09-37 , a nd 1 1OP2- 506-1 0 -09-38 insta lle d in the ai rcraft or in stock as spare. NOTE: This effectivity list inclu des the a i rcraft orig inally equipped w ith the aff ected componen t. S in ce this component is a " Line Replaceabl e Unit" (LRU) , it may be necessary to refer to the fleet maintenance control reco r d and verify whethe r the un it has not been rep laced w ith another one duri ng ro utine ma i ntenance . I n-production effectivity: The subject p resented in this bullet in does not affect any in-p rodu ction aircraft . B. CONCURRENT REQU I REME NTS None.

DA T E : 21 / Aug/2014 REVI SION No. : 

## ALERT C

opyri ght © 201 4 by EMBRAER - All rig hts reserved . SB No.: 11 0-27-A095 PAGE : 1 of 15

### ALERT



# ~EMBRAER 

# SERVICE BULLETIN

C. REASON Embraer was informed about an event of high level vibration and difficulty of controllability during an Embraer-110P1 flight that required the crew to do a forced landing . The investigation identified a condition of a severe internal at the rudde r trim tab actuator fork end , which was found disconnected , making the rudder trim tab loose . Also, the rudder horn mass balance was lost. This Alert Service Bulletin gives the instructions tp inspect the rudder trim tab actuator components for signs of corrosion , with emphasis on its spring and fork end. D. DESCRIPTION This Bulletin is divided into 2 PARTS , as follows: PART I I NSPECTION OF THE RUDDER TRIM TAB ACTUATOR COMPONENTS Applicable to: Service Bulletin Effectivity . PART I of this bulletin presents a Detailed Inspection (DI) for signs of corrosion in the Rudder Trim Tab Actuator components, specifically on its Spring and Fork End installed in Rudder Trim Tab Actuator. a) If no signs of corrosion in the Spring and Fork End are detected , the components cleaning and protection against corrosion by the application of a corrosion inhibitive compound is required; b) If any signs of corrosion is detected in the Spring and Fork End, replace these components by the accomplishment of Part II of this Bulletin. To do this, it is necessary to remove the Rudder Trim Tab Actuator from the aircraft and perform the inspection on the bench. NOTE: During the inspections mentioned in this PART I, the corros ion level identification may be different depending on the component to be inspected . The time for accomplishment of PART II of this Bulletin is also different depending on the level of the corrosion of each component. For this , refer to Section 1.E. TIME FOR ACCOMPLISHMENT below for a detailed instructions for corrosion level identification . SB No . : 110-27-A095 PAGE: 2 

## ALERT Copyright © 2014 by EMBRAER- All rights reserved. DATE: 21/Aug/2014 REVISION No.:

# ~EMBRAER ALERT 

# SERVICE BULLETIN Embraer is providing the necessary support for the accomplishment of this Bulletin with the Embraer Technical Representatives or through Embraer Fleet Technical Center. Refer to Section 2.B. I NDUSTRY SUPPORT INFORMATION for Embraer contact information. PART II REPLACEMENT OF THE SPRING AND FORK END Applicable to: Service Bulletin Effectivity. PART II of this bulletin consists in replacing the Spring and Fork End installed in Rudder Trim Tab Actuator . To do this , it is necessary to remove the Rudder Trim Tab Actuator from the aircraft and perform the modification on the bench . E. TIME FOR ACCOMPLISHMENT (1) Applicable to PART I Embraer recommends that PART I of this bulletin be accomplished within the next 10 flight hours or 15 calendar days, whichever occurs first, after the release date of this Service Bulletin. NOTE: If any report of vibration is detected , Embraer recommends the accomplishment of PART I of this Service Bulletin before the next flight.

DATE : 21/Aug/2014 REVISION No.: 

## ALERT Copyright © 20'14 by EMBRAER- All rights reserved . SB No.: 110-27-A095 PAGE: 3

# ~EMBRAER ALERT 

# SERVICE BULLETIN (2) Applicable to PART II (a) Applicable for the Fork End (Aluminum) - Internal and External surface CORROSION LEVEL

Surface oxidation or discoloration

Light Corrosion

(Local pitting corrosion not located in the cross

hole boundaries)

Severe Corrosion

(Multiple pitting corrosion or pitting located in the cross hole boundary) SB No.: 110-27-A095 PAGE: 4 CORROSION CARACTERIZA TION ACTION I TIME FOR ACCOMPLISHMENT Cha racterized by a surface color - Clean the surface with change different from the original Methyl Ethyl Ketone (MEK) aspect. Normally these affected and apply Corrosion areas present dark gray coloration. Inhibitor Compound Dinitrol Visually examining the surface it is AV 15 or AV 30 (or any not possibl e to detect pitting under Spec. MIL-PRFindications. When scribing the 16173) in the Fork End affected surface with a suitable Bore immediately after the tool , it is poss ible to observe that accomplishment of PART I the indication is just superficial with of this Bulletin. no deep indication. Use suitable tool like acrylic/plastic razor to avo id scratches in the surface.

- Clean the surface with Methyl Ethyl Ketone (M EK) and apply Corrosion Inhibitor Compound Dinitrol AV 15 or AV 30 (or any under Spec. MIL-PRF16173) in the Fork End Characterized by single pitting Bore immediately after the indications not concentrated in a accomplishment of PART I specific area and not located in the of this Bulletin, and then; cross holes boundaries.

Characterized by multiple and concentrated pitting indications in any surface of the part or by single pitting indication located in the cross hole boundary. 

## ALERT - Replace the Fork End by the accomplishment of PART II 150 flight hours or 03 calendar months (whichever occurs first) after the accomplishment of PART I.

- Replace the Fork End by the accomplishment of PART II of this Bulletin immediately after the accomplishment of PART 

### I. DATE: 21/Aug/2014 REVISION No . : Copyright© 201 4 by EMBRAER - All rights reserved.

# ~EMBRAER ALERT 

# SERVICE BULLETIN (b) Applicable for the Spring (Steel) CORROSION LEVEL

Surface oxidation or discoloration:

Light Corros ion:

Severe Corrosion:

DATE: 21/Aug/2014 REVISION No.: CORROSION CARACTERIZA TION ACTION I TIME FOR ACCOMPLISHMENT Characterized by a surface color - Clean the surface with change different from the original Methyl Ethyl Ketone (MEK) aspect. Normally these affected to remove the residues and areas present a reddish to brown apply Corrosion Inhibitor or dark coloration. When scribing Compound Dinitrol AV 15 the affected surface with a suitable or AV 30 (or any under tool, it is possible to observe that Spec. MIL-PRF- 16173) in the indication is just supe rficial the Fork E nd Bore without evidence of material immediately after the removal. Use suitab le tool like accomplishment of PART I acryli c/plastic razor to avoid of this Bulletin. scratches in the surface. Characterized by local reddish to brown indications without evidence of thickness reduction. Scribing the surface with a suitable tool it is possible to observe changes in the surface roughness between the indication area and surrounding surfaces, but there is no deep indication. Use suitable tool like acryl ic/plastic razor to avoid scratches in the surface.

Characterized by overall reddish to brown indications with evidence of thickness reduction or residues due to material exfoliation. Scribing the surface with a suitable tool it is possible to observe deep indications with evidence of thickness reduction. Use suitable tool l ike acrylic/plastic razor to avoid scratches in the surface. - Sand Smoothly the affected areas, clean the surface to remove the residues and apply Corrosion Inhibitor Compound Dinitrol AV 15 or AV 30 (or any under Spec. MIL-PRF- 16173) in the spring immediately after the accomplishment of PART I of this Bulletin, and then.

- Replace the Spring by the accomplishment of PART II 150 flight hours or 03 months (whichever occurs first) after the accomplishment of PART I . Replace the Spring by the accomplishment of PART II of this Bulletin immediately after the accomplishment of PART I.


## ALERT SB No . : 110-27-A095 PAGE: 5 Copyright © 2014 by EMBRAER- All rights reserved.

### ALERT ' 

# ~EMBRAER 

# SERVICE BULLETIN

F. APPROVAL The technical aspects of this Alert Service Bulletin are approved by: Embraer - Engineering Board. G. COMMUNICATIONS TO EMBRAER EMBRAER requests that any resu lts found duri ng these inspections be informed to your local EMBRAER representatives or offices. H . ESTIMATED MANPOWER This estimate is for direct labor only, performed by experienced personne l , and does not include the t ime to plan, prepare, or inspect the work. It is assumed that all t he tools , parts , and other means are readily available when necessary. This estimate does not i nclude the sealant, paint, or adhesive curing time. -Access opening: 1.0 man - hour. -I nspection: 1 .5 man - hours. -M odification : 3.0 man- hours.

- Access closure: 1.0 man- hour. -Test: 1.0 man-hour. I. WEIGHT AND BALANCE

- Change in basic weight: None .

- Change in basic moment: None. J .REFERE NCES T.O . 1C95A-2-5- "Maintenance Manual"- Flight Controls . T . P . 27- 00-01 /702- Component Ma intenance Manual.

SB No . : 110-27-A095 PAGE : 6 

## ALERT Copyright © 2014 by EMBRAE R- All rights rese rved. DATE: 21/Aug/2014 REVIS ION No .:

### ALERT



# ~EMBRAER 

# SERVICE BULLETIN

K. OTHER PUBLICATIONS AFFECTED None. 2. MATERIAL INFORMATION A . MATERIAL - PRICE AND AVAILAB ILITY (1) MATERIAL AVAILABLE FROM EMBRAER None. (2) MATERIAL AVAILABLE FROM OTHER VENDORS None. B . INDUSTRY SUPPORT IN FORMATION Embraer can provide the necessary support for the accomplishment of this Bulletin with the Embraer Technical Representatives or through Return to Service. See address below: EMBRAER S.A. ATT .: Return to Service - RTS. Phone: +55 12 3927 7334 or +55 12 99121 2022. E-mail: rts@embraer.com.br

DATE: 21/Aug/2014 REVISION No.: 

## ALERT Copyright © 2014 by EMBRAER - All rights reserved . SB No.: 110-27-A095 PAGE: 7

## ALERT



# ~EMBRAER 

# SERVICE BULLETIN

C. MATERIAL NECESSARY FOR EACH AIRCRAFT (1) MATERIAL TO BE PROCURED -Applicable to Part II only (a) PARTS The parts below should be ordered as spares from Embraer. For this, check the Rudder Trim Tab Actuator Part Number before ordering the Parts. Applicable for Rudder Trim Tab Actuator PN 110P2-506-10-09-36 and 110P2- 506 - 10-09-38 NEWPN DESCRIPTION OLDPN QTY DISP 11 OP2-506-1 0 -09-28-03 Fork End 11 OP2-506-1 0-09-28-03 01 7 120-09954- 001 Spring 120-09954- 001 01 7 PE49073-1 Neoprene PE49073-1 01 7/a Sleeve (a) Replace the Neoprene Sleeve on ly if it is damaged . Applicable for Rudder Trim Tab Actuator PN 11 OP2-506 - 10-09 - 37

NEWPN DESCRIPTION OLDPN QTY DISP/ Note 11 OP2-506- 10-09-29-02 Fork End 11 OP2-506-1 0-09-29-02 01 7 120-09954-001 Spring 120-09954-001 01 7 PE49073-1 Neoprene Sleeve PE49073-1 01 7/a (a) Replace the Neoprene Sleeve only if it i s damaged . (b) CONSUMABLES The material below or equivalent, required for the accomplishment of this bulletin, should be procured from the operator's inventories or from a local supplier. ITEM PN DESCRIPTION Methyl Ethyl Ketone Solvent (Spec . ASTM-D-740) DINITROL AV-30 Corrosion-inhibiting compound (Spec . MEP1 0-063) DINITROL AV-15 Corrosion- i nhibiting compound Spec. M I L- PRF-16173 Corrosion-inhibiting compound SB No. : 110-27-A095 PAGE: 8 

## ALERT Copyright © 2014 by EMBRAER - All rights reserved . QTY DISP AR 6 AR 6 AR 6 AR 6 DATE: 21/Aug/2014 REVISION No.:

## ALERT



# ~EMBRAER 

# SERVICE BULLETIN QUANTITY : AR =As Required. DISPOSITION : 6 = Apply as required 7 = Replace with part bearing same PN D . MATERIAL NECESSARY FOR EACH SPARE None.
E . REIDENTIFIED PARTS None . F. TOOLING- PRICE AND AVAILABILITY None.

DATE: 21/Aug/2014 REVISION No.: 

## ALERT Copyright© 2014 by EMBRAE R - All rights reserved . SB No . : 110-27-A095 PAGE: 9

### ALERT



# ~EMBRAER 

# SERVICE BULLETIN 3. ACCOMPLISHMENT INSTRUCTIONS NOTES: 1) For the purpose of this Service Bulletin , a Detailed Inspection (01) is: "An intensive examination of a specific item, installation or assembly to detect damage , failu re or irregularity. Avai lable l ighting is normally supp lemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as m i rrors , magnifying lenses , etc . may be necessary. Surface cleaning and elabo rate access procedures may be required ." 2) Obey all of the WARNINGS and CAUTIONS included in the referenced manuals and procedures. 3) The Manuals and other documents are referred to by means of acronyms or using a simplified form . Refer to section " 1. I. REFERENCES " for a more comp lete definition. The steps below outline the general accompl ishment instructions . The detai led sequence is included in the respective figure , when necessary. 

### A. Make sure that the aircraft is safe for maintenance . B . PART I- INSPECTION OF THE RUDDER TRIM TAB ACTUATOR COMPONENTS (1) Remove the Rudder Trim Tab Actuator from the aircraft following the instructions of T .O. 1 C95A-2- 5- "Maintenance Manual " - Flight Contro ls . (2) On the Bench , disassemble the Rudder Trim Tab Actuator by following the i nstructions mentioned in T.P . 27-00-01/702- Component Maintenance Manua l with Il l ustrated Part List- Disassembly Section . Refer to Figure 1. (3) Clean the components with the ai d of a nylon brush wet with Methyl Ethyl Ketone (ASTM-0-740) MEK. (4) Do a Detailed Inspection in the Fork End and in the Spring for signs of corrosion and then Refer to Table 1 and Table 2 to identify the applicable action .

SB No.: 110-27-A095 PAGE: 1 0 

## ALERT Copyright © 2014 by EMBRAER - All rig hts reserved . DATE: 21/Aug/2014 REVISION No.:

# ~EMBRAER ALERT 

# SERVICE BULLETIN (a) Applicable for the Fork End (Aluminum) - Internal and External surface CORROSION LEVEL ACTION

- After cleaning, apply a corrosion inhibitor Surface oxidation or compound Dinitrol AV-15 or AV-30 (or any under discoloration: Spec. MIL-PRF-16173) in the Fork End bore.

- After cleaning , apply a corrosion inhibitor

compound Dinitrol AV- 15 or AV-30 (or any under Local pitting corrosion outside Spec . MIL-PRF-16173) in the Fork End bore;

the cross hole boundaries:

- Replace the Fork End by the accomplishment of PART II of this SB in the next 150 flight hours or 03 months (whichever occurs first). Multiple pitting corrosion or - Replace the Fork End by the accomplishment of pitting around the cross hole: PART II of this Bulletin immediately after the accomplishment of PART I. TABLE 01 (b) Applicable for the Spring (Steel) CORROSION LEVEL Surface ox idation or discoloration:

Light Corrosion:

Severe Corrosion:

DATE : 21/Aug/2014 REVISION No.: ACTION -After cleaning, apply a corrosion inhibitor

compound Dinitrol AV-15 or AV-30 (or any under Spec. MIL-PRF-16173) in the Fork End bore. -Sand smoothly the spring surface, clean the

surface using Methyl Ethyl Ketone or equivalent and then apply Dinitrol AV-15 or AV-30 (or any under Spec . MIL-PRF-16173) to the Spring surface and then , .

- Replace the Spring by the accomplishment of

PART II of this SB in the next 150 flight hours or 03 months (whichever occurs first). Replace the Spring by the accomplishment of PART II of this Bulletin accomplishment of PART I. TABLE 02 

### ALERT immediately after the

SB No.: 110-27-A095 PAGE: 11 Copyright © 2014 by EMBRAE R- All rights reserved.

### ALERT



# ~EMBRAER 

# SERVICE BULLETIN (5) Assembly the Rudder Trim Tab Actuator by following the instructions mentioned in T.P. 27-00-01/702 - Component Maintenance Manual with Illustrated Part List- Assembly Section. NOTE 1: During the Assemble of the Rudder Trim Tab Actuator apply Dinitrol AV-15 or AV-30 (or any under Spec. MIL-PRF- 16173) inside the terminal bore. NOTE 2 : If the neoprene sleeve PN PE49073-1 was found damaged, replace it using a new neoprene sleeve with the same Part Number. (6) Re i nstall the Rudder Trim Tab Actuator to the aircraft following the instructions of T. O. 1C95A-2-5- "Maintenance Manual"- Flight Controls. NOTE : After reinstallation do an operation check-out and the trim tabs maximum allowable backlash checkout as described in the Maintenance Manual. C. PART II - REPLACEMENT OF THE SPRING AND FORK END (1) Remove the Rudder Trim Tab Actuator from the aircraft. (2) On the Bench, disassembly the Rudder Trim Tab Actuator by following the instructions mentioned in T.P . 27-00-01/702- Component Maintenance Manual with Illustrated Part List- Disassembly Section . Refer to Figure 1 . (3) Replace the Fork End and/or Spring by the same Part Number. (4) Assemble the Rudder Trim Tab Actuator by following the instructions mentioned in T.P. 27-00-01/702 - Component Maintenance Manual with Illustrated Part List- Assembly Section. Refer to Figure 1. NOTE 1: During the Assemble of the Rudder Trim Tab Actuator app ly Dinitrol AV-15 or AV-30 (or any under Spec. MIL-PRF-16173) inside the terminal bore. NOTE 2: If the neoprene sleeve PN PE49073-1 was found damaged, replace it using a new neoprene sleeve with the same Part Number. (5) Reinstall the Rudder Trim Tab Actuator to the aircraft following the instructions of T .O . 1C95-A-2-5- "Maintenance Manual"- Flight Controls. NOTE : After reinstallation do an operation check-out and the trim tabs maximum allowable backlash checkout as described in the Maintenance Manual. SB No.: 110-27-A095 PAGE: 12 

## ALERT Copyright© 2014 by EMBRAE R- All rights reserved . DATE: 21/Aug/2014 REVISION No . :

### ALERT



# ~EMBRAER 

# SERVICE BULLETIN

D. Put the aircraft back to a serviceable condition. E. Enter Write the accomplishment of PART I and/or PART II of this bulletin in the applicable documents. NOTES: 1) Please inform us by e-mail fleet.reliabilitv@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 has been incorporated fleetwide or that the SB will not be incorporated , so that Embraer can update the affected technical pub lications , use the "Service Bulletin Full-Fleet Incorporation Report" form, wh i ch 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 for us to improve the quality of the SBs.

DATE: 21/Aug/2014 REVISION No.: 

## ALERT Copyright © 2014 by EMBRAER- All rights reserved. SB No.: 110-27-A095 PAGE: 13

# ~EMBRAER ALERT 

# SERVICE BULLETIN

0 0 TRANSM ITT AL BOX (REF .)

DET.A RUDO:R TRIM TABACTUAT CR

RUDDE R TRIM TABACTUATCR (REMOVE AND REINSTALL)

B



## ! ------------------------------------------------------------------------------------- -------- 0 _______________ _____

## ;, **~URE** 1 . RUDDER T RIM TAB ACTUATOR INSPECTION
SB No.: 110-27-A095 PAGE: 14 . (SHEET 01 OF 02) 

## ALERT

Copyright © 2014 by E MBRAER- All rights reserved . DATE : 2 1 /Aug/2014 REVIS ION No . :

### ALERT



# ~EMBRAER 

# SERVICE BULLETIN

**~----------------------------------------------------------------------------------**
**-------------- -----**  **-- ----------**  1

' I ' I 

# \. \\

-·1



## L~ 

## [h FORK E ND ( IN SP ECT THE IN TER N AL AND E XTER N AL SURFACE)



## ~ FORK END (INSPECT THE INTERNAL AND EXTERNAL SURFAC E) NEOPRENE SLEEVE (REF)

.,.,. . --.,.,. -- - - · - · 1

. .. ....,.-· I 

### _____.,......-""·- !

-- I 

### _,-·--- --·- !

-- SPRING 1
-·-·-·- · (INSPECT) i

**.,.,..- """**  **~"""p** i 

### .-·-·-·-·-· R !



# ___

.....,..-""·
- v ___ J

- - i



# --



# ~-~~

**·~(n}\** 0



# ·- **~·**

**-·-~~** 

# v- 0 DET.B

I 1 

## [hFORK E N D OF ACTUATOR PN 110P2-S06-10-09-37. 

# i

**FORK** END OF ACTUATORS PN 110P2- 506-10-{)9-36 AND PN 11 OP2-506-1 0-09 - 3B


### · -------------------- ---- -------------- ------ --- ---------- ---------- --------------- --- --------- -- --- --- ------------- -- - FIGURE 1 : RUDDER TRIM TAB ACTUATOR INSPECTION (SHEET 02 OF 02) DATE : 21/Aug/2014 REVISION No. : 

## ALERT Copyright © 20 14 by EMBRAER - All rights reserved . SB No.: 110-27-A095 PAGE: 15

# ~EMBRAE

**R** SERVIC E B ULL ETIN EVALUATION THE PURPOSE OF THIS FORM 1$ TO COLLECT DATA T HAT WILL BE USED TO IMPROVE THE QUALITY OF OUR SERVICE BULLETINS AND UPDATE THE TECHNICAL PUBLICATION . PLEASE FILL IN FORM AND RETURN IT TO : EMBRAER- EMPRESA BRAS ILE I RA DE AERONAUTICA S.A. TECHN I CAL PUB LICATIONS AV . BRIG . FARIA LIMA , 2170 SAO JOSE DOS CAMPOS - S P - 12227
-901 BRASIL Fax: ++ 55 12 3927-7546 e-mail: service . bulletin@embraer
. com .br sa Tit le: 

# I SB: ( NumberI Rev .) Opera tor: 

# I Aircraft serial numberaffected: {per SB effectivity list) PRE-ACCOMPLISH M

E

N T EVAL U ATION : (check applicable squares below) [ I WILL BE ACCOMPLISHED ON FIRST NC [ I WILL BE ACCOMPLISHED AS REQUIRED [ I WILL BE ACCOMPLISHED ON FLEET [ I DECISION DEFERRED ( Exp la in below) 

## - - - [ I UNECONOMICAL I I SERVICE EX P E RI ENCE DOE S NOT JUSTIFY [ I WI LL NOT BE A CCOMPLISHE D : [ I OPERA TIO NAL ENVIRON M E NT DOES NOT JUST IFY I I OTHER (Explain below) POST-ACCOM PLISH MENTEVALUATION: (Check appl ic

able squares below ) ESTIMA T ED MANPOWER: [ I OK [ I NOT OK (Explain below) MATERIAL & K ITS: [ I OK [ I NOT OK (Expla i n be low) ACCOMPLISHMENT INSTRUCTIO N S: [ I OK I I NOT OK (E xpla in be low) FIGUR E S : [ I OK [ I NOT OK ( Explain be low) SB GENERAL EVALUA TIO N : I I OK [ I NOT OK (Exp la in below) COMM ENTS: (Bulletin quality / Difficulties found at the time ofincorporation! Suggested improvements! Other )

Organization: 

## IFax: 

## IPhone: E-mail : Address: 

# I Prepared by : (Name/ Title) 

## JDate: ENS-003393