HMI Revision
369/500/600 Series
Manual: CSP−HMI−2, Handbook of Maintenance Instructions
Models: 369D/E/FF − 500/600N Helicopters
Issued: 31 October 1990
Revision 41: 03 March 2008
FILING INSTRUCTIONS:
1. Before inserting this change, ensure the manual is current.
Check the existing List of Effective Pages in the manual to ensure all prior revisions are
inserted. (Do not insert this revision if prior revisions are not inserted).
2. Incorporate this change by removing old pages and inserting new pages as indicated below.
Remove Pages Insert Pages
Cover/Title
Cover/Title Cover/Title
List of Effective Pages
A thru J A thru J
Sevice Bulletins
7 and 8 7 and 8
04−00−00
1 thru 14 1 thru 14
05−50−00
9 and 10 9 and 10
20−00−00
i and ii i and ii
63−20−25
203 and 204 203 and 204
63−21−00
411 and 412 411 and 412
601 and 602 601 and 602
64−25−30
401 thru 408 401 and 408
91−00−00
3 thru 22 3 thru 22
This Page Intentionally Left Blank
Issued: 31 October 1990
Revision No. 41: 03 March 2008
Copyright E 1999−2008 by MD Helicopters, Inc.
All rights reserved under the copyright laws.
MDHI MODEL HELICOPTERS
MODELS 369D/E/FF − 500/600N
Basic Handbook of Maintenance Instructions
(CSP−HMI−2)
SERVICING AND MAINTENANCE
MD Helicopters, Inc.
4555 East McDowell Road
Mesa, Arizona 85215−9734
MD Helicopters, Inc.
4555 East McDowell Road
Mesa, Arizona 85215−9734
PROPRIETARY RIGHTS NOTICE
The technical data and information contained in this publication is the property of
and proprietary to MD Helicopters, Inc. and is not to be disclosed or reproduced in
whole or in part without the written consent of MD Helicopters, Inc.
RESTRICTED USE
MDHI provides this manual for use by owners, operators and maintainers of MDHI
products and authorized parts. Use by STC or PMA applicants or holders as
documentation to support their certificates is not an authorized use of this manual
and is prohibited. MDHI takes no responsibility for customer’s use of parts
manufactured under an STC or PMA when this manual is used as documentation with
the Federal Aviation Administration to justify the STC or PMA. Use of unauthorized
parts on MDHI products will void the MDHI warranty offered to the customer on
components and may void the warranty on the helicopter.
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
LOEP
Page A
Revision 41
LIST OF EFFECTIVE PAGES
INSERT LATEST CHANGE PAGES, DESTROY SUPERSEDED PAGES
The highest revision number indicates pages changed, added or removed by the current change.
Date of original and revision pages are:
Original 31 October 1990. . . . . . . . . . . . . . . . . . . .
Revision 1 29 March 1991. . . . . . . . . . . . . . . . . . . .
Revision 2 10 May 1991. . . . . . . . . . . . . . . . . . . . . .
Revision 3 09 September 1991. . . . . . . . . . . . . . . .
Revision 4 20 January 1992. . . . . . . . . . . . . . . . . .
Revision 5 24 August 1992. . . . . . . . . . . . . . . . . . .
Revision 6 21 December 1992. . . . . . . . . . . . . . . .
Revision 7 01 June 1993. . . . . . . . . . . . . . . . . . . . .
Revision 8 23 July 1993. . . . . . . . . . . . . . . . . . . . . .
Revision 9 22 April 1994. . . . . . . . . . . . . . . . . . . . . .
Revision 10 26 September 1994. . . . . . . . . . . . . . .
Revision 11 18 January 1995. . . . . . . . . . . . . . . . .
Revision 12 06 October 1995. . . . . . . . . . . . . . . . .
Revision 13 31 May 1996. . . . . . . . . . . . . . . . . . . . .
Revision 14 13 September 1996. . . . . . . . . . . . . . .
Revision 15 15 November 1996. . . . . . . . . . . . . . .
Revision 16 06 January 1997. . . . . . . . . . . . . . . . .
Revision 17 24 February 1997. . . . . . . . . . . . . . . . .
Revision 18 17 October 1997. . . . . . . . . . . . . . . . .
Revision 19 16 December 1997. . . . . . . . . . . . . . .
Revision 20 01 June 1998. . . . . . . . . . . . . . . . . . . .
Revision 21 24 August 1998. . . . . . . . . . . . . . . . . .
Revision 22 10 March 1998. . . . . . . . . . . . . . . . . . .
Revision 23 01 June 1999. . . . . . . . . . . . . . . . . . . .
Revision 24 07 December 1999. . . . . . . . . . . . . . .
Revision 25 28 April 2000. . . . . . . . . . . . . . . . . . . . .
Revision 26 17 August 2000. . . . . . . . . . . . . . . . . .
Revision 27 09 October 2000. . . . . . . . . . . . . . . . .
Revision 28 30 November 2000. . . . . . . . . . . . . . .
Revision 29 11 May 2001. . . . . . . . . . . . . . . . . . . . .
Revision 30 11 July 2001. . . . . . . . . . . . . . . . . . . . .
Revision 31 05 November 2001. . . . . . . . . . . . . . .
Revision 32 18 March 2002. . . . . . . . . . . . . . . . . . .
Revision 33 24 June 2002. . . . . . . . . . . . . . . . . . . .
Revision 34 21 August 2003. . . . . . . . . . . . . . . . . .
Revision 35 20 May 2004. . . . . . . . . . . . . . . . . . . . .
Revision 36 11 November 2004. . . . . . . . . . . . . . .
Revision 37 13 December 2005. . . . . . . . . . . . . . .
Revision 38 25 May 2006. . . . . . . . . . . . . . . . . . . . .
Revision 39 10 April 2007. . . . . . . . . . . . . . . . . . . . .
Revision 40 10 November 2007. . . . . . . . . . . . . . .
Revision 41 03 March 2008. . . . . . . . . . . . . . . . . . .
Cover/Title
Cover/Title Revision 41. . . . . . . . . . . . . . . . . . . . . .
Change Request
CRi and CRii N/A. . . . . . . . . . . . . . . . . . . . . . . . . . .
Temporary Revision
1 and 2 Revision 40. . . . . . . . . . . . . . . . . . . . . . . . .
List of Effective Pages
A thru J Revision 40. . . . . . . . . . . . . . . . . . . . . . . . .
Table of Contents
i and ii Revision 29. . . . . . . . . . . . . . . . . . . . . . . . . .
iii Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
iv Revision 38. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
v and vi Revision 29. . . . . . . . . . . . . . . . . . . . . . . . .
Bulletins
1 Revision 23. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2 Revision 24. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3 and 4 Revision 23. . . . . . . . . . . . . . . . . . . . . . . . .
5 and 6 Revision 24. . . . . . . . . . . . . . . . . . . . . . . . .
7 Revision 41. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8 Revision 23. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
9/(10 blank) Revision 24. . . . . . . . . . . . . . . . . . . . .
Chapter 01
i/(ii blank) Revision 26. . . . . . . . . . . . . . . . . . . . . . .
01−00−00
1 Revision 26. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2 thru 4 Revision 23. . . . . . . . . . . . . . . . . . . . . . . . .
5 and 6 Revision 26. . . . . . . . . . . . . . . . . . . . . . . . .
7 Revision 29. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8 Revision 28. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
201 Revision 23. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
202 Revision 40. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
203 Revision 23. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
204 Revision 26. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
205 thru 208 Revision 23. . . . . . . . . . . . . . . . . . . . .
209 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
210 Revision 30. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
211 and 212 Revision 36. . . . . . . . . . . . . . . . . . . . .
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page B
Revision 41
LOEP
Chapter 04
i and ii Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . .
04−00−00
1 thru 14 Revision 41. . . . . . . . . . . . . . . . . . . . . . . .
04−00−01
1/(2 blank) Revision 26. . . . . . . . . . . . . . . . . . . . . . .
Chapter 05
i and ii Revision 38. . . . . . . . . . . . . . . . . . . . . . . . . .
05−00−00
1 thru 4 Revision 38. . . . . . . . . . . . . . . . . . . . . . . . .
05−10−00
1 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2 Revision 40. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3 Revision 37. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
05−20−00
1 and 2 Revision 39. . . . . . . . . . . . . . . . . . . . . . . . .
3 Revision 40. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4 thru 6 Revision 35. . . . . . . . . . . . . . . . . . . . . . . . .
7 thru 12 Revision 39. . . . . . . . . . . . . . . . . . . . . . . .
05−20−10
1 thru 3 Revision 39. . . . . . . . . . . . . . . . . . . . . . . . .
4 Revision 38. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
05−20−15
1 Revision 29. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2 and 3/(4 blank) Revision 31. . . . . . . . . . . . . . . . .
05−20−20
1 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2 thru 4 Revision 37. . . . . . . . . . . . . . . . . . . . . . . . .
5 Revision 38. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
05−50−00
1 thru 7 Revision 24. . . . . . . . . . . . . . . . . . . . . . . . .
8 Revision 26. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
9 Revision 41. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
10 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Chapter 06
i and ii Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . .
06
−00−00
201 thru 205 Revision 23. . . . . . . . . . . . . . . . . . . . .
206 Revision 39. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
207 thru 210 Revision 23. . . . . . . . . . . . . . . . . . . . .
211 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
212 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Chapter 07
i/(ii blank) Revision 23. . . . . . . . . . . . . . . . . . . . . . .
07−00−00
201 thru 206 Revision 23. . . . . . . . . . . . . . . . . . . . .
Chapter 08
i/(ii blank) Revision 23. . . . . . . . . . . . . . . . . . . . . . .
08−00−00
201 thru 203/(204 blank) Revision 23. . . . . . . . . .
08−10−00
201 Revision 39. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
202 and 203 Revision 27. . . . . . . . . . . . . . . . . . . . .
204 thru 210 Revision 23. . . . . . . . . . . . . . . . . . . . .
211 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
212 thru 217/(218 blank) Revision 23. . . . . . . . . .
Chapter 09
i/(ii blank) Revision 23. . . . . . . . . . . . . . . . . . . . . . .
09−00−00
201 thru 204 Revision 23. . . . . . . . . . . . . . . . . . . . .
Chapter 10
i/(ii blank) Revision 23. . . . . . . . . . . . . . . . . . . . . . .
10−10−00
201 thru 204 Revision 23. . . . . . . . . . . . . . . . . . . . .
10−20−00
201 thru 203/(204 blank) Revision 23. . . . . . . . . .
10−30−00
201 thru 206 Revision 23. . . . . . . . . . . . . . . . . . . . .
Chapter 11
i/(ii blank) Revision 23. . . . . . . . . . . . . . . . . . . . . . .
11−00−00
201 thru 217/(218 blank) Revision 23. . . . . . . . . .
11−40−00
201 thru 211/(212 blank) Revision 23. . . . . . . . . .
Chapter 12
i Revision 23. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ii Revision 32. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
12−00−00
301 and 302 Revision 23. . . . . . . . . . . . . . . . . . . . .
303 Revision 24. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
304 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
305 Revision 26. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
306 and 307 Revision 24. . . . . . . . . . . . . . . . . . . . .
308 Revision 26. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
309 Revision 23. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
310 and 311 Revision 32. . . . . . . . . . . . . . . . . . . . .
312 Revision 23. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
LOEP
Page C
Revision 41
Chapter 18
i thru iii/(iv blank) Revision 23. . . . . . . . . . . . . . . . .
18−10−00
201 Revision 23. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
202 Revision 31. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
203 and 204 Revision 37. . . . . . . . . . . . . . . . . . . . .
401 thru 404 Revision 23. . . . . . . . . . . . . . . . . . . . .
501 Revision 23. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
502 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
503 thru 505 Revision 23. . . . . . . . . . . . . . . . . . . . .
506 and 507 Revision 24. . . . . . . . . . . . . . . . . . . . .
508 and 509 Revision 23. . . . . . . . . . . . . . . . . . . . .
510 Revision 39. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
18−10−60
201 Revision 23. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
202 and 203/(204 blank) Revision 31. . . . . . . . . .
401 thru 404 Revision 23. . . . . . . . . . . . . . . . . . . . .
501 Revision 23. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
502 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
503 thru 509 Revision 23. . . . . . . . . . . . . . . . . . . . .
510 Revision 37. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
511 and 512 Revision 23. . . . . . . . . . . . . . . . . . . . .
18−20−00
201 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
202 and 203 Revision 23. . . . . . . . . . . . . . . . . . . . .
204 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
205 Revision 39. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
206 Revision 23. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
18−20−30
201 thru 205/(206 blank) Revision 23. . . . . . . . . .
Chapter 20
i and ii Revision 41. . . . . . . . . . . . . . . . . . . . . . . . . .
20−10−00
201 thru 206 Revision 38. . . . . . . . . . . . . . . . . . . . .
20−20−00
201 and 202 Revision 23. . . . . . . . . . . . . . . . . . . . .
20−30−00
201 and 202 Revision 23. . . . . . . . . . . . . . . . . . . . .
203 thru 206 Revision 34. . . . . . . . . . . . . . . . . . . . .
20−40−
00
201 thru 204 Revision 23. . . . . . . . . . . . . . . . . . . . .
20−90−00
201 Revision 38. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
202 thru 204 Revision 40. . . . . . . . . . . . . . . . . . . . .
Chapter 21
i and ii Revision 23. . . . . . . . . . . . . . . . . . . . . . . . . .
21−10−00
201 thru 204 Revision 23. . . . . . . . . . . . . . . . . . . . .
21−40−00
201 thru 207 Revision 23. . . . . . . . . . . . . . . . . . . . .
208 Revision 27. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
209 Revision 37. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
210 Revision 23. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
901 thru 911/(912 blank) Revision 23. . . . . . . . . .
Chapter 25
i Revision 24. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ii thru vii/(viii blank) Revision 23. . . . . . . . . . . . . . .
25−00−00
1 and 2 Revision 23. . . . . . . . . . . . . . . . . . . . . . . . .
25−10−00
201 thru 205 Revision 23. . . . . . . . . . . . . . . . . . . . .
206 Revision 24. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
207 and 208 Revision 23. . . . . . . . . . . . . . . . . . . . .
25−15−00
201 thru 204 Revision 23. . . . . . . . . . . . . . . . . . . . .
901 and 902 Revision 23. . . . . . . . . . . . . . . . . . . . .
25−20−00
201 thru 211/(212 blank) Revision 23. . . . . . . . . .
25−21−00
201/(202 blank) Revision 23. . . . . . . . . . . . . . . . . .
901 thru 908 Revision 23. . . . . . . . . . . . . . . . . . . . .
25−30−00
201 thru 214 Revision 23. . . . . . . . . . . . . . . . . . . . .
25−40−00
201 thru 207/(208 blank) Revision 23. . . . . . . . . .
25−
50−00
101 thru 106 Revision 23. . . . . . . . . . . . . . . . . . . . .
401 thru 408 Revision 23. . . . . . . . . . . . . . . . . . . . .
601 and 602 Revision 23. . . . . . . . . . . . . . . . . . . . .
901 thru 907/(908 blank) Revision 23. . . . . . . . . .
25−60−00
201 and 202 Revision 23. . . . . . . . . . . . . . . . . . . . .
25−63−00
201 thru 216 Revision 23. . . . . . . . . . . . . . . . . . . . .
901 thru 910 Revision 23. . . . . . . . . . . . . . . . . . . . .
Chapter 26
i/(ii blank) Revision 23. . . . . . . . . . . . . . . . . . . . . . .
26−10−00
201 thru 203/(204 blank) Revision 23. . . . . . . . . .
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page D
Revision 41
LOEP
26−20−00
201 and 202 Revision 23. . . . . . . . . . . . . . . . . . . . .
Chapter 28
i Revision 19. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ii Revision 37. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
iii and iv Revision 28. . . . . . . . . . . . . . . . . . . . . . . . .
v thru vii/(viii blank) Revision 31. . . . . . . . . . . . . . .
28−00−00
1 and 2 Revision 19. . . . . . . . . . . . . . . . . . . . . . . . .
101 Revision 29. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
102 and 103 Revision 19. . . . . . . . . . . . . . . . . . . . .
104 Revision 23. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
201 and 202 Revision 19. . . . . . . . . . . . . . . . . . . . .
401 thru 414 Revision 19. . . . . . . . . . . . . . . . . . . . .
415 and 416 Revision 36. . . . . . . . . . . . . . . . . . . . .
417 thru 422 Revision 19. . . . . . . . . . . . . . . . . . . . .
501 thru 504 Revision 19. . . . . . . . . . . . . . . . . . . . .
505 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
506 Revision 19. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
507 Revision 29. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
508 thru 510 Revision 19. . . . . . . . . . . . . . . . . . . . .
601 thru 603 Revision 19. . . . . . . . . . . . . . . . . . . . .
604 Revision 28. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
605 thru 607/(608 blank) Revision 19. . . . . . . . . .
801 thru 807/(808 blank) Revision 19. . . . . . . . . .
28−00−60
1 thru 3/(4 blank) Revision 19. . . . . . . . . . . . . . . . .
101 Revision 29. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
102 Revision 19. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
103/(104 blank) Revision 21. . . . . . . . . . . . . . . . . .
201 Revision 32. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
202 Revision 39. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
401 thru 405 Revision 19. . . . . . . . . . . . . . . . . . . . .
406 and 407 Revision 34. . . . . . . . . . . . . . . . . . . . .
408 thru 422 Revision 19. . . . . . . . . . . . . . . . . . . . .
501 and 502 Revision 22. . . . . . . . . . . . . . . . . . . . .
503/(504 blank) Revision 21. . . . . . . . . . . . . . . . . .
601 Revision 19. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
602 thru 606 Revision 31. . . . . . . . . . . . . . . . . . . . .
801 thru 805/(806 blank) Revision 19. . . . . . . . . .
28−25−00
1 Revision 39. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2 Revision 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
101/(102 blank) Revision 20. . . . . . . . . . . . . . . . . .
201 and 202 Revision 20. . . . . . . . . . . . . . . . . . . . .
203 thru 205/(206 blank) Revision 19. . . . . . . . . .
601 and 602 Revision 20. . . . . . . . . . . . . . . . . . . . .
603 thru 605/(606 blank) Revision 19. . . . . . . . . .
901 and 902 Revision 20. . . . . . . . . . . . . . . . . . . . .
903 Revision 28. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
904 thru 918 Revision 19. . . . . . . . . . . . . . . . . . . . .
Chapter 32
i Revision 19. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ii thru vi Revision 26. . . . . . . . . . . . . . . . . . . . . . . . .
32−10−00
1/(2 blank) Revision 19. . . . . . . . . . . . . . . . . . . . . . .
301 thru 308 Revision 19. . . . . . . . . . . . . . . . . . . . .
401 and 402 Revision 19. . . . . . . . . . . . . . . . . . . . .
403 and 404 Revision 26. . . . . . . . . . . . . . . . . . . . .
405 Revision 19. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
406 and 407/(408 blank) Revision 26. . . . . . . . . .
601 Revision 31. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
602 thru 605/(606 blank) Revision 26. . . . . . . . . .
801 thru 805 Revision 19. . . . . . . . . . . . . . . . . . . . .
806 and 807/(808 blank) Revision 26. . . . . . . . . .
901 thru 908 Revision 19. . . . . . . . . . . . . . . . . . . . .
32−10−60
1/(2 blank) Revision 19. . . . . . . . . . . . . . . . . . . . . . .
301 thru 303/(304 blank) Revision 19. . . . . . . . . .
401 Revision 19. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
402 Revision 26. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
403 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
404 Revision 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
405 and 406 Revision 19. . . . . . . . . . . . . . . . . . . . .
407/(408 blank) Revision 20. . . . . . . . . . . . . . . . . .
601 Revision 31. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
602 Revision 19. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
603/(604 blank) Revision 22. . . . . . . . . . . . . . . . . .
801 thru 803/(804 blank) Revision 19. . . . . . . . . .
32−40−00
201 thru 206 Revision 19. . . . . . . . . . . . . . . . . . . . .
32−40−60
201 and 202 Revision 19. . . . . . . . . . . . . . . . . . . . .
32−81−00
201 thru 204 Revision 19. . . . . . . . . . . . . . . . . . . . .
901 thru 910 Revision 19. . . . . . . . . . . . . . . . . . . . .
32−82−00
201 thru 206 Revision 19. . . . . . . . . . . . . . . . . . . . .
401 thru 407/(408 blank) Revision 19. . . . . . . . . .
901 thru 912 Revision 19. . . . . . . . . . . . . . . . . . . . .
Chapter 52
i thru iv Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . .
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
LOEP
Page E
Revision 41
52−10−00
201 thru 213 Revision 25. . . . . . . . . . . . . . . . . . . . .
214 thru 216 Revision 36. . . . . . . . . . . . . . . . . . . . .
217 Revision 25. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
218 thru 224 Revision 36. . . . . . . . . . . . . . . . . . . . .
52−40−00
201 thru 205/(206 blank) Revision 18. . . . . . . . . .
52−50−00
201 thru 206 Revision 18. . . . . . . . . . . . . . . . . . . . .
207 Revision 31. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
208 thru 210 Revision 18. . . . . . . . . . . . . . . . . . . . .
Chapter 53
i thru vi Revision 40. . . . . . . . . . . . . . . . . . . . . . . . . .
53−00−00
201 Revision 19. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
202 Revision 37. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
203 Revision 19. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
204 Revision 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
53−10−00
201 thru 206 Revision 19. . . . . . . . . . . . . . . . . . . . .
53−20−00
201 thru 203/(204 blank) Revision 19. . . . . . . . . .
53−30−00
201 Revision 35. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
202 and 203 Revision 19. . . . . . . . . . . . . . . . . . . . .
204 thru 214 Revision 38. . . . . . . . . . . . . . . . . . . . .
53−30−30
201 Revision 26. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
202 thru 210 Revision 34. . . . . . . . . . . . . . . . . . . . .
53−40−00
201 thru 204 Revision 19. . . . . . . . . . . . . . . . . . . . .
53−40−30
201 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
202 Revision 19. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
203 Revision 22. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
204 Revision 19. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
205 thru 214 Revision 39. . . . . . . . . . . . . . . . . . . .
53−50−10
201 and 202 Revision 19. . . . . . . . . . . . . . . . . . . . .
203 Revision 22. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
204 and 205 Revision 37. . . . . . . . . . . . . . . . . . . . .
206 Revision 40. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
207/(208 blank) Revision 19. . . . . . . . . . . . . . . . . .
53−50−30
201 Revision 30. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
202 Revision 32. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
203 and 204 Revision 33. . . . . . . . . . . . . . . . . . . . .
205 thru 212 Revision 40. . . . . . . . . . . . . . . . . . . . .
Chapter 62
i thru viii Revision 37. . . . . . . . . . . . . . . . . . . . . . . . .
62−00−00
101 Revision 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
102 Revision 31. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
62−10−00
401 thru 403/(404 blank) Revision 20. . . . . . . . . .
601 thru 605 Revision 20. . . . . . . . . . . . . . . . . . . . .
606 Revision 40. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
607 Revision 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
608 Revision 33. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
609 Revision 29. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
610 and 611 Revision 35. . . . . . . . . . . . . . . . . . . . .
612 Revision 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
801 Revision 33. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
802 thru 808 Revision 20. . . . . . . . . . . . . . . . . . . . .
809 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
810 and 811/(812 blank) Revision 20. . . . . . . . . .
62−20−00
401 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
402 and 403 Revision 20. . . . . . . . . . . . . . . . . . . . .
404 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
405 and 406 Revision 20. . . . . . . . . . . . . . . . . . . . .
601 and 602 Revision 20. . . . . . . . . . . . . . . . . . . . .
603 Revision 29. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
604 Revision 25. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
605 thru 607 Revision 20. . . . . . . . . . . . . . . . . . . . .
608 Revision 37. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
609 and 610 Revision 20. . . . . . . . . . . . . . . . . . . . .
801 Revision 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
802 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
803 thru 810 Revision 20
. . . . . . . . . . . . . . . . . . . . .
811 thru 813 Revision 37. . . . . . . . . . . . . . . . . . . . .
814 Revision 21. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
815 Revision 35. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
816 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
817 and 818 Revision 40. . . . . . . . . . . . . . . . . . . . .
819 and 820 Revision 37. . . . . . . . . . . . . . . . . . . . .
62−20−60
401 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
402 Revision 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page F
Revision 41
LOEP
403 and 404 Revision 36. . . . . . . . . . . . . . . . . . . . .
405/(406 blank) Revision 20. . . . . . . . . . . . . . . . . .
601 and 602 Revision 20. . . . . . . . . . . . . . . . . . . . .
603 Revision 33. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
604 Revision 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
605 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
606 and 607 Revision 33. . . . . . . . . . . . . . . . . . . . .
608 Revision 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
609 Revision 25. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
610 Revision 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
801 thru 804 Revision 20. . . . . . . . . . . . . . . . . . . . .
805 thru 808 Revision 37. . . . . . . . . . . . . . . . . . . . .
809 Revision 22. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
810 Revision 37. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
811 Revision 22. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
812 and 813 Revision 34. . . . . . . . . . . . . . . . . . . . .
814 Revision 37. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
62−30−00
401 Revision 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
402 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
403 and 404 Revision 31. . . . . . . . . . . . . . . . . . . . .
405 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
406 Revision 27. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
407 and 408 Revision 35. . . . . . . . . . . . . . . . . . . . .
601 and 602 Revision 32. . . . . . . . . . . . . . . . . . . . .
801 thru 807/(808 blank) Revision 20. . . . . . . . . .
62−30−60
401 Revision 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
402 Revision 27. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
403 Revision 31. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
404 thru 406 Revision 35. . . . . . . . . . . . . . . . . . . . .
407/(408 blank) Revision 20. . . . . . . . . . . . . . . . . .
601 and 602 Revision 32. . . . . . . . . . . . . . . . . . . . .
801 and 802 Revision 20. . . . . . . . . . . . . . . . . . . . .
Chapter 63
i thru x Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . .
63−00−00
101 Revision 28. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
102 Revision 29. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
103 Revision 30. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
104 Revision 28. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
63−10−00
401 thru 403 Revision 20. . . . . . . . . . . . . . . . . . . . .
404 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
405 Revision 27. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
406 Revision 32. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
407 Revision 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
408 Revision 32. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
409 Revision 39. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
410 Revision 32. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
411 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
412 thru 414 Revision 32. . . . . . . . . . . . . . . . . . . . .
601 Revision 26. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
602 Revision 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
603 Revision 26. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
604 thru 606 Revision 20. . . . . . . . . . . . . . . . . . . . .
801 thru 804 Revision 20. . . . . . . . . . . . . . . . . . . . .
63−15−10
401 thru 403 Revision 20. . . . . . . . . . . . . . . . . . . . .
404 Revision 22. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
405 thru 409 Revision 20. . . . . . . . . . . . . . . . . . . . .
410 Revision 28. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
601 thru 603 Revision 20. . . . . . . . . . . . . . . . . . . . .
604 Revision 37. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
605/(606 blank) Revision 20. . . . . . . . . . . . . . . . . .
801 and 802 Revision 20. . . . . . . . . . . . . . . . . . . . .
63−15−30
201 Revision 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
202 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
203 thru 207/(208 blank) Revision 20. . . . . . . . . .
63−20−00
201 thru 203 Revision 20. . . . . . . . . . . . . . . . . . . . .
204 and 205 Revision 36. . . . . . . . . . . . . . . . . . . . .
206 and 207/(208 blank) Revision 20. . . . . . . . . .
63−20−25
201 and 202 Revision 20. . . . . . . . . . . . . . . . . . . . .
203 Revision 41. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
204 Revision 28. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
205 Revision 24. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
206 thru 209/(210 blank) Revision 29. . . . . . . . . .
63−21−00
401 and 402 Revision 20. . . . . . . . . . . . . . . . . . . . .
403 Revision 28. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
404 thru 408 Revision 20. . . . . . . . . . . . . . . . . . . . .
409 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
410 Revision 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
411 Revision 41. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
412 Revision 37. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
601 Revision 41. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
602 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
603 Revision 37. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
604 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
801 and 802 Revision 22. . . . . . . . . . . . . . . . . . . . .
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
LOEP
Page G
Revision 41
803 Revision 37. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
804 and 805 Revision 36. . . . . . . . . . . . . . . . . . . . .
806 and 807 Revision 37. . . . . . . . . . . . . . . . . . . . .
808 and 809 Revision 36. . . . . . . . . . . . . . . . . . . . .
810 Revision 22. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
63−22−00
201 thru 204 Revision 20. . . . . . . . . . . . . . . . . . . . .
401 thru 413/(414 blank) Revision 20. . . . . . . . . .
601 and 602 Revision 20. . . . . . . . . . . . . . . . . . . . .
901 thru 917/(918 blank) Revision 20. . . . . . . . . .
63−25−10
201 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
202 Revision 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
203 Revision 40. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
204 thru 207/(208 blank) Revision 20. . . . . . . . . .
63−25−30
201 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
202 Revision 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
203 Revision 33. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
204 Revision 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
63−30−00
201 and 202 Revision 20. . . . . . . . . . . . . . . . . . . . .
203 and 204 Revision 36. . . . . . . . . . . . . . . . . . . . .
205 Revision 29. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
206 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Chapter 64
i thru iv Revision 40. . . . . . . . . . . . . . . . . . . . . . . . . .
64−00−00
101 Revision 21. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
102 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
64−00−05
901 thru 908 Revision 21. . . . . . . . . . . . . . . . . . . . .
64−10−00
201 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
202 thru 206 Revision 21. . . . . . . . . . . . . . . . . . . . .
207 Revision 32. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
208 thru 210 Revision 21. . . . . . . . . . . . . . . . . . . . .
211 thru 214 Revision 22. . . . . . . . . . . . . . . . . . . . .
64−20−00
201 thru 203 Revision 21. . . . . . . . . . . . . . . . . . . . .
204 Revision 28. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
205 thru 207/(208 blank) Revision 21. . . . . . . . . .
64−25−30
401 thru 407 Revision 41. . . . . . . . . . . . . . . . . . . . .
408 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
601 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
602 Revision 39. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
801 thru 804 Revision 21. . . . . . . . . . . . . . . . . . . . .
805 and 806 Revision 40. . . . . . . . . . . . . . . . . . . . .
64−30−00
201 Revision 21. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
202 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
203 and 204 Revision 21. . . . . . . . . . . . . . . . . . . . .
205 Revision 40. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
206 and 207 Revision 34. . . . . . . . . . . . . . . . . . . . .
208 thru 210 Revision 21. . . . . . . . . . . . . . . . . . . . .
Chapter 67
i thru xii Revision 39. . . . . . . . . . . . . . . . . . . . . . . . .
67−00−00
101 Revision 30. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
102 and 103 Revision 21. . . . . . . . . . . . . . . . . . . . .
104 Revision 29. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
105 Revision 39. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
106 thru 111/(112 blank) Revision 30. . . . . . . . . . .
67−10−00
1 thru 5/(6 blank) Revision 21. . . . . . . . . . . . . . . . .
401 thru 405 Revision 21. . . . . . . . . . . . . . . . . . . . .
406 Revision 37. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
407 thru 411 Revision 21. . . . . . . . . . . . . . . . . . . . .
412 Revision 29. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
413 Revision 24. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
414 Revision 21. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
415 thru 417 Revision 29. . . . . . . . . . . . . . . . . . . . .
418 Revision 39. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
419 Revision 21. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
420 Revision 29. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
421 Revision 21. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
422 Revision 29. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
423 Revision 31. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
424 Revision 29. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
501 thru 503 Revision 21. . . . . . . . . . . . . . . . . . . . .
504 and 505 Revision 34. . . . . . . . . . . . . . . . . . . . .
506 Revision 21. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
507 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
508 and 509 Revision 21. . . . . . . . . . . . . . . . . . . . .
510 Revision 24. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
511 Revision 38. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
512 thru 515 Revision 21. . . . . . . . . . . . . . . . . . . . .
516 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
517 thru 521 Revision 21. . . . . . . . . . . . . . . . . . . . .
522 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
523 Revision 29. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page H
Revision 41
LOEP
524 Revision 31. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
525 and 526 Revision 36. . . . . . . . . . . . . . . . . . . . .
527 thru 530 Revision 21. . . . . . . . . . . . . . . . . . . . .
601 Revision 28. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
602 Revision 21. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
603 Revision 28. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
604 Revision 39. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
605 Revision 21. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
606 and 607 Revision 39. . . . . . . . . . . . . . . . . . . . .
608 Revision 28. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
609 and 610 Revision 39. . . . . . . . . . . . . . . . . . . . .
801 thru 813 Revision 21. . . . . . . . . . . . . . . . . . . . .
814 and 815 Revision 31. . . . . . . . . . . . . . . . . . . . .
816 Revision 21. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
67−10−20
201 thru 202 Revision 21. . . . . . . . . . . . . . . . . . . . .
203 Revision 40. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
204 thru 208 Revision 21. . . . . . . . . . . . . . . . . . . . .
67−20−10
1 and 2 Revision 21. . . . . . . . . . . . . . . . . . . . . . . . .
401 and 402 Revision 21. . . . . . . . . . . . . . . . . . . . .
403 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
404 Revision 26. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
405 thru 407/(408 blank) Revision 21. . . . . . . . . .
501 thru 504 Revision 21. . . . . . . . . . . . . . . . . . . . .
601 and 602 Revision 21. . . . . . . . . . . . . . . . . . . . .
801 thru 806 Revision 21. . . . . . . . . . . . . . . . . . . . .
67−20−30
1 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2 Revision 25. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
401 Revision 18. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
402 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
403 Revision 18. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
404 Revision 33. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
405 Revision 38. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
406 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
407 Revision 38. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
408 Revision 25. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
409 thru 412 Revision 33. . . . . . . . . . . . . . . . . . . . .
413 Revision 25. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
414 thru 416 Revision 30. . . . . . . . . . . . . . . . . . . . .
501 Revision 33. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
502 Revision 18. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
503 Revision 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
504 Revision 18. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
505 Revision 30. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
506 Revision 18. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
507 Revision 26. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
508 Revision 30. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
509 Revision 37. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
510 and 511 Revision 30. . . . . . . . . . . . . . . . . . . . .
512 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
513 thru 516 Revision 30. . . . . . . . . . . . . . . . . . . . .
601 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
602 Revision 35. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
603 Revision 39. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
604 and 605 Revision 24. . . . . . . . . . . . . . . . . . . . .
606 Revision 39. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
801 thru 803 Revision 18. . . . . . . . . . . . . . . . . . . . .
804 and 805 Revision 30. . . . . . . . . . . . . . . . . . . . .
806 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Chapter 71
i thru x Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . .
71−00−00
1/(2 blank) Revision 22. . . . . . . . . . . . . . . . . . . . . . .
401 thru 405 Revision 22. . . . . . . . . . . . . . . . . . . . .
406 Revision 30. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
407 thru 411 Revision 22. . . . . . . . . . . . . . . . . . . . .
412 and 413/(414 blank) Revision 26. . . . . . . . . .
71−00−30
1/(2 blank) Revision 22. . . . . . . . . . . . . . . . . . . . . . .
401 thru 404 Revision 22. . . . . . . . . . . . . . . . . . . . .
405 and 406 Revision 34. . . . . . . . . . . . . . . . . . . . .
407 thru 411 Revision 22. . . . . . . . . . . . . . . . . . . . .
412 Revision 26. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
71−00−47
1 thru 3/(4 blank) Revision 22. . . . . . . . . . . . . . . . .
401 thru 406 Revision 22. . . . . . . . . . . . . . . . . . . . .
407 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
408 thru 411/(412 blank) Revision 29. . . . . . . . . .
71−10−00
201 thru 206 Revision 22. . . . . . . . . . . . . . . . . . . . .
71−10−05
201/(202 blank) Revision 22. . . . . . . . . . . . . . . . . .
901 thru 904 Revision 22. . . . . . . . . . . . . . . . . . . . .
71−10−10
1 Revision 22. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3 and 4 Revision 22. . . . . . . . . . . . . . . . . . . . . . . . .
101 thru 106 Revision 36. . . . . . . . . . . . . . . . . . . . .
201 thru 207/(208 blank) Revision 22. . . . . . . . . .
401 Revision 22. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
402 Revision 37. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
LOEP
Page I
Revision 41
403/(404 blank) Revision 22. . . . . . . . . . . . . . . . . .
601 Revision 39. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
602 and 603 Revision 22. . . . . . . . . . . . . . . . . . . . .
604 Revision 38. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
801 thru 814 Revision 22. . . . . . . . . . . . . . . . . . . . .
901 thru 923/(924 blank) Revision 22. . . . . . . . . .
71−10−60
1/(2 blank) Revision 22. . . . . . . . . . . . . . . . . . . . . . .
101/(102 blank) Revision 22. . . . . . . . . . . . . . . . . .
401 Revision 22. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
402 thru 404 Revision 29. . . . . . . . . . . . . . . . . . . . .
601 Revision 29. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
602 Revision 33. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
71−20−00
1/(2 blank) Revision 22. . . . . . . . . . . . . . . . . . . . . . .
401 Revision 26. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
402 Revision 22. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
403 and 404 Revision 34. . . . . . . . . . . . . . . . . . . . .
405/(406 blank) Revision 22. . . . . . . . . . . . . . . . . .
601/(602 blank) Revision 22. . . . . . . . . . . . . . . . . .
801/(802 blank) Revision 22. . . . . . . . . . . . . . . . . .
71−30−00
1 and 2 Revision 22. . . . . . . . . . . . . . . . . . . . . . . . .
101 thru 103/(104 blank) Revision 22. . . . . . . . . .
401 thru 412 Revision 22. . . . . . . . . . . . . . . . . . . . .
413 and 414 Revision 26. . . . . . . . . . . . . . . . . . . . .
601 and 602 Revision 32. . . . . . . . . . . . . . . . . . . . .
801 thru 804 Revision 22. . . . . . . . . . . . . . . . . . . . .
901 thru 905/(906 blank) Revision 22. . . . . . . . . .
71−60−00
201 thru 205/(206 blank) Revision 22. . . . . . . . . .
Chapter 75
i/(ii blank) Revision 22. . . . . . . . . . . . . . . . . . . . . . .
75−10−00
201 thru 203 Revision 22. . . . . . . . . . . . . . . . . . . . .
204 Revision 37. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
205 and 206 Revision 22. . . . . . . . . . . . . . . . . . . . .
Chapter 76
i thru iv Revision 37. . . . . . . . . . . . . . . . . . . . . . . . . .
76−00−00
1 and 2 Revision 22. . . . . . . . . . . . . . . . . . . . . . . . .
101 and 102 Revision 22. . . . . . . . . . . . . . . . . . . . .
76
−10−00
201 thru 214 Revision 22. . . . . . . . . . . . . . . . . . . . .
215 Revision 35. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
216 Revision 22. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
217 thru 219 Revision 35. . . . . . . . . . . . . . . . . . . . .
220 and 221 Revision 22. . . . . . . . . . . . . . . . . . . . .
222 and 223 Revision 35. . . . . . . . . . . . . . . . . . . . .
224 Revision 22. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
76−20−00
201 thru 213/(214 blank) Revision 22. . . . . . . . . .
76−47−00
201 Revision 22. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
202 and 203 Revision 37. . . . . . . . . . . . . . . . . . . . .
204 Revision 33. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
205 and 206 Revision 37. . . . . . . . . . . . . . . . . . . . .
207 Revision 22. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
208 thru 211 Revision 37. . . . . . . . . . . . . . . . . . . . .
212 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Chapter 78
i and ii Revision 35. . . . . . . . . . . . . . . . . . . . . . . . . .
78−20−00
201 thru 203 Revision 38. . . . . . . . . . . . . . . . . . . . .
204 thru 209/(210 blank) Revision 22. . . . . . . . . .
78−30−00
201 Revision 38. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
202 thru 204 Revision 35. . . . . . . . . . . . . . . . . . . . .
Chapter 79
i and ii Revision 23. . . . . . . . . . . . . . . . . . . . . . . . . .
79−00−00
201 thru 212 Revision 23. . . . . . . . . . . . . . . . . . . . .
79−10−10
201 and 202 Revision 26. . . . . . . . . . . . . . . . . . . . .
901 thru 903/(904 blank) Revision 23. . . . . . . . . .
Chapter 91
i/(ii blank) Revision 29. . . . . . . . . . . . . . . . . . . . . . .
91−00−00
1 Revision 21. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2 Revision 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3 Revision 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4 thru 22 Revision 41. . . . . . . . . . . . . . . . . . . . . . . .
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page J
Revision 41
LOEP
This Page Intentionally Left Blank
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
BULLETINS
Page 7
Revision 41
Table 1. ACTIVE SERVICE BULLETINS (Cont.)
369D DATESUBJECT600N500N369F369E
013R1 Low Fuel Level Warning Light 4−15−98
090R1 077R1 017R1 014R1 Socket Contact Assembly Inspection 9−25−98
015 Engine Fuel Control Box Replacement 4−23−99
016R1 Audio Warning System Replacement 9−19−00
017 FADEC Manual Switch Guard Modification 10−6−98
018R1 Torque Pressure Transducer High Intensity Radiated Fields (HIRF) Protection
Modification
2−7−00
019 FADEC Wire Harness Standoff Installation/Inspection 4−23−99
020R2 Electromagnetic Compatability Test (EMC) for Optional Equipment Effects on the
FADEC Control
4−14−03
021R1 Inspection/Reidentification/Serialization of Cyclic Control Stick Sockets and Left
Hand Command (Co−Pilot) Cyclic Tube
3−11 −99
197 091 018 Engine Fuel Pressure Switch Replacement 2−23−99
198 092 Tail Rotor Fork Inspection, Four−Bladed 5−10−99
022 Torque Transducer Replacement 4−23−99
023R1 Cyclic Stick Replacement 7−30−99
024R1 Link Assembly Replacement 4−6−99
025 Fuel System Inspection 7−2−99
199 093 019 Turbine Outlet Temperature (TOT) Indicating System, One Time Inspection 1−11 −00
026 Turbine Outlet Temperature (TOT) Indicating System, One Time Inspection 1−11 −00
020R2 027R2 Forward and Center Thruster Control Cables, Conduit Cap Relief Area, Inspection 4−24−00
021 028 Forward and Center Thruster Cables, Conduit Cap at Telescopic Swivel End,
Inspection
11−19−99
200 094 078 022 Landing Gear Strut Inspection and Fairing Modification 4−7−00
029 Motive Flow Restrictor Removal 1−10−01
030R1 Inspection of Vertical Stabilizer and Torque Tube and Replacement of Attaching
Hardware
5−25−01
201R2 095R2 079R2 023R2 031R2 Main Rotor Blade Torque Event Inspection 2−04−04
032 Turbine Outlet Temperature (TOT) Indicator Replacement 12−13−01
033 Main Rotor Drive Shaft Life Reduction 12−13−01
034 Torque Transducer Electrical Connector One Time Inspection 12−13−01
024 035 Fan Pitch Control Aft Tube Assembly One Time Inspection 10−23−01
036 Tailboom Assembly Attach Fitting One Time Inspection and Repair 11−2−01
202 096 080 025 037 Main Transmission Bonding Jumper Inspection and Rework 8−14−02
038 Exhaust Duct Inspection 5−6−03
081 Minimum N1 Starting Speed Decal/Placard Installation 7−22−03
039 Tailboom Attach Fittings and Upper Longerons Inspection 12−9−03
040 Control Support Bracket Assembly Life Reduction with YSAS Installed 12−19−03
026 041 Tailboom Assembly Overlap Inspection and Rework 11−26−03
027 042 Forward and Center Thruster Cable Assemblies Connector One−Time Inspection 5−03−04
203R1 097R1 082R1 Tail Rotor Blade Abrasion Strip Tap Test and Modification 1−23−06
043 Tailboom Assembly Attach Fitting One Time Inspection, Attach Fitting and
Nutplate Replacement
4−13−06
044 Lateral Mixer Oputput Link Assembly, One Time Inspection 2−16−07
098 083 028 045 One Time Inspection of the Oil Cooler Blower, Drive Pulley Installation 3−28−07
204 099 084 Tail Rotor Blade Assembly, One Time Inspection. 4−26−07
029 046 NOTAR ® Fan Tension−Torsion (TT) Strap Replacement 3−6−08
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 8
Revision 23
BULLETINS
4. Cancelled or Superceded Service
Information Notices
(1). Table 2 a list of Service Information
Notices that have been cancelled or
superceded.
(2). Updated information, pertinent to the
Notice, has been incorporated into the
appropriate manuals.
(3). If the Notice is superceded by another
Notice, it will be noted in the Subject
column after the description.
5. Scope
The following is an explanation of how to read
Table 2.
(1). DN
−369D Model Helicopters
EN
−369E Model Helicopters
FN
−369F and 369FF Model Helicopters
NN
−500N Model Helicopters.
(2). Subject
− A brief description of the
Notice.
(3). Date
− Date the Notice was cancelled
or superceded.
Table 2. CANCELLED OR SUPERCEDED SERVICE INFORMATION NOTICES
369D 369E 369F 500N 600N SUBJECT DATE
2.3 Main Rotor Strap Pack Lamination Inspection (Superceded by DN−154) 1−15−88
4.1 Main Rotor Blade Phasing, Tracking and Balancing 8−2−93
5 600−Hour Periodic Inspection − Model 369D Cyclic Control System 8−2−93
7 Installation of 369D21008 Main Rotor Pitch Control Rod Assembly, Upper and
Lower Rod End Bearings
8−2−93
15 Periodic Inspection of 369D26300 and 369D26301 Landing Gear Damper
Assemblies
8−2−93
28 Field Modification of 369D29919 Main Rotor Blade Phasing Kit to new
369D29919−501 Configuration
8−2−93
29.3 Periodic Replacement of 369H5655−3 and −5 Oil Cooler Blower Fan Bearings;
Inspection of Pulley Attach Hardware and Driveshaft Couplings; Inspection and
Adjustment of Fan Drive Belt; Driveshaft Compression Check
8−2−93
32 New Periodic Inspection Intervals − Battery Overtemperature Warning System 8−2−93
33.1 Replacement of 369A1602 Tail Rotor Drive Fork Hinge Bolt and 369A1603 Nut;
New Assembly Procedure for Tail Rotor Hub and Drive Fork Unit; Periodic Check
of Flapping Hinge Bolt Preload
8−2−93
38 Daily Inspection of 369H5307 Tail Rotor Stop and 369D21724−3 Support 8−2−93
41.1 Operational Check of Engine Fuel Pump Filter Pressure (Bypass) Switch
Assembly
8−2−93
2 Inspection of Spare Main Rotor Blade Root Fitting Assemblies; Inspection of Main
Rotor Hub Lead−Lag Link Assemblies (Superceded by EN−42)
11−13−87
2 Inspection of Main Rotor Hub Lead−Lag Link Assemblies (Superceded by FN−31) 11−13−87
53.1 100−Hour Periodic Inspection of Fuel Tank Sending Unit and Fuel Low Warning
Light Indicating System
8−2−93
57 Field Repair of 369D21300 Pitch Housing Assembly, Main Rotor Hub 8−2−93
61.2 Periodic Check of 369D21400−502 and M50452 Main Rotor Elastomeric Damper
Assemblies
8−2−93
64 Pilot/Operator Check of 369D21210−501 Main Rotor Hub Strap Pack Assembly
(Superseded by DN−154)
1−15−88
74 Un−Assigned
75.1 Procedure for Installation of Tail Rotor Drive Shaft (Superceded by DN−95) 9−27−82
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
04−00−00
Page 1
Revision 41
FAA APPROVED
AIRWORTHINESS LIMITATIONS
Type Certificate No. H3WE
FAA Approved Airworthiness Limitations for MD Helicopters, Inc., Models 369D/E/F/FF and
500/600N.
1. General
The Airworthiness Limitations section is FAA approved and specifies maintenance required under
Code of Federal Regulations (CFR), Title 14, Federal Aviation Regulation (FAR), Part 43.16 and
91.403 unless an alternative program has been FAA approved.
REVISION: DATE FAA SIGNATURE AND DATE
Original Issue: October 31, 1990 Not FAA approved
Revision 1: March 29, 1991
Not FAA approved this revision
Revision 2: May 10, 1991
TR 91−001 August 12, 1991
Revision 3: September 9, 1991
TR 91−002 November 5, 1991
Revision 4: January 20, 1992
TR 92−004 May 20, 1992
Revision 5: August 24, 1992
TR 92−005 November 20, 1992
Revision 6: December 21, 1992
Revision 7: June 1, 1993 Section 04−00−00 Not Affected This Revision
TR 93−002 May 27, 1993
Revision 8: July 23, 1993
TR 94−001 January 21, 1994
Revision 9: April 22, 1994
Revision 10: September 26, 1994 Section 04−00−00 Not Affected This Revision
TR 94−002 October 24, 1994
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 2
Revision 41
04−00−00
FAA APPROVED
REVISION: DATE FAA SIGNATURE AND DATE
Revision 11: January 18, 1995
Revision 12: October 6, 1995 Section 04−00−00 Not Affected This Revision
TR 96−002: April 24, 1996
Revision 13: May 31, 1996
Revision 14: September 13, 1996
Revision 15: November 15, 1996 Section 04−00−00 Not Affected This Revision
Revision 16: January 6, 1997 Section 04−00−00 Not Affected This Revision
Revision 17: February 24, 1997
TR 97−001: July 2, 1997
TR 97−002: August 19, 1997
Revision 18: October 17, 1997
Section 04−00−00 Not Affected This Revision
T/R 97−001 and 97−002 Previously Signed
Revision 19: December 16, 1997
TR 98−001: March 25, 1998
Revision 20: June 1, 1998
Section 04−00−00 Not Affected This Revision
T/R 98−001 Previously Signed
TR 98−002: June 22, 1998
TR 98−003: 3 August 1998
Revision 21: 24 August 1998
Section 04−00−00 Not Affected This Revision
T/R 98−002 and 98−003 Previously Signed
Revision 22: 10 March 1999 Section 04−00−00 Not Affected This Revision
Revision 23: 1 June 1999 Section 04−00−00 Not Affected This Revision
Revision 24: 7 December 1999
Revision 25: 28 April 2000 Section 04−00−00 Not Affected This Revision
Revision 26: 17 August 2000
Revision 27: 9 October 2000 Section 04−00−00 Not Affected This Revision
Revision 28: 30 November 2000 Section 04−00−00 Not Affected This Revision
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
04−00−00
Page 3
Revision 41
FAA APPROVED
REVISION: DATE FAA SIGNATURE AND DATE
Revision 29: 11 May 2001
Revision 30: 11 July 2001 Section 04−00−00 Not Affected This Revision
TR 01−001: 10 August 2001
Revision 31: 5 November 2001
Section 04−00−00 Not Affected This Revision
T/R 01−001 Previously Signed
TR 02−002: 30 January 2002
Revision 32: 18 March 2002
Revision 33: 24 June 2002
TR 03−001: 18 June 2003
TR 03−002: 25 June 2003
Revision 34: 21 August 2003
Section 04−00−00 Not Affected This Revision
T/R 03−001 and 03−002 Previously Signed
TR 03−003: 30 September 2003
TR 03−004: 17 December 2003
Revision 35: 20 May 2004
Section 04−00−00 Not Affected This Revision
T/R 03−003 and 03−004 Previously Signed
TR 04−001: 28 May 2004
Revision 36: 11 November 2004
Revision 37: 13 December 2005 Section 04−00−00 Not Affected This Revision
TR 05−002: 16 December 2005
Revision 38: 25 April 2006
Section 04−00−00 Not Affected This Revision
T/R 05−002 Previously Signed
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 4
Revision 41
04−00−00
FAA APPROVED
REVISION: DATE FAA SIGNATURE AND DATE
TR 06−001: 05 July 2006
Revision 39: 10 April 2007 Section 04−00−00 Not Affected This Revision
TR 07−001: 11 April 2007 Section 04−00−00 Not Affected This Revision
Revision 41: 03 March 2008
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
04−00−00
Page 5
Revision 41
FAA APPROVED
AIRWORTHINESS LIMITATIONS
2. Component Mandatory Replacement
The Airworthiness Limitation Replacement
Schedule specifies the mandatory replacement
time, structural inspection interval and related
structural inspection procedures approved per
the certificate basis of the Type Certificate
Data Sheet No. H3WE and CAR 6 (6.250,
6.251) and CFR 27.571 for models 500/600N
unique components only. At the listed finite−
life, components or assemblies must be
removed from the helicopter and permanently
retired from service. At the listed inspection
interval, the components or assemblies must
be inspected in accordance with the Handbook
of Maintenance Instructions (HMI). The title
of the task and section of the HMI are referred
to which provide the inspection procedures and
criteria.
NOTE: Refer to CFR Part 43.10 for latest re-
quirements for the removal, installation,
storage and disposition of life−limited parts.
(1). A ‘‘life−limited’’ part is a physical
component of the helicopter to which a
maximum number of allowable operating hours or cycles are assigned.
Certain assemblies and components on
the helicopter have a limited life
established by MDHI and approved by
FAA Engineering. For example, a part
with an assigned limit of 1000 hours,
may accumulate 1000 hours of operation in service. Upon completion of the
1000 hours of operation, useful life of
the part is ended. The finite−life
assigned to different parts varies
according to engineering fatigue tests,
part experience, etc. The parts listed in
this section must be removed from the
helicopter at the finite−life indicated
and identified as to it’s expired life (Ref,
Table 1, Note (1)).
(2). All parts not having an assigned life or
stated to be of unlimited life, have a life
of not less than 20,000 hours.
(3). When a life−limited part or an assem-
bly that incorporates a life−limited part
is installed on a new or used helicopter,
the nomenclature, part number, serial
number, component time and current
helicopter hours are recorded in the Log
Book and component log for the
helicopter. Whether the life−limited
part is new or used, the remaining
number of useful life hours and previous inspection time, if applicable, for
the part is added to the existing
helicopter time. The total helicopter
hours obtained then denotes the
subsequent time at which the part must
be removed from the helicopter or
inspected.
(4). If a life−limited part, is part of an
assembly, the assembly must be
removed from the helicopter when the
time expires. The assembly may be
overhauled and restored to maximum
number of hours of useful life by
installing new life−limited parts plus
all other parts specified in the overhaul
instructions (Refer to Component
Overhaul Manual).
(5). If interchanged between different model
helicopters (for instance, Model 369D to
369FF or vice versa), any component
having a limited life or overhaul
schedule must be restricted to the
lowest service life or TBO schedule
indicated for the helicopter models and
serial numbers affected.
(6). Refer to the appropriate Allison
Operation and Maintenance Manual for
engine component replacement requirements.
3. Component Mandatory Inspections
Some components with mandatory inspection
intervals require inspections to be completed
in accordance with procedures detailed in
other sections of this maintenance manual.
The appropriate inspection procedures are
referenced in the Notes
flagged to each
component to be inspected. All maintenance
manual procedures which are referenced in the
FAA Approved Airworthiness Limitations
Component Mandatory Replacement Schedule
are FAA approved procedures which cannot be
changed without FAA review and approval of
the proposed changes.
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 6
Revision 41
04−00−00
FAA APPROVED
4. Retirement Index Number (RIN)
(1). A Retirement Index Number (RIN) is a
number that accounts for different
usage spectra in assigning the retirement time for a component.
The RIN is calculated as the sum of an
adjustment factor times flight hours
plus another adjustment factor times
Torque Events.
When a component reaches 1,000,000
RIN’s, it has reached it’s maximum life
and is to be scrapped.
5. Torque Event (TE)
A Torque Event (TE) is defined as:
The transition to a hover from forward
flight.
Any external lift operation.
NOTE: An external lift can either be on the car-
go hook, external hoist or in external baskets.
For external lift operators, an external
load is recorded as two (2) TE’s (pick−
up and drop−off).
Hover taxi with no external load will
typically result in no TEs.
6. External Lift and Torque Event (TE)
Requirements
The 369D/E/F/FF − 500/600N helicopters are
multi−use helicopters. If the helicopter is used
primarily for external lifts or training flights
(high TE flights), there may be a reduction in
inspection intervals of some components.
For safe operation of the heli-
copter, TE’s must be recorded in
the Rotorcraft Log Book. Each external lift
will be recorded as two (2) TE’s.
(1). Determine the number of TE’s and
external lifts the helicopter accumulates per hour of flight time.
(2). Record all TE’s in Rotorcraft Log Book
and continue to record all TE’s.
(3). Perform required TE inspections.
CAUTION
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
04−00−00
Page 7
Revision 41
FAA APPROVED
Table 1. Airworthiness Limitations Schedule
Component
(1)
Model
Part Number
(2)
Finite Life
Hours
(1)
Mandatory
Inspection
Hours
Main Rotor System
Blade assembly, main rotor 369D/E(5)(6)
369D21100 3530 (37) 25 (11)(20)
369D21100−516 3530 (37) 100 (20)
369D21100−517 2500 (31) 25 (22)
369D21100−517 3530 (37) 100 (20)
369D21100−523 4000 (37) 100 (20)
369D21120−501 3530 (37) 100 (20)
369D21120−503 3530 (37) 100 (20)
369F/FF (6)
369D21102 3430 (37) 25 (11)(20)
369D21102−503 3430 (37) 100 (20)
369D21102−517 2500 (31) 25 (22)
369D21102−517 3430 (37) 100 (20)
369D21102−523 4000 (37) 100 (20)
369D21121−501 3430 (37) 100 (20)
369D21121−503 3430 (37) 100 (20)
500N (6)
369D21102−503 3430 (37) 100 (20)
369D21102−517 2500 (31) 25 (22)
369D21102−517 3430 (37) 100 (20)
369D21102−523 4000 (37) 100 (20)
369D21121−501 3430 (37) 100 (20)
369D21121−503 3430 (37) 100 (20)
600N (6)
369D21102−517 (21) 1900 (32)(37) 100 (20)
369D21102−523 3200 (33)(37) 100 (20)
369D21121−501 3200 (33)(37) 100 (20)
369D21121−503 3200 (33)(37) 100 (20)
Folding pin, main rotor blade attach 369D/E/F/FF
369A1004 2850
369A1004−3 2850
369A1004−5 7600
500/600N 369A1004−5 7600
Hub subassembly, main rotor 369D/E/F/FF
500N
369D21201 8900
Pitch housing assembly, main rotor hub 369D
369D21300 9100
369D21300−501 9100
369E/F/FF
500N
369D21300−501 9100
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 8
Revision 41
04−00−00
FAA APPROVED
Table 1. Airworthiness Limitations Schedule (Cont.)
Component
(1)
Mandatory
Inspection
Hours
Finite Life
Hours
(1)
Part Number
(2)
Model
Retention strap assembly, main rotor hub 369D
369D21210 2770 100 (4)
369D21210−501 2770 100 (4)
369E/F/FF 369D21210−501 2770 100 (4)
500/600N 369D21210−501 2770 100 (4)
Bolt − lead−lag hub, main rotor
369D 369A1220 6120
369D/E/F/FF
500N
369D21220 6120
600N 369D21220 5400 (34)
Link assembly − lead lag hub, main rotor 369D/E
369H1203−BSC (39) 5762 25 (23)
369H1203−21 (39) 5762 25 (23)
369H1203−31 (39) 5762 25 (11)
369H1203−51 (39) 11080
369H1203−53 (40) 11080
369H1203−61 (39) 11080
369F/FF
369H1203−21 (39) 5762 25 (23)
369H1203−31 (39) 5762 25 (11)
369H1203−51 (39) 11080
369H1203−53 (40) 11080
369H1203−61 (39) 11080
500N
369H1203−51 (39) 11080
369H1203−53 (40) 11080
369H1203−61 (39) 11080
600N
369H1203−51 (39) 11080
369H1203−53 (40) 11080
Lead lag damper − main rotor 369D
369D21400−501 6060
M50452 On Cond. (16)
369D/E/F/FF
500/600N
369D21400−503 On Cond. (16)
Drive shaft, main rotor
369D/E 369D25510 5020 300 (8)
369F/FF 369D25510 3675 300 (8)
500N 369D25510−21 3260 300 (15)
369D/E 369F5510 (42)
369F/FF 369F5510 (42)
500N 369F5510 (42)
600N 600N5510 14000 (35)
Mast assembly, main rotor
369D/E/F/FF
500N
369D22014 10450
600N 369D22014 3500
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
04−00−00
Page 9
Revision 41
FAA APPROVED
Table 1. Airworthiness Limitations Schedule (Cont.)
Component
(1)
Mandatory
Inspection
Hours
Finite Life
Hours
(1)
Part Number
(2)
Model
Drive Shafts, Couplings and Clutches
Drive shaft, main rotor transmission 369D/E/F 369A5510 3790
Coupling, main transmission drive shaft
369D/E/F/FF 369H5660 4300
500N 369H5660 3200
Overrunning clutch assembly 369D/E/F/FF
500/600N
369F5450−501 On Cond. 100 (24)
Sprag assembly, overrunning clutch 369D/E/F/FF
369A5364 (3) 300 (10)
369D25351
500N 369D25351 (3) 300 (10)
369D/E/F/FF
500/600N
369F5456 (3) 300 (17)
Drive shaft, fan
500N 500N5200 2620
600N 500N5200 1200 (36)
Drive shaft, tail rotor
369D/E 369D25518 13900
369F/FF
369DSK152−11 13900
369D25518−503 14610
Coupling − tail rotor drive shaft (Bendix)
(NOTE
: Not certified on 369FF Model) (9)
369D/E/F
369A5501 4980
369H92564 (7) 4980
Anti−Torque System
Gearshaft assembly, tail rotor input
369D/E 369D25434 12000
369F/FF 369D25434 3365
Gearshaft, tail rotor output pinion 369D/E/F/FF 369D25430 7290
Blade assembly, tail rotor 369D/E
369D21613 5200
369D21613−11 5140
369D21613−31 5140
369D21613−41 5140
369D21613−51 5140
369D21613−61 5140
369D21613−71 5140
369D21640−501 (38) 400
369D21640−503 (38) 5140
369D21640−505 (38) 5140
369D21640−507 (38) 5140
369F/FF
369D21606 5140
369D21642−501 (38) 400
369D21642−503 (38) 5140
369D21642−505 (38) 5140
369D21642−507 (38) 5140
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 10
Revision 41
04−00−00
FAA APPROVED
Table 1. Airworthiness Limitations Schedule (Cont.)
Component
(1)
Mandatory
Inspection
Hours
Finite Life
Hours
(1)
Part Number
(2)
Model
Blade assembly, tail rotor
(optional 4−blade)
369D/E
369D21615 10000
369D21641−501 (38) 400
369D21641−503 (38) 10000
369D21641−505 (38) 10000
369D21641−507 (38) 10000
Hub, tail rotor 369D/E/F/FF 369A1725 3450
Retention strap assembly, tail rotor
369D/E/F 369A1706 5100
369FF
369A1706−507 5100
369A1706−509 5100
Blade assembly, NOTAR fan 500N
500N5310−15 7500
500N5310−19 7500
600N 500N5310−19 12500
Hub, fan 500N
500N5352−7 7500
500N5352−9 7500
600N 500N5352−9 7500
Tension−Torsion Strap, NOTAR®
500N
500N5311−5 (43)(44)
600N
Shaft, NOTAR fan support 600N 500N5357−13 4000
Pitch plate assembly 500/600N 500N5363−7 7500
Tube assembly, fan pitch 500N 500N7113−3 600 (18)
Rotating cone assembly 500N
500N3740−1 10000
500N3740−41 10000
600N 500N3740−61 10000
Tailboom
Bolts, tailboom attach 369D/E/F/FF MS21250−06014 21950
Tailboom assembly
369D/E 369D23500 10300
369F/FF 369D23500−507 10300
500N
500N3500−19 10000 100 (14)
500N3500−29 10000
500N3500−501 10000
500N3600−501 10000 100 (14)
600N
600N3500−503 2500 (25)
600N3500−505 5900
600N3500−507 1000
600N3500−509 6000 (19)
600N3500−511 6000 (19)
600N3500−513 2500 (25)
600N3500−515 5900
600N3500−517 1000
Empennage fittings 600N
500N3530−7/8 On Cond. 100 (26)
500N3530−9/10 On Cond. 100 (26)
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
04−00−00
Page 11
Revision 41
FAA APPROVED
Table 1. Airworthiness Limitations Schedule (Cont.)
Component
(1)
Mandatory
Inspection
Hours
Finite Life
Hours
(1)
Part Number
(2)
Model
Vertical stabilizer assembly
369D/E 369D23600 12700
369F/FF 369D23600−505 3388
Torque tube, horizontal stabilizer
500N 500N3950−5 5000
600N
500N3950−7 3000
600N3950 1000 (19)
Horizontal stabilizer assembly
369D (12) 369D23601 7700
369E (12)
421−087−505 7700
421−087−905 (13) 7700
369F/FF (12)
421−087−503 7700
421−087−903 7700
600N
500N3910−25 10000 (19)
500N3910−27 10000 (19)
Controls
Longitudinal idler bellcrank assembly 369D
369A7301 6500
369A7301−501 6500
369E/F/FF 369A7301−501 6500
500N 369A7301−501 2870
Idler assembly, longitudinal pitch mixer
369D/E/F/FF 369A7603 13600
500N 369A7603 6050
Longitudinal control rod 500N
369A7011−13 7740
369A7011−15 7740
Socket, cyclic stick 600N 369A7141 1000 8 (27)
Cyclic tube assembly 600N 369D27132−503 1200 8 (27)
Housing, collective stick 600N 369A7347 450
Tube, collective pitch control 600N 369A7348 400
Tube assembly, collective pitch (pilot) 600N 369H7354−3 600
Socket, cyclic stick 600N 369A7802 1000 8 (27)
Tube, collective pitch (co−pilot) 600N 369A7809 1800
Housing, collective stick 600N 369A7820 450
Housing, collective stick 600N 369H7837 450
Tube assembly, collective pitch (co−pilot) 600N 369H7838−3 1000
Fuselage Sta. 75 controls support bracket 600N
369N2608−11 6000 (41)
600N2608−9 Unlimited
Airframe
Landing gear brace 600N 600N6010−17/19 5900 (28)
Landing gear strut 600N 600N6022−7/8 696 (29)
Landing gear foot 600N 600N6043−3 3900 (30)
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 12
Revision 41
04−00−00
FAA APPROVED
Table 1. Airworthiness Limitations Schedule (Cont.)
Component
(1)
Mandatory
Inspection
Hours
Finite Life
Hours
(1)
Part Number
(2)
Model
Floats
Squib cartridge, used on Emergency float
kit 369D292473−5, −6, −9, −10, −11, −12
NOTE
: Life is based from original date of
manufacture.
369D/E/F/FF
500N
12552−1
(Holex, Inc.)
5 years
281993
(Walter Kidde)
5 years
12754−1
(Holex, Inc.)
5 years
5003527
(Tavco)
5 years
Stabilizer support, utility float 369D/E
369D292036 3190
369DSK66 3190
NOTES:
(1) Life−limited components interchanged between models or configurations must be restricted to the lowest
service life indicated for the models or configurations affected. Life−limited components removed at
retirement are to be mutilated/destroyed or conspicuously marked to prevent inadvertent return to service.
Parts are applicable only on models under which a service life is listed.
Life−limited components cannot be altered or permanently marked in any manner without compromising
the part integrity. Part tagging or other record keeping system is required.
Related component records must be updated each time component is removed from service.
(2) Service life shown for the basic (no dash number) part numbers apply to all dash numbered versions
unless
otherwise indicated.
(3) With no cargo hook attached
: − No retirement life assigned (Ref. Sec. 05−10−00, Component Overhaul or
Recommended Replacement Schedule).
With cargo hook attached and no separate log
: − 1800 hours.
With cargo hook attached and with separate log
: − 1800 hours of external load operating time when logged
separately.
(For 369D/E/F/FF helicopters with 369A5364 or 369D25351 sprag assembly, Refer to AD 90−19−02.)
(4) Inspect in accordance with Main Rotor Strap Pack Lamination Inspection at 100−hour intervals, or 25−hour
intervals if 2 laminates (369D/E/F/FF − 500N) or 1 laminate (600N) have failed in any one leg or tongue
area of any strap assembly. A single cracked laminate between the shoes at the outboard end of a strap
pack is cause for rejection of the hub assembly
369D/E/F/FF − 500N: (Ref. Sec. 62−20−00, Main Rotor Strap Pack Lamination Inspection).
600N: (Ref. Sec. 62−20−60, Main Rotor Strap Pack Lamination Inspection).
(For 369D/E/F/FF helicopters, refer to AD 89−02−01.)
(5) The 369D21100−513, −515, 516, 517 and −523 main rotor blades are not interchangeable with any earlier
configuration blades (Basic, −505 or −509); however, the −505 and −509 blades are interchangeable and
the −513 and −515 blades are interchangeable. The −505 and −509 configuration blades may be modified
to the −513M configuration, which is fully compatible with the −513 blade. (For information concerning
modification, contact MDHI Customer Service Department.)
(6) For the 369D/E helicopters, the 369D21120−501, −503 main rotor blade has all the same inspections and
interchangeability as the 369D21100−517 main rotor blade.
For the 369F/FF − 500N helicopters, the 369D21121−501, −503 main rotor blade has all the same
inspections and interchangeability as the 369D21102−517 main rotor blade.
For the 600N helicopters, the 369D21121−501, −503 main rotor blade has all the same inspections and
interchangeability as the 369D21102−523 main rotor blade.
(7) Used with 369H90123 Rotor Brake Kit.
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
04−00−00
Page 13
Revision 41
FAA APPROVED
(8) Inspect main rotor drive shaft every 300 hours (Ref. Sec. 63−10−00, Main Rotor Drive Shaft Inspection
(300 Hour)) (Reference AD 81−26−01).
(9) Failsafe device, P/N 369D25530 bolt and 369D25531 socket, must be used at both ends of tail rotor
driveshaft in accordance with Tail Rotor Drive Shaft Installation with Bendix Couplings (Reference AD
86−20−07).
(10) For helicopters equipped with a cargo hook, inspect overrunning clutch sprag assembly P/N 369D25351,
clutch inner race P/N 369A5353 and outer race 369A5352 every 300 hours (Ref. C.O.M., Sec. 63−10−10,
Overrunning Clutch Sprag Inspection (300 Hour)). To establish time in service, either clutch total time with
hook attached or a separate and permanent log of external load operating time per CFR 91.417, may be
used.
(For 369D/E/F/FF helicopters with 369A5364 or 369D25351 sprag assembly, Refer to AD 90−19−02.)
(11) Inspect main rotor blade root fittings and main rotor lead−lag link assemblies every 25 hours in accordance
with Main Rotor Blade Upper and Lower Root Fitting Attach Lug and Lead−Lag Link Attach Lug Inspection
(25 Hour) and every 100 hours in accordance with Main Rotor Blade Upper and Lower Root, Fitting Attach
Lug and Lead−Lag Link Attach Lug Inspection (100 Hour) (Ref. Sec. 62−10−00) (Reference AD 95−03−13).
(12) Tip plates, tip weights (where applicable) and attaching hardware have no retirement life and may be
reused on replacement horizontal stabilizers.
(13) 421−087−903 and −905 require addition of tip plates, tip weights and attaching hardware before
installation.
(14) Inspect the three upper slot bridges for cracks (Ref. Sec. 05−20−00).
(15) Inspect main rotor drive shaft every 300 hours (Ref. Sec. 63−10−00, Main Rotor Drive Shaft Inspection
(300 Hour)).
(16) Inspect for deterioration every 600 hours up to a total time of 4200 hours and every 300 hours thereafter
until deterioration is sufficient to retire assembly
369D/E/FF − 500N: (Ref. Sec. 62−20−00, Main Rotor Damper and Attachments Inspection)
600N: (Ref. Sec. 62−20−60, Main Rotor Damper and Attachments Inspection).
(17) For helicopters equipped with a cargo hook, inspect overrunning clutch sprag assembly P/N 369F5456,
clutch inner race P/N 369F5455 and outer race 369F5453 every 300 hours. To establish time in service,
either clutch total time with hook attached or a separate and permanent log of external load operating time
may be used.
(18) 500N7113−11 tube assembly, fan pitch is an On−Condition part and replaces the 500N7113−3 tube
assembly.
(19) Interim hours: life extension testing in progress.
(20) Inspect upper and lower blade root fittings every 100 hours in accordance with Main Rotor Blade Upper
and Lower Root, Fitting Attach Lug and Lead−Lag Link Attach Lug Inspection (100 Hour) (Ref. Sec.
62−10−00)
(For 369D/E/F/FF − 500N helicopters, Reference AD 96−
10−09).
(21) Main rotor blades, P/N 369D21102−517 with S/N 1976 thru 2100, 2106 thru 2115 are not to be installed on
600N helicopter (Reference Service Bulletin SB600N−007R2) (Reference AD 98−15−26).
(22) Inspect main rotor blades with 600 or more hours of operation every 25 hours of helicopter operation with a
10X magnifying glass for cracking of the lower surface of the blade emanating from the root fitting and
doubler at the inboard end of the blade and to detect debonding between the blade root end fitting and
doubler if missing or cracked adhesive or paint is observed. (Reference Service Bulletins SB369D−195R3,
SB369E−088R3, SB369F−075R3, SB500N−015R3) (Reference AD 98−15−26).
(23) Perform Main Rotor Blade Upper and Lower Root, Fitting Attach Lug and Lead−Lag Link Attach Lug
Inspection (25 Hour) up to a total time of 500 hours and every 15 hours thereafter and every 100 hours in
accordance with Main Rotor Blade Upper and Lower Root Fitting, Attach Lug and Lead−Lag Link Attach
Lug Inspection (100 Hour) (Ref. Sec. 62−10−00) until retirement of 369H1203−BSC and −21 Lead−Lag
Link Assembly. (Reference AD 95−03−13).
(24) Inspect clutch retainer and bearing carrier for evidence of spinning and/or wear (Ref. Sec. 05−20−20).
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 14
Revision 41
04−00−00
FAA APPROVED
(25) The 600N3500−503 tailboom may be reworked to a 600N3500−505 tailboom, and the 600N3500−513
tailboom may be reworked to a 600N3500−515 tailboom by modifying the attachment fittings to all−steel
fittings.
(26) (Ref. Sec. 05−20−00) Using a flashlight and 10X magnifying glass, inspect horizontal stabilizer mounting
brackets for cracks (pay particular attention to the forward inboard legs) (Ref. Tailboom Inspection).
(27) Sockets must be inspected for cracks every eight hours after the initial 100 hour inspection.
(28) Log all landings: Brace life is limited to 35400 logged landings or 5900 hours flight time if landing are not
logged (assumed six landings per one hour of flight time).
(29) Log all landings: Strut life is limited to 4170 logged landings or 696 hours flight time if landing are not
logged (assumed six landings per one hour of flight time).
(30) Log all landings: Foot life is limited to 23780 logged landings or 3900 hours flight time if landing are not
logged (assumed six landings per one hour of flight time).
(31) The following main rotor blades have a finite life of 2,500 hours or 15,000 torque events*, whichever occurs
first;
P/N 369D21100−517 with S/N H664, H665, H667, H669, H671, H672, H674, H676, H679, H680, H683 thru
H724, H726 thru H999 and J000 thru J039, J041 thru J055 and
P/N 369D21102−517 with S/N 1976 thru 2100, 2106 thru 2115.
* TORQUE EVENT (TE) − A TE is recorded for every transition from forward flight to a hover (Reference
Service Bulletins SB369D−195R3, SB369E−088R3, SB369F−075R3, SB500N−015R3).
(32) RIN = (200 x Hrs.) + (52 x TE).
(33) RIN = (160 x Hrs.) + (24 x TE).
(34) RIN = (153 x Hrs.) + (3 x TE).
(35) RIN = (50 x Hrs.) + (3 x TE).
(36) RIN = (768 x Hrs.) + (11 x TE).
(37) After accumulation of 750 flight hours and 13,720 TE, perform Main Rotor Blade Torque Event Inspection
(Ref. Sec. 62−10−00) every 35 flight hours or 200 TE’s (whichever occurs first).
(38) The 369D21640−501, −503, −505, −507 tail rotor blades are two−way interchangeable with the 369D21613
tail rotor blades in sets of two only.
The 369D21641−501, −503, −505, −507 tail rotor blades are two−way interchangeable with the 369D21615
tail rotor blades in sets of two only (installed on the same inboard or outboard hub).
The 369D21642−501, −503, −505, −507 tail rotor blades are two−way interchangeable with the 369D21606
tail rotor blades in sets of two only.
(39) The 369H1203−BSC, −11, −21, −31, −51 and −61 lead lag link assemblies can only be installed using the
369H1235−BSC bearing.
(40) The 369H1203−53 lead lag link assembly can only be installed using the 369H1235−1 bearing.
(41) The 369N2608−11 Control Support Bracket must be removed from 600N helicopters equipped with YSAS
(Ref. SB600N−040).
(42) RIN = (29 x Hrs.) + (1 x TE).
(43) The Tension−Torsion Strap has a 5 year calendar life. This life begins the day the original package has
been opened. Lord Corporation has determined that the straps can, over time, absorb moisture that can
cause the straps to have decreased strength.
(44) 500N5311−5 Tension−Torsion Straps previously installed on MD900 helicopters are life limited to 2,500
hours when installed on 500N and 600N series helicopters.
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
05−50−00
Page 9
Revision 41
Table 1. Conditional Inspections (Cont.)
Model Chap/SectRequirement
ALL If overrunning clutch assembly shows magnetism, remove engine and overrunning
clutch and overhaul.
ALL Perform a ground run operational check on the aircraft. Functionally check the flight
control system, and all avionics, electrical, lighting, communication, and navigation
systems.
67
96
97
ALL Repair any damage and replace damaged components as required.
If lightning strike is evident on main rotor system:
ALL Inspect blades for damage such as burns, pitting, skin separation, etc. If damage is
evident, scrap damaged blade(s).
62
ALL Remove hub assembly and return for overhaul. 62
ALL Inspect all bearings in the fixed and rotating control system located on the main rotor
mast.
62
ALL Remove transmission assembly and overhaul. 63
ALL Inspect main rotor mast and drive shaft for evidence of burns. 63
ALL Check drive shafts for residual magnetism. If magnetized or damaged, scrap drive
shafts and remove engine for overhaul.
63
71
If lightning strike is evident on tail rotor system:
369D/E/FF Inspect blades for damage such as burns, pitting, skin separation, etc. If damage is
evident, scrap damaged blade(s).
64
369D/E/FF Overhaul tail rotor assembly. COM
369D/E/FF Scrap pitch change links and pitch change assembly. 64
369D/E/FF Inspect bellcrank and control rod for any indications of arcing. Scrap parts with
indications of arcing.
67
369D/E/FF Overhaul tail rotor gearbox. COM
369D/E/FF Inspect tail rotor drive shaft and drive shaft damper for magnetism and/or burns. 63
369D/E/FF Check oil cooler blower assembly, overrunning clutch and tail rotor drive shaft
couplings for residual magnetism; replace as necessary.
63
369D/E/FF Inspect oil cooler assembly for damage; replace as necessary. 63
369D/E/FF If previous drive train items show magnetism, overhaul transmission. COM
369D/E/FF If overrunning clutch assembly shows magnetism, remove engine and overrunning
clutch and overhaul.
71
COM
369D/E/FF Inspect engine mounts and fitting for damage. Replace as necessary. 71
AFTER 369F5100 MAIN TRANSMISSION LUBRICATION PUMP IMPENDING BYPASS INDICATOR POPS
ALL Refer to Troubleshooting Power Train System 63−00−00
WHENEVER ENGINE IS REMOVED
ALL Remove fire blanket from above engine and inspect airframe above engine for
evidence of cracks.
53
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 10
Revision 34
05−50−00
This Page Intentionally Left Blank
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
TABLE OF CONTENTS
Para/Figure/Table Title Page
20−10−00 Torque A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Maintenance Practices 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1. Torque Wrenches 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2. Application of Torque Wrench Loads 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3. Bearings Installation, Staking or Swaging Force 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4. Control Tube Jam Nut Torquing 202 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5. Standard Hardware Torque Values 202 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Table 201. Recommended Standard Torques for Tension−Type Fasteners 203 . . . . .
Table 202. Recommended Standard Torques for Shear−Type Fasteners 204 . . . . . . .
Table 203. Locking (Drag) Torque for Self−Locking Fasteners 205 . . . . . . . . . . . . . . .
20−20−00 Cleaning A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Maintenance Practices 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1. Cleaning 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2. Fuselage Interior Trim and Upholstery Cleaning 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3. Airframe Exterior and Rotor Blades Cleaning 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4. Transparent Plastic Cleaning 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5. Engine Compressor Contamination Removal 202 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6. Cleaning Of Engine Air Inlet Screens 202 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
20−30−00 Painting A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Maintenance Practices 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1. Paint Finish 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2. Paint Removal 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3. Paint Touchup 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. Touchup − Small Sanded Areas 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Touchup − Flaking or Dried Paint or Primer 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C. Touchup − Primer Not Adhering to Metal Finish 201 . . . . . . . . . . . . . . . . . . . . . . . . . . .
D. Touchup − Glass Fiber Laminate Parts 202 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
E. Touchup − Polycarbonate Plastic Parts 202 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
F. Touchup − ABS Thermoplastic Parts 202 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4. Main Rotor Blade Paint 203 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. Main Rotor Blade Paint Removal 203 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Main Rotor Blade Paint Application 203 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5. Tail Rotor Blade Paint 204 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. Tail Rotor Blade Paint Removal 204 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Tail Rotor Blade Paint Application 204 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
20−40−00 Corrosion Prevention A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Maintenance Practices 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1. Corrosion Control 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
20 Contents
Page i
Revision 41
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
TABLE OF CONTENTS (Cont.)
Para/Figure/Table Title Page
2. Magnesium Alloys − Insulation Against Corrosion 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3. Sealing Compound Application 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4. Main Rotor Hub Corrosion Prevention (Tri−Flow Wash Procedure) 201 . . . . . . . . . . . . .
5. Main Rotor Blades Corrosion Arresting 202 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. Main Rotor Blade and Damper Attach Pins − Corrosion Prevention 202 . . . . . . . . . .
6. Magnesium Alloy Exterior Surface Touchup Treatment 203 . . . . . . . . . . . . . . . . . . . . . . .
7. Aluminum Alloy Exterior Surface Touchup Treatment 203 . . . . . . . . . . . . . . . . . . . . . . . .
8. Steel Alloy Exterior Surface Touchup Treatment 203 . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
9. Splitter Bungee Spring Corrosion Control (500N) 204 . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Table 201. Anti−Corrosion Chemical Finishes − Aluminum 204 . . . . . . . . . . . . . . . . . .
20−90−00 Nondestructive Inspection A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Maintenance Practices 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1. Nondestructive Inspection Methods 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A. Visual Inspection 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 201. Visual Inspection Technique 201 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B. Dye Penetrant Inspection 202 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C. Coin Tap Inspection 202 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
D. Fluorescent Penetrant Inspection 202 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
E. Magnetic Particle Inspection 202 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 202. Coin Tap Inspection 203 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
F. Eddy Current Inspection − General 203 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Page ii
Revision 41
20 Contents
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
P/N 369F5100
63−20−25
Page 203
Revision 41
Damage to main rotor drive
shaft or main transmission
splines can occur during installation. Care
should be taken while meshing drive shaft
splines into transmission output splines to
prevent damage.
NOTE: The following procedure will require
the assistance of another person.
(2). With assistance, slowly and evenly lift
and position transmission in place.
(3). Install four washers and nuts; torque to
900 − 1100 inch−pounds (101.69 −
124.28 Nm) plus drag torque.
(4). If transmission is new, drain any
residual preservative oil. Service
transmission with lubricating oil
(CM125) (Ref. Sec. 12−00−00).
(5). Connect wiring to tachometer genera-
tor, two chip detectors and oil pressure
switch.
(6). Install anti−torque drive shaft (Ref.
Sec. 63−15−10/30).
When reinstalling main rotor
drive shaft, check that there is
no gap between shaft mounting flange and
rotor hub before tightening installation
bolts. Gap indicates that shaft splines are
not correctly meshed in transmission.
(7). If main rotor drive shaft has been
removed, apply coating of preservative
oil (CM121) on shaft before reinstallation and install drive shaft (Ref. Sec.
63−10−00).
(8). Connect anti−torque output shaft seal
drain line and input shaft seal drain
line and two hoses that attach to
lubrication pump.
(9). Install cooling blower (Ref. Sec.
63−21−00).
(10). Coat input drive coupling splines with
grease (CM111) and coat bolt threads
with anti−seize compound (CM112)
before assembly.
When installing pulley and
guard, make sure the spring pin
in pulley is fully engaged inside hole in
pulley guard. If the spring pin does not align
correctly with hole in pully guard, the
torque will be incorrect.
(11). Install pulley guard, drive pulley, shim,
coupling and coupling bolt and temporarily tighten coupling bolt to approximately 250 inch−pounds (28.25 Nm).
NOTE: Refer to Sec. 63−10−00, Main Transmis-
sion Drive Shaft Installation and for coupling shimming, coupling torque and drive
shaft installation.
(12). Install main transmission drive shaft
(Ref. Sec. 63−10−00).
(13). Ground run helicopter (refer to appro-
priate PFM) and check drive system for
excessive vibration and unusual noise.
Verify absence of oil over−temperature
and low pressure indications. Inspect
for oil leakage.
(14). Install access covers and sound insula-
tion.
3. Main Transmission Stripping
(Ref. Figure 202)
(1). Remove tachometer generator.
(2). Remove coupling bolt, coupling and
shim from anti−torque output shaft.
(3). Remove coupling bolt, coupling, shim,
drive pulley and pulley guard from
main transmission input shaft.
(4). Remove input shaft seal drain connec-
tor (Ref. Sec. 12−00−00).
(5). Install suitable covers and plugs to
protect all openings, including threaded
holes.
CAUTION
CAUTION
CAUTION
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
P/N 369F5100
Page 204
Revision 28
63−20−25
CSP102−009C
COUPLING BOLT
A
B
A
B
OIL COOLER
BLOWER
OUTPUT
COUPLING
ANTI−TORQUE
DRIVE SHAFT
ROTOR
BRAKE
OUTPUT
PINION
OIL FILLER
CHIP DETEC-
TORS
INPUT
COUPLING
ENGINE−TO−TRANSMISSION
DRIVE SHAFT
DRIVE PULLEY
SNUBBER (600N
ADAPTER (369D/E/FF − 500N
PACKING
PRESSURE SWITCH LOCK WIRE
VIEW B−B
LOOKING UP
TACH GENERATOR
JUMPER ASSEMBLY
VIEW A−A
LOOKING FORWARD
TRANSMISSION
OIL FILTER
DIFFERENTIAL PRESSURE INDICATOR (IMPENDING BYPASS INDICATOR)
Figure 202. 369F5100 Main Transmission Build−Up
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
63−21−00
Page 411
Revision 41
When installing pulley and
guard, make sure the spring pin
in pulley is fully engaged inside hole in
pulley guard. If the spring pin does not align
correctly with hole in pully guard, the
torque will be incorrect.
(2). Install pulley guard on main transmis-
sion input shaft.
(3). With belt looped around transmission
input shaft, position mounting bracket
on main transmission pad and loosely
install two bolts with washers from the
bottom of bracket and two bolts with
washers from top of bracket.
(4). Before tightening bolts, insert two
shims between bracket and transmission pad.
(5). Verify that blower scroll clears anti−
torque drive shaft by a minimum of
0.190 inch (4.826 mm).
In the following step, do not use
levers or other tools on belt, or
in any way force belt onto pulley.
(6). Slide driver pulley onto transmission
input shaft to engage belt in teeth of
both pulleys.
D The minimum of 0.010 inch (0.254 mm)
measurement between the bolt seating
surface and the input shaft must be obtained to ensure proper clamp−up.
Warped shims or foreign material could
provide a false 0.010 inch (0.254 mm)
minimum measurement and improper
clamp−up could result, which during normal operation, may damage the main
transmission input shaft.
D Do not use clutch coupling shims under
transmission input coupling. Inside diameter of clutch coupling shim is different
than shim used on transmission input
coupling. Incorrect diameters can cause
an improperly seated shim, misalignment
and cocked coupling.
(7). Torque bolts to 70 − 90 inch−pounds
(7.91 − 10.17 Nm).
(8). Coat threads of coupling bolt with
anti−seize compound (CM112).
(9). Lubricate input shaft splines and
coupling splines with grease (CM111).
(10). Install input coupling shim and
coupling on transmission input shaft
with coupling bolt.
(11). Adjust belt tension (Ref. Sec. 63−21−00,
Cooling Blower Belt Tension Check and
Adjustment).
NOTE: Check coupling bolt for a minimum of
25 inch−pounds (2.82 Nm) drag torque.
(12). Torque coupling bolt to 315 − 365
inch−pounds (35.59 − 41.24 Nm) plus
drag torque.
(13). Connect drain tube to cooling blower
scroll fitting. Clamp tube to fitting with
two turns of lockwire (CM702).
(14). Roll exhaust duct rubber connectors
onto scroll outlets (transmission oil
cooler duct and engine oil cooler duct)
and secure with tie straps.
CAUTION
CAUTION
CAUTION
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 412
Revision 37
63−21−00
NOTES:
1. TORQUE BOLTS TO 70 − 90 INCH−POUNDS (7.91 − 10.17 NM).
2. AFTER TORQUING, SEAL BOLT HEADS WITH SEALANT (CM425).
3. TORQUE BOLTS TO 70 − 90 INCH POUNDS (7.91 − 10.17 NM) AND SAFETY WITH LOCKWIRE (CM702).
4. TORQUE COUPLING BOLT TO 315 − 365 INCH POUNDS (25.59 − 41.24 NM) PLUS DRAG TORQUE
(DRAG TORQUE TO BE NOT LESS THAN 25 INCH−POUNDS (2.82 NM)).
369D25626
FAN BRACKET
NAS6604H8 BOLT
(NOTES 2, 3)
NAS6604H8 BOLT
(NOTES 2, 3)
369F5190−1
OIL COOLER FAN
BRACKET
NAS6604−7 BOLT
(NOTE 1)
369F5193−1 SHIM
NAS6604−6 BOLT
(NOTE 1)
369F5137−1
PULLEY DRIVER
369F5155−1
INPUT COUPLING SHIM
369F5138−1
PULLEY GUARD
369F5160−1 BOLT
(NOTE 4)
359F5133−1 COUPLING
CSP102−012C
TRANSMISSION
INPUT COUPLING
INTERNAL
WRENCHING BOLT
0.010 IN. (0.254 MM) MINIMUM
(BETWEEN END OF SHAFT AND BOLT
SEATING ON SURFACE ON COUPLING)
Figure 406. Oil Cooler Blower Installation (369F5100 Transmission)
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
63−21−00
Page 601
Revision 41
MAIN TRANSMISSION LUBRICATION
AND COOLING SYSTEM
INSPECTION/CHECK
1. Lubrication System Inspection
(Ref. Figure 601)
(1). Inspect plumbing and system compo-
nents from oil cooler to lubrication
pump for leaks, secure attachment and
damage.
(2). Inspect oil cooler, lubrication pump, oil
filter, oil pressure switch, liquid level
plug, and chip detectors for leaks,
secure attachment and damage.
(3). Inspect electrical connections at oil
temperature switch, oil pressure
switch, and chip detectors for absence
of corrosion, secure attachment and
damage.
2. Cooling Blower Inspection
(Ref. Figure 405)
(1). Remove blower access door and inspect
belt for damage or excessive wear. Belt
should be fully seated in pulley grooves.
Limited cracking or separation of belt.
(a). Belt should be fully seated in pulley
grooves.
(b). Limited cracking or separation of belt
between pulley grooves is acceptable.
Visually monitor any propagation.
Belt should be replaced if any one
separation exceeds three inches in
length or if total separation exceeds
50 percent of peripheral length of
belt. (For belt replacement schedule,
refer to Section 05−10−00).
(2). Check belt tension.
(3). Hand−rotate main rotor to examine all
visible areas of driven pulley and driver
pulley for damage or excessive wear.
Listen for sounds of defective bearings
or of impeller touching scroll while
rotor is turned.
(4). Examine scroll for cracks or breaks,
and for secure attachment to hub.
(5). Examine rubber connectors at engine
oil cooler duct and transmission oil
cooler duct where they attach to scroll.
Examine ducts for damage.
(6). Look through hub support legs and, to
extent possible, inspect impeller for
damage. A crack, loose rivet or distorted vane is cause for impeller
replacement. Inspect mount screws and
bolts for evidence of broken slippage
mark paint.
(7). Examine scroll drain tube for damage,
secure attachment and clear passage.
(8). Examine mounting bracket and fan
mounting bracket for secure attachment. Check for broken lockwire at bolt
heads securing mounting bracket
cooling blower assembly.
3. Cooling Blower Inspection
(Disassembled)
Consumable Materials
(Ref. Section 91−00−00)
Item
Nomenclature
CM206 Chemical coating
CM318 Primer
CM801 Abrasive paper, silicon carbide
(1). Examine belt for damage or excessive
wear (Ref. Figure 405).
(2). Examine driver pulley, spring pin,
pulley guard and driven pulley for
damage or excessive wear.
(3). Check driven pulley retaining nut for a
minimum of 160 inch−pounds (18.08
Nm) plus drag torque. If loss of
torque is indicated, remove pulley nut
and inspect washer for evidence of
elongation and wear.
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 602
Revision 36
63−21−00
OIL PRESSURE
SENDER
MAIN TRANSMISSION
LUBRICATION PUMP
AND OIL FILTER
OIL TEMPERATURE
SENDER
GROUND WIRE
OIL COOLER
BYPASS VALVE
CHIP DETECTORS
OIL COOLER BLOWER
TRANSMISSION OIL
COOLER DUCTS
OIL COOLER
OIL LEVEL PLUG
VIEWED FROM RH SIDE OF
MAIN TRANSMISSION
NOTE 1
DRAIN CAP
G63−2007A
NOTE
:
DRAIN CAP INSTALLED AT THIS LOCATION
(EARLY CONFIGURATION ONLY)
Figure 601. Main Transmission Cooling Blower and Duct
(4). Check pulley shaft and splines for
condition. Replace damaged flat washer
or ring washer with flat washer. Install
and torque nut to 160 − 190 inch−
pounds (18.08 − 21.47 Nm) plus drag
torque.
(5). Examine mounting bracket and fan
mounting bracket for cracks and
breaks.
(6). Examine web of mounting bracket for
wear.
(a). Remove nicks, scratches or grooves
leaving sharp impressions in web.
Minimum acceptable web thickness:
0.125 inch (3.175 mm).
(b). Replace mounting bracket if web does
not meet 0.125 inch (3.175 mm)
minimum after repair.
(7). Examine scroll (Ref. Figure 801) for
cracks, breaks and distortion.
Handle impeller carefully to
prevent damage that could
cause imbalance and require replacement of
impeller.
(8). Visually (minimum 10X magnification)
examine impeller (Ref. Figure 801) for
cracks, deformation and separation.
(a). Look for foreign material attached to
impeller. None is permitted.
(b). Check for loose rivets at hub.
(c). Use electroprobe or gage of equiva-
lent accuracy to measure depth of
scratches or nicks.
(d). Use penetrating dye to examine
suspected cracks.
CAUTION
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
64−25−30
Page 401
Revision 41
ANTI−TORQUE FAN
REMOVAL/INSTALLATION
1. Anti−Torque Fan Assembly
The purpose of the fan is to provide anti−torque control using a variable flow of air, across
variable pitch blades, down the tailboom. The
anti−torque fan liner, felt metal seal, provides
a controlled gap between the fan and the felt
metal seal for optimum efficiency of the fan
during flight.
NOTE: The NOTARr anti−torque control sys-
tem must be re−rigged immediately after replacement of any component, control rods,
or linkages, and if helicopter operation reveals a rigging deficiency.
2. Anti−Torque Fan Replacement
(Ref. Figure 401 and Figure 402)
Special Tools
(Ref. Section 91−00−00)
Item
Nomenclature
ST605 Fan nut socket
A. Anti−Torque Fan Removal
(1). Remove tailboom (Ref. Sec. 53−40−30).
(2). Remove nut and lock washer from aft
tube assembly.
(3). Remove fan pitch control tube (Ref. Sec.
67−20−30, Fan Pitch Control Tube
Removal).
(4). Remove six bolts, washers and pitch
control housing from fan.
(5). Remove lock washer from nut and shaft
by releasing the holding tangs from lock
nut and pull locking ring from support
shaft knurl.
(6). Remove locknut in a counter−clockwise
direction, using coupling socket (ST605)
and coupling holding fixture tool.
(7). Remove washer from shaft.
(8). Remove fan from helicopter.
B. Anti−Torque Fan Installation
Consumable Materials
(Ref. Section 91−00−00)
Item
Nomenclature
CM702 Lockwire CRES
(1). Align and install fan assembly on
support shaft.
(2). Install washer on shaft.
(3). Install locknut and torque nut to 40 −
42 foot−pounds (54 − 57 Nm). Install
lock washer.
(4). Install pitch bearing housing using six
bolts and washers, Torque bolts to 80 −
100 inch−pounds (9.04 − 11.30 Nm)
and lockwire (CM702).
(5). Install fan pitch control tube (Ref. Sec.
67−20−30, Fan Pitch Control Tube
Installation).
(6). Install tailboom (Ref. Sec. 53−40−30).
3. Anti−Torque Fan Blade Replacement
(Ref. Figure 401)
NOTE: When a blade needs replacement for
any reason, whether it be service related or
at overhaul, replace associated bolt, washer,
and nut.
A. Anti−Torque Fan Blade Removal
(1). Remove anti−torque fan from helicopter
(Ref. Anti−Torque Fan Removal).
(2). Remove fan blade from strap assembly
by removing cotter pin, washer and pin.
B. Anti−Torque Fan Blade Installation
(1). Install fan blade and align retention
hole with upper strap assembly retention hole.
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 402
Revision 41
64−25−30
PITCH PLATE
NUT
WASHE
R
COTTER PIN
WASHER
PIN
RETENTION PLATES
FAN HUB
WASHER
(COUNTERSUNK)
(NOTE 2)
BOLT
BLADE
ASSY
STRAP ASSY
STUD
NUT
WASHER
COLLAR
HUB − BLADE
BUSHING
PITCH HORN
G64−2005B
NOTE
:
1. INSTALL STRAP WITH SERIAL NUMBER FACING AFT DIRECTION.
2. INSTALL WASHER WITH COUNTERSINK AGAINST BOLT−HEAD.
(NOTE 1)
SHELTON CT.USA 11/04
S/N LK1014 OO7
MDHC P/N 500N5311−5
EXPIRATION DATE XX/XX
EXAMPLE OF INK MARK DATE.
VIEW LOOKING
FORWARD
Figure 401. Anti−Torque Fan
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
64−25−30
Page 403
Revision 41
(2). Install pin, washer and cotter pin.
(3). Reinstall anti−torque fan in helicopter
(Ref. Anti−Torque Fan Installation).
(4). Perform fan balance check (Ref. Sec.
18−20−30, Fan Balance Check).
Consumable Materials
(Ref. Section 91−00−00)
Item
Nomenclature
CM312 Ink stamp, permanent
4. Fan Blade Strap and Pitch Horn
Replacement
(Ref. Figure 401) Remove and install the pitch
horn and strap assembly using the following
procedures.
NOTE:
D The following procedure covers the indi-
vidual removal of one strap assembly and
pitch horn. If disassembly of all is required, use the following steps for each
one requiring removal.
D When strap is replaced, replace related
bolt, washer, and nut.
A. Fan Blade Strap and Pitch Horn
Disassembly
(1). Remove anti−torque fan from helicopter
(Ref. Anti−Torque Fan Removal).
(2). Remove fan blade(s) (Ref. Anti−Torque
Fan Blade Replacement).
(3). Remove bolt and washer retaining
bottom half of strap assembly between
two retention plates.
(4). Remove strap assembly thru top hole of
fan hub.
(5). Remove pitch horn from fan hub.
B. Fan Blade Strap and Pitch Horn
Reassembly
NOTE: Counterweights on pitch arms are set
by the factory; do not attempt to adjust.
(1). Install pitch horn in fan assembly.
Ensure ball on lower side of pitch horn
is inserted in bushing of pitch plate.
NOTE: Inspect strap assembly for condition
and expiration date. Pay particular attention to area around the two spools. Inspect
for cracks in the polyurethane coating. If
any cuts or breaks are found that exceed
0.020 inch (0.508 mm) in depth or 0.25 inch
(6.35 mm) in length, replace the strap.
D Tension−torsion straps have a life limit
that starts when their package is opened.
D Tension−torsion straps can be put back in
their package, and life limit not started, if
no out of the package more than five days.
(2). If tension−torsion strap is removed
from package for no more than five
days, do the steps that follow:
(a). Replace desiccant in package, use
desiccant (CM826).
NOTE: If you can not seal package; put, ten-
sion−torsion strap, package, and desiccant
(CM826) in new plastic bag.
(b). Put tension−torsion strap in package
and seal package opening with tape.
(c). Put package in box and seal box with
tape.
(3). If replacement strap is new, remove
from package and write the words
EXPIRATION DATE on the strap face
and date five years after the package is
opened. Use permanent ink (CM312).
(4). Make an item component record card
for each tension−torsion strap.
NOTE: Install tension−torsion straps so that
the cure date is in view when fan is assembled.
(5). Insert strap assembly thru top of fan
hub and pitch horn until lower (smaller
diameter) hole is aligned between holes
of two retention plates.
(6). Install blade and align spar before
torquing inboard nut, this ensures
proper alignment of strap with blade.
(7). Install new
bolt, washers (countersunk
washer against bolt−head), and nut
thru holes of retention plates and of
strap assembly.
(8). Install fan blade(s) and torque bolts to
100 inch−pounds (11.30 Nm) (Ref.
Anti−Torque Fan Blade Installation).
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 404
Revision 41
64−25−30
(9). Reinstall anti−torque fan in helicopter
(Ref. Anti−Torque Fan Replacement).
(10). Perform fan balance (Ref. Sec.
18−20−30, Fan Balance Check).
5. Retention Plate and Pitch Plate
Replacement
(Ref. Figure 401) Remove and install the
retention strap and pitch plate using the
following procedures.
A. Retention Plate and Pitch Plate
Disassembly
(1). Remove anti−torque fan from helicopter
(Ref. Anti−Torque Fan Removal).
(2). Remove fan blades (Ref. Anti−Torque
Fan Blade Replacement).
(3). Remove strap assemblies and pitch
horns.
(4). Remove pitch plate and retention plates
from fan hub.
B. Retention Plate and Pitch Plate
Reassembly
(1). Position retention plates in fan hub.
NOTE: Install tension−torsion straps so that
the cure date is in view when fan is assembled.
(2). Install pitch horn and strap assemblies
(Ref. Strap and Pitch Horn Reassembly).
(3). Place pitch plate over retention plates
within fan hub.
(4). Install fan blades (Ref. Anti−Torque
Fan Blade Installation).
(5). Reinstall anti−torque fan in helicopter
(Ref. Anti−Torque Fan Installation).
6. Support Shaft Replacement
(Ref. Figure 402) Remove and install the
support shaft using the following procedures.
NOTE: When replacing pitch plate and/or sup-
port shaft bearings, do not use 900R bearings in the 500/600N helicopters.
A. Support Shaft Disassembly
(1). Remove anti−torque fan from helicopter
(Ref. Anti−Torque Fan Removal).
(2). Remove fan pitch control tube (Ref. Sec.
67−20−30).
(3). Remove fan interconnect driveshaft
(Ref. Sec. 63−15−30).
(4). Remove fan interconnect shaft coupling
from support shaft (Ref. Sec. 63−15−30).
(5). Remove support shaft and fan hub
housing from fan support assembly by
removing four cotter pins, nuts,
washers and bolts.
(6). Remove hub spacer from shaft.
(7). Remove bearing retainer from support
housing.
(8). Press shaft and fan support bearing out
of support housing.
NOTE: Removal of bearing seal at disassembly
is not required unless seals need replacement.
(9). Remove bearing seal from support
housing and bearing retainer.
(10). Press bearing off support shaft using
removal ring.
B. Support Shaft Reassembly
Consumable Materials
(Ref. Section 91−00−00)
Item
Nomenclature
CM111 Grease, aircraft
CM425 Sealing compound
(1). Install removal ring on support shaft
until firmly seated against shoulder of
support shaft.
(2). Install support bearing on support
shaft.
(3). Install bearing seal in support housing
and bearing retainer using sealant
(CM425).
(4). Fill seal cavity with 3.3−4.0 CCs of
grease (CM111).
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
64−25−30
Page 405
Revision 41
(5). Install support bearing and shaft in
support housing.
(6). Install bearing retainer and align bolt
holes on support housing.
(7). Install hub spacer on shaft.
(8). Install support shaft and housing on
fan support assembly. using four bolts,
washers, and nuts. Torque nuts to 40 −
50 inch−pounds (4.52 − 5.65 Nm).
Install cotter keys.
(9). Install fan interconnect shaft coupling
on support shaft (Ref. Sec. 63−15−30).
(10). Install fan interconnect driveshaft (Ref.
Sec. 63−15−30).
(11). Install fan pitch control tube (Ref. Sec.
67−20−30).
(12). Install anti−torque fan on helicopter
(Ref. Anti−Torque Fan Installation).
(13). Check fan balance (Ref Sec. 18−00−30,
Fan Balance Check).
7. Fan Balance Stud Replacement
A. Fan Balance Stud Removal
The following procedure is for removal of the
balance studs when the lock collars have
become loose and allow the stud to rotate.
(1). Removal with Pneumatic Tool
: Pneumatic tools may be used only on
fasteners in interference fit holes and
fasteners with aluminum collars.
(a). Select the applicable removal tool. Fit
removal tool to a 0.375 inch (9.525
mm) square socket drive that will fit
a reversible screwdriver motor.
(b). Place the collar removal tool over the
collar and press firmly.
(c). Rotate the tool counterclockwise by
hand until the teeth bite into the
collar.
(d). Place the motor on the drive socket
and unscrew the collar using reverse
drive.
(e). Tap out the pin with a nonmetallic−
faced mallet.
(2). Removal with Hand Tool
:
(a). Insert the applicable size hex wrench
into the pin wrenching cavity and
hold securely to prevent pin rotation.
(b). Rotate the collar counterclockwise
with pliers or vise grips to remove.
(c). Tap out pin with a nonmetallic−faced
mallet.
B. Fan Balance Stud Installation
Pins may be reused, provided the finish has
not been marred and the threads and wrenching cavity are in acceptable condition.
Consumable Materials
(Ref. Section 91−00−00)
Item
Nomenclature
CM409 Adhesive, epoxy
(1). Apply adhesive (CM409) to pin and
insert, while wet, using a nonmetallic−
faced mallet or rivet set into hole.
Ensure Pin is seated flush against fan
hub.
(2). Manually screw the collar onto the pin
a minimum of two threads.
(3). Installation with Pneumatic Tool
:
(a). Insert the hex wrench tip of the
power driver into the wrenching
cavity in the pin
(b). Press the power driver socket firmly
against the collar and actuate the
driver until the collar wrenching
device is torqued off.
(c). Withdraw the hex wrench tip from
the wrenching cavity and discard the
wrenching collar.
(4). Installation with hand tool
:
(a). Press socket from hand tool firmly
onto collar.
(b). Insert hex wrench though center of
tool and hold pin to prevent it from
rotating.
(c). Turn socket clockwise, while holding
hex wrench, until collar is firmly
seated against fan hub; wrenching
collar will torque off when proper
torque is reached. Discard wrenching
collar.
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 406
Revision 41
64−25−30
BEARING
SEAL
AFT CONTROL TUBE
(REF)
SUPPORT SHAFT
COTTER KEY
NUT
WASHER
FAN SUPPORT ASSEMBLY
(REF)
BEARING
HOUSING
RING
FAN SUPPORT
BEARING
BEARING
RETAINER
WASHER
BOLT
FAN
(REF)
LOCKWASHER
LOCKNUT
WASHER
BOLT
BEARING
SEAL
HUB
SPACER
PITCH BEARING
HOUSING
PITCH
SLIDER
INNER BEARING
RETAINER
PITCH BEARING
PLATE
PITCH BEARING
RETAINER
WASHER
BOLT
NUT
LOCKWASHER
G64−2006A
WASHER
Figure 402. Anti−Torque Fan Support Shaft
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
64−25−30
Page 407
Revision 41
8. Pitch Horn Counterweight Set Screw
Replacement
(Ref. Figure 403) If, during fan inspection, a
counterweight is found to be loose, the set
screw must be replaced.
Consumable Materials
(Ref. Section 91−00−00)
Item
Nomenclature
CM216 Loctite remover
CM321 Surface primer locking compound
(1). Apply heat to loose counterweight.
(2). Remove and discard set screw.
(3). Remove retaining ring and washer.
(4). Inspect threads in counterweight for
condition and cleanliness.
(5). Clean pitch horn threads with Loctite
remover (CM216).
(6). Apply grade T primer (CM321) to
threads of new set screw; allow to dry
for 30 minutes at ambient temperature.
NOTE: Ensure counterweight−to−pitch horn
index mark aligns correctly. All counterweights are indexed the same.
(7). Align index mark on counterweight to
match with mark on pitch horn and
install into pitch horn.
(8). Apply grade B locking compound
(CM321) to threads of set screw and
install into pitch horn. Tighten set
screw.
PITCH HORN
INDEX MARKS
COUNTERWEIGHT
PITCH HORN
COUNTERWEIGHT
INDEX MARK
SET SCREW
G64−2011
Figure 403. Pitch Horn Counterweight Set
Screw Replacement
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 408
Revision 34
64−25−30
This Page Intentionally Left Blank
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
91−00−00
Page 3
Revision 36
Table 1. Consumable Materials (Cont.)
Item
No.
Vendor
(Table 2)
Commercial Name/No. (2)
Specification No. (1)
Type Class Grade
Material
CM126 Oil, turbine (4) (5) MIL−L (PRF)−23699 (3)
CM127 Grease, YSAS Actuator 168043 MS90
Solvents, Cleaners and Corrosion Preventative Compounds
CM201 Protective coating MIL−C (PRF)−6799
1
(3)
CM202 Metal protector, aerosol Molykote MS22
CM203 Potting compound MIL−S (PRF)−8516G MS77
CM204 Compound, corrosion preventa-
tive
MIL−C (PRF)−16173E
3 . . . . . . . . . . . . . .
4. . . . . . . . . . . . . .
Braycote MS10
MS13
MS88
CM205 Dielectric compound DC−4 MS22
CM206 Chemical coating MIL−C−5541 Iridite 14−2
Al−Coat
Alodine 1201
MS67
MS85
CM207 Chromic acid solution (pH 2.6 to
3.4, magnesium touchup)
Dow #19 or equivalent MS22
CM208 Barrier material (grease−proof) MIL−B (PRF)−121G
12A. . . . . . . . . .
MIL−B (PRF)−131L
1. . . . . . .
(3)
CM209 Putty, general purpose MIL−P (PRF)−8116 Compound 3998 MS32
CM210 Corrosive preventive (aircraft
gas turbine, synthetic base)
MIL−C (PRF)−8188 (3)
CM211 Solvent 3339 MS82
CM212 Releasing agent TC7−527 MS26
CM213 Releasing agent 225 MS64
CM214 Releasing agent MIL−P (PRF)−23377
HMS 20−1245
MS14
MS17
CM215 Parting agent Slip−Spray
Fre−Kote 33
MS24
MS31
CM216 Loctite remover (for disas-
sembled parts)
Oakite 156 MS17
MS57
MS74
CM217 Isopropyl alcohol TT−I−735 (3)
CM218 Alcohol, denatured O−E−760
1
(3)
CM219 Methyl−ethyl−ketone TT−M−261 (3)
CM220 Naphtha aliphatic TT−N−95
2
(3)
CM221 Xylene (3)
CM222 1,1,1−Trichloroethane O−T−620 (3)
CM223
Acetone O−A−51 (3)
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 4
Revision 41
91−00−00
Table 1. Consumable Materials (Cont.)
Item
No.
Vendor
(Table 2)
Commercial Name/No. (2)
Specification No. (1)
Type Class Grade
Material
CM224 Soap paste P−S−560 (3)
CM225 Detergent, general purpose MIL−O−16791 (3)
CM226 Cleaning compound, alkaline
waterbase
MIL−C−25769 (3)
CM227 Washing compound with wax Turtle Zip Wax (3)
CM228 Surface cleaner (pre−paint solu-
tion with phosphoric acid base)
TT−C−490
MIL−C−10578
2
WO#1 MS79
CM229 Paint remover (acid−type for
epoxy)
TT−R−25134 MS79
CM230 Paint remover (solvent−type) MIL−R−25314 (3)
CM231 Plastic bead, spherical 20 − 30
mesh
Poly Plus 20/30 (8) MS1
MS2
MS61
CM232 Rust inhibitor spray WD−40 MS68
CM233 Rust inhibitor spray LPS3 MS46
CM234 Solvent, dry−cleaning P−D−680 (3)
CM235 Cleaner Desoclean 45 MS17
Paints (9), Primers and Coating Compounds
CM301 Pre−treatment MIL−P−15328 (3)
CM302 Epoxy primer /
Catalyst reducer
1−1G−69 /
1−1H−75
MS3
CM303 Wash primer MIL−C−8514 (3)
CM304 Enamel, epoxy
(Fed−Std−595)
MDM 15−1100
2
Black #37038
White #37769
Tan #20318
Parchment #20371
Red #11958
Green #34151
Gray #36231
Yellow #13655
(3)
CM305 Lacquer, acrylic
(Fed−Std−595)
MDM 15−1083 Black #17038
Black #37038
Parchment #20371
Green #34151
Blue #15102
Blue #35044
Brown #30140
(3)
CM306 Lacquer, clear (aluminum clad
alloy surfaces)
MIL−L−6066 (3)
CM307 Lacquer, acrylic semi−gloss HMS 15−1083 (3)
CM308 Lacquer, blue FED−STD−15102 (3)
CM309
Lacquer, green TT−L−32 (3)
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
91−00−00
Page 5
Revision 41
Table 1. Consumable Materials (Cont.)
Item
No.
Vendor
(Table 2)
Commercial Name/No. (2)
Specification No. (1)
Type Class Grade
Material
CM310 Enamel, lusterless TT−E−527 (3)
CM311 Coating, logo white /
Thinner
Q−881 (Color No. 484) /
T−80695
(3)
CM312
Ink stamp, permanent MIL−M−43719
TT−I−558
(3)
Ink, marking, stencil A−A−208 Type 1, color
number 37038
(3)
Fine tip permanent marker Sharpie (3)
CM313 Insulation varnish Glyptal 1201 MS33
CM314 Varnish, moisture resistant MIL−V−173
2
(3)
CM315 Adhesive primer (liquid primer) HMS 16−1069
1. . . . . . .
MS50
CM316 Epoxy coating /
Thinner
Poly−EP MS19
CM317 Resin primer /
Thinner (paint base for polycarbonate plastic)
Q−881 /
T−80679
MS11
CM318 Primer MIL−P−85582
1C2. . . . .
(3)
CM319 Barrier material, grease−proof MIL−B−121
12A . . . . . . . . . .
MIL−B−131
1. . . . . . .
(3)
CM320 Thinner, lacquer (acrylin−nitro-
cellulose)
MIL−T−19544 Prepsol
(DuPont 3919)
MS24
CM321 Surface primer locking com-
pound (single component, grade
as noted)
MIL−S−22473 Locquic MS45
CM322 Primer, Silicone, Red Dow Corning 1200 MS43
CM323 Primer MIL−P−23377
1C. . . . .
(3)
Adhesives, Cements and Sealants
CM401 Adhesive Stabond G−304 MS75
CM402 Adhesive MDM 16−1068
11. . . . . . .
EA9323
EA956
MS21
CM403 Adhesive Epon 919 MS72
CM404 Adhesive, epoxy (non−structural) HMS 16−1147
2. . . . . . .
EC2216B/A
Scotch Weld
MS86
CM405 Adhesive HMS 16−1149 C−111 MS75
CM406 Adhesive U−136
(AC−AAAA)
MS75
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 6
Revision 41
91−00−00
Table 1. Consumable Materials (Cont.)
Item
No.
Vendor
(Table 2)
Commercial Name/No. (2)
Specification No. (1)
Type Class Grade
Material
CM407 Adhesive /
Primer /
Catalyst
A−4000 /
A−4004 /
xy22
MS22
CM408 Adhesive, silicone rubber Silastic 140 MS22
CM409 Adhesive, epoxy MDM 16−1068
1. . . . . . .
EA9330.3 MS21
CM410 Adhesive, epoxy MDM 16−1068
7. . . . . . .
EA9309.3 MS21
CM411 Adhesive, epoxy (non−structural) MIL−A−52194
MDM 16−1068
2. . . . . . .
Scotch−Weld EC1838
A1177B
MS86
MS12
CM412 Adhesive, bonding, vulcanized
(synthetic rubber−to−steel)
MIL−A−1154 MS86
CM413 Not used at this time
CM414 Adhesive, cyanoacrylic /
Accelerator
MIL−A−46050 3CI−1000 /
Super Drop Accelerator
MS21
CM415 Cement MIL−A−8576B PS−18
S147
MS69
CM416 Cement #2210 MS86
CM417 Cement HMS 16−1149
21. . . . .
Grip MS38
CM418 Cement, epoxy HMS 16−1149
22. . . . .
EC1300L MS86
CM419 Sealer MDM 16−1068
2. . . . . . .
A1177B MS12
CM420 Sealant MIL−S−81733 PR−1431 Type IV
PR1436G Type II
PR1436GB−2
MS62
CM421 Sealant Anchor Weld #220 MS58
CM422 Sealant #5220 MS30
CM423 Sealant RTV106 (2)
MS34
CM424 Sealing compound HT−4 MS75
CM425 Sealing compound
(fuel resistant)
HMS 16−1097
1 B2 . . . . .
MIL−S−8802
Pro−Seal 890 MS62
CM426 Sealing compound MIL−S−8516
2. . . . . . .
3C−3007 MS14
CM427 Sealing compound MIL−S−8516
1 2 A1/2. . . . . . . . . .
PR1422 MS62
CM428 Sealing compound MIL−S−8516
12. . . . .
RTV730
Silastic 730
MS22
MS34
CM429
Sealing compound, silicone RTV11 MS34
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
91−00−00
Page 7
Revision 41
Table 1. Consumable Materials (Cont.)
Item
No.
Vendor
(Table 2)
Commercial Name/No. (2)
Specification No. (1)
Type Class Grade
Material
CM430 Sealant, solvent resistant MIL−S−8660B RTV732
Silastic 732
RTV 157
MS22
MS34
CM431 Sealing, locking and retaining
compound (single component,
grade as noted)
MIL−S−22473
MIL−R−46082
Loctite #85 or
RC/609
MS45
MS60
CM432 Dichloromethane (methylene
chloride)
MIL−D−6998 (3)
CM433 Ethylene chloride (ethylene dich-
loride, EDC)
MIL−E−10662 (3)
CM434 Thread sealant P412 MS60
CM435 Tetrahydrofuran (THF) MS51
CM436 Plastic steel Devcon A MS20
CM437 Sealing compound Permabond 102
Loctite 414
MS43
MS60
MS45
MS87
CM438 Adhesive, Epoxy HMS16−1068
12. . . . . . .
EA9321 MS21
CM439 Adhesive HMS16−1149
5
MS75
CM440 Sealant, electrically conductive MDM16−1261 Cho−bond 2165 MS91
Composite Materials
CM501 Fiberglass cloth (0.022, 2 ply) SAE−AMS−C−9084
No. 181
(3)
CM502 Sleeving, fiberglass (No. 4, 0.214
in. ID x 4.0 in.)
MIL−I−3190
HA−1. . . . . . .
(3)
CM503 Fiberglass repair kit Cordokit RK−10 MS29
CM504 Epoxy resin with catalyst (low
pressure laminating)
MIL−R−9300
1
(3)
CM505 Polyester laminating resin MIL−R−7575 (3)
CM506 Resin, fiberglass Epon 828 MS72
CM507 Resin, filler Epon 960F MS72
CM508 Resin, filler #RP1257−3 MS66
Rubber Material
CM601 Insulation sleeving, electrical
(vinyl tubing; size as notes)
MIL−I−631
F1A . . . . . . . . . .
Form U, Category 1
(3)
CM602 Insulation sleeving, electrical, fi-
berglass (size as notes)
MIL−I−3190 (3)
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 8
Revision 41
91−00−00
Table 1. Consumable Materials (Cont.)
Item
No.
Vendor
(Table 2)
Commercial Name/No. (2)
Specification No. (1)
Type Class Grade
Material
CM603 Patching material (inside/out-
side)
#5200/5187/5194 MS82
CM604 Patching material (outside only) #5218 or #5241/5241 MS82
CM605 Fuel cell repair kit RK3CL MS82
CM606 Rubber cement MIL−A−5092 (3)
CM607 Cement MIL−S−9117 EC−678 MS82
CM608 Cement Uniroyal #3230 MS80
CM609 Repair kit (non−self− sealing
cell)
Uniroyal #RK−10−34 MS80
CM610 Patch material (self− sealing cell,
exterior)
Uniroyal #5241/5241 sandwich
MS80
CM611 Tubing, vinyl clear PVC tubing, 2 GA, clear
105C
MS71
CM612 Tube, silicone No. 4 (H.A.I.) MS83
CM613 Sleeve, vinyl No. 2 Resinite MS13
CM614 Sleeving, heat−shrink (class,
type or diameter as noted)
MIL−I−23053 RNF100X3/8
RNF100X1/2
RNF100 .125 ID
MS65
Lockwire, Fasteners and Tape
CM701 Lockwire CRES MS20995C20 (3)
CM702 Lockwire CRES MS20995C32 (3)
CM703 Tie strap (size as noted) MS3367−*−* MS78
CM704 Tie strap, nylon MS17821−1−9 TY−RAP (3)
CM705 Tie, cable SST2 MS18
CM706 Tie strap base TC112 MS78
CM707 Tape, fastener (nylon hook and
pile)
Velcro (3)
CM708 Tape #850 MS86
CM709 Tape CT93C MS42
CM710 Tape, high temperature (thick-
ness as noted)
Temp−R MS16
MS39
CM711 Tape, pressure sensitive (water-
proof for packaging and sealing,
width and thickness as noted)
PPP−T−60
11. . . . .
MS60
MS86
CM712 Tape, pressure sensitive (width
as noted)
#41 MS86
CM713 Tape, pressure sensitive #471 MS86
CM714 Tape, pressure sensitive (width
as noted)
#4104 MS86
CM715
Tape, pressure sensitive (width
as noted)
#4508 MS86
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
91−00−00
Page 9
Revision 41
Table 1. Consumable Materials (Cont.)
Item
No.
Vendor
(Table 2)
Commercial Name/No. (2)
Specification No. (1)
Type Class Grade
Material
CM716 Tape, pressure sensitive (adhe-
sive, filament reinforced)
PPP−T−97 (3)
CM717 Tape, pressure sensitive, (poly-
urethane, width as noted)
#Y8560 MS86
CM718 Tape, double−faced E−706 MS8
CM719 Tape, vinyl plastic #330 MS76
CM720 Tape and activator, vinyl Scotch Cal #45
Scotch Tite A−2
MS86
CM721 Tape, aluminum foil #425 MS86
CM722 Tape, polyethylene #483 MS86
CM723 Tape, nitrile rubber NE−71−A MS7
CM724 Tape, non−slip (pressure sensi-
tive, medium grade, black)
P−D−00455 (3)
CM725 Tape, electrical, plastic MIL−I−7798 #33 MS86
CM726 Tape teflon #520
#48
MS60
MS86
CM727 Tape, foam (adhesive backing) 4104Y
92772
MS86
CM728 Tape, pressure sensitive (sponge
rubber)
4504
Scotchfoam tape
MS86
CM729 Tape, masking, pressure sensi-
tive
UU−T−106 #216
(High Temp)
MS86
CM730 Tape, duct (3)
CM731 Lockwire CRES MS20995C15 (3)
Miscellaneous Materials
CM801 Abrasive paper, silicon carbide
(grade as noted)
P−P−101 (3)
CM802 Abrasive cloth, aluminum oxide
(grade as noted)
P−C−451 (3)
CM803 Crocus cloth P−C−458 (3)
CM804 Emery cloth, fine (3)
CM805 Dye penetrant kit MIL−I−25135 MS6
MS48
CM806 Micro−Mesh plastic restoration
kit
5350−01−290−4002 Micro−Mesh Kit KR−70 MS52
CM807 Twine, nylon MIL−T−713 (3)
CM808 Lacing cord (high temperature) Type T−3333 MS84
CM809 Nylon cord (lacing) MIL−C−5040 (3)
CM810 Leak detector, liquid MIL−L−25567C Leak−Tec MS4
CM811 Leak detector, liquid Snoop MS56
CM812
Splice, knife 32445 MS5
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 10
Revision 41
91−00−00
Table 1. Consumable Materials (Cont.)
Item
No.
Vendor
(Table 2)
Commercial Name/No. (2)
Specification No. (1)
Type Class Grade
Material
CM813 Wire MS22759/34−22−9 (3)
CM814 Dykem, red or blue DX−296 MS23
MS40
MS49
CM815 Solder (tin alloy, rosin core) QQ−S−571
SN60WRP2
(3)
CM816 Solder (tin alloy, acid core) QQ−S−571 (3)
CM817 Brazing flux (paste) O−F−499 (3)
CM818 Brazing alloy (silver base) MS86
CM819 Kimwipe (3)
CM820 Cheesecloth (3)
CM821 Gasket material (adhesive one
side only)
Scotchfoam #4304 MS86
CM822 Acetylene, technical grade BB−A−106 (3)
CM823 Oxygen, industrial grade BB−O−925
1B. . . . . . . . . . . .
(3)
CM824 Welding rod (corrosion and heat
resistant alloys, class or type as
noted)
AMS 5656, AWS A5.9,
ER219
21−6−9 (Nitronic 40) (3)
CM825 Welding rod QQ−R−566
CLFS RA12 or
RA143 (04043)
5% silicon
(3)
CM826
Desiccant MIL−D−3464 Type I
or II
Desiccant (3)
NOTES:
(1) Numbers are U.S. Specifications and Standards. Prefix symbols are specified as follows:
AMS − American Materials Standards;
MS − Military Standards;
MIL − Military Specification; Single, Double or Triple alpha prefix of the same letter − Federal Specification;
AN − Air Force/Navy Aeronautical Standard;
NAS − National Aerospace Standard.
(2) Primary selection. All equivalent material can be used as a different selection. Time increments on
manufacturers instructions must be adhered to, unless given differently in a specific task.
(3) Use the best comparable grade material when conformity of available materials of same type with given
Specification Number cannot be found.
(4) Oils approved for use in 500/600N Series Helicopter main and fan transmission are synthetic compounds
having Ryder Gear Value in excess of 2500 pounds.
(5) For Model 250 Series engine oil change requirements and restrictions on mixing oils, refer to Allison
Operation and Maintenance Manual.
CAUTION
: Mixing of oils within an oil series not in the same group is permitted only in an emergency. Use
of mixed oils (oils not in the same group) in an engine is limited to five hours total running time. Adequate
maintenance records must be maintained to ensure that the five hour limit is not exceeded. Mixing of oils
from different series is not permitted.
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
91−00−00
Page 11
Revision 41
(6) Mobil oil SHC 626 can be formulated such that it may have two different colors. The oil can still be mixed
with no adverse affects.
(7) Use only Mobil SHC 626 oil in the 369F5450 overrunning clutch and 369F5100 main transmission.
(8) Do not use over 50 psig air pressure for abrasive cleaning method. Mask or shield threaded areas or
critical surfaces where damage may result from abrasive blasting.
(9) When ordering paint, give each paint by type (i.e. acrylic, epoxy, polyurethane); by color and AC part
number. Also include compatible HS or federal standard (FED−STD) number to make sure correct type and
color paint is supplied. The color code numbers for finish paints used on 500/600N Series Helicopters are
entered in helicopter log books before delivery of aircraft. When ordering paints, ensure AC Number and
SA Number are compatible.
Table 2. Manufacturer/Supplier Number
Number Name
MS1
Abrasive Cleaning Equipment
20122 State Rd.
Cerritos, CA 92701
MS2 Abrasives Unlimited
4653 S. 33rd St.
Phoenix, AZ 85040
(602) 276−0077
MS3 Advanced Coating and Chemicals
2213 N. Tyler
S. El Monte, CA 91733
MS4 American Gas and Chemical Co.
220A Pegasus Ave.
Northvale, NJ 07647 1904
(201) 767−7300
(800) 526−1008
MS5 AMP Co.
P.O. Box 55
Winston Salem, NC 27102
(336) 725−9222
(800) 522−6752
MS6 Ardrox Inc.
19 Woodburn Ave.
P.O. Box 814
St. Catherines, Ontario
Canada L2R 6Y3
(416) 684−1800
MS7 Armstrong Cork Co.
Lancaster, PA 17604
MS8 Arno Adhesive Tapes Inc.
Los Angeles, CA
MS9 Arthur Withrow
5511 District Blvd.
Los Angeles, CA 90040
Number Name
MS10
Tectyl Industrial Products A Div. Of
Ashland Inc.
3499 Dabney Dr.
Lexington, KY 40509
(859) 357−7534
MS11 Bee Chemical Co.
2700−T E. 170th St.
Lansing, IL 60438
(708) 474−7000
MS12 B.F. Goodrich Co.
500 S. Main St.
Akron, OH 44318
MS13 Castrol Industrial North America Inc.
1001− W. 31st St.
Downers Grove, IL 60515
(630) 241−4000
(800) 621−2661
MS14 Churchill Chemical Corp.
Los Angeles, CA
MS15 PRC−Desoto International, Inc.
5454 San Fernando Rd.
Glendale, CA 91203
(818) 240 2060
MS16 Connecticut Hard Rubber Co.
New Haven, CT
MS17 Crown Metro Inc
P.O. Box 5857
Greenville, SC 29606
(864) 299−1331
MS18 Danquit Corp.
Tinley Park, IL
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 12
Revision 41
91−00−00
Number Name
MS19
Detroit Graphite Co.
Detroit, MI
MS20 Devcon
30 Endicott St.
Danvers, MA 01923
(978) 777−1100
MS21 Dexter Adhesive & Coating Systems
2850 Willow Pass Rd.,
P.O. Box 312
Bay Point, CA 94565−0031
(925) 458−8000
(800) 424−9300
MS22 Dow Corning Corporation
P.O. Box 0994, South Saginaw Road
Midland, MI 48686
(800) 634−9660
MS23 ITW/Dykem
805 E. Old 56 Hwy.
Olathe, KS 6606
(800) 443−9536
MS24 Du Pont
Wilmington, DE 19898
(302) 774−1000
(800) 441−7515
MS25 E/M Corp.
100−T Cooper Circle
Peachtree City, GA 30269
(770) 261−4800
MS26 EPD Industries
2055 E. 223 St.
Long Beach, CA 90810
MS27 Everlube Corp.
North Hollywood, CA
MS28 Exxon Co.
P.O. Box 2380
Houston, TX 77001
MS29 Ferro Corp.
Composites Division
34 Smith St.
Norwalk, CT 06852
MS30 Fiber−Resin Corp
170 W Providencia Ave
Burbank, CA 91502
(800) 624−9487
MS31 Fre−Kote Inc.
Number Name
MS32
Fuller O’Brien Co.
S. San Francisco, CA
MS33 General Electric
Insulation Dept.
Schenectady, NY
MS34 General Electric Company
Silicone Products Business Division
260 Hudson River Rd.
Waterford, NY 12188
(518) 233−3330
MS35 GC Electronics
Los Angeles, CA
MS36 Harry Miller Corp.
4th & Bristol Sts.
Philadelphia, PA 19140
( 215) 324−4000
MS37 IKS American Corp.
Szumoto Seiko Division
1555 W. Rosecrans Ave.
Gardena, CA 90249
(800) 421−2761
MS38 Columbia Aluminum Products
7020 E. Slauson Ave.
Commerce, California 90040
(323) 728−7361
MS39 Insulectro Co.
1410 W. Olympic Blvd.
Los Angeles, CA
MS40 Irwin−Hobson Co.
Ninth and S.E. Woodward
Portland, OR 97202
MS41 Deleted − Not used at this time.
MS42 Jones Industrial Supply
Culver City, CA
MS43 K.R. Anderson
4316 E. University Dr.
Phoenix, AZ 85034
(602) 437−0030
MS44 Not used at this time
MS45 Loctite Inc.
1001 Trout Brook Crossing
Rocky Hill, CT 06067−3910
Phone: (860) 571−5100
FAX: (860) 571−5465
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
91−00−00
Page 13
Revision 41
Number Name
MS46
LPS Laboratories Inc.
4647 Hugh Howell Rd., Dept. M
Tucker, GA 30084
( 800) 241−8334
MS47 Lubriplate Div., Fiske Bros. Refining Co.
129−T Lockwood St.
Newark, NJ 07105
( 973) 589−9150
MS48 Magna Flux
11898−T Burnside Lane
Roscoe, IL 61073
( 815) 623−7634
MS49 Markall Products Co.
4772−T W. 139 St.
Cleveland, OH 44135
(216) 267−3235
MS50 MD Helicopters Inc.
4555 E. McDowell
Mesa, AZ 85215−9734
(480) 346−6377
(800) 388−3378
MS51 McKesson and Robbins
Chemical Dept.
Los Angeles, CA
MS52 Micro−Surface Finishing Products Inc.
1217 W. Third Street
P.O. Box 818
Wilton, IA 52778
(319) 732−3240
MS53 Miller−Stevenson Chemical Co.
1001 E. first St.
Los Angeles, CA
MS54 Mobil Oil Corp.
International Aviation Division
150 E. 42nd St.
New York, NY 10017
MS55 Rohm and Haas Company
100 Independence Mall West
Philadelphia, PA 19106−2399
(215) 592−3000
(215) 592−3377
MS56 Nupro Company
4800 East 345th Street
Willoughby, OH 44094 4460
(440) 951−7100
Number Name
MS57
Chemetall Oakite Products, Inc.
50 Valley Rd.
Berkeley Heights, NJ 07922 2712
(908) 464−6900
MS58 Pacific Upholstery
Gardena, CA
MS59 Parker−Hannifin
711 Taylor Street
P.O. Box 4032 Elyria, OH 44036
(440) 284−6300
MS60 Permabond International Corp.
480 S. Dean St.
Englewood, NJ 07631
(201) 567−9494
MS61 Polyrock Co.
4763 Murrita Ave.
Chino, CA 91710
MS62 Product Research and Chemical Co.
5426 San Fernando Rd.
Glendale, CA 91209
MS63 Product Techniques, Inc.
511 East 8th Pl.
Los Angeles, CA
MS64 Ram Chemical Co.
Gardena, CA
MS65 Raychem Corp.
305 Constitution Dr., Mailstop 103/2A
Menlo Park, CA 94025−1164
(800) 926−2425
(650) 361−3860
MS66 Ren Plastics Inc.
Lansing, MI 48910
MS67 Richardson Company
Allied−Kelite Products Division
2400 E. Devon Ave.
Des Plains, IL
MS68 Rocket Chemical Co. Inc.
San Diego, CA
MS69 Rohm and Haas Company
100 Independence Mall West
Philadelphia, PA 19106−2399
(215) 592−3000
(215) 592−3377
MS70 Royal Lubricants, Inc.
215 Merry Lane, P.O. Box 518
East Hanover, NJ 07936 0518
(800) 989−7692
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 14
Revision 41
91−00−00
Number Name
MS71
Sea Wire and Cable Inc.
P.O. Box 647
Madison, AL 35758
1−800−633−7210
MS72 Shell Chemical Co.
910 Louisiana St.
Houston, TX 77002
713−241−6161
MS73 Shell Oil Company
50 W. 50th. St.
New York, NY 10020
MS74 Sherwin Williams
MS75 Stabond Corp.
14010−T S. Western Ave.
Gardena, CA 90249
(310) 380−6168
MS76 Technical Tape Co.
363 Woodycrest Ave.
Nashville, TN 37210
(800) 714−8806
MS77 Thiokol
MS78 Thomas and Betts Co.
Elizabeth, NJ
MS79 Turco Products, Inc
Division of Atochem North America
2700 Temple Ave Suite B
Long Beach, CA 90806
(562) 981−8307
MS80 Uniroyal Inc.
Engineered Systems Dept.
Mishawaka, IN 46544
MS81 United−Erie Incorporated
438 Huron St.
Erie, PA 16502
(800) 377−7561
MS82 U.S. Rubber Co.
Fuel Container Dept.
Mishawaka, IN
Number Name
MS83
Varflex Corp.
512 W. Court St.
Rome, NY 13440
(315) 336−4400
MS84 Warren Wire Co.
MS85 Witco
Allied−Kelite Division
29111 Milford Rd.
New Hudson, MI 48165
(313) 437−8161
MS86 3M Co.
Bldg. 223−N
3M Center
St. Paul, MN 55144−1000
(612) 733−1110
(800) 362−3550
MS87 R.S, Hughes
2107 E. Magnolia
Phoenix, AZ 85034
(602) 275−5565
(602) 275−5025
MS88 Esgard Corrosion Coatings, PO Drawer
2698, Lafayette, LA 70502
(800) 888−2511
MS89 Hernon Mfg., Inc.
121−T Tech Dr.
Sanford, FL 32771 USA
(800) 527−0004
(407) 322−4000
MS90 Astronautics Corporation of America
4115 N. Teutonia Ave.
Milwaukee, WI, 53209
www.astronautics.com
Tel: (414) 449−4000
Fax: (414) 447−8231
MS91 Chomerics, Inc.
77 Dragon Court
Woburn, MA 01801
(781) 935−4850
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
91−00−00
Page 15
Revision 41
Table 3. Special Tools
Item
No.
Part No. Nomenclature Function
Vendor
(Table 4)
Ground Handling
ST101
369A9905
Ground handling wheels
(369D/E/FF can be used on
500N)
Ground handling of helicopter. TS21
BDW−500M Mechanical Ground Handling
Wheels (500N)
BDW−500H Hydraulic Ground Handling
Wheels (500N)
BDW−600M Mechanical Ground Handling
Wheels (600N)
BDW−MDH Hydraulic Ground Handling
Wheels (600N)
ST102 369H9801 Handle−jack assembly,
ground handling (straight)
(369D/E/FF − 500N)
Raising or lowering helicopter
with ground handling wheels.
ST103 369A9906 Handle−jack assembly,
ground handling (offset)
(369D/E/FF − 500N)
Raising or lowering helicopter
with ground handling wheels
when additional clearance is required.
ST104 369H90126 Ground handling wheels
(one side)
Ground handling of helicopter
equipped with utility or emergency floats.
ST105
HT−500 Tow bar (369D/E/FF, can be
used on 500N)
Towing of helicopter. TS21
HT−500P Tow bar (500N/600N)
Jacking and Leveling
ST201 369D29904
600N9904
Hoisting adapter (5−bladed)
(6−bladed)
Hoisting entire helicopter or removing main rotor.
ST202 369A2010−5 Jack fittings Jacking, leveling or tiedown of
helicopter.
ST203 02−0520−0100 Hydraulic jack: 1−5 ton
(900−4500 kg)
Jacking and leveling at Sta.
90.61.
ST204 02−0234−0100 Hydraulic jack: 80−inch
(203 cm) leg
Jacking and leveling at Sta.
197.78.
TS15
ST205 KS 5490 old
KS 5549 new
Inclinometer Angle of incidence tool, flight
control rigging.
TS9
ST206 36−D−2844 Prop protractor Measure angle of incident.
Main Transmission
ST301 369H9807 Main transmission drain hose Drain main transmission oil.
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 16
Revision 41
91−00−00
Table 3. Special Tools (Cont.)
Item
No.
Vendor
(Table 4)
FunctionNomenclaturePart No.
Engine
ST401
369A9948
369D28602−80903
−1
Engine stand
(250−C20B / 250−C20R/2)
(250−C30 / 250−C47)
Engine support and transport
dolly.
ST402 369A8009
369D29905
369DSK410
Engine hoist (250−C20B)
(250−C20R/2)
(250−C30 / 250−C47)
Engine removal and installation.
ST403
369H92537
369H92537−501
Engine compressor wash kit
(369D/E − 500N)
(369FF − 600N)
Clean engine compressor.
ST404 6798292 Wrench, ground idle adjust-
ing
Bendix fuel control idle speed adjustment.
ST405 369H9925 Rigging fixture, collective
stick
Gas producer rigging.
ST406 369A7368−80901 Alignment fixture Gas producer rigging.
ST407 MS17990−315 Rigging pin Gas producer rigging.
ST408 #1741145 Test tool Oil filter bypass indicator test. TS6
Flight Controls
ST501
369H9925
369H9925−3
Collective rigging fixture
(LH command)
(369D/E/FF − 500N)
(600N)
Rigging of main rotor collective
controls.
ST502 369A9927 Collective rigging fixture
(RH command)
Rigging of main rotor collective
controls.
ST503 369A9930 Mixer rigging plate Rigging of main rotor collective
and cyclic controls.
ST504
369D29929−9
600N9929−5
Longitudinal rigging fixture
(LH command)
(369D/E/FF − 500N)
(600N)
Rigging of main rotor cyclic controls.
ST505
369A9929−5
369D29929−5
Longitudinal rigging fixture
(RH command)
(369D/E/FF − 500N)
(600N)
Rigging of main rotor cyclic controls.
ST506
369A9928−9
369A9928−19
Lateral rigging fixture
(LH command)
(369D/E/FF − 500N)
(600N)
Rigging of main rotor cyclic controls.
ST507
369A9928−5 Lateral rigging fixture
(RH command)
Rigging of main rotor cyclic controls.
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
91−00−00
Page 17
Revision 41
Table 3. Special Tools (Cont.)
Item
No.
Vendor
(Table 4)
FunctionNomenclaturePart No.
ST508
369D29936
369A7300−ATP−1
Collective bungee installation
tool
(369D/E/FF − 500N)
(600N)
Remove bungee installation tool.
Dismantle bungee assembly.
ST509 Not used at this
time
ST510 369D29985 Bungee spring compression
tool rod and channel
(369D/E/FF − 500N)
Compress collective bungee.
ST511 369D29910−32501 Test fixture Shop aid for rigging main rotor
controls.
Anti−Torque
ST601 500N9901−3 Rigging pin
Rigging of NOTARR anti−torque
flight controls.
ST602 830006−809−00653 Spring tension removal tool Removal of anti−torque bungee
spring & splitter spring.
ST603 500N5365−1−ATP1 Tip seal cutter Anti−torque tip seal felt metal
cutting tool.
ST604 500N9505−1 Coupling socket Fan & gearbox coupling socket.
ST605 500N9506−1 Fan nut socket Anti−torque fan removal.
ST606
369D29931
369D29907
T/R swashplate rigging tool
(2−bladed tail rotor)
(4−bladed tail rotor)
Rig tail rotor controls.
ST607
369D29823
369D29826
Adapter, torque wrench
(2−bladed tail rotor)
(4−bladed tail rotor)
Install tail rotor nut.
ST608 369D29822−3 Pitch control assembly hold-
ing block
Secure tail rotor swashplate
block to remove/install nut.
ST609 369D29822−5 Adapter, torque wrench Remove/install tail rotor swash-
plate housing bearing nut.
ST610 369A1600−80902 Bushing wrench Install and torque tail rotor hub
threaded bushing.
ST611 83006−809−00090−1Arbor press fixture,
369A7951−5 bearing
Install tail rotor pitch control
link bearings.
ST612 83006−809−00090
−15
Staking tool, 369A7951−5
bearing
Stake tail rotor pitch control link
bearings.
ST613 269A9232 Plug, bearing removal Remove tail rotor pitch control
housing bearings.
ST614
500N5364−ATP1 Regreasing tool, fan bearing
Regreasing of the 500N5364
and 500N7120 fan bearings.
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 18
Revision 41
91−00−00
Table 3. Special Tools (Cont.)
Item
No.
Vendor
(Table 4)
FunctionNomenclaturePart No.
Main Rotor
ST701 369A9829 Main rotor wrench assembly Loosening/torquing of main rotor
mast nut.
ST702
369D29932
600N9932
Hub puller
(369D/E/FF − 500N)
(600N)
Separate main rotor hub from
mast.
ST703 369A9933
*369A9933−5
Main rotor hub driver Seat main rotor hub.
ST704 369D29957 old
FRDH101 new
Adapter, torque wrench Install main rotor drive shaft
fasteners.
ST705 369A9825 Pitch bearing stud wrench Remove main rotor hub pitch
bearing pivot pin.
ST706 83006−809−00090−1Arbor press fixture
(369A7951−5 bearing)
Install main rotor pitch housing
bearings.
ST707 83006−809−00090
−15
Staking tool
(369A7951−5 bearing)
Staking main rotor pitch housing
bearings.
ST708 83006−809−00088 Staking tool (pilot and punch)
(369A7951−45 bearing)
Install pitch control housing
bearings and swage rings.
ST709 3006−809−00090
−1/−8
Arbor press fixture
(369A7951−15 bearing)
Install main rotor blade bearings.
ST710 3006−809−00090
−15/−20
Staking tool (369A7951−15
bearing)
Stake main rotor blade bearings.
Fuel
ST801 MITYVACR #4000 Hand operated vacuum pump
kit
Pump down airframe and engine
fuel systems for vacuum leak
check.
TS13
ST801−1 AN840−D Nipple, hose Vacuum pump adaptive hard-
ware.
ST801−2 AN910−1D Coupling
ST801−3 AN816−4D Nipple
ST801−4 AS3084−04 O−ring
ST802 369A8100−80902 Spanner wrench Fuel cross−over fitting torquing.
Track and Balance
ST901 369D29942 Tip cap assembly Tracking main rotor blades.
ST902 369H9928 Main rotor blade fixture and
tab bending tool
Adjusting main rotor blade tab
angle/blade track.
ST903
Balancer/analyzer instrument
kit
Track and balance of dynamic
components.
TS5
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
91−00−00
Page 19
Revision 41
Table 3. Special Tools (Cont.)
Item
No.
Vendor
(Table 4)
FunctionNomenclaturePart No.
Electrical / Instruments / Avionics
ST1001 RXT20−5 (extract)
RTM20−9 (insert)
HYTIP insertion/extraction
tool.
Install/remove HYTIP electrical
contacts in terminal block modules.
TS4
ST1002 M8ND
N14HCT2
HYTOOL M8ND and
N14HCT
Crimp MINILOK and MODULOK terminal block contact tips
on electrical wire.
TS4
ST1003 107−0970 Hand operated crimping tool
(with positioners 107−0976
and 107−0977)
Crimp removable contacts in
rectangular connectors.
TS18
ST1004 107R1001
107−1015
Contact removal tool /
Contact insertion tool
Remove and insert removable
contacts in rectangular connectors.
TS18
ST1005 CEIT 20 Insertion/extraction tool (20
Wire Mate connector)
Connect/disconnect No. 20 Wire
Mate electrical connectors.
TS8
ST1006 CEIT 16 Insertion/extraction tool (16
Wire Mate connector)
Connect/disconnect No. 16 Wire
Mate electrical connectors.
TS8
ST1007 CTJ−RO6 Deutsche module removal
tool
Remove terminal block modules
from instrument panel terminal
block frames.
ST1008 46673 Crimping tool Thermocouple harness terminal
lugs.
TS1
ST1009 ^931 Voltmeter Measure voltage. TS17
ST1010 ^260−7 Volt−ohmmeter Measure resistance and voltage. TS14
ST1011 **2312−G−8 Turbine temperature indicat-
ing system test set
Test and calibrate TOT indicating system.
TS2
ST1012 **BH112JA−36 Jetcal tester Test and calibrate TOT indicat-
ing system.
TS7
ST1013 500N9701 Yaw S.A.S. test box Anti−Torque stability augmenta-
tion system control rigging.
TS10
ST1014 DPI 603 Pressure calibrator Test and calibrate torque indicat-
ing system (600N).
TS20
Miscellaneous
ST2001 369H4009 Pitot tube cover Pitot Tube protection.
ST2002 369H6661−1 Blade socks Main rotor blade tiedown.
ST2003 369D29913−37 Main rotor blade storage rack
(369D/E/FF − 500N)
Store main rotor blades. Blade
folding pole included.
ST2004 369H9803−503 Air inlet fairing cover Air inlet cover.
ST2005 369H9804−101 Engine exhaust cover Engine exhaust duct cover.
ST2006
51−C−887 Sleeve swage, oval C−type Particle separator installation. TS12
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 20
Revision 41
91−00−00
Table 3. Special Tools (Cont.)
Item
No.
Vendor
(Table 4)
FunctionNomenclaturePart No.
ST2007 C−6000 Rivnut installation speed
header
Particle separator installation. TS3
ST2008 C−3576 Rivnut keyway cutter Particle separator installation. TS3
ST2009 HG85−10 Inspection gauge Lockbolt installation inspection.
ST2010 369D29983 Adapter, torque wrench
(369D/E/FF)
Torque tailboom attachment
bolts.
ST2011 369A6001−50506−1Left landing gear foot drill jig Enlarge holes in lockbolt fas-
tened landing gear strut to
install machine−bolt−attached
skids.
ST2012 369A6001−50506−2Right landing gear foot drill
jig
Enlarge holes in lockbolt fastened landing gear strut to
install machine−bolt−attached
skids.
ST2013 WSI−HT−12AS Bushing installation tool
(WSI−B−12AS grommet)
Install tail rotor control rod
grommets.
TS16
ST2014
369D23601−80910 Angle measuring tool Check horizontal stabilizer angle
of incidence.
^ Primary selection. Any equivalent meter with an accuracy capable of measuring voltage within 0.25% full
scale range may be used.
* Hammer and handle same as 369A9933; −7 driver replaces −3 driver.
** Either tester may be used.
CSP−HMI−2MD Helicopters, Inc.
MAINTENANCE MANUAL
91−00−00
Page 21
Revision 41
Table 4. Tool Manufacturer/Supplier Number
Number Name
TS1
AMP Inc.
441 Friendship Rd.
Harrisgurg, PA 17111
Phone: (717) 564−0100
FAX: (717) 986−7575
TS2 Barfield Instrument Corporation
4101 NW 29th Street
P.O. Box 02567
Miami, FL 33102
TS3 B.F. Goodrich Co.
Aerospace Products
Akron, OH
TS4 Burndy Corp.
Norwalk, CT
TS5 Chadwich−Helmuth
4601 N. Arden Drive
El Monte, CA 91731−1299
TS6 Facet Enterprises Inc.
8439 Traid Dr.
Greensboro, NC 27409
TS7 Howell Instrument Inc.
TS8 I.T.T. Cannon Electric
3208 Humboldt St.
Los Angeles, CA 90031
TS9 Kell−Strom Tool Company
214 Church Street
Wethersfield, CT
TS10 MD Helicopters Inc.
5000 E. McDowell Road
Mesa, AZ 85215−9797
Number Name
TS11
MD Helicopters Inc.
Field Fabricated
TS12 National Telegraph Supply Co.
Cleveland, OH
TS13 Neward Enterprises Inc.
P.O. Box 725
Cucamonge, CA 91730
714−987−8975
TS14 Simpson
TS15 Tronair
South 1740 Eber Road
Holland, OH 43528
TS16 Western Sky Industries
21300 Cloud Way
Hayward, CA 94545
TS17 Weston
TS18 Winchester Electronics,
Division of Litton Industries
Main St. and Hillside Ave.
Oakville, CT 06779
TS19 Daniels Manufacturing Corp.
526 Thorpe Road
Orlando, FL 32824
Phone: (407) 855−6161
FAX: (407) 855−6884
TS20 Druck Incorporated
4 Dunham Drive
New Fairfield CT 06812
Phone: (203) 746−0400
FAX: (203) 746−2494
E−mail: druck.inc@druck.com
TS21 Brackett Aricraft Co., Inc.
7045 Flightline Dr. Kingman, AZ 86401
Phone: 928−757−4005
Fax: 928−757−1948
Sales inquiries: kfessenden@citlink.net
Technical inquiries: brackett@ctaz.com
CSP−HMI−2 MD Helicopters, Inc.
MAINTENANCE MANUAL
Page 22
Original
91−00−00
This Page Intentionally Left Blank
Loading...