~EMBRAER ALERT 

SERVICE BULLETIN 

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. 

FLIGHT CONTROLS - INSPECTION OF THE RUDDER TRIM TAB ACTUATOR 

1. PLANNING INFORMATION 

A. SB EFFECTIVITY 

Aircraft affected: 

MODEL 

EMB-110- BANDEIRANTE 

Affected component: 

SN 

All aircraft in operation equipped with the affected 

Part Number. 

Rudder Trim Tab Actuator Part Numbers 110P2-506-10-09-36, 110P2-506-1 0-09-37, 

and 11 OP2-506-1 0-09-38 installed in the aircraft or in stock as spare. 

NOTE: This effectivity list includes the aircraft originally equipped with the affected 

component. Since this component is a "Line Replaceable Unit" (LRU), it may 

be necessary to refer to the fleet maintenance control record and verify 

whether the unit has not been replaced with another one during routine 

maintenance. 

In-production effectivity: 

The subject presented in this bulletin does not affect any in-production aircraft. 

B. CONCURRENT REQUIREMENTS 

None. 

DATE: 21/Aug/2014 

REVISION No.: ALERT 

Copyright © 2014 by EMBRAER - All rights reserved. 

SB No.: 11 0-27 -A095 

PAGE: 1 of 15 
~EMBRAER ALERT 

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 rudder 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 INSPECTION 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 corrosion 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. INDUSTRY 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 

Characterized 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 possible 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 possible 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 

avoid scratches in the surface. 

- Clean the surface with 

Methyl Ethyl Ketone (MEK) 

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© 2014 by EMBRAER - All rights reserved. 
~EMBRAER ALERT 

SERVICE BULLETIN 

(b) Applicable for the Spring (Steel) 

CORROSION 

LEVEL 

Surface oxidation or 

discoloration: 

Light Corrosion: 

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 superficial the Fork End Bore 

without evidence of material immediately after the 

removal. Use suitable tool like accomplishment of PART I 

acrylic/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 

acrylic/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 like 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 results found during these inspections be informed to 

your local EMBRAER representatives or offices. 

H. 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 readily available when 

necessary. 

This estimate does not include the sealant, paint, or adhesive curing time. 

-Access opening: 1.0 man- hour. 

-Inspection: 1.5 man- hours. 

-Modification: 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.REFERENCES 

T.O. 1 C95A-2-5- "Maintenance Manual"- Flight Controls. 

T.P. 27-00-01 /702- Component Maintenance Manual. 

SB No.: 110-27-A095 

PAGE: 6 ALERT 

Copyright © 2014 by EMBRAER- All rights reserved. 

DATE: 21/Aug/2014 

REVISION No.: 
~EMBRAER ALERT 

SERVICE BULLETIN 

K. OTHER PUBLICATIONS AFFECTED 

None. 

2. MATERIAL INFORMATION 

A. MATERIAL - PRICE AND AVAILABILITY 

(1) MATERIAL AVAILABLE FROM EMBRAER 

None. 

(2) MATERIAL AVAILABLE FROM OTHER VENDORS 

None. 

B. INDUSTRY SUPPORT INFORMATION 

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. 

A TT.: 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 
~EMBRAER ALERT 

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 only if it is damaged. 

Applicable for Rudder Trim Tab Actuator PN 11 OP2-506-1 0-09-37 

NEWPN DESCRIPTION OLDPN QTY DISP/ 

Note 

11 OP2-506-1 0-09-29-02 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 is 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-inhibiting compound 

Spec. MIL-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.: 
~EMBRAER ALERT 

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 EMBRAER - 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, 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." 

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 complete definition. 

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. 

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 Controls. 

(2) On the Bench, disassemble 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) Clean the components with the aid 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: 10 ALERT 

Copyright © 2014 by EMBRAER - All rights 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 oxidation 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 EMBRAER- All rights reserved. 
~EMBRAER ALERT 

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) Reinstall the Rudder Trim Tab Actuator to the aircraft following the instructions 

of T.O. 1 C95A-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 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. 

(5) Reinstall the Rudder Trim Tab Actuator to the aircraft following the instructions 

of T.O. 1 C95-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 EMBRAER- All rights reserved. 

DATE: 21/Aug/2014 

REVISION No.: 
~EMBRAER ALERT 

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 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 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 

TRANSMITTAL 

BOX 

(REF.) 

DET.A 

RUDO:R TRIM 

TABACTUATCR 

RUDDER TRIM 

TABACTUATCR 

(REMOVE AND REINSTALL) 

B 

! --------------------------------------------------------------------------------------------- 0 _______________ _____ ;, ~URE 1

. RUDDER TRIM TAB ACTUATOR INSPECTION 

SB No.: 110-27-A095 

PAGE: 14 

. (SHEET 01 OF 02) 

ALERT 

Copyright © 2014 by EMBRAER- All rights reserved. 

DATE: 21/Aug/2014 

REVISION No.: 
~EMBRAER ALERT 

SERVICE BULLETIN 

1 ~---------------------------------------------------------------------------------- -------------- ----- -- ----------

I ' 

I ' 

\. \ 

\ 

-·1 

L~ 

[h 

FORK END 

(INSPECT THE INTERNAL 

AND EXTERNAL SURFACE) 

~ FORK END 

(INSPECT THE INTERNAL 

AND EXTERNAL SURFACE) 

NEOPRENE SLEEVE 

(REF) 

.,.,..--.,.,.-- -- ·- ·1 ....... ,.-· I _____ .,. ..... -""·- ! 

-- I 

_,-·-----·- ! -- SPRING 1 

-·-·-·-· (INSPECT) i .,.,..- """ ~"""p i 

__ _ ..... ,..

-""·-.-·-·-·-·-· R v ___ ! J 

- - i 

-- ~-~~ 

·~(n}\ 0 ·- ~· -·-~~ 

v- 0 

DET.B 

I 

1 [h FORK END 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 
~EMBRAER SERVICE BULLETIN EVALUATION 

THE PURPOSE OF THIS FORM 1$ TO COLLECT DATA THAT 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 BRASILEIRA DE AERONAUTICA S.A. 

TECHNICAL PUBLICATIONS 

AV. BRIG. FARIA LIMA, 2170 

SAO JOSE DOS CAMPOS - SP - 12227-901 

BRASIL 

Fax: ++ 55 12 3927-7546 

e-mail: service.bulletin@embraer.com.br 

sa Title: I SB: (Number I Rev.) 

Operator: I Aircraft serial number affected: {per SB effectivity list) 

PRE-ACCOMPLISHMENT EVALUATION: (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 (Explain below) 

- - - [ I UNECONOMICAL 

I I SERVICE EXPERIENCE DOES NOT JUSTIFY [ I WILL NOT BE ACCOMPLISHED: [ I OPERATIONAL ENVIRONMENT DOES NOT JUSTIFY 

I I OTHER (Explain below) 

POST-ACCOMPLISHMENT EVALUATION: (Check applicable squares below) 

ESTIMATED MANPOWER: [ I OK [ I NOT OK (Explain below) 

MATERIAL & KITS: [ I OK [ I NOT OK (Explain below) 

ACCOMPLISHMENT INSTRUCTIONS: [ I OK I I NOT OK (Explain below) 

FIGURES: [ I OK [ I NOT OK (Explain below) 

SB GENERAL EVALUATION: I I OK [ I NOT OK (Explain below) 

COMMENTS: (Bulletin quality/ Difficulties found at the time of incorporation! Suggested improvements! Other) 

Organization: I Fax: I Phone: 

E-mail: 

Address: I Prepared by: (Name/ Title) J Date: 

ENS-003393