EMB-500 - Embraer

ÀREA DE NÃO INTERFERÊNCIA 

TM 

EMB-500 

GROUND HANDLING 

AND 

SERVICING HANDBOOK 

GHSH-3260 

31 OCTOBER 2008 

REVISION 12 - 24 FEBRUARY 2011 

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TO: HOLDERS OF PUBLICATION No. GHSH-3260 - “GROUND HANDLING 

AND SERVICING HANDBOOK”, APPLICABLE TO EMB-500 AIRCRAFT. 

REVISION No.12 DATED FEBRUARY 24/11 

HIGHLIGHTS 

Pages which have been added, revised, or deleted by the current revision are indicated 

by an asterisk, on the List of Effective Pages. 



HIGHLIGHTS Page 1 of 2 

Feb 24/11 

Copyright © by EMBRAER S.A - All rights reserved - See title page for details.

GROUND HANDLING AND 


CHAPTER 

SECTION PAGE DATE 

SUBJECT 

CHAPTER 


SUBJECT 

FRONTMATTER 

LOEP * LEP-1 ............. Feb 24/11 

LOEP * LEP-2 ............. Feb 24/11 

LOEP * LEP-3 ............. Feb 24/11 

LOEP...........................* LEP-4 ..Blank.. Feb 24/11 

LOEA............................ LEA-1 ............. Dec 05/08 

LOEA............................ LEA-2 ..Blank.. Oct 31/08 

INTRODUCTION ...... INTRO-1 ............ Oct 09/09 

INTRODUCTION....... INTRO-2 ............ Feb 13/09 





INTRODUCTION ...... INTRO-7 ............ Feb 13/09 



INTRODUCTION....... INTRO-10 .......... Feb 13/09 

INTRODUCTION....... INTRO-11 .......... Feb 13/09 

INTRODUCTION....... INTRO-12 Blank. Feb 13/09 

PROCEDURE 

TOC................................. 001 .............. Feb 13/09 

TOC................................. 002 ............. Dec 05/08 

TOC................................. 003 ............. Dec 05/08 

TOC................................. 004 .. Blank.. Dec 05/08 

TOC.......................... Del 005 .......... Dec 05/08 

TOC........................... Del 006 Blank.. Dec 05/08 

07-10-00-580-801-A.. Del 201 ............. Dec 05/08 

07-10-00-580-801-A.. Del 202 ............. Dec 05/08 

07-10-00-580-801-A.. Del 203 .............. Dec 05/08 

07-10-00-580-801-A.. Del 204 ............. Dec 05/08 

07-10-00-580-802-A.. Del 201 ............. Dec 05/08 

07-10-00-580-802-A.. Del 202 ............. Dec 05/08 

07-10-00-580-803-A.. Del 201 ............. Dec 05/08 

07-10-00-580-803-A.. Del 202 ............. Dec 05/08 

07-10-00-580-803-A.. Del 203 ............. Dec 05/08 

07-10-00-580-803-A.. Del 204 ............. Dec 05/08 

07-10-00-580-803-A.. Del 205 ............. Dec 05/08 

07-10-00-580-803-A.. Del 206 .. Blank.. Dec 05/08 

07-10-00-580-804-A.. Del 201 ............. Dec 05/08 

07-10-00-580-804-A.. Del 202 ............. Dec 05/08 

07-10-00-580-804-A.. Del 203 ............. Dec 05/08 

07-10-00-580-804-A.. Del 204 .. Blank.. Dec 05/08 

09-10-01-500-801-A........ 201 .............. Oct 09/09 




09-10-01-500-801-A........ 205 .............. Apr 17/09 


09-20-01-500-801-A.. Del 201 ............. Dec 05/08 


09-20-01-500-801-A.. Del 203 .............. Dec 05/08 






10-10-00-500-801-A........ 203 ............. Dec 05/08 







10-10-00-500-801-A........ .210 .. Blank.. Oct 09/09 

10-10-00-500-802-A........ 201 .............. Apr 17/09 

10-10-00-500-802-A........ 202 .. Blank.. Feb 13/09 

10-10-00-500-802-A.. Del 203 .............. Feb 13/09 

10-10-00-500-802-A.. Del 204 .. Blank.. Feb 13/09 

10-20-00-500-801-A........ .201 .............. Oct 09/09 

10-20-00-500-801-A........ .202 .............. Oct 31/08 

10-20-00-500-801-A ....... . 203............... Oct 31/08 

10-20-00-500-801-A ....... . 204............... Oct 31/08 

10-30-00-500-801-A ....... 201.............. Oct 09/09 





10-30-00-500-801-A ....... . 206...Blank.. Oct 09/09 

10-30-00-500-802-A ....... 201............... Apr 17/09 

10-30-00-500-802-A ....... 202............... Oct 09/09 

10-30-00-500-802-A ....... 203.............. Feb 13/09 

10-30-00-500-802-A ....... 204............... Feb 13/09 

10-30-00-500-802-A ....... 205............... Feb 13/09 

10-30-00-500-802-A ....... 206...Blank...Feb 13/09 

10-30-00-500-802-A . Del 207............... Feb 13/09 

10-30-00-500-802-A . Del 208...Blank...Feb 13/09 

12-11-00-650-801-A........ 301............... Jun 16/09 

12-11-00-650-801-A........ 302............... Feb 13/09 

12-11-00-650-801-A........ 303............... Feb 13/09 

12-11-00-650-801-A........ 304.............. Dec 05/08 

12-11-00-650-802-A........ 301............... Oct 31/08 

12-11-00-650-802-A........ 302.............. Aug 14/09 

12-11-00-650-802-A........ 303............... Oct 31/08 

12-11-00-650-802-A........ 304............... Oct 31/08 

12-11-00-680-801-A........ 301.............. Dec 05/08 

12-11-00-680-801-A........ 302............... Jun 16/09 

12-11-00-680-801-A........ 303............... Oct 31/08 

12-11-00-680-801-A........ 304...Blank... Oct 31/08 

12-12-00-210-801-A ....... 301............... Jun 16/09 

12-12-00-210-801-A ....... 302............... Feb 13/09 

12-12-00-210-801-A ....... 303............... Feb 13/09 

12-12-00-210-801-A ....... 304...Blank.. Feb 13/09 

12-12-00-612-801-A ....... 301.............. Dec 05/08 

12-12-00-612-801-A ....... 302............... Jun 16/09 

12-12-00-612-801-A ....... 303............... Oct 31/08 

12-12-00-612-801-A ....... 304...Blank.. Oct 31/08 

12-13-00-610-801-A . Del 301.............. Dec 05/08 

12-13-00-610-801-A . Del 302...Blank.. Dec 05/08 

12-13-00-610-802-A . Del 301.............. Dec 05/08 

12-13-00-610-802-A . Del 302.............. Dec 05/08 

12-13-00-610-802-A . Del 303.............. Dec 05/08 

12-13-00-610-802-A . Del 304.............. Dec 05/08 

12-13-00-610-802-A . Del 305.............. Dec 05/08 

12-13-00-610-802-A . Del 306...Blank.. Dec 05/08 

12-14-00-610-801-A .......* 301.............. Feb 24/11 

12-14-00-610-801-A .......* 302.............. Feb 24/11 

12-14-00-610-801-A .......* 303.............. Feb 24/11 

12-14-00-610-801-A .......* 304.............. Feb 24/11 

12-14-01-610-801-A ....... 301.............. Dec 11/09 

12-14-01-610-801-A ....... 302............... Apr 17/09 

12-14-01-610-801-A ....... 303............... Apr 17/09 

12-14-01-610-801-A ....... 304............... Apr 17/09 

12-14-02-610-802-A . Del . 301.............. Dec 05/08 

12-14-02-610-802-A . Del . 302.............. Dec 05/08 

12-14-02-610-802-A . Del . 303.............. Dec 05/08 

12-14-02-610-802-A . Del . 304.............. Dec 05/08 

12-14-03-610-802-A . Del . 301.............. Dec 05/08 

12-14-03-610-802-A . Del . 302.............. Dec 05/08 

12-14-03-610-802-A . Del . 303.............. Dec 05/08 

12-14-03-610-802-A . Del . 304.............. Dec 05/08 

12-14-04-610-801-A . Del . 301.............. Dec 05/08 

12-14-04-610-801-A . Del . 302.............. Dec 05/08 

12-14-04-610-801-A . Del . 303.............. Dec 05/08 

12-14-04-610-801-A . Del . 304...Blank.. Dec 05/08 

12-15-03-600-801-A .......* 301.............. Feb 24/11 

12-15-03-600-801-A .......* 302.............. Feb 24/11 

12-15-03-600-801-A ....... 303............... Oct 31/08 

12-15-03-600-801-A . ....... 304...Blank.. Dec 05/08 

12-16-00-610-801-A . Del . 301.............. Dec 05/08 

12-16-00-610-801-A . Del . 302.............. Dec 05/08 

12-16-00-610-801-A . Del . 303.............. Dec 05/08 

12-16-00-610-801-A . Del . 304.............. Dec 05/08 

12-23-00-100-801-A ....... 301.............. Aug 14/09 

Pages revised or added by current revision are indicated by an asterisk (*). Pages deleted by the current revision 

are indicated by (Del)*. Pages deleted by the previous revision are indicated by (Del). 



EFFECTIVITY: ALL 

LIST OF EFFECTIVE PAGES 

Page LEP-1 

Rev.12- FEB 24/11 




CHAPTER 


SUBJECT 

CHAPTER 


SUBJECT 



12-23-00-100-801-A........ 302 .............. Aug 14/09 

12-23-00-100-801-A........ 303 .............. Aug 14/09 

12-23-00-100-801-A........ 304 .............. Aug 14/09 

12-23-00-100-801-A........ 305 .............. Aug 14/09 

12-23-00-100-801-A........ .306 ...Blank.. Jun 16/09 

12-23-00-100-802-A........ 301 .............. Oct 09/09 

12-23-00-100-802-A........ 302 .............. Oct 09/09 

12-23-00-100-802-A........ 303 .............. Oct 09/09 

12-23-00-100-802-A........ 304 .............. Oct 09/09 

12-23-00-100-802-A........ 305 .............. Oct 09/09 

12-23-00-100-802-A........ 306 .............. Oct 09/09 

12-23-00-100-802-A........ 307 .............. Oct 09/09 

12-23-00-100-802-A........ 308 .............. Oct 09/09 

12-23-00-100-802-A........ 309 .............. Oct 09/09 

12-23-00-100-802-A........ 310 .............. Oct 09/09 

12-23-00-100-802-A........ 311 .............. Oct 09/09 

12-23-00-100-802-A........ 312 .............. Oct 09/09 

12-23-00-100-802-A........ 313 .............. Oct 09/09 

12-23-00-100-802-A........ 314 .............. Oct 09/09 

12-23-00-100-802-A........ 315 .............. Oct 09/09 

12-23-00-100-802-A........ 316 .............. Oct 09/09 

12-23-00-100-802-A........ 317 .............. Oct 09/09 

12-23-00-100-802-A........ 318 .............. Oct 09/09 

12-23-00-100-802-A........ 319 .............. Oct 09/09 

12-23-00-100-802-A........ 320 .. Blank... Jun 16/09 

12-31-00-660-801-A.. Del..301 ............. Dec 05/08 

12-31-00-660-801-A.. Del..302 ............. Dec 05/08 

12-31-00-660-801-A.. Del..303 ............. Dec 05/08 

12-31-00-660-801-A.. Del..304 ............. Dec 05/08 

12-31-00-660-801-A.. Del..305 ............. Dec 05/08 

12-31-00-660-801-A.. Del..306 ............. Dec 05/08 

12-31-00-660-801-A.. Del..307 ............. Dec 05/08 

12-31-00-660-801-A.. Del..308 ............. Dec 05/08 

12-31-00-660-801-A.. Del..309 ............. Dec 05/08 

12-31-00-660-801-A.. Del..310 ............. Dec 05/08 

12-31-00-660-801-A.. Del..311 ............. Dec 05/08 

12-31-00-660-801-A.. Del..312 ............. Dec 05/08 

12-31-00-660-801-A.. Del..313 ............. Dec 05/08 

12-31-00-660-801-A.. Del..314 ............. Dec 05/08 

12-31-00-660-801-A.. Del..315 ............. Dec 05/08 

12-31-00-660-801-A.. Del..316 ............. Dec 05/08 

20-00-00-910-801-A........ 201 .............. Oct 09/09 

20-00-00-910-801-A........ 202 .............. Apr 17/09 

20-00-00-910-801-A........ 203 ...............Feb 13/09 

20-00-00-910-801-A........ 204 ...............Feb 13/09 

20-40-02-910-801-A........ 201 .............. Oct 09/09 

20-40-02-910-801-A........ 202 .............. Oct 31/08 

20-40-02-910-801-A........ 203 .............. Oct 09/09 

20-40-02-910-801-A........ 204 .............. Oct 09/09 

24-36-01-000-801-A........ 401 .............. Jun 16/09 

24-36-01-000-801-A........ 402 .............. Oct 31/08 

24-36-01-000-801-A........ 403 ............. Dec 05/08 

24-36-01-000-801-A........ 404 ............. Dec 05/08 

24-36-01-000-801-A........ 405 ............. Dec 05/08 

24-36-01-000-801-A........ 406 .. Blank.. Dec 05/08 

24-36-01-000-802-A........ 401 .............. Aug 14/09 

24-36-01-000-802-A........ 402 .............. Aug 14/09 

24-36-01-000-802-A........ 403 .............. Aug 14/09 

24-36-01-000-802-A........ 404 .............. Aug 14/09 

24-36-01-400-801-A........ 401 .............. Dec 11/09 

24-36-01-400-801-A........ 402 .............. Oct 31/08 

24-36-01-400-801-A........ 403 .............. Oct 31/08 

24-36-01-400-801-A........ 404 .. Blank....Oct 31/08 

24-36-01-400-802-A........ 401 .............. Jun 16/09 

24-36-01-400-802-A........ 402 ............. Dec 05/08 

24-36-01-400-802-A........ 403 ............. Dec 05/08 

24-36-01-400-802-A........ 404 .............. Oct 31/08 

24-41-00-860-801-A........ 201 .............. Apr 17/09 

24-41-00-860-801-A........ 202 .............. Apr 17/09 

24-41-00-860-801-A........ 203 ............. Dec 05/08 

24-41-00-860-801-A........ 204 .............. Dec 05/08 

24-41-00-860-802-A........ 201 .............. Apr 17/09 

24-41-00-860-802-A........ 202 .............. Apr 17/09 

24-41-00-860-802-A ....... 203.............. Dec 05/08 

24-41-00-860-802-A ....... 204.............. Dec 05/08 

27-04-01-710-801-A ....... 501............... Oct 31/08 

27-04-01-710-801-A ....... 502.............. Dec 11/09 

27-04-01-710-801-A ....... 503............... Oct 31/08 

27-04-01-710-801-A ....... 504...Blank....Oct 31/08 

28-00-00-910-801-A ....... 201............... Oct 31/08 

28-00-00-910-801-A ....... 202............... Oct 31/08 

28-00-00-910-801-A ....... 203............... Oct 31/08 

28-00-00-910-801-A ....... 204...Blank... Oct 31/08 

29-10-00-901-803-A ....... 201............... Jun 16/09 

29-10-00-901-803-A ....... 202............... Oct 31/08 

29-10-00-910-801-A ....... 201............... Jun 16/09 

29-10-00-910-801-A ....... . 202............... Oct 31/08 

29-11-00-710-801-A.. Del . 501.............. Dec 05/08 

29-11-00-710-801-A.. Del . 502.............. Dec 05/08 

32-00-00-910-801-A ....... 201............... Oct 31/08 

32-00-00-910-801-A ....... 202............... Oct 31/08 

32-43-00-710-801-A . Del . 501.............. Dec 05/08 

32-43-00-710-801-A . Del . 502.............. Dec 05/08 

32-43-00-710-801-A . Del . 503.............. Dec 05/08 

32-43-00-710-801-A . Del . 504...Blank.. Dec 05/08 

32-45-00-210-801-A . ....... 601............... Oct 31/08 

32-45-00-210-801-A ....... 602............... Oct 31/08 

32-45-00-210-801-A ....... 603............... Oct 31/08 

32-45-00-210-801-A ....... 604............... Oct 31/08 

32-45-00-210-801-A ....... 605............... Oct 31/08 

32-45-00-210-801-A ....... 606... Blank....Oct 31/08 

32-63-00-860-801-A . Del . 201.............. Dec 05/08 

32-63-00-860-801-A . Del . 202.............. Dec 05/08 

32-63-00-860-802-A . Del . 201.............. Dec 05/08 

32-63-00-860-802-A . Del . 202.............. Dec 05/08 

45-45-00-970-801-A . Del . 201.............. Dec 05/08 

45-45-00-970-801-A . Del . 202.............. Dec 05/08 

45-45-00-970-801-A . Del . 203.............. Dec 05/08 

45-45-00-970-801-A . Del . 204.............. Dec 05/08 

45-45-00-970-801-A . Del . 205.............. Dec 05/08 

45-45-00-970-801-A . Del . 206.............. Dec 05/08 

52-00-00-800-801-A . Del . 201.............. Dec 05/08 

52-00-00-800-801-A . Del . 202.............. Dec 05/08 

52-00-00-800-801-A . Del . 203.............. Dec 05/08 

52-00-00-800-801-A . Del . 204.............. Dec 05/08 

52-00-00-800-801-A . Del . 205.............. Dec 05/08 

52-00-00-800-801-A . Del . 206.............. Dec 05/08 

52-00-00-800-801-A . Del . 207.............. Dec 05/08 

52-00-00-800-801-A . Del . 208.............. Dec 05/08 

52-00-00-800-801-A . Del . 209.............. Dec 05/08 

52-00-00-800-801-A . Del . 210.............. Dec 05/08 

52-00-00-800-801-A . Del . 211.............. Dec 05/08 

52-00-00-800-801-A . Del . 212.............. Dec 05/08 

52-00-00-800-801-A . Del . 213.............. Dec 05/08 

52-00-00-800-801-A . Del . 214.............. Dec 05/08 

52-00-00-800-801-A . Del . 215.............. Dec 05/08 

52-00-00-800-801-A . Del . 216...Blank.. Dec 05/08 

53-05-00-800-801-A . Del . 101.............. Dec 05/08 

53-05-00-800-801-A . Del . 102.............. Dec 05/08 

71-00-00-910-801-A . Del . 201.............. Dec 05/08 

71-00-00-910-801-A . Del . 202.............. Dec 05/08 

71-00-00-910-801-A . Del . 203.............. Dec 05/08 

71-00-00-910-801-A . Del . 204.............. Dec 05/08 

71-00-00-910-801-A . Del . 205.............. Dec 05/08 

71-00-00-910-801-A . Del . 206.............. Dec 05/08 

71-00-00-910-801-A . Del . 207.............. Dec 05/08 

71-00-00-910-801-A . Del . 208.............. Dec 05/08 

APPENDIX 

GSE TOC..................... .. TOC-1........... Dec 05/08 

GSE TOC........................ TOC-2 .Blank.. Oct 31/08 

GSE 001 ................. .Del......... 1 ........... Dec 05/08 

GSE 001 ................. .Del......... 2 ........... Dec 05/08 

GSE 001 ................. .Del......... 3 ........... Dec 05/08 

GSE 001 ................. .Del......... 4 .Blank. Dec 05/08 





Page LEP-2 

Rev.12- FEB 24/11 




CHAPTER 


SUBJECT 

CHAPTER 


SUBJECT 

GSE 002.................. Del ........ 1........... Dec 05/08 

GSE 002.................. Del ........ 2........... Dec 05/08 

GSE 003................... .............. 1............ Oct 31/08 

GSE 003................... .............. 2............ Oct 31/08 

GSE 008................... .............. 1............ Oct 31/08 

GSE 008................... .............. 2............ Oct 31/08 

GSE 009................... .............. 1............ Oct 31/08 

GSE 009................... .............. 2............ Oct 31/08 

GSE 016......................... ........ 1........... Dec 05/08 

GSE 016......................... ........ 2........... Dec 05/08 

GSE 016......................... ........ 3........... Dec 05/08 

GSE 016......................... ........ 4.Blank . Dec 05/08 

GSE 022................... .............. 1............ Oct 31/08 

GSE 022................... .............. 2............ Oct 31/08 

GSE 023......................... ........ 1........... Dec 05/08 

GSE 023......................... ........ 2........... Dec 05/08 

GSE 024.................. Del ........ 1........... Dec 05/08 

GSE 024.................. Del ........ 2........... Dec 05/08 

GSE 026................... .............. 1............ Oct 31/08 

GSE 026................... .............. 2............ Oct 31/08 

GSE 027................... .............. 1............ Oct 31/08 

GSE 027................... .............. 2............ Oct 31/08 

GSE 029................... .............. 1............ Oct 31/08 

GSE 029................... .............. 2............ Oct 31/08 

GSE 030................... .............. 1............ Oct 31/08 

GSE 030................... .............. 2............ Oct 31/08 

GSE 042.................. Del ........ 1........... Dec 05/08 

GSE 042.................. Del ........ 2........... Dec 05/08 

CPA .............................. ..CON-1........... Feb 13/09 

CPA .............................. ..CON-2........... Feb 13/09 







Page LEP-3/4 

Rev.12- FEB 24/11 

Copyright © by Embraer S.A. All rights reserved – See title page for details.



THIS MANUAL IS APPLICABLE TO ALL PHENOM 100 

EXECUTIVE JETS IN OPERATION. 


BEFORE USING, MAKE SURE THIS HARDCOPY IS THE LATEST ISSUE. 


GHSH List of Effective Aircraft 

Page LEA-1/2 

Rev.01 - DEC 05/08 




INTRODUCTION 





GHSH INTRODUCTION 

1. General 

A. This handbook is intended to assist ground handling and servicing personnel 

that are not familiar with the Embraer Phenom 100 aircraft. The Embraer Phenom 

100 Aircraft Maintenance Manual contains detailed maintenance or 

inspection information. 

B. The source of all information in this manual is, basically, the information in the 

publications listed below: 

(1) Aircraft Maintenance Manual (AMM). 

(2) Illustrated Tool and Equipment Manual (ITEM). 

(3) Consumable Products Catalog (CPC). 

C. In case of conflict between this manual and the AMM, ITEM and / or CPC, the 

AMM, ITEM and / or CPC shall take precedence. 

2. The improvement of methods and development of new techniques by the operators 

are contributions to be included in this manual. If you have suggestions or 

need any assistance regarding maintenance technical publications, please contact 

us at: 

• contact.center@embraer.com - For contributions/request for assistance regarding 

technical subjects related to Maintenance Technical Publications, GSE, 

Service Bulletins, AIPC and SRM I; 

• distrib@embraer.com.br - For assistance regarding purchase and distribution 

of manuals; 

• cdrom.support@embraer.com.br - For assistance regarding Digital Technical 

Publications contained in electronic media. 

3. It is vital that the operators commit themselves to keeping this manual update by 

strictly inserting the revised pages in the proper locations according to the last 

revision of manual available in the FlyEmbraer site. 

4. The GHSH is composed by (Figure 1): 

A. The front matter: 

(1) Front Page 

Shows the manufacturer's masthead, identification of the manual, the initial 

issue date, and revision number and date. 

(2) Customer Comment Form 

(3) List of Effective Aircraft 

Provides a cross-reference tabulation of Aircraft Commercial Designation, 

Customer Aircraft Number, and Manufacturer Serial Number. 

(4) List of Effective Pages: 

Lists all chapters and their list of effective pages with the latest issue dates. 

NOTE: • Pages revised or added by the current revision are indicated 




INTRODUCTION 

Page INTRO-1 

Rev.06 - OCT 09/09 






(5) Title of Introduction 

(6) Introduction 

by an asterisk (*). 

• Pages deleted by the current revision are indicated by del *. 

Pages deleted by the previous revision are indicated by del. 

B. GHSH Procedures 

The GHSH procedures section is composed by: 

(1) Procedures Title Page 

(2) Table of Contents 

(3) GHSH Procedures 

(a) The GHSH procedures are organized into chapters: 

Chapter Number 

Table 1 – GHSH Chapters 

9 Towing & Taxing 

Chapter Title 

10 Parking, Mooring, Storage & Return to Service 

12 Servicing 

20 Standard Practices-Airframe 

24 Electrical Power 

27 Flight Controls 

28 Fuel 

29 Hydraulic Power 

32 Landing Gear 

(b) PDF Page Identification and Numbering 

The GHSH task numbering is shown in the top of the body page and in 

the skirting board page, and is composed as follows: 

1. Top of Body Page 

GHSH TASK 12-11-00-650-801-A 

Elements 1, 2, and 3 comprise the equipment identifier. The fourth 

element is the three-digit function code, which defines the maintenance 

function being performed by tasks. The fifth element is a 

three-digit number used to create unique numbers for all tasks, which 

are similarly numbered through the first four elements. Tasks are 

numbered from 801 through 999. The sixth element is an alphabetic 

identifier (task) used to uniquely identify differences in configuration, 

methods / techniques, variations of standard practices applications, 

etc. 

2. Skirting Board Page 

The task numbering shown in the skirting board page shows the 

body page numbering followed by the page block numbering, that is 


INTRODUCTION 

Page INTRO-2 

Rev.02 - FEB 13/09 




used to inform the type of procedure to be executed. 

12-11-00-650-801-A/300 

The table below lists the pageblocks and their respective names: 

Table 2 - GHSH PageBlocks 

PageBlock Name 

PageBlocks 

System Description Section 000 

Component Location 100 

Maintenance Practices 200 

Servicing 300 

Removal/Installation 400 

Adjustment 500 

Inspection 600 

Cleaning 700 

Repairs 800 

C. GHSH Appendixes 

(1) Appendix Title Page 

(2) GSE (Ground Support Equipments) Title Page 

(3) TOC GSE 

(4) GSE (Ground Support Equipments) 

(a) The GSE Appendix is composed of the GSE's referenced in the GHSH 

tasks.The GSE Appendix is arranged in GSE number increasing order. 

For information about other GSE's used in the Phenom 100, please 

check the Illustrated Tool and Equipment Manual (ITEM). 

(5) Consumable Products Title Page 

(6) Consumable Products 

(a) The Consumable Products Appendix is composed of a table which 

lists all the consumable products referenced in the GHSH tasks. The 

Consumable Products Appendix is arranged in part number alphabetical 

order. The Consumable Products Appendix provides the following 

information about consumables: 

1. PART NUMBER Column 

This column provides the product part number and/or trade name. 

When the product does not have a part number, its specification is 

repeated in this column. 

2. SPECIFICATION Column 

This column gives the specification with which the material must 

comply. A simple dash in this column denotes that the product does 

not meet any specification or that only the product referred to in this 

catalog shall be used. 

3. DESIGNATION Column 




INTRODUCTION 

Page INTRO-3 

Rev.02 - FEB 13/09 






This column presents a brief description of the material. 

4. SUPPLIER Column 

This column lists the names of the most usual suppliers of the 

material. 

5. SHELF LIFE Column 

This column gives the period of time (in months) between the fabrication 

date and the last date when the conditions for use of the 

product are still assured, providing the material is packed and 

stored as specified. 

6. DANGER CLASS Column 

This column gives the product danger class according to the International 

Air Transportation Association (IATA) - Dangerous Goods 

Regulations. 

7. STORAGE CODE Column 

This column lists codes referring to the conditions that assure the 

proper preservation of the consumable products during their storage 

period. 

NOTE: The information from the manufacturer/supplier shall 

always prevail over the one herein. 

The table Storage Conditions gives the codes associated with the 

conditions under which each product must be stored. This table 

presents the following requirements: 

a. Temperature 

This column gives the proper ambient temperature, both in Celsius 

and Fahrenheit degrees, to store a product. It may give a 

range of temperature (4 to 38°C, for example) or the maximum 

allowable temperature (25°C (maximum), for example). 

b. Away From 

This column gives the products/conditions from which the item 

should stay away in order to guarantee its adequate preservation. 

The following table gives the storage conditions. 

Table 3 - Storage Code 

Storage Code Temperature Away From 

01 4 to 38°C (39 to 100°F) 

Fuel, Ozone and/or spark generating 

devices Moisture, Dust, Oil, 

Grease, Direct Sunlight, Fluorescent 

Light, Air in Circulation. 

02 25°C (MAX.)(77°F (MAX)) 

Sources of heat, Ozone and/or 

spark generating devices, Oxidants, 

Dust, Oil, Fuel, Water, 

Direct Sunlight, Air in Circulation. 


INTRODUCTION 

Page INTRO-4 

Rev.02 - FEB 13/09 




Table 3 – Storage Code (Continued) 

Storage Code Temperature Away From 

04 4 to 38°C (39 to 100°F) 

07 4 to 38°C (39 to 100°F) 

08 4 to 38°C (39 to 100°F) 

09 25°C (MAX)(77°F (MAX)) 

10 4 to 38°C (39 to 100°F) 

11 25°C (MAX)(77°F (MAX)) 

12 4 to 38°C (39 to 100°F) 

13 4 to 38°C (39 to 100°F) 

14 4 to 38°C (39 to 100°F) 

15 4 to 38°C (39 to 100°F) 

Sources of heat, Spark generating 

devices, Oxidants, Dust, Direct 

Sunlight. 


devices, Oxidants, Oxygen cylinders. 


devices, Oxidants, Corrosive acid, 

Direct sunlight. 

Sources of heat, Dust, Oil,Grease, 


Sources of heat, Dust, Oil, 

Grease, Direct sunlight. 


spark generating devices, Dust, 

Vibrations, Magnetic fields, Air in 

circulation. 


devices, Oxidants, Corrosive 

base, Direct sunlight. 


devices, Oxidants, Direct sunlight. 


devices, Oxidants, Direct sunlight. 


devices, Corrosive acid and base, 


16 According to local regulatory authorities and manufacturer. 

17 25°C (MAX)(77°F (MAX)) 

50 According to local manufacturer/supplier. 

99 4 to 38°C (39 to 100°F) 

Electrostatic fields, Magnetic 

fields, Dust, Direct sunlight. 


spark generating devices, Dust, 

Vibrations, Magnetic fields, Corrosive 

acid and base, Oxidants, 

Flammable liquids, Explosives. 



The figure 1 shows the GHSH manual structure. 


INTRODUCTION 

Page INTRO-5 

Rev.02 - FEB 13/09 


TM 

Copyright 2008 by EMBRAER − Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document 

shall not be copied or reproduced, whether in whole or in part, in any form or by any means without the express 

without permission of Embraer. 

GHSH−3260 

31 OCTOBER 2008 

written authorization of Embraer. The information, technical data, designs and drawings disclosed in this docu− 

ment are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party 



EMB−500 



GROUND HANDLING 

AND 



LIST OF EFFECTIVE AIRCRAFT 


INTRODUCTION TITLE 

INTRODUCTION 

PROCEDURES TITLE PAGE 

PROCEDURES TABLE OF CONTENTS 

PROCEDURES 

APPENDIX TITLE PAGE 

GROUND SUPPORT EQUIPMENT APPENDIX 

TITLE PAGE 

GSE APPENDIX TABLE OF CONTENTS 

GROUND SUPPORT EQUIPMENTS 

CONSUMABLE PRODUCTS APPENDIX 

TITLE PAGE 

CONSUMABLE PRODUCTS APPENDIX 

EM500ENGHSH000018A.DGN 

GHSH Manual Structure 

Figure 1 


INTRODUCTION 

Page INTRO-6 

Rev.02 - FEB 13/09 




D. Revisions 

(1) Revisions to the GHSH are issued for the whole manual. 

(2) A list of effective pages is provided for the whole manual. The pages that 

are revised, added, or deleted by the current revision will be identified on 

the list of effective pages by an asterisk. 

(3) When texts or art in illustrations are revised, a black bar will appear in the 

page left-side margin, beside the revised, added, or deleted material. For 

PDF files, a bar beside the page number or the section title and the printing 

date indicates that neither the text nor the illustration has been 

changed, but the material has been relocated to a different page or a 

totally new page has been added. 

D. Tools, Equipment and Auxiliary Items 

(1) Aircraft Zones (Figure 2) 

The GHSH procedures may refer to a zone to give the references necessary 

for the identification of the service areas or components. The figure 2 

illustrates the zones location. 




INTRODUCTION 

Page INTRO-7 

Rev.02 - FEB 13/09 







EMB − 500 

Aircraft Zones 

Figure 2 


INTRODUCTION 

Page INTRO-8 

Rev.02 - FEB 13/09 




(2) Consumable Materials 

The consumable material used in the GHSH procedures are describe in 

the Consumable Appendix, localized in the end of the manual. 

(3) Circuit Breakers (Figure 3) (Figure 4) 

The circuit breakers used in the GHSH procedures appear in the follow 

way: 

"TOILET FLUSH-RHCBP (SHED BUS)" 

where: 

(a) TOILET FLUSH identifies the designation; 

(b) RHCBP identifies the location of the circuit breaker. On the example, 

the circuit breaker is located in right (RH) circuit breaker panel (CBP). 

(c) (SHED BUS) identifies the bus. 

The figure 3 and figure 4 shows the circuit breaker panels location on the 

aircraft. 




INTRODUCTION 

Page INTRO-9 

Rev.02 - FEB 13/09 




A 



LH LATERAL 

CONSOLE 

DC BUS 2 

B 

HOT BUS 1 

EMERGENCY BUS 

EMERGENCY BUS 

RH LATERAL 

CONSOLE 

LH CB PANEL 

HOT BUS 2 

A 

DC BUS 1 

RH CB PANEL 

B 

SHED BUS 


RH and LH Circuit Breaker Panels Location 

Figure 3 


INTRODUCTION 

Page INTRO-10 

Rev.02 - FEB 13/09 




ZONES 

241 

242 

B 

E 

A 

ZONE 

211 

B 

LH LATERAL 

CONSOLE 

D 

A 

C 

RH LATERAL 

CONSOLE 



LPDU 

D 

RPDU 

E 

EPDU 

C 


EPDU, RPDU and LPDU Location 

Figure 4 


INTRODUCTION 

Page INTRO-11/12 

Rev.02 - FEB 13/09 




PROCEDURES 





GHSH PROCEDURES - TABLE OF CONTENTS 

SUBJECT 

CHAPTER 

SECTION 

SUBJECT 

TASK NUMBER 

PAGE 

Towing & Taxing 

Towing with Towbar - 

Procedure......................................... 09-10-01-500-801-A 201 

Parking, Mooring, Storage & 

Return to Service 

Parking - Maintenance 

Practices .......................................... 10-10-00-500-801-A 201 

Parking in Cold Weather Condition - 

Maintenance Practices..................... 10-10-00-500-802-A 201 

Aircraft Mooring - Maintenance 


Return-to-Service after Normal 

Parking - Maintenance Practices ...... 10-30-00-500-801-A 201 

Cold Weather - Maintenance 


Servicing 

Fuel Tank - Refueling ....................... 12-11-00-650-801-A 301 



Fuel Tank - Defueling ....................... 12-11-00-650-802-A 301 

Fuel Tank - Draining......................... 12-11-00-680-801-A 301 

Engine Oil Level - Visual 

Check............................................... 12-12-00-210-801-A 301 

Engine Oil - Filling............................ 12-12-00-612-801-A 301 


GHSH Procedures - Table of Contents 

Page TOC-1 

Rev.02 - FEB 13/09 

Copyright © by EMBRAER S.A. - All rights reserved - See title page for details.



SUBJECT 

CHAPTER 

SECTION 

SUBJECT 

TASK NUMBER 

PAGE 

Servicing of NLG and MLG 

Tires ................................................. 12-14-00-610-801-A 301 



Servicing of Emergency/Parking 

Brake Accumulator........................... 12-14-01-610-801-A 301 

Waste Tank - Servicing .................... 12-15-03-600-801-A 301 

External Aircraft - Cleaning .............. 12-23-00-100-801-A 301 

Internal Aircraft - Cleaning ............... 12-23-00-100-802-A 301 

Standard Practices-Airframe 

Aircraft Maintenance Safety 

Procedures....................................... 20-00-00-910-801-A 201 

Static Grounding - Standard 

Practices .......................................... 20-40-02-910-801-A 201 

Electrical Power 

Main Battery - Removal.................... 24-36-01-000-801-A 401 

Main Battery - Disconnection ........... 24-36-01-000-802-A 401 

Main Battery - Installation................. 24-36-01-400-801-A 401 

Main Battery - Connection................ 24-36-01-400-802-A 401 

Energization of the Aircraft with an 

External DC Power Supply - Aircraft/System 

Configuration............... 24-41-00-860-801-A 201 

Aircraft De-energization - Aircraft/ 

System Configuration....................... 24-41-00-860-802-A 201 

Flight Controls 

Trim Actuator Controller - 

Operational Test............................... 27-04-01-710-801-A 501 



Page TOC-2 

Rev.01 - DEC 05/08 




SUBJECT 

CHAPTER 

SECTION 

SUBJECT 

TASK NUMBER 

PAGE 

Fuel 

Fuel - Maintenance 

Practices .......................................... 28-00-00-910-801-A 201 

Hydraulic Power 

Main Hydraulic System - 

Depressurization .............................. 29-10-00-910-801-A 201 

Main Hydraulic System - 

Pressurization .................................. 29-10-00-901-803-A 201 

Landing Gear 

Landing-Gear Safety Pin - 

Standard Practices........................... 32-00-00-910-801-A 201 

NLG and MLG Tires - General 

Visual Inspection .............................. 32-45-00-210-801-A 601 





Page TOC-3/4 

Rev.01 - DEC 05/08 




GHSH TASK 09-10-01-500-801-A 

1. Towing With Towbar - Procedure 

A. General 

(1) The aircraft towing is the usual procedure when it is necessary to move 

the aircraft on the ground. 

B. Job Set-Up 

WARNING: MAKE SURE THAT THE AIRCRAFT IS IN A SAFE 

CONDITION BEFORE YOU DO THE MAINTENANCE 

PROCEDURES. THIS IS TO PREVENT INJURY TO 

PERSONS AND/OR DAMAGE TO THE EQUIPMENT. 

(1) Make sure that the landing gear safety pins are installed (GHSH TASK 32- 

00-00-910-801-A/200). 

CAUTION: REMOVE ALL TOOLS, EQUIPMENT, AND MATERIALS 

FROM THE TOWING AREA. MAKE SURE THAT THE AREA 

IS CLEAN. 

(2) Before you start the towing operation, remove the unnecessary objects 

from around the aircraft. 

(3) Make sure that the aircraft is in a safe condition before you start the towing 

procedure. 

NOTE: If the aircraft had a flat tire while parked or moving on the 

ground, you must replace this tire because it is permanently 

damaged. 

WARNING: BEFORE YOU DO THE TOWING PROCEDURE, MAKE 

SURE THAT THE LOWER PART OF THE TORQUE LINK 

IS DISCONNECTED. IF YOU DO NOT OBEY THIS 

PRECAUTION, DAMAGE TO THE NLG AND INJURY TO 

PERSONS CAN OCCUR. 

(3) Disconnect the torque link from the nose landing gear (Figure 201) as follows: 

(a) Remove the quick disconnect pin from the torque link. 

(b) Install the torque link to the upper support. 

(c) Install the quick disconnect pin. 

(4) Install the towbar head (GSE 026 ) to the towbar (GSE 027) (Figure 202). 

NOTE: Make sure that the shear pin of the towbar head is in good 

condition. 

(5) Connect the towbar head (GSE 026) to the Nose Landing Gear tow fitting 

as follows: 

(a) Pull the towing lever. 

(b) Connect the towbar head to the nose landing gear tow fitting. 



EFFECTIVITY: ALL 09-10-01-500-801-A/200 

Page 201 

Rev.06 - OCT 09/09 






(c) Release the towing lever to lock the towbar head to the nose landing 

gear tow fitting. 

(6) Connect the other end of the towbar (GSE 027) to the tractor. 

C. Towing with Towbar 

CAUTION: OBEY THE SAFETY PRECAUTIONS DURING THE TOWING 

OPERATIONS: A TECHNICIAN MUST STAY IN THE COCK- 

PIT TO SET THE EMERGENCY/PARKING BRAKE, IF NEC- 

ESSARY. ALL PERSONS IN THE COCKPIT MUST BE IN A 

SEAT AND THE SEATBELT MUST BE FASTENED. 

(1) Pressurize the main hydraulic system (GHSH TASK 29-10-00-901-803-A/ 

200). 

(2) Make sure that there is a technician in the cockpit to set the emergency 

parking brake if necessary. 

(3) Release the emergency/parking brake. 

(4) Tow the aircraft slowly straight ahead before you try to do a turn. The maximum 

speed recommended for aircraft towing is the walking speed. 

NOTE: • During the towing operation, use the emergency/parking 

brake only if the towbar (GSE 027) uncouples from the towing 

vehicle or from the aircraft. 

• If the aircraft emergency/parking brake is applied during the 

towing operation, regardless of the speed, do a check of the 

integrity of the shear pin of the towbar head (GSE 026). 

• If during the towing operation, the towbar head (GSE 026) 

shear pin is broken, do the inspection of the NLG (Nose 

Landing Gear) for damage and replacement of the shear pin 

,as given in step (5) of this procedure. 

(5) Nose Landing Gear - Inspection (Figure 203) 





(a) Make sure that the wheel chocks are in position against the landing 

gear wheels. 

(b) In the cockpit, make sure that the landing-gear control lever is in the 

DN position. 

(c) Use a flashlight and a mirror, if necessary, to examine these components 

of the NLG: 

• Main fitting 

• Sliding tube 

• Retraction actuator 


Page 202 

Rev.06 - OCT 09/09 




• Locking stay 

• Downlock release actuator 

• Downlock proximity switch 

• Bonding jumpers 

• Torque links 

• Shimmy damper 

• Drag brace 

• Doors 

• Door mechanism 

• Grounding Cable 

NOTE:Make sure that the grounding cable end touches the 

ground. If it does not touch the ground, adjust its length. 

(d) Make sure that these components show no signs of: 

• Mechanical damage 

• Unsatisfactory installation 

• Surface corrosion 

• Damage to the surface finish 

• Loose or missing items 

(e) Examine these components for leakage of hydraulic fluid: 

• Sliding tube 

• Downlock release actuator 

• Shimmy damper 

• Retraction actuator 

D. Job Close-Up 

CAUTION: AFTER YOU SET THE PARKING BRAKE, IT WILL BE 

EFFECTIVE FOR APPROXIMATELY 48 HOURS OR UNTIL 

THE PRESSURE IS LOST. THE PARKING BRAKE MUST BE 

RELEASED AFTER A MAXIMUM OF 48 HOURS BECAUSE 

THERE IS A RISK THAT THE BRAKE LININGS STICK TO 

THE BRAKE DISCS WITH POSSIBLE DAMAGE TO THE 

AIRCRAFT. 

(1) Apply the emergency/parking brake. 

(2) Remove the towbar (GSE 027) from the tractor (Figure 202). 

(3) If the nose wheel is not in the zero-degree position, align it with the zerodegree 

reference in the NLG. 

(4) Remove the towbar head (GSE 026) from the NLG tow fitting. 

(5) Connect the torque link back to its initial position as follows (Figure 201): 

(a) Remove the quick disconnect pin from the upper support. 

(b) Connect the torque link to the NLG. 

(c) Install the quick disconnect pin of the torque link. 




Page 203 

Rev.06 - OCT 09/09 




A 

ZONE 

711 



TORQUE−LINK 

LOCKING PIN 

SUPPORT 

TORQUE−LINK 

LOCKING PIN 

A 

TORQUE LINK 

B 

B 

EM500ENGHSH090001B.DGN 

Torque Link - Towing 

Figure 201 


Page 204 

OCT 31/08 




A 

ZONE 

711 

A 

TOWBAR 

(GSE 027) 

B 

SHEAR PIN 

B 

TOWBAR 

HEAD 

(GSE 026) 

STOP BOLT 

TOWING 

LEVER 

C 

TOWBAR 

HEAD 

(GSE 026) 



C 

SAFETY BOLT 


Towbar - Towing 

Figure 202 


Page 205 

Rev.03 - APR 17/09 




DRAG 

BRACE 

RETRACTION 

ACTUATOR 

B 

A 

MAIN 

FITTING 



ZONES 

711 

713 

714 

DOOR 

DOWN LOCK 

ACTUATOR 

BONDING JUMP 

DOWN LOCK 

SPRING 

BONDING JUMP 

DOOR MECHANISM 

DOOR 

SLIDING TUBE 

A 

DOWN LOCK 

PROXIMITY SWITCH 

BONDING 

JUMP 

TORQUE 

LINKS 

GROUND 

CABLE 

B 


NLG - General Visual Inspection 

Figure 203 


Page 206 

OCT 31/08 





1. Normal Parking - Maintenance Practices 

A. General 

(1) This task gives the procedure to do the aircraft normal parking. 

(2) Normal parking includes overnight parking and parking from 0 to 7 days. 

B. Job Set-Up 

(1) Make sure that there is sufficient room in the aircraft parking area, to permit 

its movement. 

NOTE: We recommend that the aircraft be sheltered in the hangar. 

(2) Tow the aircraft into the position specified for parking (GHSH TASK 09-10- 

01-500-801-A/200). 

NOTE: • If possible, park the aircraft headed into the wind. 

• Before you park the aircraft, move it in straight line for 

approximately 3 meters. This will remove all torsional 

stresses applied to the landing gear components and tires 

during a turn. 

(3) Make sure that the flaps are in neutral position. 

(4) Release the emergency/parking brake. 

(5) Make sure that the LG safety pins are installed. 

C. Normal Parking - Maintenance Practices 

(1) Put the wheel chocks against the LG wheels. 

(2) If the aircraft will stay parked outside the hangar, do as follows: 

CAUTION: IF UNFAVOURABLE WEATHER CONDITIONS SUCH AS 

THUNDERSTORMS AND STRONG WINDS ARE FORE- 

CAST, MAKE SURE THAT THE AIRCRAFT IS PROPERLY 

AND SAFELY PARKED. IF YOU DO NOT OBEY THIS PRE- 

CAUTION, DAMAGE TO THE AIRCRAFT CAN OCCUR. 

CAUTION:THE AIRCRAFT MUST BE SHELTERED IN THE HAN- 

GAR WHEN THERE ARE WIND VELOCITIES OF 65 

KNOTS OR MORE. IF YOU DO NOT OBEY THIS PRE- 

CAUTION, DAMAGE TO THE AIRCRAFT CAN OCCUR. 

(a) Look for the wind velocity chart best suitable for the floor condition in 

Figure 203, and, if the wind velocity is out of the limits, refer to AMM 

TASK 10-20-00-500-801-A/200 to moor the aircraft. 

NOTE: Perform frequent visual inspections of the mooring ropes 

and wheel chocks. 

(b) Install the cockpit transparency shade set (GSE 029). 




Page 201 

Rev.06 - OCT 09/09 






(c) Close the window shades. 

(d) Set the gust locks. 

CAUTION: MAKE SURE THAT ALL COVERS ARE IN GOOD CON- 

DITIONS, WITH NO DAMAGE AND FREE OF LINTS. IF 

YOU DO NOT OBEY THIS PRECAUTION, DAMAGE TO 

THIS EQUIPMENT CAN OCCUR. 

(e) Install the covers to these parts: 

1. Pitot probe (GSE 009). 

2. Pitot-static probe (GSE 003). 

3. Dual static port (GSE 008). 

4. Engine (GSE 030). 

(f) Cover the outlet and inlet openings that follow with a cotton fabric or 

equivalent attached to the aircraft skin with adhesive tape: 

1. Ram air inlet 

2. Ground cooling fan inlet. 

3. Ground cooling fan exhaust. 

(g) Close all the doors and access panels. 

(h) Make sure that wheel chocks are installed. 

(i) Where there are freezing or ice conditions, do the subsequent step: 

1. Remove, drain and storage the waste tank. Refer to GHSH TASK 

12-15-03-600-801-A/300. 

NOTE: For matter of hygiene, we recommend that the waste 

tank be serviced. 


Page 202 

Rev.06 - OCT 09/09 




ZONES 

430 

440 

ZONES 

223 

224 

E 

C 

G 

A 

ZONES 

711 

721 

731 

B 

TYPICAL 

WHEEL 

CHOCKS 

ZONE 

351 

B 

COCKPIT TRANSPARENCY 

SHADE SET (GSE 029) 

D 

A 

TYPICAL 

C 

D 



D 


Normal Parking - Maintenance Practices 

Figure 201 


Page 203 

Rev.01-DEC 05/08 




E 

C 

B 

A 



ZONES 

223 

224 

PLUG PROTECTION 

STATIC PORT GSE 008 

PITOT−STATIC COVER 

GSE 003 

PITOT COVER 

GSE 009 

C 

TYPICAL 

D 

E 

TYPICAL 

GUST LOCK 

SAFETY PIN 

PILOT CONTROL 

YOKE (REF.) 

C 

B 

E 

D 

A 

AILERON/ELEVATOR 

GUST LOCK 



Figure 202 - Sheet 1 


Page 204 

Rev.01-DEC 05/08 




F 

RAM AIR 

INLET (REF.) 

GROUND COOLING 

FAN INLET (REF.) 

RAM AIR 

INLET (REF.) 


FAN EXHAUST (REF.) 

F 

ENGINE COVERS 

(GSE 030) 

G 

RUDDER GUST 

LOCK HANDLE 

E 

ENGINE COVERS 

(GSE 030) 







Page 205 

Rev.01-DEC 05/08 






WIND (knot) 

65 

64 

63 

62 

61 

60 

59 

58 

57 

WEIGHT 

56 

55 

54 

4770 kgf 

53 

52 

51 

4500 kgf 

50 

49 


48 

47 

46 

45 

4000 kgf 

44 

43 


42 

41 

40 

39 

38 

37 

36 

35 

34 

33 

32 

31 

30 

29 

28 

27 

26 

3000 kgf 

25 

24 

23 


22 

21 

20 

0 20 25 30 35 40 45 50 55 

CG POSITION (% MAC) 

WIND VELOCITY VS. CG POSITION − DRY FLOOR 


Wind Velocity Charts 



Page 206 

Rev.06 - OCT 09/09 




WIND (knot) 

60 

59 

58 

57 

56 

55 

54 

53 

52 

51 

50 

49 

48 

47 

46 

45 

44 

43 

42 

41 

40 

39 

38 

37 

36 

35 

34 

33 

32 

31 

30 

29 

28 

27 

26 

25 

24 

23 

22 

21 

WEIGHT 

4770 kgf 



4000 kgf 


3000 kgf 


20 

15 20 25 30 35 40 45 50 55 


WIND VELOCITY VS. CG POSITION − WET FLOOR 







Page 207 

Rev.06 - OCT 09/09 






WIND (knot) 

60 

59 

58 

57 

56 

55 

54 

53 

52 

51 

50 

49 

48 

47 

46 

45 

44 

43 

42 

41 

40 

39 

38 

37 

36 

35 

34 

33 

32 

31 

30 

29 

28 

27 

26 

25 

24 

23 

22 

21 

20 

WEIGHT 

4770 kgf 



4000 kgf 


3000 kgf 


19 

18 

17 

16 

15 

15 20 25 30 35 40 45 50 55 


WIND VELOCITY VS. CG POSITION − SNOWY FLOOR 





Page 208 

Rev.06 - OCT 09/09 




35 

34 

33 

32 

WIND (knot) 

31 

30 

29 

28 

27 

26 

25 

24 

23 

22 

21 

20 

19 

18 

17 

16 

15 

14 

13 

12 

WEIGHT 

4770 kgf 



4000 kgf 


3000 kgf 


11 

10 

15 20 25 30 35 40 45 50 55 


WIND VELOCITY VS. CG POSITION − ICY FLOOR 







Page 209/210 

Rev.06 - OCT 09/09 





1. Normal Parking in Cold Weather Conditions - Maintenance Practices 

A. General 

(1) This task gives the procedure for normal parking in cold weather condition. 

(2) A cold weather condition is when the temperature is lower than 0°C 

(32°F). 

(3) Normal Parking in cold weather includes overnight parking. 

B. Job Set-Up 

(1) Obey the procedures given in GHSH TASK 10-10-00-500-801-A/200. 

C. Normal Parking in Cold Weather Condition - Maintenance Practices 

(1) If the parking area has ice or snow, put one of these items under the tires, 

as applicable: 

(a) A mat, or 

(b) A layer of thick sand or 

(c) Other applicable material. 

NOTE: This will prevent the freezing of the tires to the ground. 

CAUTION: WHILE THE AIRCRAFT IS PARKED, EXAMINE THE 

WINGS AND STABILIZERS AT REGULAR INTERVALS 

AND, IF NECESSARY, APPLY DEICING/ANTI-ICING 

FLUIDS TO THESE AREAS. YOU MUST ALSO EXAMINE 

FOR THE PRESENCE OF DEICING/ANTI-ICING FLUID 

RESIDUES IN HIDDEN PLACES OF THE WINGS AND 

STABILIZERS AND, IF NECESSARY, REMOVE THESE 

RESIDUES. IF YOU DO NOT OBEY THIS PRECAUTION, 

DAMAGE TO THE AIRCRAFT CAN OCCUR. 

CAUTION: REPETITIVE APPLICATION OF THICKENED DEICING/ 

ANTI-ICING FLUID CAN CAUSE THE FORMATION/ 

BUILDUP OF DRIED RESIDUES. DRIED RESIDUES CAN 

OCCUR WHEN SURFACES ARE TREATED BUT THE 

AIRCRAFT DOES NOT FLY SUBSEQUENTLY, AND IS NOT 

SUBJECT TO PRECIPITATION. AN APPROPRIATE 

INSPECTION AND CLEANING PROGRAM MUST BE 

ESTABLISHED. 

(2) Perform frequent visual inspections not to permit accumulation of snow or 

ice on the aircraft. 

(3) Make sure that the wheel chocks are installed to the LG wheels. 

(4) Make sure that you obeyed the procedures for waste tank given in GHSH 

TASK 10-10-00-500-801-A/200. 

(5) If the temperature is foreseen to be less than -18 °C (0 °F), remove the 

main battery (GHSH TASK 24-36-01-000-801-A/400). 


Page 201/202 

Rev.03 - APR 17/09 

Copyright © by EMBRAER S.A - All rights reserved - See title page for details. 






1. Aircraft Mooring - Maintenance Practices 

A. General 

(1) The mooring procedure must be performed only when required in GHSH 

TASK10-10-00-500-801-A/200 normal parking procedures. 

(2) This task gives the procedure to moor the aircraft. 

(3) There is one mooring point on each MLG, one on the NLG, and one on the 

rear fuselage. 

B. Job Set-Up 

(1) Tow the aircraft to the parking area where there are tie-down anchors 

(GHSH TASK 09-10-01-500-801-A/200). 

(2) Refer to Figure 201 for mooring points coordinates. 

(3) Do the procedures to make the aircraft safe for maintenance (GHSH TASK 

20-00-00-910-801-A/200). 

(4) Do the normal parking procedure (GHSH TASK 10-10-00-500-801-A/200). 

C. Mooring - Maintenance Practices (Figure 202) (Figure 203) 

CAUTION: THE AIRCRAFT MUST BE SHELTERED IN THE HANGAR 

WHEN THERE ARE WIND VELOCITIES OF 65 KNOTS OR 

MORE. IF YOU DO NOT OBEY THIS PRECAUTION, DAMAGE 

TO THE AIRCRAFT CAN OCCUR. 

(1) Moor the aircraft in the parking area with nylon rope. 

(2) Attach the nylon rope to the mooring point and attach the anchor with a 

bowline knot. 




10-20-00-500-801-A/200 

Page 201 

Rev.06 - OCT 09/09 




Y 

A 

D 



A’ 

NOTE: 

TO MARK THE TIEDOWN POINTS ON THE GROUND, USE THE NOSE LANDING 

GEAR WHEEL TIRE FOOT PRINT AS THE ZERO REFERENCE POINT. 

A 

A’ 

B 

B’ 

C 

C’ 

X 

B 

C 

B’ 

C’ 

NLG TIEDOWN POINTS 

X 

− 0.24m 

− 0.24m 

MLG TIEDOWN POINTS 

X 

+ 4.00m UP TO +4.20m 

+ 4.80m UP TO + 5.00m 

+ 4.00m UP TO + 4.20m 

+ 4.80m UP TO + 5.00m 

Y 

+ 0.44m 

− 0.44m 

Y 

+ 1.25m UP TO + 1.46m 

+ 1.25m UP TO + 1.46m 

− 1.25m UP TO − 1.46m 

− 1.25m UP TO − 1.46m 

D’ 

REAR FUSELAGE TIEDOWN POINTS 

X 

Y 

D 

D’ 

+ 9.20m UP TO + 9.50m 

+ 9.20m UP TO + 9.50m 

+ 0.70m UP TO + 0.90m 

− 0.70m UP TO − 0.90m 


Mooring Points Coordinates 

Figure 201 



Page 202 

OCT 31/08 




A 

ZONES 

321 

322 

D 

MOORING 

POINT 

NYLON 

ROPE 

B 

ZONES 

721 

731 

B 

TYPICAL 

C 

ZONE 

711 

MAIN LANDING 

GEAR (REF.) 

A 

NOSE LANDING 

GEAR (REF.) 

MOORING 

POINT 

NYLON ROPE 

MOORING 

POINT 

C 



D 

NYLON ROPE 


Mooring Points 

Figure 202 



Page 203 

OCT 31/08 




1 2 



3 

5 6 

BOWLINE 

KNOT 

4 

MOORING 

ATTACHMENT 

POINT 


Aircraft Mooring Ropes 

Figure 203 



Page 204 

OCT 31/08 





1. Return-to-Service after Normal Parking - Maintenance Practices 

A. General 

(1) This task gives the procedure to return the aircraft to service after normal 

parking. 

B. Return-to-Service after Normal Parking 

(1) Remove the wheel chocks. 

(2) Make sure that the LGCL is in down position. 

(3) Do the steps below if the aircraft is parked outside the hangar. 

(a) If applicable, unground the aircraft (GHSH TASK 10-20-00-500-801-A/ 

200). 

(b) Remove cockpit transparency shade set. 

(c) Release the gust lock. 

(d) Remove these covers from these parts: 

1. Pitot probe (GSE 009). 

2. Pitot-static probe (GSE 003). 

3. Dual static port (GSE 008). 

NOTE: Be careful when you remove the protective plug from 

the static port not to break it and let pieces of material 

stay inside the holes. 

4. Engine (GSE 030). 

CAUTION: MAKE SURE THAT YOU REMOVED THE COVERS AND 

ADHESIVE TAPES FROM THESE PARTS AND THERE 

IS NO OBSTRUCTION AND/OR FOREIGN OBJECT IN 

THEM. IF YOU DO NOT OBEY THIS PRECAUTION, 

MALFUNCTION OF THE SYSTEM CAN OCCUR. 

(e) Remove the covers and the adhesive tapes from these parts: 

1. Ground cooling fan inlet. 

2. Ground cooling fan exhaust. 

3. Ram air inlet. 

(f) Refill and install the waste tank, if applicable (GHSH TASK 12-15-03- 

600-801-A/300). 

(g) If the aircraft stayed parked for exactly 7 days, do this additional step: 

1. Drain the fuel tanks to check for presence of water (GHSH 

TASK12-11-00-680-801-A/300). 

(h) Tow the aircraft from the parking area (GHSH TASK 09-10-01-500- 

801-A/200). 

(i) Do a visual inspection of the pitot probe, pitot-static probe and staticport 

for: 

• Damage 





Page 201 

Rev.06 - OCT 09/09 




• Obstruction 

• Foreign objects 

(5) Make sure that there is no obstruction and foreign objects in the NACA air 

intakes of wing tanks. 

(6) Cycle the Landing Gear control lever and free-fall control handle two times 

to lubricate the manifold internal chambers. 





Page 202 

Rev.06 - OCT 09/09 




ZONES 

430 

440 

ZONES 

223 

224 

E 

C 

G 

A 

ZONES 

711 

721 

731 

B 

TYPICAL 

WHEEL 

CHOCKS 

ZONE 

351 

B 

COCKPIT TRANSPARENCY 

SHADE SET (GSE 029) 

D 

A 

TYPICAL 

C 

D 



D 


Aircraft Return-to-Service - Maintenance Practices 

Figure 201 



Page 203 

Rev.06 - OCT 09/09 




E 

C 

B 

A 



ZONES 

223 

224 

PLUG PROTECTION 

STATIC PORT GSE 008 

PITOT−STATIC COVER 

GSE 003 

PITOT COVER 

GSE 009 

C 

TYPICAL 

D 

E 

TYPICAL 

GUST LOCK 

SAFETY PIN 

PILOT CONTROL 

YOKE (REF.) 

C 

B 

E 

D 

A 

AILERON/ELEVATOR 

GUST LOCK 






Page 204 

Rev.06 - OCT 09/09 




F 

RAM AIR 

INLET (REF.) 


FAN INLET (REF.) 

RAM AIR 

INLET (REF.) 


FAN EXHAUST (REF.) 

F 

ENGINE COVERS 

(GSE 030) 

G 

RUDDER GUST 

LOCK HANDLE 

E 

ENGINE COVERS 

(GSE 030) 








Page 205/206 

Rev.06 - OCT 09/09 





1. Return-to-Service from Normal Parking in Cold Weather Condition - Maintenance 

Practices 

A. General 

(1) This task gives the procedures to return the aircraft to service after normal 

parking in cold weather condition. 

B. Job Set-Up 

(1) Obey the procedures given in GHSH TASK 10-30-00-500-801-A/200. 

C. Return-to-Service after Normal Parking in Cold Weather Condition Maintenance 

Practices 

(1) Remove ice, frost, slush, or snow from the aircraft surfaces (GHSH TASK 

12-23-00-100-801-A/300). 

(2) Install the batteries, if applicable (GHSH TASK 24-36-01-400-801-A/400). 

(3) Install the waste tank, and do the servicing (GHSH TASK 12-15-03-600- 

801-/300). 

(4) Do a check of the portable fire extinguishers as follows (Figure 201): 

(a) Open the clamp and remove the portable fire extinguisher. 

(b) Examine the portable fire extinguisher and make sure that the nozzle 

is not clogged. 

(c) Examine the extinguisher for exterior damage and corrosion. 

(d) Examine the frangible green seal. Make sure that it is in position and 

not damaged. 

(e) Install the portable fire extinguisher on its support and close the clamp 

that attaches it. 

(5) Do a check of the oxygen cylinder pressure. If necessary, do the servicing 

of the oxygen system. 

(a) Do the servicing of the oxygen system as follows (Figure 202): 


NOTE: Use aviator's breathing oxygen only (MIL-O-27210). 

1. Do a check of the overboard discharge indicator before you fill the 

oxygen cylinder to make sure that the oxygen did not discharge. 

2. Remove the protective cap from the fill valve. 

3. Connect the high pressure oxygen servicing regulator to the oxygen 

source. 

4. Connect the high pressure oxygen servicing regulator to the filling 

valve and make sure that there is no leak. 

5. Measure the ambient temperature (OAT). 

6. With the OAT, find the filling pressure. Refer to Figure 203. 

NOTE: The system filling pressure is 12755.3 kPa (1850 psig) 

at OAT of 21 °C (70 °F). 

7. Slowly fill the oxygen cylinder up to the recommended pressure. 

Copyright © by EMBRAER S.A. - All rights reserved - See title page for details. 


Page 201 

Rev.03 - APR 17/09 







NOTE: Slowly fill the system at a rate not greater than 1378.95 

kPa (200 psig) to prevent heating in the system and, 

consequently, an incorrect pressure indication. Refer to 

SAE AIR1059 - Transfilling and Maintenance of Oxygen 

Cylinders. 

8. Monitor the pressure gauge of the aircraft and of the high pressure 

oxygen servicing regulator. 

9. Wait at least 10 minutes to let the temperature of the oxygen cylinder 

become stable. 

10. Close the high pressure oxygen servicing regulator shutoff valve. 

11. Carefully disconnect and remove the high pressure oxygen servicing 

regulator from the fill valve to release the remaining pressure 

in the hose. 

(b) Do a leak test on the fill valve. 

1. Use fluid Leak-Tec 16-OX (Refer to Consumable Products Appendix) 

on the connection to do the leak test. If there are leaks, replace 

the fill valve. 

(6) Do a check of the engine oil level (GHSH TASK 12-12-00-210-801-A/300). 

(7) Do a check of the pressure of the MLG (Main Landing Gear) and NLG 

(Nose Landing Gear) tires (GHSH TASK 32-45-00-210-801-A/600). If 

necessary, do the servicing of the tires (GHSH TASK 12-14-00-610-801- 

A/300). 

(8) Do a check of the hydraulic system (AMM TASK 29-11-00-710-801-A/ 

500). If necessary, do the servicing of the hydraulic system (AMM TASK 

12-13-00-610-801-A/300) (AMM TASK 12-13-00-610-802-A/300). 

(9) Do a check to make sure that the primary control surfaces and the trim 

tabs operate correctly (GHSH TASK 27-04-01-710-801-A/500). 

(10) Do a check of the rain repellent coating. Please use the contact information 

given in the GHSH introduction for the applicable maintenance action. 

(11) Make sure that there is no obstruction and foreign objects in the NACA air 

intakes of the wing tanks. 

(12) If the aircraft stayed parked for exactly 7 days, do this additional step: 

(a) Drain the fuel tanks to check for presence of water GHSH TASK 12-11- 

00-680-801-A/300 

(13) To start the engines after normal parking in cold weather conditions, refer 

to engine starting procedure (cold weather). Please use the contact information 

given in the GHSH introduction for the applicable maintenance 

action. 



Page 202 

Rev.06 - OCT 09/09 




FRANGIBLE 

GREEN SEAL 

CLAMP 

A 

ZONE 

224 

BRACKET (REF.) 

A 

TYPICAL 

PORTABLE FIRE 

EXTINGUISHER 



01 

FIRE EXTINGUISHER GLYPH 

A 

01 


Portable Fire Extinguisher 

Figure 201 



Page 203 

Rev.02 - FEB 13/09 






A 

ZONES 

211 

B 

OVERBOARD DISCHARGE 

INDICATOR (REF.) 

OXYGEN PRESSURE 

REGULATOR 

C 

A 

FILL 

VALVE 

B 

PROTECTIVE 

CAP 

OXYGEN SOURCE (REF.) 

C 

OXYGEN PRESSURE 

GAUGE 


Oxigen Cylinder 

Figure 202 



Page 204 

Rev.02 - FEB 13/09 




CORRECTED OXYGEN PRESSURE 

AT 21°C (70°F) − PSI 

2200 

2100 

21°C 

INDICATED GAUGE PRESSURE − PSI 

2000 

1900 

1800 

1700 

1600 

1500 

1400 

1300 

1200 

1100 

1000 

900 

800 

700 

600 

500 

400 

300 

200 

−40 

−30 −20 −10 0 10 20 30 40 50 60 

CYLINDER COMPARTMENT TEMPERATURE − °C 

−40 −22 −4 −14 32 50 68 86 104 122 140 

1850 

1600 

1400 

1200 

1000 

800 

600 

400 

320 



CYLINDER COMPARTMENT TEMPERATURE − °F 


Chart 

Figure 203 



Page 205/206 

Rev.02 - FEB 13/09 




GHSH TASK 12-11-00-650-801-A 

1. Fuel Tank - Refueling 

A. General 

(1) This task gives the procedure to refuel the aircraft by gravity. 

(2) These fuels are approved by Embraer: 

• Fuel JET A-1 (Refer to Consumable Products Appendix) 

• Fuel JET A (Refer to Consumable Products Appendix) 

• Fuel JP-8 (Refer to Consumable Products Appendix) 

(3) These fuel additives are approved by Embraer: 

• DIETHYLENE GLYCOL MONOMETHYL ETHER (Refer to Consumable 

Products Appendix). 

• CORROSION INHIBITOR/LUBRICITY ADDITIVE - MIL-I-25017 (Refer 

to Consumable Products Appendix). 

B. Job Set-Up 

(1) Do the procedure to make the aircraft safe for maintenance (GHSH TASK 

20-00-00-910-801-A/200). 

(2) Do the procedure to make the aircraft safe for maintenance of the fuel system 

(GHSH TASK 28-00-00-910-801-A/200). 

(3) Statically ground the aircraft (GHSH TASK 20-40-02-910-801-A/200). 

NOTE: Make all grounding connections between the fuel source, aircraft, 

and fuel nozzle (refer to the requirements of the local 

regulatory authorities). 

(4) Energize the aircraft with an external DC power supply (GHSH TASK 24- 

41-00-860-801-A/200). 

(5) Open the LH and RH gravity filler caps: 

(a) Insert the key to the key lock port and turn it counterclockwise to the 

OPEN position. 

NOTE: It is not possible to remove the key from the key lock port 

when it is in the OPEN position. 

(b) Lift the lever of the gravity filler cap and turn it counterclockwise. 

(c) Pull the gravity filler cap from the gravity filler neck. 

C. Fuel Tank - Gravity Refueling 

WARNING: DO NOT LET JET FUEL AND LUBRICATING OILS TOUCH 

YOU. THESE FLUIDS CAUSE INJURY TO THE SKIN. 

(1) Put the fueling nozzle into the gravity filler neck. 

(2) Start the fueling operation and monitor the fuel quantity in the tank on the 

MFD fuel synoptic page or on the EICAS fuel indicating area. 

NOTE: The total fuel-tank capacity is approximately 1610 l (425 gal.). 

(3) Remove the fueling nozzle from the gravity filler neck after you have the 




12-11-00-650-801-A/300 

Page 301 

Rev.04 - JUN 16/09 






correct fuel quantity in the tank. 


CAUTION: WHEN YOU INSERT THE GRAVITY FILLER CAP INTO THE 

GRAVITY FILLER ADAPTER, MAKE SURE THAT THE LAN- 

YARD IS CORRECTLY POSITIONED INTO THE ADAPTER. 

IF YOU DO NOT OBEY THIS PRECAUTION, THE FILLER 

CAP CAN SMASH THE LANYARD AGAINST THE FILLER 

ADAPTER. 

(1) Close the LH and RH gravity filler caps: 

(a) Put the gravity filler cap on the gravity filler neck. 

(b) Turn the lever on the gravity filler cap clockwise and then turn the lever down. 

(c) Turn the key clockwise to the CLOSE position and remove the key from the 

key lock port. 

(2) De-energize the aircraft (GHSH TASK 24-41-00-860-802-A/200). 

(3) Remove the grounding cable(s) from the aircraft (GHSH TASK 20-40-02- 

910-801-A/200). 


12-11-00-650-801-A/300 

Page 302 

Rev.02 - FEB 13/09 




ZONE 

641 

A 

RIB 13 

RIB 12 

ZONE 

541 

A 

B 

RIB 12 

RIB 13 

C 

KEY LOCK 

PORT 

(REF.) 

B 

RIB 12 

RIB 13 

LEVER 

GRAVITY 

FILLER CAP 

GRAVITY 

FILLER CAP 

GRAVITY 

FILLER 

NECK 

A 

TYPICAL 

FUELING NOZZLE 

GRAVITY 

FILLER 

NECK 



C 

EM500ENGHSH120003C.DGN 

Fuel Tank - Refueling 

Figure 301 


12-11-00-650-801-A/300 

Page 303 

Rev.02 - FEB 13/09 




A 

B 

87.8 TO 87.8 

ATR 

2.5 

N1% 2.5 

EICAS 



LEFT TANK ANALOGUE 

FUEL QUANTITY BAR 

LEFT TANK 

FUEL QUANTITY 

FUEL USED 

XXX LB 

XFR 

TOTAL 

XXXX LB 

USED 

XXXX LB 

B 

LEFT FUEL 

QUANTITY 

TOTAL FUEL 

QUANTITY 

MFD 

(FUEL SYNOPTIC PAGE) 

XXX LB 

IGN 

OFF 

____ 

55.1 N2% 55.1 

TEMP XX C 

ELEC 

BATT1 

BATT2 

OAT-237 

ATR 

SPDBRK 

ON 

LG 

DN 

0V 

0V 

ITT C 

OIL PRES PSI 

FUEL 

TAKEOFF DATA SET 

C 

OIL TEMP C 

FF PPH 

FQ LB 

ALT 

A 

RATE 

DELTA-P 

LFE 

OXY 

____ 

CABIN 

FLAPS 

IGN 

OFF 

RIGHT TANK ANALOGUE 


RIGHT TANK 

FUEL QUANTITY 

TOTAL FUEL 

QUANTITY 

RIGHT FUEL 

QUANTITY 


Fuel Tank - Indicating 

Figure 302 


12-11-00-650-801-A/300 

Page 304 

Rev.01 - DEC 05/08 




GHSH TASK 12-11-00-650-802-A 

1. Fuel Tank - Defueling 

A. General 

(1) This task gives the procedure to defuel the aircraft by gravity. 

(2) The fuel tanks are defueled through the dump valves installed in the lowest 

part of each fuel tank, near the wing root and the centerline of the aircraft. 

B. Job Set-Up 


20-00-00-910-801-A/200). 


(GHSH TASK 28-00-00-910-801-A/200). 






41-00-860-801-A/200). 

(5) Open access door 523BL. 



(6) Remove the drain valve: 

(a) Put a container (1 gal.) below the drain valve. 

(b) Remove the screws from the drain valve. 

(c) Install two of the removed screws in the drain-valve removal nuts. 

(d) Pull the drain valve through the screws and remove the drain valve 

from the dump valve. 

NOTE: In cold weather, use a pair of pliers to help in the pulling of 

the drain valve. 

(e) Discard the face seal O-ring. 

C. Fuel Tank - Gravity Defueling 



(1) Install two of the screws removed from the drain valve in the dump valve 

180 degrees apart from each other. 

NOTE: Do not tighten the screws fully. Let a gap of approximately 2 - 

3 mm (0.08 - 0.12 in.) stay between the screw head and the 

dump valve flange. 




12-11-00-650-802-A/300 

Page 301 

OCT 31/08 






(2) Push up and turn counterclockwise the Defueling Tool (GSE 023) until it is 

held by the screws installed in the dump valve to open it and defuel the aircraft 

fuel tank. Refer to GSE Appendix. 

NOTE: Assemble a hose with proper diameter and a clamp together 

with the Defueling Tool (GSE 023) and put the other hose end 

into a suitable fuel container. 

CAUTION: DO NOT OPERATE THE FUEL PUMP WITHOUT FUEL (DRY 

OPERATION). DRY OPERATION WILL CAUSE DAMAGE TO 

THE SYSTEM. 

(3) Monitor the defueled quantity on the MFD fuel synoptic page or on the EICAS 

fuel indicating area. When you have the quantity of fuel to be defueled, turn 

clockwise and pull down the Defueling Tool (GSE 023) to remove it, close 

the dump valve and stop the aircraft fuel-tank defueling. 

(4) Remove the screws from the dump valve. 


(1) Lubricate a new face seal O-ring with grease DC-33 and install it to the 

drain valve. 



(2) Remove the screws from the drain valve. 

(3) Put the drain valve in its position, install the screws and torque them to 

1.36 - 1.69 N.m (12 - 15 lb.in). 

(4) Close the access door 523BL. 



910-801-A/200). 


12-11-00-650-802-A/300 

Page 302 

Rev.05- AUG 14/09 




DUMP VALVE 

DRAIN VALVE 

REMOVAL NUTS 

DUMP VALVE 

CLAMP 

A 

ZONES 

532 

632 

DRAIN 

VALVE 

B 

INTO FUEL CONTAINER 

01 TORQUE: 1.36 − 1.69 N.m (12 − 15 lb.in) 

01 

C 

SCREW (4x) 

SCREW (2x) 

DEFUELING 

TOOL 

HOSE 

LOWER WING 

SKIN 

E 

523 BL 

E 

O−RING 

A 

C 

D 

B 

D 



BEFORE USING, MAKE SURE THIS HARDCOPY IS THE LATEST ISSUE. 

Fuel Tank - Defueling 

Figure 301 


12-11-00-650-802-A/300 

Page 303 

OCT 31/08 




A 

B 

87.8 TO 87.8 

ATR 

2.5 

N1% 2.5 

EICAS 



LEFT TANK ANALOGUE 


LEFT TANK 

FUEL QUANTITY 

FUEL USED 

XXX LB 

XFR 

TOTAL 

XXXX LB 

USED 

XXXX LB 

B 

LEFT FUEL 

QUANTITY 

TOTAL FUEL 

QUANTITY 

MFD 

(FUEL SYNOPTIC PAGE) 

XXX LB 

IGN 

OFF 

____ 

55.1 N2% 55.1 

TEMP XX C 

ELEC 

BATT1 

BATT2 

OAT-237 

ATR 

SPDBRK 

ON 

LG 

DN 

0V 

0V 

ITT C 

OIL PRES PSI 

FUEL 

TAKEOFF DATA SET 

C 

OIL TEMP C 

FF PPH 

FQ LB 

ALT 

A 

RATE 

DELTA-P 

LFE 

OXY 

____ 

CABIN 

FLAPS 

IGN 

OFF 

RIGHT TANK ANALOGUE 


RIGHT TANK 

FUEL QUANTITY 

TOTAL FUEL 

QUANTITY 

RIGHT FUEL 

QUANTITY 


Fuel Tank - Indicating 

Figure 302 


12-11-00-650-802-A/300 

Page 304 

OCT 31/08 




GHSH TASK 12-11-00-680-801-A 

1. Fuel Tank - Draining 

A. General 

(1) This task gives the procedure to drain the fuel from the fuel tanks. 

(2) Examine the fuel drained from each tank for water and other contaminants. 

You will usually see water as a layer below the fuel or as small bubbles 

in the fuel. 

(3) Let the aircraft be stable for approximately 2h (hours) before you drain it. 

B. Job Set-Up 


20-00-00-910-801-A/200). 


(GHSH TASK 28-00-00-910-801-A/200). 





WARNING: USE AN EXPLOSION-PROOF HEAT GUN IN AREAS 

WHERE THERE IS RISK OF EXPLOSION. ADJUST THE 

TEMPERATURE OF THE HEAT GUN TO A VALUE LESS 

THAN THE FUEL SELF-IGNITION TEMPERATURE IN THE 

AIRCRAFT FUEL TANK. IF YOU DO NOT OBEY THIS 

PRECAUTION, AN EXPLOSION CAN OCCUR AND 

CAUSE INJURY TO PERSONS AND DAMAGE TO 

EQUIPMENT. 

CAUTION: THE HOT AIR TEMPERATURE FROM THE HEATING GUN 

MUST NOT BE MORE THAN 50 °C. TEMPERATURES 

ABOVE 50 °C CAN CAUSE DAMAGE TO THE AIRCRAFT 

SYSTEMS. 

(4) For cold weather conditions, do a check of the fuel temperature as follows: 

NOTE: When the tank temperature is less than 0 °C (32 °F), you must 

not directly operate the drain valve. At a temperature less than 

0 °C (32 °F), water can freeze around the drain valve and make 

the water flow impossible. If applicable, before you operate the 

drain valve to drain the wing tank, use a heat gun to apply heat 

to the drain valve area. 

• Energize the aircraft with an external DC power supply (GHSH TASK 24- 

41-00-860-801-A/200). 

• Do a check of the fuel temperature on the synoptic page. 




12-11-00-680-801-A/300 

Page 301 

Rev.01 - DEC 05/09 






• De-energize the aircraft (GHSH TASK 24-41-00-860-802-A/200). 

(5) Open the access door 523BL. 

C. Fuel Tank - Water Draining 



(1) Do the steps that follow to drain the water from the fuel tanks: 

(a) Use the fuel sampler (GSE 022) to push the drain valve poppet up to 

open the drain valve. Refer to GSE Appendix. 

NOTE: The drain valve closes when you remove the fuel sampler 

(GSE 022) from the drain valve poppet. Drain several 

times until the fuel in the container shows no water. Examine 

the collected fuel for contamination, especially at the 

fuel/water interface. 

(b) Remove the fuel sampler (GSE 022) after you drain a sufficient 

amount of fuel. 

NOTE: Make sure that the drain valve poppet is in the closed position 

and that there is no fuel leak. 

(2) Visually examine the collected fuel for contamination. If you see microorganisms 

or other unwanted matter in the fuel, use a Fuel Microorganisms 

Test Kit (Microb Monitor 2) to check for the presence of microorganisms. 

Obey the instructions of the test kit manufacturer. 

NOTE: Refer to the full instructions (aviation fuel item) to do the procedures. 

(4) If the Fuel Microorganisms Test Kit (Microb Monitor 2) detects the presence 

of microorganisms, please use the contact information given in the GHSH 

Introduction for the applicable maintenance action to wing fuel tank decontamination. 

WARNING: WHEN YOU DISCARD DANGEROUS CONSUMABLE 

MATERIALS, USE PROCEDURES THAT AGREE WITH 

LOCAL REGULATIONS. THESE MATERIALS CAN 

CAUSE INJURY TO PERSONS AND CONTAMINATION OF 

THE ENVIRONMENT. 

(5) Discard the collected fuel. 

(6) Do this procedure again for the other drain valve. 


(1) Close the access door 523BL. 


910-801-A/200). 


12-11-00-680-801-A/300 

Page 302 

Rev.04 - JUN 16/09 




A 

ZONES 

532 

632 

523 BL 

A 

DRAIN VALVE 

FUEL SAMPLE 

TEST TOOL 

B 



B 


Fuel Tank - Draining 

Figure 301 


12-11-00-680-801-A/300 

Page 303/304 

OCT 31/08 




GHSH TASK 12-12-00-210-801-A 

1. Engine Oil Level - Visual Check 

A. General 

(1) This task gives the procedure to do the check of the engine oil level. 

B. Job Set-Up 





WARNING: MAKE SURE THAT THERE WILL BE NO ACCIDENTAL 

OPERATION OF THE ENGINES. AN ACCIDENTAL 

OPERATION OF THE ENGINES CAN CAUSE INJURY TO 

PERSONS. 

(1) Wait for a minimum of ten minutes to elapse after engine shutdown before 

doing the oil level check. 

NOTE: If the engine oil system is empty following a draining operation 

or if the engine has been newly installed after an overhaul, fill 

the engine oil tank before checking the engine oil level (GHSH 

TASK 12-12-00-612-801-A/300). 

(2) Put the workstand in the work area. 

(3) Open the oil service door (Figure 301). 

C. Engine - Oil Level Check 

WARNING: OBEY ALL POWERPLANT SAFETY PRECAUTIONS. IF 

YOU ARE NOT CAREFUL DURING THE POWERPLANT 

MAINTENANCE, INJURY TO PERSONS AND/OR 

DAMAGE TO EQUIPMENT CAN OCCUR. 



(1) Do a check of the engine oil level. through the oil level sight glass mounted 

on the outboard side of the AGB (Acessory Gear Box). 

(2) If the engine oil level is not visible in the visual oil level sight glass, check 

the engine for external oil leaks and do repairs as necessary. If no evidence 

of an external oil leak is found, please use the contact information 

given in the GHSH Introduction for the applicable maintenance action. 

(3) If the engine oil level is between the "MIN" and "MAX" marks, no further 

action is required. 

(4) If oil tank contents are visible but below the "MIN" mark in the visual oil 

level indicator and there is no indication of excessive oil consumption, add 




12-12-00-210-801-A/300 

Page 301 

Rev.04 - JUN 16/09 




engine lubricating oil to the oil tank to between the MIN and MAX marks on 

the visual oil level sight glass (Figure 301). 


(1) Close the oil service door (Figure 301). 

(2) Remove the workstand from the work area. 




12-12-00-210-801-A/300 

Page 302 

Rev.02 - FEB 13/09 




OIL FILLER 

CAP 

B 

OIL LEVEL / 

FILLING PORT 

ACESSORY 

GEAR BOX 

OIL LEVEL 

SIGHT GLASS 

A 

A 

B 

433 AL 

443 AL 




Oil Level Check - Components Location 

Figure 301 


12-12-00-210-801-A/300 

Page 303/304 

Rev.02 - FEB 13/09 




GHSH TASK 12-12-00-612-801-A 

1. Engine Oil - Filling 

A. General 

(1) This task gives the procedures to fill the engine oil system. 

B. Job Set-Up 





WARNING: MAKE SURE THAT THERE WILL BE NO ACCIDENTAL 

OPERATION OF THE ENGINES. AN ACCIDENTAL 

OPERATION OF THE ENGINES CAN CAUSE INJURY TO 

PERSONS. 

(1) Do the procedures to make the aircraft safe for maintenance (GHSH TASK 

20-00-00-910-801-A/200). 

(2) Make sure that the engines are not operating during the oil filling procedure. 

(3) Put the workstand in the work area. 

(4) Open the oil servicing door (Figure 301). 

(5) Open the oil filler cap. 

C. Engine - Oil Filling 

WARNING: OBEY ALL POWERPLANT SAFETY PRECAUTIONS. IF 

YOU ARE NOT CAREFUL DURING THE POWERPLANT 

MAINTENANCE, INJURY TO PERSONS AND/OR 

DAMAGE TO EQUIPMENT CAN OCCUR. 



(1) Fill the engine oil system as follows: 

a) Make sure that the oil-tank drain plug is installed and tightened. 

b) Add oil until the oil level is at the MAX mark on the oil level sight glass 

(Figure 301). PW&C does not recommend the casual mixing of different 

approved brands of the same oil type or mixing of different types of oil. 

Refer to last revision of AFM (Airplane Flight Manual) to check the list of 

approved engine oils. 

NOTE: The engine oil capacity is 3.79 l. 

c) If deliberate approved oil brand mixing is necessary, or if inadvertent 

approved oil brand mixing occurred, please contact Embraer Support 

for the applicable maintenance action. 




12-12-00-612-801-A/300 

Page 301 

Rev.01- DEC 05/08 




d) If oils of brands not approved and/or other chemical substances were 

inadvertently put in the engine oil tank, please use the contact information 

given in the GHSH Introduction for the applicable action related to 

the restoration of the engine oil system. 

e) Close and lock the engine-oil filler cap (Figure 301). 


(1) Close the oil servicing door (Figure 301). 

(2) Remove the workstand from the work area. 




12-12-00-612-801-A/300 

Page 302 

Rev.04 - JUN 16/09 




OIL FILLER 

CAP 

B 

OIL LEVEL / 

FILLING PORT 

ACESSORY 

GEAR BOX 

OIL LEVEL 

SIGHT GLASS 

A 

A 

B 

433 AL 

443 AL 




Oil Level Check - Components Location 

Figure 301 


12-12-00-612-801-A/300 

Page 303/304 

OCT 31/08 




GHSH TASK 12-14-00-610-801-A 

1. Servicing of NLG and MLG Tires 

A. General 

(1) This task gives the procedure to do the check and servicing of the NLG 

and MLG tires. 

B. Job Set-Up 


20-00-00-910-801-A/200). 

WARNING: DO NOT GO NEAR HOT TIRES INSTALLED ON THE 

AIRCRAFT. IF IT IS NECESSARY TO MEASURE THE TIRE 

TEMPERATURE, GO NEAR THE TIRE FROM ITS FRONT, 

NOT FROM ITS SIDE. HIGH TEMPERATURE CAN CAUSE 

TIRE EXPLOSION. 

(2) Make sure that the temperature of the tire is the same as the ambient temperature. 

NOTE: If the aircraft had a flat tire while parked or moving on the 

ground, you must replace this tire because it is permanently 

damaged. 

(3) Remove the cap from the valve. 

C. Check of Landing-Gear Tire Pressure 

(1) Connect the tire pressure gauge to the valve. 

NOTE: • Tire pressure must be checked within limits daily or before 

the first flight of the day. 

• Only use a pressure gauge which is calibrated and uses the 

correct unit of measurement. 

CAUTION: DO NOT BLEED AIR FROM A HOT TIRE TO MAKE THE 

PRESSURE COME TO THE CORRECT LIMITS BECAUSE, 

AT AMBIENT TEMPERATURE, ITS PRESSURE WILL BE 

LESS THAN THE CORRECT OPERATIONAL PRESSURE. 

(2) The pressure must be at the values that follow with the aircraft on the 

ground (loaded): 

NOTE: For unloaded inflation pressure, decrease these values by 4% 

to get the equivalent loaded inflation pressure. 

(a) For the NLG, the pressure must be in the range from 772 to 807 kPa 

(112 to 117 psi). 

(b) For the MLG, the pressure must be in the range from 1145 to 1214 kPa 

(166 to 176 psi). 




12-14-00-610-801-A/300 

Page 301 

Rev.12- FEB 24/11 




(3) If the destination airport temperature is lower than the departure airport 

temperature with a difference greater than 27 °C (50 °F), increase the tire 

pressure by 1% for each 3 °C (5 °F) of difference. 

NOTE: The pressure is limited to 982 kPa (142 psi) for the NLG tire 

and to 1337 kPa (194 psi) for the MLG tire in loaded condition 

(aircraft on the ground). Do not increase the tire pressure to 

more than these values. 



(4) If the pressure in a tire is at (or near) the bottom limit of the range, it is 

recommended that the tire be inflated to the upper limit to prevent 

unnecessary removals at subsequent pressure checks. 

(5) For tire with less than the minimum service pressure, refer to this table: 

COLD TIRE PRESSURE 

95% to less than 100% of the minimum 

loaded service pressure. 

90% to less than 95% of the minimum 


Less than 90% of the minimum 


Table 301 - COLD PRESSURE SETTING 

[1] THE TIRE REMOVED BECAUSE OF LOW INFLATION PRESSURE MUST BE EXAMINED BY AN AUTHORIZED 

RETREADER TO MAKE SURE THAT THE CASING DID NOT HAVE INTERNAL DEGRADATION. IF IT DID, DIS- 

CARD THE TIRE. 

NOTE: If the tire pressure was fully lost during rolling, scrap the tire. 

(6) After the check, remove the tire pressure gauge from the valve. 

D. Service of Landing Gear Tire 

MAINTENANCE PROCEDURE 

Inflate to the specified service pressure 

again. 

Do a check of the tire/wheel assembly 

for the cause of the pressure loss. Inflate 

again and record this in the log book. 

Remove the tire/wheel assembly if the 

pressure loss is more than 5% and 

occurs again in 24 hours. [1] 

Remove the tire/wheel assembly from 

the aircraft. [1] 

WARNING: YOU MUST GO TO THE TIRE FROM THE FRONT OR 

BEHIND IN RELATION TO FLIGHT DIRECTION. NEVER 

STAY ON THE SIDE OF THE TIRE (IN FRONT OF THE 

WHEEL) DURING THIS PROCEDURE. 

WARNING: ONLY USE TIRE INFLATION EQUIPMENT WHICH HAS 

THE APPROVAL OF THE AIRCRAFT MANUFACTURER. 

IF YOU INFLATE AN AIRCRAFT TIRE DIRECTLY FROM A 

HIGH-PRESSURE STORAGE CYLINDER, AN 

EXPLOSION CAN OCCUR. 


12-14-00-610-801-A/300 

Page 302 

Rev.12- FEB 24/11 




(1) Set up the tire servicing gauge with the low pressure servicing regulator 

and nitrogen cylinder. 

(2) Connect the hose to the valve. 

(3) Inflate the tire and monitor the pressure with the pressure gauge. 

(4) Remove the hose from the valve. 


(1) Make sure that there is no leakage from the valve. 

(2) Install the cap to the valve. 

(3) Remove from the work area all tools, equipment, and materials that you 

used. 




12-14-00-610-801-A/300 

Page 303 

Rev.12- FEB 24/11 




A 

ZONE 

711 

A 



TIRE (REF.) 

VALVE 

ZONES 

721 

731 

A 

TYPICAL 

CAP 

2 

kg/Cm 

lbs/Pol 2 

TIRE SERVICING 

GAUGE 

TIRE PRESSURE 

GAUGE 

HOSE 

LOW PRESSURE 

SERVICING REGULATOR 

NITROGEN 

CYLINDER 


NLG and MLG Tires - Servicing 

Figure 301 


12-14-00-610-801-A/300 

Page 304 

Rev.12- FEB 24/11 


TM 



GHSH TASK 12-14-01-610-801-A 

1. Servicing of Emergency/Parking Brake Accumulator 

A. General 

(1) This section gives the procedure to charge the emergency/parking brake 

accumulator with nitrogen. 

B. Job Set-Up 


20-00-00-910-801-A/200). 

(2) Put wheel chocks at the landing gear wheels. 

(3) Open access door 191BL. 


41-00-860-801-A/200). 

(5) Release the pressure from the hydraulic system (GHSH TASK 29-10-00- 

910-801-A/200). 

C. Servicing of Emergency/Parking Brake System 

(1) Remove the cap from the charging valve. 

(2) Connect the hose of the nitrogen A-A-59503 cylinder with an outlet connection 

to the charging valve. 

(3) Open the cylinder valve and actuate the pressure regulating valve to 

adjust the pressure. 

(4) Open the charging valve. 

(5) Stop the nitrogen supply when the pressure shown on the synoptic page of 

the CAS is according to the chart. 

(6) Close the cylinder valve. 

(7) Close the charging valve. 

(8) Repeat the next two steps until the nitrogen pressure is stable at the value 

given in the chart. 

(9) Look at the synoptic page of the CAS to see if the nitrogen pressure 

stayed stable. 

NOTE: Wait 10 minutes for the nitrogen pressure to become stable. 

(10)If necessary, adjust the nitrogen pressure again until it stays stable. To do 

so, open the cylinder valve and actuate the pressure regulating valve to 

adjust the pressure. (Refer to the chart). 

(11)Use a torque wrench to tighten the charging valve nut from 5.6 to 6.8 N.m 

(50 to 60 lb.in). 

(12)Do an inspection of the charging valve for leakage. 

(13)Use a torque wrench to install and tighten the cap from 1.5 to 3.5 N.m 

(13.3 to 31.0 lb.in). 


CAUTION: NO NITROGEN LEAKS ARE PERMITTED. IF A LEAK IS 



12-14-01-610-801-A/300 

Page 301 

Rev.07 - DEC 11/09 



TM 





FOUND, IT MUST BE REPAIRED IMMEDIATELY. IF YOU DO 

NOT OBEY THIS PRECAUTION, THE SYSTEM WILL NOT 

OPERATE CORRECTLY. 

(1) Use a fluid Leak-Tec 16-OX to do a leakage check. 

(2) Do the operational test of the emergency/parking brake system as follows: 

(a) Pull the T-handle to the end of its stroke and turn it 90 degrees clockwise 

and do the following check: 

1. Make sure that the "EMERG/PRKG BRAKE" lamp on the main 

instrument panel comes on. 

2. Make sure that all pistons of the RH and LH brake assemblies are 

actuated. 

(b) Release the T-handle and do the following check: 

1. Make sure that the "EMERG/PRKG BRAKE" lamp on the main 

instrument panel goes off. 

2. Make sure that all pistons of the RH and LH brake assemblies are 

not actuated. 

(3) On the HYDRAULIC control panel, set the "HYD PUMP" switch to AUTO. 


(5) Close access door 191BL. 


12-14-01-610-801-A/300 

Page 302 

Rev.03 - APR 17/09 


TM 



191 AL 

B 

A 

01 

02 

03 

ZONE 

191 

01 03 

VALVE 

TORQUE: 5.6 − 6.8 N.m (50 − 60 lb.in) 

C 

TORQUE: 1.5 − 3.5 N.m (13.3 − 31.0 lb.in) 

HOSE 

02 

CAP 

C 

USE A FLUID LEAK−TEC TO DO A LEAKAGE CHECK 

B 

191 BL 

PRESSURE 

REGULATOR 

VALVE 

NITROGEN 

CYLINDER (REF.) 

A 

CYLINDER 

VALVE 





Servicing of Emergency/Parking Brake Accumulator 

Figure 301, Sheet 1 


12-14-01-610-801-A/300 

Page 303 

Rev.03 - APR 17/09

TM 





TEMP (°C) 

60 

50 

40 

30 

20 

10 

0 

−10 

−20 

−30 

−40 

−50 

MINIMUM 

NOMINAL 

140 

122 

104 

86 

68 

50 

32 

MAXIMUM 

14 

−4 

−22 

−40 

−58 

−60 

−76 

1100 1200 1300 1400 1500 1600 1700 

PRESSURE (psi) 


TEMP (°F) 

Servicing of Emergency/Parking Brake Accumulator 



12-14-01-610-801-A/300 

Page 304 

Rev.11 - NOV 26/10 




GHSH TASK 12-15-03-600-801-A 

1. Waste Tank - Servicing 

A. General 

(1) This task gives the procedure to do the servicing of the waste tank. 

B. Job Set-Up 


20-00-00-910-801-A/200). 

C. Waste Tank - Servicing 

WARNING: DO NOT LET THE TOILET SYSTEM CLEANER GET IN 

YOUR EYES, IN YOUR MOUTH OR IN YOUR SKIN. IF 

YOU DO, FLUSH YOUR EYES, MOUTH OR SKIN WITH 

WATER AND GET MEDICAL AID. THE TOILET SYSTEM 

CLEANER IS AN ACID AND CAN BURN YOU. 

WARNING: DO NOT GET WASTE FLUID ON YOUR SKIN, IN YOUR 

EYES OR MOUTH. PUT ON APPROVED PROTECTIVE 

CLOTHING, GOGGLES AND RUBBER GLOVES. IF 

WASTE FLUID TOUCHES YOU, HEALTH PROBLEMS 

CAN OCCUR. 

(1) Do the cleaning of the waste tank as follows: 

(a) Flush the toilet and clean it with a toilet brush. 

(b) Let the water rinse into the waste tank. 

(c) Open the circuit breaker and put a circuit breaker ring and tag on it: 

• TOILET FLUSH-RHCBP (SHED BUS) 

(d) Disconnect the electrical connection and put a protective cap on it. 

(e) Loosen the clamp and remove it from the flush hose. 

(f) Remove the flush hose from the hydraulic connection. 

(g) Disengage the hydraulic protective cap and put it on the hydraulic connection. 

(h) Put the clamp on the hydraulic protective cap and lock it. 

(i) Pull the manual closure valve. 

(j) Unlock the latch that attaches the waste tank to the toilet shroud box. 

(k) Pull the waste tank and remove it from the aircraft. 

(l) Open the cap and empty the waste tank suitable disposal facility. 

(m) Keep the cap open. 

(n) Fill the waste tank with 5 liters of water. 

(o) Close the cap. 

(p) Pivot and shake the waste tank to rinse all internal surfaces for at least 

1 minute. 

(q) Open the cap and empty the waste tank to a suitable disposal facility. 

(r) Completely clean the waste tank. 




12-15-03-600-801-A/300 

Page 301 

Rev.12- FEB 24/11 






(s) Wipe the waste tank exterior surfaces with a cloth moistened with 

clean water and disinfectant. 

NOTE: If it is necessary to store the empty waste tank, keep it in an 

environment where the temperature is more than 10 °C. 

This is to facilitate the next servicing of the waste tank. 

(2) Do the servicing of the waste tank as follows: 

(a) Prepare the precharge solution as follows: 

1. Put 3.5 liters of water in a separate container. 

2. Add the germicide deodorant 125 ml of URBAKTOL - CLEANER, 

BASE, VACUUM TOYLET SYSTEM LINES (URBAKTOL AF). 

(b) If you prefer, you can use DEJET as an alternative for germicide 

deodorant as follows: 

1. Put 3.55 liters of water in a separate container. 

2. Add the germicide deodorant 70 ml of DEJET - CLEANER, BASE, 

VACUUM TOYLET SYSTEM LINES. 

(c) Fill the waste tank with the precharge solution through the cap. 

(d) Close the cap. 

(e) Engage the waste tank into the toilet shroud box. 

(f) Remove the clamp from the hydraulic protective cap, and remove the 

hydraulic protective cap from the hydraulic connection. 

(g) Engage the flush hose on the hydraulic connection and install the 

clamp. 

(h) Put the clamp on the flush hose, and tighten the clamp. 

(i) Engage the hydraulic protective cap on the support. 

(j) Remove the protective cap from the electrical connection and connect it. 

(k) Lock the latch and push the manual closure valve. 

(l) Remove the circuit breaker ring and tag from this circuit breaker and 

close it: 

• TOILET FLUSH-RHCBP (SHED BUS) 

(m) Flush the toilet three times. 


CAUTION: TO PREVENT DAMAGE, EXAMINE ALL THE WORK AREAS 

TO MAKE SURE THAT YOU REMOVED ALL TOOLS AND 

EQUIPMENT AFTER YOU COMPLETED THE WORK. 

(1) Remove from the work area all tools, equipment, and materials that you used. 


12-15-03-600-801-A/300 

Page 302 

Rev.12- FEB 24/11 




AFT CABIN 

PARTITION (REF.) 

TOILET 

BOWL 

A 

ZONE 

242 

TOILET 

SHROUD 

BOX 

MAGNETIC 

PIN (2x) 

LATCH 

WASTE 

TANK 

HANDLE 

CAP 

B 

C 

LANYARD 

(REF.) 

WASTE 

TANK 

HYDRAULIC 

PROTECTIVE 

CAP 

HANDLE (2x) 

A 

TWIN BALL 

CATCH (2x) 

C 

B 

TOILET 

FRONT 

COVER 

FLUSH HOSE 

ELECTRICAL 

CONNECTION 

HYDRAULIC 

CONNECTION 

CLAMP 

SUPPORT 

MANUAL 

CLOSURE 

VALVE 




Waste Tank- Servicing 

Figure 301 


12-15-03-600-801-A/300 

Page 303/304 

OCT 31/08 




GHSH TASK 12-23-00-100-801-A 

1. External Aircraft - Cleaning 

A. General 

(1) This task gives the instructions to clean the aircraft. 

(2) Clean the external aircraft surfaces frequently to keep them with their 

good visual properties and resistance to corrosion. 

(3) Always clean the aircraft external surfaces from the top to the bottom. 

(4) The aircraft external dirt can be light (dust, mud, etc.) or heavy (grease, 

exhaust deposits, oil, etc.). 

B. Job Set-Up 





WARNING: DURING THE CLEANING PROCEDURE, DO NOT LET 

THE CLEANING SOLUTION TOUCH YOU AND DO NOT 

BREATHE ITS VAPORS OR MISTS. DO THE 

PROCEDURE IN AN AREA WITH A GOOD AIRFLOW. 

PUT ON SAFETY CLOTHES, GOGGLES, AND GLOVES. 

WARNING: BEFORE YOU CLEAN AN EXHAUST SURFACE, MAKE 

SURE THAT THE EXHAUST SYSTEM IS COLD. 

CLEANING PRODUCTS ARE FLAMMABLE AND, IF YOU 

APPLY THEM TO HOT SURFACES, INJURY TO 

PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. 

WARNING: IT IS VERY IMPORTANT THAT YOU OBEY THE 

CLEANING PRODUCT SAFETY PRECAUTIONS. USE 

PROTECTION GOGGLES AND CLOTHES. DO NOT LET 

CLEANING PRODUCT TOUCH YOUR SKIN, EYES, OR 

CLOTHES. IF YOU DO NOT OBEY THIS PRECAUTION, 

DAMAGE TO THE EQUIPMENT AND/OR INJURY TO 

PERSONNEL CAN OCCUR. 

WARNING: • DO THIS PROCEDURE IN AN AREA WITH A GOOD 

FLOW OF AIR. 


• USE MASK, SAFETY GOGGLES, AND RUBBER OR 

LATEX GLOVES WHEN YOU TOUCH BIRD STRIKE 

REMAINS. 

• DISCARD THE RUBBER OR LATEX GLOVES THAT YOU 

USED. 

• WHEN YOU HANDLE BIRD STRIKE REMAINS, OBEY 

THE LOCAL AUTHORITY RULES TO PREVENT 


12-23-00-100-801-A/300 

Page 301 

Rev.05 - AUG 14/09 







HEALTH PROBLEMS. 

(1) Do the procedure to make the aircraft safe for maintenance. 

WARNING: MAKE SURE THAT THE LANDING GEAR SAFETY PINS 

ARE INSTALLED. THIS IS TO PREVENT INJURIES TO 

PERSONS AND DAMAGE TO MATERIAL. 

(2) Make sure that the landing gear safety pins are installed. 

(3) Make sure that the aircraft is parked correctly. 

(4) Seal the inlets and outlets of the refrigeration pack compartments with 

polyethylene film or equivalent water and detergent-resistant film, and 

adhesive tape or equivalent. 

(5) Seal the AOA vanes and their attachment bases on the fuselage with 

polyethylene film or equivalent water and detergent-resistant film, and 

adhesive tape or equivalent. 

(6) Close the forward baggage-compartment door and seal it with adhesive 

tape or equivalent. 

(7) Close the aft baggage-compartment door and seal it with adhesive tape or 

equivalent. 

(8) Close the main door and seal it with adhesive tape or equivalent. 

(9) Install these items of GSE: GSE 003, GSE 009 and GSE 030. 

(10) Make sure that the water used for cleaning is free from sand residues and 

other contaminants. 

C. Aircraft Cleaning - Removal of Light Dirt from the Fuselage 

CAUTION: DO NOT APPLY CLEANING SOLUTION TO LARGE AREAS 

THAT YOU CANNOT FULLY CLEAN BEFORE THE SOLU- 

TION DRIES ON THE SURFACE AND THE SURFACE 

BECOMES GLOSSY. 

(1) Prepare a cleaning solution in a dilution ratio of 10% by volume of detergent 

SUPERSOL-10 for 1 liter of distilled water. 

(2) Apply the cleaning solution of distilled water and detergent SUPERSOL- 

10 to the aircraft fuselage with a spray gun or a cleaning brush or equivalent 

equipment. 

(3) Let the cleaning solution of distilled water and detergent SUPERSOL-10 soak 

into the surface for sufficient time for the dirt to become soft (approximately 5 

minutes). 

CAUTION: DO NOT USE HIGH PRESSURE (MAXIMUM 70 PSI) AND 

DO NOT POINT THE FLOW OF WATER DIRECTLY TO THE 

ANGLE-OF-ATTACK SENSORS OR OTHER MECHANICAL, 

ELECTRICAL, OR HYDRAULIC COMPONENTS. LIQUIDS 

THAT GET INTO THESE AREAS CAN CAUSE SERIOUS 

DAMAGE TO THE EQUIPMENT. 


12-23-00-100-801-A/300 

Page 302 

Rev.05 - AUG 14/09 




(4) Use a wiper cloth soaked in the solution to clean the fuselage. 

(5) Fully flush with clean water, three or more times. Finally flush the surface 

from its top down to the bottom. Make sure that the solution is fully 

removed. 

NOTE: If necessary, apply the solution again and rub with a cleaning 

brush to help remove the dirt. 

(6) Dry with forced air or dry rags. 

D. Aircraft Cleaning - Removal of Heavy Dirt from the Fuselage 

CAUTION: DO NOT APPLY CLEANING SOLUTION TO LARGE AREAS 

THAT YOU CANNOT FULLY CLEAN BEFORE THE SOLU- 

TION DRIES ON THE SURFACE AND THE SURFACE 

BECOMES GLOSSY. 

(1) Prepare a cleaning solution with REMOVEGRAX MLS-12 detergent and 

distilled water. 

(2) Apply the cleaning solution of distilled water and REMOVEGRAX MLS-12 

detergent under the dirt areas with a wiper cloth, a cleaning brush, or 

equivalent equipment. 

(3) Let the cleaning solution of distilled water and REMOVEGRAX MLS-12 

detergent soak into the surface for a sufficient time for the dirt to become 

soft (approximately 5 minutes). 

(4) Use a wiper cloth soaked in the solution to clean the fuselage. 

(5) Fully flush with clean water, three or more times. Finally flush the surface 

from its top down to the bottom. Make sure that the solution is fully 

removed. 

NOTE: If necessary, apply the solution again and rub with a cleaning 

brush to help remove the dirt. 

(6) Dry with compressed air or dry rags. 

E. Aircraft Cleaning - Landing Gear Washing 

(1) Apply a solution of water and REMOVEGRAX MLS-12 detergent to the 

aircraft landing gear with the aid of a spray gun or cleaning brush. 

(2) Fully flush the landing gear with clean water until all the cleaning solution 

is removed. 

(3) Polish the shock absorber rods with a flannel and make these surfaces 

moist with hydraulic fluid. 

(4) It is recommended to lubricate the MLG and NLG not later than 6 hours 

after you finish the cleaning procedure. 

NOTE: • EMBRAER strongly recommends that lubrication of the MLG 

and NLG be performed around 6 hours after the washing procedure. 




12-23-00-100-801-A/300 

Page 303 

Rev.05 - AUG 14/09 






• High-pressure washing can remove the protective greases 

and let water go into the inner working surface of the landing 

gear, which increases the risk of further environmental attack. 

F. Aircraft Cleaning - Windshield Washing 

(1) Remove all excess amounts of dirt and other foreign matter from the glass 

surface with clean water. Preferred initial application is by spraying or 

flooding the surface to wash away any abrasive materials. If spraying or 

flooding is impractical, a clean sponge or soft cloth should be used. 

NOTE: Remove or cover/protect watches, rings, and other metal 

objects on person (belt buckle, rivets on jeans, tools in pockets) 

that may cause scratches before a windshield maintenance. 

(2) Wash gently using 50/50 water-to-isopropyl alcohol solution containing mild 

liquid soap in a 2% to 5% concentration. 

NOTE: The mild liquid soap can be detergents formulated for washing 

dishes by hand. Dawn, Joy, Palmolive or Ivory are recommended. 

(3) Rinse thoroughly with clean water and dry with a damp chamois, sponge, 

or cloth. 

G. Aircraft Cleaning - Side Window Washing 

(1) Remove all excess amounts of dirt and other foreign matter from the 

acrylic surface with clean water. Preferred initial application is by spraying 

or flooding the surface to wash away any abrasive materials. If spraying or 

flooding is impractical, a clean sponge or soft cloth should be used. 


objects on person (belt buckle, rivets on jeans, tools in pockets) 

that may cause scratches before a side-window maintenance. 

(2) Wash gently using 50/50 isopropyl alcohol solution containing a mild liquid 

soap in a 2% to 5% concentration. 




or cloth. 

H. Aircraft Cleaning - De-Icer Boots 

(1) Mix detergent (Calla 800 meets Mil Spec MIL-C-87936 Type 1) with clean 

warm water in accordance with the following ratios/conditions: 


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Surface Contamination 

Severity/Surface Condition 

Detergent 

Ratio 

Water 

Normal 1 part 20 parts 

Badly weathered or yellowed surface 1 part 3 parts 

Surface stains Full strength None 

CAUTION: DO NOT ABRADE THE SURFACE OF THE DE-ICER BOOT. 

THE CLEANING CLOTHS AND THE SURFACE OF THE DE- 

ICER BOOT MUST STAY FULLY WET THROUGHOUT THE 

CLEANING PROCEDURE TO MINIMIZE THE POSSIBILITY 

OF ABRADING THE DE-ICER BOOT SURFACE. 

(2) Using clean, soft wiper cloth, fully wet the de-icer boot surface with detergent/water 

solution. 

NOTE: If the de-icer boot surface is stained, detergent can be used 

full-strength on stained areas of de-icer boot. 

(3) Allow detergent solution to penetrate surface contamination (approximately 

60 to 90 seconds) before gently removing contamination with fully 

wetted cloths. 

NOTE: If the de-icer boot surface is stained, allow a longer penetration 

time for severe cleaning conditions, up to 30 minutes. 

(4) Rinse the de-icer boot with clean water and clean, soft wiper cloth; maintain 

the cloths fully wetted at all times. 

(5) Dry the de-icer boot with clean, soft wiper cloth. Use caution not to drag a 

dry cloth across the de-icer boot surface or score it by rubbing too hard. 

(6) Repeat the procedure as needed until the de-icer boot surface is clean 

and free of contamination. 

I. Job Close-Up 

(1) Remove the adhesive tape from the aft baggage-compartment door. 

(2) Remove the adhesive tape from the forward baggage-compartment door. 

(3) Remove the adhesive tape from the main door. 

(4) Open the inlets and outlets of the refrigeration pack compartments sealed 

before. 

(5) Remove the adhesive tape and polyethylene film form the AOA vanes and 

from their attachment bases in the fuselage. 

(6) Remove these items of GSE: GSE 003, GSE 009 and GSE 030. 


TO MAKE THAT YOU REMOVED ALL TOOLS AND EQUIP- 

MENT AFTER YOU COMPLETED THE WORK. 


used. 




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GHSH TASK 12-23-00-100-802-A 

1. Internal Aircraft - Cleaning 

A. General 

(1) This task gives the instructions for maintenance and cleaning of materials 

and components of the aircraft interior. 

B. Job Set-Up 





USE SAFETY CLOTHES, GOGGLES, AND GLOVES. 





(1) Do the procedure to make the aircraft safe for maintenance. 

(2) Do the aircraft normal parking procedure. 

WARNING: MAKE SURE THAT THE LANDING GEAR SAFETY PINS 

ARE INSTALLED. THIS IS TO PREVENT INJURIES TO 

PERSONS AND DAMAGE TO MATERIAL. 

(3) Make sure that the landing-gear safety pins are installed. 

EFFECTIVITY: ON ACFT REGISTERED IN ENGLAND 

C. Carpets - Cleaning 

WARNING: YOU MUST REPLACE CARPETS AND FABRICS 

TREATED WITH FLAME-RESISTANT PROTECTION 

WHENEVER THEY BECOME CONTAMINATED OR DIRTY. 

DO NOT DRY-CLEAN NOR WASH CARPETS AND 

FABRICS TREATED WITH FLAME-RESISTANT 

PROTECTION BECAUSE THE PROTECTIVE COATING 

CAN BE DESTROYED OR SERIOUSLY IMPAIRED. 

(1) Replace the carpet. Please use the contact information given in the GHSH 

Introduction for the applicable maintenance action. 

NOTE: If you have any doubts, report to Embraer technical support. 

EFFECTIVITY: ON ACFT REGISTERED OUTSIDE ENGLAND 

D. Carpets - Cleaning 






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PUT ON SAFETY CLOTHES, GOGGLES, AND GLOVES. 

CAUTION: FROM THE INSTALLATION OF THE CARPET, VACUUM 

THE CARPET ONCE A WEEK MINIMUM TO REMOVE SOIL 

AND OTHER PARTICLES BEFORE THEY ARE EMBEDDED 

INTO THE PILE OF THE CARPET. IN HEAVY TRAFFIC, 

VACUUM THE CARPET MORE FREQUENTLY. 

(1) Do a regular cleaning as follows: 

(a) Remove all loose particles from the carpet with a vacuum cleaner. 

NOTE: Move the vacuum cleaner slowly to allow time for dirt 

removal. 

(b) Do not let the dust bag be more than half full. 

NOTE: You cannot over-vacuum. 

(c) Prepare the carpet cleaning-solution. Refer to the manufacture's instructions. 

(d) Apply it to the surface while you use a soft-bristle brush lightly. 

(e) Let the cleaned area dry. 

(f ) Clean the area with a vacuum cleaner to complete the cleaning. 

(2) Remove the general spots as follows: 

(a) Blot spills with white paper towels or a clean absorbent cloth. 

(b) Use a polyethylene spatula and a lint-free cloth to lightly clean the 

area. 

(c) Do a visual check to see if the spot was removed. 

CAUTION: BEFORE YOU APPLY CLEANING CHEMICAL TO THE 

CARPET, DO A TEST FOR COLORFASTNESS IN A 

SAMPLE OR IN A PART OF THE CARPET THAT CAN- 

NOT BE EASILY SEEN. 

CAUTION: MAKE SURE THAT ALL SOLUTIONS HAVE PH 

BETWEEN 4 AND 7. 

CAUTION: DO NOT SQUIRT SOLVENT INTO THE CARPET, IT 

CAN DISSOLVE THE BACKING MATERIALS. 

(d) Prepare the carpet cleaning solution. Use the treatments given in 

Table 301 to soak the area to remove the dirty spots. 

NOTE: • Use the manufacturer's instructions. 

• Use the same order of treatment as given in Table 301. 

(e) To remove these spots, use the order of the treatments given in the 

table: 


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Table 301 – Carpet – Spot Treatment 

SPOT 

Alcoholic Beverages 

ORDER OF TREATMENT 

STEP 1 STEP 2 STEP 3 

Cold water 

Carpet shampoo. 

This solution must 

be well rinsed with 

clear water. 

Bleach Cold water Ammonia solution White vinegar solution 

Blood 

Butter 

Chewing Gum 

Chocolate 

Coffee 

Colas and Soft 

Drinks 

Cold water 

Solvent. 

Chill with 

aerosol 

freezing 

agent or ice 

cubes in a 

plastic bag. 

Pick or 

scrape off 

gum. 

Carpet 

shampoo. 

This solution 

must be well 

rinsed with 

clear water. 

Cold water 

Cold water. 




clear water. 




clear water. 

Solvent. - 

Ammonia solution. 




clear water. 




clear water. 

- 

- 

- 

White vinegar solution. 

Solvent. 

- 




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Table 301 – Carpet – Spot Treatment (Continued) 



SPOT 

Cooking Oils 

Cream 

Egg 

Excrement 

Floor Wax 

Fruit Juice 

Furniture Polish 



Solvent. 

Carpet 

shampoo. 

This solution 

must be well 

rinsed with 

clear water. 

Carpet 

shampoo. 

This solution 

must be well 

rinsed with 

clear water. 

Cold water. 

Solvent. 

Cold water. 

Solvent. 




clear water. 

Solvent. - 




clear water. 




clear water. 




clear water. 




clear water. 

- - 


Ammonia solution and 

- 

- 

- 

white vinegar solution. 


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SPOT 

Gravy and Sauces 

Ink (fountain pen) 

Ink (ball point) 

Ink (felt tip) 

Ketchup 

Lipstick 

Mercurochrome 



Warm water. 

Cold water. 

Solvent. 

Warm water. 

Warm water. 

Solvent. 

Carpet 

shampoo. 

This solution 

must be well 

rinsed with 

clear water. 




clear water. 




clear water. 

Alcohol, methylated 

spirits or mineral 

turpentine. 




clear water. 




clear water. 




clear water. 

Milk Warm water. Solvent. 


- 

- 

Carpet shampoo. This 

solution must be well 

rinsed with clear water. 

Acetone. 

- 

- 

White vinegar solution. 







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SPOT 



Mustard 

Carpet 

shampoo. 

This solution 

must be well 

- - 

rinsed with 

clear water. 

Nail Polish Acetone. Solvent. - 

Oil and Grease Solvent. 




- 

clear water. 


Paint (latex) Cold water. 



Solvent. 

clear water. 

Paint (oil) 

Alcohol, 

methylated 

spirits or mineral 

turpentine. 

Solvent. 




Rust 

Solvent. 




Rust remover. 

clear water. 

Salad Dressing 

Carpet 

shampoo. 

This solution 

must be well 

Solvent. - 

rinsed with 

clear water. 

Shoe Polish Solvent. 




clear water. 

- 


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SPOT 



Soot 

Solvent. 


This solution must Ammonia solution and 

be well rinsed with white vinegar solution. 

clear water. 

Tar Solvent. - - 


Tea 

Cold water. 



Solvent. 

clear water. 


Urine (fresh) Cold water. 



- 

clear water. 

Urine (old) 

Carpet 

shampoo. 

This solution 

must be well 

Ammonia solution. White vinegar solution. 

rinsed with 

clear water. 

Vomit 

Carpet 

shampoo. 

This solution 

must be well 

- - 

rinsed with 

clear water. 

Absorbent 

Wine 

powder (salt, 


talc or proprietary 

absor- 

Cold water. solution must be well 


bent 

powders). 

Unknow Material Solvent. 


Absorbent cleaner 


(host or Dri-matic). 





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(f) Lightly apply it to the surface with a soft-bristle brush. 

(g) Do the operation again until the surface is fully clean. 

NOTE: • Do not wet the carpet too much. 

• Clean from the edge of the spot to prevent too much 

spread. 

(h) When the spot is removed, apply pressure with paper towels or dry 

absorbent cloth to blot excessive moisture. 

(i) Use a clean cloth soaked in warm water again from the edge to the 

center. 

NOTE: Do not rub the carpet. 

(j) Apply pressure with paper towels or dry absorbent cloth to blot excessive 

moisture. 

(k) After the removal of the spots, clean the surface. 

NOTE: Do not walk on moist areas of the carpet. 

(3) Remove the wool and sink spot as follows: 

CAUTION: FOR SILK CLEANING, AVOID USING WATER AND 

WATER-BASED CLEANERS. USE DRY CLEANING 

AGENTS ONLY. 

(a) Beverage: 

NOTE: Do not use metal bristles. 

1. Use a dry cloth towel to blot the spot. 

2. Apply pressure moderately. If the spot continues, use club soda to 

make the area moist. 

3. Blot until the spot is removed. 

4. Use the CAPTURE product to remove residual discoloration. 

NOTE: Follow manufacturer's instructions. 

(b) Food spill: 

1. Remove as much solid matter as possible. 

2. Blot up as much liquid matter as possible. 

3. For a wool spot, use a shop wipe soaked in club soda to make the 

area moist and blot up again. 

4. Use CAPTURE water based residual solution. 

CAUTION: DO NOT OVER-SPRAY THE CARPET. APPLY ZEP-X- 

OUT TO THE TOWEL THEN GENTLY WORK INTO 

CARPET. 

5. Use Zep-X-out II for grease or oil. 

NOTE: Use the manufacturer's instructions. 


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(c) Spill at lavatory: 

1. Blot the area immediately 

2. Use a shop wipe soaked in club soda and blot again. 

NOTE: • Use a tea spoon of white vinegar per 170 g (6 oz) club 

soda. 

• Do not use vinegar rinse on silk carpet. 

3. After the area is clean, use club soda and vinegar solution to blot 

again. 

(d) Grease, Oil, Tar or Asphalt: 

1. Remove as much as possible but do not push it deeper into the pile 

or you will increase the spot. 

2. Apply 1:1:1 of trichloroethane volatile dry cleaning solvent to a 

clean dry towel. 

3. Rub the towel on the spot with a soft circular motion. 

4. Immediately blot with a dry part of the towel. 

5. Do these procedures again until the spot is removed. 

EFFECTIVITY: ON ACFT REGISTERED IN ENGLAND 

E. Curtain Fabric - Cleaning 

WARNING: YOU MUST REPLACE CARPETS AND FABRICS 

TREATED WITH FLAME-RESISTANT PROTECTION 

WHENEVER THEY BECOME CONTAMINATED OR DIRTY. 

DO NOT DRY-CLEAN NOR WASH CARPETS AND 

FABRICS TREATED WITH FLAME-RESISTANT 

PROTECTION BECAUSE THE PROTECTIVE COATING 

CAN BE DESTROYED OR SERIOUSLY IMPAIRED. 

(1) Replace the cockpit/passenger cabin curtain. Please use the contact information 

given in the GHSH Introduction for the applicable maintenance 

action. 


EFFECTIVITY: ON ACFT WITHOUT LAVATORY DOOR 

(2) Replace the passenger cabin/lavatory curtain. Please use the contact 

information given in the GHSH Introduction for the applicable maintenance 

action. 


EFFECTIVITY: ON ACFT REGISTERED OUTSIDE ENGLAND 

F. Curtain Fabric - Cleaning 

NOTE: When the fire-blocking fabric is dirty, use a commercially available 

dry cleaning agent (Solvent per MIL-PRF-680 Type I or equiva- 




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Rev.06 - OCT 09/09 






lent). 

(1) To clean the curtains without their removal, do as follows: 

(a) Collect all loose particles with a vacuum cleaner. 

(b) For spots not easy to remove, you can use a soft-bristle brush. 

(c) Remove spots from the fabric and be careful not to soak the seat 

upholstery. See Table 301. 

(d) If necessary, remove the upholstery to do the cleaning procedure. 

(2) To clean the curtains with their removal, do as follows: 

(a) Apply a matching-type Velcro tape to all Velcro tapes to prevent damage 

during the cleaning. 

(b) Use a polyethylene spatula and a lint-free cloth to lightly clean the 

area. 

(c) Prepare the carpet cleaning solution. 

NOTE: Follow the manufacture's instructions. 

(d) Apply it lightly to the surface with a soft-bristle brush. 

(e) Repeat the operation until the surface is fully clean. 

(f) Fully dry the surface with a lint-free cloth. 

(g) Make the area moist with a cleaning solution. Use the treatments 

given in Table 301 to soak the area to remove the dirty spots. 

NOTE: • Use the manufacture's instructions 

• Use the same order of treatment as given in Table 301. 

(h) While the surface is wet, use a polyethylene spatula lightly on the dirty 

area. 

(i) After the removal of the spots, let the cleaned area dry. 

(j) Clean the area with a vacuum cleaner to complete the cleaning. 

G. Acrylic Parts - Cleaning 

(1) Lightly rub the surface with a lint-free cloth soaked in neutral detergent to 

fully clean the surface. 

(2) Use a lint-free cloth soaked in clean water to fully remove the detergent. 

(3) Rub the surface dry with a lint-free cloth. 

(4) If necessary, clean the surface with a lint-free cloth moist with Naphtha 

and detergent. 

NOTE: Do not let Naphtha touch the plastic surfaces. Naphtha can 

cause damage to them. 

(5) Rub the surface with a lint-free cloth soaked in neutral detergent to make 

sure that it is fully clean. 

(6) Fully remove all detergent with a soft cloth soaked in clean water. 

(7) Rub the surface dry with a lint-free cloth. 


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H. Leathers - Cleaning 

(1) Do the regular Cleaning as follows: 

(a) Prepare the neutral detergent solution (refer to the manufacturer's 

instructions) and apply only foam to leather with a lint-free cloth. 

Lightly wipe with circular movements. 

(b) Remove all detergent with a lint-free cloth soaked in water. 

(c) Rub the surface dry with a lint-free cloth. 

(2) Remove the spots as follows: 

(a) Clean stains (coffee, milk, liqueur, etc.) with neutral detergent (Refer to 

the manufacturer's instructions). 

(b) Clean stains (grease, oil, etc.) with a lint-free cloth soaked in MIL-PRF- 

680 Type I or equivalent. 

(c) Remove all detergent with a lint-free cloth moist with clean water. 

(d) Rub the surface with a dry lint-free cloth. 

I. Metal Surfaces - Cleaning 

CAUTION: WHEN YOU SOAK THE CLOTH, DO NOT PUT IT OVER 

THE SOLVENT CONTAINER MOUTH AND TURN THE CON- 

TAINER. THIS CAN CAUSE CONTAMINATION OF THE SOL- 

VENT SOURCE. ALWAYS POUR THE SOLVENT ONTO THE 

CLOTH OR USE A DISPENSER CAN DESIGNED TO ISO- 

LATE CONTAMINATS. 

CAUTION: DO NOT LET SOLVENTS TOUCH THE DECOR MATERIAL OR 

PLASTIC COMPONENTS. MEK AND ACETONE CAN CAUSE 

DAMAGE TO SOME COMPONENTS AND MATERIALS. 

(1) Clean the metal surfaces with solvents as follows: 

NOTE: • We recommend that you apply a corrosion inhibitor to metal 

surfaces independently of the cleaning material that you use. 

Metal surfaces are normally treated or anodized to prevent 

corrosion. Normal wear and abnormal abuse cause corrosion, 

and it is always a factor that you must consider. 

• Do not scour or abrade surfaces. Corrosion protection is normally 

a thin layer of anodizing or organic agent. Abrasion can 

remove the protective film or coating. 

• Do not permit solvent to evaporate on the surface. 

• Do not use a cloth a second time because this can redeposit 

contaminants on the surface. 

(a) Dampen a clean dry cotton cloth with the solvent. Pour the solvent on 

the cloth. 

(b) Wipe the metal surfaces with the solvent. Repeat the applications as 

necessary to remove all dirt. 




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NOTE: For oxidation, powdery white corrosion, use corrosion 

inhibitor/cleaner. 

(c) Dry the parts with a clean, dry cotton cloth. 

CAUTION: DO NOT USE BRULIN 815MX CLEANER UNDILUTED. 

SOLUTIONS STRONGER THAN THOSE SPECIFIED CAN 

DAMAGE THE DECORATIVE SURFACES. 

(2) Use BRULIN 815MX: 

NOTE: Cool water works better with normal dirt and dust. Warm water 

works better with oily surfaces. 

(a) Prepare a solution of BRULIN 815MX with cool or lukewarm water 

between 32°C - 49°C (90°F - 120°F). Prepare a solution with 1 part 

BRULIN 815MX to 64 parts of water by volume, for light dirt. You can 

increase the solution up to 1 part of BRULIN 815MX to 10 parts of 

water by volume. 

(b) Apply the solution with a spray bottle, soft-bristle brush, sponge or cotton 

cloth. 

(c) Rub the surface with a wet sponge or cotton cloth. You can also spray 

the material on the surfaces and rub with a clean sponge or soft-bristle 

brush. Do not permit excess to run off to adjacent surfaces. 

(d) Rub the dirty areas as necessary and repeat the application of the 

solution to remove contamination. 

(e) Rinse the surface with a fresh sponge or a cloth dampened with clean 

water to remove residue. 

(f) Dry the surface with a clean, dry cotton cloth. 

(3) Use CALLA 301-A LEMON: 



(a) Prepare a solution of CALLA 301-A LEMON with cool or lukewarm 

water within 32°C - 49°C (90°F - 120°F). Prepare a solution with 1 part 

of CALLA 301-A LEMON to 4-8 parts of water by volume for normal 

cleaning. For concentrated dirt or spots, use full strength. 

(b) Apply the solution with a spray bottle, soft-bristle brush, or cotton cloth. 

(c) Spray the solution on the surface. Rub the surface with a clean cloth or 

sponge. Do not permit excess to run off to adjacent surfaces. 

NOTE: Make sure that no solution excess comes into contact with 

porous surfaces. 

(d) Rub the dirty area as necessary and repeat the applications as necessary 

to remove contamination. 




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J. Plastic or Vinyl Panels - Cleaning 

(1) Use of mild household detergent: 

(a) Prepare a solution of mild household detergent with lukewarm water 

between 32°C - 49°C (90°F - 120°F). Prepare the solution with 1 part 

detergent to 50 parts of water by volume. 

(b) Wet a cotton cloth or sponge with the solution. 

(c) Apply the solution to the surface. Use circular movement. Do not permit 

excess to run off to adjacent surfaces. 

(d) Rub the dirty area as necessary and repeat the application of the solution 





NOTE: Do not use BRULIN 815MX cleaner. Solutions stronger 

than those specified can damage the decorative surfaces. 

(2) Use of BRULIN 815MX: 



(a) Prepare a solution of BRULIN 815MX with cool or lukewarm water 

between 32°C - 49°C (90°F - 120°F). Prepare a solution with 1 part of 

BRULIN 815MX to 64 parts of water by volume, for light dirt. You can 

increase the solution up to 1 of BRULIN 815MX to 10 parts of water by 

volume. 

(b) Apply the solution with a spray bottle, soft-bristle brush, sponge or cotton 

cloth. 


sponge. Do not permit excess to run off to adjacent surfaces. Make 

sure that no excess comes into contact with porous surfaces. 


to remove contamination 




(3) Use of CALLA 301-A LEMON: 



(a) Prepare a solution of CALLA 301-A LEMON with cool or lukewarm 

water between 32°C - 49°C (90°F - 120°F). Prepare a solution with 1 

part of CALLA 301-A LEMON to 4-8 parts of water by volume for nor- 




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Rev.06 - OCT 09/09 






mal cleaning. For concentrated dirt or spots, use full strength. 

(b) Apply the solution with a spray bottle, soft-bristle brush, or cotton cloth. 


sponge. Do not permit excess to run off to adjacent surfaces. Make 

sure that no excess comes into contact with porous surfaces. 






K. Ultrasuede - Cleaning 

(1) Do the regular maintenance as follows: 

(a) Vacuum the carpet to remove all loose particles. 

(b) To prepare the Ultrasuede cleaning-solution refer to the manufacturer's 

instructions. 


NOTE: You can remove stains with detergent. Use denatured 

alcohol or a mild cleaning fluid when required. Refer to 

Table 302. 

(c) Apply it to the surface while you use a medium-bristle brush lightly. 

(d) Let the cleaned area dry. 

(e) Vacuum it to complete the cleaning. 

(2) Clean the everyday stains as follows: 

(a) Lightly use a spatula and a wiper to clean the area. 

(b) Prepare a solution of water and mild detergent. 

NOTE: You can remove stains with detergent. Use denatured 

alcohol or a mild cleaning fluid when required. Refer to 

Table 302. 

(c) Lightly apply it to the surface with a medium-bristle brush. 

(d) Repeat the operation until the surface is fully cleaned. 

(e) Remove the Ultrasuede cleaning solution with a cloth and water. 

(f) Use a heat gum to dry the area or dry naturally by air. 

(2) Extremely tough stains: 

(a) Lightly use a spatula and a wipe to clean the area. 

(b) Clean stains (grease, etc.) with a lint-free cloth soaked in solvent MIL- 

PRF-680 Type I or equivalent. 

(c) Lightly apply it to the surface with a medium-bristle brush. 

(d) Repeat the operation until the surface is fully clean. 

(e) Prepare the neutral detergent solution (refer to the manufacturer's 

instructions) and apply foam with a lint-free cloth. Lightly wipe with circular 

movements. 

(f) Remove all detergent with a lint-free cloth soaked in clean water. 

(g) Rub the surface with a dry lint-free cloth. 

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(3) To remove a specific stain from Ultrasuede, use these materials indicated 

in the table to do a spot treatment: 

Table 302 - Ultrasuede - Spot Treatment 

STAIN 

Coffee, Tea, Bear, Wine, Liquor, Milk, 

Ketchup, Steak Sauce. 

Mayonnaise, Butter, Salad Oil, Chocolate, 

Cosmestic Foundation, Lipstick, Face Cream, 

Suntain Oil/Lotion, ball Point Pen (Ink), Shoe 

Polish, Urine 

Machine Oil 

L. Painted Surfaces - Cleaning 

(1) Apply neutral detergent to the dirty area with a soft cloth. 

(2) Rub the surface with a soft clean soaked in clean water to remove the 

detergent. 

(3) Rub the surface dry with a soft clean cloth. 

CAUTION: DO NOT USE CHLORINATED AND FLUORCARBON SOL- 

VENTS IN AREAS PAINTED WITH WATER-BASE PAINTS. 

(4) If necessary, rub the surface with a cloth dampened with solvent (per MIL- 

PRF-680 Type I or equivalent). 

(5) Apply neutral detergent to the dirty area with a soft cloth. 

(6) Rub the surface with a soft clean cloth soaked in water to remove the 

detergent. 


M. Decals - Cleaning 

Detergent. 

SPOT TREATMENT 

STEP 1 

Detergent and denatured alcohol 

Denatured alcohol 

CAUTION: DO NOT USE ORGANIC SOLVENTS (METHYL-KETONE, 

ALCOHOL, CHLORINATED SOLVENTS, FLUORINATED 

SOLVENTS, ETC.). THE MATERIAL IS NOT RESISTANT TO 

ORGANIC SOLVENTS. 

(1) Rub the decal with a soft clean cloth soaked in neutral detergent (Refer to 

the manufacturer's instructions). 

(2) Remove all detergent with a soft cloth soaked in clean water. 




N. Wooden Surfaces - Cleaning 

NOTE: These steps are not applicable to the areas that had light 

scratches removed. These areas must be re-sanded with Scotchbrite 

(white) sponge. 

(1) Carefully wipe the panel with a shop wipe to make sure that there is no 


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debris on the surface that can scratch the finish. 

(2) Mix the cleaning solution, which must have 90 parts of warm clean water 

and 10 parts of mild liquid soap. 

NOTE: You can use Windex to clean the surface as an alternative. 

(3) Lightly soak a shop wipe in soap solution and clean the surface in a circular 

soft motion. 

NOTE: Turn the cloth frequently to prevent the dirt from redepositing. 

O. Formica Surfaces - Cleaning 

(1) Lightly rub the surface with a wiper cloth soaked in neutral detergent to 

fully clean it. 

(2) Use a wiper cloth soaked in clean water to fully remove the neutral detergent. 

(3) Rub the surface dry with a wiper cloth. 

(4) If necessary, clean the surface with a wiper cloth moist with water and 

neutral detergent. 

(5) Rub the surface with a wiper cloth soaked in neutral detergent to make 

sure that it is fully clean. 

(6) Fully remove all neutral detergent with a cloth soaked in clean water. 

(7) Rub the surface dry with a wiper cloth. 

P. Decorative Platings - Cleaning 

(1) This procedure is applicable to decorative platings of a distinct variety of 

materials. These include gold, nickel, copper, brass, chrome, smoke 

nickel, rose gold, silver and platinum. 

CAUTION: IT IS RECOMMENDED THAT PLATED SURFACE CON- 

TACTED BY MOISTURE (ESPECIALLY WATER, TOMATO 

AND ORANGE JUICE, CARBONATED SOFT DRINKS, AND 

ALCOHOL) BE WIPED IMMEDIATELY AFTER EACH 

FLIGHT. 

CAUTION: DO NOT PERMIT WATER TO DRY ON THE PARTS. THE 

MINERAL CONTENT IN SOME WATER WILL LEAVE 

DEPOSITS THAT CAN BE DIFFICULT TO REMOVE. 

CAUTION: WHEN YOU SOAK THE CLOTH, DO NOT PUT IT OVER 

THE SOLVENT CONTAINER MOUTH AND TURN THE CON- 

TAINER. THIS CAN CAUSE CONTAMMINATION OF THE 

SOLVENT SOURCE. ALWAYS POUR THE SOLVENT ONTO 

THE CLOTH OR USE A DISPENSER CAN DESIGNED TO 

ISOLATE CONTAMINANTS. 

CAUTION:DO NOT LET SOLVENTS TOUCH THE DECOR MATERIAL 

OR PLASTIC COMPONENTS. MEK AND ACETONE CAN 

CAUSE DAMAGE TO SOME COMPONENTS AND MATE- 


12-23-00-100-802-A/300 

Page 316 

Rev.06 - OCT 09/09 




RIALS. 

(2) Use of solvents: 

NOTE: • We recommend that you apply a corrosion inhibitor to metal 

surfaces independently of the cleaning material that you use. 

Metal surfaces are normally treated or anodized to prevent 

corrosion. Normal wear and abnormal abuse cause corrosion 

and it is always a factor that you must consider. 

• Do not scour or abrade surfaces. Corrosion protection is normally 

a thin layer of anodizing or organic agent. Abrasion can 

remove the protective film or coating. 

• Do not permit solvent to evaporate on the surface. 

• Do not use cloth a second time because this can redeposit 

contaminants on the surface. 

• Keep the platings away from the sun. Long exposures discolor 

the finish. 

• You must clean the platings every two weeks. 

• Avoid spills on the finished surface. If it occurs clean immediately. 

(a) Dampen a clean dry cotton cloth with Windex. Pour it on the cloth. 

CAUTION: DO NOT USE HARSH OR AMMONIATED CLEANING 

AGENTS ON A FINISH WHICH WAS SEALED BY A 

CLEAR COAT. 

CAUTION: DO NOT USE FORCE DURING CLEANING PROCE- 

DURES. 

CAUTION: USE ONLY SOFT NON-SCRATCHING CLOTH. 

(b) Lightly dust the metal surfaces with the Windex. Repeat the applications 

as necessary to remove all dirt. For oxidation, powdery white corrosion, 

use corrosion inhibitor/cleaner. 

(c) Use a new soft paper towel and gently dust the surface to make sure 

that it is dried. 

NOTE: If the parts remain slightly wet, stains appears. 

(d) Use a clean cloth to apply a thin layer of turtle liquid wax to the platings. 

NOTE: The turtle liquid wax protects the plated surfaces. 

(e) Gently wipe the turtle liquid wax off in a circular motion until the wax disappears. 




12-23-00-100-802-A/300 

Page 317 

Rev.06 - OCT 09/09 






Q. Windshield - Cleaning 

CAUTION: DO NOT LET CLEANING PRODUCTS (SOLVENTS) TOUCH 

PAINT-FINISHED SURFACES, PLASTICS, OR SEALANT 

BEADS TO PREVENT DAMAGE. 

CAUTION: • DO NOT PUT CLEANING CLOTHS, BRUSHES, OR 

SPONGES IN A SOLVENT CONTAINER. THIS IS TO 

PREVENT SOLVENT CONTAMINATION. 

• CONTAMINATED SOLVENT CAN DAMAGE THE 

EQUIPMENT. 


SEALANT BEADS, LENSES, POLYCARBONATE WIN- 

DOWS, WINDSHIELDS, PAINTED SURFACES, AND 

ACRYLIC PARTS. SOLVENTS CAN CAUSE DAMAGE TO 

THESE SURFACES. 

CAUTION: DO NOT PUT ON WATCHES, BRACELETS, RINGS, OR 

CLOTHES WITH ZIP FASTENERS WHEN YOU CLEAN WIN- 

DOWS. DO NOT USE METAL TOOLS TO CLEAN WIN- 

DOWS.METAL OBJECTS CAN SCRATCH THE 

TRANSPARENCY AND CAUSE OPTICAL DISTORTION. 

CAUTION: DO NOT USE ABRASIVE MATERIALS TO CLEAN WIN- 

DOWS. ABRASIVE MATERIALS CAN SCRATCH THE 

TRANSPARECNCY AND CAUSE OPTICAL DISTORTION. 

(1) Remove all excess amounts of dirt and other foreign matter from the glass 

surface with clean water. Preferred initial application is by spraying or 

flooding the surface to wash away any abrasive materials. If spraying or 

flooding is impractical, a clean sponge or wipe cloth should be used. 


object on person (belt buckle, rivets on jeans, tools in pockets) 

that may cause scratches before any windshield maintenance. 

(2) Wash gently with a 50/50 water-to-TT-I-735 alcohol solution containing a 

mild liquid soap in a 2% to 5% concentration. 




or wipe cloth. 

R. Side Window - Cleaning 


PAINT-FINISHED SURFACES, PLASTICS, OR SEALANT 


12-23-00-100-802-A/300 

Page 318 

Rev.06 - OCT 09/09 




BEADS TO PREVENT DAMAGE. 

CAUTION: • DO NOT PUT CLEANING CLOTHS, BRUSHES, OR 

SPONGES IN A SOLVENT CONTAINER. THIS TO 

PREVENT SOLVENT CONTAMINATION. 

• CONTAMINATED SOLVENT CAN DAMAGE THE 

EQUIPMENT. 


SEALANT BEADS, LENSES, POLYCARBONATE WIN- 

DOWS, WINDSHIELDS, PAINTED SURFACES, AND 

ACRYLIC PARTS. SOLVENTS CAN CAUSE DAMAGE TO 

THESE SURFACES. 

CAUTION: DO NOT PUT ON WATCHES, BRACELETS, RINGS, OR 

CLOTHES WITH ZIP FASTENERS WHEN YOU CLEAN WIN- 

DOWS. DO NOT USE METAL TOOLS TO CLEAN WIN- 

DOWS. METAL OBJECTS CAN SCRATCH THE 


CAUTION: DO NOT USE ABRASIVE MATERIALS TO CLEAN WIN- 

DOWS. ABRASIVE MATERIALS CAN SCRATCH THE 


(1) Remove all excess amounts of dirt and other foreign matter from the 

acrylic surface with clean water. Preferred initial application is by spraying 

or flooding the surface to wash away any abrasive materials. If spraying or 

flooding is impractical, a clean sponge or wipe cloth should be used. 


object on person (belt buckle, rivets on jeans, tools in pockets) 

that may cause scratches before any windshield maintenance. 

(2) Wash gently with 50/50 water-to-TT-I-735 alcohol solution containing a mild 

liquid soap in a 2% to 5% concentration. 




or wipe cloth. 

S. Job Close-Up 


TO MAKE SURE THAT YOU REMOVED ALL TOOLS AND 

EQUIPMENT AFTER YOU COMPLETED THE WORK. 

(1) Remove from the work area all tools, equipment and materials that you 

used. 




12-23-00-100-802-A/300 

Page 319/320 

Rev.06 - OCT 09/09 




GHSH TASK 20-00-00-910-801-A 

1. Aircraft Maintenance Safety Procedures 

A. General 

(1) This task gives the usual safety procedure for the aircraft maintenance. 

(2) The functions of this task are to configure the aircraft before the maintenance 

procedures and to restore the aircraft after the maintenance procedures. 

(3) We recommend the use of a hangar for maintenance procedures. 

B. Aircraft Safety Procedures for Maintenance Services - Maintenance 

Practices. 

(1) For the maintenance procedures, do as follows: 

WARNING: MAKE SURE THAT THE FLIGHT CONTROLS WILL 

NOT BE OPERATED WHEN THERE ARE PERSONS 

NEAR THESE SURFACES. 

(a) Make sure that the flaps are retracted. 

(b) Put a warning notice in the cockpit to tell people not to operate the aircraft 

flight control surfaces. 

CAUTION: AFTER YOU SET THE PARKING BRAKE, IT WILL BE 

EFFECTIVE FOR APPROXIMATELY 48 HOURS OR 

UNTIL THE PRESSURE IS LOST. THE PARKING 

BRAKE MUST BE RELEASED AFTER A MAXIMUM OF 

48 HOURS BECAUSE THERE IS A RISK THAT THE 

BRAKE LININGS STICK TO THE BRAKE DISCS WITH 

POSSIBLE DAMAGE TO THE AIRCRAFT. 

(c) Apply the emergency/parking. 

WARNING: MAKE SURE THAT THE LANDING GEAR SAFETY 

PINS ARE INSTALLED. THIS IS TO PREVENT 

INJURIES TO PERSONS AND DAMAGE TO 

MATERIAL. 

(d) Install the landing gear safety pins in the LG (Landing Gear). Refer to 

GHSH TASK 32-00-00-910-801-A/200. 

(e) Put the wheel chocks against the LG wheels. 

CAUTION: THE MODULE OR UNIT CONTAINS ELECTROSTATIC 

DISCHARGE SENSITIVE (ESDS) ITEMS. OBEY THE 

APPROVED INDUSTRY PRECAUTIONS WHEN YOU 

TOUCH, REMOVE, OR INSTALL PARTS OR ASSEM- 

BLIES. DAMAGE CAN OCCUR FROM ELECTRO- 

STATIC DISCHARGE. 

(f) When you work with electronic equipment, obey the ESD (Electrostatic 



20-00-00-910-801-A/200 

Page 201 

Rev.06 - OCT 09/09 







Discharge Sensitive) rules (GHSH TASK20-40-00-910-801-A/200). 

(g) Use the approved platforms to get access to the aircraft. 

(h) Keep the area around the aircraft free from residues, grease, oil and 

fuel. 

(i) Put "NO SMOKING" placards around the maintenance area. 

WARNING: DO NOT GET HYDRAULIC FLUID, FUEL, OR VAPOUR 

CYCLE REFRIGERANT FLUID ON YOUR SKIN, IN 

YOUR EYES, OR MOUTH. PUT ON APPROVED 

PROTECTIVE CLOTHING, GLOVES AND GOGGLES. 

THESE FLUIDS ARE TOXIC AND CAN CAUSE 

INJURIES TO YOU 

(j) Use the correct containers to collect/drain fluids. 

(k) To prevent accidents, circulation areas outside the work place must be 

available for persons who are not included in the maintenance procedures. 

(l) If possible, do the maintenance procedures in an isolate area. Let a 

radius of at least 3m from other aircraft. 

WARNING: MAKE SURE THAT THERE ARE NO PERSONS OR 

EQUIPMENT IN THE RANGE OF TRAVEL OF THE 

LANDING GEAR. INJURY TO PERSONS OR DAMAGE 

TO EQUIPMENT CAN OCCUR IF THE AREA IS NOT 

CLEAR. 

(m) If necessary to retract and extend the nose landing gear and the main 

landing gears, isolate the area around them to prevent injures to persons 

and damage to the system. 

WARNING: OBEY THE FUEL SYSTEM SAFETY PRECAUTIONS. 

THIS IS TO PREVENT INJURY TO PERSONS AND 

DAMAGE TO THE EQUIPMENT. 

(n) When you work with fuel system, obey the safety precautions given in 

GHSH TASK 28-00-00-910-801-A/200. 

(2) Before you do maintenance operations near the wings, attach a blanket of 

bubble plastic over the deicer with adhesive tape. 

C. Aircraft Restore Procedures for Maintenance Services - Maintenance 

Practices 

(1) To restore the aircraft after the maintenance procedure, do as follows: 

(a) Remove the warning notice in the cockpit that tells people not to operate 

the aircraft flight controls. 

(b) Remove all circuit breaker ring and tag that you installed in the CBP. 

CAUTION: TO PREVENT DAMAGE, EXAMINE ALL THE WORK 

AREAS TO MAKE SURE THAT YOU EMOVED ALL- 


20-00-00-910-801-A/200 

Page 202 

Rev.03 - APR 17/09 




TOOLS AND EQUIPMENT AFTER YOU COMPLETED 

THE WORK. 

(c) Remove the platforms, safety devices, tools, equipment and unwanted 

materials from the work area. 




20-00-00-910-801-A/200 

Page 203 

Rev.02 - FEB 13/09 






A 

B 

A 

A 

WHEEL 

CHOCKS 

EMERG/PARK 

BRAKE HANDLE 

B 



Maintenance Practices 

Figure 201 

20-00-00-910-801-A/200 

Page 204 

Rev.02 - FEB 13/09 




GHSH TASK 20-40-02-910-801-A 

1. Static Grounding - Standard Practices 

A. General 

(1) The aircraft has one grounding point on the undersurface of each wing leading 

edge and one grounding point on the nose landing gear. 

(2) Bonding is the process of connecting two or more conductive objects with 

a conductor to make sure that there is the same electrical potential 

between them. 

(3) Grounding is the process of connecting two or more conductive objects 

with a conductor to the ground. 

(4) Static Grounding is mandatory in the following situations: 

(a) Maintenance in the aircraft with power tools, lights or any other equipment 

connected to a power source. 

(b) Maintenance or servicing operations outside the aircraft, during electrical 

storms. 

(5) For fuel system servicing, the electrical bonding between the aircraft and 

the refueling equipment is necessary to prevent sparks generated 

because of differential potential between them. Static Grounding is recommended. 

(6) For oxygen system servicing, there are two options to prevent sparks 

caused by static charges: 

(a) Static grounding of the aircraft and oxygen system servicing equipment 

are necessary, or; 

(b) Electrical bonding between the aircraft and the oxygen system servicing 

equipment is necessary. Static Grounding is recommended. 

B. Static Grounding - Standard Practices (Figure 1) (Figure 2) 

WARNING: DURING ATMOSPHERIC ELECTRICAL DISTURBANCES, 

DO NOT WEAR HEADSET, TOUCH EQUIPMENT 

ELECTRICALLY CONNECTED TO THE AIRCRAFT, OR 

HOLD A GROUND CONNECTION. A LIGHTNING STRIKE 

CAN CAUSE SEVERE INJURY TO PERSONS. 

(1) Make sure that the aircraft is parked adjacent to an approved and identified 

grounding point. 

NOTE: The approved and identified grounding points can be located 

in the parking surface or another fixed location. 

(2) Examine the static discharge cable for damage and make sure that the 

end-fittings are correctly attached. 

NOTE: • For static grounding with the use of the wing leading edge 

points, use a flexible grounding cable (specification MIL-W- 

83420) with a plug (specification MIL-C-83413/4). 



20-40-02-910-801-A/200 

Page 201 

Rev.06 - OCT 09/09 







• For static grounding with the use of the nose landing gear 

point, use a flexible grounding cable (specification MIL-W- 

83420) with a grounding clamp (specification MIL-C-83413/7). 

WARNING: ALWAYS ATTACH THE GROUNDING CABLE TO THE 

GROUNDING CONNECTION FIRST. DO NOT ATTACH 

THE CABLE TO THE AIRCRAFT AND THEN TO THE 

GROUNDING CONNECTION. 

(3) For aircraft static grounding, use one of the two options that follow: 

(a) For the grounding point on the undersurface of the wings: 

1. Connect the static grounding cable to a grounding point in the hangar 

and then plug to the grounding point on the undersurface of the 

left wing leading edge (Figure 201), or; 


and then plug to the grounding point on the undersurface of the 

right wing leading edge (Figure 201). 

(b) For the grounding point on the nose landing gear: 


and attach the grounding clamp to the nose landing gear 

grounding point (Figure 202). 

(4) For oxygen or fuel system servicing, do the electrical bonding of the aircraft 

to servicing equipment as follows: 

(a) Connect the bonding cable to the servicing equipment. 

(b) Connect the grounding clamp/plug of the bonding cable to the approved 

static grounding point on the aircraft (Figure 201) (Figure 202). 


20-40-02-910-801-A/200 

Page 202 

OCT 31/08 




A 

B 

A 

ZONES 

541 

641 

B 

A 

GROUNDING POINT 



GROUNDING 

PLUG 

B 

END CONNECTED TO THE 

SERVICING EQUIPMENT 

OR AT AN APPROPRIATE 




Wing Ground Points 

Figure 201 

20-40-02-910-801-A/200 

Page 203 

Rev.06 - OCT 09/09 




A 

ZONE 

711 



GROUNDING 

CLAMP 

END CONNECTED TO THE 

SERVICING EQUIPMENT 

OR AT AN APPROPRIATE 


B 

B 

GROUNDING 

POINT 

A 


Landing Gear Ground Point 

Figure 202 


20-40-02-910-801-A/200 

Page 204 

Rev.06 - OCT 09/09 




GHSH TASK 24-36-01-000-801-A 

1. Main Battery - Removal 

A. General 

(1) This task gives the procedure to remove the main batteries. 

(2) There are 2 batteries. Battery 1 is installed in the LH (Left Hand) forward 

compartment, and battery 2 is installed in a non-controlled environment 

compartment in the RH (Right Hand) wing-to-fuselage aft. 

B. Job Set-Up 






20-00-00-910-801-A/200). 

(2) On the ELECTRICAL control panel, put a DO NOT OPERATE, tag on the 

BATT 1 and BATT 2 switches. Refer to Figure 401. 

(3) To get access to battery 1, do as follows: 

(a) Open the forward baggage door. 

(b) Remove the access panel 211DZ. 


(a) Open the access door 195FR. 

C. Main Battery - Removal 

(1) Remove battery 1 as follows: (Refer to Figure 402) 

(a) Loosen the clamp that attaches the air-escape hose to battery 1. 

(b) Move the clamp to the center of the air-escape hose. 

(c) Pull the air-escape hose from the battery 1 outlet. 

(d) Remove the clamp from air-escape hose. 

WARNING: USE EYE PROTECTION WHEN YOU REMOVE OR 

INSTALL LOCK WIRE OR SAFETY CABLE. IF YOU 

DO NOT USE EYE PROTECTION, PIECES OF WIRE 

CAN HIT YOUR EYES AND CAUSE INJURY TO THEM. 

(e) Cut the lock wire from the electrical connector. 

(f) Disconnect the electrical connector from the connector of the battery 1. 

(g) Put a protective cap on the electrical connector and on the connector 

of the battery 1. 

(h) Loosen the self-locking retainer. 

(i) Carefully pull and remove the battery 1 from the aircraft. 

(2) Remove battery 2 as follows: (Refer to Figure 403) 




24-36-01-000-801-A/400 

Page 401 

Rev.04 - JUN 16/09 




WARNING: USE EYE PROTECTION WHEN YOU REMOVE OR 

INSTALL LOCK WIRE OR SAFETY CABLE. IF YOU 

DO NOT USE EYE PROTECTION, PIECES OF WIRE 

CAN HIT YOUR EYES AND CAUSE INJURY TO THEM. 



(a) Cut the lock wire from the electrical connector. 

(b) Disconnect the electrical connector from the connector of the battery 2. 

(c) Put a protective cap on the electrical connector and on the connector 

of the battery 2. 

(d) Loosen the self-locking retainer. 

(e) Carefully pull and remove the battery 2 from the aircraft. 


24-36-01-000-801-A/400 

Page 402 

OCT 31/08 




A 

GEN 1 

BATT 1 

AUTO 

OFF 

ON 

OFF 

ELECTRICAL 

GPU 

BUS TIE 

AUTO 

1 OPEN 2 OPEN 

ELEC EMER 

GEN 2 

BATT 2 

AUTO 

OFF 

ON 

OFF 



ELECTRICAL CONTROL 

PANEL 

A 


Electrical Control Panel - Location 

Figure 401 


24-36-01-000-801-A/400 

Page 403 

Rev.01- DEC 05/08 




211 DZ 



A 

ZONE 

211 

BATTERY 1 

SELF−LOCKING 

RETAINER (2x) 

CLAMP 

B 

A 

ELECTRICAL 

CONNECTOR 

B 

VENTILATION 

HOSE 


Main Battery 1 - Removal/Installation 

Figure 402 


24-36-01-000-801-A/400 

Page 404 

Rev.01- DEC 05/08 




A 

ZONE 

195 

BATTERY 2 


RETAINER (2x) 

195 FR 

B 

A 



ELECTRICAL 

CONNECTOR 

B 



Figure 403 


24-36-01-000-801-A/400 

Page 405/406 

Rev.01- DEC 05/08 




GHSH TASK 24-36-01-000-802-A 

1. Main Battery - Disconnection 

A. General 

(1) This task gives the procedure to disconnect the main batteries from the 

electrical bus. 



compartment, in the RH (Right Hand) aft wing-to-fuselage fairing. 

B. Job Set-Up 






20-00-00-910-801-A/200). 

(2) On the ELECTRICAL control panel, put a DO NOT OPERATE tag on the 

BATT 1 and BATT 2 switches. 


(a) Open the forward baggage door. 

(b) Remove the access panel 211DZ. 


(a) Open the access door 195FR. 

C. Main Battery - Disconnection 

(1) Disconnect battery 1 from the electrical bus as follows: (Refer to figure 402) 

(a) Disconnect the electrical connector from the battery connector. 

(b) Put a protective cap on the electrical connector and on the battery connector. 

(2) Disconnect battery 2 from the electrical bus as follows: (Refer to figure 403) 

(a) Disconnect the electrical connector from the battery connector. 

(b) Put a protective cap on the electrical connector and on the battery connector. 




24-36-01-000-802-A/400 

Page 401 

Rev.10 - AUG 27/10 




A 



GEN 1 

BATT 1 

AUTO 

OFF 

ON 

OFF 

ELECTRICAL 

GPU 

BUS TIE 

AUTO 

1 OPEN 2 OPEN 

ELEC EMER 

GEN 2 

BATT 2 

AUTO 

OFF 

ON 

OFF 


PANEL 

A 



Figure 401 


24-36-01-000-802-A/400 

Page 402 

Rev.05 - AUG 14/09 




211 DZ 

A 

ZONE 

211 

ELECTRICAL 

CONNECTOR 

BATTERY 

CONNECTOR 

B 

A 

MAIN BATTERY 



B 


Main Battery 1 - Disconnection/Connection 

Figure 402 


24-36-01-000-802-A/400 

Page 403 

Rev.10 - AUG 27/10 




A 

ZONE 

195 



ELECTRICAL 

CONNECTOR 

BATTERY 

CONNECTOR 

195 FR 

B 

A 

MAIN BATTERY 

B 



Figure 403 


24-36-01-000-802-A/400 

Page 404 

Rev.10 - AUG 27/10 


TM 



GHSH TASK 24-36-01-400-801-A 

1. Main Battery - Installation 

A. General 

(1) This task gives the procedure to install the main batteries. 



compartment in the RH (Right Hand) wing-to-fuselage aft fairing. 

B. Job Set-Up 

(1) Make sure that the aircraft is in the same configuration as it was at the end 

of the removal task (GHSH TASK 24-36-01-000-801-A/400). 

C. Main Battery - Installation 

(1) Install the battery 1 as follows: (Refer to figure 402) 

(a) Carefully put the battery 1 in its installation position. 

(b) Tighten the self-locking retainers. 

(c) Put the clamp to the air-escape hose. 

(d) Install the air-escape hose to battery 1 outlet. 

NOTE: • Before the installation of the air-escape hose, make sure 

that its interior and outlets are dry and clear of unwanted 

material. 

• Make sure that there are no kinks in the air-escape hose 

that can prevent airflow. 

(e) Tighten the hose clamp. 

(f) Remove the protective cap from the electrical connector and from the 

connector of the battery 1. 

(g) Connect the electrical connector to the battery 1. 

(h) Safety the electrical connector with lock wire. 

(2) Install the battery 2 as follows: (Refer to figure 403) 

(a) Carefully put the battery 2 in its installation position. 

(b) Tighten the self-locking retainers. 

(c) Remove the protective cap from the electrical connector and from the 

connector of the battery 1. 

(d) Connect the electrical connector to the battery 1. 




(1) Remove all tools, equipment and unwanted materials from the work area. 

(2) For battery 1: 

(a) Install the access panel 211DZ. 

(b) Close the forward baggage-compartment door. 

(3) For battery 2, close the access door 195FR. 


24-36-01-400-801-A/400 

Page 401 

Rev.07 - DEC 11/09 


TM 



211 DZ 



A 

ZONE 

211 

BATTERY 1 


RETAINER (2x) 

CLAMP 

B 

A 

ELECTRICAL 

CONNECTOR 

B 

VENTILATION 

HOSE 



Figure 401 


24-36-01-400-801-A/400 

Page 402 

OCT 31/08 


TM 



A 

ZONE 

195 

BATTERY 2 


RETAINER (2x) 

195 FR 

B 

A 



ELECTRICAL 

CONNECTOR 

B 



Figure 402 


24-36-01-400-801-A/400 

Page 403/404 

OCT 31/08 




GHSH TASK 24-36-01-400-802-A 

1. Main Battery - Connection 

A. General 

(1) This task gives the procedure to connect the main batteries. 



compartment, in the RH (Right Hand) wing-to-fuselage aft fairing. 

B. Job Set-Up 


of the removal task (GHSH TASK 24-36-01-000-802-A/400). 

C. Main Battery - Connection 

(1) Connect battery 1 as follows: (Refer to Figure 401) 

(a) Remove the protective cap from the electrical connector and from the 

battery connector. 

(b) Connect the electrical connector to the battery connector. 

(2) Connect battery 2 as follows: (Refer to Figure 402) 

(a) Remove the protective cap from the electrical connector and from the 

battery connector. 

(b) Connect the electrical connector to the battery connector. 


(1) Remove all tools, equipment and unwanted materials from the work area. 

(2) For battery 1: 

(a) Install the access panel 211DZ. 

(b) Close the forward baggage-compartment door. 

(3) For battery 2, close the access door 195FR. 

(4) On the ELECTRICAL control panel, remove the DO NOT OPERATE tag 

from the BATT 1 and BATT 2 switches. 




24-36-01-400-802-A/400 

Page 401 

Rev.10 - AUG 27/10 




211 DZ 



A 

ZONE 

211 

ELECTRICAL 

CONNECTOR 

BATTERY 

CONNECTOR 

B 

A 

MAIN BATTERY 

B 



Figure 401 


24-36-01-400-802-A/400 

Page 402 

Rev.10 - AUG 27/10 




A 

ZONE 

195 

ELECTRICAL 

CONNECTOR 

BATTERY 

CONNECTOR 

195 FR 

B 

A 

MAIN BATTERY 



B 



Figure 402 


24-36-01-400-802-A/400 

Page 403 

Rev.10 - AUG 27/10 




A 



GEN 1 

BATT 1 

AUTO 

OFF 

ON 

OFF 

ELECTRICAL 

GPU 

BUS TIE 

AUTO 

1 OPEN 2 OPEN 

ELEC EMER 

GEN 2 

BATT 2 

AUTO 

OFF 

ON 

OFF 


PANEL 

A 


Electrical Control Panel - Disconnection/Connection 

Figure 403 


24-36-01-400-802-A/400 

Page 404 

OCT 31/08 




GHSH TASK 24-41-00-860-801-A 

1. Energization of the Aircraft with an External DC Power Supply - Aircraft/ 

System Configuration 

A. General 

(1) This task gives the procedure to supply electrical power to the aircraft with 

an external DC (Direct Current) power supply. 

(2) The 28 V DC (Volt Direct Current), external power supply is connected to 

the aircraft by means of the receptacle installed on the left side of the rear 

fuselage. 

B. Job Set-Up 

WARNING: MAKE SURE THAT IT IS SAFE TO ENERGIZE THE 

AIRCRAFT. CIRCUITS THAT ARE NOT SAFE CAN 

CAUSE INJURY TO PERSONS AND/OR DAMAGE TO 

EQUIPMENT. 

(1) Make sure that the external power supply operates correctly before you 

supply power to the aircraft. 


20-00-00-910-801-A/200). 

(3) If the conditioned air is not necessary, open these circuit breakers and 

attach a circuit breaker ring and tag to each one of them: 

• TEMP PWR 1-LHCBP (EMERGENCY BUS 1 AIR COND) 

• TEMP PWR 2-RHCBP (DC BUS 2 AIR COND PRESN) 

(4) On the LH (Left Hand) lateral console, on the ELECTRICAL control panel, 

make sure that these switches are set to these positions: 

• BUS TIE - AUTO 

• ELEC EMER - unlatched (off) 

• BATT 1 - OFF 

• BATT 2 - OFF 

(5) Set the GPU (Ground Power Unit) (GSE 016) to ON. Refer to the GSE 

Appendix. 

(6) Adjust the output voltage of the external DC power supply to 28 V DC. 

(7) Set the GPU (GSE 016) to OFF. Refer to the GSE Appendix. 

(8) Open the access door 195CL to get access to the external DC power-supply 

receptacle. 

C. Energization of the Aircraft with an External DC Power Supply - Maintenance 

Practices 

(1) Connect the main batteries (GHSH TASK 24-36-01-400-802-A/400). 

(2) Connect the GPU (GSE 016) to the external DC power-supply receptacle. 

Refer to the GSE Appendix. 

(3) Set the GPU (GSE 016) to ON. Refer to the GSE Appendix. 




24-41-00-860-801-A/200 

Page 201 

Rev.03 - APR 17/09 






(4) On the ELECTRICAL control panel, do the steps that follow: 

• Set the BATT 2 switch to ON. 

• Set the BATT 1 switch to ON. 

(5) Make sure that the AVAIL lamp in the GPU pushbutton comes on. 

(6) Set the GPU pushbutton to the latched (on) position. 

Result: 

• The AVAIL lamp in the GPU pushbutton goes off. 

• The IN USE lamp in the GPU pushbutton comes on. 

(7) On the MFD (Multi Function Display), on the ELEC page, make sure that 

the electrical synoptic status shows as follows: 

Table 201 - ELECTRICAL SYNOPTIC STATUS 

BUS/LINE STATUS COLOR 

All Buses Energized Green 

CENTRAL BUS to DC BUS 1 Energized Green 

CENTRAL BUS to DC BUS 2 Energized Green 

CENTRAL BUS to DC BUS 2 De-energized White 


24-41-00-860-801-A/200 

Page 202 

Rev.03 - APR 17/09 




A 

GEN 1 

BATT 1 

AUTO 

OFF 

ON 

OFF 

ELECTRICAL 

GPU 

BUS TIE 

AUTO 

1 OPEN 2 OPEN 

ELEC EMER 

GEN 2 

BATT 2 

AUTO 

OFF 

ON 

OFF 




PANEL 

A 



Figure 201 


24-41-00-860-801-A/200 

Page 203 

Rev.01 -DEC 05/08 




A 

ZONE 

195 

195 CL 



B 

B 

A 

EXTERNAL DC POWER 

RECEPTACLE 


Energization of the Aircraft with an 

External DC Power Supply - Maintenance Practices 

Figure 202 


24-41-00-860-801-A/200 

Page 204 

Rev.01 - DEC 05/08 




GHSH TASK 24-41-00-860-802-A 

1. Aircraft De-energization - Aircraft/System Configuration 

A. General 

(1) This task gives the procedure remove the external DC (Direct Current) 

electrical power supply from the aircraft. 

(2) The 28 V DC (Volt Direct Current), external power supply is connected to 

the aircraft by means of the receptacle installed on the left side of the rear 

fuselage. 

B. Job Set-Up 






of the energization task (GHSH TASK 24-41-00-860-801-A/200). 

C. Aircraft De-energization - Maintenance Practices 

(1) Do these procedures to de-energize the aircraft: 

(a) On the ELECTRICAL control panel, set the BATT 1 and BATT 2 

switches to OFF. 

(b) On the ELECTRICAL control panel, set the GPU pushbutton to the 

latched-out (off) position. 

Result: 

1. The IN USE lamp in the GPU pushbutton goes off. 

2. The AVAIL lamp in the GPU pushbutton comes on. 

(c) Set the GPU (GSE 016) to OFF. Refer to the GSE Appendix. 

Result: 

1. On the ELECTRICAL control panel, the AVAIL lamp in the GPU 

pushbutton goes off. 

WARNING: REMOVE THE ELECTRICAL POWER FROM THE 

EXTERNAL POWER CABLE BEFORE YOU REMOVE 

IT FROM THE AIRCRAFT. IF YOU DO NOT OBEY THIS 

PRECAUTION, AN ELECTRIC SHOCK CAN OCCUR 

AND CAUSE INJURY TO PERSONS. 

(d) Disconnect the GPU (Ground Power Unit) (GSE 016) from the external 

DC power receptacle. Refer to the GSE Appendix. 

(e) Disconnet the main batteries (GHSH TASK 24-36-01-000-802-A/400). 


(1) Close access door 195CL. 

(2) If applicable, remove the circuit breaker ring and tag from these circuit 




24-41-00-860-802-A/200 

Page 201 

Rev.03 - APR 17/09 




breakers and close them: 

• TEMP PWR 1-LHCBP (EMERGENCY BUS 1 AIR COND) 

• TEMP PWR 2-RHCBP (DC BUS 2 AIR COND PRESN) 


used. 




24-41-00-860-802-A/200 

Page 202 

Rev.03 - APR 17/09 




A 

GEN 1 

BATT 1 

AUTO 

OFF 

ON 

OFF 

ELECTRICAL 

GPU 

BUS TIE 

AUTO 

1 OPEN 2 OPEN 

ELEC EMER 

GEN 2 

BATT 2 

AUTO 

OFF 

ON 

OFF 




PANEL 

A 



Figure 201 


24-41-00-860-802-A/200 

Page 203 

Rev.01 - DEC 05/08 




A 

ZONE 

195 

195 CL 



B 

B 

A 

EXTERNAL DC POWER 

RECEPTACLE 


De-energization of the Aircraft with an 

External DC Power Supply - Maintenance Practices 

Figure 202 


24-41-00-860-802-A/200 

Page 204 

Rev.01 - DEC 05/08 


TM 



GHSH TASK 27-04-01-710-801-A 

1. Trim Actuator Controller - Operational Test 

A. General 

(1) This task gives the procedure to do the operational check of trim actuator 

controllers TAC1 and TAC2. 

B. Job Set-Up 






41-00-860-801-A/200). 

C. Trim Actuator Controller - Operational Test 

(1) Do the operational check of the roll trim system as follows: 

(a) On the TRIM control panel, turn the roll trim switch and do a full travel 

test. 

NOTE: If you operate the trim switch for more than 3 seconds, the 

TAC automatically stops the motion. 

(b) Make sure that the roll trim indication on the MFD (Multi-Function Display) 

makes a full travel. 

(2) Do the operational test of the normal pitch trim system as follows: 

(a) On the control yoke, push the pitch trim switch and do a full travel test. 



(b) Make sure that the pitch trim indication on the MFD makes a full travel. 

(c) Make sure that the trim indication on the MFD does not show asymmetric 

or invalid pitch trim position. 

(d) After pitch trim command, make sure that there are no CAS (Crew 

Alerting System) messages. 

(3) Do the operational test of the yaw trim system as follows: 

(a) On the TRIM control panel, push the yaw trim switch and do a full 

travel test. 



(b) Make sure that the yaw trim indication on the MFD makes a full travel. 

(4) Do the operational test of the backup pitch trim system as follows: 

(a) On the TRIM control panel, select the backup mode and do a full travel 

test of the pitch-trim backup system. 




27-04-01-710-801-A/500 

Page 501 

OCT 31/08 


TM 







(b) Make sure that the CAS message "PTRIM NML FAIL" appears on the 

CAS window. 

(c) Make sure that the pitch trim indication on the MFD makes a full travel. 

(d) Make sure that the trim indication on the MFD does not show asymmetric 

or invalid pitch trim position. 

(e) After pitch trim command, make sure that there are no additional CAS 

messages related to the trim system. 

(f) On the TRIM control panel, return the backup mode switch to the OFF 

position. 




used. 



Page 502 

Rev.07 - DEC 11/09 


TM 



A 

A 

PITCH TRIM 

SWITCH 

TRIMS 

B 

ROLL 

YAW 

B 

C 

MFD DISPLAY 

TRIM INDICATIONS 

PITCH 

20 

LEFT 

LWD 

BKP 

OFF 

TRIM 

YAW 

ROLL 

PITCH BKP 

DN 

UP 

MODE 

RIGHT 

RWD 

A 

TYPICAL 

YAW TRIM 

SWITCH 

ROLL TRIM 

SWITCH 

BACKUP PITCH 

TRIM SWITCH 



C 



Trim Actuator Controller - Operational Test 

Figure 501 



Page 503/504 

OCT 31/08



GHSH TASK 28-00-00-910-801-A 

1. Fuel - Maintenance and Servicing Practices 

A. General 

(1) This task gives procedures and information related to the maintenance 

and servicing of the fuel system. 

B. General Warnings for the Fuel System Maintenance and Servicing Procedures 

WARNING: • FOR CORRECT AND CAREFUL HANDLING OF FUEL 

AND SUPPORT EQUIPMENT, MAINTENANCE 

PERSONNEL MUST KNOW THE SYSTEM AND ITS 

SAFETY CONDITIONS. MAKE SURE THAT ONLY 

TRAINED AND APPROVED PERSONNEL DO THE FUEL 

SYSTEM MAINTENANCE. 

• IF FUEL GETS INTO YOUR EYES, WASH THE EYES 

IMMEDIATELY WITH A LARGE QUANTITY OF WATER. 

GET MEDICAL AID IMMEDIATELY. 

• IMMEDIATELY REMOVE CLOTHING THAT IS WET WITH 

FUEL. ALL JET FUELS CAN CAUSE INJURY TO THE 

SKIN. FULLY FLUSH THE RELATED SKIN AREA. DO 

NOT LET THESE FUELS TOUCH YOU. 

• DO NOT WEAR CLOTHING MADE OF SYNTHETIC 

MATERIAL OR CLOTHING WITH METAL ZIPPERS OR 

BUTTONS. THESE ITEMS CAN CAUSE A SPARK. AS A 

RESULT, A FIRE OR EXPLOSION CAN OCCUR. 

• WHEN YOU DO MAINTENANCE ON THE FUEL 

SYSTEM, YOU MUST DISCHARGE THE STATIC 

ELECTRICITY FROM YOUR BODY. TO DO THIS, YOU 

MUST TOUCH A STATIC GROUND CABLE OR 

GROUNDED OBJECT BEFORE YOU START THE 

OPERATION. 

• DO THE FUEL SYSTEM MAINTENANCE ONLY IN AN 

AREA THAT PERMITS FREE MOVEMENT AND ACCESS 

OF FIRE FIGHTING EQUIPMENT AND PERSONNEL. 

MAKE SURE THAT FIRE EXTINGUISHERS WITH A 

MINIMUM OF 55 LB (25 KGF) OF CARBON DIOXIDE, OR 

EQUIVALENT, ARE AVAILABLE AND READY FOR USE 

IN AN EMERGENCY SITUATION. USE ONLY 

EXPLOSION-PROOF EQUIPMENT WHEN YOU DO 

TASKS AT LESS THAN 15 M (50 FT) AWAY FROM AN 




28-00-00-910-801-A/200 

Page 201 

OCT 31/08 







OPEN TANK OR HAZARDOUS LOCATIONS. 

• ALWAYS DO MAINTENANCE ON THE FUEL SYSTEM IN 

AN AREA THAT HAS A GOOD AIRFLOW. NO FUEL 

VAPOR CONCENTRATION IS PERMITTED. THIS IS TO 

PREVENT A FIRE OR EXPLOSION. 

• ALL SUPPORT EQUIPMENT NOT NECESSARY FOR 

THESE TASKS MUST BE AT A MINIMUM DISTANCE OF 

15 M (50 FT) FROM THE AIRCRAFT. 

• MAKE SURE THAT THERE ARE NO PERSONS WITH 

LIT CIGARETTES OR OTHER SOURCES OF SPARKS 

OR OPEN FLAMES IN A RADIUS OF 15 M (50 FT) FROM 

THE AREA WHERE THE MAINTENANCE IS DONE. 

• INSTALLATION OR REMOVAL OF THE BATTERIES OR 

RELATED EQUIPMENT IS NOT PERMITTED. 

• STATICALLY GROUND THE ELECTRIC EQUIPMENT TO 

PREVENT A HIGH CONCENTRATION OF STATIC 

ELECTRICITY WHEN YOU USE THE EQUIPMENT. 

• ALL EXTERNAL LIGHT SOURCES MUST BE AWAY 

FROM THE AIRCRAFT BEFORE YOU START TO DO 

THE TASKS. 

• DO NOT USE HEAT GUNS AT LESS THAN 35 M (100 FT) 

FROM THE AIRCRAFT WHEN YOU REFUEL OR 

DEFUEL THE TANK, OR WHEN THE FUEL LINES ARE 

OPEN. IF YOU DO NOT OBEY THIS PRECAUTION, AN 

EXPLOSION CAN OCCUR IN THE FUEL TANK. 

(1) Obey these safety precautions and warnings when you do maintenance or 

servicing procedures in the fuel system. 

C. Specific Warnings for Servicing Procedures 

WARNING: • DO NOT DO THE REFUELING PROCEDURE IN A 

HANGAR OR AT LESS THAN 30 M (100 FT) FROM 

HANGARS. 

• DURING THE PRESSURE REFUELING PROCEDURE, 

KEEP THE AREAS AROUND THE FUEL TANKS AND 

VENTS WITH NO VEHICLES AND EQUIPMENT. 

• DURING THE REFUELING OPERATION, MAKE SURE 

THAT NO HIGH-FREQUENCY RADIO TRANSMITTER IS 

IN OPERATION AT LESS THAN 60M (200 FT) FROM THE 

AIRCRAFT. NO RADAR EQUIPMENT MUST BE IN 

OPERATION AT 120 M (400 FT) FROM THE AIRCRAFT. 

28-00-00-910-801-A/200 

Page 202 

OCT 31/08 




THIS IS TO PREVENT A FIRE OR EXPLOSION. 

• MAKE SURE THAT THE AIRCRAFT IS PARKED AT 

RAMP LEVEL AND IS HEADED INTO THE WIND. 

• DO NOT REFUEL THE AIRCRAFT IF THERE IS AN 

OVERHEAT INDICATION IN THE AIRCRAFT. 

• DO NOT FILL OR CHANGE THE OXYGEN BOTTLE 

DURING THE REFUELING PROCEDURES. 

• PREVENT FUEL SPILLAGE. IF FUEL SPILLAGE 

OCCURS, CLEAN THE AREA IMMEDIATELY. 

• WHEN YOU REFUEL THE AIRCRAFT, MAKE SURE 

THAT THE FUEL QUANTITY UNIT IS CORRECT. AN 

INCORRECT READING OF THE FUEL QUANTITY CAN 

CAUSE AN AIRCRAFT ACCIDENT. 

• MAKE SURE THAT THE FUEL LEVEL IN THE TANKS IS 

SYMMETRICAL AFTER THE REFUELING OPERATION 

IS COMPLETE. 

• STOP THE REFUELING PROCEDURE WHEN THERE 

ARE THUNDERSTORMS OR LIGHTNING AT A 

DISTANCE OF LESS THAN 16 KM (10 MILES). 

(1) Obey these safety precautions and warnings when you do the servicing 

procedures in the fuel system. 




28-00-00-910-801-A/200 

Page 203/204 

OCT 31/08 




GHSH TASK 29-10-00-901-803-A 

1. Main Hydraulic System - Pressurization 

A. General 

(1) This task gives the procedure to pressurize the hydraulic system. 

B. Job Set-Up 


20-00-00-910-801-A/200). 

(2) Do a check of the level of the hydraulic reservoir (GHSH TASK 12-13-00- 

610-802-A/300). 

C. Pressurization of the hydraulic system 


(2) Energize the aircraft (GHSH TASK 24-41-00-860-801-A/200). 

(3) Remove access panel 242AZ to get access to the RPDU. 

(4) Open this circuit breaker and put a circuit breaker ring and tag on it: 

• S/GENS OFF MON-RPDU (DC BUS2) 

(5) Make sure that the aircraft is in the on ground configuration. 

NOTE: This configuration is required to open the Emergency / Parking 

Brake Line SOV. 

(6) Make sure that the engine throttle levers are in idle position. 

NOTE: This configuration is required to open the Emergency / Parking 

Brake Line SOV. 

(7) Make sure that the hydraulic pressure indication on the MFD is near 3000 psi. 

(8) Make sure that the emergency / parking brake pressure (EMER BRK 

ACCU PRES) on the MFD is near 3000 psi. 

(9) Make sure that the messages "HYD LO PRESS" and "HYD HI TEMP" or 

"EMER BRK LO PRES" do not show" on the CAS. 


(1) Install access panel 242AZ. 


used. 




29-10-00-901-803-A/200 

Page 201 

Rev.04 - JUN 16/09 


PUSH 

VOL 

ID 

NAV 

PUSH 

1−2 

INSET 

TAS 

170KT 

SENSOR 

HDG 356 CRS 049 

PDF 

W 

OBS 

S 

CDI 

ADF/DME 

E 

XPDR 

1600 

1500 

1400 

1200 

1100 

IDENT 

2992IN 

4 

2 

2 

4 

XPDR1 1253 ALT LCL 17:12:20 

TMR/REF 

CAS 

AP FAIL 

YD FAIL 

SWS FAIL 

ADS 2 FAIL 

ADS 1 FAIL 

AHRS 2 FAIL 

AHRS 1 FAIL 

GIA 2 FAIL 

CONFIG MDL FAIL 

HYD LO PRESS 

FLAP FAIL 

BRK FAIL 

AURAL WARNING FAIL 

OXY LO PRESS 

NRST 

CAUTION 

EMERG 

FPL 

CLR 

DFLT MAP 

COM 

PUSH 

1−2 

BARO 

PUSH 

STD 

FMS 

VOL PUSH 

SQ 

MENU 

PROC 

ENT 

PUSH CRSR 

PUSH 

VOL 

ID 

NAV 

PUSH 

1−2 

VOL PUSH 

SQ 

NAV1 

GS 0KT ETA LCL TRK NM ETE __:__ COM1 

NAV2 

COM2 

EMERG 

LAKE AS NORTH UP 12 H 44 

DELTONA 

TAT 10 C 

COM 

TFR 

BARY 

SAT 10 C 

NO DATA 

ENTERPRISE 

TAS 0 KT 

GW4290 

KG 

OSTEEN ELEC HYD PRES OXY EMER BRK 

PUSH 

ACCU PRES 1−2 

LAKE MONROE 

15 C 

SANFORD 

BARO 

KSFB 

C 

+12 

15 C 

42.8 N2% 42.8 

3000 PSI 1400 PSI 3000 PSI 

125 OIL PRES PSI 125 LAKE JESSUP 

PUSH 

95 OIL TEMP C 95 

DOORS 

STD 

+12 

PASSENGER 

FUEL 

25 FF KGH 25 

WINTER OPRINOO 

LAKE HA 

330 

330 

BAGGAGE FWD 

3 ODIEDO 

TEMP 0 C 

ELEC CABIN 

417 

CHULUOTA 

BATT1 28V 

+50 

ALT 5200FT 

+50 

BATT2 28V 

GOLDENROD 6 

RATE 0FPM 

LAKE PICKETT 

SPDBRK 

DELTA-P 0PSI 

CLOSED LFE 5200FT 

UNION PARK 

BITHLO 

OXY 1400 PSI 

50 

LG 

FLAPS 417 

408 3 

DN 

MENU 

DN DN 2 

FPL PROC 

TRIM 

ROLL 

PITCH 

12 

CLR ENT 

20 

YAW 

528 

30NM 

SYSTEM 

DFLT MAP 

ENG SET LFE STATUS ECS ELEC FUEL DEICE ENG MNT BACK 

FMS 

PUSH CRSR 



A 

D 

110.80 

109.90 

108.40 

108.90 

__:___ _.__ 

SYSTEM - STATUS 

120.350 

122.800 

122.800 

134.150 

42.0 N1% 

42.0 

BATT1 

28.2 V 

ST. JOWNS RIVER 

713 ITT 

713 

BATT2 

28.2 V 

FQ KG 

660 

RANGE 

− + 

D 

PUSH 

PAN 



C 

200 

180 

170 

160 

140 

3O 

24 

B 

20 

33 

N 

3 

20 

10 10 

10 10 

21 

NAV1 

356 

15 

PFD 1 

6 

12 

B 

HYD SYS 

B 

CAS WINDOW 

40 

13 

20 

E 

RANGE 

− + 

D 

PUSH 

PAN 

PFD 2 

FUEL 

A 

PUMP 1 XFR PUMP 2 

ON 

AUTO 

OFF 

PAX SIGNS ELT HYD PUMP 

PED−BELTS 

BELTS 

OFF 

ON 

ARMED 

ON 

AUTO 

OFF 

TEST/RESET 

C 

HYD LO PRES 

HYD HI TEMP 

OFF 

STALL WRN 

INHIB 

AUTO 

ON 

3000 

D 

PSI 

E 


Main Hydraulic System - Pressurization 

Figure 201 


29-10-00-901-803-A/200 

Page 202 

OCT 31/08 




GHSH TASK 29-10-00-910-801-A 

1. Main Hydraulic System - Depressurization 

A. General 

(1) This task gives the procedure to release the pressure from the hydraulic 

system. 

B. Job Set-Up 


20-00-00-910-801-A/200). 

(2) Open access door 212BR in zone 212. 

(3) Open this circuit breaker and put a circuit breaker ring and tag on it: 

• HYD PUMP-RHCBP (DC BUS 2) 

C. Main Hydraulic System - Depressurization 

(1) Release the pressure from the hydraulic system as follows: 

(a) On the HYDRAULIC control panel, set the "HYD PUMP" switch to OFF. 

(b) Push the dump valve button until all hydraulic fluid returns to the 

hydraulic reservoir. 

(2) Release the pressure from the emergency/parking brake line as follows: 

(a) Slowly push and pull the emergency/parking brake T-handle until the 

emergency/parking brake indicating lamp on the main panel goes off 

(7 complete cycles). 


(1) Remove the circuit breaker ring and tag from this circuit breaker, and 

close it: 

• HYD PUMP-RHCBP (DC BUS 2) 


(3) Close access door 212BR in zone 212. 


used. 




29-10-00-910-801-A/200 

Page 201 

Rev.04 - JUN 16/09 






A 

ZONE 

210 

A 

B 

ACCUMULATOR 

DUMP VALVE 

C 

EMERGENCY/PARKING 

BRAKE HANDLE 

EMERGENCY/PARKING 

BRAKE CABLE 

B 

C 


Depressurization of the Hydraulic System 

Figure 201 


29-10-00-910-801-A/200 

Page 202 

OCT 31/08 




GHSH TASK 32-00-00-910-801-A 

1. Landing-Gear Safety Pin - Standard Practices 

A. General 

(1) The landing-gear safety pins must be installed while the aircraft is parked, 

during maintenance procedures, and during the towing of the aircraft. 

B. Job Set-Up 





(1) Make sure that the landing gear control lever is in the DOWN position. 

C. Landing-Gear Safety Pin - Location 

(1) Use the landing-gear safety pins to lock the nose and main landing gears 

in the down position. 

(2) Make sure that personnel can see the red REMOVE-BEFORE-FLIGHT 

streamer clearly. 




32-00-00-910-801-A/200 

Page 201 

OCT 31/08 




B 

ZONE 

711 

C 

A 



ZONES 

721 

731 

B 

C 

SAFETY PIN 

A 

C 



Landing-Gear Safety Pin - Location 

Figure 201 

32-00-00-910-801-A/200 

Page 202 

OCT 31/08 




GHSH TASK 32-45-00-210-801-A 

1. NLG and MLG Tires - General Visual Inspection 

A. General 

(1) This task gives the procedure to do an inspection of the tires of the NLG 

(Nose Landing Gear) and MLG (Main Landing Gear). This inspection is a 

visual examination of the tires for wear, damage, and general condition. 

(2) When you must replace a tire, before you disassemble the wheel assembly, 

make a mark with a chalk in the damaged area. 

B. Job Set-Up 





(1) Install the landing-gear safety pins (GHSH TASK 32-00-00-910-801-A/200). 

C. Nose and Main Wheel Tire - Inspection 

WARNING: DO NOT GO NEAR HOT TIRES INSTALLED ON THE 

AIRCRAFT. IF IT IS NECESSARY TO MEASURE THE TIRE 

TEMPERATURE, GO NEAR THE TIRE FROM ITS FRONT, 

NOT FROM ITS SIDE. HIGH TEMPERATURE CAN CAUSE 

TIRE EXPLOSION. 

(1) Examine the tires of the NLG and MLG. Replace the wheel if you find on a 

tire one or more of the conditions that follow: 

(a) Cut into the casing plies. 

(b) For NLG tires, damage, cut, or wear on the chine. 

(c) Cut across the tread rib to the fabric. 

(d) Rib undercutting. 

(e) Tread worn, with top fabric worn through for more than 1/8 of the circumference 

of the tire or more than 1 in. (25 mm) wide. 

NOTE: • Tires within these limits can continue in service no longer 

than necessary to be replaced. Tires worn beyond this 

limit may be unsafe. 

• For MLG, 1/8 of circumference of the tire is equal to 8.2 

in. (210 mm). 

• For NLG, 1/8 of circumference of the tire is equal to 5.9 

in. (150 mm). 

(f) Tread or sidewall bulge. 

(g) Peeled rib. 

(h) Thrown tread. 

(i) Open tread splice. 




32-45-00-210-801-A/600 

Page 601 

Rev.10 - AUG 27/10 






(j) Heat damage in bead. 

(k) Impact break. 

(l) One or more of the conditions that follow with exposed fabric: 

1. Groove cracking. 

2. Dry braking flat spot. 

3. Tread chunking. 

4. Chevron cutting. 

5. Sidewall crack. 

6. Sidewall cut or snag. 

7. Radial or circumferential crack. 

(m) Balance affected because of wet braking flat spot or dry braking flat spot. 

NOTE: Uneven wear - if you find irregular wear, the tire can be 

disassembled and turned in the opposite direction if there 

is no fabric that can be seen. 


(1) Put the aircraft back to its initial condition. 


32-45-00-210-801-A/600 

Page 602 

Rev.10 - AUG 27/10 




A 

ZONE 

711 

02 

01 

A 

ZONES 

721 

731 

CUT ACROSS TREAD RIBS 

1/8 OF THE 

CIRCUNFERENCE 

02 

1 in 

SIDEWALL 

BEAD 

TREAD WORN TO ANY 

GROOVE BASE 

01 

CHINE 

TOP FABRIC 

APPLICABLE ONLY TO THE NLG TIRE. 

TREAD 

TREAD 

GROOVE 

CASING PLIES 

(FABRIC) 

A 

TYPICAL 

TREAD 

RIB 

RIB UNDERCUTTING 

1/8 OF THE CIRCUNFERENCE = 8.2 in (210 mm) FOR MAIN LANDING GEAR 

OR 5.9 in (150 mm) FOR NOSE LANDING GEAR 

TREAD OR SIDEWALL BULGE 





Nose and Main Wheel Tires - Inspection 



32-45-00-210-801-A/600 

Page 603 

Rev.10 - AUG 27/10





PEELED RIB 

OPEN TREAD SPLICE 

THROWN TREAD 

HEAT DAMAGE 

IMPACT BREAK 

GROOVE CRACKING 






32-45-00-210-801-A/600 

Page 604 

Rev.10 - AUG 27/10



DRY−BRAKING FLAT−SPOT 

CHEVRON CUTTING 

SIDEWALL CRACKS 

TREAD CHUNKING 

CUT OR SNAG 



RADIAL OR CIRCUMFERENTIAL CRACK 

WET BRAKING FLAT−SPOT 






32-45-00-210-801-A/600 

Page 605/606 

Rev.10 - AUG 27/10



APPENDIX 





GROUND SUPPORT 

EQUIPMENT 

APPENDIX 





GHSH GSE APPENDIX - TABLE OF CONTENTS 

Ground Support 

Equipment Appendix 

SUBJECT GSE NUMBER PAGE 

Cover, Pitot-static ......................................... GSE 003 1 

Plug-protection, Static 

Port............................................................... GSE 008 1 

Cover-pitot.................................................... GSE 009 1 

Ground Power Unit....................................... GSE 016 1 

Sampler, Fuel............................................... GSE 022 1 

Tool, Defueling ............................................. GSE 023 1 

Towbar Head................................................ GSE 026 1 

Towbar.......................................................... GSE 027 1 

Set-transparency Shade, 

Cockpit ......................................................... GSE 029 1 

Cover, Engine............................................... GSE 030 1 




GHSH GSE Appendix - Table of Contents 

Page TOC-1/2 

Rev.01 -DEC 05/08 




GSE NUMBER: 003 

ITEM NAME: PITOT-STATIC COVER 

PURPOSE AND USE: Used to protect the pitot-static port. 

PART NUMBER: KPC3-640-35 (Figure 1) 

1. MANUFACTURER 

SESAME TECHNOLOGIES INC. 

2. TECHNICAL SPECIFICATIONS 

A. The cover is made of red Kevlar 

B. It withstands temperatures of 427ºC (800ºF) 

3. BRIEF OPERATION DESCRIPTION 

Not applicable. 

4. TOOL CONSISTS OF 


5. REPLACEMENT PARTS LIST 


6. QUANTITY 

1 

7. DIMENSIONS AND WEIGHT 

120 x 15 mm (4.72 x 0.60 in); 0.1 kg (0.22 lb) 

8. SUPPORTING TOOLS 


9. GSE MAINTENANCE 

Keep the cover clean and protected against rain, sun, and dust. 

10. TOOL HISTORY 




EFFECTIVITY: ALL GSE 003 

Page 1 

OCT 31/08 






A 

A 


Pitot-Static Cover 

Figure 1 


Page 2 

OCT 31/08 





ITEM NAME: PLUG-PROTECTION, STATIC PORT 

PURPOSE AND USE: Used to protect the static ports. 

PART NUMBER: AGE-05118-401 (Figure 1) 


EMBRAER 


It is a pair of machined nylon plugs equipped with a "REMOVE BEFORE FLIGHT" 

flag. 






Item Nomenclature P/N Quantity 

1 Plug AGE-05118-901 2 

2 Flag PE915103-5NF 1 

6. QUANTITY 

2 


38 x 16 mm (1.5 x 0.63 in); 0.1 kg (0.22 lb) 

NOTE: The dimensions above refer to the nylon plug. 




Keep the plugs clean and protected against rain, sun, and dust. 

Before and after using the plugs, make sure that they are in perfect conditions. 






Page 1 

OCT 31/08 






ANEMOMETRIC STATIC 

PORTS 1 AND 3 

A 

TYPICAL 

A 

2 

1 

A 

ANEMOMETRIC STATIC 

PORTS 2 AND 4 


Plug-Protection, Static Port 

Figure 1 


Page 2 

OCT 31/08 





ITEM NAME: PITOT COVER 

PURPOSE AND USE: Used to protect the pitot pressure ports. 

PART NUMBER: KPC3-480-325 (Figure 1) 


SESAME TECHNOLOGIES INC. 


A. The cover is made of red Kevlar 

B. It withstands temperatures of 427ºC (800ºF) 







6. QUANTITY 

2 


115 x 12 mm (4.52 x 0.47 in); 0.1 kg (0.22 lb) 




Keep the covers clean and protected against rain, sun, and dust. 






Page 1 

OCT 31/08 






A 

B 

B 

A 


Pitot Cover 

Figure 1 


Page 2 

OCT 31/08 





ITEM NAME: UNIT, GROUND POWER 

PURPOSE AND USE: Used to supply electrical power on the ground for starting 

the engines and servicing the electrical and avionics systems. 

PART NUMBER: 11A6647-1010 (Figure 1) 


TRONAIR 


A. A solid state rectifier 28.5 V DC, nominal current 600 A, input voltage 200 to 

230 V AC 3-phase, 50/60 Hz and 56 A (power 20 Kva) 

B. Three-position current limit control with DC on/off switch 

C. Adjustable voltage control from 20 to 31 V DC located on the control panel 

(digital LED) 

D. DC ripple voltage (with filter)






For information on maintenance, refer to the vendor's documentation. 






Page 2 

Rev.01 -DEC 05/08 




A 

ZONE 

195 

A 




Ground Power Unit 

Figure 1 


Page 3/4 

Rev.01 -DEC 05/08 





ITEM NAME: FUEL SAMPLER 

PURPOSE AND USE: Used to take fuel samples for visual analysis. 

PART NUMBER: CCA-39680 (Figure 1) 


Curtis Superior Valve Company 


A transparent plastic cup, provided with a stainless steel drain rod. 


The fuel drain valve is actuated by means of the steel rod of the drain cup. As the 

drain valve poppet is pushed by the rod, fuel is allowed to flow into the plastic 

cup. 





6. QUANTITY 

1 


45 x 80 mm (1.8 x 3.1 in) 










Page 1 

OCT 31/08 




A 



A 


Fuel Sampler 

Figure 1 


Page 2 

OCT 31/08 





ITEM NAME: TOOL, DEFUELING 

PURPOSE AND USE: Used to connect the aircraft dump valve to permit defueling 

of the fuel tanks by gravity. 

PART NUMBER: 3V98-005 (Figure 1) 


INTERTECHNIQUE. 


Device made of aluminum, consisting of a tubular frame that couples to the 

dump valve. 






For information on parts, refer to the vendor's documentation. 

6. QUANTITY 

1 


89 x 48 x 48 mm (3.50 x 1.89 x 1.89 in); 0.0034 kg (0.075 lb) 










Page 1 

Rev.01 -DEC 05/08 




A 



ZONES 

532 

632 

B 

A 

B 


Tool, Defueling 

Figure 1 


Page 2 

Rev.01 -DEC 05/08 





ITEM NAME: TOWBAR HEAD 

PURPOSE AND USE: Used to attach the towbar to the aircraft NLG for towing. 

PART NUMBER: 01-0601-0000 (Figure 1) 


TRONAIR 


A. Features: 

- Torsional and tension/compression shear protection: a shear pin breaks in 

case of tension/compression overload. 

- Attachment safety: a safety bolt keeps the towbar head attached to the towbar 

so as to maintain aircraft control and avoid unintentional free movements. 

B. Specifications: 

- Tension/Compression Shear Load: 12,000 N (2,698 lb) 

- Torsional (radial) Shear Moment: 1,200 N.m (10,620 lb.in) 







6. QUANTITY 

1 


584 x 159 x 102 mm (23.00 x 6.25 x 4.00 in); 10.4 kg (23 lb) 


Used in conjunction with GSE 027 - TOWBAR. 








Page 1 

OCT 31/08 




B 



A 

A 

GSE 027 

(REF.) 

B 


Towbar Head 

Figure 1 


Page 2 

OCT 31/08 





ITEM NAME: TOWBAR 

PURPOSE AND USE: Used to tow, push, and steer the aircraft. 

PART NUMBER: 01-1202-0000 (Figure 1) 


TRONAIR 


A. Capacity: 30,000 kg (66,000 lb) 

B. Main tube made of heavy duty aluminum 

C. Standard 2 3/16 in towing eye 

NOTE: To substitute the towing eye for a 2 2/8 in. one, insert a letter "A" in 

place of the first dash (third digit) of the part number. 

D. Characteristics: 

- Shock absorber to protect the NLG during towing operations. 

- Casters and handles for easier movement and attachment. 

- Pneumatic wheels to absorb towing speed shock. 







6. QUANTITY 

1 


3230 x 560 mm (127 x 22 in); 42 kg (92 lb) 


Used in conjunction with GSE 026 - TOWBAR HEAD. 








Page 1 

OCT 31/08 






A 

A 

GSE 026 

(REF.) 


Towbar 

Figure 1 


Page 2 

OCT 31/08 





ITEM NAME: SET - TRANSPARENCY SHADE, COCKPIT 

PURPOSE AND USE: Used to protect the cockpit equipment from solar radiation. 



SOUTHERN CROSS AVIATION LLC 


A. The GSE consists of conveniently shaped pleated aluminum-lined cardboards 

installed on the inside face of the cockpit windshield. 

B. An elastic band keeps the GSE collapsed for ease of stowage. 






ITEM NAME P/N QUANTITY 

1 Sun Shade-lateral Prot, Cockpit AGE-04963-901 1 




6. QUANTITY 

1 


ITEMS 1 and 4: 632 x 372 mm (24.8 x 14.6 in); 0.1 kg (0.22 lb) 

ITEMS 2 and 3: 726 x 649 mm (28.6 x 25.6 in); 0.2 kg (0.44 lb) 




Keep the set clean and protected against rain, sun, and dust. 






Page 1 

OCT 31/08 




A 

A 



A 


Set-Transparency Shade Cockpit 

Figure 1 


Page 2 

OCT 31/08 





ITEM NAME: PLUGS, ENGINE 

PURPOSE AND USE: Used to protect the engine (air inlet/exhaust and starter genera 

tor air inlet/exhaust). 



SOUTHERN CROSS AVIATION LLC 


A. All plugs are internally-stuck foam cushions (plug-type), covered with PVCimpregnated 

polyamide cloth. 

B. The engine air inlet, the starter generator air inlet and exhaust plugs are connected 

to each other with stripes. 


It covers the engine air inlet/exhaust and the starter generator air inlet/exhaust to 

prevent unwanted material from entering the engine through them. 




ITEM NOMENCLATURE P/N QUANTITY 

1 Plug-Air Inlet, Engine AGE- 05108-901 1 

2 Plug-Exhaust Outlet, Engine AGE- 05109-901 1 

6. QUANTITY 

2 


ITEM 1: 433 x 45 x 433 mm (17 x 1.8 x 17 in); 0.5 kg (1.1 lb) 

ITEM 2: 350.5 x 22 x 350.5 mm (13.80 x 0.87 x 13.80 in); 0.2 (0.44 in) 




Keep the plugs clean and protected against rain, sun, and dust. 






Page 1 

OCT 31/08 




A 



A 

B 

B 


Plugs, Engine 

Figure 1 


Page 2 

OCT 31/08 




CONSUMABLE 

PRODUCTS 

APPENDIX 




EFFECTIVITY: ALL CONSUMABLE PRODUCTS APPENDIX 

Page CON-1 

Rev.02 - FEB 13/09 

PART NUMBER SPECIFICATION DESIGNATION SUPPLIER 

Diethylene 

Glycol Monomethyl 

Ether 

Honey Bee 

Cleaner 60 

ASTM D4171 

AMS 1640 

Anti-Ice Fuel Aditive 

(DI-EGME) 

Disinfectant, Cleaner, 

Aircraft Lavatory 

System 

SHELF LIFE 

(days) 

JET A ASTM D 1655 Jet Fuel Local Supplier 0 

JET A-1 ASTM D 1655 Jet Fuel Local Supplier 0 

JP-8 MIL-DTL-83133 Jet Fuel Local Supplier 0 

LEAK-TEC 

16-OX 

MIL-I-25017 

DANGER CLASS 

STORAGE 

CODE 

- - - - 

Local Supplier 720 Toxic Substance 12 

Non-Dangerous 

Material 

Non-Dangerous 

Material 

Non-Dangerous 

Material 

MIL-PRF-25567 Leak Test Solution 

AMERICAN GAS 

AND CHEMICAL 

3600 Miscellaneous 99 

MIL-PRF-25567 Leak Test Solution PACAERO 3600 Miscellaneous 99 


CBOL 

CORPORATION 



TIERNAY 

AEROSPACE 3600 Miscellaneous 99 

SERVICES 


DAVID H 

SUTHERLAND 



FIRST WAVE 

AVIATION 


MIL-PRF-25567 Leak Test Solution AGS US 3600 Miscellaneous 99 

MIL-I-25017 

Corrosion Inhibitor/ 

Lubricity Additive 

- - - - 

99 

99 

99 








EFFECTIVITY: ALL CONSUMABLE PRODUCTS APPENDIX 

Page CON-2 

Rev.02 - FEB 13/09 

PART NUMBER SPECIFICATION DESIGNATION SUPPLIER 

MIL-PRF-680 

Type I 

REMOVEGRAX 

MLS-12 

MIL-PRF-680 

TYPE I 

MEP 21-018 

MEP 21-018 

MEP 21-018 

MEP 21-018 

MEP 21-018 

MEP 21-018 

MEP 21-018 

SUPERSOL-10 MEP 21-015 

Cleaning Compound 

Solvent 

Biodegradable 

Detergent 

Biodegradable 

Detergent 

Biodegradable 

Detergent 

Biodegradable 

Detergent 

Biodegradable 

Detergent 

Biodegradable 

Detergent 

Biodegradable 

Detergent 

Concentrate Liquid 

Detergent 

Local Supplier 


EMPRESA BRASILE- 

IRA DE AERON 


AIRCRAFT 

CUSTOMER 

SERVICES 


AVIATION 

INTERNATIONAL 

SAS 


AIRCRAFT 

CORPORATION 


AVIATION 

INTERNATIONAL 

SAS 

CLARUS 

TECHNOLOGY DO 

BRASIL LTDA 

INTERTURBINE 

LOGISTIK GMBH 

SHELF LIFE 

(months) 

Refer to 

Manufacturer 

360 

360 

360 

360 

360 

360 

360 

- 720 

DANGER CLASS 

STORAGE 

CODE 

Flammable Liquid 2 

Non-Dangerous 

Material 

Non-Dangerous 

Material 

Non-Dangerous 

Material 

Non-Dangerous 

Material 

Non-Dangerous 

Material 

Non-Dangerous 

Material 

Non-Dangerous 

Material 

Corrosive 

Material 

4 

4 

4 

4 

4 

4 

4 

08 


SERVICING HANDBOOK

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