SB500-27-A026-REV.01 - FLIGHT CONTROLS - AILERON TRIM

EMBRAER EMB-500 Phenom 100 · Service Bulletins

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Overview

This document is Revision 01 of Service Bulletin 500-27-A026 for the Embraer EMB-500 Phenom 100. It outlines inspection and torque procedures for the aileron, rudder, and elevator trim tabs, including the installation of cotter pins to ensure proper functionality and safety.

Revision 01 incorporates changes from previous issues.
No additional action is required for aircraft that complied with the previous bulletin.
The bulletin affects specific serial numbers of the EMB-500 Phenom 100.
Inspection and torque of trim tabs are necessary to prevent loss of control.
Embraer recommends compliance within the next 50 flight hours.
Parts for the service bulletin will be provided at no charge.
Labor will be compensated if performed at an authorized service center.
No concurrent requirements are specified.

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Document details

Type: Service Bulletins
Year: 2017
File size: 1.1 MB
Publisher: regulations.gov
Language: en

About this document

What is the SB500-27-A026-REV.01 - FLIGHT CONTROLS - AILERON TRIM?

The SB500-27-A026-REV.01 - FLIGHT CONTROLS - AILERON TRIM is a service bulletins for the EMBRAER EMB-500 Phenom 100, dated 2017.

Where does the SB500-27-A026-REV.01 - FLIGHT CONTROLS - AILERON TRIM come from?

This copy of the SB500-27-A026-REV.01 - FLIGHT CONTROLS - AILERON TRIM was originally published by regulations.gov and is hosted on Sprinkle as a free, searchable reference copy.

What year was the SB500-27-A026-REV.01 - FLIGHT CONTROLS - AILERON TRIM published?

The SB500-27-A026-REV.01 - FLIGHT CONTROLS - AILERON TRIM — the EMBRAER EMB-500 Phenom 100 service bulletins on file — is dated 2017.

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In this document

Description

This section provides an overview of the service bulletin, including the reason for revision and the affected aircraft.

Planning Information

Details the effectivity of the service bulletin and the specific aircraft serial numbers affected.

Accomplishment Instructions

Outlines the steps for inspecting and installing cotter pins on the trim tabs.

Material Information

Describes the parts required for the service bulletin and warranty coverage.

Compliance

Recommends that the inspection and modifications be completed within 50 flight hours.

Approval

Confirms that the technical aspects of the service bulletin are approved by Embraer Engineering Board.

Safety notes

Inspection is necessary to avoid total loss of trim tab actuation connection.
Failure to install cotter pins may lead to flutter and possible loss of airplane control.
Ensure the aircraft is safe for maintenance before proceeding with inspections.

Full document text

1. DESCRIPTION This sheet transmits Revision 01 to Service Bulletin 500-27-A026. This is a complete reissue of the Service Bulletin. This revision incorporates the information presented in the Information Notice related to the previous issues of this Service Bulletin, as listed below: None. 2. ADDITIONAL ACTION Aircraft that have complied with the previous issue of this service bulletin do not need any additional action. 3. RECORD OF REVISION Basic issue: 29/Sep/2017 Revision 01: 06/Oct/2017 4. HIGHLIGHTS The topics, affected pages, and a brief description of the content-related changes introduced by this revision are presented below. Revision bars are put in the left margin of each page to show the location of the significant changes. Text displacement and text format changes are not indicated. TOPIC/PAGE DESCRIPTION OF REVISION 1. PLANNING INFORMATION 1.A. SB EFFECTIVITY / 01 Added aircraft to the SB effectivity. 1.C. REASON / 02 Added reason for Revision 01. TM TRANSMITTAL LETTER SB No.: 500-27-A026 PAGE: 1 of 1 Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details. FLIGHT CONTROLS - AILERON TRIM TAB, RUDDER TRIM TAB AND ELEVATOR TRIM TAB INSPECTION AND TORQUE In connection with the use of this document, Embraer does not provide any express or implied warranties and expressly disclaims any warranty of merchantability or fitness for a particular purpose. This document contains trade secrets, confidential, proprietary information of Embraer and technical data subject to U.S. Export Administration Regulation (″EAR″) and other countries export control laws and regulations. Diversion contrary to the EAR and other laws and regulations is strictly forbidden. The above restrictions may apply to data on all pages of this document. 1. PLANNING INFORMATION A. SB EFFECTIVITY (1) PART I: INSPECTION OF AILERON TRIM TAB, RUDDER TRIM TAB AND ELEVA- TOR TRIM TAB Aircraft affected: MODEL SN EMB-500 ’Phenom 100’ 50000246, 50000267, 50000286, 50000289, 50000291, 50000299, 50000304 thru 50000306, 50000310, 50000348, 50000359, 50000368, 50000370, 50000372, and 50000376 thru 50000380. (2) PART II: AILERON TRIM TAB, RUDDER TRIM TAB AND ELEVATOR TRIM TAB COTTER PIN INSTALLATION AND TORQUE Aircraft affected: MODEL SN EMB-500 ’Phenom 100’ 50000246, 50000267, 50000286, 50000289, 50000291, 50000299, 50000304 thru 50000306, 50000310, 50000348, 50000359, 50000368, 50000370, 50000372, and 50000376 thru 50000380. In-production effectivity: The subject presented in this bulletin does not affect any in-production aircraft. TM SERVICE BULLETIN ALERT ALERT DATE: 29/Sep/2017 REVISION No.:01 - 06/Oct/2017 SB No.: 500-27-A026 PAGE: 1 of 21 Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details. B. CONCURRENT REQUIREMENTS None. C. REASON (1) HISTORY At the assembly line, during an inspection, the aileron trim tab, rudder trim tab and elevator trim tab were found without cotter pin installed. (2) OBJECTIVE To inspect the aileron trim tab, rudder trim tab and elevator trim tab, apply torque and to install the cotter pin, as necessary. (3) EXPECTED BENEFITS The inspection and torque are aimed to make sure that the components are correctly installed to avoid total loss of trim tab actuation connection which could cause flutter and possible loss of airplane control. (4) REVISION HISTORY Revision 01. – This revision is issued to add aircraft to the SB effectivity. D. DESCRIPTION (1) PART I: INSPECTION OF AILERON TRIM TAB, RUDDER TRIM TAB AND ELEVA- TOR TRIM TAB The modification presented in PART I of this service bulletin consists of inspecting the aileron trim tab, rudder trim tab and elevator trim tab. If the aileron trim tab, rudder trim tab or elevator trim tab is found without cotter pin installed, apply torque to the aileron trim tab, rudder trim tab and to the elevator trim tab and install cotter pin to them, as given in PART II of this service bulletin. TM SERVICE BULLETIN ALERT ALERT SB No.: 500-27-A026 PAGE: 2 DATE: 29/Sep/2017 REVISION No.: 01 - 06/Oct/2017 Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details. (2) PART II: AILERON TRIM TAB, RUDDER TRIM TAB AND ELEVATOR TRIM TAB COTTER PIN INSTALLATION AND TORQUE The modification presented in PART II of this service bulletin consists of to apply torque to the aileron trim tab, rudder trim tab and elevator trim tab and to install cotter pin to them. E. COMPLIANCE Embraer recommends that PART I and PART II of this bulletin be accomplished within the next 50 flight hours. F. APPROVAL The technical aspects of this Service Bulletin are approved by: Embraer - Engineering Board. G. ESTIMATED MANPOWER This estimate is for direct labor only, performed by experienced personnel, and does not include the time to plan, prepare, or inspect the work. It is assumed that all the tools, parts, and other means are promptly available when necessary. This estimate does not include the sealant, paint, or adhesive curing time. (1) APPLICABLE TO PART I: INSPECTION OF AILERON TRIM TAB, RUDDER TRIM TAB AND ELEVATOR TRIM TAB – Access opening: None. – Inspection: 1.0 man-hour. – Access closure: None. – Test: Not applicable. TM SERVICE BULLETIN ALERT ALERT DATE: 29/Sep/2017 REVISION No.:01 - 06/Oct/2017 SB No.: 500-27-A026 PAGE: 3 Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details. (2) APPLICABLE TO PART II: AILERON TRIM TAB COTTER PIN INSTALLATION AND TORQUE – Access opening: 0.1 man-hours. – Modification: 0.3 man-hours. – Access closure: 0.1 man-hours. – Test: 0.5 man-hours. RUDDER TRIM TAB COTTER PIN INSTALLATION AND TORQUE – Access opening: 0.1 man-hours. – Modification: 0.3 man-hours. – Access closure: 0.1 man-hours. – Test: 0.5 man-hours. ELEVATOR TRIM TAB COTTER PIN INSTALLATION AND TORQUE – Access opening: 0.1 man-hours. – Modification: 0.3 man-hours. – Access closure: 0.1 man-hours. – Test: 0.5 man-hours.

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H. COMMUNICATIONS TO EMBRAER EMBRAER requests that any results found during these inspections be informed to your local EMBRAER representatives or offices (contact.center@embraer.com.br). TM SERVICE BULLETIN ALERT ALERT SB No.: 500-27-A026 PAGE: 4 DATE: 29/Sep/2017 REVISION No.: 01 - 06/Oct/2017 Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details. I. REFERENCES AMM 500/( ) Aircraft Maintenance Manual PART II - 20-00-00 - STANDARD PRACTICES-AIRFRAME. AMM 500/( ) Aircraft Maintenance Manual PART II - 27-14-02, 27-14-03, 27-24- 02, 27-24-03, 27-34-02, and 27-34-05 - FLIGHT CONTROLS. J. PUBLICATIONS AFFECTED None. TM SERVICE BULLETIN ALERT ALERT DATE: 29/Sep/2017 REVISION No.:01 - 06/Oct/2017 SB No.: 500-27-A026 PAGE: 5 Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details. 2. MATERIAL INFORMATION A. MATERIAL - PRICE AND AVAILABILITY None. B. INDUSTRY SUPPORT INFORMATION (1) WARRANTY COVERAGE (a) Parts The SB parts will be provided at no charge. (b) Labor Embraer will compensate the man-hours listed in 1.G. ESTIMATED MAN- POWER if it is performed in an Embraer-authorized service center (c) Expiration Not applicable. C. MATERIAL NECESSARY FOR EACH AIRCRAFT The expendable or consumable parts presented in the AMM Tasks referred to in this bulletin, which are necessary for its accomplishment, should be procured from the operator’s inventories or ordered as spares. (1) MATERIAL TO BE PROCURED (a) APPLICABLE TO PART II - Parts The parts below should be procured from Embraer as spare part. NEW PN DESCRIPTION OLD PN QTY DISP MS24665-86 Cotter Pin MS24665-86 16 7 MS24665-151 Cotter Pin MS24665-151 04 7 TM SERVICE BULLETIN ALERT ALERT SB No.: 500-27-A026 PAGE: 6 DATE: 29/Sep/2017 REVISION No.: 01 - 06/Oct/2017 Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details. NEW PN DESCRIPTION OLD PN QTY DISP MS24665-153 Cotter Pin MS24665-153 04 7 DISPOSITION: 7 = Replace with part bearing same PN TM SERVICE BULLETIN ALERT ALERT DATE: 29/Sep/2017 REVISION No.:01 - 06/Oct/2017 SB No.: 500-27-A026 PAGE: 7 Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details. 3. ACCOMPLISHMENT INSTRUCTIONS 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- 801-A/200 - Aircraft Maintenance Safety Procedures. B. APPLICABLE TO PART I: (1) Inspect the aileron trim tab, rudder trim tab and elevator trim tab attachment points to make sure the cotter pin is installed. Refer to Figure 1, Figure 2 and Figure 3. NOTE: You can move the surface to have a view of the entire installation. (2) If the cotter pin is installed, no action is required. (3) If the cotter pin is not installed, perform PART II of this service bulletin. C. APPLICABLE TO PART II: (1) Torque and Install the aileron trim tab cotter pin, as follows: (a) Apply torque to the aileron trim tab, according to AMM TASK 27-14-02-400- 801-A/400 - Roll Trim Actuator - Installation and AMM TASK 27-14-03-400-801- A/400 - Aileron Trim-Tab Surface - Installation. Refer to Figure 4. (b) Install the cotter pin, according to AMM TASK 27-14-02-400-801-A/400 - Roll Trim Actuator - Installation and AMM TASK 27-14-03-400-801-A/400 - Aileron Trim-Tab Surface - Installation. Refer to Figure 4. (c) Perform the backlash procedure according to AMM TASK 27-14-03-720-801- A/500 - Aileron Trim-Tab Backlash - Functional Check. (2) Torque and Install the rudder trim tab cotter pin, as follows: (a) Apply torque to the rudder trim tab, according to AMM TASK 27-24-02-400-801- A/400 - Yaw Trim Actuator - Installation and AMM TASK 27-24-03-400-801- A/400 - Rudder Trim-Tab Surface - Installation. Refer to Figure 5. TM SERVICE BULLETIN ALERT ALERT SB No.: 500-27-A026 PAGE: 8 DATE: 29/Sep/2017 REVISION No.: 01 - 06/Oct/2017 Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details. (b) Install new cotter pin, according to AMM TASK 27-24-02-400-801-A/400 - Yaw Trim Actuator - Installation and AMM TASK 27-24-03-400-801-A/400 - Rudder Trim-Tab Surface - Installation. Refer to Figure 5. (c) Perform the backlash procedure according to AMM TASK 27-24-03-720-801- A/500 - Rudder Trim-Tab Backlash - Functional Check. (3) Torque and Install the elevator trim tab cotter pin, as follows: (a) Apply torque to the elevator trim tab, according to AMM TASK 27-34-02-400- 801-A/400 - Pitch Trim Actuator - Installation and AMM TASK 27-34-05-400- 801-A/400 - Elevator Trim-Tab Surface - Installation. Refer to Figure 6. (b) Install new cotter pin, according to AMM TASK 27-34-02-400-801-A/400 - Pitch Trim Actuator - Installation and AMM TASK 27-34-05-400-801-A/400 - Elevator Trim-Tab Surface - Installation. Refer to Figure 6. (c) Perform the backlash procedure according to AMM TASK 27-34-05-720-801- A/500 - Elevator Trim-Tab Backlash - Functional Check. D. Restore the aircraft to normal. Refer to AMM TASK 20-00-00-910-801-A/200 - Aircraft Maintenance Safety Procedures. E. Enter the accomplishment of this bulletin in the applicable documents. F. Fill out the attached “Service Bulletin Implementation and Evaluation” form and return it to: NOTE: To formally inform that the SB has been incorporated fleet-wide or that the SB will not be incorporated, so that Embraer can update the affected technical publica- tions, use the “Service Bulletin Full-Fleet Incorporation Report” form, which is available on the FLYEmbraer portal (http://www.flyembraer.com). TM SERVICE BULLETIN ALERT ALERT DATE: 29/Sep/2017 REVISION No.:01 - 06/Oct/2017 SB No.: 500-27-A026 PAGE: 9 Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details. A ZONE 672 A B C B EM500ENSB270398A.DGN COTTER PIN (INSPECT) TM SERVICE BULLETIN ALERT ALERT SB No.: 500-27-A026 PAGE: 10 DATE: 29/Sep/2017 REVISION No.: 01 - 06/Oct/2017 FIGURE 1 - AILERON TRIM TAB INSPECTION (SHEET 01 OF 02) Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details. C EM500ENSB270399A.DGN COTTER PIN (INSPECT) COTTER PIN (INSPECT) TM SERVICE BULLETIN ALERT ALERT DATE: 29/Sep/2017 REVISION No.:01 - 06/Oct/2017 SB No.: 500-27-A026 PAGE: 11 FIGURE 1 - AILERON TRIM TAB INSPECTION (SHEET 02 OF 02) Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details. ZONE 336 A A B B C D EM500ENSB270391A.DGN TM SERVICE BULLETIN ALERT ALERT SB No.: 500-27-A026 PAGE: 12 DATE: 29/Sep/2017 REVISION No.: 01 - 06/Oct/2017 FIGURE 2 - RUDDER TRIM TAB INSPECTION (SHEET 01 OF 02) Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details. C D EM500ENSB270392A.DGN COTTER PIN (INSPECT) COTTER PIN (INSPECT) COTTER PIN (INSPECT) COTTER PIN (INSPECT) TM SERVICE BULLETIN ALERT ALERT DATE: 29/Sep/2017 REVISION No.:01 - 06/Oct/2017 SB No.: 500-27-A026 PAGE: 13 FIGURE 2 - RUDDER TRIM TAB INSPECTION (SHEET 02 OF 02) Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details. A A ZONE 348 ZONE 347 TYPICAL A B C B EM500ENSB270394A.DGN COTTER PIN (INSPECT) TM SERVICE BULLETIN ALERT ALERT SB No.: 500-27-A026 PAGE: 14 DATE: 29/Sep/2017 REVISION No.: 01 - 06/Oct/2017 FIGURE 3 - ELEVATOR TRIM TAB INSPECTION (SHEET 01 OF 02) Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details. EM500ENSB270395A.DGN C COTTER PIN (INSPECT) COTTER PIN (INSPECT) TM SERVICE BULLETIN ALERT ALERT DATE: 29/Sep/2017 REVISION No.:01 - 06/Oct/2017 SB No.: 500-27-A026 PAGE: 15 FIGURE 3 - ELEVATOR TRIM TAB INSPECTION (SHEET 02 OF 02) Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details. A ZONE 672 A B C B EM500ENSB270400A.DGN 01 NUT (APPLY TORQUE) COTTER PIN PN MS24665−86 (2 POSITIONS) (INSTALL) 01 APPLY TORQUE ACCORDING TO AMM TASK 27−14−03−400−801−A TM SERVICE BULLETIN ALERT ALERT SB No.: 500-27-A026 PAGE: 16 DATE: 29/Sep/2017 REVISION No.: 01 - 06/Oct/2017 FIGURE 4 - AILERON TRIM TAB TORQUE AND COTTER PIN INSTALLATION (SHEET 01 OF 02) Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details. C EM500ENSB270401A.DGN 01 APPLY TORQUE ACCORDING TO AMM TASK 27−14−02−400−801−A NUT (APPLY TORQUE) COTTER PIN PN MS24665−86 (2 POSITIONS) (INSTALL) 01 NUT (APPLY TORQUE) COTTER PIN PN MS24665−86 (2 POSITIONS) (INSTALL) 01 TM SERVICE BULLETIN ALERT ALERT DATE: 29/Sep/2017 REVISION No.:01 - 06/Oct/2017 SB No.: 500-27-A026 PAGE: 17 FIGURE 4 - AILERON TRIM TAB TORQUE AND COTTER PIN INSTALLATION (SHEET 02 OF 02) Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details. ZONE 336 A A B B C D EM500ENSB270391A.DGN TM SERVICE BULLETIN ALERT ALERT SB No.: 500-27-A026 PAGE: 18 DATE: 29/Sep/2017 REVISION No.: 01 - 06/Oct/2017 FIGURE 5 - RUDDER TRIM TAB TORQUE AND COTTER PIN INSTALLATION (SHEET 01 OF 02) Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details. C D EM500ENSB270393A.DGN 01 01 APPLY TORQUE ACCORDING TO AMM TASK 27−24−02−400−801−A AND 27−24−03−400−801−A NUT (APPLY TORQUE) COTTER PIN PN MS24665−86 (2 POSITIONS) (INSTALL) 01 NUT (APPLY TORQUE) COTTER PIN PN MS24665−151 (2 POSITIONS) (INSTALL) NUT (APPLY TORQUE) COTTER PIN PN MS24665−151 (2 POSITIONS) (INSTALL) 01 TM SERVICE BULLETIN ALERT ALERT DATE: 29/Sep/2017 REVISION No.:01 - 06/Oct/2017 SB No.: 500-27-A026 PAGE: 19 FIGURE 5 - RUDDER TRIM TAB TORQUE AND COTTER PIN INSTALLATION (SHEET 02 OF 02) Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details. A A ZONE 348 ZONE 347 TYPICAL A B C B EM500ENSB270396A.DGN 01 NUT (APPLY TORQUE) COTTER PIN PN MS24665−153 (2 POSITIONS) (INSTALL) 01 APPLY TORQUE ACCORDING TO AMM TASK 27−34−05−400−801−A TM SERVICE BULLETIN ALERT ALERT SB No.: 500-27-A026 PAGE: 20 DATE: 29/Sep/2017 REVISION No.: 01 - 06/Oct/2017 FIGURE 6 - ELEVATOR TRIM TAB TORQUE AND COTTER PIN INSTALLATION (SHEET 01 OF 02) Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details. C EM500ENSB270397A.DGN NUT (APPLY TORQUE) COTTER PIN PN MS24665−86 (2 POSITIONS) (INSTALL) 01 01 NUT (APPLY TORQUE) COTTER PIN PN MS24665−86 (2 POSITIONS) (INSTALL) 01 APPLY TORQUE ACCORDING TO AMM TASK 27−34−02−400−801−A TM SERVICE BULLETIN ALERT ALERT DATE: 29/Sep/2017 REVISION No.:01 - 06/Oct/2017 SB No.: 500-27-A026 PAGE: 21 FIGURE 6 - ELEVATOR TRIM TAB TORQUE AND COTTER PIN INSTALLATION (SHEET 02 OF 02) Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details. SERVICE BULLETIN IMPLEMENTATION AND EVALUATION FORM The purpose of this form is to collect data that will be used to improve the quality of our Service Bulletins and Reliability Program. Please fill in this form and return it to: EMBRAER S.A. Phenom Maintenance Support Av. Brig. Faria Lima, 2170 SÃO JOSÉ DOS CAMPOS - SP CEP: 12227-901 - PO Box: 36/2 BRASIL Fax: ++ 55 12 3927-2619 e-mail: phenom.reliability@embraer.com.br SB Number/Revision: SB Title: SB Implementation Report Aircraft Serial Number or Registration Number: Incorporation Date: Aircraft Flight Hours: Aircraft Landings: SB Evaluation (Check applicable boxes bellow and use the space as required to provide any additional information) Estimated Manpower: [ ] OK [ ] NOT OK Material & Kits: [ ] OK [ ] NOT OK Accomplishment Instructions: [ ] OK [ ] NOT OK Figures: [ ] OK [ ] NOT OK SB General Evaluation: [ ] OK [ ] NOT OK Comments: (Bulletin quality, difficulties found at the time of incorporation, suggested improvements, other) Company/Service Center: E-mail: Phone: Address: Form filled by: Work Order: Copyright © 2017 by Embraer S.A. All rights reserved - See title page for details.

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